From 3601eb92eec39706d25e02bdb5a4b5f30d840a1a Mon Sep 17 00:00:00 2001
From: Luc Maisonobe <luc@orekit.org>
Date: Mon, 10 Jan 2011 08:11:44 +0000
Subject: [PATCH] completely revamped partial derivatives computation in
numerical propagation added a way to perform numerical propagation in either
cartesian parameters or equinoctial parameters
---
.gitignore | 4 +
checkstyle.xml | 20 +-
findbugs-exclude-filter.xml | 31 +-
pom.xml | 28 +-
src/design/OrekitForces.png | Bin 0 -> 8678 bytes
src/design/OrekitVariableThrust.png | Bin 0 -> 11477 bytes
src/design/attitude-class-diagram.png | Bin 0 -> 33375 bytes
src/design/bodies-class-diagram.png | Bin 0 -> 12819 bytes
src/design/cartesian-class-diagram.png | Bin 0 -> 16939 bytes
src/design/data-class-diagram.png | Bin 0 -> 13104 bytes
src/design/frames-class-diagram.png | Bin 0 -> 25254 bytes
src/design/orbits-class-diagram.png | Bin 0 -> 23939 bytes
src/design/orekit-packages.png | Bin 0 -> 29050 bytes
.../partial-derivatives-class-diagram.png | Bin 0 -> 21022 bytes
src/design/propagation-class-diagram.png | Bin 0 -> 44744 bytes
src/design/sequence_diagram_propagation.png | Bin 0 -> 11621 bytes
src/design/time-class-diagram.png | Bin 0 -> 25568 bytes
src/design/tle-class-diagram.png | Bin 0 -> 7119 bytes
.../java/org/orekit/attitudes/LofOffset.java | 6 +-
.../orekit/bodies/AbstractCelestialBody.java | 14 +-
.../java/org/orekit/bodies/CelestialBody.java | 5 +
.../orekit/bodies/JPLEphemeridesLoader.java | 18 +-
.../org/orekit/bodies/OneAxisEllipsoid.java | 2 +-
.../org/orekit/errors/OrekitMessages.java | 10 +-
.../forces/AbstractParameterizable.java | 89 +++
.../forces/BoxAndSolarArraySpacecraft.java | 7 +
.../java/org/orekit/forces/ForceModel.java | 4 +-
.../forces/ForceModelWithJacobians.java | 47 --
.../org/orekit/forces/Parameterizable.java | 14 +-
.../orekit/forces/SphericalSpacecraft.java | 39 +-
.../org/orekit/forces/drag/DragForce.java | 27 +-
.../gravity/CunninghamAttractionModel.java | 20 +-
.../gravity/DrozinerAttractionModel.java | 20 +-
.../forces/gravity/NewtonianAttraction.java | 127 +++++
.../forces/gravity/ThirdBodyAttraction.java | 28 +-
.../gravity/potential/SHMFormatReader.java | 3 +-
.../maneuvers/ConstantThrustManeuver.java | 35 +-
src/main/java/org/orekit/forces/package.html | 5 +-
.../forces/radiation/RadiationSensitive.java | 9 +
.../radiation/SolarRadiationPressure.java | 126 +++--
src/main/java/org/orekit/frames/Frame.java | 2 +-
.../java/org/orekit/frames/FramesFactory.java | 2 +-
.../org/orekit/frames/SpacecraftFrame.java | 2 +-
.../java/org/orekit/frames/TIRF2000Frame.java | 2 +-
.../java/org/orekit/frames/VEISFrame.java | 2 +-
.../org/orekit/orbits/CartesianOrbit.java | 233 +++++++-
.../java/org/orekit/orbits/CircularOrbit.java | 108 +++-
.../org/orekit/orbits/EquinoctialOrbit.java | 89 ++-
.../org/orekit/orbits/KeplerianOrbit.java | 322 +++++++++--
src/main/java/org/orekit/orbits/Orbit.java | 75 +--
.../orekit/propagation/SpacecraftState.java | 4 +-
.../events/AdaptedEventDetector.java | 51 +-
.../orekit/propagation/events/EventState.java | 6 +-
.../events/GroundMaskElevationDetector.java | 16 +-
.../AccelerationJacobiansProvider.java | 51 ++
.../numerical/AdditionalEquations.java | 71 +++
.../AdditionalStateAndEquations.java | 82 +++
.../propagation/numerical/Jacobianizer.java | 282 ++++++++++
.../propagation/numerical/ModeHandler.java | 11 +-
.../numerical/NumericalPropagator.java | 374 +++++++++---
.../NumericalPropagatorWithJacobians.java | 530 ------------------
.../numerical/ParameterConfiguration.java | 77 +++
.../PartialDerivativesEquations.java | 454 +++++++++++++++
.../propagation/numerical/StateMapper.java | 59 ++
.../numerical/StateMapperCartesian.java | 87 +++
.../numerical/StateMapperEquinoctial.java | 74 +++
.../numerical/TimeDerivativesEquations.java | 294 +---------
.../TimeDerivativesEquationsCartesian.java | 114 ++++
.../TimeDerivativesEquationsEquinoctial.java | 280 +++++++++
...TimeDerivativesEquationsWithJacobians.java | 90 ---
.../java/org/orekit/propagation/package.html | 4 -
.../precomputed/IntegratedEphemeris.java | 52 +-
.../sampling/AdaptedStepHandler.java | 64 ++-
.../sampling/BasicStepInterpolator.java | 9 +
.../sampling/OrekitStepInterpolator.java | 10 +
.../localization/OrekitMessages_de.properties | 24 +
.../localization/OrekitMessages_en.properties | 24 +
.../localization/OrekitMessages_es.properties | 24 +
.../localization/OrekitMessages_fr.properties | 24 +
.../localization/OrekitMessages_gl.properties | 24 +
.../localization/OrekitMessages_it.properties | 24 +
.../localization/OrekitMessages_no.properties | 24 +
src/site/xdoc/changes.xml | 27 +
.../attitudes/LofOffsetPointingTest.java | 2 +-
.../org/orekit/attitudes/LofOffsetTest.java | 2 +-
.../org/orekit/errors/OrekitMessagesTest.java | 2 +-
.../java/org/orekit/frames/FrameTest.java | 4 +-
.../TODFrameAlternateConfigurationTest.java | 4 +-
.../java/org/orekit/frames/TODFrameTest.java | 2 +-
.../orbits/CartesianParametersTest.java | 76 +++
.../orbits/KeplerianParametersTest.java | 67 ++-
.../propagation/SpacecraftStateTest.java | 5 +-
.../EcksteinHechlerPropagatorTest.java | 2 +-
.../propagation/events/DetectorTest.java | 2 +
.../numerical/NumericalPropagatorTest.java | 96 +++-
.../NumericalPropagatorWithJacobiansTest.java | 347 ------------
.../IntegratedEphemerisTest.java | 3 +-
.../org/orekit/time/AbsoluteDateTest.java | 2 +-
98 files changed, 3772 insertions(+), 1760 deletions(-)
create mode 100644 .gitignore
create mode 100644 src/design/OrekitForces.png
create mode 100644 src/design/OrekitVariableThrust.png
create mode 100644 src/design/attitude-class-diagram.png
create mode 100644 src/design/bodies-class-diagram.png
create mode 100644 src/design/cartesian-class-diagram.png
create mode 100644 src/design/data-class-diagram.png
create mode 100644 src/design/frames-class-diagram.png
create mode 100644 src/design/orbits-class-diagram.png
create mode 100644 src/design/orekit-packages.png
create mode 100644 src/design/partial-derivatives-class-diagram.png
create mode 100644 src/design/propagation-class-diagram.png
create mode 100644 src/design/sequence_diagram_propagation.png
create mode 100644 src/design/time-class-diagram.png
create mode 100644 src/design/tle-class-diagram.png
create mode 100644 src/main/java/org/orekit/forces/AbstractParameterizable.java
delete mode 100644 src/main/java/org/orekit/forces/ForceModelWithJacobians.java
create mode 100644 src/main/java/org/orekit/forces/gravity/NewtonianAttraction.java
create mode 100644 src/main/java/org/orekit/propagation/numerical/AccelerationJacobiansProvider.java
create mode 100644 src/main/java/org/orekit/propagation/numerical/AdditionalEquations.java
create mode 100644 src/main/java/org/orekit/propagation/numerical/AdditionalStateAndEquations.java
create mode 100644 src/main/java/org/orekit/propagation/numerical/Jacobianizer.java
delete mode 100644 src/main/java/org/orekit/propagation/numerical/NumericalPropagatorWithJacobians.java
create mode 100644 src/main/java/org/orekit/propagation/numerical/ParameterConfiguration.java
create mode 100644 src/main/java/org/orekit/propagation/numerical/PartialDerivativesEquations.java
create mode 100644 src/main/java/org/orekit/propagation/numerical/StateMapper.java
create mode 100644 src/main/java/org/orekit/propagation/numerical/StateMapperCartesian.java
create mode 100644 src/main/java/org/orekit/propagation/numerical/StateMapperEquinoctial.java
create mode 100644 src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquationsCartesian.java
create mode 100644 src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquationsEquinoctial.java
delete mode 100644 src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquationsWithJacobians.java
delete mode 100644 src/test/java/org/orekit/propagation/numerical/NumericalPropagatorWithJacobiansTest.java
rename src/test/java/org/orekit/propagation/{numerical => precomputed}/IntegratedEphemerisTest.java (97%)
diff --git a/.gitignore b/.gitignore
new file mode 100644
index 0000000000..1b74f44447
--- /dev/null
+++ b/.gitignore
@@ -0,0 +1,4 @@
+.classpath
+.project
+bin
+
diff --git a/checkstyle.xml b/checkstyle.xml
index 3903d294b9..2e039e229e 100644
--- a/checkstyle.xml
+++ b/checkstyle.xml
@@ -11,16 +11,15 @@
<module name="FallThrough"/>
<module name="FinalLocalVariable"/>
<module name="FinalParameters"/>
- <module name="GenericIllegalRegexp">
- <property name="format" value="\s$"/>
- <property name="message" value="spurious spaces at end of line"/>
+ <module name="Regexp">
+ <property name="format" value="[ \t]+$"/>
+ <property name="illegalPattern" value="true"/>
+ <property name="message" value="Trailing whitespace"/>
</module>
- <module name="GenericIllegalRegexp">
+ <module name="Regexp">
<property name="format" value="System\.out\.println"/>
- <property name="message" value="forbidden print to standard output"/>
- </module>
- <module name="RegexpHeader">
- <property name="headerFile" value="license-header.txt" />
+ <property name="illegalPattern" value="true"/>
+ <property name="ignoreComments" value="true"/>
</module>
<module name="HiddenField">
<property name="ignoreConstructorParameter" value="true"/>
@@ -55,7 +54,6 @@
</module>
<module name="RedundantModifier"/>
<module name="StringLiteralEquality"/>
- <module name="TabCharacter"/>
<module name="TodoComment"/>
<module name="UnnecessaryParentheses"/>
<module name="UnusedImports"/>
@@ -74,6 +72,10 @@
</module>
<module name="FileContentsHolder"/>
</module>
+ <module name="RegexpHeader">
+ <property name="headerFile" value="license-header.txt" />
+ </module>
+ <module name="FileTabCharacter"/>
<module name="NewlineAtEndOfFile"/>
<module name="SuppressionCommentFilter">
<property name="offCommentFormat" value="CHECKSTYLE\: stop JavadocVariable check"/>
diff --git a/findbugs-exclude-filter.xml b/findbugs-exclude-filter.xml
index 249f7a91c6..7ae26a4e0b 100644
--- a/findbugs-exclude-filter.xml
+++ b/findbugs-exclude-filter.xml
@@ -63,11 +63,40 @@
<Bug pattern="DLS_DEAD_LOCAL_STORE" />
</Match>
- <!-- The following equality test is intentional and needed for semantic purposes -->
+ <!-- The following equality tests are intentional and needed for semantic purposes -->
<Match>
<Class name="org.orekit.time.TimeComponents" />
<Method name="equals" params="java.lang.Object" returns="boolean" />
<Bug pattern="FE_FLOATING_POINT_EQUALITY" />
</Match>
+ <Match>
+ <Class name="org.orekit.orbits.KeplerianOrbit"/>
+ <Method name ="eMeSinE" params="double" returns="double" />
+ <Bug pattern="FE_FLOATING_POINT_EQUALITY" />
+ </Match>
+
+ <!-- The following internal representation exposure are intentional,
+ They are used to pass data back and forth between classes
+ -->
+ <Match>
+ <Class name="org.orekit.propagation.numerical.AdditionalStateAndEquations"/>
+ <Method name ="getAdditionalState" params="" returns="double[]" />
+ <Bug pattern="EI_EXPOSE_REP" />
+ </Match>
+ <Match>
+ <Class name="org.orekit.propagation.numerical.AdditionalStateAndEquations"/>
+ <Method name ="getAdditionalStateDot" params="" returns="double[]" />
+ <Bug pattern="EI_EXPOSE_REP" />
+ </Match>
+ <Match>
+ <Class name="org.orekit.propagation.numerical.TimeDerivativesEquationsCartesian"/>
+ <Method name ="initDerivatives" params="double[],org.orekit.orbits.Orbit" returns="void" />
+ <Bug pattern="EI_EXPOSE_REP2" />
+ </Match>
+ <Match>
+ <Class name="org.orekit.propagation.numerical.TimeDerivativesEquationsEquinoctial"/>
+ <Method name ="initDerivatives" params="double[],org.orekit.orbits.Orbit" returns="void" />
+ <Bug pattern="EI_EXPOSE_REP2" />
+ </Match>
</FindBugsFilter>
diff --git a/pom.xml b/pom.xml
index 82b34be574..48600ae829 100644
--- a/pom.xml
+++ b/pom.xml
@@ -133,7 +133,7 @@
<dependency>
<groupId>junit</groupId>
<artifactId>junit</artifactId>
- <version>4.4</version>
+ <version>4.8.1</version>
<type>jar</type>
<scope>test</scope>
<optional>false</optional>
@@ -144,7 +144,7 @@
<plugins>
<plugin>
<artifactId>maven-assembly-plugin</artifactId>
- <version>2.2-beta-4</version>
+ <version>2.2-beta-5</version>
<configuration>
<descriptors>
<descriptor>src/main/assembly/source-assembly.xml</descriptor>
@@ -155,7 +155,7 @@
<plugin>
<groupId>org.apache.felix</groupId>
<artifactId>maven-bundle-plugin</artifactId>
- <version>2.0.1</version>
+ <version>2.1.0</version>
<extensions>true</extensions>
<configuration>
<instructions>
@@ -181,7 +181,7 @@
<plugin>
<groupId>org.apache.maven.plugins</groupId>
<artifactId>maven-compiler-plugin</artifactId>
- <version>2.0.2</version>
+ <version>2.3.1</version>
<configuration>
<source>1.5</source>
<target>1.5</target>
@@ -190,7 +190,7 @@
</plugin>
<plugin>
<artifactId>maven-site-plugin</artifactId>
- <version>2.0.1</version>
+ <version>2.1.1</version>
<configuration>
<inputEncoding>UTF-8</inputEncoding>
<outputEncoding>UTF-8</outputEncoding>
@@ -199,12 +199,12 @@
<plugin>
<groupId>org.codehaus.mojo</groupId>
<artifactId>cobertura-maven-plugin</artifactId>
- <version>2.3</version>
+ <version>2.4</version>
</plugin>
<plugin>
<groupId>org.codehaus.mojo</groupId>
<artifactId>findbugs-maven-plugin</artifactId>
- <version>2.1</version>
+ <version>2.3.1</version>
<configuration>
<threshold>Normal</threshold>
<effort>Default</effort>
@@ -214,22 +214,22 @@
<plugin>
<groupId>org.apache.maven.plugins</groupId>
<artifactId>maven-surefire-plugin</artifactId>
- <version>2.4.3</version>
+ <version>2.5</version>
</plugin>
<plugin>
<groupId>org.apache.maven.plugins</groupId>
<artifactId>maven-checkstyle-plugin</artifactId>
- <version>2.3</version>
+ <version>2.5</version>
<configuration>
<encoding>UTF-8</encoding>
- <configLocation>checkstyle.xml</configLocation>
+ <configLocation>${basedir}/checkstyle.xml</configLocation>
<enableRulesSummary>false</enableRulesSummary>
</configuration>
</plugin>
<plugin>
<groupId>org.apache.maven.plugins</groupId>
<artifactId>maven-changes-plugin</artifactId>
- <version>2.1</version>
+ <version>2.3</version>
<configuration>
<xmlPath>${basedir}/src/site/xdoc/changes.xml</xmlPath>
</configuration>
@@ -244,7 +244,7 @@
<plugin>
<groupId>org.apache.maven.plugins</groupId>
<artifactId>maven-jxr-plugin</artifactId>
- <version>2.1</version>
+ <version>2.2</version>
<configuration>
<outputEncoding>UTF-8</outputEncoding>
<linkJavadoc>false</linkJavadoc>
@@ -253,7 +253,7 @@
<plugin>
<groupId>org.apache.maven.plugins</groupId>
<artifactId>maven-javadoc-plugin</artifactId>
- <version>2.6</version>
+ <version>2.7</version>
<configuration>
<overview>${basedir}/src/main/java/org/orekit/overview.html</overview>
<links>
@@ -283,7 +283,7 @@
<plugin>
<groupId>org.apache.maven.plugins</groupId>
<artifactId>maven-source-plugin</artifactId>
- <version>2.1</version>
+ <version>2.1.2</version>
<executions>
<execution>
<id>create-source-jar</id>
diff --git a/src/design/OrekitForces.png b/src/design/OrekitForces.png
new file mode 100644
index 0000000000000000000000000000000000000000..c51a7e9b3eb634e7ae520778cd9679bf1e5e19c1
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z20C8vnL^i7Tr!Jf9q+?0Rz)OZG@X6JYK*{#Oy)pE5vnaua64#HGUKh5^ckb)dBG<K
zb8>kiD$PH=RLfK_0ngt*{eFP<E*Gv_Bg~=_o4;;fgXyr#a;Xh0dX@o<sS$;3CfkuA
z{6yEYUl{{>?CgR)6SML2b3+{s5U&wV(LLPSw6=pYg}I$Qjil22r_^{FFru}-1g2ol
z%4PO`(CHf^?-^<ArLMfz`3jtXT7mdTNrob?i0lr>lt0X>VL2OlCIQ3j^JXH_DN5@A
zh1Ji_<pFT%#l%vz8-=-(!v3h=tJAEZ*(OPoh*{@+<kBkt6taKyR1#{+c4)k4Ur#t~
zS=z^}cy`)T@ys`i8kldPl9MgLb!z#8^NYs;(>4N)x8U^UA=*UU7*sZO7g{(dm$lM0
zT5L!}(PQYH&PF-pq_RmKjIg?7UKkPvG0RyhI^d>tVD5<m(>t&@`;D{h$tz*YXEN0Y
z75=S_0Tv6qA`SZ8hfveS1>4HAbh7_`dkyzKHV~sOGgJMarrKes%@OD8$sFDPOn21q
zQ<H5h`r?dD|6b~hFd)$|N>-mqZfpKd+^s<d`Pl2Pgw$lzc@NQ=xe%-<Socro{NIaj
zejm)`^TJI`oPBQUcU=F85Gos<ajwCJDQB8hRnagI?MI*b-6TT2P`iJ9LRvJ$=Ut84
zBWx56ZLOTSm~QXj%U16!&CG5j@p|jdH&83*r#!jod;ZP>{}n;3m7LXyquqYom6E~M
z0LsLsLB=O4w)jNVzdRv#L_So~590d!rE0excNKXBX-{zOcvD&}z@bdA|855EYa;Vq
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zeacQW1&#!gP5P9=nGm3;SK&ZqZ{(#58cR_ntZo*rc)TA7&prgG#~-4t+pk#n0Z3qe
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literal 0
HcmV?d00001
diff --git a/src/main/java/org/orekit/attitudes/LofOffset.java b/src/main/java/org/orekit/attitudes/LofOffset.java
index f7a511a11b..03ca560ea4 100644
--- a/src/main/java/org/orekit/attitudes/LofOffset.java
+++ b/src/main/java/org/orekit/attitudes/LofOffset.java
@@ -75,9 +75,9 @@ public class LofOffset implements AttitudeLaw {
* // note the call to revert in the following statement
* double[] angles = offsetProper.revert().getAngles(order);
*
- * System.out.println(alpha1 + " == " + angles[0]);
- * System.out.println(alpha2 + " == " + angles[1]);
- * System.out.println(alpha3 + " == " + angles[2]);
+ * System.out.println(alpha1 + " == " + angles[0]);
+ * System.out.println(alpha2 + " == " + angles[1]);
+ * System.out.println(alpha3 + " == " + angles[2]);
* </pre>
* @param order order of rotations to use for (alpha1, alpha2, alpha3) composition
* @param alpha1 angle of the first elementary rotation
diff --git a/src/main/java/org/orekit/bodies/AbstractCelestialBody.java b/src/main/java/org/orekit/bodies/AbstractCelestialBody.java
index b1f1936617..6b31d11bc3 100644
--- a/src/main/java/org/orekit/bodies/AbstractCelestialBody.java
+++ b/src/main/java/org/orekit/bodies/AbstractCelestialBody.java
@@ -44,6 +44,9 @@ public abstract class AbstractCelestialBody implements CelestialBody {
/** Serializable UID. */
private static final long serialVersionUID = 6769512376971866660L;
+ /** Name of the body. */
+ private final String name;
+
/** Attraction coefficient of the body (m<sup>3</sup>/s<sup>2</sup>). */
private final double gm;
@@ -60,15 +63,17 @@ public abstract class AbstractCelestialBody implements CelestialBody {
private final Frame bodyFrame;
/** Build an instance and the underlying frame.
+ * @param name name of the body
* @param gm attraction coefficient (in m<sup>3</sup>/s<sup>2</sup>)
* @param iauPole IAU pole implementation
* @param definingFrame frame in which celestial body coordinates are defined
* @param inertialFrameName name to use for inertially oriented body centered frame
* @param bodyFrameName name to use for body oriented body centered frame
*/
- protected AbstractCelestialBody(final double gm, final IAUPole iauPole,
- final Frame definingFrame,
+ protected AbstractCelestialBody(final String name, final double gm,
+ final IAUPole iauPole, final Frame definingFrame,
final String inertialFrameName, String bodyFrameName) {
+ this.name = name;
this.gm = gm;
this.iauPole = iauPole;
this.definingFrame = definingFrame;
@@ -76,6 +81,11 @@ public abstract class AbstractCelestialBody implements CelestialBody {
this.bodyFrame = new BodyOrientedFrame(bodyFrameName);
}
+ /** {@inheritDoc} */
+ public String getName() {
+ return name;
+ }
+
/** {@inheritDoc} */
public double getGM() {
return gm;
diff --git a/src/main/java/org/orekit/bodies/CelestialBody.java b/src/main/java/org/orekit/bodies/CelestialBody.java
index 48cc229c85..a06fade659 100644
--- a/src/main/java/org/orekit/bodies/CelestialBody.java
+++ b/src/main/java/org/orekit/bodies/CelestialBody.java
@@ -57,6 +57,11 @@ public interface CelestialBody extends Serializable, PVCoordinatesProvider {
*/
Frame getBodyOrientedFrame() throws OrekitException;
+ /** Get the name of the body.
+ * @return name of the body
+ */
+ String getName();
+
/** Get the attraction coefficient of the body.
* @return attraction coefficient of the body (m<sup>3</sup>/s<sup>2</sup>)
*/
diff --git a/src/main/java/org/orekit/bodies/JPLEphemeridesLoader.java b/src/main/java/org/orekit/bodies/JPLEphemeridesLoader.java
index 6a181ae903..6c48873dd2 100644
--- a/src/main/java/org/orekit/bodies/JPLEphemeridesLoader.java
+++ b/src/main/java/org/orekit/bodies/JPLEphemeridesLoader.java
@@ -207,7 +207,7 @@ public class JPLEphemeridesLoader implements CelestialBodyLoader {
switch (generateType) {
case SOLAR_SYSTEM_BARYCENTER :
- return new JPLCelestialBody(supportedNames, gm, IAUPoleFactory.getIAUPole(generateType),
+ return new JPLCelestialBody(supportedNames, name, gm, IAUPoleFactory.getIAUPole(generateType),
CelestialBodyFactory.getEarthMoonBarycenter().getInertiallyOrientedFrame(),
inertialFrameName, bodyFrameName) {
@@ -226,7 +226,7 @@ public class JPLEphemeridesLoader implements CelestialBodyLoader {
};
case EARTH_MOON :
final double scale = 1.0 / (1.0 + getLoadedEarthMoonMassRatio());
- return new JPLCelestialBody(supportedNames, gm, IAUPoleFactory.getIAUPole(generateType),
+ return new JPLCelestialBody(supportedNames, name, gm, IAUPoleFactory.getIAUPole(generateType),
FramesFactory.getEME2000(), inertialFrameName, bodyFrameName) {
/** Serializable UID. */
@@ -272,6 +272,11 @@ public class JPLEphemeridesLoader implements CelestialBodyLoader {
return FramesFactory.getITRF2005();
}
+ /** {@inheritDoc} */
+ public String getName() {
+ return name;
+ }
+
/** {@inheritDoc} */
public double getGM() {
return gm;
@@ -279,10 +284,10 @@ public class JPLEphemeridesLoader implements CelestialBodyLoader {
};
case MOON :
- return new JPLCelestialBody(supportedNames, gm, IAUPoleFactory.getIAUPole(generateType),
+ return new JPLCelestialBody(supportedNames, name, gm, IAUPoleFactory.getIAUPole(generateType),
FramesFactory.getEME2000(), inertialFrameName, bodyFrameName);
default :
- return new JPLCelestialBody(supportedNames, gm, IAUPoleFactory.getIAUPole(generateType),
+ return new JPLCelestialBody(supportedNames, name, gm, IAUPoleFactory.getIAUPole(generateType),
CelestialBodyFactory.getSolarSystemBarycenter().getInertiallyOrientedFrame(),
inertialFrameName, bodyFrameName);
}
@@ -899,16 +904,17 @@ public class JPLEphemeridesLoader implements CelestialBodyLoader {
/** Private constructor for the singletons.
* @param supportedNames regular expression for supported files names (may be null)
+ * @param name name of the body
* @param gm attraction coefficient (in m<sup>3</sup>/s<sup>2</sup>)
* @param iauPole IAU pole implementation
* @param definingFrame frame in which ephemeris are defined
* @param inertialFrameName name to use for inertially oriented body centered frame
* @param bodyFrameName name to use for body oriented body centered frame
*/
- private JPLCelestialBody(final String supportedNames, final double gm,
+ private JPLCelestialBody(final String supportedNames, final String name, final double gm,
final IAUPole iauPole, final Frame definingFrame,
final String inertialFrameName, String bodyFrameName) {
- super(gm, iauPole, definingFrame, inertialFrameName, bodyFrameName);
+ super(name, gm, iauPole, definingFrame, inertialFrameName, bodyFrameName);
this.model = null;
this.definingFrame = definingFrame;
}
diff --git a/src/main/java/org/orekit/bodies/OneAxisEllipsoid.java b/src/main/java/org/orekit/bodies/OneAxisEllipsoid.java
index 62bdbc4aff..a93266c51f 100644
--- a/src/main/java/org/orekit/bodies/OneAxisEllipsoid.java
+++ b/src/main/java/org/orekit/bodies/OneAxisEllipsoid.java
@@ -77,7 +77,7 @@ public class OneAxisEllipsoid implements BodyShape {
/** Simple constructor.
* <p>The following table provides conventional parameters for global Earth models:</p>
* <table border="1" cellpadding="5">
- * <tr bgcolor="#ccccff"><font size="+3"><th>model</th><th>a<sub>e</sub> (m)</th><th>f</th></font></tr>
+ * <tr bgcolor="#ccccff"><th>model</th><th>a<sub>e</sub> (m)</th><th>f</th></tr>
* <tr><td bgcolor="#eeeeff">GRS 80</td><td>6378137.0</td><td>1.0 / 298.257222101</td></tr>
* <tr><td bgcolor="#eeeeff">WGS84</td><td>6378137.0</td><td>1.0 / 298.257223563</td></tr>
* </table>
diff --git a/src/main/java/org/orekit/errors/OrekitMessages.java b/src/main/java/org/orekit/errors/OrekitMessages.java
index f72a99bdd2..389193c542 100644
--- a/src/main/java/org/orekit/errors/OrekitMessages.java
+++ b/src/main/java/org/orekit/errors/OrekitMessages.java
@@ -54,7 +54,7 @@ public enum OrekitMessages implements Localizable {
FRAME_ANCESTOR_OF_BOTH_FRAMES("frame {0} is an ancestor of both frames {1} and {2}"),
FRAME_ANCESTOR_OF_NEITHER_FRAME("frame {0} is an ancestor of neither frame {1} nor {2}"),
UNSUPPORTED_LOCAL_ORBITAL_FRAME("unsupported local orbital frame, supported types: {0} and {1}"),
- NON_QUASI_INERTIAL_FRAME_NOT_SUITABLE_FOR_DEFINING_ORBITS("non quasi-inertial frame \"{0}\" is not suitable for defining orbits"),
+ NON_PSEUDO_INERTIAL_FRAME_NOT_SUITABLE_FOR_DEFINING_ORBITS("non pseudo-inertial frame \"{0}\" is not suitable for defining orbits"),
DATA_ROOT_DIRECTORY_DOESN_NOT_EXISTS("data root directory {0} does not exist"),
NOT_A_DIRECTORY("{0} is not a directory"),
NEITHER_DIRECTORY_NOR_ZIP_OR_JAR("{0} is neither a directory nor a zip/jar archive file"),
@@ -117,6 +117,14 @@ public enum OrekitMessages implements Localizable {
OUT_OF_RANGE_EPHEMERIDES_DATE("out of range date for ephemerides: {0}, [{1}, {2}]"),
UNEXPECTED_TWO_ELEVATION_VALUES_FOR_ONE_AZIMUTH("unexpected two elevation values: {0} and {1}, for one azimuth: {2}"),
UNKNOWN_PARAMETER("unknown parameter {0}"),
+ UNSUPPORTED_PARAMETER_1_2("unsupported parameter name {0}: supported names {1}, {2}"),
+ UNKNOWN_ADDITIONAL_EQUATION("unknown additional equation"),
+ PARTIAL_DERIVATIVES_ONLY_IN_CARTESIAN("partial derivatives can be propagated only in cartesian parameters type"),
+ STATE_JACOBIAN_NEITHER_6X6_NOR_7X7("state jacobian is a {0}x{1} matrix, it should be either a 6x6 or a 7x7 matrix"),
+ STATE_AND_PARAMETERS_JACOBIANS_ROWS_MISMATCH("state jacobian has {0} rows but parameters jacobian has {1} rows"),
+ INITIAL_MATRIX_AND_PARAMETERS_NUMBER_MISMATCH("initial jacobian matrix has {0} columns, but {1} parameters have been selected"),
+ ORBIT_A_E_MISMATCH_WITH_CONIC_TYPE("orbit should be either elliptic with a > 0 and e < 1 or hyperbolic with a < 0 and e > 1, a = {0}, e = {1}"),
+ HYPERBOLIC_ORBIT_NOT_HANDLED_AS("hyperbolic orbits cannot be handled as {0} instances"),
CCSDS_DATE_INVALID_PREAMBLE_FIELD("invalid preamble field in CCSDS date: {0}"),
CCSDS_DATE_INVALID_LENGTH_TIME_FIELD("invalid time field length in CCSDS date: {0}, expected {1}"),
CCSDS_DATE_MISSING_AGENCY_EPOCH("missing agency epoch in CCSDS date"),
diff --git a/src/main/java/org/orekit/forces/AbstractParameterizable.java b/src/main/java/org/orekit/forces/AbstractParameterizable.java
new file mode 100644
index 0000000000..159fb4cc7d
--- /dev/null
+++ b/src/main/java/org/orekit/forces/AbstractParameterizable.java
@@ -0,0 +1,89 @@
+/* Copyright 2010 Centre National d'Études Spatiales
+ * Licensed to CS Communication & Systèmes (CS) under one or more
+ * contributor license agreements. See the NOTICE file distributed with
+ * this work for additional information regarding copyright ownership.
+ * CS licenses this file to You under the Apache License, Version 2.0
+ * (the "License"); you may not use this file except in compliance with
+ * the License. You may obtain a copy of the License at
+ *
+ * http://www.apache.org/licenses/LICENSE-2.0
+ *
+ * Unless required by applicable law or agreed to in writing, software
+ * distributed under the License is distributed on an "AS IS" BASIS,
+ * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
+ * See the License for the specific language governing permissions and
+ * limitations under the License.
+ */
+package org.orekit.forces;
+
+import java.util.ArrayList;
+import java.util.Collection;
+
+import org.orekit.errors.OrekitException;
+import org.orekit.errors.OrekitMessages;
+
+/** Simple abstract class providing boilerplate parameters list.
+ *
+ * @author Luc Maisonobe
+ * @version $Revision$ $Date$
+ */
+
+public abstract class AbstractParameterizable implements Parameterizable {
+
+ /** Serializable UID. */
+ private static final long serialVersionUID = 3408804493769459294L;
+
+ /** List of the parameters names. */
+ private final Collection<String> parametersNames;
+
+ /** Simple constructor.
+ * @param names names of the supported parameters
+ */
+ protected AbstractParameterizable(final String ... names) {
+ parametersNames = new ArrayList<String>();
+ for (final String name : names) {
+ parametersNames.add(name);
+ }
+ }
+
+ /** Simple constructor.
+ * @param names names of the supported parameters
+ */
+ protected AbstractParameterizable(final Collection<String> names) {
+ parametersNames = new ArrayList<String>();
+ parametersNames.addAll(names);
+ }
+
+ /** {@inheritDoc} */
+ public Collection<String> getParametersNames() {
+ return parametersNames;
+ }
+
+ /** {@inheritDoc} */
+ public boolean isSupported(final String name) {
+ for (final String supportedName : parametersNames) {
+ if (supportedName.equals(name)) {
+ return true;
+ }
+ }
+ return false;
+ }
+
+ /** Check if a parameter is supported and throw an IllegalArgumentException if not.
+ * @param name name of the parameter to check
+ * @exception IllegalArgumentException if the parameter is not supported
+ * @see #isSupported(String)
+ */
+ public void complainIfNotSupported(final String name) throws IllegalArgumentException {
+ if (!isSupported(name)) {
+ throw OrekitException.createIllegalArgumentException(OrekitMessages.UNKNOWN_PARAMETER, name);
+ }
+ }
+
+ /** {@inheritDoc} */
+ public abstract double getParameter(String name) throws IllegalArgumentException;
+
+ /** {@inheritDoc} */
+ public abstract void setParameter(String name, double value) throws IllegalArgumentException;
+
+}
diff --git a/src/main/java/org/orekit/forces/BoxAndSolarArraySpacecraft.java b/src/main/java/org/orekit/forces/BoxAndSolarArraySpacecraft.java
index 55d4a950da..2841c70c1b 100644
--- a/src/main/java/org/orekit/forces/BoxAndSolarArraySpacecraft.java
+++ b/src/main/java/org/orekit/forces/BoxAndSolarArraySpacecraft.java
@@ -490,4 +490,11 @@ public class BoxAndSolarArraySpacecraft implements RadiationSensitive, DragSensi
return dragCoeff;
}
+ /** {@inheritDoc} */
+ public void addDAccDParam(final Vector3D acceleration, final String paramName, final double[] dAccdParam)
+ throws OrekitException {
+ // TODO: not supported yet
+ throw OrekitException.createInternalError(null);
+ }
+
}
diff --git a/src/main/java/org/orekit/forces/ForceModel.java b/src/main/java/org/orekit/forces/ForceModel.java
index f972e2ef4f..e3d95fb975 100644
--- a/src/main/java/org/orekit/forces/ForceModel.java
+++ b/src/main/java/org/orekit/forces/ForceModel.java
@@ -16,8 +16,6 @@
*/
package org.orekit.forces;
-import java.io.Serializable;
-
import org.orekit.errors.OrekitException;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.events.EventDetector;
@@ -53,7 +51,7 @@ import org.orekit.propagation.numerical.TimeDerivativesEquations;
* @author Véronique Pommier-Maurussane
* @version $Revision$ $Date$
*/
-public interface ForceModel extends Serializable {
+public interface ForceModel extends Parameterizable {
/** Compute the contribution of the force model to the perturbing
* acceleration.
diff --git a/src/main/java/org/orekit/forces/ForceModelWithJacobians.java b/src/main/java/org/orekit/forces/ForceModelWithJacobians.java
deleted file mode 100644
index 6a581ffd51..0000000000
--- a/src/main/java/org/orekit/forces/ForceModelWithJacobians.java
+++ /dev/null
@@ -1,47 +0,0 @@
-/* Copyright 2002-2010 CS Communication & Systèmes
- * Licensed to CS Communication & Systèmes (CS) under one or more
- * contributor license agreements. See the NOTICE file distributed with
- * this work for additional information regarding copyright ownership.
- * CS licenses this file to You under the Apache License, Version 2.0
- * (the "License"); you may not use this file except in compliance with
- * the License. You may obtain a copy of the License at
- *
- * http://www.apache.org/licenses/LICENSE-2.0
- *
- * Unless required by applicable law or agreed to in writing, software
- * distributed under the License is distributed on an "AS IS" BASIS,
- * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
- * See the License for the specific language governing permissions and
- * limitations under the License.
- */
-package org.orekit.forces;
-
-import org.orekit.errors.OrekitException;
-import org.orekit.propagation.SpacecraftState;
-import org.orekit.propagation.numerical.TimeDerivativesEquationsWithJacobians;
-
-/** This interface represents a parameterized force modifying spacecraft motion.
- *
- * <p> Objects implementing this interface are intended to be added, before the propagation is started,
- * to a {@link org.orekit.propagation.numerical.NumericalPropagatorWithJacobians numerical propagator}
- * in order to compute partial derivatives of orbital parameters with respect to the
- * {@link org.orekit.propagation.numerical.NumericalPropagatorWithJacobians#selectParameters(String[]) selected}
- * force model parameters.</p>
- *
- * @see ForceModel
- *
- * @author Pascal Parraud
- * @version $Revision$ $Date$
- */
-public interface ForceModelWithJacobians extends Parameterizable, ForceModel {
-
- /** Compute the contribution of the force model to the perturbing
- * acceleration and to the jacobians.
- * @param s current state information: date, kinematics, attitude
- * @param adder object where the contribution should be added
- * @exception OrekitException if some specific error occurs
- */
- void addContributionWithJacobians(SpacecraftState s, TimeDerivativesEquationsWithJacobians adder)
- throws OrekitException;
-
-}
diff --git a/src/main/java/org/orekit/forces/Parameterizable.java b/src/main/java/org/orekit/forces/Parameterizable.java
index 7fec1641c9..35eccb5463 100644
--- a/src/main/java/org/orekit/forces/Parameterizable.java
+++ b/src/main/java/org/orekit/forces/Parameterizable.java
@@ -16,6 +16,7 @@
*/
package org.orekit.forces;
+import java.io.Serializable;
import java.util.Collection;
/** This interface enables to process partial derivatives
@@ -25,13 +26,24 @@ import java.util.Collection;
* @version $Revision$ $Date$
*/
-public interface Parameterizable {
+public interface Parameterizable extends Serializable {
/** Get the names of the supported parameters for partial derivatives processing.
* @return parameters names
+ * @see #isSupported(String)
*/
Collection<String> getParametersNames();
+ /** Check if a parameter is supported.
+ * <p>
+ * Supported parameters are the ones that are listed in {@link #getParametersNames()}
+ * </p>
+ * @param name parameter name to check
+ * @return true if the parameter is supported
+ * @see #getParametersNames()
+ */
+ boolean isSupported(String name);
+
/** Get parameter value from its name.
* @param name parameter name
* @return parameter value
diff --git a/src/main/java/org/orekit/forces/SphericalSpacecraft.java b/src/main/java/org/orekit/forces/SphericalSpacecraft.java
index 0429606e6f..d7c41853bf 100644
--- a/src/main/java/org/orekit/forces/SphericalSpacecraft.java
+++ b/src/main/java/org/orekit/forces/SphericalSpacecraft.java
@@ -17,8 +17,11 @@
package org.orekit.forces;
import org.apache.commons.math.geometry.Vector3D;
+import org.orekit.errors.OrekitException;
+import org.orekit.errors.OrekitMessages;
import org.orekit.forces.drag.DragSensitive;
import org.orekit.forces.radiation.RadiationSensitive;
+import org.orekit.forces.radiation.SolarRadiationPressure;
import org.orekit.propagation.SpacecraftState;
/** This class represents the features of a simplified spacecraft.
@@ -129,7 +132,41 @@ public class SphericalSpacecraft implements RadiationSensitive, DragSensitive {
/** Set kP value. */
private void setKP() {
- kP = crossSection * (1 + 4 * (1.0 - absorptionCoeff) * (1.0 - specularReflectionCoeff) / 9);
+ kP = crossSection * (1 + 4 * (1.0 - absorptionCoeff) * (1.0 - specularReflectionCoeff) / 9.0);
+ }
+
+ /** Computes kP derivative with respect to absorption coefficient.
+ * @return kP derivative with respect to absorption coefficient*/
+ private double computeDKPDCa() {
+ return -4 * crossSection * (1.0 - specularReflectionCoeff) / 9;
+ }
+
+ /** Computes kP derivative with respect to reflection coefficient.
+ * @return kP derivative with respect to reflection coefficient*/
+ private double computeDKPDCr() {
+ return -4 * crossSection * (1.0 - absorptionCoeff) / 9;
+ }
+
+ /** {@inheritDoc} */
+ public void addDAccDParam(final Vector3D acceleration, final String paramName, final double[] dAccdParam)
+ throws OrekitException {
+
+ final double coefficient;
+ if (paramName.equals(SolarRadiationPressure.ABSORPTION_COEFFICIENT)) {
+ coefficient = computeDKPDCa() / kP;
+ } else if (paramName.equals(SolarRadiationPressure.REFLECTION_COEFFICIENT)) {
+ coefficient = computeDKPDCr() / kP;
+ } else {
+ throw OrekitException.createIllegalArgumentException(OrekitMessages.UNSUPPORTED_PARAMETER_1_2,
+ paramName,
+ SolarRadiationPressure.ABSORPTION_COEFFICIENT,
+ SolarRadiationPressure.REFLECTION_COEFFICIENT);
+ }
+
+ dAccdParam[0] += coefficient * acceleration.getX();
+ dAccdParam[1] += coefficient * acceleration.getY();
+ dAccdParam[2] += coefficient * acceleration.getZ();
+
}
}
diff --git a/src/main/java/org/orekit/forces/drag/DragForce.java b/src/main/java/org/orekit/forces/drag/DragForce.java
index 16035827e0..c6f9b15b75 100644
--- a/src/main/java/org/orekit/forces/drag/DragForce.java
+++ b/src/main/java/org/orekit/forces/drag/DragForce.java
@@ -22,12 +22,11 @@ import java.util.Collection;
import org.apache.commons.math.geometry.Vector3D;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitMessages;
-import org.orekit.forces.ForceModelWithJacobians;
+import org.orekit.forces.Parameterizable;
import org.orekit.frames.Frame;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.events.EventDetector;
import org.orekit.propagation.numerical.TimeDerivativesEquations;
-import org.orekit.propagation.numerical.TimeDerivativesEquationsWithJacobians;
import org.orekit.time.AbsoluteDate;
@@ -47,13 +46,20 @@ import org.orekit.time.AbsoluteDate;
* @version $Revision:1665 $ $Date:2008-06-11 12:12:59 +0200 (mer., 11 juin 2008) $
*/
-public class DragForce implements ForceModelWithJacobians {
+public class DragForce implements Parameterizable {
/** Parameter name for drag coefficient enabling jacobian processing. */
public static final String DRAG_COEFFICIENT = "DRAG COEFFICIENT";
+ /** List of the parameters names. */
+ private static final ArrayList<String> PARAMETERS_NAMES;
+ static {
+ PARAMETERS_NAMES = new ArrayList<String>();
+ PARAMETERS_NAMES.add(DRAG_COEFFICIENT);
+ }
+
/** Serializable UID. */
- private static final long serialVersionUID = 2574653656986559955L;
+ private static final long serialVersionUID = 5386256916056674950L;
/** Atmospheric model. */
private final Atmosphere atmosphere;
@@ -61,9 +67,6 @@ public class DragForce implements ForceModelWithJacobians {
/** Spacecraft. */
private final DragSensitive spacecraft;
- /** List of the parameters names. */
- private final ArrayList<String> parametersNames = new ArrayList<String>();
-
/** Simple constructor.
* @param atmosphere atmospheric model
* @param spacecraft the object physical and geometrical information
@@ -71,7 +74,6 @@ public class DragForce implements ForceModelWithJacobians {
public DragForce(final Atmosphere atmosphere, final DragSensitive spacecraft) {
this.atmosphere = atmosphere;
this.spacecraft = spacecraft;
- this.parametersNames.add(DRAG_COEFFICIENT);
}
/** Compute the contribution of the drag to the perturbing acceleration.
@@ -104,14 +106,13 @@ public class DragForce implements ForceModelWithJacobians {
}
/** {@inheritDoc} */
- public void addContributionWithJacobians(final SpacecraftState s,
- final TimeDerivativesEquationsWithJacobians adder)
- throws OrekitException {
+ public Collection<String> getParametersNames() {
+ return PARAMETERS_NAMES;
}
/** {@inheritDoc} */
- public Collection<String> getParametersNames() {
- return parametersNames;
+ public boolean isSupported(final String name) {
+ return name.equals(DRAG_COEFFICIENT);
}
/** {@inheritDoc} */
diff --git a/src/main/java/org/orekit/forces/gravity/CunninghamAttractionModel.java b/src/main/java/org/orekit/forces/gravity/CunninghamAttractionModel.java
index 75784896b0..c40768939e 100644
--- a/src/main/java/org/orekit/forces/gravity/CunninghamAttractionModel.java
+++ b/src/main/java/org/orekit/forces/gravity/CunninghamAttractionModel.java
@@ -21,6 +21,7 @@ import org.apache.commons.math.geometry.Vector3D;
import org.apache.commons.math.util.FastMath;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitMessages;
+import org.orekit.forces.AbstractParameterizable;
import org.orekit.forces.ForceModel;
import org.orekit.frames.Frame;
import org.orekit.frames.Transform;
@@ -42,10 +43,10 @@ import org.orekit.propagation.numerical.TimeDerivativesEquations;
* @version $Revision:1665 $ $Date:2008-06-11 12:12:59 +0200 (mer., 11 juin 2008) $
*/
-public class CunninghamAttractionModel implements ForceModel {
+public class CunninghamAttractionModel extends AbstractParameterizable implements ForceModel {
/** Serializable UID. */
- private static final long serialVersionUID = 2609845747545125479L;
+ private static final long serialVersionUID = 759122284106467933L;
/** Equatorial radius of the Central Body. */
private final double equatorialRadius;
@@ -81,6 +82,7 @@ public class CunninghamAttractionModel implements ForceModel {
final double equatorialRadius, final double mu,
final double[][] C, final double[][] S)
throws IllegalArgumentException {
+ super("central attraction coefficient");
this.bodyFrame = centralBodyFrame;
this.equatorialRadius = equatorialRadius;
@@ -375,4 +377,18 @@ public class CunninghamAttractionModel implements ForceModel {
return new EventDetector[0];
}
+ /** {@inheritDoc} */
+ public double getParameter(final String name)
+ throws IllegalArgumentException {
+ complainIfNotSupported(name);
+ return mu;
+ }
+
+ /** {@inheritDoc} */
+ public void setParameter(final String name, final double value)
+ throws IllegalArgumentException {
+ complainIfNotSupported(name);
+ mu = value;
+ }
+
}
diff --git a/src/main/java/org/orekit/forces/gravity/DrozinerAttractionModel.java b/src/main/java/org/orekit/forces/gravity/DrozinerAttractionModel.java
index 3218ff9986..2469fd4b44 100644
--- a/src/main/java/org/orekit/forces/gravity/DrozinerAttractionModel.java
+++ b/src/main/java/org/orekit/forces/gravity/DrozinerAttractionModel.java
@@ -20,6 +20,7 @@ import org.apache.commons.math.geometry.Vector3D;
import org.apache.commons.math.util.FastMath;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitMessages;
+import org.orekit.forces.AbstractParameterizable;
import org.orekit.forces.ForceModel;
import org.orekit.frames.Frame;
import org.orekit.frames.Transform;
@@ -39,10 +40,10 @@ import org.orekit.propagation.numerical.TimeDerivativesEquations;
* @version $Revision:1665 $ $Date:2008-06-11 12:12:59 +0200 (mer., 11 juin 2008) $
*/
-public class DrozinerAttractionModel implements ForceModel {
+public class DrozinerAttractionModel extends AbstractParameterizable implements ForceModel {
/** Serializable UID. */
- private static final long serialVersionUID = 9117000158528461356L;
+ private static final long serialVersionUID = -6897768625006106349L;
/** Reference equatorial radius of the potential. */
private final double equatorialRadius;
@@ -79,6 +80,7 @@ public class DrozinerAttractionModel implements ForceModel {
final double[][] C, final double[][] S)
throws IllegalArgumentException {
+ super("central attraction coefficient");
this.centralBodyFrame = centralBodyFrame;
this.equatorialRadius = equatorialRadius;
this.mu = mu;
@@ -274,4 +276,18 @@ public class DrozinerAttractionModel implements ForceModel {
return new EventDetector[0];
}
+ /** {@inheritDoc} */
+ public double getParameter(final String name)
+ throws IllegalArgumentException {
+ complainIfNotSupported(name);
+ return mu;
+ }
+
+ /** {@inheritDoc} */
+ public void setParameter(final String name, final double value)
+ throws IllegalArgumentException {
+ complainIfNotSupported(name);
+ mu = value;
+ }
+
}
diff --git a/src/main/java/org/orekit/forces/gravity/NewtonianAttraction.java b/src/main/java/org/orekit/forces/gravity/NewtonianAttraction.java
new file mode 100644
index 0000000000..1bddd9aa07
--- /dev/null
+++ b/src/main/java/org/orekit/forces/gravity/NewtonianAttraction.java
@@ -0,0 +1,127 @@
+/* Copyright 2010 Centre National d'Études Spatiales
+ * Licensed to CS Communication & Systèmes (CS) under one or more
+ * contributor license agreements. See the NOTICE file distributed with
+ * this work for additional information regarding copyright ownership.
+ * CS licenses this file to You under the Apache License, Version 2.0
+ * (the "License"); you may not use this file except in compliance with
+ * the License. You may obtain a copy of the License at
+ *
+ * http://www.apache.org/licenses/LICENSE-2.0
+ *
+ * Unless required by applicable law or agreed to in writing, software
+ * distributed under the License is distributed on an "AS IS" BASIS,
+ * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
+ * See the License for the specific language governing permissions and
+ * limitations under the License.
+ */
+package org.orekit.forces.gravity;
+
+import org.apache.commons.math.geometry.Vector3D;
+import org.apache.commons.math.util.FastMath;
+import org.orekit.errors.OrekitException;
+import org.orekit.forces.AbstractParameterizable;
+import org.orekit.forces.ForceModel;
+import org.orekit.propagation.SpacecraftState;
+import org.orekit.propagation.events.EventDetector;
+import org.orekit.propagation.numerical.AccelerationJacobiansProvider;
+import org.orekit.propagation.numerical.TimeDerivativesEquations;
+
+/** Force model for Newtonian central body attraction.
+ * @author Luc Maisonobe
+ * @version $Revision$ $Date$
+ */
+public class NewtonianAttraction extends AbstractParameterizable implements AccelerationJacobiansProvider, ForceModel {
+
+ /** Name of the single parameter of this model: the central attraction coefficient. */
+ public static final String CENTRAL_ATTRACTION_COEFFICIENT = "central attraction coefficient";
+
+ /** Serializable UID. */
+ private static final long serialVersionUID = -7754312556095545327L;
+
+ /** Central attraction coefficient (m^3/s^2). */
+ private double mu;
+
+ /** Simple constructor.
+ * @param mu central attraction coefficient (m^3/s^2)
+ */
+ public NewtonianAttraction(final double mu) {
+ super(CENTRAL_ATTRACTION_COEFFICIENT);
+ this.mu = mu;
+ }
+
+ /** {@inheritDoc} */
+ public void addDAccDState(final SpacecraftState s,
+ final double[][] dAccdPos, final double[][] dAccdVel, final double[] dAccdM)
+ throws OrekitException {
+
+ final Vector3D position = s.getPVCoordinates().getPosition();
+ final double r2 = position.getNormSq();
+ final Vector3D acceleration = new Vector3D(-mu / (r2 * FastMath.sqrt(r2)), position);
+
+ final double x2 = position.getX() * position.getX();
+ final double y2 = position.getY() * position.getY();
+ final double z2 = position.getZ() * position.getZ();
+ final double xy = position.getX() * position.getY();
+ final double yz = position.getY() * position.getZ();
+ final double zx = position.getZ() * position.getX();
+ final double prefix = -Vector3D.dotProduct(acceleration, position) / (r2 * r2);
+
+ // the only non-null contribution for this force is on dAcc/dPos
+ dAccdPos[0][0] += prefix * (2 * x2 - y2 - z2);
+ dAccdPos[0][1] += prefix * 3 * xy;
+ dAccdPos[0][2] += prefix * 3 * zx;
+ dAccdPos[1][0] += prefix * 3 * xy;
+ dAccdPos[1][1] += prefix * (2 * y2 - z2 - x2);
+ dAccdPos[1][2] += prefix * 3 * yz;
+ dAccdPos[2][0] += prefix * 3 * zx;
+ dAccdPos[2][1] += prefix * 3 * yz;
+ dAccdPos[2][2] += prefix * (2 * z2 - x2 - y2);
+
+ }
+
+ /** {@inheritDoc} */
+ public void addDAccDParam(final SpacecraftState s, final String paramName, final double[] dAccdParam)
+ throws OrekitException {
+ complainIfNotSupported(paramName);
+ final Vector3D position = s.getPVCoordinates().getPosition();
+ final double r2 = position.getNormSq();
+ final double factor = -1.0 / (r2 * FastMath.sqrt(r2));
+ dAccdParam[0] += factor * position.getX();
+ dAccdParam[1] += factor * position.getY();
+ dAccdParam[2] += factor * position.getZ();
+ }
+
+ /** Get the central attraction coefficient μ.
+ * @return mu central attraction coefficient (m<sup>3</sup>/s<sup>2</sup>)
+ */
+ public double getMu() {
+ return mu;
+ }
+
+ /** {@inheritDoc} */
+ public double getParameter(final String name)
+ throws IllegalArgumentException {
+ complainIfNotSupported(name);
+ return mu;
+ }
+
+ /** {@inheritDoc} */
+ public void setParameter(final String name, final double value)
+ throws IllegalArgumentException {
+ complainIfNotSupported(name);
+ this.mu = value;
+ }
+
+ /** {@inheritDoc} */
+ public void addContribution(final SpacecraftState s, final TimeDerivativesEquations adder)
+ throws OrekitException {
+ adder.addKeplerContribution(mu);
+ }
+
+ /** {@inheritDoc} */
+ public EventDetector[] getEventsDetectors() {
+ return new EventDetector[0];
+ }
+
+}
+
diff --git a/src/main/java/org/orekit/forces/gravity/ThirdBodyAttraction.java b/src/main/java/org/orekit/forces/gravity/ThirdBodyAttraction.java
index 7b806383b6..b99b3d4f9c 100644
--- a/src/main/java/org/orekit/forces/gravity/ThirdBodyAttraction.java
+++ b/src/main/java/org/orekit/forces/gravity/ThirdBodyAttraction.java
@@ -20,6 +20,7 @@ import org.apache.commons.math.geometry.Vector3D;
import org.apache.commons.math.util.FastMath;
import org.orekit.bodies.CelestialBody;
import org.orekit.errors.OrekitException;
+import org.orekit.forces.AbstractParameterizable;
import org.orekit.forces.ForceModel;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.events.EventDetector;
@@ -32,21 +33,26 @@ import org.orekit.propagation.numerical.TimeDerivativesEquations;
* @author Véronique Pommier-Maurussane
* @version $Revision:1665 $ $Date:2008-06-11 12:12:59 +0200 (mer., 11 juin 2008) $
*/
-public class ThirdBodyAttraction implements ForceModel {
+public class ThirdBodyAttraction extends AbstractParameterizable implements ForceModel {
/** Serializable UID. */
- private static final long serialVersionUID = 9017402538195695004L;
+ private static final long serialVersionUID = -1703641239448217284L;
/** The body to consider. */
private final CelestialBody body;
+ /** Local value for body attraction coefficient. */
+ private double gm;
+
/** Simple constructor.
* @param body the third body to consider
* (ex: {@link org.orekit.bodies.CelestialBodyFactory#getSun()} or
* {@link org.orekit.bodies.CelestialBodyFactory#getMoon()})
*/
public ThirdBodyAttraction(final CelestialBody body) {
+ super(body.getName() + " attraction coefficient");
this.body = body;
+ this.gm = body.getGM();
}
/** {@inheritDoc} */
@@ -61,8 +67,8 @@ public class ThirdBodyAttraction implements ForceModel {
// compute relative acceleration
final Vector3D gamma =
- new Vector3D(body.getGM() * FastMath.pow(r2Sat, -1.5), satToBody,
- -body.getGM() * FastMath.pow(r2Central, -1.5), centralToBody);
+ new Vector3D(gm * FastMath.pow(r2Sat, -1.5), satToBody,
+ -gm * FastMath.pow(r2Central, -1.5), centralToBody);
// add contribution to the ODE second member
adder.addXYZAcceleration(gamma.getX(), gamma.getY(), gamma.getZ());
@@ -74,4 +80,18 @@ public class ThirdBodyAttraction implements ForceModel {
return new EventDetector[0];
}
+ /** {@inheritDoc} */
+ public double getParameter(final String name)
+ throws IllegalArgumentException {
+ complainIfNotSupported(name);
+ return gm;
+ }
+
+ /** {@inheritDoc} */
+ public void setParameter(final String name, final double value)
+ throws IllegalArgumentException {
+ complainIfNotSupported(name);
+ gm = value;
+ }
+
}
diff --git a/src/main/java/org/orekit/forces/gravity/potential/SHMFormatReader.java b/src/main/java/org/orekit/forces/gravity/potential/SHMFormatReader.java
index 78fc9492f7..7002869b6e 100644
--- a/src/main/java/org/orekit/forces/gravity/potential/SHMFormatReader.java
+++ b/src/main/java/org/orekit/forces/gravity/potential/SHMFormatReader.java
@@ -68,7 +68,8 @@ public class SHMFormatReader extends PotentialCoefficientsReader {
boolean okSHM = false;
boolean okCoeffs = false;
String line = r.readLine();
- if ("FIRST ".equals(line.substring(0, 6)) &&
+ if ((line != null) &&
+ "FIRST ".equals(line.substring(0, 6)) &&
"SHM ".equals(line.substring(49, 56))) {
for (line = r.readLine(); line != null; line = r.readLine()) {
if (line.length() >= 6) {
diff --git a/src/main/java/org/orekit/forces/maneuvers/ConstantThrustManeuver.java b/src/main/java/org/orekit/forces/maneuvers/ConstantThrustManeuver.java
index ff20bbb216..6b140a081d 100644
--- a/src/main/java/org/orekit/forces/maneuvers/ConstantThrustManeuver.java
+++ b/src/main/java/org/orekit/forces/maneuvers/ConstantThrustManeuver.java
@@ -18,6 +18,7 @@ package org.orekit.forces.maneuvers;
import org.apache.commons.math.geometry.Vector3D;
import org.orekit.errors.OrekitException;
+import org.orekit.forces.AbstractParameterizable;
import org.orekit.forces.ForceModel;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.events.DateDetector;
@@ -37,11 +38,17 @@ import org.orekit.time.AbsoluteDate;
* @author Luc Maisonobe
* @version $Revision:1665 $ $Date:2008-06-11 12:12:59 +0200 (mer., 11 juin 2008) $
*/
-public class ConstantThrustManeuver implements ForceModel {
+public class ConstantThrustManeuver extends AbstractParameterizable implements ForceModel {
/** Reference gravity acceleration constant (m/s<sup>2</sup>). */
public static final double G0 = 9.80665;
+ /** Parameter name for thrust. */
+ private static final String THRUST = "thrust";
+
+ /** Parameter name for flow rate. */
+ private static final String FLOW_RATE = "flow rate";
+
/** Serializable UID. */
private static final long serialVersionUID = 5349622732741384211L;
@@ -55,10 +62,10 @@ public class ConstantThrustManeuver implements ForceModel {
private final AbsoluteDate endDate;
/** Engine thrust. */
- private final double thrust;
+ private double thrust;
/** Engine flow-rate. */
- private final double flowRate;
+ private double flowRate;
/** Direction of the acceleration in satellite frame. */
private final Vector3D direction;
@@ -75,6 +82,7 @@ public class ConstantThrustManeuver implements ForceModel {
final double thrust, final double isp,
final Vector3D direction) {
+ super(THRUST, FLOW_RATE);
if (duration >= 0) {
this.startDate = date;
this.endDate = date.shiftedBy(duration);
@@ -115,6 +123,27 @@ public class ConstantThrustManeuver implements ForceModel {
};
}
+ /** {@inheritDoc} */
+ public double getParameter(final String name)
+ throws IllegalArgumentException {
+ complainIfNotSupported(name);
+ if (name.equals(THRUST)) {
+ return thrust;
+ }
+ return flowRate;
+ }
+
+ /** {@inheritDoc} */
+ public void setParameter(final String name, final double value)
+ throws IllegalArgumentException {
+ complainIfNotSupported(name);
+ if (name.equals(THRUST)) {
+ thrust = value;
+ } else {
+ flowRate = value;
+ }
+ }
+
/** Detector for start of maneuver. */
private class FiringStartDetector extends DateDetector {
diff --git a/src/main/java/org/orekit/forces/package.html b/src/main/java/org/orekit/forces/package.html
index 53c91fd7f2..864d2d8dc6 100644
--- a/src/main/java/org/orekit/forces/package.html
+++ b/src/main/java/org/orekit/forces/package.html
@@ -1,12 +1,11 @@
<html>
<body>
This package provides the interface for force models that will be used by the
-{@link org.orekit.propagation.numerical.NumericalPropagator} and the
-{@link org.orekit.propagation.numerical.NumericalPropagatorWithJacobians}, as well as
+{@link org.orekit.propagation.numerical.NumericalPropagator}, as well as
some classical spacecraft models for surface forces (spherical, box and solar array ...).
@author Luc Maisonobe
@author Pascal Parraud
</body>
-</html>
\ No newline at end of file
+</html>
diff --git a/src/main/java/org/orekit/forces/radiation/RadiationSensitive.java b/src/main/java/org/orekit/forces/radiation/RadiationSensitive.java
index ae49115fd2..b111d33eba 100644
--- a/src/main/java/org/orekit/forces/radiation/RadiationSensitive.java
+++ b/src/main/java/org/orekit/forces/radiation/RadiationSensitive.java
@@ -64,4 +64,13 @@ public interface RadiationSensitive extends Serializable {
*/
double getReflectionCoefficient();
+ /** Compute acceleration derivatives with respect to additional parameters.
+ * @param acceleration spacecraft acceleration
+ * @param paramName name of the parameter with respect to which derivatives are required
+ * @param dAccdParam acceleration derivatives with respect to additional parameters
+ * @exception OrekitException if derivatives cannot be computed
+ */
+ void addDAccDParam(Vector3D acceleration, String paramName, double[] dAccdParam)
+ throws OrekitException;
+
}
diff --git a/src/main/java/org/orekit/forces/radiation/SolarRadiationPressure.java b/src/main/java/org/orekit/forces/radiation/SolarRadiationPressure.java
index 12ff8a86ab..b89717d77d 100644
--- a/src/main/java/org/orekit/forces/radiation/SolarRadiationPressure.java
+++ b/src/main/java/org/orekit/forces/radiation/SolarRadiationPressure.java
@@ -16,20 +16,18 @@
*/
package org.orekit.forces.radiation;
-import java.util.ArrayList;
-import java.util.Collection;
-
import org.apache.commons.math.geometry.Vector3D;
import org.apache.commons.math.util.FastMath;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitMessages;
-import org.orekit.forces.ForceModelWithJacobians;
+import org.orekit.forces.AbstractParameterizable;
+import org.orekit.forces.ForceModel;
import org.orekit.frames.Frame;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.events.AbstractDetector;
import org.orekit.propagation.events.EventDetector;
+import org.orekit.propagation.numerical.AccelerationJacobiansProvider;
import org.orekit.propagation.numerical.TimeDerivativesEquations;
-import org.orekit.propagation.numerical.TimeDerivativesEquationsWithJacobians;
import org.orekit.time.AbsoluteDate;
import org.orekit.utils.PVCoordinates;
import org.orekit.utils.PVCoordinatesProvider;
@@ -42,18 +40,18 @@ import org.orekit.utils.PVCoordinatesProvider;
* @author Pascal Parraud
* @version $Revision:1665 $ $Date:2008-06-11 12:12:59 +0200 (mer., 11 juin 2008) $
*/
-public class SolarRadiationPressure implements ForceModelWithJacobians {
+public class SolarRadiationPressure extends AbstractParameterizable implements ForceModel, AccelerationJacobiansProvider {
- /** Parameter name for absorption coefficient enabling jacobian processing. */
- public static final String ABSORPTION_COEFFICIENT = "ABSORPTION COEFFICIENT";
+ /** Parameter name for absorption coefficient. */
+ public static final String ABSORPTION_COEFFICIENT = "absorption coefficient";
- /** Parameter name for specular reflection coefficient enabling jacobian processing. */
- public static final String REFLECTION_COEFFICIENT = "REFLECTION COEFFICIENT";
+ /** Parameter name for reflection coefficient. */
+ public static final String REFLECTION_COEFFICIENT = "reflection coefficient";
/** Serializable UID. */
- private static final long serialVersionUID = 8874297900604482921L;
+ private static final long serialVersionUID = -4510170320082379419L;
- /** Sun radius (m). */
+ /** Sun radius (m). */
private static final double SUN_RADIUS = 6.95e8;
/** Reference flux normalized for a 1m distance (N). */
@@ -68,9 +66,6 @@ public class SolarRadiationPressure implements ForceModelWithJacobians {
/** Spacecraft. */
private final RadiationSensitive spacecraft;
- /** List of the parameters names. */
- private final ArrayList<String> parametersNames = new ArrayList<String>();
-
/** Simple constructor with default reference values.
* <p>When this constructor is used, the reference values are:</p>
* <ul>
@@ -102,30 +97,49 @@ public class SolarRadiationPressure implements ForceModelWithJacobians {
final PVCoordinatesProvider sun,
final double equatorialRadius,
final RadiationSensitive spacecraft) {
+ super(ABSORPTION_COEFFICIENT, REFLECTION_COEFFICIENT);
this.kRef = pRef * dRef * dRef;
this.sun = sun;
this.equatorialRadius = equatorialRadius;
this.spacecraft = spacecraft;
- this.parametersNames.add(ABSORPTION_COEFFICIENT);
- this.parametersNames.add(REFLECTION_COEFFICIENT);
}
- /** {@inheritDoc} */
- public void addContribution(final SpacecraftState s, final TimeDerivativesEquations adder)
- throws OrekitException {
-
+ /** Compute radiation coefficient.
+ * @param s spacecraft state
+ * @return coefficient for acceleration computation
+ * @exception OrekitException if position cannot be computed
+ */
+ private double computeRawP (final SpacecraftState s) throws OrekitException {
final AbsoluteDate date = s.getDate();
final Frame frame = s.getFrame();
final Vector3D position = s.getPVCoordinates().getPosition();
- // raw radiation pressure
final Vector3D satSunVector = getSatSunVector(s);
final double r2 = satSunVector.getNormSq();
- final double rawP = kRef * getLightningRatio(position, frame, date) / r2;
- final Vector3D flux = new Vector3D(-rawP / FastMath.sqrt(r2), satSunVector);
+ return kRef * getLightningRatio(position, frame, date) / r2;
+ }
+
+ /** Compute radiation acceleration.
+ * @param s spacecraft state
+ * @return acceleration
+ * @exception OrekitException if position cannot be computed
+ */
+ private Vector3D computeAcceleration(final SpacecraftState s) throws OrekitException {
+
+ final Vector3D satSunVector = getSatSunVector(s);
+ final double r2 = satSunVector.getNormSq();
+
+ final double rawP = computeRawP(s);
+ // raw radiation pressure
+ return spacecraft.radiationPressureAcceleration(s, new Vector3D(-rawP / FastMath.sqrt(r2), satSunVector));
+ }
+
+ /** {@inheritDoc} */
+ public void addContribution(final SpacecraftState s, final TimeDerivativesEquations adder)
+ throws OrekitException {
// provide the perturbing acceleration to the derivatives adder
- adder.addAcceleration(spacecraft.radiationPressureAcceleration(s, flux), frame);
+ adder.addAcceleration(computeAcceleration(s), s.getFrame());
}
@@ -185,12 +199,8 @@ public class SolarRadiationPressure implements ForceModelWithJacobians {
alpha2 * FastMath.sqrt(alphaEarth * alphaEarth - alpha2 * alpha2);
result = (P1 - P2) / (FastMath.PI * alphaSun * alphaSun);
-
-
}
-
return result;
-
}
/** Compute sat-Sun vector in spacecraft state frame.
@@ -213,37 +223,69 @@ public class SolarRadiationPressure implements ForceModelWithJacobians {
}
/** {@inheritDoc} */
- public void addContributionWithJacobians(final SpacecraftState s,
- final TimeDerivativesEquationsWithJacobians adder)
+ public void addDAccDState(final SpacecraftState s,
+ final double[][] dAccdPos, final double[][] dAccdVel, final double[] dAccdM)
throws OrekitException {
+
+ final Vector3D satSunVector = getSatSunVector(s);
+ final double r2 = satSunVector.getNormSq();
+ final double rawP = computeRawP(s);
+ final Vector3D acceleration = spacecraft.radiationPressureAcceleration(s, new Vector3D(-rawP / FastMath.sqrt(r2), satSunVector));
+
+ final double x2 = satSunVector.getX() * satSunVector.getX();
+ final double y2 = satSunVector.getY() * satSunVector.getY();
+ final double z2 = satSunVector.getZ() * satSunVector.getZ();
+ final double xy = satSunVector.getX() * satSunVector.getY();
+ final double yz = satSunVector.getY() * satSunVector.getZ();
+ final double zx = satSunVector.getZ() * satSunVector.getX();
+ final double prefix = Vector3D.dotProduct(acceleration, satSunVector) / (r2 * r2);
+
+ // jacobian with respect to position
+ dAccdPos[0][0] += prefix * (2 * x2 - y2 - z2);
+ dAccdPos[0][1] += prefix * 3 * xy;
+ dAccdPos[0][2] += prefix * 3 * zx;
+ dAccdPos[1][0] += prefix * 3 * xy;
+ dAccdPos[1][1] += prefix * (2 * y2 - z2 - x2);
+ dAccdPos[1][2] += prefix * 3 * yz;
+ dAccdPos[2][0] += prefix * 3 * zx;
+ dAccdPos[2][1] += prefix * 3 * yz;
+ dAccdPos[2][2] += prefix * (2 * z2 - x2 - y2);
+
+ // jacobian with respect to velocity is null
+
+ if (dAccdM != null) {
+ // jacobian with respect to mass
+ dAccdM[0] -= acceleration.getX() / s.getMass();
+ dAccdM[1] -= acceleration.getY() / s.getMass();
+ dAccdM[2] -= acceleration.getZ() / s.getMass();
+ }
+
}
/** {@inheritDoc} */
- public Collection<String> getParametersNames() {
- return parametersNames;
+ public void addDAccDParam(final SpacecraftState s, final String paramName, final double[] dAccdParam)
+ throws OrekitException {
+ spacecraft.addDAccDParam(computeAcceleration(s), paramName, dAccdParam);
}
/** {@inheritDoc} */
public double getParameter(final String name)
throws IllegalArgumentException {
- if (name.matches(ABSORPTION_COEFFICIENT)) {
+ complainIfNotSupported(name);
+ if (name.equals(ABSORPTION_COEFFICIENT)) {
return spacecraft.getAbsorptionCoefficient();
- } else if (name.matches(REFLECTION_COEFFICIENT)) {
- return spacecraft.getReflectionCoefficient();
- } else {
- throw OrekitException.createIllegalArgumentException(OrekitMessages.UNKNOWN_PARAMETER, name);
}
+ return spacecraft.getReflectionCoefficient();
}
/** {@inheritDoc} */
public void setParameter(final String name, final double value)
throws IllegalArgumentException {
- if (name.matches(ABSORPTION_COEFFICIENT)) {
+ complainIfNotSupported(name);
+ if (name.equals(ABSORPTION_COEFFICIENT)) {
spacecraft.setAbsorptionCoefficient(value);
- } else if (name.matches(REFLECTION_COEFFICIENT)) {
- spacecraft.setReflectionCoefficient(value);
} else {
- throw OrekitException.createIllegalArgumentException(OrekitMessages.UNKNOWN_PARAMETER, name);
+ spacecraft.setReflectionCoefficient(value);
}
}
diff --git a/src/main/java/org/orekit/frames/Frame.java b/src/main/java/org/orekit/frames/Frame.java
index 67f73be414..1bc68a3e82 100644
--- a/src/main/java/org/orekit/frames/Frame.java
+++ b/src/main/java/org/orekit/frames/Frame.java
@@ -64,7 +64,7 @@ public class Frame implements Serializable {
private Transform transform;
/** Map of deepest frames commons with other frames. */
- private final WeakHashMap<Frame, Frame> commons;
+ private final transient WeakHashMap<Frame, Frame> commons;
/** Instance name. */
private final String name;
diff --git a/src/main/java/org/orekit/frames/FramesFactory.java b/src/main/java/org/orekit/frames/FramesFactory.java
index 01b4aa9e54..5438d21d13 100644
--- a/src/main/java/org/orekit/frames/FramesFactory.java
+++ b/src/main/java/org/orekit/frames/FramesFactory.java
@@ -149,7 +149,7 @@ public class FramesFactory implements Serializable {
private static final long serialVersionUID = 1720647682459923909L;
/** Predefined frames. */
- private static Map<Predefined, FactoryManagedFrame> FRAMES =
+ private static transient Map<Predefined, FactoryManagedFrame> FRAMES =
new WeakHashMap<Predefined, FactoryManagedFrame>();
/** EOP 1980 loaders. */
diff --git a/src/main/java/org/orekit/frames/SpacecraftFrame.java b/src/main/java/org/orekit/frames/SpacecraftFrame.java
index e533a8cf9f..105b226e77 100644
--- a/src/main/java/org/orekit/frames/SpacecraftFrame.java
+++ b/src/main/java/org/orekit/frames/SpacecraftFrame.java
@@ -37,7 +37,7 @@ public class SpacecraftFrame extends Frame implements PVCoordinatesProvider {
private final Propagator propagator;
/** Cached date to avoid useless computation. */
- private AbsoluteDate cachedDate;
+ private transient AbsoluteDate cachedDate;
/** Simple constructor.
* @param propagator orbit/attitude propagator computing spacecraft state evolution
diff --git a/src/main/java/org/orekit/frames/TIRF2000Frame.java b/src/main/java/org/orekit/frames/TIRF2000Frame.java
index 6fb3c8110b..b9d919ba2b 100644
--- a/src/main/java/org/orekit/frames/TIRF2000Frame.java
+++ b/src/main/java/org/orekit/frames/TIRF2000Frame.java
@@ -54,7 +54,7 @@ class TIRF2000Frame extends FactoryManagedFrame {
private static final double ERA_1B = ERA_1A * 0.00273781191135448;
/** Cached date to avoid useless calculus. */
- private AbsoluteDate cachedDate;
+ private transient AbsoluteDate cachedDate;
/** Earth Rotation Angle, in radians. */
private double era;
diff --git a/src/main/java/org/orekit/frames/VEISFrame.java b/src/main/java/org/orekit/frames/VEISFrame.java
index e113db2b4b..143a3bb9ee 100644
--- a/src/main/java/org/orekit/frames/VEISFrame.java
+++ b/src/main/java/org/orekit/frames/VEISFrame.java
@@ -50,7 +50,7 @@ class VEISFrame extends FactoryManagedFrame {
private static final double VSTD = 7.292115146705209e-5;
/** Cached date to avoid useless calculus. */
- private AbsoluteDate cachedDate;
+ private transient AbsoluteDate cachedDate;
/** Constructor for the singleton.
* @param factoryKey key of the frame within the factory
diff --git a/src/main/java/org/orekit/orbits/CartesianOrbit.java b/src/main/java/org/orekit/orbits/CartesianOrbit.java
index af7740ef3e..8db09f7b5d 100644
--- a/src/main/java/org/orekit/orbits/CartesianOrbit.java
+++ b/src/main/java/org/orekit/orbits/CartesianOrbit.java
@@ -16,6 +16,9 @@
*/
package org.orekit.orbits;
+import org.apache.commons.math.geometry.Rotation;
+import org.apache.commons.math.geometry.Vector3D;
+import org.apache.commons.math.util.FastMath;
import org.orekit.frames.Frame;
import org.orekit.time.AbsoluteDate;
import org.orekit.utils.PVCoordinates;
@@ -59,10 +62,10 @@ import org.orekit.utils.PVCoordinates;
public class CartesianOrbit extends Orbit {
/** Serializable UID. */
- private static final long serialVersionUID = -6035381767203311530L;
+ private static final long serialVersionUID = -5411308212620896302L;
- /** Underlying equinoctial orbit providing non-cartesian elements. */
- private final EquinoctialOrbit equinoctial;
+ /** Underlying equinoctial orbit to which high-level methods are delegated. */
+ private transient EquinoctialOrbit equinoctial;
/** Constructor from cartesian parameters.
* @param pvCoordinates the position and velocity of the satellite.
@@ -77,7 +80,7 @@ public class CartesianOrbit extends Orbit {
final AbsoluteDate date, final double mu)
throws IllegalArgumentException {
super(pvCoordinates, frame, date, mu);
- equinoctial = new EquinoctialOrbit(pvCoordinates, frame, date, mu);
+ equinoctial = null;
}
/** Constructor from any kind of orbital parameters.
@@ -85,34 +88,56 @@ public class CartesianOrbit extends Orbit {
*/
public CartesianOrbit(final Orbit op) {
super(op.getPVCoordinates(), op.getFrame(), op.getDate(), op.getMu());
- equinoctial = (op instanceof EquinoctialOrbit) ? (EquinoctialOrbit) op : new EquinoctialOrbit(op);
+ if (op instanceof EquinoctialOrbit) {
+ equinoctial = (EquinoctialOrbit) op;
+ } else if (op instanceof CartesianOrbit) {
+ equinoctial = ((CartesianOrbit) op).equinoctial;
+ } else {
+ equinoctial = null;
+ }
+ }
+
+ /** Lazy evaluation of equinoctial parameters. */
+ private void initEquinoctial() {
+ if (equinoctial == null) {
+ equinoctial = new EquinoctialOrbit(getPVCoordinates(), getFrame(), getDate(), getMu());
+ }
}
/** Get the semi-major axis.
* @return semi-major axis (m)
*/
public double getA() {
- return equinoctial.getA();
+ // lazy evaluation of semi-major axis
+ final double r = getPVCoordinates().getPosition().getNorm();
+ final double V2 = getPVCoordinates().getVelocity().getNormSq();
+ return r / (2 - r * V2 / getMu());
}
/** Get the eccentricity.
* @return eccentricity
*/
public double getE() {
- return equinoctial.getE();
+ final Vector3D pvP = getPVCoordinates().getPosition();
+ final Vector3D pvV = getPVCoordinates().getVelocity();
+ final double rV2OnMu = pvP.getNorm() * pvV.getNormSq() / getMu();
+ final double eSE = Vector3D.dotProduct(pvP, pvV) / FastMath.sqrt(getMu() * getA());
+ final double eCE = rV2OnMu - 1;
+ return FastMath.sqrt(eCE * eCE + eSE * eSE);
}
/** Get the inclination.
* @return inclination (rad)
*/
public double getI() {
- return equinoctial.getI();
+ return Vector3D.angle(Vector3D.PLUS_K, getPVCoordinates().getMomentum());
}
/** Get the first component of the eccentricity vector.
* @return first component of the eccentricity vector
*/
public double getEquinoctialEx() {
+ initEquinoctial();
return equinoctial.getEquinoctialEx();
}
@@ -120,6 +145,7 @@ public class CartesianOrbit extends Orbit {
* @return second component of the eccentricity vector
*/
public double getEquinoctialEy() {
+ initEquinoctial();
return equinoctial.getEquinoctialEy();
}
@@ -127,20 +153,31 @@ public class CartesianOrbit extends Orbit {
* @return first component of the inclination vector.
*/
public double getHx() {
- return equinoctial.getHx();
+ final Vector3D w = getPVCoordinates().getMomentum().normalize();
+ // Check for equatorial retrograde orbit
+ if (((w.getX() * w.getX() + w.getY() * w.getY()) == 0) && w.getZ() < 0) {
+ return Double.NaN;
+ }
+ return -w.getY() / (1 + w.getZ());
}
/** Get the second component of the inclination vector.
* @return second component of the inclination vector.
*/
public double getHy() {
- return equinoctial.getHy();
+ final Vector3D w = getPVCoordinates().getMomentum().normalize();
+ // Check for equatorial retrograde orbit
+ if (((w.getX() * w.getX() + w.getY() * w.getY()) == 0) && w.getZ() < 0) {
+ return Double.NaN;
+ }
+ return w.getX() / (1 + w.getZ());
}
/** Get the true latitude argument.
* @return true latitude argument (rad)
*/
public double getLv() {
+ initEquinoctial();
return equinoctial.getLv();
}
@@ -148,6 +185,7 @@ public class CartesianOrbit extends Orbit {
* @return eccentric latitude argument.(rad)
*/
public double getLE() {
+ initEquinoctial();
return equinoctial.getLE();
}
@@ -155,12 +193,185 @@ public class CartesianOrbit extends Orbit {
* @return mean latitude argument.(rad)
*/
public double getLM() {
+ initEquinoctial();
return equinoctial.getLM();
}
+ /** {@inheritDoc} */
+ protected PVCoordinates initPVCoordinates() {
+ // nothing to do here, as the canonical elements are already the cartesian ones
+ return getPVCoordinates();
+ }
+
/** {@inheritDoc} */
public CartesianOrbit shiftedBy(final double dt) {
- return new CartesianOrbit(equinoctial.shiftedBy(dt));
+ final PVCoordinates shiftedPV = (getA() < 0) ? shiftPVHyperbolic(dt) : shiftPVElliptic(dt);
+ return new CartesianOrbit(shiftedPV, getFrame(), getDate().shiftedBy(dt), getMu());
+ }
+
+ /** Compute shifted position and velocity in elliptic case.
+ * @param dt time shift
+ * @return shifted position and velocity
+ */
+ private PVCoordinates shiftPVElliptic(final double dt) {
+
+ // preliminary computation
+ final Vector3D pvP = getPVCoordinates().getPosition();
+ final Vector3D pvV = getPVCoordinates().getVelocity();
+ final double r = pvP.getNorm();
+ final double rV2OnMu = r * pvV.getNormSq() / getMu();
+ final double a = getA();
+ final double eSE = Vector3D.dotProduct(pvP, pvV) / FastMath.sqrt(getMu() * a);
+ final double eCE = rV2OnMu - 1;
+ final double e2 = eCE * eCE + eSE * eSE;
+
+ // we can use any arbitrary reference 2D frame in the orbital plane
+ // in order to simplify some equations below, we use the current position as the u axis
+ final Vector3D u = pvP.normalize();
+ final Vector3D v = Vector3D.crossProduct(getPVCoordinates().getMomentum(), u).normalize();
+
+ // the following equations rely on the specific choice of u explained above,
+ // some coefficients that vanish to 0 in this case have already been removed here
+ final double ex = (eCE - e2) * a / r;
+ final double ey = -FastMath.sqrt(1 - e2) * eSE * a / r;
+ final double beta = 1 / (1 + FastMath.sqrt(1 - e2));
+ final double thetaE0 = FastMath.atan2(ey + eSE * beta * ex, r / a + ex - eSE * beta * ey);
+ final double thetaM0 = thetaE0 - ex * FastMath.sin(thetaE0) + ey * FastMath.cos(thetaE0);
+
+ // compute in-plane shifted eccentric argument
+ final double thetaM1 = thetaM0 + getKeplerianMeanMotion() * dt;
+ final double thetaE1 = meanToEccentric(thetaM1, ex, ey);
+ final double cTE = FastMath.cos(thetaE1);
+ final double sTE = FastMath.sin(thetaE1);
+
+ // compute shifted in-plane cartesian coordinates
+ final double exey = ex * ey;
+ final double exCeyS = ex * cTE + ey * sTE;
+ final double x = a * ((1 - beta * ey * ey) * cTE + beta * exey * sTE - ex);
+ final double y = a * ((1 - beta * ex * ex) * sTE + beta * exey * cTE - ey);
+ final double factor = FastMath.sqrt(getMu() / a) / (1 - exCeyS);
+ final double xDot = factor * (-sTE + beta * ey * exCeyS);
+ final double yDot = factor * ( cTE - beta * ex * exCeyS);
+
+ return new PVCoordinates(new Vector3D(x, u, y, v), new Vector3D(xDot, u, yDot, v));
+
+ }
+
+ /** Compute shifted position and velocity in hyperbolic case.
+ * @param dt time shift
+ * @return shifted position and velocity
+ */
+ private PVCoordinates shiftPVHyperbolic(final double dt) {
+
+ final PVCoordinates pv = getPVCoordinates();
+ final Vector3D pvP = pv.getPosition();
+ final Vector3D pvV = pv.getVelocity();
+ final Vector3D pvM = pv.getMomentum();
+ final double r = pvP.getNorm();
+ final double rV2OnMu = r * pvV.getNormSq() / getMu();
+ final double a = getA();
+ final double muA = getMu() * a;
+ final double e = FastMath.sqrt(1 - Vector3D.dotProduct(pvM, pvM) / muA);
+ final double sqrt = FastMath.sqrt((e + 1) / (e - 1));
+
+ // compute mean anomaly
+ final double eSH = Vector3D.dotProduct(pvP, pvV) / FastMath.sqrt(-muA);
+ final double eCH = rV2OnMu - 1;
+ final double H0 = FastMath.log((eCH + eSH) / (eCH - eSH)) / 2;
+ final double M0 = e * FastMath.sinh(H0) - H0;
+
+ // find canonical 2D frame with p pointing to perigee
+ final double v0 = 2 * FastMath.atan(sqrt * FastMath.tanh(H0 / 2));
+ final Vector3D p = new Rotation(pvM, -v0).applyTo(pvP).normalize();
+ final Vector3D q = Vector3D.crossProduct(pvM, p).normalize();
+
+ // compute shifted eccentric anomaly
+ final double M1 = M0 + getKeplerianMeanMotion() * dt;
+ final double H1 = meanToHyperbolicEccentric(M1, e);
+
+ // compute shifted in-plane cartesian coordinates
+ final double cH = FastMath.cosh(H1);
+ final double sH = FastMath.sinh(H1);
+ final double sE2m1 = FastMath.sqrt((e - 1) * (e + 1));
+
+ // coordinates of position and velocity in the orbital plane
+ final double x = a * (cH - e);
+ final double y = -a * sE2m1 * sH;
+ final double factor = FastMath.sqrt(getMu() / -a) / (e * cH - 1);
+ final double xDot = -factor * sH;
+ final double yDot = factor * sE2m1 * cH;
+
+ return new PVCoordinates(new Vector3D(x, p, y, q), new Vector3D(xDot, p, yDot, q));
+
+ }
+
+ /** Computes the eccentric in-plane argument from the mean in-plane argument.
+ * @param thetaM = mean in-plane argument (rad)
+ * @param ex first component of eccentricity vector
+ * @param ey second component of eccentricity vector
+ * @return the eccentric in-plane argument.
+ */
+ private double meanToEccentric(final double thetaM, final double ex, final double ey) {
+ // Generalization of Kepler equation to in-plane parameters
+ // with thetaE = eta + E and
+ // thetaM = eta + M = thetaE - ex.sin(thetaE) + ey.cos(thetaE)
+ // and eta being counted from an arbitrary reference in the orbital plane
+ double thetaE = thetaM;
+ double shift = 0.0;
+ double thetaEMthetaM = 0.0;
+ double cosThetaE = FastMath.cos(thetaE);
+ double sinThetaE = FastMath.sin(thetaE);
+ int iter = 0;
+ do {
+ final double f2 = ex * sinThetaE - ey * cosThetaE;
+ final double f1 = 1.0 - ex * cosThetaE - ey * sinThetaE;
+ final double f0 = thetaEMthetaM - f2;
+
+ final double f12 = 2.0 * f1;
+ shift = f0 * f12 / (f1 * f12 - f0 * f2);
+
+ thetaEMthetaM -= shift;
+ thetaE = thetaM + thetaEMthetaM;
+ cosThetaE = FastMath.cos(thetaE);
+ sinThetaE = FastMath.sin(thetaE);
+
+ } while ((++iter < 50) && (FastMath.abs(shift) > 1.0e-12));
+
+ return thetaE;
+
+ }
+
+ /** Computes the hyperbolic eccentric anomaly from the mean anomaly.
+ * <p>
+ * The algorithm used here for solving hyperbolic Kepler equation is
+ * a naive initialization and classical Halley method for iterations.
+ * </p>
+ * @param M mean anomaly (rad)
+ * @param e eccentricity
+ * @return the true anomaly
+ */
+ private double meanToHyperbolicEccentric(final double M, final double e) {
+
+ // resolution of hyperbolic Kepler equation for keplerian parameters
+ double H = -M;
+ double shift = 0.0;
+ double HpM = 0.0;
+ int iter = 0;
+ do {
+ final double f2 = e * FastMath.sinh(H);
+ final double f1 = e * FastMath.cosh(H) - 1;
+ final double f0 = f2 - HpM;
+
+ final double f12 = 2 * f1;
+ shift = f0 * f12 / (f1 * f12 - f0 * f2);
+
+ HpM -= shift;
+ H = HpM - M;
+
+ } while ((++iter < 50) && (FastMath.abs(shift) > 1.0e-12));
+
+ return H;
+
}
/** Returns a string representation of this Orbit object.
diff --git a/src/main/java/org/orekit/orbits/CircularOrbit.java b/src/main/java/org/orekit/orbits/CircularOrbit.java
index 8901690b7f..ce021871e6 100644
--- a/src/main/java/org/orekit/orbits/CircularOrbit.java
+++ b/src/main/java/org/orekit/orbits/CircularOrbit.java
@@ -78,7 +78,7 @@ public class CircularOrbit
public static final int TRUE_LONGITUDE_ARGUMENT = 2;
/** Serializable UID. */
- private static final long serialVersionUID = -5031200932453701026L;
+ private static final long serialVersionUID = 5042463409964008691L;
/** Semi-major axis (m). */
private final double a;
@@ -133,10 +133,10 @@ public class CircularOrbit
switch (type) {
case MEAN_LONGITUDE_ARGUMENT :
- this.alphaV = computeAlphaM(alpha);
+ this.alphaV = eccentricToTrue(meanToEccentric(alpha));
break;
case ECCENTRIC_LONGITUDE_ARGUMENT :
- this.alphaV = computeAlphaE(alpha);
+ this.alphaV = eccentricToTrue(alpha);
break;
case TRUE_LONGITUDE_ARGUMENT :
this.alphaV = alpha;
@@ -171,6 +171,12 @@ public class CircularOrbit
final double r = pvP.getNorm();
final double V2 = pvV.getNormSq();
final double rV2OnMu = r * V2 / mu;
+
+ if (rV2OnMu > 2) {
+ throw OrekitException.createIllegalArgumentException(
+ OrekitMessages.HYPERBOLIC_ORBIT_NOT_HANDLED_AS, getClass().getName());
+ }
+
a = r / (2 - rV2OnMu);
// compute inclination
@@ -188,10 +194,11 @@ public class CircularOrbit
final double sinRaan = FastMath.sin(raan);
final double cosI = FastMath.cos(i);
final double sinI = FastMath.sin(i);
- final Vector3D rVec = new Vector3D(cosRaan, FastMath.sin(raan), 0);
- final Vector3D sVec = new Vector3D(-cosI * sinRaan, cosI * cosRaan, sinI);
- final double x2 = Vector3D.dotProduct(pvP, rVec) / a;
- final double y2 = Vector3D.dotProduct(pvP, sVec) / a;
+ final double xP = pvP.getX();
+ final double yP = pvP.getY();
+ final double zP = pvP.getZ();
+ final double x2 = (xP * cosRaan + yP * sinRaan) / a;
+ final double y2 = ((yP * cosRaan - xP * sinRaan) * cosI + zP * sinI) / a;
// compute eccentricity vector
final double eSE = Vector3D.dotProduct(pvP, pvV) / FastMath.sqrt(mu * a);
@@ -206,7 +213,7 @@ public class CircularOrbit
// compute longitude argument
final double beta = 1 / (1 + FastMath.sqrt(1 - ex * ex - ey * ey));
- alphaV = computeAlphaE(FastMath.atan2(y2 + ey + eSE * beta * ex, x2 + ex - eSE * beta * ey));
+ alphaV = eccentricToTrue(FastMath.atan2(y2 + ey + eSE * beta * ex, x2 + ex - eSE * beta * ey));
}
/** Constructor from any kind of orbital parameters.
@@ -293,11 +300,11 @@ public class CircularOrbit
(epsilon + 1 + ex * cosAlphaV + ey * sinAlphaV));
}
- /** Computes the eccentric longitude argument.
+ /** Computes the true longitude argument from the eccentric longitude argument.
* @param alphaE = E + ω eccentric longitude argument (rad)
* @return the true longitude argument.
*/
- private double computeAlphaE(final double alphaE) {
+ private double eccentricToTrue(final double alphaE) {
final double epsilon = FastMath.sqrt(1 - ex * ex - ey * ey);
final double cosAlphaE = FastMath.cos(alphaE);
final double sinAlphaE = FastMath.sin(alphaE);
@@ -313,23 +320,23 @@ public class CircularOrbit
return alphaE - ex * FastMath.sin(alphaE) + ey * FastMath.cos(alphaE);
}
- /** Computes the mean longitude argument.
+ /** Computes the eccentric longitude argument from the mean longitude argument.
* @param alphaM = M + ω mean longitude argument (rad)
- * @return the true longitude argument.
+ * @return the eccentric longitude argument.
*/
- private double computeAlphaM(final double alphaM) {
- // Generalization of Kepler equation to equinoctial parameters
+ private double meanToEccentric(final double alphaM) {
+ // Generalization of Kepler equation to circular parameters
// with alphaE = PA + E and
// alphaM = PA + M = alphaE - ex.sin(alphaE) + ey.cos(alphaE)
- double alphaE = alphaM;
- double shift = 0.0;
+ double alphaE = alphaM;
+ double shift = 0.0;
double alphaEMalphaM = 0.0;
- double cosLE = FastMath.cos(alphaE);
- double sinLE = FastMath.sin(alphaE);
- int iter = 0;
+ double cosAlphaE = FastMath.cos(alphaE);
+ double sinAlphaE = FastMath.sin(alphaE);
+ int iter = 0;
do {
- final double f2 = ex * sinLE - ey * cosLE;
- final double f1 = 1.0 - ex * cosLE - ey * sinLE;
+ final double f2 = ex * sinAlphaE - ey * cosAlphaE;
+ final double f1 = 1.0 - ex * cosAlphaE - ey * sinAlphaE;
final double f0 = alphaEMalphaM - f2;
final double f12 = 2.0 * f1;
@@ -337,12 +344,12 @@ public class CircularOrbit
alphaEMalphaM -= shift;
alphaE = alphaM + alphaEMalphaM;
- cosLE = FastMath.cos(alphaE);
- sinLE = FastMath.sin(alphaE);
+ cosAlphaE = FastMath.cos(alphaE);
+ sinAlphaE = FastMath.sin(alphaE);
} while ((++iter < 50) && (FastMath.abs(shift) > 1.0e-12));
- return computeAlphaE(alphaE); // which set the alphaV parameter
+ return alphaE;
}
@@ -388,6 +395,59 @@ public class CircularOrbit
return getAlphaM() + raan;
}
+ /** {@inheritDoc} */
+ protected PVCoordinates initPVCoordinates() {
+
+ // get equinoctial parameters
+ final double equEx = getEquinoctialEx();
+ final double equEy = getEquinoctialEy();
+ final double hx = getHx();
+ final double hy = getHy();
+ final double lE = getLE();
+
+ // inclination-related intermediate parameters
+ final double hx2 = hx * hx;
+ final double hy2 = hy * hy;
+ final double factH = 1. / (1 + hx2 + hy2);
+
+ // reference axes defining the orbital plane
+ final double ux = (1 + hx2 - hy2) * factH;
+ final double uy = 2 * hx * hy * factH;
+ final double uz = -2 * hy * factH;
+
+ final double vx = uy;
+ final double vy = (1 - hx2 + hy2) * factH;
+ final double vz = 2 * hx * factH;
+
+ // eccentricity-related intermediate parameters
+ final double exey = equEx * equEy;
+ final double ex2 = equEx * equEx;
+ final double ey2 = equEy * equEy;
+ final double e2 = ex2 + ey2;
+ final double eta = 1 + FastMath.sqrt(1 - e2);
+ final double beta = 1. / eta;
+
+ // eccentric latitude argument
+ final double cLe = FastMath.cos(lE);
+ final double sLe = FastMath.sin(lE);
+ final double exCeyS = equEx * cLe + equEy * sLe;
+
+ // coordinates of position and velocity in the orbital plane
+ final double x = a * ((1 - beta * ey2) * cLe + beta * exey * sLe - equEx);
+ final double y = a * ((1 - beta * ex2) * sLe + beta * exey * cLe - equEy);
+
+ final double factor = FastMath.sqrt(getMu() / a) / (1 - exCeyS);
+ final double xdot = factor * (-sLe + beta * equEy * exCeyS);
+ final double ydot = factor * ( cLe - beta * equEx * exCeyS);
+
+ final Vector3D position =
+ new Vector3D(x * ux + y * vx, x * uy + y * vy, x * uz + y * vz);
+ final Vector3D velocity =
+ new Vector3D(xdot * ux + ydot * vx, xdot * uy + ydot * vy, xdot * uz + ydot * vz);
+ return new PVCoordinates(position, velocity);
+
+ }
+
/** {@inheritDoc} */
public CircularOrbit shiftedBy(final double dt) {
return new CircularOrbit(a, ex, ey, i, raan,
diff --git a/src/main/java/org/orekit/orbits/EquinoctialOrbit.java b/src/main/java/org/orekit/orbits/EquinoctialOrbit.java
index ded75577dc..b2d96c4e20 100644
--- a/src/main/java/org/orekit/orbits/EquinoctialOrbit.java
+++ b/src/main/java/org/orekit/orbits/EquinoctialOrbit.java
@@ -76,7 +76,7 @@ public class EquinoctialOrbit extends Orbit {
public static final int TRUE_LATITUDE_ARGUMENT = 2;
/** Serializable UID. */
- private static final long serialVersionUID = -1779638201767656602L;
+ private static final long serialVersionUID = -2000712440570076839L;
/** Semi-major axis (m). */
private final double a;
@@ -131,10 +131,10 @@ public class EquinoctialOrbit extends Orbit {
switch (type) {
case MEAN_LATITUDE_ARGUMENT :
- this.lv = computeLM(l);
+ this.lv = eccentricToTrue(meanToEccentric(l));
break;
case ECCENTRIC_LATITUDE_ARGUMENT :
- this.lv = computeLE(l);
+ this.lv = eccentricToTrue(l);
break;
case TRUE_LATITUDE_ARGUMENT :
this.lv = l;
@@ -169,7 +169,11 @@ public class EquinoctialOrbit extends Orbit {
final double r = pvP.getNorm();
final double V2 = pvV.getNormSq();
final double rV2OnMu = r * V2 / mu;
- a = r / (2 - rV2OnMu);
+
+ if (rV2OnMu > 2) {
+ throw OrekitException.createIllegalArgumentException(
+ OrekitMessages.HYPERBOLIC_ORBIT_NOT_HANDLED_AS, getClass().getName());
+ }
// compute inclination vector
final Vector3D w = pvCoordinates.getMomentum().normalize();
@@ -178,19 +182,23 @@ public class EquinoctialOrbit extends Orbit {
hy = d * w.getX();
// compute true latitude argument
- final Vector3D p = pvP;
- final double cLv = (p.getX() - d * p.getZ() * w.getX()) / r;
- final double sLv = (p.getY() - d * p.getZ() * w.getY()) / r;
+ final double cLv = (pvP.getX() - d * pvP.getZ() * w.getX()) / r;
+ final double sLv = (pvP.getY() - d * pvP.getZ() * w.getY()) / r;
lv = FastMath.atan2(sLv, cLv);
+
+ // compute semi-major axis
+ a = r / (2 - rV2OnMu);
+
// compute eccentricity vector
- final double eSE = Vector3D.dotProduct(p, pvV) / FastMath.sqrt(mu * a);
+ final double eSE = Vector3D.dotProduct(pvP, pvV) / FastMath.sqrt(mu * a);
final double eCE = rV2OnMu - 1;
final double e2 = eCE * eCE + eSE * eSE;
final double f = eCE - e2;
final double g = FastMath.sqrt(1 - e2) * eSE;
ex = a * (f * cLv + g * sLv) / r;
ey = a * (f * sLv - g * cLv) / r;
+
}
/** Constructor from any kind of orbital parameters.
@@ -260,16 +268,16 @@ public class EquinoctialOrbit extends Orbit {
return lv + 2 * FastMath.atan(num / den);
}
- /** Computes the eccentric latitude argument.
+ /** Computes the true latitude argument from the eccentric latitude argument.
* @param lE = E + ω + Ω eccentric latitude argument (rad)
* @return the true latitude argument
*/
- private double computeLE(final double lE) {
+ private double eccentricToTrue(final double lE) {
final double epsilon = FastMath.sqrt(1 - ex * ex - ey * ey);
final double cosLE = FastMath.cos(lE);
final double sinLE = FastMath.sin(lE);
- final double num = ex * sinLE - ey * cosLE;
- final double den = epsilon + 1 - ex * cosLE - ey * sinLE;
+ final double num = ex * sinLE - ey * cosLE;
+ final double den = epsilon + 1 - ex * cosLE - ey * sinLE;
return lE + 2 * FastMath.atan(num / den);
}
@@ -281,11 +289,11 @@ public class EquinoctialOrbit extends Orbit {
return lE - ex * FastMath.sin(lE) + ey * FastMath.cos(lE);
}
- /** Computes the mean latitude argument.
+ /** Computes the eccentric latitude argument from the mean latitude argument.
* @param lM = M + ω + Ω mean latitude argument (rad)
- * @return the true latitude argument
+ * @return the eccentric latitude argument
*/
- private double computeLM(final double lM) {
+ private double meanToEccentric(final double lM) {
// Generalization of Kepler equation to equinoctial parameters
// with lE = PA + RAAN + E and
// lM = PA + RAAN + M = lE - ex.sin(lE) + ey.cos(lE)
@@ -310,7 +318,7 @@ public class EquinoctialOrbit extends Orbit {
} while ((++iter < 50) && (FastMath.abs(shift) > 1.0e-12));
- return computeLE(lE); // which set the lv parameter
+ return lE;
}
@@ -328,6 +336,55 @@ public class EquinoctialOrbit extends Orbit {
return 2 * FastMath.atan(FastMath.sqrt(hx * hx + hy * hy));
}
+ /** {@inheritDoc} */
+ protected PVCoordinates initPVCoordinates() {
+
+ // get equinoctial parameters
+ final double lE = getLE();
+
+ // inclination-related intermediate parameters
+ final double hx2 = hx * hx;
+ final double hy2 = hy * hy;
+ final double factH = 1. / (1 + hx2 + hy2);
+
+ // reference axes defining the orbital plane
+ final double ux = (1 + hx2 - hy2) * factH;
+ final double uy = 2 * hx * hy * factH;
+ final double uz = -2 * hy * factH;
+
+ final double vx = uy;
+ final double vy = (1 - hx2 + hy2) * factH;
+ final double vz = 2 * hx * factH;
+
+ // eccentricity-related intermediate parameters
+ final double exey = ex * ey;
+ final double ex2 = ex * ex;
+ final double ey2 = ey * ey;
+ final double e2 = ex2 + ey2;
+ final double eta = 1 + FastMath.sqrt(1 - e2);
+ final double beta = 1. / eta;
+
+ // eccentric latitude argument
+ final double cLe = FastMath.cos(lE);
+ final double sLe = FastMath.sin(lE);
+ final double exCeyS = ex * cLe + ey * sLe;
+
+ // coordinates of position and velocity in the orbital plane
+ final double x = a * ((1 - beta * ey2) * cLe + beta * exey * sLe - ex);
+ final double y = a * ((1 - beta * ex2) * sLe + beta * exey * cLe - ey);
+
+ final double factor = FastMath.sqrt(getMu() / a) / (1 - exCeyS);
+ final double xdot = factor * (-sLe + beta * ey * exCeyS);
+ final double ydot = factor * ( cLe - beta * ex * exCeyS);
+
+ final Vector3D position =
+ new Vector3D(x * ux + y * vx, x * uy + y * vy, x * uz + y * vz);
+ final Vector3D velocity =
+ new Vector3D(xdot * ux + ydot * vx, xdot * uy + ydot * vy, xdot * uz + ydot * vz);
+ return new PVCoordinates(position, velocity);
+
+ }
+
/** {@inheritDoc} */
public EquinoctialOrbit shiftedBy(final double dt) {
return new EquinoctialOrbit(a, ex, ey, hx, hy,
diff --git a/src/main/java/org/orekit/orbits/KeplerianOrbit.java b/src/main/java/org/orekit/orbits/KeplerianOrbit.java
index ddbecdab78..5ea68d580b 100644
--- a/src/main/java/org/orekit/orbits/KeplerianOrbit.java
+++ b/src/main/java/org/orekit/orbits/KeplerianOrbit.java
@@ -18,6 +18,7 @@ package org.orekit.orbits;
import org.apache.commons.math.geometry.Vector3D;
import org.apache.commons.math.util.FastMath;
+import org.apache.commons.math.util.MathUtils;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitMessages;
import org.orekit.frames.Frame;
@@ -42,6 +43,10 @@ import org.orekit.utils.PVCoordinates;
* Right Ascension of the Ascending Node and v stands for the true anomaly.
* </p>
* <p>
+ * This class supports hyperbolic orbits, using the convention that semi major
+ * axis is negative for such orbits (and of course eccentricity is greater than 1).
+ * </p>
+ * <p>
* When orbit is either equatorial or circular, some keplerian elements
* (more precisely ω and Ω) become ambiguous so this class should not
* be used for such orbits. For this reason, {@link EquinoctialOrbit equinoctial
@@ -78,7 +83,21 @@ public class KeplerianOrbit extends Orbit {
public static final double E_CIRC = 1.e-10;
/** Serializable UID. */
- private static final long serialVersionUID = -8628129146897296527L;
+ private static final long serialVersionUID = 2077785958734298873L;
+
+ /** First coefficient to compute Kepler equation solver starter. */
+ private static final double A;
+
+ /** Second coefficient to compute Kepler equation solver starter. */
+ private static final double B;
+
+ static {
+ final double k1 = 3 * FastMath.PI + 2;
+ final double k2 = FastMath.PI - 1;
+ final double k3 = 6 * FastMath.PI - 1;
+ A = 3 * k2 * k2 / k1;
+ B = k3 * k3 / (6 * k1);
+ }
/** Semi-major axis (m). */
private final double a;
@@ -99,7 +118,7 @@ public class KeplerianOrbit extends Orbit {
private final double v;
/** Creates a new instance.
- * @param a semi-major axis (m)
+ * @param a semi-major axis (m), negative for hyperbolic orbits
* @param e eccentricity
* @param i inclination (rad)
* @param pa perigee argument (ω, rad)
@@ -125,6 +144,11 @@ public class KeplerianOrbit extends Orbit {
final Frame frame, final AbsoluteDate date, final double mu)
throws IllegalArgumentException {
super(frame, date, mu);
+
+ if (a * (1 - e) < 0) {
+ throw OrekitException.createIllegalArgumentException(OrekitMessages.ORBIT_A_E_MISMATCH_WITH_CONIC_TYPE, a, e);
+ }
+
this.a = a;
this.e = e;
this.i = i;
@@ -133,10 +157,14 @@ public class KeplerianOrbit extends Orbit {
switch (type) {
case MEAN_ANOMALY :
- this.v = computeMeanAnomaly(anomaly);
+ this.v = (a < 0) ?
+ hyperbolicEccentricToTrue(meanToHyperbolicEccentric(anomaly)) :
+ ellipticEccentricToTrue(meanToEllipticEccentric(anomaly));
break;
case ECCENTRIC_ANOMALY :
- this.v = computeEccentricAnomaly(anomaly);
+ this.v = (a < 0) ?
+ hyperbolicEccentricToTrue(anomaly) :
+ ellipticEccentricToTrue(anomaly);
break;
case TRUE_ANOMALY :
this.v = anomaly;
@@ -164,20 +192,6 @@ public class KeplerianOrbit extends Orbit {
throws IllegalArgumentException {
super(pvCoordinates, frame, date, mu);
- // compute semi-major axis
- final Vector3D pvP = pvCoordinates.getPosition();
- final Vector3D pvV = pvCoordinates.getVelocity();
- final double r = pvP.getNorm();
- final double V2 = pvV.getNormSq();
- final double rV2OnMu = r * V2 / mu;
- a = r / (2 - rV2OnMu);
-
- // compute eccentricity
- final double muA = mu * a;
- final double eSE = Vector3D.dotProduct(pvP, pvV) / FastMath.sqrt(muA);
- final double eCE = rV2OnMu - 1;
- e = FastMath.sqrt(eSE * eSE + eCE * eCE);
-
// compute inclination
final Vector3D momentum = pvCoordinates.getMomentum();
final double m2 = Vector3D.dotProduct(momentum, momentum);
@@ -189,36 +203,50 @@ public class KeplerianOrbit extends Orbit {
// the following comparison with 0 IS REALLY numerically justified and stable
raan = (n2 == 0) ? 0 : FastMath.atan2(node.getY(), node.getX());
+ // preliminary computations for parameters depending on orbit shape (elliptic or hyperbolic)
+ final Vector3D pvP = pvCoordinates.getPosition();
+ final Vector3D pvV = pvCoordinates.getVelocity();
+ final double r = pvP.getNorm();
+ final double V2 = pvV.getNormSq();
+ final double rV2OnMu = r * V2 / mu;
+
+ // compute semi-major axis (will be negative for hyperbolic orbits)
+ a = r / (2 - rV2OnMu);
+
+ // compute eccentricity (will be larger than 1 for hyperbolic orbits)
+ final double muA = mu * a;
+ e = FastMath.sqrt(1 - m2 / muA);
+
// compute true anomaly
- if (e < E_CIRC) {
- v = 0;
+ if (a > 0) {
+ if (e < E_CIRC) {
+ // circular orbit
+ v = 0;
+ } else {
+ // elliptic orbit
+ final double eSE = Vector3D.dotProduct(pvP, pvV) / FastMath.sqrt(muA);
+ final double eCE = rV2OnMu - 1;
+ v = ellipticEccentricToTrue(FastMath.atan2(eSE, eCE));
+ }
} else {
- final double E = FastMath.atan2(eSE, eCE);
- final double k = 1 / (1 + FastMath.sqrt(m2 / muA));
- v = E + 2 * FastMath.atan(k * eSE / (1 - k * eCE));
+ // hyperbolic orbit
+ final double eSH = Vector3D.dotProduct(pvP, pvV) / FastMath.sqrt(-muA);
+ final double eCH = rV2OnMu - 1;
+ v = hyperbolicEccentricToTrue(FastMath.log((eCH + eSH) / (eCH - eSH)) / 2);
}
// compute perigee argument
- final double cosRaan = FastMath.cos(raan);
- final double sinRaan = FastMath.sin(raan);
- final double px = cosRaan * pvP.getX() +
- sinRaan * pvP.getY();
- final double py = FastMath.cos(i) * (cosRaan * pvP.getY() - sinRaan * pvP.getX()) +
- FastMath.sin(i) * pvP.getZ();
+ final double px = Vector3D.dotProduct(pvP, node);
+ final double py = Vector3D.dotProduct(pvP, Vector3D.crossProduct(momentum, node)) / FastMath.sqrt(m2);
pa = FastMath.atan2(py, px) - v;
+
}
/** Constructor from any kind of orbital parameters.
* @param op orbital parameters to copy
*/
public KeplerianOrbit(final Orbit op) {
- super(op.getFrame(), op.getDate(), op.getMu());
- a = op.getA();
- e = op.getE();
- i = op.getI();
- raan = FastMath.atan2(op.getHy(), op.getHx());
- pa = FastMath.atan2(op.getEquinoctialEy(), op.getEquinoctialEx()) - raan;
- v = op.getLv() - (pa + raan);
+ this(op.getPVCoordinates(), op.getFrame(), op.getDate(), op.getMu());
}
/** Get the semi-major axis.
@@ -267,52 +295,165 @@ public class KeplerianOrbit extends Orbit {
* @return eccentric anomaly (rad)
*/
public double getEccentricAnomaly() {
+ if (a < 0) {
+ // hyperbolic case
+ final double t = FastMath.sqrt((e - 1) / (e + 1)) * FastMath.tan(v / 2);
+ return FastMath.log((1 + t) / (1 - t));
+ }
+
+ // elliptic case
final double beta = e / (1 + FastMath.sqrt((1 - e) * (1 + e)));
return v - 2 * FastMath.atan(beta * FastMath.sin(v) / (1 + beta * FastMath.cos(v)));
+
}
- /** Computes the eccentric anomaly.
+ /** Computes the true anomaly from the elliptic eccentric anomaly.
* @param E eccentric anomaly (rad)
* @return v the true anomaly
*/
- private double computeEccentricAnomaly (final double E) {
+ private double ellipticEccentricToTrue(final double E) {
final double beta = e / (1 + FastMath.sqrt((1 - e) * (1 + e)));
return E + 2 * FastMath.atan(beta * FastMath.sin(E) / (1 - beta * FastMath.cos(E)));
}
+ /** Computes the true anomaly from the hyperbolic eccentric anomaly.
+ * @param H hyperbolic eccentric anomaly (rad)
+ * @return v the true anomaly
+ */
+ private double hyperbolicEccentricToTrue(final double H) {
+ return 2 * FastMath.atan(FastMath.sqrt((e + 1) / (e - 1)) * FastMath.tanh(H / 2));
+ }
+
/** Get the mean anomaly.
* @return mean anomaly (rad)
*/
public double getMeanAnomaly() {
+
+ if (a < 0) {
+ // hyperbolic case
+ final double H = getEccentricAnomaly();
+ return e * FastMath.sinh(H) - H;
+ }
+
+ // elliptic case
final double E = getEccentricAnomaly();
return E - e * FastMath.sin(E);
+
}
- /** Computes the mean anomaly.
+ /** Computes the elliptic eccentric anomaly from the mean anomaly.
+ * <p>
+ * The algorithm used here for solving Kepler equation has been published
+ * in: "Procedures for solving Kepler's Equation", A. W. Odell and
+ * R. H. Gooding, Celestial Mechanics 38 (1986) 307-334
+ * </p>
* @param M mean anomaly (rad)
* @return v the true anomaly
*/
- private double computeMeanAnomaly (final double M) {
+ private double meanToEllipticEccentric(final double M) {
+
+ // reduce M to [-PI PI) interval
+ final double reducedM = MathUtils.normalizeAngle(M, 0.0);
+
+ // compute start value according to A. W. Odell and R. H. Gooding S12 starter
+ double E;
+ if (FastMath.abs(reducedM) < 1.0 / 6.0) {
+ E = reducedM + e * (FastMath.cbrt(6 * reducedM) - reducedM);
+ } else {
+ if (reducedM < 0) {
+ final double w = FastMath.PI + reducedM;
+ E = reducedM + e * (A * w / (B - w) - FastMath.PI - reducedM);
+ } else {
+ final double w = FastMath.PI - reducedM;
+ E = reducedM + e * (FastMath.PI - A * w / (B - w) - reducedM);
+ }
+ }
+
+ final double e1 = 1 - e;
+ final boolean noCancellationRisk = (e1 + E * E / 6) >= 0.1;
+
+ // perform two iterations, each consisting of one Halley step and one Newton-Raphson step
+ for (int j = 0; j < 2; ++j) {
+ double f;
+ double fd;
+ final double fdd = e * FastMath.sin(E);
+ final double fddd = e * FastMath.cos(E);
+ if (noCancellationRisk) {
+ f = (E - fdd) - reducedM;
+ fd = 1 - fddd;
+ } else {
+ f = eMeSinE(E) - reducedM;
+ final double s = FastMath.sin(0.5 * E);
+ fd = e1 + 2 * e * s * s;
+ }
+ final double dee = f * fd / (0.5 * f * fdd - fd * fd);
+
+ // update eccentric anomaly, using expressions that limit underflow problems
+ final double w = fd + 0.5 * dee * (fdd + dee * fddd / 3);
+ fd += dee * (fdd + 0.5 * dee * fddd);
+ E -= (f - dee * (fd - w)) / fd;
+
+ }
- // resolution of Kepler equation for keplerian parameters
- double E = M;
+ // expand the result back to original range
+ E += M - reducedM;
+
+ return E;
+
+ }
+
+ /** Accurate computation of E - e sin(E).
+ * <p>
+ * This method is used when E is close to 0 and e close to 1,
+ * i.e. near the perigee of almost parabolic orbits
+ * </p>
+ * @param E eccentric anomaly
+ * @return E - e sin(E)
+ */
+ private double eMeSinE(final double E) {
+ double x = (1 - e) * FastMath.sin(E);
+ final double mE2 = -E * E;
+ double term = E;
+ double d = 0;
+ // the inequality test below IS intentional and should NOT be replaced by a check with a small tolerance
+ for (double x0 = Double.NaN; x != x0;) {
+ d += 2;
+ term *= mE2 / (d * (d + 1));
+ x0 = x;
+ x = x - term;
+ }
+ return x;
+ }
+
+ /** Computes the hyperbolic eccentric anomaly from the mean anomaly.
+ * <p>
+ * The algorithm used here for solving hyperbolic Kepler equation is
+ * a naive initialization and classical Halley method for iterations.
+ * </p>
+ * @param M mean anomaly (rad)
+ * @return v the true anomaly
+ */
+ private double meanToHyperbolicEccentric(final double M) {
+
+ // resolution of hyperbolic Kepler equation for keplerian parameters
+ double H = -M;
double shift = 0.0;
- double EmM = 0.0;
- int iter = 0;
+ double HpM = 0.0;
+ int iter = 0;
do {
- final double f2 = e * FastMath.sin(E);
- final double f1 = 1.0 - e * FastMath.cos(E);
- final double f0 = EmM - f2;
+ final double f2 = e * FastMath.sinh(H);
+ final double f1 = e * FastMath.cosh(H) - 1;
+ final double f0 = f2 - HpM;
final double f12 = 2 * f1;
shift = f0 * f12 / (f1 * f12 - f0 * f2);
- EmM -= shift;
- E = M + EmM;
+ HpM -= shift;
+ H = HpM - M;
} while ((++iter < 50) && (FastMath.abs(shift) > 1.0e-12));
- return computeEccentricAnomaly(E);
+ return H;
}
@@ -334,6 +475,10 @@ public class KeplerianOrbit extends Orbit {
* @return first component of the inclination vector.
*/
public double getHx() {
+ // Check for equatorial retrograde orbit
+ if (FastMath.abs(i - FastMath.PI) < 1.0e-10) {
+ return Double.NaN;
+ }
return FastMath.cos(raan) * FastMath.tan(i / 2);
}
@@ -341,6 +486,10 @@ public class KeplerianOrbit extends Orbit {
* @return second component of the inclination vector.
*/
public double getHy() {
+ // Check for equatorial retrograde orbit
+ if (FastMath.abs(i - FastMath.PI) < 1.0e-10) {
+ return Double.NaN;
+ }
return FastMath.sin(raan) * FastMath.tan(i / 2);
}
@@ -365,6 +514,79 @@ public class KeplerianOrbit extends Orbit {
return pa + raan + getMeanAnomaly();
}
+ /** {@inheritDoc} */
+ protected PVCoordinates initPVCoordinates() {
+
+ // preliminary variables
+ final double cosRaan = FastMath.cos(raan);
+ final double sinRaan = FastMath.sin(raan);
+ final double cosPa = FastMath.cos(pa);
+ final double sinPa = FastMath.sin(pa);
+ final double cosI = FastMath.cos(i);
+ final double sinI = FastMath.sin(i);
+
+ final double crcp = cosRaan * cosPa;
+ final double crsp = cosRaan * sinPa;
+ final double srcp = sinRaan * cosPa;
+ final double srsp = sinRaan * sinPa;
+
+ // reference axes defining the orbital plane
+ final Vector3D p = new Vector3D( crcp - cosI * srsp, srcp + cosI * crsp, sinI * sinPa);
+ final Vector3D q = new Vector3D(-crsp - cosI * srcp, -srsp + cosI * crcp, sinI * cosPa);
+
+ return (a > 0) ? initPVCoordinatesElliptical(p, q) : initPVCoordinatesHyperbolic(p, q);
+
+ }
+
+ /** Initialize the position/velocity coordinates, elliptic case.
+ * @param p unit vector in the orbital plane pointing towards perigee
+ * @param q unit vector in the orbital plane in quadrature with q
+ * @return computed position/velocity coordinates
+ */
+ private PVCoordinates initPVCoordinatesElliptical(final Vector3D p, final Vector3D q) {
+
+ // elliptic eccentric anomaly
+ final double uME2 = (1 - e) * (1 + e);
+ final double s1Me2 = FastMath.sqrt(uME2);
+ final double E = getEccentricAnomaly();
+ final double cosE = FastMath.cos(E);
+ final double sinE = FastMath.sin(E);
+
+ // coordinates of position and velocity in the orbital plane
+ final double x = a * (cosE - e);
+ final double y = a * sinE * s1Me2;
+ final double factor = FastMath.sqrt(getMu() / a) / (1 - e * cosE);
+ final double xDot = -sinE * factor;
+ final double yDot = cosE * s1Me2 * factor;
+
+ return new PVCoordinates(new Vector3D(x, p, y, q), new Vector3D(xDot, p, yDot, q));
+
+ }
+
+ /** Initialize the position/velocity coordinates, hyperbolic case.
+ * @param p unit vector in the orbital plane pointing towards perigee
+ * @param q unit vector in the orbital plane in quadrature with q
+ * @return computed position/velocity coordinates
+ */
+ private PVCoordinates initPVCoordinatesHyperbolic(final Vector3D p, final Vector3D q) {
+
+ // hyperbolic eccentric anomaly
+ final double h = getEccentricAnomaly();
+ final double cH = FastMath.cosh(h);
+ final double sH = FastMath.sinh(h);
+ final double sE2m1 = FastMath.sqrt((e - 1) * (e + 1));
+
+ // coordinates of position and velocity in the orbital plane
+ final double x = a * (cH - e);
+ final double y = -a * sE2m1 * sH;
+ final double factor = FastMath.sqrt(getMu() / -a) / (e * cH - 1);
+ final double xDot = -factor * sH;
+ final double yDot = factor * sE2m1 * cH;
+
+ return new PVCoordinates(new Vector3D(x, p, y, q), new Vector3D(xDot, p, yDot, q));
+
+ }
+
/** {@inheritDoc} */
public KeplerianOrbit shiftedBy(final double dt) {
return new KeplerianOrbit(a, e, i, pa, raan,
diff --git a/src/main/java/org/orekit/orbits/Orbit.java b/src/main/java/org/orekit/orbits/Orbit.java
index 8583335706..d20563b70a 100644
--- a/src/main/java/org/orekit/orbits/Orbit.java
+++ b/src/main/java/org/orekit/orbits/Orbit.java
@@ -18,9 +18,7 @@ package org.orekit.orbits;
import java.io.Serializable;
-import org.apache.commons.math.geometry.Vector3D;
import org.apache.commons.math.util.FastMath;
-import org.apache.commons.math.util.MathUtils;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitMessages;
import org.orekit.frames.Frame;
@@ -63,7 +61,7 @@ import org.orekit.utils.PVCoordinates;
public abstract class Orbit implements TimeStamped, Serializable {
/** Serializable UID. */
- private static final long serialVersionUID = -5391613859481554640L;
+ private static final long serialVersionUID = 438733454597999578L;
/** Frame in which are defined the orbital parameters. */
private final Frame frame;
@@ -136,6 +134,7 @@ public abstract class Orbit implements TimeStamped, Serializable {
}
/** Get the semi-major axis.
+ * <p>Note that the semi-major axis is considered negative for hyperbolic orbits.</p>
* @return semi-major axis (m)
*/
public abstract double getA();
@@ -197,11 +196,11 @@ public abstract class Orbit implements TimeStamped, Serializable {
/** Get the keplerian period.
* <p>The keplerian period is computed directly from semi major axis
* and central acceleration constant.</p>
- * @return keplerian period in seconds
+ * @return keplerian period in seconds, or positive infinity for hyperbolic orbits
*/
public double getKeplerianPeriod() {
final double a = getA();
- return MathUtils.TWO_PI * a * FastMath.sqrt(a / mu);
+ return (a < 0) ? Double.POSITIVE_INFINITY : 2.0 * FastMath.PI * a * FastMath.sqrt(a / mu);
}
/** Get the keplerian mean motion.
@@ -210,8 +209,8 @@ public abstract class Orbit implements TimeStamped, Serializable {
* @return keplerian mean motion in radians per second
*/
public double getKeplerianMeanMotion() {
- final double a = getA();
- return FastMath.sqrt(mu / a) / a;
+ final double absA = FastMath.abs(getA());
+ return FastMath.sqrt(mu / absA) / absA;
}
/** Get the date of orbital parameters.
@@ -221,7 +220,7 @@ public abstract class Orbit implements TimeStamped, Serializable {
return date;
}
- /** Get the {@link PVCoordinates}.
+ /** Get the {@link PVCoordinates} in a specified frame.
* @param outputFrame frame in which the position/velocity coordinates shall be computed
* @return pvCoordinates in the specified output frame
* @exception OrekitException if transformation between frames cannot be computed
@@ -230,7 +229,7 @@ public abstract class Orbit implements TimeStamped, Serializable {
public PVCoordinates getPVCoordinates(final Frame outputFrame)
throws OrekitException {
if (pvCoordinates == null) {
- initPVCoordinates();
+ pvCoordinates = initPVCoordinates();
}
// If output frame requested is the same as definition frame,
@@ -250,65 +249,15 @@ public abstract class Orbit implements TimeStamped, Serializable {
*/
public PVCoordinates getPVCoordinates() {
if (pvCoordinates == null) {
- initPVCoordinates();
+ pvCoordinates = initPVCoordinates();
}
return pvCoordinates;
}
- /** Initialize the position/velocity coordinates.
+ /** Compute the position/velocity coordinates from the canonical parameters.
+ * @return computed position/velocity coordinates
*/
- private void initPVCoordinates() {
-
- // get equinoctial parameters
- final double a = getA();
- final double ex = getEquinoctialEx();
- final double ey = getEquinoctialEy();
- final double hx = getHx();
- final double hy = getHy();
- final double lE = getLE();
-
- // inclination-related intermediate parameters
- final double hx2 = hx * hx;
- final double hy2 = hy * hy;
- final double factH = 1. / (1 + hx2 + hy2);
-
- // reference axes defining the orbital plane
- final double ux = (1 + hx2 - hy2) * factH;
- final double uy = 2 * hx * hy * factH;
- final double uz = -2 * hy * factH;
-
- final double vx = uy;
- final double vy = (1 - hx2 + hy2) * factH;
- final double vz = 2 * hx * factH;
-
- // eccentricity-related intermediate parameters
- final double exey = ex * ey;
- final double ex2 = ex * ex;
- final double ey2 = ey * ey;
- final double e2 = ex2 + ey2;
- final double eta = 1 + FastMath.sqrt(1 - e2);
- final double beta = 1. / eta;
-
- // eccentric latitude argument
- final double cLe = FastMath.cos(lE);
- final double sLe = FastMath.sin(lE);
- final double exCeyS = ex * cLe + ey * sLe;
-
- // coordinates of position and velocity in the orbital plane
- final double x = a * ((1 - beta * ey2) * cLe + beta * exey * sLe - ex);
- final double y = a * ((1 - beta * ex2) * sLe + beta * exey * cLe - ey);
-
- final double factor = FastMath.sqrt(mu / a) / (1 - exCeyS);
- final double xdot = factor * (-sLe + beta * ey * exCeyS);
- final double ydot = factor * ( cLe - beta * ex * exCeyS);
-
- final Vector3D position =
- new Vector3D(x * ux + y * vx, x * uy + y * vy, x * uz + y * vz);
- final Vector3D velocity =
- new Vector3D(xdot * ux + ydot * vx, xdot * uy + ydot * vy, xdot * uz + ydot * vz);
- pvCoordinates = new PVCoordinates(position, velocity);
-
- }
+ protected abstract PVCoordinates initPVCoordinates();
/** Get a time-shifted orbit.
* <p>
diff --git a/src/main/java/org/orekit/propagation/SpacecraftState.java b/src/main/java/org/orekit/propagation/SpacecraftState.java
index 29b1d823f8..3af432e63c 100644
--- a/src/main/java/org/orekit/propagation/SpacecraftState.java
+++ b/src/main/java/org/orekit/propagation/SpacecraftState.java
@@ -160,9 +160,9 @@ public class SpacecraftState implements TimeStamped, Serializable {
* that these results may be different for other orbits.
* </p>
* <table border="1" cellpadding="5">
- * <tr bgcolor="#ccccff"><font size="+3"><th>interpolation time (s)</th>
+ * <tr bgcolor="#ccccff"><th>interpolation time (s)</th>
* <th>position error (m)</th><th>velocity error (m/s)</th>
- * <th>attitude error (°)</th></font></tr>
+ * <th>attitude error (°)</th></tr>
* <tr><td bgcolor="#eeeeff"> 60</td><td> 20</td><td>1</td><td>0.001</td></tr>
* <tr><td bgcolor="#eeeeff">120</td><td> 100</td><td>2</td><td>0.002</td></tr>
* <tr><td bgcolor="#eeeeff">300</td><td> 600</td><td>4</td><td>0.005</td></tr>
diff --git a/src/main/java/org/orekit/propagation/events/AdaptedEventDetector.java b/src/main/java/org/orekit/propagation/events/AdaptedEventDetector.java
index da28c71409..79454eaf82 100644
--- a/src/main/java/org/orekit/propagation/events/AdaptedEventDetector.java
+++ b/src/main/java/org/orekit/propagation/events/AdaptedEventDetector.java
@@ -18,11 +18,10 @@ package org.orekit.propagation.events;
import org.apache.commons.math.ode.events.EventException;
import org.apache.commons.math.ode.events.EventHandler;
-import org.orekit.attitudes.AttitudeLaw;
import org.orekit.errors.OrekitException;
import org.orekit.frames.Frame;
-import org.orekit.orbits.EquinoctialOrbit;
import org.orekit.propagation.SpacecraftState;
+import org.orekit.propagation.numerical.StateMapper;
import org.orekit.time.AbsoluteDate;
/** Adapt an {@link org.orekit.propagation.events.EventDetector}
@@ -35,6 +34,9 @@ public class AdaptedEventDetector implements EventHandler {
/** Serializable UID. */
private static final long serialVersionUID = -2156830611432730429L;
+ /** Mapper between spacecraft state and simple array. */
+ private StateMapper mapper;
+
/** Underlying event detector. */
private final EventDetector detector;
@@ -47,31 +49,29 @@ public class AdaptedEventDetector implements EventHandler {
/** integrationFrame frame in which integration is performed. */
private final Frame integrationFrame;
- /** attitudeLaw spacecraft attitude law. */
- private final AttitudeLaw attitudeLaw;
-
/** Build a wrapped event detector.
* @param detector event detector to wrap
+ * @param mapper mapper between spacecraft state and simple array
* @param referenceDate reference date from which t is counted
* @param mu central body attraction coefficient (m<sup>3</sup>/s<sup>2</sup>)
* @param integrationFrame frame in which integration is performed
- * @param attitudeLaw spacecraft attitude law
*/
- public AdaptedEventDetector(final EventDetector detector,
+ public AdaptedEventDetector(final EventDetector detector, final StateMapper mapper,
final AbsoluteDate referenceDate, final double mu,
- final Frame integrationFrame, final AttitudeLaw attitudeLaw) {
+ final Frame integrationFrame) {
this.detector = detector;
+ this.mapper = mapper;
this.referenceDate = referenceDate;
this.mu = mu;
this.integrationFrame = integrationFrame;
- this.attitudeLaw = attitudeLaw;
}
/** {@inheritDoc} */
public double g(final double t, final double[] y)
throws EventException {
try {
- return detector.g(mapState(t, y));
+ final AbsoluteDate currentDate = referenceDate.shiftedBy(t);
+ return detector.g(mapper.mapArrayToState(y, currentDate, mu, integrationFrame));
} catch (OrekitException oe) {
throw new EventException(oe);
}
@@ -81,7 +81,10 @@ public class AdaptedEventDetector implements EventHandler {
public int eventOccurred(final double t, final double[] y, final boolean increasing)
throws EventException {
try {
- final int whatNext = detector.eventOccurred(mapState(t, y), increasing);
+ final AbsoluteDate currentDate = referenceDate.shiftedBy(t);
+ final int whatNext = detector.eventOccurred(mapper.mapArrayToState(y, currentDate, mu,
+ integrationFrame),
+ increasing);
switch (whatNext) {
case EventDetector.STOP :
return STOP;
@@ -101,7 +104,9 @@ public class AdaptedEventDetector implements EventHandler {
public void resetState(final double t, final double[] y)
throws EventException {
try {
- final SpacecraftState newState = detector.resetState(mapState(t, y));
+ final AbsoluteDate currentDate = referenceDate.shiftedBy(t);
+ final SpacecraftState newState = detector.resetState(mapper.mapArrayToState(y, currentDate, mu,
+ integrationFrame));
y[0] = newState.getA();
y[1] = newState.getEquinoctialEx();
y[2] = newState.getEquinoctialEy();
@@ -114,26 +119,4 @@ public class AdaptedEventDetector implements EventHandler {
}
}
- /** Convert state array to space dynamics objects
- * ({@link org.orekit.time.AbsoluteDate AbsoluteDate} and
- * ({@link org.orekit.orbits.Orbit OrbitalParameters}).
- * @param t integration time (s)
- * @param y state as a flat array
- * @return state corresponding to the flat array as a space dynamics object
- * @exception OrekitException if attitude law cannot provide state
- */
- private SpacecraftState mapState(final double t, final double [] y)
- throws OrekitException {
-
- // update space dynamics view
- final AbsoluteDate currentDate = referenceDate.shiftedBy(t);
- final EquinoctialOrbit currentOrbit =
- new EquinoctialOrbit(y[0], y[1], y[2], y[3], y[4], y[5],
- EquinoctialOrbit.TRUE_LATITUDE_ARGUMENT,
- integrationFrame, currentDate, mu);
-
- return new SpacecraftState(currentOrbit, attitudeLaw.getAttitude(currentOrbit), y[6]);
-
- }
-
}
diff --git a/src/main/java/org/orekit/propagation/events/EventState.java b/src/main/java/org/orekit/propagation/events/EventState.java
index cd2b41a522..7bea078535 100644
--- a/src/main/java/org/orekit/propagation/events/EventState.java
+++ b/src/main/java/org/orekit/propagation/events/EventState.java
@@ -148,7 +148,9 @@ class EventState implements Serializable {
for (int i = 0; i < n; ++i) {
// evaluate detector value at the end of the substep
- final AbsoluteDate tb = (i == n - 1) ? t1 : start.shiftedBy((i + 1) * h);
+ // TODO this may lead to infinite loops
+ // final AbsoluteDate tb = (i == n - 1) ? t1 : start.shiftedBy((i + 1) * h);
+ final AbsoluteDate tb = start.shiftedBy((i + 1) * h);
interpolator.setInterpolatedDate(tb);
final double gb = detector.g(interpolator.getInterpolatedState());
@@ -195,7 +197,7 @@ class EventState implements Serializable {
}
}
- final double dtRoot = (dtA <= dtB) ? solver.solve(f, dtA, dtB) : solver.solve(f, dtB, dtA);
+ final double dtRoot = (dtA <= dtB) ? solver.solve(1000, f, dtA, dtB) : solver.solve(1000, f, dtB, dtA);
final AbsoluteDate root = t0.shiftedBy(dtRoot);
if ((previousEventTime != null) &&
diff --git a/src/main/java/org/orekit/propagation/events/GroundMaskElevationDetector.java b/src/main/java/org/orekit/propagation/events/GroundMaskElevationDetector.java
index 744325ea6e..e41a5b8bec 100644
--- a/src/main/java/org/orekit/propagation/events/GroundMaskElevationDetector.java
+++ b/src/main/java/org/orekit/propagation/events/GroundMaskElevationDetector.java
@@ -38,14 +38,14 @@ import org.orekit.propagation.SpacecraftState;
* azimuth values, second row with elevation values, as in the following snippet:
* <pre>
* double [][] mask = {
- * {FastMathMath.toRadians(0), FastMath.toRadians(10)},
- * {FastMathMath.toRadians(45), FastMath.toRadians(8)},
- * {FastMathMath.toRadians(90), FastMath.toRadians(6)},
- * {FastMathMath.toRadians(135), FastMath.toRadians(4)},
- * {FastMathMath.toRadians(180), FastMath.toRadians(5)},
- * {FastMathMath.toRadians(225), FastMath.toRadians(6)},
- * {FastMathMath.toRadians(270), FastMath.toRadians(8)},
- * {FastMathMath.toRadians(315), FastMath.toRadians(9)}
+ * {FastMathFastMath.toRadians(0), FastMath.toRadians(10)},
+ * {FastMathFastMath.toRadians(45), FastMath.toRadians(8)},
+ * {FastMathFastMath.toRadians(90), FastMath.toRadians(6)},
+ * {FastMathFastMath.toRadians(135), FastMath.toRadians(4)},
+ * {FastMathFastMath.toRadians(180), FastMath.toRadians(5)},
+ * {FastMathFastMath.toRadians(225), FastMath.toRadians(6)},
+ * {FastMathFastMath.toRadians(270), FastMath.toRadians(8)},
+ * {FastMathFastMath.toRadians(315), FastMath.toRadians(9)}
* };
* </pre>
* </p>
diff --git a/src/main/java/org/orekit/propagation/numerical/AccelerationJacobiansProvider.java b/src/main/java/org/orekit/propagation/numerical/AccelerationJacobiansProvider.java
new file mode 100644
index 0000000000..bdcf843564
--- /dev/null
+++ b/src/main/java/org/orekit/propagation/numerical/AccelerationJacobiansProvider.java
@@ -0,0 +1,51 @@
+/* Copyright 2010 Centre National d'Études Spatiales
+ * Licensed to CS Communication & Systèmes (CS) under one or more
+ * contributor license agreements. See the NOTICE file distributed with
+ * this work for additional information regarding copyright ownership.
+ * CS licenses this file to You under the Apache License, Version 2.0
+ * (the "License"); you may not use this file except in compliance with
+ * the License. You may obtain a copy of the License at
+ *
+ * http://www.apache.org/licenses/LICENSE-2.0
+ *
+ * Unless required by applicable law or agreed to in writing, software
+ * distributed under the License is distributed on an "AS IS" BASIS,
+ * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
+ * See the License for the specific language governing permissions and
+ * limitations under the License.
+ */
+package org.orekit.propagation.numerical;
+
+import org.orekit.errors.OrekitException;
+import org.orekit.forces.Parameterizable;
+import org.orekit.propagation.SpacecraftState;
+
+/**
+ * Interface for computing acceleration jacobians, for the sake of {@link PartialDerivativesEquations
+ * partial derivatives equations}.
+ * @author Luc Maisonobe
+ * @version $Revision$ $Date$
+ */
+public interface AccelerationJacobiansProvider extends Parameterizable {
+
+ /** Compute acceleration derivatives with respect to state parameters.
+ * @param s spacecraft state
+ * @param dAccdPos acceleration derivatives with respect to position
+ * @param dAccdVel acceleration derivatives with respect to velocity
+ * @param dAccdM acceleration derivatives with respect to mass (may be null when
+ * the caller does not need the derivatives with respect to mass)
+ * @exception OrekitException if derivatives cannot be computed
+ */
+ void addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel, double[] dAccdM)
+ throws OrekitException;
+
+ /** Compute acceleration derivatives with respect to additional parameters.
+ * @param s spacecraft state
+ * @param paramName name of the parameter with respect to which derivatives are required
+ * @param dAccdParam acceleration derivatives with respect to specified parameters
+ * @exception OrekitException if derivatives cannot be computed
+ */
+ void addDAccDParam(SpacecraftState s, String paramName, double[] dAccdParam)
+ throws OrekitException;
+
+}
diff --git a/src/main/java/org/orekit/propagation/numerical/AdditionalEquations.java b/src/main/java/org/orekit/propagation/numerical/AdditionalEquations.java
new file mode 100644
index 0000000000..99fbfe064a
--- /dev/null
+++ b/src/main/java/org/orekit/propagation/numerical/AdditionalEquations.java
@@ -0,0 +1,71 @@
+/* Copyright 2010 Centre National d'Études Spatiales
+ * Licensed to CS Communication & Systèmes (CS) under one or more
+ * contributor license agreements. See the NOTICE file distributed with
+ * this work for additional information regarding copyright ownership.
+ * CS licenses this file to You under the Apache License, Version 2.0
+ * (the "License"); you may not use this file except in compliance with
+ * the License. You may obtain a copy of the License at
+ *
+ * http://www.apache.org/licenses/LICENSE-2.0
+ *
+ * Unless required by applicable law or agreed to in writing, software
+ * distributed under the License is distributed on an "AS IS" BASIS,
+ * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
+ * See the License for the specific language governing permissions and
+ * limitations under the License.
+ */
+package org.orekit.propagation.numerical;
+
+import java.io.Serializable;
+
+import org.orekit.errors.OrekitException;
+import org.orekit.propagation.SpacecraftState;
+
+
+/** This interface allows users to add their own differential equations to a numerical propagator.
+ *
+ * <p>
+ * In some cases users may need to integrate some problem-specific equations along with
+ * classical spacecraft equations of motions. One example is optimal control in low
+ * thrust where adjoint parameters linked to the minimized hamiltonian must be integrated.
+ * Another example is formation flying or rendez-vous which use the Clohessy-Whiltshire
+ * equations for the relative motion.
+ * </p>
+ * <p>
+ * This interface allows users to add such equations to a {@link NumericalPropagator numerical
+ * propagator}. Users provide the equations as an implementation of this interface and register
+ * it to the propagator thanks to its {@link
+ * NumericalPropagator#addAdditionalEquations(AdditionalEquations)} method. Several such objects
+ * can be registered with each numerical propagator, but it is recommended to gather in the same
+ * object the sets of parameters which equations can interact on each others states.
+ * </p>
+ * <p>
+ * The additional parameters are gathered in a simple p array. The additional equations compute
+ * the pDot array, which is the time-derivative of the p array. Since the additional parameters
+ * p may also have an influence on the equations of motion themselves (for example an equation
+ * linked to a complex thrust model may induce an acceleration and a mass change), the same
+ * {@link TimeDerivativesEquations time derivatives equations adder} already shared by all force
+ * models to add their contributions is also provided to the additional equations implementation
+ * object. This means these equations can be used as an additional force model if needed. If the
+ * additional parameters have no influence at all on the spacecraft state, this adder can
+ * simply be ignored.
+ * </p>
+ * @see NumericalPropagator
+ * @author Luc Maisonobe
+ * @version $Revision$ $Date$
+ */
+public interface AdditionalEquations extends Serializable {
+
+ /** Compute the derivatives related to the additional parameters.
+ * @param s current state information: date, kinematics, attitude
+ * @param adder object where the contribution of the additional parameters
+ * p to the orbit evolution (accelerations, mass time-derivative) should be added
+ * @param p current value of the additional parameters
+ * @param pDot placeholder where the derivatives of the additional parameters
+ * should be put
+ * @exception OrekitException if some specific error occurs
+ */
+ void computeDerivatives(SpacecraftState s, TimeDerivativesEquations adder,
+ double[] p, double[] pDot) throws OrekitException;
+
+}
diff --git a/src/main/java/org/orekit/propagation/numerical/AdditionalStateAndEquations.java b/src/main/java/org/orekit/propagation/numerical/AdditionalStateAndEquations.java
new file mode 100644
index 0000000000..e9ebcf578b
--- /dev/null
+++ b/src/main/java/org/orekit/propagation/numerical/AdditionalStateAndEquations.java
@@ -0,0 +1,82 @@
+/* Copyright 2010 Centre National d'Études Spatiales
+ * Licensed to CS Communication & Systèmes (CS) under one or more
+ * contributor license agreements. See the NOTICE file distributed with
+ * this work for additional information regarding copyright ownership.
+ * CS licenses this file to You under the Apache License, Version 2.0
+ * (the "License"); you may not use this file except in compliance with
+ * the License. You may obtain a copy of the License at
+ *
+ * http://www.apache.org/licenses/LICENSE-2.0
+ *
+ * Unless required by applicable law or agreed to in writing, software
+ * distributed under the License is distributed on an "AS IS" BASIS,
+ * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
+ * See the License for the specific language governing permissions and
+ * limitations under the License.
+ */
+package org.orekit.propagation.numerical;
+
+
+/** This class is a container for additional state parameters and their associated evolution equation.
+*
+* <p>
+* This object is a container allowing the propagator to keep constant consistency between additional
+* states and the corresponding equations. It allows to set additional state values, get current
+* additional state value and by reference on the associated additional equations.
+* </p>
+* @see NumericalPropagator
+* @see AdditionalEquations
+* @author Luc Maisonobe
+* @version $Revision: 3409 $ $Date: 2010-06-10 15:42:04 +0200 (jeu., 10 juin 2010) $
+*/
+public class AdditionalStateAndEquations {
+
+ /** Additional equations. */
+ private AdditionalEquations addEquations;
+
+ /** Current additional state. */
+ private double[] addState;
+
+ /** Current additional state derivatives. */
+ private double[] addStateDot;
+
+ /** Create a new instance of AdditionalStateAndEquations, based on additional equations definition.
+ * @param addEqu additional equations.
+ */
+ public AdditionalStateAndEquations(final AdditionalEquations addEqu) {
+ this.addEquations = addEqu;
+ }
+
+ /** Get a reference to the current value of the additional state.
+ * <p>The array returned is a true reference to the state array, so it may be used
+ * to store data into it.</>
+ * @return a reference current value of the addditional state.
+ */
+ public double[] getAdditionalState() {
+ return addState;
+ }
+
+ /** Get a reference to the current value of the additional state derivatives.
+ * <p>The array returned is a true reference to the state array, so it may be used
+ * to store data into it.</>
+ * @return a reference current value of the addditional state derivatives.
+ */
+ public double[] getAdditionalStateDot() {
+ return addStateDot;
+ }
+
+ /** Gets the instance of additional equations.
+ * @return current value of the additional equations.
+ */
+ public AdditionalEquations getAdditionalEquations() {
+ return addEquations;
+ }
+
+ /** Sets a value to additional state.
+ * @param state additional state value.
+ */
+ public void setAdditionalState(final double[] state) {
+ this.addState = state.clone();
+ this.addStateDot = new double[state.length];
+ }
+}
diff --git a/src/main/java/org/orekit/propagation/numerical/Jacobianizer.java b/src/main/java/org/orekit/propagation/numerical/Jacobianizer.java
new file mode 100644
index 0000000000..0706c580b6
--- /dev/null
+++ b/src/main/java/org/orekit/propagation/numerical/Jacobianizer.java
@@ -0,0 +1,282 @@
+/* Copyright 2010 Centre National d'Études Spatiales
+ * Licensed to CS Communication & Systèmes (CS) under one or more
+ * contributor license agreements. See the NOTICE file distributed with
+ * this work for additional information regarding copyright ownership.
+ * CS licenses this file to You under the Apache License, Version 2.0
+ * (the "License"); you may not use this file except in compliance with
+ * the License. You may obtain a copy of the License at
+ *
+ * http://www.apache.org/licenses/LICENSE-2.0
+ *
+ * Unless required by applicable law or agreed to in writing, software
+ * distributed under the License is distributed on an "AS IS" BASIS,
+ * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
+ * See the License for the specific language governing permissions and
+ * limitations under the License.
+ */
+package org.orekit.propagation.numerical;
+
+import java.util.Collection;
+import java.util.HashMap;
+import java.util.Map;
+
+import org.apache.commons.math.geometry.Vector3D;
+import org.apache.commons.math.util.FastMath;
+import org.apache.commons.math.util.MathUtils;
+import org.orekit.errors.OrekitException;
+import org.orekit.forces.ForceModel;
+import org.orekit.frames.Frame;
+import org.orekit.frames.Transform;
+import org.orekit.orbits.CartesianOrbit;
+import org.orekit.orbits.Orbit;
+import org.orekit.propagation.SpacecraftState;
+import org.orekit.utils.PVCoordinates;
+
+/** Class enabling basic {@link ForceModel} instances
+ * to be used when processing spacecraft state partial derivatives.
+ * @author Véronique Pommier-Maurussane
+ * @version $Revision$ $Date$
+ */
+class Jacobianizer implements AccelerationJacobiansProvider {
+
+ /** Serializable UID. */
+ private static final long serialVersionUID = -352915943197943037L;
+
+ /** Wrapped force model instance. */
+ private final ForceModel forceModel;
+
+ /** Step used for finite difference computation with respect to spacecraft position. */
+ private double hPos;
+
+ /** Step used for finite difference computation with respect to spacecraft velocity. */
+ private double hVel;
+
+ /** Step used for finite difference computation with respect to spacecraft mass. */
+ private double hMass;
+
+ /** Step used for finite difference computation with respect to parameters value. */
+ private final Map<String, Double> hParam;
+
+ /** Dedicated adder used to retrieve nominal acceleration. */
+ private final AccelerationRetriever nominal;
+
+ /** Dedicated adder used to retrieve shifted acceleration. */
+ private final AccelerationRetriever shifted;
+
+ /** Simple constructor.
+ * @param forceModel force model instance to wrap
+ * @param paramsAndSteps collection of parameters and their associated steps
+ * @param hPos step used for finite difference computation with respect to spacecraft position (m)
+ * @param hVel step used for finite difference computation with respect to spacecraft velocity (m/s)
+ * @param hMass step used for finite difference computation with respect to spacecraft mass (kg)
+ */
+ public Jacobianizer(final ForceModel forceModel, final Collection<ParameterConfiguration> paramsAndSteps,
+ final double hPos, final double hVel, final double hMass) {
+
+ this.forceModel = forceModel;
+ this.hParam = new HashMap<String, Double>();
+ this.hPos = hPos;
+ this.hVel = hVel;
+ this.hMass = hMass;
+ this.nominal = new AccelerationRetriever();
+ this.shifted = new AccelerationRetriever();
+
+ // set up parameters for jacobian computation
+ for (final ParameterConfiguration param : paramsAndSteps) {
+ final String name = param.getParameterName();
+ if (forceModel.isSupported(name)) {
+ double step = param.getHP();
+ if (Double.isNaN(step)) {
+ step = forceModel.getParameter(name) * FastMath.sqrt(MathUtils.EPSILON);
+ }
+ hParam.put(name, step);
+ }
+ }
+
+ }
+
+ /** Compute acceleration.
+ * @param retriever acceleration retriever to use for storing acceleration
+ * @param s original state
+ * @param p shifted position
+ * @param v shifted velocity
+ * @param m shifted mass
+ * @exception OrekitException if the underlying force models cannot compute the acceleration
+ */
+ private void computeShiftedAcceleration(final AccelerationRetriever retriever, final SpacecraftState s,
+ final Vector3D p, final Vector3D v, final double m)
+ throws OrekitException {
+ final Orbit shiftedORbit = new CartesianOrbit(new PVCoordinates(p, v), s.getFrame(), s.getDate(), s.getMu());
+ retriever.initDerivatives(null, shiftedORbit);
+ forceModel.addContribution(new SpacecraftState(shiftedORbit, s.getAttitude(), m), retriever);
+ }
+
+ /** {@inheritDoc} */
+ public void addDAccDState(final SpacecraftState s,
+ final double[][] dAccdPos, final double[][] dAccdVel, final double[] dAccdM)
+ throws OrekitException {
+
+ // compute df/dy where f is the ODE and y is the state array
+
+ final Vector3D p0 = s.getPVCoordinates().getPosition();
+ final Vector3D v0 = s.getPVCoordinates().getVelocity();
+ final double m0 = s.getMass();
+ computeShiftedAcceleration(nominal, s, p0, v0, m0);
+
+ // jacobian with respect to position
+ computeShiftedAcceleration(shifted, s, new Vector3D(p0.getX() + hPos, p0.getY(), p0.getZ()), v0, m0);
+ dAccdPos[0][0] += (shifted.getX() - nominal.getX()) / hPos;
+ dAccdPos[1][0] += (shifted.getY() - nominal.getY()) / hPos;
+ dAccdPos[2][0] += (shifted.getZ() - nominal.getZ()) / hPos;
+
+ computeShiftedAcceleration(shifted, s, new Vector3D(p0.getX(), p0.getY() + hPos, p0.getZ()), v0, m0);
+ dAccdPos[0][1] += (shifted.getX() - nominal.getX()) / hPos;
+ dAccdPos[1][1] += (shifted.getY() - nominal.getY()) / hPos;
+ dAccdPos[2][1] += (shifted.getZ() - nominal.getZ()) / hPos;
+
+ computeShiftedAcceleration(shifted, s, new Vector3D(p0.getX(), p0.getY(), p0.getZ() + hPos), v0, m0);
+ dAccdPos[0][2] += (shifted.getX() - nominal.getX()) / hPos;
+ dAccdPos[1][2] += (shifted.getY() - nominal.getY()) / hPos;
+ dAccdPos[2][2] += (shifted.getZ() - nominal.getZ()) / hPos;
+
+ // jacobian with respect to velocity
+ computeShiftedAcceleration(shifted, s, p0, new Vector3D(v0.getX() + hVel, v0.getY(), v0.getZ()), m0);
+ dAccdVel[0][0] += (shifted.getX() - nominal.getX()) / hPos;
+ dAccdVel[1][0] += (shifted.getY() - nominal.getY()) / hPos;
+ dAccdVel[2][0] += (shifted.getZ() - nominal.getZ()) / hPos;
+
+ computeShiftedAcceleration(shifted, s, p0, new Vector3D(v0.getX(), v0.getY() + hVel, v0.getZ()), m0);
+ dAccdVel[0][1] += (shifted.getX() - nominal.getX()) / hPos;
+ dAccdVel[1][1] += (shifted.getY() - nominal.getY()) / hPos;
+ dAccdVel[2][1] += (shifted.getZ() - nominal.getZ()) / hPos;
+
+ computeShiftedAcceleration(shifted, s, p0, new Vector3D(v0.getX(), v0.getY(), v0.getZ() + hVel), m0);
+ dAccdVel[0][2] += (shifted.getX() - nominal.getX()) / hPos;
+ dAccdVel[1][2] += (shifted.getY() - nominal.getY()) / hPos;
+ dAccdVel[2][2] += (shifted.getZ() - nominal.getZ()) / hPos;
+
+ if (dAccdM != null) {
+ // jacobian with respect to mass
+ computeShiftedAcceleration(shifted, s, p0, v0, m0 + hMass);
+ dAccdM[0] += (shifted.getX() - nominal.getX()) / hMass;
+ dAccdM[1] += (shifted.getY() - nominal.getY()) / hMass;
+ dAccdM[2] += (shifted.getZ() - nominal.getZ()) / hMass;
+ }
+
+
+ }
+
+ /** {@inheritDoc} */
+ public void addDAccDParam(final SpacecraftState s, final String paramName,
+ final double[] dAccdParam) throws OrekitException {
+ final double hP = hParam.get(paramName);
+ nominal.initDerivatives(null, s.getOrbit());
+ forceModel.addContribution(s, nominal);
+
+ final double paramValue = forceModel.getParameter(paramName);
+ forceModel.setParameter(paramName, paramValue + hP);
+ shifted.initDerivatives(null, s.getOrbit());
+ forceModel.addContribution(s, shifted);
+ forceModel.setParameter(paramName, paramValue);
+
+ dAccdParam[0] += (shifted.getX() - nominal.getX()) / hP;
+ dAccdParam[1] += (shifted.getY() - nominal.getY()) / hP;
+ dAccdParam[2] += (shifted.getZ() - nominal.getZ()) / hP;
+ }
+
+ /** {@inheritDoc} */
+ public double getParameter(final String name) throws IllegalArgumentException {
+ return forceModel.getParameter(name);
+ }
+
+ /** {@inheritDoc} */
+ public Collection<String> getParametersNames() {
+ return forceModel.getParametersNames();
+ }
+
+ /** {@inheritDoc} */
+ public boolean isSupported(final String name) {
+ return forceModel.isSupported(name);
+ }
+
+ /** {@inheritDoc} */
+ public void setParameter(final String name, final double value) throws IllegalArgumentException {
+ forceModel.setParameter(name, value);
+ }
+
+ /** Internal class for retrieving accelerations. */
+ private static class AccelerationRetriever extends TimeDerivativesEquations {
+
+ /** Serializable UID. */
+ private static final long serialVersionUID = -2794923839784176080L;
+
+ /** Stored acceleration. */
+ private final double[] acceleration;
+
+ /** Current orbit. */
+ private Orbit orbit;
+
+ /** Simple constructor.
+ */
+ protected AccelerationRetriever() {
+ acceleration = new double[3];
+ this.orbit = null;
+ }
+
+ /** Get X component of acceleration.
+ * @return X component of acceleration
+ */
+ public double getX() {
+ return acceleration[0];
+ }
+
+ /** Get Y component of acceleration.
+ * @return Y component of acceleration
+ */
+ public double getY() {
+ return acceleration[1];
+ }
+
+ /** Get Z component of acceleration.
+ * @return Z component of acceleration
+ */
+ public double getZ() {
+ return acceleration[2];
+ }
+
+ /** {@inheritDoc} */
+ void initDerivatives(final double[] yDot, final Orbit currentOrbit) {
+ acceleration[0] = 0;
+ acceleration[1] = 0;
+ acceleration[2] = 0;
+ this.orbit = currentOrbit;
+ }
+
+ /** {@inheritDoc} */
+ public void addKeplerContribution(final double mu) {
+ final Vector3D position = orbit.getPVCoordinates().getPosition();
+ final double r2 = position.getNormSq();
+ final double coeff = -mu / (r2 * FastMath.sqrt(r2));
+ acceleration[0] += coeff * position.getX();
+ acceleration[1] += coeff * position.getY();
+ acceleration[2] += coeff * position.getZ();
+ }
+
+ /** {@inheritDoc} */
+ public void addXYZAcceleration(final double x, final double y, final double z) {
+ acceleration[0] += x;
+ acceleration[1] += y;
+ acceleration[2] += z;
+ }
+
+ /** {@inheritDoc} */
+ public void addAcceleration(final Vector3D gamma, final Frame frame)
+ throws OrekitException {
+ final Transform t = frame.getTransformTo(orbit.getFrame(), orbit.getDate());
+ final Vector3D gammInRefFrame = t.transformVector(gamma);
+ addXYZAcceleration(gammInRefFrame.getX(), gammInRefFrame.getY(), gammInRefFrame.getZ());
+ }
+
+ }
+
+}
diff --git a/src/main/java/org/orekit/propagation/numerical/ModeHandler.java b/src/main/java/org/orekit/propagation/numerical/ModeHandler.java
index 9b055437bc..9b2e8f8844 100644
--- a/src/main/java/org/orekit/propagation/numerical/ModeHandler.java
+++ b/src/main/java/org/orekit/propagation/numerical/ModeHandler.java
@@ -1,4 +1,4 @@
-/* Copyright 2002-2010 CS Communication & Systèmes
+/* Copyright 2010 Centre National d'Études Spatiales
* Licensed to CS Communication & Systèmes (CS) under one or more
* contributor license agreements. See the NOTICE file distributed with
* this work for additional information regarding copyright ownership.
@@ -16,7 +16,8 @@
*/
package org.orekit.propagation.numerical;
-import org.orekit.attitudes.AttitudeLaw;
+import java.util.List;
+
import org.orekit.frames.Frame;
import org.orekit.time.AbsoluteDate;
@@ -27,11 +28,13 @@ import org.orekit.time.AbsoluteDate;
public interface ModeHandler {
/** Initialize the mode handler.
+ * @param mapper mapper between spacecraft state and simple array
+ * @param addStateAndEqu list of additional state and equations
* @param reference reference date
* @param frame reference frame
* @param mu central body attraction coefficient
- * @param attitudeLaw attitude law
*/
- void initialize(AbsoluteDate reference, Frame frame, double mu, AttitudeLaw attitudeLaw);
+ void initialize(StateMapper mapper, List <AdditionalStateAndEquations> addStateAndEqu,
+ AbsoluteDate reference, Frame frame, double mu);
}
diff --git a/src/main/java/org/orekit/propagation/numerical/NumericalPropagator.java b/src/main/java/org/orekit/propagation/numerical/NumericalPropagator.java
index 687185fcee..ac2d5e6851 100644
--- a/src/main/java/org/orekit/propagation/numerical/NumericalPropagator.java
+++ b/src/main/java/org/orekit/propagation/numerical/NumericalPropagator.java
@@ -16,7 +16,9 @@
*/
package org.orekit.propagation.numerical;
+import java.lang.reflect.Field;
import java.util.ArrayList;
+import java.util.Arrays;
import java.util.Collection;
import java.util.Collections;
import java.util.List;
@@ -26,16 +28,18 @@ import org.apache.commons.math.ode.FirstOrderDifferentialEquations;
import org.apache.commons.math.ode.FirstOrderIntegrator;
import org.apache.commons.math.ode.IntegratorException;
import org.apache.commons.math.ode.events.EventHandler;
-import org.apache.commons.math.ode.sampling.DummyStepHandler;
-import org.orekit.attitudes.Attitude;
+import org.apache.commons.math.ode.nonstiff.AdaptiveStepsizeIntegrator;
import org.orekit.attitudes.AttitudeLaw;
import org.orekit.attitudes.InertialLaw;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitMessages;
import org.orekit.errors.PropagationException;
import org.orekit.forces.ForceModel;
+import org.orekit.forces.gravity.NewtonianAttraction;
import org.orekit.frames.Frame;
+import org.orekit.orbits.CartesianOrbit;
import org.orekit.orbits.EquinoctialOrbit;
+import org.orekit.orbits.Orbit;
import org.orekit.propagation.BoundedPropagator;
import org.orekit.propagation.Propagator;
import org.orekit.propagation.SpacecraftState;
@@ -125,49 +129,75 @@ import org.orekit.utils.PVCoordinates;
*/
public class NumericalPropagator implements Propagator {
+ /** Parameters types that can be used for propagation. */
+ public enum PropagationParametersType {
+
+ /** Type for propagation in cartesian parameters. */
+ CARTESIAN,
+
+ /** Type for propagation in equinoctial parameters. */
+ EQUINOCTIAL
+
+ }
+
/** Serializable UID. */
private static final long serialVersionUID = -2385169798425713766L;
+ /** Absolute vectorial error field name. */
+ private static final String ABSOLUTE_TOLERANCE = "vecAbsoluteTolerance";
+
+ /** Relative vectorial error field name. */
+ private static final String RELATIVE_TOLERANCE = "vecRelativeTolerance";
+
// CHECKSTYLE: stop VisibilityModifierCheck
/** Attitude law. */
- protected AttitudeLaw attitudeLaw;
+ private AttitudeLaw attitudeLaw;
- /** Central body gravitational constant. */
- protected double mu;
+ /** Central body attraction. */
+ private NewtonianAttraction newtonianAttraction;
- /** Force models used during the extrapolation of the Orbit. */
- protected final List<ForceModel> forceModels;
+ /** Force models used during the extrapolation of the Orbit, without jacobians. */
+ private final List<ForceModel> forceModels;
/** Event detectors not related to force models. */
- protected final List<EventDetector> detectors;
+ private final List<EventDetector> detectors;
/** State vector. */
- protected final double[] stateVector;
+ private double[] stateVector;
/** Start date. */
- protected AbsoluteDate startDate;
+ private AbsoluteDate startDate;
/** Initial state to propagate. */
- protected SpacecraftState initialState;
+ private SpacecraftState initialState;
/** Current state to propagate. */
- protected SpacecraftState currentState;
+ private SpacecraftState currentState;
/** Integrator selected by the user for the orbital extrapolation process. */
- protected transient FirstOrderIntegrator integrator;
+ private transient FirstOrderIntegrator integrator;
/** Counter for differential equations calls. */
- protected int calls;
+ private int calls;
/** Gauss equations handler. */
- protected TimeDerivativesEquations adder;
+ private TimeDerivativesEquations adder;
+
+ /** Mapper between spacecraft state and simple array. */
+ private StateMapper mapper;
/** Propagator mode handler. */
- protected ModeHandler modeHandler;
+ private ModeHandler modeHandler;
/** Current mode. */
- protected int mode;
+ private int mode;
+
+ /** Propagation parameters type. */
+ private PropagationParametersType type;
+
+ /** Additional equations. */
+ private List<AdditionalStateAndEquations> addStateAndEqu;
// CHECKSTYLE: resume VisibilityModifierCheck
@@ -176,20 +206,21 @@ public class NumericalPropagator implements Propagator {
* unspecified default law and there are no perturbing forces at all.
* This means that if {@link #addForceModel addForceModel} is not
* called after creation, the integrated orbit will follow a keplerian
- * evolution only.
+ * evolution only. The default parameter type for propagation is {@link
+ * PropagationParametersType#EQUINOCTIAL}.
* @param integrator numerical integrator to use for propagation.
*/
public NumericalPropagator(final FirstOrderIntegrator integrator) {
- this.mu = Double.NaN;
- this.forceModels = new ArrayList<ForceModel>();
- this.detectors = new ArrayList<EventDetector>();
- this.startDate = new AbsoluteDate();
- this.currentState = null;
- this.adder = null;
- this.attitudeLaw = InertialLaw.EME2000_ALIGNED;
- this.stateVector = new double[7];
+ this.forceModels = new ArrayList<ForceModel>();
+ this.detectors = new ArrayList<EventDetector>();
+ this.startDate = new AbsoluteDate();
+ this.currentState = null;
+ this.adder = null;
+ this.addStateAndEqu = new ArrayList<AdditionalStateAndEquations>();
+ this.attitudeLaw = InertialLaw.EME2000_ALIGNED;
setIntegrator(integrator);
setSlaveMode();
+ setPropagationParametersType(PropagationParametersType.EQUINOCTIAL);
}
/** Set the integrator.
@@ -200,20 +231,20 @@ public class NumericalPropagator implements Propagator {
}
/** Set the central attraction coefficient μ.
- * @param mu central attraction coefficient (m^3/s^2)
+ * @param mu central attraction coefficient (m<sup>3</sup>/s<sup>2</sup>)
* @see #getMu()
* @see #addForceModel(ForceModel)
*/
public void setMu(final double mu) {
- this.mu = mu;
+ newtonianAttraction = new NewtonianAttraction(mu);
}
/** Get the central attraction coefficient μ.
- * @return mu central attraction coefficient (m^3/s^2)
+ * @return mu central attraction coefficient (m<sup>3</sup>/s<sup>2</sup>)
* @see #setMu(double)
*/
public double getMu() {
- return mu;
+ return (newtonianAttraction == null) ? Double.NaN : newtonianAttraction.getMu();
}
/** Set the attitude law.
@@ -239,10 +270,6 @@ public class NumericalPropagator implements Propagator {
}
/** Add a force model to the global perturbation model.
- * <p>If the force models is associated to discrete events, these
- * events will be handled automatically, they must <strong>not</strong>
- * be added using the {@link #addEventDetector(EventDetector) addEventDetector}
- * method.</p>
* <p>If this method is not called at all, the integrated orbit will follow
* a keplerian evolution only.</p>
* @param model perturbing {@link ForceModel} to add
@@ -263,6 +290,24 @@ public class NumericalPropagator implements Propagator {
forceModels.clear();
}
+ /** Get perturbing force models list.
+ * @return list of perturbing force models
+ * @see #addForceModel(ForceModel)
+ * @see #getNewtonianAttractionForceModel()
+ */
+ public List<ForceModel> getForceModels() {
+ return forceModels;
+ }
+
+ /** Get the Newtonian attraction from the central body force model.
+ * @return Newtonian attraction force model
+ * @see #setMu(double)
+ * @see #getForceModels()
+ */
+ public NewtonianAttraction getNewtonianAttractionForceModel() {
+ return newtonianAttraction;
+ }
+
/** {@inheritDoc} */
public int getMode() {
return mode;
@@ -277,7 +322,6 @@ public class NumericalPropagator implements Propagator {
*/
public void setSlaveMode() {
integrator.clearStepHandlers();
- integrator.addStepHandler(DummyStepHandler.getInstance());
modeHandler = null;
mode = SLAVE_MODE;
}
@@ -287,7 +331,7 @@ public class NumericalPropagator implements Propagator {
* of the underlying integrator set up in the {@link
* #NumericalPropagator(FirstOrderIntegrator) constructor} or the {@link
* #setIntegrator(FirstOrderIntegrator) setIntegrator} method. So if a specific
- * step handler is needed, it should be added after this method has been callled.</p>
+ * step handler is needed, it should be added after this method has been called.</p>
*/
public void setMasterMode(final double h, final OrekitFixedStepHandler handler) {
setMasterMode(new OrekitStepNormalizer(h, handler));
@@ -318,11 +362,25 @@ public class NumericalPropagator implements Propagator {
public void setEphemerisMode() {
integrator.clearStepHandlers();
final IntegratedEphemeris ephemeris = new IntegratedEphemeris();
- integrator.addStepHandler(ephemeris);
modeHandler = ephemeris;
+ integrator.addStepHandler(ephemeris);
mode = EPHEMERIS_GENERATION_MODE;
}
+ /** Set propagation parameter type.
+ * @param propagationType parameters type to use for propagation
+ */
+ public void setPropagationParametersType(final PropagationParametersType propagationType) {
+ this.type = propagationType;
+ }
+
+ /** Get propagation parameter type.
+ * @return parameters type used for propagation
+ */
+ public PropagationParametersType getPropagationParametersType() {
+ return type;
+ }
+
/** {@inheritDoc} */
public BoundedPropagator getGeneratedEphemeris()
throws IllegalStateException {
@@ -347,12 +405,59 @@ public class NumericalPropagator implements Propagator {
/** {@inheritDoc} */
public void resetInitialState(final SpacecraftState state) {
- if (Double.isNaN(mu)) {
- mu = state.getMu();
+ if (newtonianAttraction == null) {
+ setMu(state.getMu());
}
this.initialState = state;
}
+ /** Select additional state and equations pair in the list.
+ * @param addEqu Additional equations used as a reference for selection
+ * @return additional state and equations pair
+ * @throws OrekitException if additional equation is unknown */
+ private AdditionalStateAndEquations selectStateAndEquations(final AdditionalEquations addEqu)
+ throws OrekitException {
+ for (AdditionalStateAndEquations stateAndEqu : addStateAndEqu) {
+ if (stateAndEqu.getAdditionalEquations() == addEqu) {
+ return stateAndEqu;
+ }
+ }
+ throw new OrekitException(OrekitMessages.UNKNOWN_ADDITIONAL_EQUATION);
+ }
+
+ /** Add a set of user-specified equations to be integrated along with the orbit propagation.
+ * @param addEqu additional equations
+ * @see #setInitialAdditionalState(double[], AdditionalEquations)
+ * @see #getCurrentAdditionalState(AdditionalEquations)
+ */
+ public void addAdditionalEquations(final AdditionalEquations addEqu) {
+ addStateAndEqu.add(new AdditionalStateAndEquations(addEqu));
+ }
+
+ /** Set initial additional state.
+ * @param addState additional state
+ * @param addEqu additional equations used as a reference for selection
+ * @throws OrekitException if additional equation is unknown
+ * @see #addAdditionalEquations(AdditionalEquations)
+ * @see #getCurrentAdditionalState(AdditionalEquations)
+ */
+ public void setInitialAdditionalState(final double[] addState, final AdditionalEquations addEqu)
+ throws OrekitException {
+ selectStateAndEquations(addEqu).setAdditionalState(addState);
+ }
+
+ /** Get current additional state.
+ * @param addEqu additional equations used as a reference for selection
+ * @return current additional state
+ * @throws OrekitException if additional equation is unknown
+ * @see #addAdditionalEquations(AdditionalEquations)
+ * @see #setInitialAdditionalState(double[], AdditionalEquations)
+ */
+ public double[] getCurrentAdditionalState(final AdditionalEquations addEqu)
+ throws OrekitException {
+ return selectStateAndEquations(addEqu).getAdditionalState();
+ }
+
/** {@inheritDoc} */
public SpacecraftState propagate(final AbsoluteDate finalDate)
throws PropagationException {
@@ -371,18 +476,36 @@ public class NumericalPropagator implements Propagator {
// space dynamics view
startDate = initialState.getDate();
+
+ // set propagation parameters type
+ Orbit initialOrbit = null;
+ switch (type) {
+ case CARTESIAN :
+ initialOrbit = new CartesianOrbit(initialState.getOrbit());
+ adder = new TimeDerivativesEquationsCartesian((CartesianOrbit) initialOrbit);
+ mapper = new StateMapperCartesian();
+ break;
+ case EQUINOCTIAL :
+ initialOrbit = new EquinoctialOrbit(initialState.getOrbit());
+ adder = new TimeDerivativesEquationsEquinoctial((EquinoctialOrbit) initialOrbit);
+ mapper = new StateMapperEquinoctial();
+ break;
+ default :
+ throw OrekitException.createInternalError(null);
+ }
+ mapper.setAttitudeLaw(attitudeLaw);
+
+ // initialize mode handler
if (modeHandler != null) {
- modeHandler.initialize(startDate, initialState.getFrame(), mu, attitudeLaw);
+ modeHandler.initialize(mapper, addStateAndEqu, startDate, initialState.getFrame(), getMu());
}
- final EquinoctialOrbit initialOrbit =
- new EquinoctialOrbit(initialState.getOrbit());
+ // creating state vector
+ this.stateVector = new double[computeDimension()];
currentState =
new SpacecraftState(initialOrbit, initialState.getAttitude(), initialState.getMass());
- adder = new TimeDerivativesEquations(initialOrbit);
-
if (initialState.getMass() <= 0.0) {
throw new IllegalArgumentException("Mass is null or negative");
}
@@ -392,13 +515,14 @@ public class NumericalPropagator implements Propagator {
final double t1 = finalDate.durationFrom(startDate);
// Map state to array
- stateVector[0] = initialOrbit.getA();
- stateVector[1] = initialOrbit.getEquinoctialEx();
- stateVector[2] = initialOrbit.getEquinoctialEy();
- stateVector[3] = initialOrbit.getHx();
- stateVector[4] = initialOrbit.getHy();
- stateVector[5] = initialOrbit.getLv();
- stateVector[6] = initialState.getMass();
+ mapper.mapStateToArray(initialState, stateVector);
+ int index = 7;
+ for (final AdditionalStateAndEquations stateAndEqu : addStateAndEqu) {
+ final double[] addState = stateAndEqu.getAdditionalState();
+ System.arraycopy(addState, 0, stateVector, index, addState.length);
+ // Incrementing index
+ index += addState.length;
+ }
integrator.clearEventHandlers();
@@ -418,17 +542,28 @@ public class NumericalPropagator implements Propagator {
}
// mathematical integration
+ if (!addStateAndEqu.isEmpty()) {
+ expandToleranceArray();
+ }
final double stopTime = integrator.integrate(new DifferentialEquations(), t0, stateVector, t1, stateVector);
+ if (!addStateAndEqu.isEmpty()) {
+ resetToleranceArray();
+ }
// back to space dynamics view
final AbsoluteDate date = startDate.shiftedBy(stopTime);
- final EquinoctialOrbit orbit =
- new EquinoctialOrbit(stateVector[0], stateVector[1], stateVector[2], stateVector[3],
- stateVector[4], stateVector[5], EquinoctialOrbit.TRUE_LATITUDE_ARGUMENT,
- initialOrbit.getFrame(), date, mu);
+ // get final additional state
+ index = 7;
+ for (final AdditionalStateAndEquations stateAndEqu : addStateAndEqu) {
+ final double[] addState = stateAndEqu.getAdditionalState();
+ System.arraycopy(stateVector, index, addState, 0, addState.length);
+ // Incrementing index
+ index += addState.length;
+ }
- resetInitialState(new SpacecraftState(orbit, attitudeLaw.getAttitude(orbit), stateVector[6]));
+ // get final state
+ initialState = mapper.mapArrayToState(stateVector, date, getMu(), initialState.getFrame());
return initialState;
} catch (OrekitException oe) {
@@ -458,6 +593,56 @@ public class NumericalPropagator implements Propagator {
}
}
+ /** Expand integrator tolerance array to fit compound state vector.
+ */
+ private void expandToleranceArray() {
+ if (integrator instanceof AdaptiveStepsizeIntegrator) {
+ final int n = computeDimension();
+ resizeArray(integrator, ABSOLUTE_TOLERANCE, n, Double.POSITIVE_INFINITY);
+ resizeArray(integrator, RELATIVE_TOLERANCE, n, 0.0);
+ }
+ }
+
+ /** Reset integrator tolerance array to original size.
+ */
+ private void resetToleranceArray() {
+ if (integrator instanceof AdaptiveStepsizeIntegrator) {
+ final int n = stateVector.length;
+ resizeArray(integrator, ABSOLUTE_TOLERANCE, n, Double.POSITIVE_INFINITY);
+ resizeArray(integrator, RELATIVE_TOLERANCE, n, 0.0);
+ }
+ }
+
+ /** Resize object internal array.
+ * @param instance instance concerned
+ * @param fieldName field name
+ * @param newSize new array size
+ * @param filler value to use to fill uninitialized elements of the new array
+ */
+ private void resizeArray(final Object instance, final String fieldName,
+ final int newSize, final double filler) {
+ try {
+ final Field arrayField = AdaptiveStepsizeIntegrator.class.getDeclaredField(fieldName);
+ arrayField.setAccessible(true);
+ final double[] originalArray = (double[]) arrayField.get(instance);
+ final int originalSize = originalArray.length;
+ final double[] resizedArray = new double[newSize];
+ if (newSize > originalSize) {
+ // expand array
+ System.arraycopy(originalArray, 0, resizedArray, 0, originalSize);
+ Arrays.fill(resizedArray, originalSize, newSize, filler);
+ } else {
+ // shrink array
+ System.arraycopy(originalArray, 0, resizedArray, 0, newSize);
+ }
+ arrayField.set(instance, resizedArray);
+ } catch (NoSuchFieldException nsfe) {
+ throw OrekitException.createInternalError(nsfe);
+ } catch (IllegalAccessException iae) {
+ throw OrekitException.createInternalError(iae);
+ }
+ }
+
/** {@inheritDoc} */
public PVCoordinates getPVCoordinates(final AbsoluteDate date, final Frame frame)
throws OrekitException {
@@ -478,14 +663,32 @@ public class NumericalPropagator implements Propagator {
*/
protected void setUpEventDetector(final EventDetector osf) {
final EventHandler handler =
- new AdaptedEventDetector(osf, startDate, mu,
- initialState.getFrame(), attitudeLaw);
+ new AdaptedEventDetector(osf, mapper, startDate, getMu(), initialState.getFrame());
integrator.addEventHandler(handler,
osf.getMaxCheckInterval(),
osf.getThreshold(),
osf.getMaxIterationCount());
}
+ /** Get state vector dimension without additional parameters.
+ * @return state vector dimension without additional parameters.
+ */
+ public int getBasicDimension() {
+ return 7;
+
+ }
+ /** Compute complete state vector dimension.
+ * @return state vector dimension
+ */
+ private int computeDimension() {
+ int sum = getBasicDimension();
+ for (final AdditionalStateAndEquations stateAndEqu : addStateAndEqu) {
+ sum += stateAndEqu.getAdditionalState().length;
+ }
+ return sum;
+
+ }
+
/** Internal class for differential equations representation. */
private class DifferentialEquations implements FirstOrderDifferentialEquations {
@@ -499,7 +702,7 @@ public class NumericalPropagator implements Propagator {
/** {@inheritDoc} */
public int getDimension() {
- return 7;
+ return computeDimension();
}
/** {@inheritDoc} */
@@ -508,14 +711,15 @@ public class NumericalPropagator implements Propagator {
try {
// update space dynamics view
- currentState = mapState(t, y, startDate, currentState.getFrame());
+ currentState = mapper.mapArrayToState(y, startDate.shiftedBy(t), currentState.getMu(), currentState.getFrame());
+
if (currentState.getMass() <= 0.0) {
throw new PropagationException(OrekitMessages.SPACECRAFT_MASS_BECOMES_NEGATIVE,
currentState.getMass());
}
// initialize derivatives
- adder.initDerivatives(yDot, (EquinoctialOrbit) currentState.getOrbit());
+ adder.initDerivatives(yDot, currentState.getOrbit());
// compute the contributions of all perturbing forces
for (final ForceModel forceModel : forceModels) {
@@ -523,7 +727,26 @@ public class NumericalPropagator implements Propagator {
}
// finalize derivatives by adding the Kepler contribution
- adder.addKeplerContribution();
+ newtonianAttraction.addContribution(currentState, adder);
+
+ // Add contribution for additional state
+ int index = 7;
+ for (final AdditionalStateAndEquations stateAndEqu : addStateAndEqu) {
+ final double[] p = stateAndEqu.getAdditionalState();
+ final double[] pDot = stateAndEqu.getAdditionalStateDot();
+
+ // update current additional state
+ System.arraycopy(y, index, p, 0, p.length);
+
+ // compute additional derivatives
+ stateAndEqu.getAdditionalEquations().computeDerivatives(currentState, adder, p, pDot);
+
+ // update each additional state contribution in global array
+ System.arraycopy(pDot, 0, yDot, index, p.length);
+
+ // incrementing index
+ index += p.length;
+ }
// increment calls counter
++calls;
@@ -534,31 +757,8 @@ public class NumericalPropagator implements Propagator {
}
- /** Convert state array to space dynamics objects (AbsoluteDate and OrbitalParameters).
- * @param t integration time (s)
- * @param y state as a flat array
- * @param referenceDate reference date from which t is counted
- * @param frame frame in which integration is performed
- * @return state corresponding to the flat array as a space dynamics object
- * @exception OrekitException if the attitude state cannot be determined
- * by the attitude law
- */
- private SpacecraftState mapState(final double t, final double [] y,
- final AbsoluteDate referenceDate, final Frame frame)
- throws OrekitException {
-
- // convert raw mathematical data to space dynamics objects
- final AbsoluteDate date = referenceDate.shiftedBy(t);
- final EquinoctialOrbit orbit =
- new EquinoctialOrbit(y[0], y[1], y[2], y[3], y[4], y[5],
- EquinoctialOrbit.TRUE_LATITUDE_ARGUMENT,
- frame, date, mu);
- final Attitude attitude = attitudeLaw.getAttitude(orbit);
-
- return new SpacecraftState(orbit, attitude, y[6]);
-
- }
-
}
}
+
+
diff --git a/src/main/java/org/orekit/propagation/numerical/NumericalPropagatorWithJacobians.java b/src/main/java/org/orekit/propagation/numerical/NumericalPropagatorWithJacobians.java
deleted file mode 100644
index e77f34d784..0000000000
--- a/src/main/java/org/orekit/propagation/numerical/NumericalPropagatorWithJacobians.java
+++ /dev/null
@@ -1,530 +0,0 @@
-/* Copyright 2002-2010 CS Communication & Systèmes
- * Licensed to CS Communication & Systèmes (CS) under one or more
- * contributor license agreements. See the NOTICE file distributed with
- * this work for additional information regarding copyright ownership.
- * CS licenses this file to You under the Apache License, Version 2.0
- * (the "License"); you may not use this file except in compliance with
- * the License. You may obtain a copy of the License at
- *
- * http://www.apache.org/licenses/LICENSE-2.0
- *
- * Unless required by applicable law or agreed to in writing, software
- * distributed under the License is distributed on an "AS IS" BASIS,
- * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
- * See the License for the specific language governing permissions and
- * limitations under the License.
- */
-package org.orekit.propagation.numerical;
-
-import java.lang.reflect.Field;
-import java.util.ArrayList;
-import java.util.Arrays;
-import java.util.Collection;
-import java.util.List;
-
-import org.apache.commons.math.exception.MathUserException;
-import org.apache.commons.math.ode.FirstOrderIntegrator;
-import org.apache.commons.math.ode.IntegratorException;
-import org.apache.commons.math.ode.jacobians.FirstOrderIntegratorWithJacobians;
-import org.apache.commons.math.ode.jacobians.ODEWithJacobians;
-import org.apache.commons.math.ode.jacobians.ParameterizedODE;
-import org.apache.commons.math.ode.nonstiff.AdaptiveStepsizeIntegrator;
-import org.apache.commons.math.util.FastMath;
-import org.apache.commons.math.util.MathUtils;
-import org.orekit.attitudes.Attitude;
-import org.orekit.errors.OrekitException;
-import org.orekit.errors.OrekitMessages;
-import org.orekit.errors.PropagationException;
-import org.orekit.forces.ForceModel;
-import org.orekit.forces.ForceModelWithJacobians;
-import org.orekit.forces.Parameterizable;
-import org.orekit.frames.Frame;
-import org.orekit.orbits.EquinoctialOrbit;
-import org.orekit.propagation.SpacecraftState;
-import org.orekit.propagation.events.EventDetector;
-import org.orekit.time.AbsoluteDate;
-
-
-/** This class propagates {@link org.orekit.orbits.Orbit orbits} using
- * numerical integration and enables jacobians computation for orbit parameters
- * and partial derivatives computation with respect to some force models parameters.
- * <p>
- * As of 5.0, this class is still considered experimental, so use it with care,
- * the API could change in the future.
- * </p>
- * <p>
- * The underlying numerical integrator configuration can be exactly the same
- * as these for a simple {@link NumericalPropagator numerical integration}.
- * </p>
- * <p>
- * The Jacobian for the six {@link EquinoctialOrbit equinoctial orbit parameters}
- * (a, e<sub>x</sub>, e<sub>y</sub>, h<sub>x</sub>, h<sub>y</sub>, l<sub>v</sub>)
- * and the mass is computed as a 7x7 array such as:
- * <pre>
- * dFdY[i][j] = dyi/dyj
- * with: y0Â = a, y1Â = ex, y2Â = ey, y3Â = hx, y4Â = hy, y5Â = lv, y6Â = mass
- * </pre>
- * </p>
- * <p>
- * Partial derivatives can also be computed for the 7 elements state vector with
- * respect to n {@link #selectParameters selected parameters} from
- * {@link ForceModelWithJacobians force models}. They are computed as a 7xn array:
- * <pre>
- * dFdP[i][j] = dyi/dpj
- * </pre>
- * </p>
- *
- * @see NumericalPropagator
- * @see ForceModelWithJacobians
- *
- * @author Pascal Parraud
- * @version $Revision$ $Date$
- */
-public class NumericalPropagatorWithJacobians extends NumericalPropagator {
-
- /** Serializable UID. */
- private static final long serialVersionUID = 4139595812211569107L;
-
- /** Force models used when extrapolating the Orbit. */
- private final List<ForceModelWithJacobians> forceModelsWJ;
-
- /** State vector derivative with respect to the parameter. */
- private double[][] DY0DP = null;
-
- /** Gauss equations handler. */
- private TimeDerivativesEquationsWithJacobians adder;
-
- /** Selected parameters for jacobian computation. */
- private String[] selectedParameters = new String[0];
-
- /** Selected parameters with force model associated for jacobian computation. */
- private List<ParameterPair> paramPairs = new ArrayList<ParameterPair>();
-
- /** Create a new instance of NumericalPropagatorWithJacobians.
- * After creation, the instance is empty, i.e. the attitude law is set to an
- * unspecified default law and there are no perturbing forces at all.
- * This means that if {@link #addForceModel addForceModel} is not
- * called after creation, the integrated orbit will follow a keplerian
- * evolution only.
- * @param integrator numerical integrator to use for propagation.
- */
- public NumericalPropagatorWithJacobians(final FirstOrderIntegrator integrator) {
- super(integrator);
- this.forceModelsWJ = new ArrayList<ForceModelWithJacobians>();
- }
-
- /** Add a force model to the global perturbation model.
- * @param model perturbing force model to add
- * @see #removeForceModels()
- * @see #removeForceModels()
- */
- public void addForceModel(final ForceModel model) {
- forceModels.add(model);
- if (!(model instanceof ForceModelWithJacobians)) {
- forceModelsWJ.add(new ForceModelWrapper(model));
- } else {
- forceModelsWJ.add((ForceModelWithJacobians) model);
- }
- }
-
- /** Remove all perturbing force models from the global perturbation model.
- * <p>Once all perturbing forces have been removed (and as long as no new force
- * model is added), the integrated orbit will follow a keplerian evolution
- * only.</p>
- * @see #addForceModel(ForceModel)
- */
- public void removeForceModels() {
- forceModels.clear();
- forceModelsWJ.clear();
- }
-
- /** Select the parameters to consider for jacobian processing.
- * <p>Parameters names have to be consistent with some
- * {@link ForceModelWithJacobians} added elsewhere.</p>
- * @param parameters parameters to consider for jacobian processing
- * @see #addForceModel(ForceModel)
- * @see ForceModelWithJacobians
- * @see Parameterizable
- */
- public void selectParameters(final String[] parameters) {
- selectedParameters = parameters.clone();
- DY0DP = new double[7][selectedParameters.length];
- for (final double[] row : DY0DP) {
- Arrays.fill(row, 0.0);
- }
- }
-
- /** Get the parameters selected for jacobian processing.
- * @return parameters considered for jacobian processing
- * @see #selectParameters(String[])
- */
- public String[] getParameterNames() {
- return selectedParameters.clone();
- }
-
- /** Propagate towards a target date and compute partial derivatives.
- * <p>Propagation is the same as the
- * {@link NumericalPropagator#propagate(AbsoluteDate) basic one}.</p>
- * <p>Jacobian for orbit parameters is given as a 7x7 array.</p>
- * <p>Partial derivatives will be computed as a 7xn array
- * when n parameters have been {@link #selectParameters(String[]) selected}
- * (n may be 0).</p>
- * <p>Those parameters are related to some {@link ForceModelWithJacobians force models}
- * which must have been added elsewhere.</p>
- * @param finalDate target date towards which orbit state should be propagated
- * @param dFdY equinoctial orbit parameters + mass jacobian (7x7 array)
- * @param dFdP partial derivatives with respect to selected parameters (7xn)
- * @return propagated state
- * @exception PropagationException if state cannot be propagated
- */
- public SpacecraftState propagate(final AbsoluteDate finalDate,
- final double[][] dFdY, final double[][] dFdP)
- throws PropagationException {
- try {
-
- if (initialState == null) {
- throw new PropagationException(OrekitMessages.INITIAL_STATE_NOT_SPECIFIED_FOR_ORBIT_PROPAGATION);
- }
- if (initialState.getMass() <= 0.0) {
- throw new PropagationException(OrekitMessages.NOT_POSITIVE_SPACECRAFT_MASS, initialState.getMass());
- }
- if (initialState.getDate().equals(finalDate)) {
- // don't extrapolate
- return initialState;
- }
- if (integrator == null) {
- throw new PropagationException(OrekitMessages.ODE_INTEGRATOR_NOT_SET_FOR_ORBIT_PROPAGATION);
- }
-
- // space dynamics view
- startDate = initialState.getDate();
- if (modeHandler != null) {
- modeHandler.initialize(startDate, initialState.getFrame(), mu, attitudeLaw);
- }
-
- final EquinoctialOrbit initialOrbit =
- new EquinoctialOrbit(initialState.getOrbit());
-
- currentState =
- new SpacecraftState(initialOrbit, initialState.getAttitude(), initialState.getMass());
-
- adder = new TimeDerivativesEquationsWithJacobians(initialOrbit);
-
- integrator.clearEventHandlers();
-
- // set up events related to force models
- for (final ForceModelWithJacobians forceModel : forceModelsWJ) {
- final EventDetector[] modelDetectors = forceModel.getEventsDetectors();
- if (modelDetectors != null) {
- for (final EventDetector detector : modelDetectors) {
- setUpEventDetector(detector);
- }
- }
- }
-
- // set up events added by user
- for (final EventDetector detector : detectors) {
- setUpEventDetector(detector);
- }
-
- // mathematical view
- final double t0 = 0;
- final double t1 = finalDate.durationFrom(startDate);
-
- // Map state to array
- stateVector[0] = initialOrbit.getA();
- stateVector[1] = initialOrbit.getEquinoctialEx();
- stateVector[2] = initialOrbit.getEquinoctialEy();
- stateVector[3] = initialOrbit.getHx();
- stateVector[4] = initialOrbit.getHy();
- stateVector[5] = initialOrbit.getLv();
- stateVector[6] = initialState.getMass();
-
- // set up parameters for jacobian computation
- int noParam = 0;
- final int nbParam = selectedParameters.length;
- final double[] paramWJ = new double[nbParam];
- final double[] hP = new double[nbParam];
-
- for (final String parameter : selectedParameters) {
- boolean found = false;
- for (final ForceModelWithJacobians fmwj : forceModelsWJ) {
- for (String parFMWJ : fmwj.getParametersNames()) {
- if (parFMWJ.matches(parameter)) {
- found = true;
- paramWJ[noParam] = fmwj.getParameter(parFMWJ);
- hP[noParam] = paramWJ[noParam] * FastMath.sqrt(MathUtils.EPSILON);
- paramPairs.add(new ParameterPair(parameter, fmwj));
- noParam++;
- }
- }
- }
- if (!found) {
- throw new PropagationException(OrekitMessages.UNKNOWN_PARAMETER, parameter);
- }
- }
-
- // if selectParameters was not invoked and then no parameter selected
- if (DY0DP == null) {
- DY0DP = new double[7][nbParam];
- for (final double[] row : DY0DP) {
- Arrays.fill(row, 0.0);
- }
- }
-
- // get hY from integrator tolerance array
- final double[] hY = getHy(integrator);
-
- final FirstOrderIntegratorWithJacobians integratorWJ =
- new FirstOrderIntegratorWithJacobians(integrator,
- new DifferentialEquations(),
- paramWJ, hY, hP);
-
- // mathematical integration
- final double stopTime = integratorWJ.integrate(t0, stateVector, DY0DP,
- t1, stateVector, dFdY, DY0DP);
- // fill in jacobian
- for (int i = 0; i < DY0DP.length; i++) {
- System.arraycopy(DY0DP[i], 0, dFdP[i], 0, DY0DP[i].length);
- }
-
- // back to space dynamics view
- final AbsoluteDate date = startDate.shiftedBy(stopTime);
-
- final EquinoctialOrbit orbit =
- new EquinoctialOrbit(stateVector[0], stateVector[1], stateVector[2], stateVector[3],
- stateVector[4], stateVector[5], EquinoctialOrbit.TRUE_LATITUDE_ARGUMENT,
- initialOrbit.getFrame(), date, mu);
-
- resetInitialState(new SpacecraftState(orbit, attitudeLaw.getAttitude(orbit), stateVector[6]));
-
- return initialState;
-
- } catch (OrekitException oe) {
- throw new PropagationException(oe);
- } catch (MathUserException mue) {
-
- // recover a possible embedded PropagationException
- for (Throwable t = mue; t != null; t = t.getCause()) {
- if (t instanceof PropagationException) {
- throw (PropagationException) t;
- }
- }
-
- throw new PropagationException(mue, mue.getGeneralPattern(), mue.getArguments());
-
- } catch (IntegratorException ie) {
-
- // recover a possible embedded PropagationException
- for (Throwable t = ie; t != null; t = t.getCause()) {
- if (t instanceof PropagationException) {
- throw (PropagationException) t;
- }
- }
-
- throw new PropagationException(ie, ie.getGeneralPattern(), ie.getArguments());
-
- }
- }
-
- /** Get hY from integrator absolute tolerance array.
- * @param integrator integrator
- * @return step sizes array for df/dy computing
- */
- private double[] getHy(final FirstOrderIntegrator integrator) {
- double[] hY = new double[0];
- if (integrator instanceof AdaptiveStepsizeIntegrator) {
- try {
- final Field arrayField = AdaptiveStepsizeIntegrator.class.getDeclaredField("vecAbsoluteTolerance");
- arrayField.setAccessible(true);
- hY = (double[]) arrayField.get(integrator);
- for (int i = 0; i < hY.length; i++) {
- hY[i] *= 10.;
- }
- } catch (NoSuchFieldException nsfe) {
- throw OrekitException.createInternalError(nsfe);
- } catch (IllegalAccessException iae) {
- throw OrekitException.createInternalError(iae);
- }
- }
- return hY;
- }
-
- /** Internal class for differential equations representation. */
- private class DifferentialEquations implements ParameterizedODE, ODEWithJacobians {
-
- /** Build a new instance. */
- protected DifferentialEquations() {
- calls = 0;
- }
-
- /** {@inheritDoc} */
- public int getDimension() {
- return 7;
- }
-
- /** {@inheritDoc} */
- public void computeDerivatives(final double t, final double[] y, final double[] yDot)
- throws MathUserException {
-
- try {
- // update space dynamics view
- currentState = mapState(t, y, startDate, currentState.getFrame());
-
- // compute cartesian coordinates
- if (currentState.getMass() <= 0.0) {
- throw new PropagationException(OrekitMessages.SPACECRAFT_MASS_BECOMES_NEGATIVE,
- currentState.getMass());
- }
-
- // initialize derivatives
- adder.initDerivatives(yDot, (EquinoctialOrbit) currentState.getOrbit());
-
- // compute the contributions of all perturbing forces
- for (final ForceModel forceModel : forceModels) {
- forceModel.addContribution(currentState, adder);
- }
-
- // finalize derivatives by adding the Kepler contribution
- adder.addKeplerContribution();
-
- // increment calls counter
- ++calls;
-
- } catch (OrekitException oe) {
- throw new MathUserException(oe, oe.getSpecifier(), oe.getParts());
- }
-
- }
-
- /** {@inheritDoc} */
- public void computeJacobians(final double t, final double[] y, final double[] yDot,
- final double[][] dFdY, final double[][] dFdP) {
- }
-
- /** {@inheritDoc} */
- public int getParametersDimension() {
- return selectedParameters.length;
- }
-
- /** {@inheritDoc} */
- public void setParameter(final int index, final double value) {
- final ParameterPair pp = paramPairs.get(index);
- pp.getParamHandler().setParameter(pp.getParamName(), value);
- }
-
- /** Convert state array to space dynamics objects (AbsoluteDate and OrbitalParameters).
- * @param t integration time (s)
- * @param y state as a flat array
- * @param referenceDate reference date from which t is counted
- * @param frame frame in which integration is performed
- * @return state corresponding to the flat array as a space dynamics object
- * @exception OrekitException if the attitude state cannot be determined
- * by the attitude law
- */
- private SpacecraftState mapState(final double t, final double [] y,
- final AbsoluteDate referenceDate, final Frame frame)
- throws OrekitException {
-
- // convert raw mathematical data to space dynamics objects
- final AbsoluteDate date = referenceDate.shiftedBy(t);
- final EquinoctialOrbit orbit =
- new EquinoctialOrbit(y[0], y[1], y[2], y[3], y[4], y[5],
- EquinoctialOrbit.TRUE_LATITUDE_ARGUMENT,
- frame, date, mu);
- final Attitude attitude = attitudeLaw.getAttitude(orbit);
-
- return new SpacecraftState(orbit, attitude, y[6]);
-
- }
-
- }
-
- /** Internal class used to pair a parameter name with its handler. */
- private static class ParameterPair {
-
- /** Parameter name. */
- private final String paramName;
-
- /** Parameter handler. */
- private final Parameterizable paramHandler;
-
- /** Simple constructor.
- * @param paramName parameter name
- * @param paramHandler force model handling the parameter
- */
- public ParameterPair(final String paramName, final Parameterizable paramHandler) {
- this.paramName = paramName;
- this.paramHandler = paramHandler;
- }
-
- /** Get parameter name.
- * @return parameter name
- */
- public String getParamName() {
- return paramName;
- }
-
- /** Get parameter handler.
- * @return force model handling the parameter
- */
- public Parameterizable getParamHandler() {
- return paramHandler;
- }
-
- }
-
- /** Internal class enabling basic force model
- * to be used when processing parameters jacobian.
- */
- private static class ForceModelWrapper implements ForceModelWithJacobians {
-
- /** Serializable UID. */
- private static final long serialVersionUID = 3625153851142193056L;
-
- /** Wrapped basic force model. */
- private final ForceModel basic;
-
- /** Simple constructor.
- * @param basic force model to wrap
- */
- public ForceModelWrapper(final ForceModel basic) {
- this.basic = basic;
- }
-
- /** {@inheritDoc} */
- public void addContribution(final SpacecraftState s,
- final TimeDerivativesEquations adder)
- throws OrekitException {
- basic.addContribution(s, adder);
- }
-
- /** {@inheritDoc} */
- public EventDetector[] getEventsDetectors() {
- return basic.getEventsDetectors();
- }
-
- /** {@inheritDoc} */
- public void addContributionWithJacobians(final SpacecraftState s,
- final TimeDerivativesEquationsWithJacobians adder)
- throws OrekitException {
- }
-
- /** {@inheritDoc} */
- public double getParameter(final String name) throws IllegalArgumentException {
- return Double.NaN;
- }
-
- /** {@inheritDoc} */
- public Collection<String> getParametersNames() {
- return new ArrayList<String>();
- }
-
- /** {@inheritDoc} */
- public void setParameter(final String name, final double value)
- throws IllegalArgumentException {
- }
-
- }
-
-}
diff --git a/src/main/java/org/orekit/propagation/numerical/ParameterConfiguration.java b/src/main/java/org/orekit/propagation/numerical/ParameterConfiguration.java
new file mode 100644
index 0000000000..bd892f1306
--- /dev/null
+++ b/src/main/java/org/orekit/propagation/numerical/ParameterConfiguration.java
@@ -0,0 +1,77 @@
+/* Copyright 2010 Centre National d'Études Spatiales
+ * Licensed to CS Communication & Systèmes (CS) under one or more
+ * contributor license agreements. See the NOTICE file distributed with
+ * this work for additional information regarding copyright ownership.
+ * CS licenses this file to You under the Apache License, Version 2.0
+ * (the "License"); you may not use this file except in compliance with
+ * the License. You may obtain a copy of the License at
+ *
+ * http://www.apache.org/licenses/LICENSE-2.0
+ *
+ * Unless required by applicable law or agreed to in writing, software
+ * distributed under the License is distributed on an "AS IS" BASIS,
+ * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
+ * See the License for the specific language governing permissions and
+ * limitations under the License.
+ */
+package org.orekit.propagation.numerical;
+
+import java.io.Serializable;
+
+/** Simple container associating a parameter name with a step to compute its jacobian
+ * and the provider thant manages it.
+ * @author Véronique Pommier-Maurussane
+ * @version $Revision$ $Date$
+ */
+class ParameterConfiguration implements Serializable {
+
+ /** Serializable UID. */
+ private static final long serialVersionUID = 2247518849090889379L;
+
+ /** Parameter name. */
+ private String parameterName;
+
+ /** Parameter step for finite difference computation of partial derivative with respect to that parameter. */
+ private double hP;
+
+ /** Provider handling this parameter. */
+ private AccelerationJacobiansProvider provider;
+
+ /** Parameter name and step pair constructor.
+ * @param parameterName parameter name
+ * @param hP parameter step */
+ public ParameterConfiguration(final String parameterName, final double hP) {
+ this.parameterName = parameterName;
+ this.hP = hP;
+ this.provider = null;
+ }
+
+ /** Get parameter name.
+ * @return parameterName parameter name
+ */
+ public String getParameterName() {
+ return parameterName;
+ }
+
+ /** Get parameter step.
+ * @return hP parameter step
+ */
+ public double getHP() {
+ return hP;
+ }
+
+ /** Set the povider handling this parameter.
+ * @param provider provider handling this parameter
+ */
+ public void setProvider(final AccelerationJacobiansProvider provider) {
+ this.provider = provider;
+ }
+
+ /** Get the povider handling this parameter.
+ * @return provider handling this parameter
+ */
+ public AccelerationJacobiansProvider getProvider() {
+ return provider;
+ }
+
+}
diff --git a/src/main/java/org/orekit/propagation/numerical/PartialDerivativesEquations.java b/src/main/java/org/orekit/propagation/numerical/PartialDerivativesEquations.java
new file mode 100644
index 0000000000..9fd2d9a41d
--- /dev/null
+++ b/src/main/java/org/orekit/propagation/numerical/PartialDerivativesEquations.java
@@ -0,0 +1,454 @@
+/* Copyright 2010 Centre National d'Études Spatiales
+ * Licensed to CS Communication & Systèmes (CS) under one or more
+ * contributor license agreements. See the NOTICE file distributed with
+ * this work for additional information regarding copyright ownership.
+ * CS licenses this file to You under the Apache License, Version 2.0
+ * (the "License"); you may not use this file except in compliance with
+ * the License. You may obtain a copy of the License at
+ *
+ * http://www.apache.org/licenses/LICENSE-2.0
+ *
+ * Unless required by applicable law or agreed to in writing, software
+ * distributed under the License is distributed on an "AS IS" BASIS,
+ * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
+ * See the License for the specific language governing permissions and
+ * limitations under the License.
+ */
+package org.orekit.propagation.numerical;
+
+import java.util.ArrayList;
+import java.util.Arrays;
+import java.util.List;
+
+import org.apache.commons.math.util.FastMath;
+import org.apache.commons.math.util.MathUtils;
+import org.orekit.errors.OrekitException;
+import org.orekit.errors.OrekitMessages;
+import org.orekit.forces.ForceModel;
+import org.orekit.propagation.SpacecraftState;
+
+/** Set of {@link AdditionalEquations additional equations} computing the partial derivatives
+ * of the state (orbit) with respect to initial state and force models parameters.
+ * <p>
+ * This set of equations can be added to a {@link NumericalPropagator numerical propagator}
+ * in order to compute partial derivatives of the orbit along with the orbit itself. This is
+ * useful for example in orbit determination applications.
+ * </p>
+ * @author Véronique Pommier-Maurussane
+ * @version $Revision$ $Date$
+ */
+public class PartialDerivativesEquations implements AdditionalEquations {
+
+ /** Serializable UID. */
+ private static final long serialVersionUID = 8373349999733456541L;
+
+ /** Selected parameters for jacobian computation. */
+ private NumericalPropagator propagator;
+
+ /** Jacobians providers. */
+ private final List<AccelerationJacobiansProvider> jacobiansProviders;
+
+ /** List of parameters selected for jacobians computation. */
+ private List<ParameterConfiguration> selectedParameters;
+
+ /** State vector dimension without additional parameters
+ * (either 6 or 7 depending on mass derivatives being included or not). */
+ private int stateDim;
+
+ /** Parameters vector dimension. */
+ private int paramDim;
+
+ /** Step used for finite difference computation with respect to spacecraft position. */
+ private double hPos;
+
+ /** Step used for finite difference computation with respect to spacecraft velocity. */
+ private double hVel;
+
+ /** Step used for finite difference computation with respect to spacecraft mass. */
+ private double hM;
+
+ /** Boolean for force models / selected parameters consistency. */
+ private boolean dirty = false;
+
+ /** Jacobian of acceleration with respect to spacecraft position. */
+ private transient double[][] dAccdPos;
+
+ /** Jacobian of acceleration with respect to spacecraft velocity. */
+ private transient double[][] dAccdVel;
+
+ /** Jacobian of acceleration with respect to spacecraft mass. */
+ private transient double[] dAccdM;
+
+ /** Jacobian of acceleration with respect to one force model parameter (array reused for all parameters). */
+ private transient double[] dAccdParam;
+
+ /** Simple constructor.
+ * @param propagator the propagator that will handle the orbit propagation
+ */
+ public PartialDerivativesEquations(final NumericalPropagator propagator) {
+ jacobiansProviders = new ArrayList<AccelerationJacobiansProvider>();
+ dirty = true;
+ this.propagator = propagator;
+ selectedParameters = new ArrayList<ParameterConfiguration>();
+ stateDim = -1;
+ paramDim = -1;
+ hPos = Double.NaN;
+ hVel = Double.NaN;
+ hM = Double.NaN;
+ }
+
+ /** Get the names of the available parameters in the propagator.
+ * <p>
+ * The names returned depend on the force models set up in the propagator,
+ * including the Newtonian attraction from the central body.
+ * </p>
+ * @return available parameters
+ */
+ public List<String> getAvailableParameters() {
+ final List<String> available = new ArrayList<String>();
+ available.addAll(propagator.getNewtonianAttractionForceModel().getParametersNames());
+ for (final ForceModel model : propagator.getForceModels()) {
+ available.addAll(model.getParametersNames());
+ }
+ return available;
+ }
+
+ /** Select the parameters to consider for jacobian processing.
+ * <p>Parameters names have to be consistent with some
+ * {@link ForceModel} added elsewhere.</p>
+ * @param parameters parameters to consider for jacobian processing
+ * @see NumericalPropagator#addForceModel(ForceModel)
+ * @see #setInitialJacobians(double[][], double[][])
+ * @see ForceModel
+ * @see org.orekit.forces.Parameterizable
+ */
+ public void selectParameters(final String ... parameters) {
+
+ selectedParameters.clear();
+ for (String param : parameters) {
+ selectedParameters.add(new ParameterConfiguration(param, Double.NaN));
+ }
+ dirty = true;
+ }
+
+ /** Select the parameters to consider for jacobian processing.
+ * <p>Parameters names have to be consistent with some
+ * {@link ForceModel} added elsewhere.</p>
+ * @param parameter parameter to consider for jacobian processing
+ * @param hP step to use for computing jacobian column with respect to the specified parameter
+ * @see NumericalPropagator#addForceModel(ForceModel)
+ * @see #setInitialJacobians(double[][], double[][])
+ * @see ForceModel
+ * @see org.orekit.forces.Parameterizable
+ */
+ public void selectParamAndStep(final String parameter, final double hP) {
+ selectedParameters.add(new ParameterConfiguration(parameter, hP));
+ dirty = true;
+ }
+
+ /** Set the steps for finite differences with respect to spacecraft state.
+ * @param hPosition step used for finite difference computation with respect to spacecraft position (m)
+ * @param hVelocity step used for finite difference computation with respect to spacecraft velocity (m/s)
+ * @param hMass step used for finite difference computation with respect to spacecraft mass (kg)
+ */
+ public void setSteps(final double hPosition, final double hVelocity, final double hMass) {
+ this.hPos = hPosition;
+ this.hVel = hVelocity;
+ this.hM = hMass;
+ }
+
+ /** Set the initial value of the jacobian with respect to state and parameter.
+ * <p>
+ * This method is equivalent to call {@link #setInitialJacobians(double[][], double[][])}
+ * with dYdY0 set to the identity matrix and dYdP set to a zero matrix.
+ * </p>
+ * @param stateDimension state dimension, must be either 6 for orbit only or 7 for orbit and mass
+ * @param paramDimension parameters dimension
+ * @exception OrekitException if the partial equation has not been registered in
+ * the propagator or if matrices dimensions are incorrect
+ * @see #selectedParameters
+ * @see #selectParamAndStep(String, double)
+ */
+ public void setInitialJacobians(final int stateDimension, final int paramDimension)
+ throws OrekitException {
+ final double[][] dYdY0 = new double[stateDimension][stateDimension];
+ final double[][] dYdP = new double[stateDimension][paramDimension];
+ for (int i = 0; i < stateDimension; ++i) {
+ dYdY0[i][i] = 1.0;
+ }
+ setInitialJacobians(dYdY0, dYdP);
+ }
+
+ /** Set the initial value of the jacobian with respect to state and parameter.
+ * @param dYdY0 initial jacobian w.r to state (may be either 6x6 for orbit only
+ * or 7x7 for orbit and mass)
+ * @param dYdP initial jacobian w.r to parameter (may be null if no parameters are selected)
+ * @exception OrekitException if the partial equation has not been registered in
+ * the propagator or if matrices dimensions are incorrect
+ * @see #selectedParameters
+ * @see #selectParamAndStep(String, double)
+ */
+ public void setInitialJacobians(final double[][] dYdY0, final double[][] dYdP)
+ throws OrekitException {
+
+ // Check dimensions
+ stateDim = dYdY0.length;
+ if ((stateDim < 6) || (stateDim > 7) || (stateDim != dYdY0[0].length)) {
+ throw new OrekitException(OrekitMessages.STATE_JACOBIAN_NEITHER_6X6_NOR_7X7,
+ stateDim, dYdY0[0].length);
+ }
+ if ((dYdP != null) && (stateDim != dYdP.length)) {
+ throw new OrekitException(OrekitMessages.STATE_AND_PARAMETERS_JACOBIANS_ROWS_MISMATCH,
+ stateDim, dYdP.length);
+ }
+
+ paramDim = (dYdP == null) ? 0 : dYdP[0].length;
+
+ // store the matrices in row major order as a single dimension array
+ final double[] p = new double[stateDim * (stateDim + paramDim)];
+ int index = 0;
+ for (final double[] row : dYdY0) {
+ System.arraycopy(row, 0, p, index, stateDim);
+ index += stateDim;
+ }
+
+ if (dYdP != null) {
+ for (final double[] row : dYdP) {
+ System.arraycopy(row, 0, p, index, paramDim);
+ index += paramDim;
+ }
+ }
+
+ // set value in propagator
+ propagator.setInitialAdditionalState(p, this);
+
+ }
+
+ /** Get the initial value of the jacobian with respect to state and parameter.
+ * @param dYdY0 current jacobian w.r to state.
+ * @param dYdP current jacobian w.r to parameter (may be null if no parameters are selected)
+ * @exception OrekitException if the partial equation has not been registered in
+ * the propagator
+ */
+ public void getCurrentJacobians(final double[][] dYdY0, final double[][] dYdP)
+ throws OrekitException {
+
+ // get current state from propagator
+ final double[] p = propagator.getCurrentAdditionalState(this);
+
+ int index = 0;
+ for (int i = 0; i < stateDim; i++) {
+ System.arraycopy(p, index, dYdY0[i], 0, stateDim);
+ index += stateDim;
+ }
+
+ if (paramDim != 0) {
+ for (int i = 0; i < stateDim; i++) {
+ System.arraycopy(p, index, dYdP[i], 0, paramDim);
+ index += paramDim;
+ }
+ }
+
+ }
+
+ /** {@inheritDoc} */
+ public void computeDerivatives(final SpacecraftState s, final TimeDerivativesEquations adder,
+ final double[] p, final double[] pDot) throws OrekitException {
+
+ final int dim = 3;
+
+ // Lazy initialization
+ if (dirty) {
+
+ if (propagator.getPropagationParametersType() != NumericalPropagator.PropagationParametersType.CARTESIAN) {
+ throw new OrekitException(OrekitMessages.PARTIAL_DERIVATIVES_ONLY_IN_CARTESIAN);
+ }
+
+ // if steps have not been set by user, set default values
+ if (Double.isNaN(hPos)) {
+ final double factor = FastMath.sqrt(MathUtils.EPSILON);
+ hPos = factor * s.getPVCoordinates().getPosition().getNorm();
+ hVel = factor * s.getPVCoordinates().getVelocity().getNorm();
+ hM = factor * s.getMass();
+ }
+
+ // set up jacobians providers
+ jacobiansProviders.clear();
+ for (final ForceModel model : propagator.getForceModels()) {
+ if (model instanceof AccelerationJacobiansProvider) {
+
+ // the force model already provides the jacobians by itself
+ jacobiansProviders.add((AccelerationJacobiansProvider) model);
+
+ } else {
+
+ // wrap the force model to compute the jacobians by finite differences
+ jacobiansProviders.add(new Jacobianizer(model, selectedParameters, hPos, hVel, hM));
+
+ }
+ }
+ jacobiansProviders.add(propagator.getNewtonianAttractionForceModel());
+
+ // check all parameters are handled by at least one jacobian provider
+ for (final ParameterConfiguration param : selectedParameters) {
+ final String name = param.getParameterName();
+ boolean found = false;
+ for (final AccelerationJacobiansProvider provider : jacobiansProviders) {
+ if (provider.isSupported(name)) {
+ param.setProvider(provider);
+ found = true;
+ }
+ }
+ if (!found) {
+ throw new OrekitException(OrekitMessages.UNKNOWN_PARAMETER, name);
+ }
+ }
+
+ // check the numbers of parameters and matrix size agree
+ if (selectedParameters.size() != paramDim) {
+ throw new OrekitException(OrekitMessages.INITIAL_MATRIX_AND_PARAMETERS_NUMBER_MISMATCH,
+ paramDim, selectedParameters.size());
+ }
+
+ dAccdParam = new double[dim];
+ dAccdPos = new double[dim][dim];
+ dAccdVel = new double[dim][dim];
+ dAccdM = (stateDim > 6) ? new double[dim] : null;
+
+ dirty = false;
+
+ }
+
+ // compute forces gradients dAccDState
+ for (final double[] row : dAccdPos) {
+ Arrays.fill(row, 0.0);
+ }
+ for (final double[] row : dAccdVel) {
+ Arrays.fill(row, 0.0);
+ }
+ if (dAccdM != null) {
+ Arrays.fill(dAccdM, 0.0);
+ }
+ for (final AccelerationJacobiansProvider jacobProv : jacobiansProviders) {
+ jacobProv.addDAccDState(s, dAccdPos, dAccdVel, dAccdM);
+ }
+
+ // the variational equations of the complete state jacobian matrix have the
+ // following form for 7x7, i.e. when mass partial derivatives are also considered
+ // (when mass is not considered, only the A, B, D and E matrices are used along
+ // with their derivatives):
+
+ // [ ] [ ] [ ] [ ] [ ] [ ] [ ] [ ] [ ]
+ // [ Adot ] [ Bdot ] [ Cdot ] [ dVel/dPos = 0 ] [ dVel/dVel = Id ] [ dVel/dm = 0 ] [ A ] [ B ] [ C ]
+ // [ ] [ ] [ ] [ ] [ ] [ ] [ ] [ ] [ ]
+ // --------+--------+--- ---- ------------------+------------------+---------------- -----+-----+-----
+ // [ ] [ ] [ ] [ ] [ ] [ ] [ ] [ ] [ ]
+ // [ Ddot ] [ Edot ] [ Fdot ] = [ dAcc/dPos ] [ dAcc/dVel ] [ dAcc/dm ] * [ D ] [ E ] [ F ]
+ // [ ] [ ] [ ] [ ] [ ] [ ] [ ] [ ] [ ]
+ // --------+--------+--- ---- ------------------+------------------+---------------- -----+-----+-----
+ // [ Gdot ] [ Hdot ] [ Idot ] [ dmDot/dPos = 0 ] [ dmDot/dVel = 0 ] [ dmDot/dm = 0 ] [ G ] [ H ] [ I ]
+
+ // The A, B, D and E sub-matrices and their derivatives (Adot ...) are 3x3 matrices,
+ // the C and F sub-matrices and their derivatives (Cdot ...) are 3x1 matrices,
+ // the G and H sub-matrices and their derivatives (Gdot ...) are 1x3 matrices,
+ // the I sub-matrix and its derivative (Idot) are 1x1 matrices.
+
+ // The expanded multiplication above can be rewritten to take into account
+ // the fixed values found in the sub-matrices in the left factor. This leads to:
+
+ // [ Adot ] = [ D ]
+ // [ Bdot ] = [ E ]
+ // [ Cdot ] = [ F ]
+ // [ Ddot ] = [ dAcc/dPos ] * [ A ] + [ dAcc/dVel ] * [ D ] + [ dAcc/dm ] * [ G ]
+ // [ Edot ] = [ dAcc/dPos ] * [ B ] + [ dAcc/dVel ] * [ E ] + [ dAcc/dm ] * [ H ]
+ // [ Fdot ] = [ dAcc/dPos ] * [ C ] + [ dAcc/dVel ] * [ F ] + [ dAcc/dm ] * [ I ]
+ // [ Gdot ] = [ 0 ]
+ // [ Hdot ] = [ 0 ]
+ // [ Idot ] = [ 0 ]
+
+ // The following loops compute these expressions taking care of the mapping of the
+ // (A, B, ... I) matrices into the single dimension array p and of the mapping of the
+ // (Adot, Bdot, ... Idot) matrices into the single dimension array pDot.
+
+ // copy D, E and F into Adot, Bdot and Cdot
+ System.arraycopy(p, dim * stateDim, pDot, 0, dim * stateDim);
+
+ // compute Ddot, Edot and Fdot
+ for (int i = 0; i < dim; ++i) {
+ final double[] dAdPi = dAccdPos[i];
+ final double[] dAdVi = dAccdVel[i];
+ for (int j = 0; j < stateDim; ++j) {
+ pDot[(dim + i) * stateDim + j] =
+ dAdPi[0] * p[j] + dAdPi[1] * p[j + stateDim] + dAdPi[2] * p[j + 2 * stateDim] +
+ dAdVi[0] * p[j + 3 * stateDim] + dAdVi[1] * p[j + 4 * stateDim] + dAdVi[2] * p[j + 5 * stateDim] +
+ ((dAccdM == null) ? 0.0 : dAccdM[i] * p[j + 6 * stateDim]);
+ }
+ }
+
+ if (dAccdM != null) {
+ // set Gdot, Hdot and Idot to 0
+ Arrays.fill(pDot, 6 * stateDim, 7 * stateDim, 0.0);
+ }
+
+ for (int k = 0; k < paramDim; ++k) {
+
+ // compute the acceleration gradient with respect to current parameter
+ final ParameterConfiguration param = selectedParameters.get(k);
+ final AccelerationJacobiansProvider provider = param.getProvider();
+ Arrays.fill(dAccdParam, 0.0);
+ provider.addDAccDParam(s, param.getParameterName(), dAccdParam);
+
+ // the variational equations of the parameters jacobian matrix are computed
+ // one column at a time, they have the following form:
+ // [ ] [ ] [ ] [ ] [ ] [ ]
+ // [ Jdot ] [ dVel/dPos = 0 ] [ dVel/dVel = Id ] [ dVel/dm = 0 ] [ J ] [ dVel/dParam = 0 ]
+ // [ ] [ ] [ ] [ ] [ ] [ ]
+ // -------- ------------------+------------------+---------------- ----- --------------------
+ // [ ] [ ] [ ] [ ] [ ] [ ]
+ // [ Kdot ] = [ dAcc/dPos ] [ dAcc/dVel ] [ dAcc/dm ] * [ K ] + [ dAcc/dParam ]
+ // [ ] [ ] [ ] [ ] [ ] [ ]
+ // -------- ------------------+------------------+---------------- ----- --------------------
+ // [ Ldot ] [ dmDot/dPos = 0 ] [ dmDot/dVel = 0 ] [ dmDot/dm = 0 ] [ L ] [ dmDot/dParam = 0 ]
+
+ // The J and K sub-columns and their derivatives (Jdot ...) are 3 elements columns,
+ // the L sub-colums and its derivative (Ldot) are 1 elements columns.
+
+ // The expanded multiplication and addition above can be rewritten to take into
+ // account the fixed values found in the sub-matrices in the left factor. This leads to:
+
+ // [ Jdot ] = [ K ]
+ // [ Kdot ] = [ dAcc/dPos ] * [ J ] + [ dAcc/dVel ] * [ K ] + [ dAcc/dm ] * [ L ] + [ dAcc/dParam ]
+ // [ Ldot ] = [ 0 ]
+
+ // The following loops compute these expressions taking care of the mapping of the
+ // (J, K, L) columns into the single dimension array p and of the mapping of the
+ // (Jdot, Kdot, Ldot) columns into the single dimension array pDot.
+
+ // copy K into Jdot
+ final int columnTop = stateDim * stateDim + k;
+ pDot[columnTop] = p[columnTop + 3 * paramDim];
+ pDot[columnTop + paramDim] = p[columnTop + 4 * paramDim];
+ pDot[columnTop + 2 * paramDim] = p[columnTop + 5 * paramDim];
+
+ // compute Kdot
+ for (int i = 0; i < dim; ++i) {
+ final double[] dAdPi = dAccdPos[i];
+ final double[] dAdVi = dAccdVel[i];
+ pDot[columnTop + (dim + i) * paramDim] =
+ dAccdParam[i] +
+ dAdPi[0] * p[columnTop] + dAdPi[1] * p[columnTop + paramDim] + dAdPi[2] * p[columnTop + 2 * paramDim] +
+ dAdVi[0] * p[columnTop + 3 * paramDim] + dAdVi[1] * p[columnTop + 4 * paramDim] + dAdVi[2] * p[columnTop + 5 * paramDim] +
+ ((dAccdM == null) ? 0.0 : dAccdM[i] * p[columnTop + 6 * paramDim]);
+ }
+
+ if (dAccdM != null) {
+ // set Ldot to 0
+ pDot[columnTop + 6 * paramDim] = 0;
+ }
+
+ }
+
+ }
+
+}
+
diff --git a/src/main/java/org/orekit/propagation/numerical/StateMapper.java b/src/main/java/org/orekit/propagation/numerical/StateMapper.java
new file mode 100644
index 0000000000..9fd512351a
--- /dev/null
+++ b/src/main/java/org/orekit/propagation/numerical/StateMapper.java
@@ -0,0 +1,59 @@
+/* Copyright 2002-2010 Centre National d'Études Spatiales
+ * Licensed to CS Communication & Systèmes (CS) under one or more
+ * contributor license agreements. See the NOTICE file distributed with
+ * this work for additional information regarding copyright ownership.
+ * CS licenses this file to You under the Apache License, Version 2.0
+ * (the "License"); you may not use this file except in compliance with
+ * the License. You may obtain a copy of the License at
+ *
+ * http://www.apache.org/licenses/LICENSE-2.0
+ *
+ * Unless required by applicable law or agreed to in writing, software
+ * distributed under the License is distributed on an "AS IS" BASIS,
+ * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
+ * See the License for the specific language governing permissions and
+ * limitations under the License.
+ */
+package org.orekit.propagation.numerical;
+
+import java.io.Serializable;
+
+import org.orekit.attitudes.AttitudeLaw;
+import org.orekit.errors.OrekitException;
+import org.orekit.frames.Frame;
+import org.orekit.propagation.SpacecraftState;
+import org.orekit.time.AbsoluteDate;
+
+/** Interface defining mapping between simple state arrays and {@link SpacecraftState} instances.
+ *
+ * @see org.orekit.propagation.SpacecraftState
+ * @see org.orekit.propagation.numerical.NumericalPropagator
+ * @author Véronique Pommier-Maurussane
+ * @version $Revision$ $Date$
+ */
+public interface StateMapper extends Serializable {
+
+ /** Set the attitude law.
+ * @param attitudeLaw attitude law
+ */
+ void setAttitudeLaw(final AttitudeLaw attitudeLaw);
+
+ /** Convert spacecraft state to state array.
+ * @param s spacecraft state to map
+ * @param stateVector flat array into which the state vector should be mapped */
+ void mapStateToArray(SpacecraftState s, double[] stateVector);
+
+ /** Convert state array to space dynamics objects (AbsoluteDate and OrbitalParameters).
+ * @param array state as a flat array
+ * @param date integration date
+ * @param mu central attraction coefficient used for propagation (m<sup>3</sup>/s<sup>2</sup>)
+ * @param frame frame in which integration is performed
+ * @return state corresponding to the flat array as a space dynamics object
+ * @exception OrekitException if the attitude state cannot be determined
+ * by the attitude law
+ */
+ SpacecraftState mapArrayToState(final double[] array, final AbsoluteDate date,
+ final double mu, final Frame frame)
+ throws OrekitException;
+
+}
diff --git a/src/main/java/org/orekit/propagation/numerical/StateMapperCartesian.java b/src/main/java/org/orekit/propagation/numerical/StateMapperCartesian.java
new file mode 100644
index 0000000000..b82365d923
--- /dev/null
+++ b/src/main/java/org/orekit/propagation/numerical/StateMapperCartesian.java
@@ -0,0 +1,87 @@
+/* Copyright 2002-2010 Centre National d'Études Spatiales
+ * Licensed to CS Communication & Systèmes (CS) under one or more
+ * contributor license agreements. See the NOTICE file distributed with
+ * this work for additional information regarding copyright ownership.
+ * CS licenses this file to You under the Apache License, Version 2.0
+ * (the "License"); you may not use this file except in compliance with
+ * the License. You may obtain a copy of the License at
+ *
+ * http://www.apache.org/licenses/LICENSE-2.0
+ *
+ * Unless required by applicable law or agreed to in writing, software
+ * distributed under the License is distributed on an "AS IS" BASIS,
+ * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
+ * See the License for the specific language governing permissions and
+ * limitations under the License.
+ */
+package org.orekit.propagation.numerical;
+
+import org.apache.commons.math.geometry.Vector3D;
+import org.orekit.attitudes.AttitudeLaw;
+import org.orekit.errors.OrekitException;
+import org.orekit.frames.Frame;
+import org.orekit.orbits.CartesianOrbit;
+import org.orekit.propagation.SpacecraftState;
+import org.orekit.time.AbsoluteDate;
+import org.orekit.utils.PVCoordinates;
+
+/** Implementation of the {@link StateMapper} interface for state arrays in cartesian coordinates.
+ *
+ * @see org.orekit.propagation.SpacecraftState
+ * @see org.orekit.propagation.numerical.NumericalPropagator
+ * @see TimeDerivativesEquationsCartesian
+ * @author Véronique Pommier-Maurussane
+ * @version $Revision$ $Date$
+ */
+public class StateMapperCartesian implements StateMapper {
+
+ /** Serializable UID. */
+ private static final long serialVersionUID = -8228988658997240720L;
+
+ /** Attitude law. */
+ private AttitudeLaw attitudeLaw;
+
+ /** Create a new instance.
+ */
+ public StateMapperCartesian() {
+ }
+
+ /** Set the attitude law.
+ * @param attitudeLaw attitude law
+ */
+ public void setAttitudeLaw(final AttitudeLaw attitudeLaw) {
+ this.attitudeLaw = attitudeLaw;
+ }
+
+ /** {@inheritDoc} */
+ public void mapStateToArray(final SpacecraftState s, final double[] stateVector) {
+
+ final PVCoordinates pv = s.getPVCoordinates();
+ final Vector3D p = pv.getPosition();
+ final Vector3D v = pv.getVelocity();
+
+ stateVector[0] = p.getX();
+ stateVector[1] = p.getY();
+ stateVector[2] = p.getZ();
+ stateVector[3] = v.getX();
+ stateVector[4] = v.getY();
+ stateVector[5] = v.getZ();
+ stateVector[6] = s.getMass();
+
+ }
+
+ /** {@inheritDoc} */
+ public SpacecraftState mapArrayToState(final double[] stateVector, final AbsoluteDate date,
+ final double mu, final Frame frame)
+ throws OrekitException {
+
+ final Vector3D p = new Vector3D(stateVector[0], stateVector[1], stateVector[2]);
+ final Vector3D v = new Vector3D(stateVector[3], stateVector[4], stateVector[5]);
+ final PVCoordinates pv = new PVCoordinates(p, v);
+ final CartesianOrbit orbit = new CartesianOrbit(pv, frame, date, mu);
+
+ return new SpacecraftState(orbit, attitudeLaw.getAttitude(orbit), stateVector[6]);
+
+ }
+
+}
diff --git a/src/main/java/org/orekit/propagation/numerical/StateMapperEquinoctial.java b/src/main/java/org/orekit/propagation/numerical/StateMapperEquinoctial.java
new file mode 100644
index 0000000000..5095e68e08
--- /dev/null
+++ b/src/main/java/org/orekit/propagation/numerical/StateMapperEquinoctial.java
@@ -0,0 +1,74 @@
+/* Copyright 2002-2010 Centre National d'Études Spatiales
+ * Licensed to CS Communication & Systèmes (CS) under one or more
+ * contributor license agreements. See the NOTICE file distributed with
+ * this work for additional information regarding copyright ownership.
+ * CS licenses this file to You under the Apache License, Version 2.0
+ * (the "License"); you may not use this file except in compliance with
+ * the License. You may obtain a copy of the License at
+ *
+ * http://www.apache.org/licenses/LICENSE-2.0
+ *
+ * Unless required by applicable law or agreed to in writing, software
+ * distributed under the License is distributed on an "AS IS" BASIS,
+ * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
+ * See the License for the specific language governing permissions and
+ * limitations under the License.
+ */
+package org.orekit.propagation.numerical;
+
+import org.orekit.attitudes.AttitudeLaw;
+import org.orekit.errors.OrekitException;
+import org.orekit.frames.Frame;
+import org.orekit.orbits.EquinoctialOrbit;
+import org.orekit.propagation.SpacecraftState;
+import org.orekit.time.AbsoluteDate;
+
+/** Implementation of the {@link StateMapper} interface for state arrays in equinoctial parameters.
+*
+* @see org.orekit.propagation.SpacecraftState
+* @see org.orekit.propagation.numerical.NumericalPropagator
+* @see TimeDerivativesEquationsEquinoctial
+* @author Véronique Pommier-Maurussane
+* @version $Revision$ $Date$
+*/
+public class StateMapperEquinoctial implements StateMapper {
+
+ /** Serializable UID. */
+ private static final long serialVersionUID = 2882088208801391437L;
+
+ /** Attitude law. */
+ private AttitudeLaw attitudeLaw;
+
+ /** Set the attitude law.
+ * @param attitudeLaw attitude law
+ */
+ public void setAttitudeLaw(final AttitudeLaw attitudeLaw) {
+ this.attitudeLaw = attitudeLaw;
+ }
+
+ /** {@inheritDoc} */
+ public void mapStateToArray(final SpacecraftState s, final double[] stateVector) {
+
+ stateVector[0] = s.getA();
+ stateVector[1] = s.getEquinoctialEx();
+ stateVector[2] = s.getEquinoctialEy();
+ stateVector[3] = s.getHx();
+ stateVector[4] = s.getHy();
+ stateVector[5] = s.getLv();
+ stateVector[6] = s.getMass();
+
+ }
+
+ /** {@inheritDoc} */
+ public SpacecraftState mapArrayToState(final double[] stateVector, final AbsoluteDate date,
+ final double mu, final Frame frame) throws OrekitException {
+ final EquinoctialOrbit orbit =
+ new EquinoctialOrbit(stateVector[0], stateVector[1], stateVector[2], stateVector[3],
+ stateVector[4], stateVector[5], EquinoctialOrbit.TRUE_LATITUDE_ARGUMENT,
+ frame, date, mu);
+
+ return new SpacecraftState(orbit, attitudeLaw.getAttitude(orbit), stateVector[6]);
+
+ }
+
+}
diff --git a/src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquations.java b/src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquations.java
index 8f95bd0a87..0a3c6a89e1 100644
--- a/src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquations.java
+++ b/src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquations.java
@@ -17,36 +17,32 @@
package org.orekit.propagation.numerical;
import java.io.Serializable;
-import java.util.Arrays;
+
import org.apache.commons.math.geometry.Vector3D;
-import org.apache.commons.math.util.FastMath;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitMessages;
import org.orekit.errors.PropagationException;
import org.orekit.frames.Frame;
-import org.orekit.frames.Transform;
-import org.orekit.orbits.EquinoctialOrbit;
-import org.orekit.utils.PVCoordinates;
-
+import org.orekit.orbits.Orbit;
-/** This class sums up the contribution of several forces into orbit and mass derivatives.
+/** Interface summing up the contribution of several forces into orbit and mass derivatives.
*
- * <p>The aim of this class is to gather the contributions of various perturbing
+ * <p>The aim of this interface is to gather the contributions of various perturbing
* forces expressed as accelerations into one set of time-derivatives of
- * {@link org.orekit.orbits.EquinoctialOrbit} plus one mass derivatives.
- * It implements Gauss equations for the equinoctial parameters.</p>
+ * {@link org.orekit.orbits.Orbit} plus one mass derivatives.
+ * It implements Gauss equations for different kind of parameters.</p>
* <p>
* The state vector handled internally has the form that follows:
* <pre>
- * y[0]Â = a
- * y[1]Â = ex
- * y[2]Â = ey
- * y[3]Â = hx
- * y[4]Â = hy
- * y[5]Â = lv
- * y[6]Â = mass
+ * y[0]Â
+ * y[1]
+ * y[2]
+ * y[3]
+ * y[4]
+ * y[5]
+ * y[6]
* </pre>
- * where the six firsts paramters stands for the equinoctial parameters and the 7th
+ * where the six firsts parameters stands for the chosen parameters and the 7th
* for the mass (kg) at the current time.
* </p>
* <p>The proper way to use this class is to have the object implementing the
@@ -55,7 +51,7 @@ import org.orekit.utils.PVCoordinates;
* <ul>
* <li>
* reinitialize the instance using the
- * {@link #initDerivatives(double[], EquinoctialOrbit)} method
+ * {@link #initDerivatives(double[], Orbit)} method
* </li>
* <li>
* pass the instance to each force model in turn so that they can put their
@@ -67,233 +63,45 @@ import org.orekit.utils.PVCoordinates;
* </li>
* </ul>
* </p>
- * @see org.orekit.orbits.EquinoctialOrbit
+ * @see org.orekit.orbits.Orbit
* @see org.orekit.propagation.numerical.NumericalPropagator
* @author Luc Maisonobe
* @author Fabien Maussion
* @author Véronique Pommier-Maurussane
* @version $Revision$ $Date$
*/
-public class TimeDerivativesEquations implements Serializable {
+public abstract class TimeDerivativesEquations implements Serializable {
/** Serializable UID. */
- private static final long serialVersionUID = 1524631993375841290L;
+ private static final long serialVersionUID = 4183908052500627555L;
- /** Orbital parameters. */
- private EquinoctialOrbit storedParameters;
+ // CHECKSTYLE: stop VisibilityModifierCheck
/** Reference to the derivatives array to initialize. */
- private double[] storedYDot;
-
- /** First vector of the (q, s, w) local orbital frame. */
- private Vector3D lofQ;
-
- /** Second vector of the (q, s, w) local orbital frame. */
- private Vector3D lofS;
-
- /** First vector of the (t, n, w) local orbital frame. */
- private Vector3D lofT;
-
- /** Second vector of the (t, n, w) local orbital frame. */
- private Vector3D lofN;
-
- /** Third vector of both the (q, s, w) and (t, n, w) local orbital frames. */
- private Vector3D lofW;
-
- // CHECKSTYLE: stop JavadocVariable check
+ protected double[] storedYDot;
- /** Multiplicative coefficients for the perturbing accelerations along lofQ. */
- private double aQ;
- private double exQ;
- private double eyQ;
-
- /** Multiplicative coefficients for the perturbing accelerations along lofS. */
- private double aS;
- private double exS;
- private double eyS;
-
- /** Multiplicative coefficients for the perturbing accelerations along lofT. */
- private double aT;
- private double exT;
- private double eyT;
-
- /** Multiplicative coefficients for the perturbing accelerations along lofN. */
- private double exN;
- private double eyN;
-
- /** Multiplicative coefficients for the perturbing accelerations along lofW. */
- private double eyW;
- private double exW;
- private double hxW;
- private double hyW;
- private double lvW;
-
- // CHECKSTYLE: resume JavadocVariable check
-
- /** Kepler evolution on true latitude argument. */
- private double lvKepler;
+ //CHECKSTYLE: resume VisibilityModifierCheck
/** Create a new instance.
- * @param orbit current orbit parameters
*/
- protected TimeDerivativesEquations(final EquinoctialOrbit orbit) {
- this.storedParameters = orbit;
- lofQ = Vector3D.ZERO;
- lofS = Vector3D.ZERO;
- lofT = Vector3D.ZERO;
- lofN = Vector3D.ZERO;
- lofW = Vector3D.ZERO;
- updateOrbitalFrames();
- }
-
- /** Update the orbital frames. */
- private void updateOrbitalFrames() {
-
- // get the position/velocity vectors
- final PVCoordinates pvCoordinates = storedParameters.getPVCoordinates();
-
- // compute orbital plane normal vector
- lofW = pvCoordinates.getMomentum().normalize();
-
- // compute (q, s, w) local orbital frame
- lofQ = pvCoordinates.getPosition().normalize();
- lofS = Vector3D.crossProduct(lofW, lofQ);
-
- // compute (t, n, w) local orbital frame
- lofT = pvCoordinates.getVelocity().normalize();
- lofN = Vector3D.crossProduct(lofW, lofT);
-
+ protected TimeDerivativesEquations() {
}
/** Initialize all derivatives to zero.
* @param yDot reference to the array where to put the derivatives.
- * @param orbit current orbit parameters
+ * @param currentOrbit current orbit parameters
* @exception PropagationException if the orbit evolve out of supported range
*/
- protected void initDerivatives(final double[] yDot,
- final EquinoctialOrbit orbit)
- throws PropagationException {
-
-
- this.storedParameters = orbit;
- updateOrbitalFrames();
-
- // store derivatives array reference
- this.storedYDot = yDot;
-
- // initialize derivatives to zero
- Arrays.fill(storedYDot, 0.0);
-
- // intermediate variables
- final double ex = storedParameters.getEquinoctialEx();
- final double ey = storedParameters.getEquinoctialEy();
- final double ex2 = ex * ex;
- final double ey2 = ey * ey;
- final double e2 = ex2 + ey2;
- final double e = FastMath.sqrt(e2);
- if (e >= 1) {
- throw new PropagationException(OrekitMessages.ORBIT_BECOMES_HYPERBOLIC_UNABLE_TO_PROPAGATE_FURTHER, e);
- }
-
- // intermediate variables
- final double oMe2 = (1 - e) * (1 + e);
- final double epsilon = FastMath.sqrt(oMe2);
- final double a = storedParameters.getA();
- final double na = FastMath.sqrt(orbit.getMu() / a);
- final double n = na / a;
- final double lv = storedParameters.getLv();
- final double cLv = FastMath.cos(lv);
- final double sLv = FastMath.sin(lv);
- final double excLv = ex * cLv;
- final double eysLv = ey * sLv;
- final double excLvPeysLv = excLv + eysLv;
- final double ksi = 1 + excLvPeysLv;
- final double nu = ex * sLv - ey * cLv;
- final double sqrt = FastMath.sqrt(ksi * ksi + nu * nu);
- final double oPksi = 2 + excLvPeysLv;
- final double hx = storedParameters.getHx();
- final double hy = storedParameters.getHy();
- final double h2 = hx * hx + hy * hy;
- final double oPh2 = 1 + h2;
- final double hxsLvMhycLv = hx * sLv - hy * cLv;
-
- final double epsilonOnNA = epsilon / na;
- final double epsilonOnNAKsi = epsilonOnNA / ksi;
- final double epsilonOnNAKsiSqrt = epsilonOnNAKsi / sqrt;
- final double tOnEpsilonN = 2 / (n * epsilon);
- final double tEpsilonOnNASqrt = 2 * epsilonOnNA / sqrt;
- final double epsilonOnNAKsit = epsilonOnNA / (2 * ksi);
-
- // Kepler natural evolution
- lvKepler = n * ksi * ksi / (oMe2 * epsilon);
-
- // coefficients along T
- aT = tOnEpsilonN * sqrt;
- exT = tEpsilonOnNASqrt * (ex + cLv);
- eyT = tEpsilonOnNASqrt * (ey + sLv);
-
- // coefficients along N
- exN = -epsilonOnNAKsiSqrt * (2 * ey * ksi + oMe2 * sLv);
- eyN = epsilonOnNAKsiSqrt * (2 * ex * ksi + oMe2 * cLv);
-
- // coefficients along Q
- aQ = tOnEpsilonN * nu;
- exQ = epsilonOnNA * sLv;
- eyQ = -epsilonOnNA * cLv;
-
- // coefficients along S
- aS = tOnEpsilonN * ksi;
- exS = epsilonOnNAKsi * (ex + oPksi * cLv);
- eyS = epsilonOnNAKsi * (ey + oPksi * sLv);
-
- // coefficients along W
- lvW = epsilonOnNAKsi * hxsLvMhycLv;
- exW = -ey * lvW;
- eyW = ex * lvW;
- hxW = epsilonOnNAKsit * oPh2 * cLv;
- hyW = epsilonOnNAKsit * oPh2 * sLv;
-
- }
+ abstract void initDerivatives(double[] yDot, Orbit currentOrbit)
+ throws PropagationException;
/** Add the contribution of the Kepler evolution.
* <p>Since the Kepler evolution is the most important, it should
* be added after all the other ones, in order to improve
* numerical accuracy.</p>
+ * @param mu central body gravitational constant
*/
- protected void addKeplerContribution() {
- storedYDot[5] += lvKepler;
- }
-
- /** Add the contribution of an acceleration expressed in (t, n, w)
- * local orbital frame.
- * @param t acceleration along the T axis (m/s<sup>2</sup>)
- * @param n acceleration along the N axis (m/s<sup>2</sup>)
- * @param w acceleration along the W axis (m/s<sup>2</sup>)
- */
- public void addTNWAcceleration(final double t, final double n, final double w) {
- storedYDot[0] += aT * t;
- storedYDot[1] += exT * t + exN * n + exW * w;
- storedYDot[2] += eyT * t + eyN * n + eyW * w;
- storedYDot[3] += hxW * w;
- storedYDot[4] += hyW * w;
- storedYDot[5] += lvW * w;
- }
-
- /** Add the contribution of an acceleration expressed in (q, s, w)
- * local orbital frame.
- * @param q acceleration along the Q axis (m/s<sup>2</sup>)
- * @param s acceleration along the S axis (m/s<sup>2</sup>)
- * @param w acceleration along the W axis (m/s<sup>2</sup>)
- */
- public void addQSWAcceleration(final double q, final double s, final double w) {
- storedYDot[0] += aQ * q + aS * s;
- storedYDot[1] += exQ * q + exS * s + exW * w;
- storedYDot[2] += eyQ * q + eyS * s + eyW * w;
- storedYDot[3] += hxW * w;
- storedYDot[4] += hyW * w;
- storedYDot[5] += lvW * w;
- }
-
+ public abstract void addKeplerContribution(final double mu);
/** Add the contribution of an acceleration expressed in the inertial frame
* (it is important to make sure this acceleration is defined in the
@@ -302,26 +110,14 @@ public class TimeDerivativesEquations implements Serializable {
* @param y acceleration along the Y axis (m/s<sup>2</sup>)
* @param z acceleration along the Z axis (m/s<sup>2</sup>)
*/
- public void addXYZAcceleration(final double x, final double y, final double z) {
- addTNWAcceleration(x * lofT.getX() + y * lofT.getY() + z * lofT.getZ(),
- x * lofN.getX() + y * lofN.getY() + z * lofN.getZ(),
- x * lofW.getX() + y * lofW.getY() + z * lofW.getZ());
- }
+ public abstract void addXYZAcceleration(final double x, final double y, final double z);
/** Add the contribution of an acceleration expressed in some inertial frame.
* @param gamma acceleration vector (m/s<sup>2</sup>)
* @param frame frame in which acceleration is defined (must be an inertial frame)
* @exception OrekitException if frame transforms cannot be computed
*/
- public void addAcceleration(final Vector3D gamma, final Frame frame)
- throws OrekitException {
- final Transform t = frame.getTransformTo(storedParameters.getFrame(),
- storedParameters.getDate());
- final Vector3D gammInRefFrame = t.transformVector(gamma);
- addTNWAcceleration(Vector3D.dotProduct(gammInRefFrame, lofT),
- Vector3D.dotProduct(gammInRefFrame, lofN),
- Vector3D.dotProduct(gammInRefFrame, lofW));
- }
+ public abstract void addAcceleration(final Vector3D gamma, final Frame frame) throws OrekitException;
/** Add the contribution of the flow rate (dm/dt).
* @param q the flow rate, must be negative (dm/dt)
@@ -334,37 +130,5 @@ public class TimeDerivativesEquations implements Serializable {
storedYDot[6] += q;
}
- /** Get the first vector of the (q, s, w) local orbital frame.
- * @return first vector of the (q, s, w) local orbital frame */
- public Vector3D getQ() {
- return lofQ;
- }
-
- /** Get the second vector of the (q, s, w) local orbital frame.
- * @return second vector of the (q, s, w) local orbital frame */
- public Vector3D getS() {
- return lofS;
- }
-
- /** Get the first vector of the (t, n, w) local orbital frame.
- * @return first vector of the (t, n, w) local orbital frame */
- public Vector3D getT() {
- return lofT;
- }
-
- /** Get the second vector of the (t, n, w) local orbital frame.
- * @return second vector of the (t, n, w) local orbital frame */
- public Vector3D getN() {
- return lofN;
- }
-
- /** Get the third vector of both the (q, s, w) and (t, n, w) local orbital
- * frames.
- * @return third vector of both the (q, s, w) and (t, n, w) local orbital
- * frames
- */
- public Vector3D getW() {
- return lofW;
- }
}
diff --git a/src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquationsCartesian.java b/src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquationsCartesian.java
new file mode 100644
index 0000000000..551a0b3dbe
--- /dev/null
+++ b/src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquationsCartesian.java
@@ -0,0 +1,114 @@
+/* Copyright 2002-2010 CS Centre National d'Études Spatiales
+ * Licensed to CS Communication & Systèmes (CS) under one or more
+ * contributor license agreements. See the NOTICE file distributed with
+ * this work for additional information regarding copyright ownership.
+ * CS licenses this file to You under the Apache License, Version 2.0
+ * (the "License"); you may not use this file except in compliance with
+ * the License. You may obtain a copy of the License at
+ *
+ * http://www.apache.org/licenses/LICENSE-2.0
+ *
+ * Unless required by applicable law or agreed to in writing, software
+ * distributed under the License is distributed on an "AS IS" BASIS,
+ * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
+ * See the License for the specific language governing permissions and
+ * limitations under the License.
+ */
+package org.orekit.propagation.numerical;
+
+import java.util.Arrays;
+
+import org.apache.commons.math.geometry.Vector3D;
+import org.apache.commons.math.util.FastMath;
+import org.orekit.errors.OrekitException;
+import org.orekit.errors.PropagationException;
+import org.orekit.frames.Frame;
+import org.orekit.frames.Transform;
+import org.orekit.orbits.CartesianOrbit;
+import org.orekit.orbits.Orbit;
+
+/** Implementation of the {@link TimeDerivativesEquations} interface for state arrays in cartesian coordinates
+*
+* <p>It implements Gauss equations for cartesian parameters. This implementation is specialized
+* for state vectors that have the following form:
+* <pre>
+* y[0]Â = x
+* y[1]Â = y
+* y[2]Â = z
+* y[3]Â = v<sub>x</sub>
+* y[4]Â = v<sub>y</sub>
+* y[5]Â = v<sub>z</sub>
+* y[6]Â = mass
+* </pre>
+* where the six first parameters stands for the cartesian parameters and the 7<sup>th</sup>
+* for the mass (kg) at the current time.
+* </p>
+* @see org.orekit.orbits.CartesianOrbit
+* @see org.orekit.propagation.numerical.NumericalPropagator
+* @author Luc Maisonobe
+* @author Fabien Maussion
+* @author Véronique Pommier-Maurussane
+* @version $Revision$ $Date$
+*/
+public class TimeDerivativesEquationsCartesian extends TimeDerivativesEquations {
+
+ /** Serializable UID. */
+ private static final long serialVersionUID = -1882870530923825699L;
+
+ /** Orbital parameters. */
+ private CartesianOrbit storedParameters;
+
+ /** Create a new instance.
+ * @param orbit current orbit parameters
+ */
+ public TimeDerivativesEquationsCartesian(final CartesianOrbit orbit) {
+ this.storedParameters = orbit;
+ }
+
+ /** {@inheritDoc} */
+ public void addAcceleration(final Vector3D gamma, final Frame frame)
+ throws OrekitException {
+ final Transform t = frame.getTransformTo(storedParameters.getFrame(),
+ storedParameters.getDate());
+ final Vector3D gammInRefFrame = t.transformVector(gamma);
+ addXYZAcceleration(gammInRefFrame.getX(), gammInRefFrame.getY(), gammInRefFrame.getZ());
+ }
+
+ /** {@inheritDoc} */
+ public void addKeplerContribution(final double mu) {
+ final Vector3D position = storedParameters.getPVCoordinates().getPosition();
+ final double r2 = position.getNormSq();
+ final double coeff = -mu / (r2 * FastMath.sqrt(r2));
+ storedYDot[3] += coeff * position.getX();
+ storedYDot[4] += coeff * position.getY();
+ storedYDot[5] += coeff * position.getZ();
+ }
+
+ /** {@inheritDoc} */
+ public void addXYZAcceleration(final double x, final double y, final double z) {
+ storedYDot[3] += x;
+ storedYDot[4] += y;
+ storedYDot[5] += z;
+ }
+
+ /** {@inheritDoc} */
+ void initDerivatives(final double[] yDot, final Orbit orbit)
+ throws PropagationException {
+
+ storedParameters = (CartesianOrbit) orbit;
+
+ // store derivatives array reference
+ this.storedYDot = yDot;
+
+ // initialize derivatives to zero
+ Arrays.fill(storedYDot, 0.0);
+
+ // position derivative is velocity
+ final Vector3D velocity = storedParameters.getPVCoordinates().getVelocity();
+ storedYDot[0] = velocity.getX();
+ storedYDot[1] = velocity.getY();
+ storedYDot[2] = velocity.getZ();
+
+ }
+
+}
diff --git a/src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquationsEquinoctial.java b/src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquationsEquinoctial.java
new file mode 100644
index 0000000000..c9c1d47550
--- /dev/null
+++ b/src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquationsEquinoctial.java
@@ -0,0 +1,280 @@
+/* Copyright 2002-2010 CS Communication & Systèmes
+ * Licensed to CS Communication & Systèmes (CS) under one or more
+ * contributor license agreements. See the NOTICE file distributed with
+ * this work for additional information regarding copyright ownership.
+ * CS licenses this file to You under the Apache License, Version 2.0
+ * (the "License"); you may not use this file except in compliance with
+ * the License. You may obtain a copy of the License at
+ *
+ * http://www.apache.org/licenses/LICENSE-2.0
+ *
+ * Unless required by applicable law or agreed to in writing, software
+ * distributed under the License is distributed on an "AS IS" BASIS,
+ * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
+ * See the License for the specific language governing permissions and
+ * limitations under the License.
+ */
+package org.orekit.propagation.numerical;
+
+import java.util.Arrays;
+
+import org.apache.commons.math.geometry.Vector3D;
+import org.apache.commons.math.util.FastMath;
+import org.orekit.errors.OrekitException;
+import org.orekit.errors.OrekitMessages;
+import org.orekit.errors.PropagationException;
+import org.orekit.frames.Frame;
+import org.orekit.frames.Transform;
+import org.orekit.orbits.EquinoctialOrbit;
+import org.orekit.orbits.Orbit;
+import org.orekit.utils.PVCoordinates;
+
+/** Implementation of the {@link TimeDerivativesEquations} interface for state arrays in cartesian coordinates
+ *
+ * <p>It implements Gauss equations for equinoctial parameters. This implementation is specialized for
+ * state vectors that have the following form:
+ * <pre>
+ * y[0]Â = a
+ * y[1]Â = e<sub>x</sub>
+ * y[2]Â = e<sub>y</sub>
+ * y[3]Â = h<sub>x</sub>
+ * y[4]Â = h<sub>y</sub>
+ * y[5]Â = l<sub>v</sub>
+ * y[6]Â = mass
+ * </pre>
+ * where the six first parameters stands for the equinoctial parameters and the 7<sup>th</sup>
+ * for the mass (kg) at the current time.
+ * </p>
+ * @see org.orekit.orbits.EquinoctialOrbit
+ * @see org.orekit.propagation.numerical.NumericalPropagator
+ * @author Luc Maisonobe
+ * @author Fabien Maussion
+ * @author Véronique Pommier-Maurussane
+ * @version $Revision$ $Date$
+ */
+public class TimeDerivativesEquationsEquinoctial extends TimeDerivativesEquations {
+
+ /** Serializable UID. */
+ private static final long serialVersionUID = -7676218190057010433L;
+
+ /** First vector of the (q, s, w) local orbital frame. */
+ private Vector3D lofQ;
+
+ /** Second vector of the (q, s, w) local orbital frame. */
+ private Vector3D lofS;
+
+ /** First vector of the (t, n, w) local orbital frame. */
+ private Vector3D lofT;
+
+ /** Second vector of the (t, n, w) local orbital frame. */
+ private Vector3D lofN;
+
+ /** Third vector of both the (q, s, w) and (t, n, w) local orbital frames. */
+ private Vector3D lofW;
+
+ // CHECKSTYLE: stop JavadocVariable check
+
+ /** Multiplicative coefficients for the perturbing accelerations along lofT. */
+ private double aT;
+ private double exT;
+ private double eyT;
+
+ /** Multiplicative coefficients for the perturbing accelerations along lofN. */
+ private double exN;
+ private double eyN;
+
+ /** Multiplicative coefficients for the perturbing accelerations along lofW. */
+ private double eyW;
+ private double exW;
+ private double hxW;
+ private double hyW;
+ private double lvW;
+
+ // CHECKSTYLE: resume JavadocVariable check
+
+ /** Kepler evolution on true latitude argument. */
+ private double lvKepler;
+
+ /** Orbital parameters. */
+ private EquinoctialOrbit storedParameters;
+
+ /** Create a new instance.
+ * @param orbit current orbit parameters
+ */
+ public TimeDerivativesEquationsEquinoctial(final EquinoctialOrbit orbit) {
+ this.storedParameters = orbit;
+ lofQ = Vector3D.ZERO;
+ lofS = Vector3D.ZERO;
+ lofT = Vector3D.ZERO;
+ lofN = Vector3D.ZERO;
+ lofW = Vector3D.ZERO;
+ updateOrbitalFrames();
+ }
+
+ /** Update the orbital frames. */
+ private void updateOrbitalFrames() {
+ // get the position/velocity vectors
+ final PVCoordinates pvCoordinates = storedParameters.getPVCoordinates();
+
+ // compute orbital plane normal vector
+ lofW = pvCoordinates.getMomentum().normalize();
+
+ // compute (q, s, w) local orbital frame
+ lofQ = pvCoordinates.getPosition().normalize();
+ lofS = Vector3D.crossProduct(lofW, lofQ);
+
+ // compute (t, n, w) local orbital frame
+ lofT = pvCoordinates.getVelocity().normalize();
+ lofN = Vector3D.crossProduct(lofW, lofT);
+ }
+
+
+ /** {@inheritDoc} */
+ public void initDerivatives(final double[] yDot, final Orbit orbit)
+ throws PropagationException {
+
+
+ storedParameters = (EquinoctialOrbit) orbit;
+ updateOrbitalFrames();
+
+ // store derivatives array reference
+ this.storedYDot = yDot;
+
+ // initialize derivatives to zero
+ Arrays.fill(storedYDot, 0.0);
+
+ // intermediate variables
+ final double ex = storedParameters.getEquinoctialEx();
+ final double ey = storedParameters.getEquinoctialEy();
+ final double ex2 = ex * ex;
+ final double ey2 = ey * ey;
+ final double e2 = ex2 + ey2;
+ final double e = FastMath.sqrt(e2);
+ if (e >= 1) {
+ throw new PropagationException(OrekitMessages.ORBIT_BECOMES_HYPERBOLIC_UNABLE_TO_PROPAGATE_FURTHER, e);
+ }
+
+ // intermediate variables
+ final double oMe2 = (1 - e) * (1 + e);
+ final double epsilon = FastMath.sqrt(oMe2);
+ final double a = storedParameters.getA();
+ final double mu = orbit.getMu();
+ final double na = FastMath.sqrt(mu / a);
+ final double n = na / a;
+ final double lv = storedParameters.getLv();
+ final double cLv = FastMath.cos(lv);
+ final double sLv = FastMath.sin(lv);
+ final double excLv = ex * cLv;
+ final double eysLv = ey * sLv;
+ final double excLvPeysLv = excLv + eysLv;
+ final double ksi = 1 + excLvPeysLv;
+ final double nu = ex * sLv - ey * cLv;
+ final double sqrt = FastMath.sqrt(ksi * ksi + nu * nu);
+ final double hx = storedParameters.getHx();
+ final double hy = storedParameters.getHy();
+ final double h2 = hx * hx + hy * hy;
+ final double oPh2 = 1 + h2;
+ final double hxsLvMhycLv = hx * sLv - hy * cLv;
+
+ final double epsilonOnNA = epsilon / na;
+ final double epsilonOnNAKsi = epsilonOnNA / ksi;
+ final double epsilonOnNAKsiSqrt = epsilonOnNAKsi / sqrt;
+ final double tOnEpsilonN = 2 / (n * epsilon);
+ final double tEpsilonOnNASqrt = 2 * epsilonOnNA / sqrt;
+ final double epsilonOnNAKsit = epsilonOnNA / (2 * ksi);
+
+ // Kepler natural evolution without the mu part
+ lvKepler = n * ksi * ksi / (FastMath.sqrt(mu) * oMe2 * epsilon);
+
+ // coefficients along T
+ aT = tOnEpsilonN * sqrt;
+ exT = tEpsilonOnNASqrt * (ex + cLv);
+ eyT = tEpsilonOnNASqrt * (ey + sLv);
+
+ // coefficients along N
+ exN = -epsilonOnNAKsiSqrt * (2 * ey * ksi + oMe2 * sLv);
+ eyN = epsilonOnNAKsiSqrt * (2 * ex * ksi + oMe2 * cLv);
+
+ // coefficients along W
+ lvW = epsilonOnNAKsi * hxsLvMhycLv;
+ exW = -ey * lvW;
+ eyW = ex * lvW;
+ hxW = epsilonOnNAKsit * oPh2 * cLv;
+ hyW = epsilonOnNAKsit * oPh2 * sLv;
+
+ }
+
+ /** {@inheritDoc} */
+ public void addKeplerContribution(final double mu) {
+ storedYDot[5] += lvKepler * FastMath.sqrt(mu);
+ }
+
+ /** Add the contribution of an acceleration expressed in (t, n, w)
+ * local orbital frame.
+ * @param t acceleration along the T axis (m/s<sup>2</sup>)
+ * @param n acceleration along the N axis (m/s<sup>2</sup>)
+ * @param w acceleration along the W axis (m/s<sup>2</sup>)
+ */
+ private void addTNWAcceleration(final double t, final double n, final double w) {
+ storedYDot[0] += aT * t;
+ storedYDot[1] += exT * t + exN * n + exW * w;
+ storedYDot[2] += eyT * t + eyN * n + eyW * w;
+ storedYDot[3] += hxW * w;
+ storedYDot[4] += hyW * w;
+ storedYDot[5] += lvW * w;
+ }
+
+
+ /** {@inheritDoc} */
+ public void addXYZAcceleration(final double x, final double y, final double z) {
+ addTNWAcceleration(x * lofT.getX() + y * lofT.getY() + z * lofT.getZ(),
+ x * lofN.getX() + y * lofN.getY() + z * lofN.getZ(),
+ x * lofW.getX() + y * lofW.getY() + z * lofW.getZ());
+ }
+
+ /** {@inheritDoc} */
+ public void addAcceleration(final Vector3D gamma, final Frame frame)
+ throws OrekitException {
+ final Transform t = frame.getTransformTo(storedParameters.getFrame(),
+ storedParameters.getDate());
+ final Vector3D gammInRefFrame = t.transformVector(gamma);
+ addTNWAcceleration(Vector3D.dotProduct(gammInRefFrame, lofT),
+ Vector3D.dotProduct(gammInRefFrame, lofN),
+ Vector3D.dotProduct(gammInRefFrame, lofW));
+ }
+
+
+ /** Get the first vector of the (q, s, w) local orbital frame.
+ * @return first vector of the (q, s, w) local orbital frame */
+ public Vector3D getQ() {
+ return lofQ;
+ }
+
+ /** Get the second vector of the (q, s, w) local orbital frame.
+ * @return second vector of the (q, s, w) local orbital frame */
+ public Vector3D getS() {
+ return lofS;
+ }
+
+ /** Get the first vector of the (t, n, w) local orbital frame.
+ * @return first vector of the (t, n, w) local orbital frame */
+ public Vector3D getT() {
+ return lofT;
+ }
+
+ /** Get the second vector of the (t, n, w) local orbital frame.
+ * @return second vector of the (t, n, w) local orbital frame */
+ public Vector3D getN() {
+ return lofN;
+ }
+
+ /** Get the third vector of both the (q, s, w) and (t, n, w) local orbital
+ * frames.
+ * @return third vector of both the (q, s, w) and (t, n, w) local orbital
+ * frames
+ */
+ public Vector3D getW() {
+ return lofW;
+ }
+
+}
diff --git a/src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquationsWithJacobians.java b/src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquationsWithJacobians.java
deleted file mode 100644
index a78c6cbb85..0000000000
--- a/src/main/java/org/orekit/propagation/numerical/TimeDerivativesEquationsWithJacobians.java
+++ /dev/null
@@ -1,90 +0,0 @@
-/* Copyright 2002-2010 CS Communication & Systèmes
- * Licensed to CS Communication & Systèmes (CS) under one or more
- * contributor license agreements. See the NOTICE file distributed with
- * this work for additional information regarding copyright ownership.
- * CS licenses this file to You under the Apache License, Version 2.0
- * (the "License"); you may not use this file except in compliance with
- * the License. You may obtain a copy of the License at
- *
- * http://www.apache.org/licenses/LICENSE-2.0
- *
- * Unless required by applicable law or agreed to in writing, software
- * distributed under the License is distributed on an "AS IS" BASIS,
- * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
- * See the License for the specific language governing permissions and
- * limitations under the License.
- */
-package org.orekit.propagation.numerical;
-
-import java.util.Arrays;
-
-import org.orekit.errors.PropagationException;
-import org.orekit.orbits.EquinoctialOrbit;
-
-
-/** This class sums up the contribution of several forces into
- * orbit and mass derivatives and partial derivatives.
- * <p>
- * As of 5.0, this class is still considered experimental, so use it with care.
- * </p>
- * <p>
- * It is related to {@link NumericalPropagatorWithJacobians} like
- * {@link TimeDerivativesEquations} to {@link NumericalPropagator}.
- * </p>
- *
- * @see TimeDerivativesEquations
- * @see NumericalPropagator
- * @see NumericalPropagatorWithJacobians
- *
- * @author Pascal Parraud
- * @version $Revision$ $Date$
- */
-public class TimeDerivativesEquationsWithJacobians extends TimeDerivativesEquations {
-
- /** Serializable UID. */
- private static final long serialVersionUID = -1378236382967204061L;
-
- /** Reference to the orbital parameters jacobian array to initialize. */
- private double[][] storedDFDY;
-
- /** Reference to the force models parameters jacobian array to initialize. */
- private double[][] storedDFDP;
-
- /** Create a new instance.
- * @param orbit current orbit parameters
- */
- protected TimeDerivativesEquationsWithJacobians(final EquinoctialOrbit orbit) {
- super(orbit);
- }
-
- /** Initialize all derivatives and jacobians to zero.
- * @param yDot reference to the array where to put the derivatives.
- * @param dFdY placeholder array where to put the jacobian of the ODE with respect to the state vector
- * @param dFdP placeholder array where to put the jacobian of the ODE with respect to the parameters
- * @param orbit current orbit parameters
- * @exception PropagationException if the orbit evolve out of supported range
- */
- protected void initDerivativesWithJacobians(final double[] yDot,
- final double[][] dFdY,
- final double[][] dFdP,
- final EquinoctialOrbit orbit)
- throws PropagationException {
-
- initDerivatives(yDot, orbit);
-
- // store jacobians reference
- this.storedDFDY = dFdY;
- this.storedDFDP = dFdP;
-
- // initialize jacobians to zero
- for (final double[] row : storedDFDY) {
- Arrays.fill(row, 0.0);
- }
-
- for (final double[] row : storedDFDP) {
- Arrays.fill(row, 0.0);
- }
-
- }
-
-}
diff --git a/src/main/java/org/orekit/propagation/package.html b/src/main/java/org/orekit/propagation/package.html
index 11ff5daa25..ffc19ef73c 100644
--- a/src/main/java/org/orekit/propagation/package.html
+++ b/src/main/java/org/orekit/propagation/package.html
@@ -57,10 +57,6 @@ This package provides tools to propagate orbital states with different methods.
ask for the next first time derivative, etc. until it reaches the final
asked date.
</p>
-<p> The {@link org.orekit.propagation.numerical.NumericalPropagatorWithJacobians}
- is a specialized class which enables to compute jacobians with respect to orbital
- parameters and force models parameters while propagating.
-</p>
@author Luc Maisonobe
@author Fabien Maussion
diff --git a/src/main/java/org/orekit/propagation/precomputed/IntegratedEphemeris.java b/src/main/java/org/orekit/propagation/precomputed/IntegratedEphemeris.java
index 0fab821dbf..f3080379f5 100644
--- a/src/main/java/org/orekit/propagation/precomputed/IntegratedEphemeris.java
+++ b/src/main/java/org/orekit/propagation/precomputed/IntegratedEphemeris.java
@@ -16,19 +16,21 @@
*/
package org.orekit.propagation.precomputed;
+import java.util.List;
+
import org.apache.commons.math.exception.MathUserException;
import org.apache.commons.math.ode.ContinuousOutputModel;
import org.apache.commons.math.ode.sampling.StepHandler;
import org.apache.commons.math.ode.sampling.StepInterpolator;
-import org.orekit.attitudes.AttitudeLaw;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitMessages;
import org.orekit.errors.PropagationException;
import org.orekit.frames.Frame;
-import org.orekit.orbits.EquinoctialOrbit;
import org.orekit.propagation.BoundedPropagator;
import org.orekit.propagation.SpacecraftState;
+import org.orekit.propagation.numerical.AdditionalStateAndEquations;
import org.orekit.propagation.numerical.ModeHandler;
+import org.orekit.propagation.numerical.StateMapper;
import org.orekit.time.AbsoluteDate;
import org.orekit.utils.PVCoordinates;
@@ -70,7 +72,10 @@ public class IntegratedEphemeris
implements BoundedPropagator, ModeHandler, StepHandler {
/** Serializable UID. */
- private static final long serialVersionUID = 3997196481383054719L;
+ private static final long serialVersionUID = -7217642644695032540L;
+
+ /** Mapper between spacecraft state and simple array. */
+ private StateMapper mapper;
/** Reference date. */
private AbsoluteDate initializedReference;
@@ -81,9 +86,6 @@ public class IntegratedEphemeris
/** Central body gravitational constant. */
private double initializedMu;
- /** Attitude law. */
- private AttitudeLaw initializedAttitudeLaw;
-
/** Start date of the integration (can be min or max). */
private AbsoluteDate startDate;
@@ -104,13 +106,12 @@ public class IntegratedEphemeris
}
/** {@inheritDoc} */
- public void initialize(final AbsoluteDate reference,
- final Frame frame, final double mu,
- final AttitudeLaw attitudeLaw) {
- this.initializedReference = reference;
- this.initializedFrame = frame;
- this.initializedMu = mu;
- this.initializedAttitudeLaw = attitudeLaw;
+ public void initialize(final StateMapper mapper, final List <AdditionalStateAndEquations> addStateAndEqu,
+ final AbsoluteDate reference, final Frame frame, final double mu) {
+ this.mapper = mapper;
+ this.initializedReference = reference;
+ this.initializedFrame = frame;
+ this.initializedMu = mu;
// dates will be set when last step is handled
startDate = null;
@@ -128,18 +129,12 @@ public class IntegratedEphemeris
date, minDate, maxDate);
}
model.setInterpolatedTime(date.durationFrom(startDate));
- final double[] state = model.getInterpolatedState();
-
- final EquinoctialOrbit eq =
- new EquinoctialOrbit(state[0], state[1], state[2],
- state[3], state[4], state[5], 2, initializedFrame, date, initializedMu);
- final double mass = state[6];
-
- return new SpacecraftState(eq, initializedAttitudeLaw.getAttitude(eq), mass);
- } catch (OrekitException oe) {
- throw new PropagationException(oe);
+ return mapper.mapArrayToState(model.getInterpolatedState(), date,
+ initializedMu, initializedFrame);
} catch (MathUserException mue) {
throw new PropagationException(mue, mue.getGeneralPattern(), mue.getArguments());
+ } catch (OrekitException oe) {
+ throw new PropagationException(oe);
}
}
@@ -164,13 +159,14 @@ public class IntegratedEphemeris
}
/** {@inheritDoc} */
- public void handleStep(final StepInterpolator interpolator,
- final boolean isLast) {
+ public void handleStep(final StepInterpolator interpolator, final boolean isLast) {
model.handleStep(interpolator, isLast);
if (isLast) {
- startDate = initializedReference.shiftedBy(model.getInitialTime());
- maxDate = initializedReference.shiftedBy(model.getFinalTime());
- if (maxDate.durationFrom(startDate) < 0) {
+ final double tI = model.getInitialTime();
+ final double tF = model.getFinalTime();
+ startDate = initializedReference.shiftedBy(tI);
+ maxDate = initializedReference.shiftedBy(tF);
+ if (tF < tI) {
minDate = maxDate;
maxDate = startDate;
} else {
diff --git a/src/main/java/org/orekit/propagation/sampling/AdaptedStepHandler.java b/src/main/java/org/orekit/propagation/sampling/AdaptedStepHandler.java
index 5b8776eb35..8e8060ba92 100644
--- a/src/main/java/org/orekit/propagation/sampling/AdaptedStepHandler.java
+++ b/src/main/java/org/orekit/propagation/sampling/AdaptedStepHandler.java
@@ -17,18 +17,20 @@
package org.orekit.propagation.sampling;
import java.io.Serializable;
+import java.util.List;
import org.apache.commons.math.exception.MathUserException;
import org.apache.commons.math.ode.sampling.StepHandler;
import org.apache.commons.math.ode.sampling.StepInterpolator;
-import org.orekit.attitudes.AttitudeLaw;
import org.orekit.errors.OrekitException;
+import org.orekit.errors.OrekitMessages;
import org.orekit.errors.PropagationException;
import org.orekit.frames.Frame;
-import org.orekit.orbits.EquinoctialOrbit;
-import org.orekit.orbits.Orbit;
import org.orekit.propagation.SpacecraftState;
+import org.orekit.propagation.numerical.AdditionalEquations;
+import org.orekit.propagation.numerical.AdditionalStateAndEquations;
import org.orekit.propagation.numerical.ModeHandler;
+import org.orekit.propagation.numerical.StateMapper;
import org.orekit.time.AbsoluteDate;
/** Adapt an {@link org.orekit.propagation.sampling.OrekitStepHandler}
@@ -42,6 +44,12 @@ public class AdaptedStepHandler
/** Serializable UID. */
private static final long serialVersionUID = -8067262257341902186L;
+ /** Mapper between spacecraft state and simple array. */
+ private StateMapper mapper;
+
+ /** Additional state and equations list. */
+ private List <AdditionalStateAndEquations> addStateAndEqu;
+
/** Reference date. */
private AbsoluteDate initializedReference;
@@ -51,9 +59,6 @@ public class AdaptedStepHandler
/** Central body attraction coefficient. */
private double initializedMu;
- /** Attitude law. */
- private AttitudeLaw initializedAttitudeLaw;
-
/** Underlying handler. */
private final OrekitStepHandler handler;
@@ -68,11 +73,12 @@ public class AdaptedStepHandler
}
/** {@inheritDoc} */
- public void initialize(final AbsoluteDate reference, final Frame frame,
- final double mu, final AttitudeLaw attitudeLaw) {
+ public void initialize(final StateMapper stateMapper, final List <AdditionalStateAndEquations> stateAndEqu,
+ final AbsoluteDate reference, final Frame frame, final double mu) {
+ this.mapper = stateMapper;
+ this.addStateAndEqu = stateAndEqu;
this.initializedReference = reference;
this.initializedFrame = frame;
- this.initializedAttitudeLaw = attitudeLaw;
this.initializedMu = mu;
}
@@ -144,16 +150,46 @@ public class AdaptedStepHandler
try {
final double[] y = rawInterpolator.getInterpolatedState();
final AbsoluteDate interpolatedDate = initializedReference.shiftedBy(rawInterpolator.getInterpolatedTime());
- final Orbit orbit =
- new EquinoctialOrbit(y[0], y[1], y[2], y[3], y[4], y[5],
- EquinoctialOrbit.TRUE_LATITUDE_ARGUMENT,
- initializedFrame, interpolatedDate, initializedMu);
- return new SpacecraftState(orbit, initializedAttitudeLaw.getAttitude(orbit), y[6]);
+ return mapper.mapArrayToState(y, interpolatedDate, initializedMu, initializedFrame);
} catch (MathUserException mue) {
throw new PropagationException(mue, mue.getGeneralPattern(), mue.getArguments());
}
}
+ /** Get the interpolated additional state corresponding to the additional equations.
+ * @param addEqu additional equation used as a reference for selection
+ * @return interpolated additional state at the current interpolation date
+ * @exception OrekitException if state cannot be interpolated or converted
+ * @see #getInterpolatedDate()
+ * @see #setInterpolatedDate(AbsoluteDate)
+ */
+ public double[] getInterpolatedAdditionalState(final AdditionalEquations addEqu)
+ throws OrekitException {
+ try {
+
+ // propagate the whole state vector
+ final double[] y = rawInterpolator.getInterpolatedState();
+
+ // get portion of additional state to update
+ int index = 7;
+ for (final AdditionalStateAndEquations stateAndEqu : addStateAndEqu) {
+ if (stateAndEqu.getAdditionalEquations() == addEqu) {
+ final double[] state = stateAndEqu.getAdditionalState();
+ System.arraycopy(y, index, state, 0, state.length);
+ return state;
+ }
+ // incrementing index
+ index += stateAndEqu.getAdditionalState().length;
+ }
+
+ throw new OrekitException(OrekitMessages.UNKNOWN_ADDITIONAL_EQUATION);
+
+ } catch (MathUserException mue) {
+ throw new PropagationException(mue, mue.getGeneralPattern(), mue.getArguments());
+ }
+
+ }
+
/** Check is integration direction is forward in date.
* @return true if integration is forward in date
*/
diff --git a/src/main/java/org/orekit/propagation/sampling/BasicStepInterpolator.java b/src/main/java/org/orekit/propagation/sampling/BasicStepInterpolator.java
index c0a3bc696e..28ab851e32 100644
--- a/src/main/java/org/orekit/propagation/sampling/BasicStepInterpolator.java
+++ b/src/main/java/org/orekit/propagation/sampling/BasicStepInterpolator.java
@@ -20,6 +20,7 @@ import org.orekit.errors.OrekitException;
import org.orekit.errors.PropagationException;
import org.orekit.propagation.BasicPropagator;
import org.orekit.propagation.SpacecraftState;
+import org.orekit.propagation.numerical.AdditionalEquations;
import org.orekit.time.AbsoluteDate;
/** Implementation of the {@link OrekitStepInterpolator} interface based
@@ -87,6 +88,13 @@ public class BasicStepInterpolator implements OrekitStepInterpolator {
interpolatedState = propagator.propagate(date);
}
+ /** {@inheritDoc} */
+ public double[] getInterpolatedAdditionalState(final AdditionalEquations addEqu)
+ throws OrekitException {
+ // This should never happen
+ throw OrekitException.createInternalError(null);
+ }
+
/** Shift one step forward.
* Copy the current date into the previous date, hence preparing the
* interpolator for future calls to {@link #storeDate storeDate}
@@ -106,4 +114,5 @@ public class BasicStepInterpolator implements OrekitStepInterpolator {
setInterpolatedDate(currentDate);
}
+
}
diff --git a/src/main/java/org/orekit/propagation/sampling/OrekitStepInterpolator.java b/src/main/java/org/orekit/propagation/sampling/OrekitStepInterpolator.java
index 50e9cdf62a..96bb206c7c 100644
--- a/src/main/java/org/orekit/propagation/sampling/OrekitStepInterpolator.java
+++ b/src/main/java/org/orekit/propagation/sampling/OrekitStepInterpolator.java
@@ -21,6 +21,7 @@ import java.io.Serializable;
import org.orekit.errors.OrekitException;
import org.orekit.errors.PropagationException;
import org.orekit.propagation.SpacecraftState;
+import org.orekit.propagation.numerical.AdditionalEquations;
import org.orekit.time.AbsoluteDate;
/** This interface is a space-dynamics aware step interpolator.
@@ -73,6 +74,15 @@ public interface OrekitStepInterpolator extends Serializable {
*/
SpacecraftState getInterpolatedState() throws OrekitException;
+ /** Get the interpolated additional state corresponding to the additional equations.
+ * @param addEqu additional equation used as a reference for selection
+ * @return interpolated additional state at the current interpolation date
+ * @exception OrekitException if state cannot be interpolated or converted
+ * @see #getInterpolatedDate()
+ * @see #setInterpolatedDate(AbsoluteDate)
+ */
+ double[] getInterpolatedAdditionalState(AdditionalEquations addEqu) throws OrekitException;
+
/** Check is integration direction is forward in date.
* @return true if integration is forward in date
*/
diff --git a/src/main/resources/META-INF/localization/OrekitMessages_de.properties b/src/main/resources/META-INF/localization/OrekitMessages_de.properties
index e159329962..dd340dd297 100644
--- a/src/main/resources/META-INF/localization/OrekitMessages_de.properties
+++ b/src/main/resources/META-INF/localization/OrekitMessages_de.properties
@@ -220,6 +220,30 @@ UNEXPECTED_TWO_ELEVATION_VALUES_FOR_ONE_AZIMUTH = <MISSING TRANSLATION!>
# unknown parameter {0}
UNKNOWN_PARAMETER = unbekannter Parameter {0}
+# unsupported parameter name {0}: supported names {1}, {2}
+UNSUPPORTED_PARAMETER_1_2 = <MISSING TRANSLATION!>
+
+# unknown additional equation
+UNKNOWN_ADDITIONAL_EQUATION = <MISSING TRANSLATION!>
+
+# partial derivatives can be propagated only in cartesian parameters type
+PARTIAL_DERIVATIVES_ONLY_IN_CARTESIAN = <MISSING TRANSLATION!>
+
+# state jacobian is a {0}x{1} matrix, it should be either a 6x6 or a 7x7 matrix
+STATE_JACOBIAN_NEITHER_6X6_NOR_7X7 = <MISSING TRANSLATION!>
+
+# state jacobian has {0} rows but parameters jacobian has {1} rows
+STATE_AND_PARAMETERS_JACOBIANS_ROWS_MISMATCH = <MISSING TRANSLATION!>
+
+# initial jacobian matrix has {0} columns, but {1} parameters have been selected
+INITIAL_MATRIX_AND_PARAMETERS_NUMBER_MISMATCH = <MISSING TRANSLATION!>
+
+# orbit should be either elliptic with a > 0 and e < 1 or hyperbolic with a < 0 and e > 1, a = {0}, e = {1}
+ORBIT_A_E_MISMATCH_WITH_CONIC_TYPE = <MISSING TRANSLATION!>
+
+# hyperbolic orbits cannot be handled as {0} instances
+HYPERBOLIC_ORBIT_NOT_HANDLED_AS = <MISSING TRANSLATION!>
+
# invalid preamble field in CCSDS date: {0}
CCSDS_DATE_INVALID_PREAMBLE_FIELD = <MISSING TRANSLATION!>
diff --git a/src/main/resources/META-INF/localization/OrekitMessages_en.properties b/src/main/resources/META-INF/localization/OrekitMessages_en.properties
index c561165411..8c0ea681cb 100644
--- a/src/main/resources/META-INF/localization/OrekitMessages_en.properties
+++ b/src/main/resources/META-INF/localization/OrekitMessages_en.properties
@@ -220,6 +220,30 @@ UNEXPECTED_TWO_ELEVATION_VALUES_FOR_ONE_AZIMUTH = unexpected two elevation value
# unknown parameter {0}
UNKNOWN_PARAMETER = unknown parameter {0}
+# unsupported parameter name {0}: supported names {1}, {2}
+UNSUPPORTED_PARAMETER_1_2 = unsupported parameter name {0}: supported names {1}, {2}
+
+# unknown additional equation
+UNKNOWN_ADDITIONAL_EQUATION = unknown additional equation
+
+# partial derivatives can be propagated only in cartesian parameters type
+PARTIAL_DERIVATIVES_ONLY_IN_CARTESIAN = partial derivatives can be propagated only in cartesian parameters type
+
+# state jacobian is a {0}x{1} matrix, it should be either a 6x6 or a 7x7 matrix
+STATE_JACOBIAN_NEITHER_6X6_NOR_7X7 = state jacobian is a {0}x{1} matrix, it should be either a 6x6 or a 7x7 matrix
+
+# state jacobian has {0} rows but parameters jacobian has {1} rows
+STATE_AND_PARAMETERS_JACOBIANS_ROWS_MISMATCH = state jacobian has {0} rows but parameters jacobian has {1} rows
+
+# initial jacobian matrix has {0} columns, but {1} parameters have been selected
+INITIAL_MATRIX_AND_PARAMETERS_NUMBER_MISMATCH = initial jacobian matrix has {0} columns, but {1} parameters have been selected
+
+# orbit should be either elliptic with a > 0 and e < 1 or hyperbolic with a < 0 and e > 1, a = {0}, e = {1}
+ORBIT_A_E_MISMATCH_WITH_CONIC_TYPE = orbit should be either elliptic with a > 0 and e < 1 or hyperbolic with a < 0 and e > 1, a = {0}, e = {1}
+
+# hyperbolic orbits cannot be handled as {0} instances
+HYPERBOLIC_ORBIT_NOT_HANDLED_AS = hyperbolic orbits cannot be handled as {0} instances
+
# invalid preamble field in CCSDS date: {0}
CCSDS_DATE_INVALID_PREAMBLE_FIELD = invalid preamble field in CCSDS date: {0}
diff --git a/src/main/resources/META-INF/localization/OrekitMessages_es.properties b/src/main/resources/META-INF/localization/OrekitMessages_es.properties
index 03c77a7acd..d00979f6c1 100644
--- a/src/main/resources/META-INF/localization/OrekitMessages_es.properties
+++ b/src/main/resources/META-INF/localization/OrekitMessages_es.properties
@@ -220,6 +220,30 @@ UNEXPECTED_TWO_ELEVATION_VALUES_FOR_ONE_AZIMUTH = <MISSING TRANSLATION!>
# unknown parameter {0}
UNKNOWN_PARAMETER = par\u00e1metro {0} desconocido
+# unsupported parameter name {0}: supported names {1}, {2}
+UNSUPPORTED_PARAMETER_1_2 = <MISSING TRANSLATION!>
+
+# unknown additional equation
+UNKNOWN_ADDITIONAL_EQUATION = <MISSING TRANSLATION!>
+
+# partial derivatives can be propagated only in cartesian parameters type
+PARTIAL_DERIVATIVES_ONLY_IN_CARTESIAN = <MISSING TRANSLATION!>
+
+# state jacobian is a {0}x{1} matrix, it should be either a 6x6 or a 7x7 matrix
+STATE_JACOBIAN_NEITHER_6X6_NOR_7X7 = <MISSING TRANSLATION!>
+
+# state jacobian has {0} rows but parameters jacobian has {1} rows
+STATE_AND_PARAMETERS_JACOBIANS_ROWS_MISMATCH = <MISSING TRANSLATION!>
+
+# initial jacobian matrix has {0} columns, but {1} parameters have been selected
+INITIAL_MATRIX_AND_PARAMETERS_NUMBER_MISMATCH = <MISSING TRANSLATION!>
+
+# orbit should be either elliptic with a > 0 and e < 1 or hyperbolic with a < 0 and e > 1, a = {0}, e = {1}
+ORBIT_A_E_MISMATCH_WITH_CONIC_TYPE = <MISSING TRANSLATION!>
+
+# hyperbolic orbits cannot be handled as {0} instances
+HYPERBOLIC_ORBIT_NOT_HANDLED_AS = <MISSING TRANSLATION!>
+
# invalid preamble field in CCSDS date: {0}
CCSDS_DATE_INVALID_PREAMBLE_FIELD = <MISSING TRANSLATION!>
diff --git a/src/main/resources/META-INF/localization/OrekitMessages_fr.properties b/src/main/resources/META-INF/localization/OrekitMessages_fr.properties
index 704d41597d..0b8e7717e7 100644
--- a/src/main/resources/META-INF/localization/OrekitMessages_fr.properties
+++ b/src/main/resources/META-INF/localization/OrekitMessages_fr.properties
@@ -220,6 +220,30 @@ UNEXPECTED_TWO_ELEVATION_VALUES_FOR_ONE_AZIMUTH = donn\u00e9es inattendues, deux
# unknown parameter {0}
UNKNOWN_PARAMETER = param\u00e8tre {0} inconnu
+# unsupported parameter name {0}: supported names {1}, {2}
+UNSUPPORTED_PARAMETER_1_2 = param\u00e8tre {0} inconnu : param\u00e8tres connus {1}, {2}
+
+# unknown additional equation
+UNKNOWN_ADDITIONAL_EQUATION = \u00e9quation additionelle inconnue
+
+# partial derivatives can be propagated only in cartesian parameters type
+PARTIAL_DERIVATIVES_ONLY_IN_CARTESIAN = les d\u00e9riv\u00e9es partielles ne peuvent \u00eatre propag\u00e9es qu''en param\u00e8tres cart\u00e9siens
+
+# state jacobian is a {0}x{1} matrix, it should be either a 6x6 or a 7x7 matrix
+STATE_JACOBIAN_NEITHER_6X6_NOR_7X7 = la jacobienne de l''\u00e9tat est une matrice {0}x{1}, alors qu''elle devrait \u00eatre soit une matrice 6x6 soit une matrice 7x7
+
+# state jacobian has {0} rows but parameters jacobian has {1} rows
+STATE_AND_PARAMETERS_JACOBIANS_ROWS_MISMATCH = la jacobienne de l''\u00e9tat a {0} lignes alors que la jacobienne des param\u00e8tres en a {1}
+
+# initial jacobian matrix has {0} columns, but {1} parameters have been selected
+INITIAL_MATRIX_AND_PARAMETERS_NUMBER_MISMATCH = la matrice initiale a {0} colonnes alors que {1} param\u00e8tres ont \u00e9t\u00e9 s\u00e9lectionn\u00e9s
+
+# orbit should be either elliptic with a > 0 and e < 1 or hyperbolic with a < 0 and e > 1, a = {0}, e = {1}
+ORBIT_A_E_MISMATCH_WITH_CONIC_TYPE = l''orbite devrait \u00eatre soit elliptique avec a > 0 et e < 1 ou hyperbolique avec a < 0 et e > 1, a = {0}, e = {1}
+
+# hyperbolic orbits cannot be handled as {0} instances
+HYPERBOLIC_ORBIT_NOT_HANDLED_AS = les orbites hyperboliques ne peuvent pas \u00eatre des instances de {0}
+
# invalid preamble field in CCSDS date: {0}
CCSDS_DATE_INVALID_PREAMBLE_FIELD = pr\u00e9ambule invalide dans une date CCSDS : {0}
diff --git a/src/main/resources/META-INF/localization/OrekitMessages_gl.properties b/src/main/resources/META-INF/localization/OrekitMessages_gl.properties
index 6fe471ccf3..3c706a2f75 100644
--- a/src/main/resources/META-INF/localization/OrekitMessages_gl.properties
+++ b/src/main/resources/META-INF/localization/OrekitMessages_gl.properties
@@ -220,6 +220,30 @@ UNEXPECTED_TWO_ELEVATION_VALUES_FOR_ONE_AZIMUTH = <MISSING TRANSLATION!>
# unknown parameter {0}
UNKNOWN_PARAMETER = par\u00e1metro {0} desco\u00f1ecido
+# unsupported parameter name {0}: supported names {1}, {2}
+UNSUPPORTED_PARAMETER_1_2 = <MISSING TRANSLATION!>
+
+# unknown additional equation
+UNKNOWN_ADDITIONAL_EQUATION = <MISSING TRANSLATION!>
+
+# partial derivatives can be propagated only in cartesian parameters type
+PARTIAL_DERIVATIVES_ONLY_IN_CARTESIAN = <MISSING TRANSLATION!>
+
+# state jacobian is a {0}x{1} matrix, it should be either a 6x6 or a 7x7 matrix
+STATE_JACOBIAN_NEITHER_6X6_NOR_7X7 = <MISSING TRANSLATION!>
+
+# state jacobian has {0} rows but parameters jacobian has {1} rows
+STATE_AND_PARAMETERS_JACOBIANS_ROWS_MISMATCH = <MISSING TRANSLATION!>
+
+# initial jacobian matrix has {0} columns, but {1} parameters have been selected
+INITIAL_MATRIX_AND_PARAMETERS_NUMBER_MISMATCH = <MISSING TRANSLATION!>
+
+# orbit should be either elliptic with a > 0 and e < 1 or hyperbolic with a < 0 and e > 1, a = {0}, e = {1}
+ORBIT_A_E_MISMATCH_WITH_CONIC_TYPE = <MISSING TRANSLATION!>
+
+# hyperbolic orbits cannot be handled as {0} instances
+HYPERBOLIC_ORBIT_NOT_HANDLED_AS = <MISSING TRANSLATION!>
+
# invalid preamble field in CCSDS date: {0}
CCSDS_DATE_INVALID_PREAMBLE_FIELD = <MISSING TRANSLATION!>
diff --git a/src/main/resources/META-INF/localization/OrekitMessages_it.properties b/src/main/resources/META-INF/localization/OrekitMessages_it.properties
index 0988870357..55bf929bf6 100644
--- a/src/main/resources/META-INF/localization/OrekitMessages_it.properties
+++ b/src/main/resources/META-INF/localization/OrekitMessages_it.properties
@@ -220,6 +220,30 @@ UNEXPECTED_TWO_ELEVATION_VALUES_FOR_ONE_AZIMUTH = <MISSING TRANSLATION!>
# unknown parameter {0}
UNKNOWN_PARAMETER = parametro {0} sconosciuto
+# unsupported parameter name {0}: supported names {1}, {2}
+UNSUPPORTED_PARAMETER_1_2 = <MISSING TRANSLATION!>
+
+# unknown additional equation
+UNKNOWN_ADDITIONAL_EQUATION = <MISSING TRANSLATION!>
+
+# partial derivatives can be propagated only in cartesian parameters type
+PARTIAL_DERIVATIVES_ONLY_IN_CARTESIAN = <MISSING TRANSLATION!>
+
+# state jacobian is a {0}x{1} matrix, it should be either a 6x6 or a 7x7 matrix
+STATE_JACOBIAN_NEITHER_6X6_NOR_7X7 = <MISSING TRANSLATION!>
+
+# state jacobian has {0} rows but parameters jacobian has {1} rows
+STATE_AND_PARAMETERS_JACOBIANS_ROWS_MISMATCH = <MISSING TRANSLATION!>
+
+# initial jacobian matrix has {0} columns, but {1} parameters have been selected
+INITIAL_MATRIX_AND_PARAMETERS_NUMBER_MISMATCH = <MISSING TRANSLATION!>
+
+# orbit should be either elliptic with a > 0 and e < 1 or hyperbolic with a < 0 and e > 1, a = {0}, e = {1}
+ORBIT_A_E_MISMATCH_WITH_CONIC_TYPE = <MISSING TRANSLATION!>
+
+# hyperbolic orbits cannot be handled as {0} instances
+HYPERBOLIC_ORBIT_NOT_HANDLED_AS = <MISSING TRANSLATION!>
+
# invalid preamble field in CCSDS date: {0}
CCSDS_DATE_INVALID_PREAMBLE_FIELD = <MISSING TRANSLATION!>
diff --git a/src/main/resources/META-INF/localization/OrekitMessages_no.properties b/src/main/resources/META-INF/localization/OrekitMessages_no.properties
index c44d3679ef..1e045e0524 100644
--- a/src/main/resources/META-INF/localization/OrekitMessages_no.properties
+++ b/src/main/resources/META-INF/localization/OrekitMessages_no.properties
@@ -220,6 +220,30 @@ UNEXPECTED_TWO_ELEVATION_VALUES_FOR_ONE_AZIMUTH = <MISSING TRANSLATION!>
# unknown parameter {0}
UNKNOWN_PARAMETER = ukjent parametere {0}
+# unsupported parameter name {0}: supported names {1}, {2}
+UNSUPPORTED_PARAMETER_1_2 = <MISSING TRANSLATION!>
+
+# unknown additional equation
+UNKNOWN_ADDITIONAL_EQUATION = <MISSING TRANSLATION!>
+
+# partial derivatives can be propagated only in cartesian parameters type
+PARTIAL_DERIVATIVES_ONLY_IN_CARTESIAN = <MISSING TRANSLATION!>
+
+# state jacobian is a {0}x{1} matrix, it should be either a 6x6 or a 7x7 matrix
+STATE_JACOBIAN_NEITHER_6X6_NOR_7X7 = <MISSING TRANSLATION!>
+
+# state jacobian has {0} rows but parameters jacobian has {1} rows
+STATE_AND_PARAMETERS_JACOBIANS_ROWS_MISMATCH = <MISSING TRANSLATION!>
+
+# initial jacobian matrix has {0} columns, but {1} parameters have been selected
+INITIAL_MATRIX_AND_PARAMETERS_NUMBER_MISMATCH = <MISSING TRANSLATION!>
+
+# orbit should be either elliptic with a > 0 and e < 1 or hyperbolic with a < 0 and e > 1, a = {0}, e = {1}
+ORBIT_A_E_MISMATCH_WITH_CONIC_TYPE = <MISSING TRANSLATION!>
+
+# hyperbolic orbits cannot be handled as {0} instances
+HYPERBOLIC_ORBIT_NOT_HANDLED_AS = <MISSING TRANSLATION!>
+
# invalid preamble field in CCSDS date: {0}
CCSDS_DATE_INVALID_PREAMBLE_FIELD = <MISSING TRANSLATION!>
diff --git a/src/site/xdoc/changes.xml b/src/site/xdoc/changes.xml
index 2765c28153..fca260b867 100644
--- a/src/site/xdoc/changes.xml
+++ b/src/site/xdoc/changes.xml
@@ -153,6 +153,33 @@
fixed an error in FramesFactory when getting ITRF2005 and TIRF2000 frames:
ignoreTidalEffects was handled wrong.
</action>
+ <action dev="luc" type="update" >
+ removed serialization of some cached data in frames
+ </action>
+ <action dev="luc" type="fix" >
+ fixed deserialization problems of frame singletons, they were not unique any more
+ </action>
+ <action dev="véronique" type="add" >
+ numerical propagation can now be done either using equinoctial parameters or
+ cartesian parameters, thus allowing propagation of any kind of trajectories,
+ including hyperbolic orbits used for interplanetary missions or atmospheric
+ re-entry trajectories
+ </action>
+ <action dev="véronique" type="update" >
+ completely revamped the partial derivatives matrices computation using the additional
+ equations mechanism
+ </action>
+ <action dev="véronique" type="add" >
+ added a mechanism to integrate user-supplied additional equations alongside with
+ orbital parameters during numerical propagation
+ </action>
+ <action dev="luc" type="update">
+ use A. W. Odell and R. H. Gooding (1986) fast and robust solver for Kepler equation
+ </action>
+ <action dev="luc" type="add">
+ keplerian and cartesian orbits now support hyperbolic orbits (i.e. eccentricity greater
+ than 1, and in this case negative semi major axis by convention)
+ </action>
<action dev="luc" type="fix">
fixed an error in LofOffset attitude mode: the computed attitude was reversed
with respect to the specification
diff --git a/src/test/java/org/orekit/attitudes/LofOffsetPointingTest.java b/src/test/java/org/orekit/attitudes/LofOffsetPointingTest.java
index 87bfd4ed05..67c2664e82 100644
--- a/src/test/java/org/orekit/attitudes/LofOffsetPointingTest.java
+++ b/src/test/java/org/orekit/attitudes/LofOffsetPointingTest.java
@@ -140,7 +140,7 @@ public class LofOffsetPointingTest {
sPlus.getAttitude().getRotation(),
2 * h);
Assert.assertTrue(spin0.getNorm() > 1.0e-3);
- Assert.assertEquals(0.0, spin0.subtract(reference).getNorm(), 4.0e-11);
+ Assert.assertEquals(0.0, spin0.subtract(reference).getNorm(), 1.0e-10);
}
diff --git a/src/test/java/org/orekit/attitudes/LofOffsetTest.java b/src/test/java/org/orekit/attitudes/LofOffsetTest.java
index 76a5c72634..4e014ac7bd 100644
--- a/src/test/java/org/orekit/attitudes/LofOffsetTest.java
+++ b/src/test/java/org/orekit/attitudes/LofOffsetTest.java
@@ -195,7 +195,7 @@ public class LofOffsetTest {
Vector3D reference = Attitude.estimateSpin(sMinus.getAttitude().getRotation(),
sPlus.getAttitude().getRotation(),
2 * h);
- Assert.assertEquals(0.0, spin0.subtract(reference).getNorm(), 4.0e-11);
+ Assert.assertEquals(0.0, spin0.subtract(reference).getNorm(), 1.0e-10);
}
diff --git a/src/test/java/org/orekit/errors/OrekitMessagesTest.java b/src/test/java/org/orekit/errors/OrekitMessagesTest.java
index 799408fd41..97ba642664 100644
--- a/src/test/java/org/orekit/errors/OrekitMessagesTest.java
+++ b/src/test/java/org/orekit/errors/OrekitMessagesTest.java
@@ -30,7 +30,7 @@ public class OrekitMessagesTest {
@Test
public void testMessageNumber() {
- Assert.assertEquals(89, OrekitMessages.values().length);
+ Assert.assertEquals(97, OrekitMessages.values().length);
}
@Test
diff --git a/src/test/java/org/orekit/frames/FrameTest.java b/src/test/java/org/orekit/frames/FrameTest.java
index 20ee53cf59..74f6a10c84 100644
--- a/src/test/java/org/orekit/frames/FrameTest.java
+++ b/src/test/java/org/orekit/frames/FrameTest.java
@@ -145,8 +145,8 @@ public class FrameTest {
Frame rotatingPadFrame = new TopocentricFrame(new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
itrf),
- new GeodeticPoint(Math.toRadians(5.0),
- Math.toRadians(-100.0),
+ new GeodeticPoint(FastMath.toRadians(5.0),
+ FastMath.toRadians(-100.0),
0.0),
"launch pad");
diff --git a/src/test/java/org/orekit/frames/TODFrameAlternateConfigurationTest.java b/src/test/java/org/orekit/frames/TODFrameAlternateConfigurationTest.java
index 0fe8e7451a..193fcab5b3 100644
--- a/src/test/java/org/orekit/frames/TODFrameAlternateConfigurationTest.java
+++ b/src/test/java/org/orekit/frames/TODFrameAlternateConfigurationTest.java
@@ -142,8 +142,8 @@ public class TODFrameAlternateConfigurationTest {
throws OrekitException {
super(ignoreNutationCorrection, factoryKey);
}
- protected void setInterpolatedNutationElements(final double t) {
- computeNutationElements(t);
+ public double[] getInterpolatedNutationElements(final double t) {
+ return computeNutationElements(t);
}
}
diff --git a/src/test/java/org/orekit/frames/TODFrameTest.java b/src/test/java/org/orekit/frames/TODFrameTest.java
index 740a51f095..14391d8739 100644
--- a/src/test/java/org/orekit/frames/TODFrameTest.java
+++ b/src/test/java/org/orekit/frames/TODFrameTest.java
@@ -46,7 +46,7 @@ public class TODFrameTest {
double previousEQE = currentEQE;
currentEQE = tod.getEquationOfEquinoxes(d);
if (!Double.isNaN(previousEQE)) {
- double deltaMicroAS = 3.6e9 * Math.toDegrees(currentEQE - previousEQE);
+ double deltaMicroAS = 3.6e9 * FastMath.toDegrees(currentEQE - previousEQE);
if ((dt - h) * dt > 0) {
// away from switch date, equation of equinox should decrease at
// about 1.06 micro arcsecond per second
diff --git a/src/test/java/org/orekit/orbits/CartesianParametersTest.java b/src/test/java/org/orekit/orbits/CartesianParametersTest.java
index eb37fb942b..d7af72d09b 100644
--- a/src/test/java/org/orekit/orbits/CartesianParametersTest.java
+++ b/src/test/java/org/orekit/orbits/CartesianParametersTest.java
@@ -16,6 +16,12 @@
*/
package org.orekit.orbits;
+import java.io.ByteArrayInputStream;
+import java.io.ByteArrayOutputStream;
+import java.io.IOException;
+import java.io.ObjectInputStream;
+import java.io.ObjectOutputStream;
+
import org.apache.commons.math.geometry.Vector3D;
import org.apache.commons.math.util.FastMath;
import org.apache.commons.math.util.MathUtils;
@@ -167,6 +173,76 @@ public class CartesianParametersTest {
}
}
+ @Test
+ public void testSerialization()
+ throws IOException, ClassNotFoundException, NoSuchFieldException, IllegalAccessException {
+ Vector3D position = new Vector3D(-29536113.0, 30329259.0, -100125.0);
+ Vector3D velocity = new Vector3D(-2194.0, -2141.0, -8.0);
+ PVCoordinates pvCoordinates = new PVCoordinates( position, velocity);
+ CartesianOrbit orbit = new CartesianOrbit(pvCoordinates, FramesFactory.getEME2000(), date, mu);
+ Assert.assertEquals(42255170.003, orbit.getA(), 1.0e-3);
+
+ ByteArrayOutputStream bos = new ByteArrayOutputStream();
+ ObjectOutputStream oos = new ObjectOutputStream(bos);
+ oos.writeObject(orbit);
+
+ Assert.assertTrue(bos.size () > 1400);
+ Assert.assertTrue(bos.size () < 1500);
+
+ ByteArrayInputStream bis = new ByteArrayInputStream(bos.toByteArray());
+ ObjectInputStream ois = new ObjectInputStream(bis);
+ CartesianOrbit deserialized = (CartesianOrbit) ois.readObject();
+ Vector3D dp = orbit.getPVCoordinates().getPosition().subtract(deserialized.getPVCoordinates().getPosition());
+ Vector3D dv = orbit.getPVCoordinates().getVelocity().subtract(deserialized.getPVCoordinates().getVelocity());
+ Assert.assertEquals(0.0, dp.getNorm(), 1.0e-10);
+ Assert.assertEquals(0.0, dv.getNorm(), 1.0e-10);
+
+ }
+
+ @Test
+ public void testShiftElliptic() {
+ Vector3D position = new Vector3D(-29536113.0, 30329259.0, -100125.0);
+ Vector3D velocity = new Vector3D(-2194.0, -2141.0, -8.0);
+ PVCoordinates pvCoordinates = new PVCoordinates( position, velocity);
+ CartesianOrbit orbit = new CartesianOrbit(pvCoordinates, FramesFactory.getEME2000(), date, mu);
+ testShift(orbit, new KeplerianOrbit(orbit), 1.0e-13);
+ }
+
+ @Test
+ public void testShiftCircular() {
+ Vector3D position = new Vector3D(-29536113.0, 30329259.0, -100125.0);
+ Vector3D velocity = new Vector3D(FastMath.sqrt(mu / position.getNorm()), position.orthogonal());
+ PVCoordinates pvCoordinates = new PVCoordinates( position, velocity);
+ CartesianOrbit orbit = new CartesianOrbit(pvCoordinates, FramesFactory.getEME2000(), date, mu);
+ testShift(orbit, new CircularOrbit(orbit), 1.0e-15);
+ }
+
+ @Test
+ public void testShiftHyperbolic() {
+ Vector3D position = new Vector3D(-29536113.0, 30329259.0, -100125.0);
+ Vector3D velocity = new Vector3D(3 * FastMath.sqrt(mu / position.getNorm()), position.orthogonal());
+ PVCoordinates pvCoordinates = new PVCoordinates( position, velocity);
+ CartesianOrbit orbit = new CartesianOrbit(pvCoordinates, FramesFactory.getEME2000(), date, mu);
+ testShift(orbit, new KeplerianOrbit(orbit), 1.0e-15);
+ }
+
+ private void testShift(CartesianOrbit tested, Orbit reference, double threshold) {
+ for (double dt = - 1000; dt < 1000; dt += 10.0) {
+
+ PVCoordinates pvTested = tested.shiftedBy(dt).getPVCoordinates();
+ Vector3D pTested = pvTested.getPosition();
+ Vector3D vTested = pvTested.getVelocity();
+
+ PVCoordinates pvReference = reference.shiftedBy(dt).getPVCoordinates();
+ Vector3D pReference = pvReference.getPosition();
+ Vector3D vReference = pvReference.getVelocity();
+
+ Assert.assertEquals(0, pTested.subtract(pReference).getNorm(), threshold * pReference.getNorm());
+ Assert.assertEquals(0, vTested.subtract(vReference).getNorm(), threshold * vReference.getNorm());
+
+ }
+ }
+
@Test(expected=IllegalArgumentException.class)
public void testNonInertialFrame() throws IllegalArgumentException {
diff --git a/src/test/java/org/orekit/orbits/KeplerianParametersTest.java b/src/test/java/org/orekit/orbits/KeplerianParametersTest.java
index 15d0484293..7bab02c8c3 100644
--- a/src/test/java/org/orekit/orbits/KeplerianParametersTest.java
+++ b/src/test/java/org/orekit/orbits/KeplerianParametersTest.java
@@ -79,6 +79,24 @@ public class KeplerianParametersTest {
Assert.assertEquals(MathUtils.normalizeAngle(paramCir.getLE(), kepCir.getLE()), kepCir.getLE(), Utils.epsilonAngle * FastMath.abs(kepCir.getLE()));
Assert.assertEquals(MathUtils.normalizeAngle(paramCir.getLv(), kepCir.getLv()), kepCir.getLv(), Utils.epsilonAngle * FastMath.abs(kepCir.getLv()));
+ // hyperbolic orbit
+ KeplerianOrbit kepHyp =
+ new KeplerianOrbit(-24464560.0, 1.7311, 0.122138, 3.10686, 1.00681,
+ 0.048363, KeplerianOrbit.MEAN_ANOMALY,
+ FramesFactory.getEME2000(), date, mu);
+
+ Vector3D posHyp = kepHyp.getPVCoordinates().getPosition();
+ Vector3D vitHyp = kepHyp.getPVCoordinates().getVelocity();
+
+ KeplerianOrbit paramHyp = new KeplerianOrbit(new PVCoordinates(posHyp,vitHyp),
+ FramesFactory.getEME2000(), date, mu);
+ Assert.assertEquals(paramHyp.getA(), kepHyp.getA(), Utils.epsilonTest * FastMath.abs(kepHyp.getA()));
+ Assert.assertEquals(paramHyp.getE(), kepHyp.getE(), Utils.epsilonE * FastMath.abs(kepHyp.getE()));
+ Assert.assertEquals(MathUtils.normalizeAngle(paramHyp.getI(), kepHyp.getI()), kepHyp.getI(), Utils.epsilonAngle * FastMath.abs(kepHyp.getI()));
+ Assert.assertEquals(MathUtils.normalizeAngle(paramHyp.getPerigeeArgument(), kepHyp.getPerigeeArgument()), kepHyp.getPerigeeArgument(), Utils.epsilonAngle * FastMath.abs(kepHyp.getPerigeeArgument()));
+ Assert.assertEquals(MathUtils.normalizeAngle(paramHyp.getRightAscensionOfAscendingNode(), kepHyp.getRightAscensionOfAscendingNode()), kepHyp.getRightAscensionOfAscendingNode(), Utils.epsilonAngle * FastMath.abs(kepHyp.getRightAscensionOfAscendingNode()));
+ Assert.assertEquals(MathUtils.normalizeAngle(paramHyp.getMeanAnomaly(), kepHyp.getMeanAnomaly()), kepHyp.getMeanAnomaly(), Utils.epsilonAngle * FastMath.abs(kepHyp.getMeanAnomaly()));
+
}
public void testKeplerianToCartesian() {
@@ -377,7 +395,7 @@ public class KeplerianParametersTest {
@Test
public void testSymmetry() {
- // elliptic and non equatorail orbit
+ // elliptic and non equatorial orbit
Vector3D position = new Vector3D(-4947831., -3765382., -3708221.);
Vector3D velocity = new Vector3D(-2079., 5291., -7842.);
double mu = 3.9860047e14;
@@ -426,6 +444,53 @@ public class KeplerianParametersTest {
Assert.assertEquals(0.00094277682051291315229, orbit.getKeplerianMeanMotion(), 1.0e-16);
}
+ @Test
+ public void testHyperbola() {
+ KeplerianOrbit orbit = new KeplerianOrbit(-10000000.0, 2.5, 0.3, 0, 0, 0.0,
+ KeplerianOrbit.TRUE_ANOMALY,
+ FramesFactory.getEME2000(), AbsoluteDate.J2000_EPOCH,
+ mu);
+ Vector3D perigeeP = orbit.getPVCoordinates().getPosition();
+ Vector3D u = perigeeP.normalize();
+ Vector3D focus1 = Vector3D.ZERO;
+ Vector3D focus2 = new Vector3D(-2 * orbit.getA() * orbit.getE(), u);
+ for (double dt = -5000; dt < 5000; dt += 60) {
+ PVCoordinates pv = orbit.shiftedBy(dt).getPVCoordinates();
+ double d1 = Vector3D.distance(pv.getPosition(), focus1);
+ double d2 = Vector3D.distance(pv.getPosition(), focus2);
+ Assert.assertEquals(-2 * orbit.getA(), FastMath.abs(d1 - d2), 1.0e-6);
+ KeplerianOrbit rebuilt =
+ new KeplerianOrbit(pv, orbit.getFrame(), orbit.getDate().shiftedBy(dt), mu);
+ Assert.assertEquals(-10000000.0, rebuilt.getA(), 1.0e-6);
+ Assert.assertEquals(2.5, rebuilt.getE(), 1.0e-13);
+ }
+ }
+
+ @Test
+ public void testKeplerEquation() {
+
+ for (double M = -6 * FastMath.PI; M < 6 * FastMath.PI; M += 0.01) {
+ KeplerianOrbit pElliptic =
+ new KeplerianOrbit(24464560.0, 0.7311, 2.1, 3.10686, 1.00681,
+ M, KeplerianOrbit.MEAN_ANOMALY,
+ FramesFactory.getEME2000(), date, mu);
+ double E = pElliptic.getEccentricAnomaly();
+ double e = pElliptic.getE();
+ Assert.assertEquals(M, E - e * FastMath.sin(E), 2.0e-14);
+ }
+
+ for (double M = -6 * FastMath.PI; M < 6 * FastMath.PI; M += 0.01) {
+ KeplerianOrbit pAlmostParabolic =
+ new KeplerianOrbit(24464560.0, 0.9999, 2.1, 3.10686, 1.00681,
+ M, KeplerianOrbit.MEAN_ANOMALY,
+ FramesFactory.getEME2000(), date, mu);
+ double E = pAlmostParabolic.getEccentricAnomaly();
+ double e = pAlmostParabolic.getE();
+ Assert.assertEquals(M, E - e * FastMath.sin(E), 3.0e-13);
+ }
+
+ }
+
@Before
public void setUp() {
diff --git a/src/test/java/org/orekit/propagation/SpacecraftStateTest.java b/src/test/java/org/orekit/propagation/SpacecraftStateTest.java
index 7f7804cf4e..ccaa10df78 100644
--- a/src/test/java/org/orekit/propagation/SpacecraftStateTest.java
+++ b/src/test/java/org/orekit/propagation/SpacecraftStateTest.java
@@ -24,7 +24,6 @@ import junit.framework.Assert;
import org.apache.commons.math.analysis.polynomials.PolynomialFunction;
import org.apache.commons.math.geometry.Rotation;
import org.apache.commons.math.geometry.Vector3D;
-import org.apache.commons.math.optimization.OptimizationException;
import org.apache.commons.math.util.FastMath;
import org.junit.After;
import org.junit.Before;
@@ -50,7 +49,7 @@ public class SpacecraftStateTest {
@Test
public void testInterpolationError()
- throws ParseException, OrekitException, OptimizationException {
+ throws ParseException, OrekitException {
// polynomial models for interpolation error in position, velocity and attitude
@@ -110,7 +109,7 @@ public class SpacecraftStateTest {
@Test
public void testTransform()
- throws ParseException, OrekitException, OptimizationException {
+ throws ParseException, OrekitException {
double maxDP = 0;
double maxDV = 0;
diff --git a/src/test/java/org/orekit/propagation/analytical/EcksteinHechlerPropagatorTest.java b/src/test/java/org/orekit/propagation/analytical/EcksteinHechlerPropagatorTest.java
index 71e180177c..05a3c4f181 100644
--- a/src/test/java/org/orekit/propagation/analytical/EcksteinHechlerPropagatorTest.java
+++ b/src/test/java/org/orekit/propagation/analytical/EcksteinHechlerPropagatorTest.java
@@ -488,7 +488,7 @@ public class EcksteinHechlerPropagatorTest {
@Test(expected = PropagationException.class)
public void hyperbolic() throws PropagationException {
KeplerianOrbit hyperbolic =
- new KeplerianOrbit(1.0e10, 2, 0, 0, 0, 0, KeplerianOrbit.TRUE_ANOMALY,
+ new KeplerianOrbit(-1.0e10, 2, 0, 0, 0, 0, KeplerianOrbit.TRUE_ANOMALY,
FramesFactory.getEME2000(), AbsoluteDate.J2000_EPOCH, 3.986004415e14);
EcksteinHechlerPropagator propagator =
new EcksteinHechlerPropagator(hyperbolic, ae, mu, c20, c30, c40, c50, c60);
diff --git a/src/test/java/org/orekit/propagation/events/DetectorTest.java b/src/test/java/org/orekit/propagation/events/DetectorTest.java
index 6aa91050a1..edeba3e102 100644
--- a/src/test/java/org/orekit/propagation/events/DetectorTest.java
+++ b/src/test/java/org/orekit/propagation/events/DetectorTest.java
@@ -33,6 +33,7 @@ import org.orekit.propagation.sampling.OrekitFixedStepHandler;
import org.orekit.time.AbsoluteDate;
import org.orekit.time.TimeScale;
import org.orekit.time.TimeScalesFactory;
+import org.orekit.utils.Constants;
import org.orekit.utils.PVCoordinates;
public class DetectorTest {
@@ -98,6 +99,7 @@ public class DetectorTest {
@Before
public void setUp() {
Utils.setDataRoot("regular-data");
+ mu = Constants.EIGEN5C_EARTH_MU;
}
}
diff --git a/src/test/java/org/orekit/propagation/numerical/NumericalPropagatorTest.java b/src/test/java/org/orekit/propagation/numerical/NumericalPropagatorTest.java
index 6d3f540417..3b9bf564a1 100644
--- a/src/test/java/org/orekit/propagation/numerical/NumericalPropagatorTest.java
+++ b/src/test/java/org/orekit/propagation/numerical/NumericalPropagatorTest.java
@@ -16,7 +16,10 @@
*/
package org.orekit.propagation.numerical;
-import org.apache.commons.math.exception.util.DummyLocalizable;
+import java.io.IOException;
+import java.text.ParseException;
+
+import org.apache.commons.math.exception.util.LocalizedFormats;
import org.apache.commons.math.geometry.Vector3D;
import org.apache.commons.math.ode.nonstiff.AdaptiveStepsizeIntegrator;
import org.apache.commons.math.ode.nonstiff.ClassicalRungeKuttaIntegrator;
@@ -26,16 +29,23 @@ import org.junit.After;
import org.junit.Assert;
import org.junit.Before;
import org.junit.Test;
+import org.orekit.Utils;
import org.orekit.errors.OrekitException;
import org.orekit.errors.PropagationException;
+import org.orekit.frames.Frame;
import org.orekit.frames.FramesFactory;
+import org.orekit.orbits.CartesianOrbit;
import org.orekit.orbits.EquinoctialOrbit;
import org.orekit.orbits.Orbit;
import org.orekit.propagation.SpacecraftState;
+import org.orekit.propagation.events.ApsideDetector;
import org.orekit.propagation.events.DateDetector;
+import org.orekit.propagation.numerical.NumericalPropagator.PropagationParametersType;
import org.orekit.propagation.sampling.OrekitStepHandler;
import org.orekit.propagation.sampling.OrekitStepInterpolator;
import org.orekit.time.AbsoluteDate;
+import org.orekit.time.TimeScale;
+import org.orekit.time.TimeScalesFactory;
import org.orekit.utils.PVCoordinates;
@@ -97,6 +107,26 @@ public class NumericalPropagatorTest {
}
+ @Test
+ public void testCartesian() throws OrekitException {
+
+ // Propagation of the initial at t + dt
+ final double dt = 3200;
+ propagator.setPropagationParametersType(NumericalPropagator.PropagationParametersType.CARTESIAN);
+ final PVCoordinates finalState =
+ propagator.propagate(initDate.shiftedBy(dt)).getPVCoordinates();
+ final Vector3D pFin = finalState.getPosition();
+ final Vector3D vFin = finalState.getVelocity();
+
+ // Check results
+ final PVCoordinates reference = initialState.shiftedBy(dt).getPVCoordinates();
+ final Vector3D pRef = reference.getPosition();
+ final Vector3D vRef = reference.getVelocity();
+ Assert.assertEquals(0, pRef.subtract(pFin).getNorm(), 0.4);
+ Assert.assertEquals(0, vRef.subtract(vFin).getNorm(), 0.0002);
+
+ }
+
@Test(expected=OrekitException.class)
public void testException() throws OrekitException {
propagator.setMasterMode(new OrekitStepHandler() {
@@ -109,7 +139,7 @@ public class NumericalPropagatorTest {
Assert.assertTrue(interpolator.getInterpolatedDate().compareTo(previousCall) < 0);
}
if (--countDown == 0) {
- throw new PropagationException((Throwable) null, new DummyLocalizable("dummy error"));
+ throw new PropagationException(LocalizedFormats.SIMPLE_MESSAGE, "dummy error");
}
}
public boolean requiresDenseOutput() {
@@ -211,8 +241,70 @@ public class NumericalPropagatorTest {
this.gotHere = gotHere;
}
+ @Test
+ public void testEventDetectionBug() throws OrekitException, IOException, ParseException {
+
+ TimeScale utc = TimeScalesFactory.getUTC();
+ AbsoluteDate initialDate = new AbsoluteDate(2005, 1, 1, 0, 0, 0.0, utc);
+ double duration = 100000.;
+ AbsoluteDate endDate = new AbsoluteDate(initialDate,duration);
+
+ // Initialization of the frame EME2000
+ Frame EME2000 = FramesFactory.getEME2000();
+
+
+ // Initial orbit
+ double a = 35786000. + 6378137.0;
+ double e = 0.70;
+ double rApogee = a*(1+e);
+ double vApogee = FastMath.sqrt(mu*(1-e)/(a*(1+e)));
+ Orbit geo = new CartesianOrbit(new PVCoordinates(new Vector3D(rApogee, 0., 0.),
+ new Vector3D(0., vApogee, 0.)), EME2000,
+ initialDate, mu);
+
+
+ duration = geo.getKeplerianPeriod();
+ endDate = new AbsoluteDate(initialDate, duration);
+
+ // Numerical Integration
+ final double minStep = 0.001;
+ final double maxStep = 1000;
+ final double initStep = 60;
+ final double[] absTolerance = {
+ 0.001, 1.0e-9, 1.0e-9, 1.0e-6, 1.0e-6, 1.0e-6, 0.001};
+ final double[] relTolerance = {
+ 1.0e-7, 1.0e-4, 1.0e-4, 1.0e-7, 1.0e-7, 1.0e-7, 1.0e-7};
+
+ AdaptiveStepsizeIntegrator integrator =
+ new DormandPrince853Integrator(minStep, maxStep, absTolerance, relTolerance);
+ integrator.setInitialStepSize(initStep);
+
+ // Numerical propagator based on the integrator
+ propagator = new NumericalPropagator(integrator);
+ double mass = 1000.;
+ SpacecraftState initialState = new SpacecraftState(geo, mass);
+ propagator.setInitialState(initialState);
+ propagator.setPropagationParametersType(PropagationParametersType.CARTESIAN);
+
+
+ // Set the events Detectors
+ ApsideDetector event1 = new ApsideDetector(geo);
+ propagator.addEventDetector(event1);
+
+ // Set the propagation mode
+ propagator.setSlaveMode();
+
+ // Propagate
+ SpacecraftState finalState = propagator.propagate(endDate);
+
+ // we should stop long before endDate
+ Assert.assertTrue(endDate.durationFrom(finalState.getDate()) > 40000.0);
+ }
+
+
@Before
public void setUp() {
+ Utils.setDataRoot("compressed-data");
mu = 3.9860047e14;
final Vector3D position = new Vector3D(7.0e6, 1.0e6, 4.0e6);
final Vector3D velocity = new Vector3D(-500.0, 8000.0, 1000.0);
diff --git a/src/test/java/org/orekit/propagation/numerical/NumericalPropagatorWithJacobiansTest.java b/src/test/java/org/orekit/propagation/numerical/NumericalPropagatorWithJacobiansTest.java
deleted file mode 100644
index 8b1cf93c34..0000000000
--- a/src/test/java/org/orekit/propagation/numerical/NumericalPropagatorWithJacobiansTest.java
+++ /dev/null
@@ -1,347 +0,0 @@
-/* Copyright 2002-2010 CS Communication & Systèmes
- * Licensed to CS Communication & Systèmes (CS) under one or more
- * contributor license agreements. See the NOTICE file distributed with
- * this work for additional information regarding copyright ownership.
- * CS licenses this file to You under the Apache License, Version 2.0
- * (the "License"); you may not use this file except in compliance with
- * the License. You may obtain a copy of the License at
- *
- * http://www.apache.org/licenses/LICENSE-2.0
- *
- * Unless required by applicable law or agreed to in writing, software
- * distributed under the License is distributed on an "AS IS" BASIS,
- * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
- * See the License for the specific language governing permissions and
- * limitations under the License.
- */
-package org.orekit.propagation.numerical;
-
-import org.apache.commons.math.ode.nonstiff.AdaptiveStepsizeIntegrator;
-import org.apache.commons.math.ode.nonstiff.DormandPrince853Integrator;
-import org.apache.commons.math.util.FastMath;
-import org.apache.commons.math.util.MathUtils;
-import org.junit.After;
-import org.junit.Assert;
-import org.junit.Before;
-import org.junit.Test;
-import org.orekit.Utils;
-import org.orekit.bodies.CelestialBodyFactory;
-import org.orekit.errors.OrekitException;
-import org.orekit.errors.PropagationException;
-import org.orekit.forces.ForceModelWithJacobians;
-import org.orekit.forces.SphericalSpacecraft;
-import org.orekit.forces.drag.DragForce;
-import org.orekit.forces.radiation.SolarRadiationPressure;
-import org.orekit.frames.FramesFactory;
-import org.orekit.orbits.EquinoctialOrbit;
-import org.orekit.propagation.SpacecraftState;
-import org.orekit.time.AbsoluteDate;
-import org.orekit.time.TimeScalesFactory;
-import org.orekit.utils.Constants;
-
-
-public class NumericalPropagatorWithJacobiansTest {
-
- private AbsoluteDate initDate;
- private SphericalSpacecraft spaceCraft;
- private SpacecraftState initialState;
- private NumericalPropagatorWithJacobians propagator;
-
- // Integrator parameters
- private final double minStep = 0.001;
- private final double maxStep = 1000.0;
- private final double[] absTolV = {0.001, 1.0e-9, 1.0e-9, 1.0e-6, 1.0e-6, 1.0e-6, 0.001};
- private final double[] relTolV = {1.0e-10, 1.0e-7, 1.0e-7, 1.0e-10, 1.0e-10, 1.0e-10, 1.0e-10};
-
- // Orbit parameters : position = (7.0e6, 1.0e6, 4.0e6) ; velocity = (-500.0, 8000.0, 1000.0)
- private final double a = 1.2123382253763368E7;
- private final double ex = 0.33088598908457206;
- private final double ey = -0.119544860585116;
- private final double hx = 0.07403074327464344;
- private final double hy = -0.25499478239043855;
- private final double lv = 0.1602263984451438;
- private final double mu = 3.9860047e14;
-
- // Force models parameters
- private final double drag = 0.4; // drag coeff.
- private final double srpr = 0.9; // solar radiation pressure coeff.
-
- // Threshold for test acceptance
- private final double ERRMAX = FastMath.sqrt(MathUtils.EPSILON);
-
- @Test
- public void testWithoutJacobian() throws OrekitException {
-
- // Propagation of the initial at t + dt
- // NumericalPropagatorWithJacobians behaves just the
- // same as NumericalPropagator for simple propagation
- final double dt = 300;
- final SpacecraftState finalState =
- propagator.propagate(initDate.shiftedBy(dt));
-
- // Check results
- final double n = FastMath.sqrt(initialState.getMu() / initialState.getA()) / initialState.getA();
- Assert.assertEquals(initialState.getA(), finalState.getA(), 1.0e-10);
- Assert.assertEquals(initialState.getEquinoctialEx(), finalState.getEquinoctialEx(), 1.0e-10);
- Assert.assertEquals(initialState.getEquinoctialEy(), finalState.getEquinoctialEy(), 1.0e-10);
- Assert.assertEquals(initialState.getHx(), finalState.getHx(), 1.0e-10);
- Assert.assertEquals(initialState.getHy(), finalState.getHy(), 1.0e-10);
- Assert.assertEquals(initialState.getLM() + n * dt, finalState.getLM(), 2.0e-8);
- }
-
- @Test
- public void testKeplerianJacobian() throws OrekitException {
- double[][] dFdY = new double[7][7];
- double[][] dFdP = new double[7][0];
- final double dt = 300;
- propagator.setInitialState(initialState);
- propagator.propagate(initDate.shiftedBy(dt), dFdY, dFdP);
-
- // Check results
- // without forces, the orbit is keplerian
- // all elements but the latitude argument are constant
- for (int i = 0; i < dFdY.length; i++) {
- if (i != 5) {
- for (int j = 0; j < dFdY[i].length; j++) {
- if (i != j) {
- Assert.assertEquals(dFdY[i][j], 0.0, MathUtils.EPSILON);
- } else {
- Assert.assertEquals(dFdY[i][j], 1.0, MathUtils.EPSILON);
- }
- }
- }
- }
- }
-
- @Test
- public void testOrbitalParametersJacobian() throws OrekitException {
-
- double[][] dFdY = new double[7][7];
- double[][] dFdP = new double[7][0];
- final double dt = 3;
-
- ForceModelWithJacobians sunPressure =
- new SolarRadiationPressure(CelestialBodyFactory.getSun(),
- Constants.WGS84_EARTH_EQUATORIAL_RADIUS, spaceCraft);
- propagator.addForceModel(sunPressure);
- propagator.setInitialState(initialState);
- final SpacecraftState finalState =
- propagator.propagate(initDate.shiftedBy(dt), dFdY, dFdP);
-
- final double da = absTolV[0]*1.e1;
- propagator.resetInitialState(
- new SpacecraftState(new EquinoctialOrbit(a + da, ex, ey, hx, hy, lv,
- EquinoctialOrbit.TRUE_LATITUDE_ARGUMENT,
- FramesFactory.getEME2000(), initDate, mu)));
- final SpacecraftState endStateDa = propagator.propagate(initDate.shiftedBy(dt));
- // Check results
- final double dAda0 = (endStateDa.getA() - finalState.getA()) / da;
- final double dExda0 = (endStateDa.getEquinoctialEx() - finalState.getEquinoctialEx()) / da;
- final double dEyda0 = (endStateDa.getEquinoctialEy() - finalState.getEquinoctialEy()) / da;
- final double dHxda0 = (endStateDa.getHx() - finalState.getHx()) / da;
- final double dHyda0 = (endStateDa.getHy() - finalState.getHy()) / da;
- final double dLvda0 = (endStateDa.getLv() - finalState.getLv()) / da;
- final double dMda0 = (endStateDa.getMass() - finalState.getMass()) / da;
-
- Assert.assertTrue(FastMath.abs((dAda0 - dFdY[0][0])/finalState.getA()) < ERRMAX);
- Assert.assertTrue(FastMath.abs((dExda0 - dFdY[1][0])/finalState.getEquinoctialEx()) < ERRMAX);
- Assert.assertTrue(FastMath.abs((dEyda0 - dFdY[2][0])/finalState.getEquinoctialEy()) < ERRMAX);
- Assert.assertTrue(FastMath.abs((dHxda0 - dFdY[3][0])/finalState.getHx()) < ERRMAX);
- Assert.assertTrue(FastMath.abs((dHyda0 - dFdY[4][0])/finalState.getHy()) < ERRMAX);
- Assert.assertTrue(FastMath.abs((dLvda0 - dFdY[5][0])/finalState.getHy()) < ERRMAX);
- Assert.assertEquals(dMda0, dFdY[6][0], 0.0);
-
- final double dex = absTolV[1]*1.e1;
- propagator.resetInitialState(
- new SpacecraftState(new EquinoctialOrbit(a, ex + dex, ey, hx, hy, lv,
- EquinoctialOrbit.TRUE_LATITUDE_ARGUMENT,
- FramesFactory.getEME2000(), initDate, mu)));
- final SpacecraftState endStateDex = propagator.propagate(initDate.shiftedBy(dt));
- // Check results
- final double dAdex0 = (endStateDex.getA() - finalState.getA()) / dex;
- final double dExdex0 = (endStateDex.getEquinoctialEx() - finalState.getEquinoctialEx()) / dex;
- final double dEydex0 = (endStateDex.getEquinoctialEy() - finalState.getEquinoctialEy()) / dex;
- final double dHxdex0 = (endStateDex.getHx() - finalState.getHx()) / dex;
- final double dHydex0 = (endStateDex.getHy() - finalState.getHy()) / dex;
- final double dLvdex0 = (endStateDex.getLv() - finalState.getLv()) / dex;
- final double dMdex0 = (endStateDex.getMass() - finalState.getMass()) / dex;
-
- Assert.assertTrue(FastMath.abs((dAdex0 - dFdY[0][1])/finalState.getA()) < ERRMAX);
- Assert.assertTrue(FastMath.abs((dExdex0 - dFdY[1][1])/finalState.getEquinoctialEx()) < ERRMAX);
- Assert.assertTrue(FastMath.abs((dEydex0 - dFdY[2][1])/finalState.getEquinoctialEy()) < ERRMAX);
- Assert.assertTrue(FastMath.abs((dHxdex0 - dFdY[3][1])/finalState.getHx()) < ERRMAX);
- Assert.assertTrue(FastMath.abs((dHydex0 - dFdY[4][1])/finalState.getHy()) < ERRMAX);
- Assert.assertTrue(FastMath.abs((dLvdex0 - dFdY[5][1])/finalState.getHy()) < ERRMAX);
- Assert.assertEquals(dMdex0, dFdY[6][1], 0.0);
-
- final double dey = absTolV[2]*1.e1;
- propagator.resetInitialState(
- new SpacecraftState(new EquinoctialOrbit(a, ex, ey + dey, hx, hy, lv,
- EquinoctialOrbit.TRUE_LATITUDE_ARGUMENT,
- FramesFactory.getEME2000(), initDate, mu)));
- final SpacecraftState endStateDey = propagator.propagate(initDate.shiftedBy(dt));
- // Check results
- final double dAdey0 = (endStateDey.getA() - finalState.getA()) / dey;
- final double dExdey0 = (endStateDey.getEquinoctialEx() - finalState.getEquinoctialEx()) / dey;
- final double dEydey0 = (endStateDey.getEquinoctialEy() - finalState.getEquinoctialEy()) / dey;
- final double dHxdey0 = (endStateDey.getHx() - finalState.getHx()) / dey;
- final double dHydey0 = (endStateDey.getHy() - finalState.getHy()) / dey;
- final double dLvdey0 = (endStateDey.getLv() - finalState.getLv()) / dey;
- final double dMdey0 = (endStateDey.getMass() - finalState.getMass()) / dey;
-
- Assert.assertTrue(FastMath.abs(dAdey0 - dFdY[0][2])/finalState.getA() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dExdey0 - dFdY[1][2])/finalState.getEquinoctialEx() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dEydey0 - dFdY[2][2])/finalState.getEquinoctialEy() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dHxdey0 - dFdY[3][2])/finalState.getHx() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dHydey0 - dFdY[4][2])/finalState.getHy() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dLvdey0 - dFdY[5][2])/finalState.getLv() < ERRMAX);
- Assert.assertEquals(dMdey0, dFdY[6][2], 0.0);
-
- final double dhx = absTolV[3]*1.e1;
- propagator.resetInitialState(
- new SpacecraftState(new EquinoctialOrbit(a, ex, ey, hx + dhx, hy, lv,
- EquinoctialOrbit.TRUE_LATITUDE_ARGUMENT,
- FramesFactory.getEME2000(), initDate, mu)));
- final SpacecraftState endStateDhx = propagator.propagate(initDate.shiftedBy(dt));
- // Check results
- final double dAdhx0 = (endStateDhx.getA() - finalState.getA()) / dhx;
- final double dExdhx0 = (endStateDhx.getEquinoctialEx() - finalState.getEquinoctialEx()) / dhx;
- final double dEydhx0 = (endStateDhx.getEquinoctialEy() - finalState.getEquinoctialEy()) / dhx;
- final double dHxdhx0 = (endStateDhx.getHx() - finalState.getHx()) / dhx;
- final double dHydhx0 = (endStateDhx.getHy() - finalState.getHy()) / dhx;
- final double dLvdhx0 = (endStateDhx.getLv() - finalState.getLv()) / dhx;
- final double dMdhx0 = (endStateDhx.getMass() - finalState.getMass()) / dhx;
-
- Assert.assertTrue(FastMath.abs(dAdhx0 - dFdY[0][3])/finalState.getA() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dExdhx0 - dFdY[1][3])/finalState.getEquinoctialEx() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dEydhx0 - dFdY[2][3])/finalState.getEquinoctialEy() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dHxdhx0 - dFdY[3][3])/finalState.getHx() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dHydhx0 - dFdY[4][3])/finalState.getHy() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dLvdhx0 - dFdY[5][3])/finalState.getLv() < ERRMAX);
- Assert.assertEquals(dMdhx0, dFdY[6][3], 0.0);
-
- final double dhy = absTolV[4]*1.e1;
- propagator.resetInitialState(
- new SpacecraftState(new EquinoctialOrbit(a, ex, ey, hx, hy + dhy, lv,
- EquinoctialOrbit.TRUE_LATITUDE_ARGUMENT,
- FramesFactory.getEME2000(), initDate, mu)));
- final SpacecraftState endStateDhy = propagator.propagate(initDate.shiftedBy(dt));
- // Check results
- final double dAdhy0 = (endStateDhy.getA() - finalState.getA()) / dhy;
- final double dExdhy0 = (endStateDhy.getEquinoctialEx() - finalState.getEquinoctialEx()) / dhy;
- final double dEydhy0 = (endStateDhy.getEquinoctialEy() - finalState.getEquinoctialEy()) / dhy;
- final double dHxdhy0 = (endStateDhy.getHx() - finalState.getHx()) / dhy;
- final double dHydhy0 = (endStateDhy.getHy() - finalState.getHy()) / dhy;
- final double dLvdhy0 = (endStateDhy.getLv() - finalState.getLv()) / dhy;
- final double dMdhy0 = (endStateDhy.getMass() - finalState.getMass()) / dhy;
-
- Assert.assertTrue(FastMath.abs(dAdhy0 - dFdY[0][4])/finalState.getA() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dExdhy0 - dFdY[1][4])/finalState.getEquinoctialEx() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dEydhy0 - dFdY[2][4])/finalState.getEquinoctialEy() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dHxdhy0 - dFdY[3][4])/finalState.getHx() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dHydhy0 - dFdY[4][4])/finalState.getHy() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dLvdhy0 - dFdY[5][4])/finalState.getLv() < ERRMAX);
- Assert.assertEquals(dMdhy0, dFdY[6][4], 0.0);
-
- final double dlv = absTolV[5]*1.e1;
- propagator.resetInitialState(
- new SpacecraftState(new EquinoctialOrbit(a, ex, ey, hx, hy, lv + dlv,
- EquinoctialOrbit.TRUE_LATITUDE_ARGUMENT,
- FramesFactory.getEME2000(), initDate, mu)));
- final SpacecraftState endStateDlv = propagator.propagate(initDate.shiftedBy(dt));
- // Check results
- final double dAdlv0 = (endStateDlv.getA() - finalState.getA()) / dlv;
- final double dExdlv0 = (endStateDlv.getEquinoctialEx() - finalState.getEquinoctialEx()) / dlv;
- final double dEydlv0 = (endStateDlv.getEquinoctialEy() - finalState.getEquinoctialEy()) / dlv;
- final double dHxdlv0 = (endStateDlv.getHx() - finalState.getHx()) / dlv;
- final double dHydlv0 = (endStateDlv.getHy() - finalState.getHy()) / dlv;
- final double dLvdlv0 = (endStateDlv.getLv() - finalState.getLv()) / dlv;
- final double dMdlv0 = (endStateDlv.getMass() - finalState.getMass()) / dlv;
-
- Assert.assertTrue(FastMath.abs(dAdlv0 - dFdY[0][5])/finalState.getA() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dExdlv0 - dFdY[1][5])/finalState.getEquinoctialEx() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dEydlv0 - dFdY[2][5])/finalState.getEquinoctialEy() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dHxdlv0 - dFdY[3][5])/finalState.getHx() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dHydlv0 - dFdY[4][5])/finalState.getHy() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dLvdlv0 - dFdY[5][5])/finalState.getLv() < ERRMAX);
- Assert.assertEquals(dMdlv0, dFdY[6][5], 0.0);
- }
-
- @Test
- public void testForceParameterJacobian() throws OrekitException {
- double[][] dFdY = new double[7][7];
- double[][] dFdP = new double[7][1];
- final double dt = 300;
-
- ForceModelWithJacobians sunPressure =
- new SolarRadiationPressure(CelestialBodyFactory.getSun(),
- Constants.WGS84_EARTH_EQUATORIAL_RADIUS, spaceCraft);
- propagator.addForceModel(sunPressure);
- propagator.selectParameters(new String[] {SolarRadiationPressure.ABSORPTION_COEFFICIENT});
- propagator.setInitialState(initialState);
- final SpacecraftState finalState = propagator.propagate(initDate.shiftedBy(dt), dFdY, dFdP);
-
- propagator.removeForceModels();
- final double dp = srpr * 0.1;
- final double srprDP = srpr + dp;
- sunPressure.setParameter(SolarRadiationPressure.ABSORPTION_COEFFICIENT, srprDP);
- propagator.addForceModel(sunPressure);
- propagator.setInitialState(initialState);
- final SpacecraftState endStateDP = propagator.propagate(initDate.shiftedBy(dt));
-
- // Check results
- final double dAdP = (endStateDP.getA() - finalState.getA()) / dp;
- final double dExdP = (endStateDP.getEquinoctialEx() - finalState.getEquinoctialEx()) / dp;
- final double dEydP = (endStateDP.getEquinoctialEy() - finalState.getEquinoctialEy()) / dp;
- final double dHxdP = (endStateDP.getHx() - finalState.getHx()) / dp;
- final double dHydP = (endStateDP.getHy() - finalState.getHy()) / dp;
- final double dLvdP = (endStateDP.getLv() - finalState.getLv()) / dp;
-
- Assert.assertTrue(FastMath.abs(dAdP - dFdP[0][0])/finalState.getA() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dExdP - dFdP[1][0])/finalState.getEquinoctialEx() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dEydP - dFdP[2][0])/finalState.getEquinoctialEy() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dHxdP - dFdP[3][0])/finalState.getHx() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dHydP - dFdP[4][0])/finalState.getHy() < ERRMAX);
- Assert.assertTrue(FastMath.abs(dLvdP - dFdP[5][0])/finalState.getLv() < ERRMAX);
- }
-
- @Test(expected=PropagationException.class)
- public void testException() throws OrekitException {
- double[][] dFdY = null;
- double[][] dFdP = null;
- final double dt = 300;
- propagator.removeForceModels();
- propagator.selectParameters(new String[] {DragForce.DRAG_COEFFICIENT});
- propagator.propagate(initDate.shiftedBy(dt), dFdY, dFdP);
- }
-
- @Before
- public void setUp() {
-
- Utils.setDataRoot("regular-data");
-
- initDate = new AbsoluteDate(2003, 1, 1, TimeScalesFactory.getTAI());
- initialState =
- new SpacecraftState(
- new EquinoctialOrbit(a, ex, ey, hx, hy, lv,
- EquinoctialOrbit.TRUE_LATITUDE_ARGUMENT,
- FramesFactory.getEME2000(), initDate, mu));
- AdaptiveStepsizeIntegrator integrator =
- new DormandPrince853Integrator(minStep, maxStep, absTolV, relTolV);
- propagator = new NumericalPropagatorWithJacobians(integrator);
- propagator.setInitialState(initialState);
-
- // Spacecraft definition for force models
- final double surf = 25.;
- spaceCraft = new SphericalSpacecraft(surf, drag, srpr, srpr);
- }
-
- @After
- public void tearDown() {
- initDate = null;
- initialState = null;
- propagator = null;
- }
-
-}
-
diff --git a/src/test/java/org/orekit/propagation/numerical/IntegratedEphemerisTest.java b/src/test/java/org/orekit/propagation/precomputed/IntegratedEphemerisTest.java
similarity index 97%
rename from src/test/java/org/orekit/propagation/numerical/IntegratedEphemerisTest.java
rename to src/test/java/org/orekit/propagation/precomputed/IntegratedEphemerisTest.java
index 59e8058f85..bf832d23ea 100644
--- a/src/test/java/org/orekit/propagation/numerical/IntegratedEphemerisTest.java
+++ b/src/test/java/org/orekit/propagation/precomputed/IntegratedEphemerisTest.java
@@ -14,7 +14,7 @@
* See the License for the specific language governing permissions and
* limitations under the License.
*/
-package org.orekit.propagation.numerical;
+package org.orekit.propagation.precomputed;
import java.io.FileNotFoundException;
@@ -30,6 +30,7 @@ import org.orekit.orbits.Orbit;
import org.orekit.propagation.BoundedPropagator;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.analytical.KeplerianPropagator;
+import org.orekit.propagation.numerical.NumericalPropagator;
import org.orekit.time.AbsoluteDate;
import org.orekit.utils.Constants;
import org.orekit.utils.PVCoordinates;
diff --git a/src/test/java/org/orekit/time/AbsoluteDateTest.java b/src/test/java/org/orekit/time/AbsoluteDateTest.java
index 71c93529cc..2959237671 100644
--- a/src/test/java/org/orekit/time/AbsoluteDateTest.java
+++ b/src/test/java/org/orekit/time/AbsoluteDateTest.java
@@ -248,7 +248,7 @@ public class AbsoluteDateTest {
public void testCCSDSUnsegmented() throws OrekitException {
AbsoluteDate reference = new AbsoluteDate("2002-05-23T12:34:56.789", TimeScalesFactory.getUTC());
- double lsb = Math.pow(2.0, -24);
+ double lsb = FastMath.pow(2.0, -24);
byte[] timeCCSDSEpoch = new byte[] { 0x53, 0x7F, 0x40, -0x70, -0x37, -0x05, -0x19 };
for (int preamble = 0x00; preamble < 0x100; ++preamble) {
--
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