Commit f6d3c8ea authored by Luc Maisonobe's avatar Luc Maisonobe
Browse files

Removed tabs and trailing whitespace.

Some tabs have been preserved in resource test files (EOP data and CCSDS
files) for testing purposes.
parent 54b4e321
Pipeline #2150 passed with stages
in 31 minutes and 11 seconds
......@@ -125,13 +125,13 @@
<pathelement location="${main.classes.dir}" />
<pathelement location="${test.classes.dir}" />
<pathelement location="${lib.dir}/${hipparchus.core.jar}" />
<pathelement location="${lib.dir}/${hipparchus.geometry.jar}" />
<pathelement location="${lib.dir}/${hipparchus.ode.jar}" />
<pathelement location="${lib.dir}/${hipparchus.fitting.jar}" />
<pathelement location="${lib.dir}/${hipparchus.optim.jar}" />
<pathelement location="${lib.dir}/${hipparchus.stat.jar}" />
<pathelement location="${lib.dir}/${junit.jar}" />
<pathelement location="${lib.dir}/${hamcrest.core.jar}" />
<pathelement location="${lib.dir}/${hipparchus.geometry.jar}" />
<pathelement location="${lib.dir}/${hipparchus.ode.jar}" />
<pathelement location="${lib.dir}/${hipparchus.fitting.jar}" />
<pathelement location="${lib.dir}/${hipparchus.optim.jar}" />
<pathelement location="${lib.dir}/${hipparchus.stat.jar}" />
<pathelement location="${lib.dir}/${junit.jar}" />
<pathelement location="${lib.dir}/${hamcrest.core.jar}" />
<pathelement location="${lib.dir}/${hipparchus.filtering.jar}"/>
<pathelement location="${lib.dir}/${mockito.jar}" />
<pathelement location="${lib.dir}/${objenesis.jar}" />
......
......@@ -112,6 +112,6 @@
</module>
<module name="FileTabCharacter"/>
<module name="NewlineAtEndOfFile">
<property name="lineSeparator" value="LF_CR_CRLF"/>
</module>
<property name="lineSeparator" value="LF_CR_CRLF"/>
</module>
</module>
......@@ -346,19 +346,19 @@
when building the state transition matrix in multi satellites
orbit determination. It also fixes bugs in TLE and CRD files.
Finally it includes an update of the release guide.">
<action dev="bryan" type="fix" issue="859" due-to="Emmanuel Papanagiotou">
<action dev="bryan" type="fix" issue="859" due-to="Emmanuel Papanagiotou">
Allowed custom setting of state to TLE conversion in propagator builder.
</action>
<action dev="bryan" type="fix" issue="847">
<action dev="bryan" type="fix" issue="847">
Fixed handling of comments in CRD files.
</action>
<action dev="bryan" type="fix" issue="851">
<action dev="bryan" type="fix" issue="851">
Fixed deserialization of TLE caused by the bStarParameterDriver.
</action>
<action dev="bryan" type="fix" issue="850">
<action dev="bryan" type="fix" issue="850">
Fixed indexes when build state transition matrix for multi sat Kalman.
</action>
<action dev="sdinot" type="update">
<action dev="sdinot" type="update">
Updated the release guide to remove actions that are no longer required.
</action>
</release>
......@@ -367,26 +367,26 @@
It fixes an important issue related to the calculation of the relativistic
clock correction for GNSS measurements. It also fixes bugs in OEM and CPF
files writing. Finally it includes some improvements in the class documentation">
<action dev="bryan" type="fix" issue="846">
<action dev="bryan" type="fix" issue="846">
Fixed wrong computation of relativistic clock correction for GNSS measurements.
</action>
<action dev="bryan" type="fix" issue="845">
<action dev="bryan" type="fix" issue="845">
Fixed parsing of Rinex clock files.
</action>
<action dev="bryan" type="fix" issue="844">
<action dev="bryan" type="fix" issue="844">
Fixed null pointer exception when constructing CPF from coordinates.
</action>
<action dev="bryan" type="update" issue="843">
<action dev="bryan" type="update" issue="843">
Improved documentation of solar radiation pressure class to include
additional information about osculating bodies.
</action>
<action dev="sdinot" type="update" issue="842">
<action dev="sdinot" type="update" issue="842">
Used the latest version of Maven available in RedHat 8.
</action>
<action dev="pascal" type="fix" issue="839">
<action dev="pascal" type="fix" issue="839">
Fixed handling of time system in OemWriter.
</action>
<action dev="bryan" type="update" issue="838" due-to="Kendra Hale">
<action dev="bryan" type="update" issue="838" due-to="Kendra Hale">
Improved documentation of ImpulseManeuver class.
</action>
</release>
......@@ -405,14 +405,14 @@
to add several step handlers for the same orbit propagation, a new
event detector for angular separation as seen from the spacecraft.
See the list below for a full description of the changes.">
<action dev="bryan" type="update" issue="766" due-to="Gowtham Sivaraman">
<action dev="bryan" type="update" issue="766" due-to="Gowtham Sivaraman">
Allowed setting of AttitudeProvider to the BoundedPropagator
generated via propagation.
</action>
<action dev="bryan" type="fix" issue="835">
<action dev="bryan" type="fix" issue="835">
Fixed format symbols for year, month, day in DateComponents#toString().
</action>
<action dev="thomas" type="fix" issue="668">
<action dev="thomas" type="fix" issue="668">
Added a new event detector for angular separation as seen from the spacecraft.
</action>
<action dev="maxime" type="fix" issue="829">
......@@ -623,8 +623,8 @@
<action dev="bryan" type="fix" issue="670">
Fixed call to ForceModel.init() in AbstractGaussianContribution class.
</action>
<action dev="thomas" type="add" issue="712">
Added IGS clock file support.
<action dev="thomas" type="add" issue="712">
Added IGS clock file support.
</action>
<action dev="bryan" type="update" issue="650">
Methods computeMeanState() and computeOsculatingState()
......@@ -640,7 +640,7 @@
Fixed reference frame in tabulated attitude provider.
</action>
<action dev="luc" type="update" >
Renamed SINEXLoader into SinexLoader.
Renamed SINEXLoader into SinexLoader.
</action>
<action dev="luc" type="update" >
Use DataSource in RinexLoader and SinexLoader.
......@@ -694,13 +694,13 @@
Fixed NullPointerException in DSSTTesseral Hansen object.
</action>
<action dev="bryan" type="update" issue="601">
Changed getPVInPZ90() method to private.
Changed getPVInPZ90() method to private.
</action>
<action dev="bryan" type="fix" issue="744">
Fixed calculation of CR3BP constants.
Fixed calculation of CR3BP constants.
</action>
<action dev="bryan" type="update" issue="743">
Updated JUnit version to 4.13.1.
Updated JUnit version to 4.13.1.
</action>
</release>
<release version="10.3.1" date="2021-06-16"
......@@ -728,14 +728,14 @@
<action dev="bryan" type="update" issue="741">
Updated Hipparchus version to 1.8 and updated code with new functionalities.
</action>
<action dev="bryan" type="add" issue="740">
Added aggregator for bounded attitude providers.
<action dev="bryan" type="add" issue="740">
Added aggregator for bounded attitude providers.
</action>
<action dev="thomas" type="add" issue="8">
<action dev="thomas" type="add" issue="8">
Added Knocke's Earth rediffused radiation pressure force model.
</action>
<action dev="bryan" type="add" issue="739">
Allowed initialization of attitude provider from attitude segment.
<action dev="bryan" type="add" issue="739">
Allowed initialization of attitude provider from attitude segment.
</action>
<action dev="raphael" type="add" issue="705">
Allowed writing an AEM file from a list of SpacecraftStates.
......@@ -750,20 +750,20 @@
Allowed user-defined format for ephemeris data lines in
StreamingAemWriter, AEMWriter, StreamingOemWriter and OEMWriter.
</action>
<action dev="bryan" type="fix" issue="683">
Updated building instructions.
<action dev="bryan" type="fix" issue="683">
Updated building instructions.
</action>
<action dev="bryan" type="add" issue="734">
Added getters for phase measurement ambiguity driver.
<action dev="bryan" type="add" issue="734">
Added getters for phase measurement ambiguity driver.
</action>
<action dev="bryan" type="fix" issue="696">
Allowed to configure initial covariance for measurements in Kalman Filter.
<action dev="bryan" type="fix" issue="696">
Allowed to configure initial covariance for measurements in Kalman Filter.
</action>
<action dev="thomas, bryan" type="add" issue="709">
Added clock drift contribution to range rate measurements.
</action>
<action dev="bryan" type="fix" issue="687">
Fixed Javadoc of ElevationMask.
<action dev="bryan" type="fix" issue="687">
Fixed Javadoc of ElevationMask.
</action>
<action dev="raphael" type="fix" issue="711">
Allowed definition of a default interpolation degree in both AEMParser and OEMParser.
......@@ -777,14 +777,14 @@
<action dev="bryan" type="add" issue="732">
Added documentation for checkstyle configuration.
</action>
<action dev="thomas" type="fix" issue="730">
Removed useless loop over an empty list
<action dev="thomas" type="fix" issue="730">
Removed useless loop over an empty list
</action>
<action dev="luc" type="fix" issue="731">
Fixed parsing of some ICGEM gravity fields files.
</action>
<action dev="raphael" type="fix" issue="720">
Added support for measurements parameters in UnivariateProcessNoise
Added support for measurements parameters in UnivariateProcessNoise
</action>
<action dev="luc" type="fix" issue="729">
Fixed wrong handling of RESET-STATE in analytical propagators.
......@@ -834,7 +834,7 @@
<action dev="bryan" type="fix" issue="706">
Fixed missing measurement parameter in inter-satellites range measurement.
</action>
<action dev="thomas" type="fix" issue="713">
<action dev="thomas" type="fix" issue="713">
Fixed computation of DSST short period Jacobian.
</action>
<action dev="luc" type="fix" issue="699">
......@@ -1029,22 +1029,22 @@
Improve performance of ZipJarCrawler.
</action>
<action dev="bryan" type="add" issue="625">
Added default constructors for DSSTZonal and DSSTTesseral.
Added default constructors for DSSTZonal and DSSTTesseral.
</action>
<action dev="bryan" type="add" issue="622">
Added OrekitException for unknown number of frequencies in ANTEX files.
Added OrekitException for unknown number of frequencies in ANTEX files.
</action>
<action dev="bryan" type="add" issue="621">
Added OrekitException in the case where IONEX header is corrupted.
Added OrekitException in the case where IONEX header is corrupted.
</action>
<action dev="dylan" type="add" issue="359">
Added a specific test for issue 359 in BatchLSEstimatorTest.
The test verifies that a Newtonian attraction is known
by both the propagator builder and the propagator when
it is not added explicitly.
Added a specific test for issue 359 in BatchLSEstimatorTest.
The test verifies that a Newtonian attraction is known
by both the propagator builder and the propagator when
it is not added explicitly.
</action>
<action dev="dylan" type="add" issue="367">
Added write of covariance matrices in OEMWriter.
Added write of covariance matrices in OEMWriter.
</action>
<action dev="dylan" type="fix" issue="619">
Fixed origin transform in CcsdsModifierFrame.
......@@ -1495,12 +1495,12 @@
Allow parsing of SP3 files that use non-predefined orbit types.
Fixes issue #491.
</action>
<action dev="maxime" type="add" issue="485">
<action dev="maxime" type="add" issue="485">
Added access to Kalman filter matrices.
KalmanEstimation interface now has methods returning the physical values of:
state transition matrix phi, measurement matrix H, innovation matrix S and Kalman gain matrix K.
The methods are implemented in Model class. A class ModelTest was added to test these values.
Fixes issue #485
KalmanEstimation interface now has methods returning the physical values of:
state transition matrix phi, measurement matrix H, innovation matrix S and Kalman gain matrix K.
The methods are implemented in Model class. A class ModelTest was added to test these values.
Fixes issue #485
</action>
<action dev="luc" type="fix" issue="492" due-to="Lebas">
Fixed error message for TLE with incorrect checksum.
......@@ -3380,7 +3380,7 @@
Removed too stringent test on trajectory in TLE propagator (fixes bug #86).
</action>
<action dev="thomas" type="fix">
Set the initial state for a TLEPropagator (fixes bug #85).
Set the initial state for a TLEPropagator (fixes bug #85).
</action>
<action dev="luc" type="update">
Improved testing of error messages.
......
......@@ -42,10 +42,10 @@
package attitude #DDEBD8 {
class Attitude {
+Attitude withReferenceFrame
+Frame getReferenceFrame
+Attitude withReferenceFrame
+Frame getReferenceFrame
+Rotation getRotation
+Vector3D getSpin
+Vector3D getSpin
}
class AttitudesSequence {
......
......@@ -34,7 +34,7 @@
interface DataLoader
abstract class AbstractSelfFeedingLoader {
#feed(final DataLoader loader)
#feed(final DataLoader loader)
}
}
......
......@@ -38,8 +38,8 @@
}
class DataSource {
+String getName()
+DataSource.Opener getOpener()
+String getName()
+DataSource.Opener getOpener()
}
interface DataFilter {
......
......@@ -86,8 +86,8 @@
}
enum FilterType {
TRIGGER_ONLY_DECREASING_EVENTS
TRIGGER_ONLY_INCREASING_EVENTS
TRIGGER_ONLY_DECREASING_EVENTS
TRIGGER_ONLY_INCREASING_EVENTS
}
interface EnablingPredicate {
......
......@@ -63,7 +63,7 @@ j = 0 Nb of terms = 33
12 -0.63 0.00 1 0 0 0 1 0 0 0 0 0 0 0 0 0
13 0.46 0.00 0 1 2 -2 3 0 0 0 0 0 0 0 0 0
14 0.45 0.00 0 1 2 -2 1 0 0 0 0 0 0 0 0 0
15 0.36 0.00 0 0 4 -4 4 0 0 0 0 0 0 0 0 0
15 0.36 0.00 0 0 4 -4 4 0 0 0 0 0 0 0 0 0
16 -0.24 -0.12 0 0 1 -1 1 0 -8 12 0 0 0 0 0 0
17 0.32 0.00 0 0 2 0 0 0 0 0 0 0 0 0 0 0
18 0.28 0.00 0 0 2 0 2 0 0 0 0 0 0 0 0 0
......
......@@ -65,7 +65,7 @@ j = 0 Number of terms = 33
12 -0.63 0.00 1 0 0 0 1 0 0 0 0 0 0 0 0 0
13 0.46 0.00 0 1 2 -2 3 0 0 0 0 0 0 0 0 0
14 0.45 0.00 0 1 2 -2 1 0 0 0 0 0 0 0 0 0
15 0.36 0.00 0 0 4 -4 4 0 0 0 0 0 0 0 0 0
15 0.36 0.00 0 0 4 -4 4 0 0 0 0 0 0 0 0 0
16 -0.24 -0.12 0 0 1 -1 1 0 -8 12 0 0 0 0 0 0
17 0.32 0.00 0 0 2 0 0 0 0 0 0 0 0 0 0 0
18 0.28 0.00 0 0 2 0 2 0 0 0 0 0 0 0 0 0
......
......@@ -97,7 +97,7 @@ public class Utils {
DataContext.getDefault().getDataProvidersManager().clearProviders();
DataContext.getDefault().getDataProvidersManager().resetFiltersToDefault();
DataContext.getDefault().getDataProvidersManager().clearLoadedDataNames();
}
public static DataContext setDataRoot(String root) {
......
......@@ -118,7 +118,7 @@ public class AggregateBoundedAttitudeProviderTest {
final AemSatelliteEphemeris ephemeris = file.getSatellites().get("1996-062A");
final BoundedAttitudeProvider provider = ephemeris.getAttitudeProvider();
// before bound of first attitude provider
try {
provider.getAttitude(null, provider.getMinDate().shiftedBy(-60.0), null);
......@@ -148,7 +148,7 @@ public class AggregateBoundedAttitudeProviderTest {
final AemSatelliteEphemeris ephemeris = file.getSatellites().get("1996-062A");
final BoundedAttitudeProvider provider = ephemeris.getAttitudeProvider();
// before bound of first attitude provider
try {
provider.getAttitude(null, new FieldAbsoluteDate<>(provider.getMinDate(), field.getZero().subtract(60.0)), null);
......@@ -165,5 +165,5 @@ public class AggregateBoundedAttitudeProviderTest {
}
}
......@@ -257,7 +257,7 @@ public class AttitudesSequenceTest {
// Propagator : consider the analytical Eckstein-Hechler model
final FieldPropagator<T> propagator = new FieldEcksteinHechlerPropagator<T>(initialOrbit, attitudesSequence,
Constants.EIGEN5C_EARTH_EQUATORIAL_RADIUS,
field.getZero().add(Constants.EIGEN5C_EARTH_MU),
field.getZero().add(Constants.EIGEN5C_EARTH_MU),
Constants.EIGEN5C_EARTH_C20,
Constants.EIGEN5C_EARTH_C30, Constants.EIGEN5C_EARTH_C40,
Constants.EIGEN5C_EARTH_C50, Constants.EIGEN5C_EARTH_C60);
......@@ -501,27 +501,27 @@ public class AttitudesSequenceTest {
Assert.assertEquals(0.5 * reorientationAngle,
Rotation.distance(state.getAttitude().getRotation(), nadirR),
0.03 * reorientationAngle);
// check that if we restart a forward propagation from an intermediate state
// we properly get the "after" attitude law despite we missed the event trigger
// This check have been added to the test after the issue #552 fix
final AbsoluteDate afterTransition = midTransition.shiftedBy(transitionTime);
state = propagator.propagate(midTransition, afterTransition);
targetR = targetPointing.getAttitude(state.getOrbit(), state.getDate(), state.getFrame()).getRotation();
Assert.assertEquals(targetR.getQ0(),
state.getAttitude().getRotation().getQ0(),
1.0e-16);
state.getAttitude().getRotation().getQ0(),
1.0e-16);
Assert.assertEquals(targetR.getQ1(),
state.getAttitude().getRotation().getQ1(),
1.0e-16);
state.getAttitude().getRotation().getQ1(),
1.0e-16);
Assert.assertEquals(targetR.getQ2(),
state.getAttitude().getRotation().getQ2(),
1.0e-16);
state.getAttitude().getRotation().getQ2(),
1.0e-16);
Assert.assertEquals(targetR.getQ3(),
state.getAttitude().getRotation().getQ3(),
1.0e-16);
state.getAttitude().getRotation().getQ3(),
1.0e-16);
}
@Test
......@@ -577,23 +577,23 @@ public class AttitudesSequenceTest {
Assert.assertEquals(0.5 * reorientationAngle,
Rotation.distance(state.getAttitude().getRotation(), targetR),
0.03 * reorientationAngle);
}
/**
* Test for the issue 551 fix
*/
@Test
@Test
public void testAnalyticalPropagatorTransition() {
// Define initial state
// Define initial state
final AbsoluteDate initialDate = new AbsoluteDate(2017, 03, 27, 0, 0, 00.000, TimeScalesFactory.getUTC());
final Vector3D position = new Vector3D(-39098981.4866597, -15784239.3610601, 78908.2289853595);
final Vector3D velocity = new Vector3D(1151.00321021175, -2851.14864755189, -2.02133248357321);
final Orbit initialOrbit = new KeplerianOrbit(new PVCoordinates(position, velocity),
FramesFactory.getGCRF(), initialDate,
Constants.WGS84_EARTH_MU);
Constants.WGS84_EARTH_MU);
// Define attitude laws
final AttitudeProvider before = new InertialProvider(new Rotation(0, 0, 0, 1, false));
final AttitudeProvider current = new InertialProvider(Rotation.IDENTITY);
......@@ -604,51 +604,51 @@ public class AttitudesSequenceTest {
final AbsoluteDate backwardSwitchDate = initialDate.shiftedBy(-600);
final DateDetector forwardSwitchDetector = new DateDetector(forwardSwitchDate).withHandler(new ContinueOnEvent<DateDetector>());
final DateDetector backwardSwitchDetector = new DateDetector(backwardSwitchDate).withHandler(new ContinueOnEvent<DateDetector>());
// Initialize the attitude sequence
final AttitudesSequence attitudeSequence = new AttitudesSequence();
attitudeSequence.resetActiveProvider(current);
attitudeSequence.addSwitchingCondition(before, current, backwardSwitchDetector, true, true, 60, AngularDerivativesFilter.USE_RR, null);
attitudeSequence.addSwitchingCondition(current, after, forwardSwitchDetector, true, true, 60, AngularDerivativesFilter.USE_RR, null);
// Initialize analytical propagator
Propagator propagator = new KeplerianPropagator(initialOrbit);
propagator.setAttitudeProvider(attitudeSequence);
attitudeSequence.registerSwitchEvents(propagator);
SpacecraftState stateAfter = propagator.propagate(initialDate, initialDate.shiftedBy(1200));
SpacecraftState stateBefore = propagator.propagate(initialDate, initialDate.shiftedBy(-1200));
// Check that the dates are correct
Assert.assertEquals(1200, stateAfter.getDate().durationFrom(initialDate), 1.0E-3);
Assert.assertEquals(-1200, stateBefore.getDate().durationFrom(initialDate), 1.0E-3);
// Check that the attitudes are correct
Assert.assertEquals(before.getAttitude(stateBefore.getOrbit(), stateBefore.getDate(), stateBefore.getFrame()).getRotation().getQ0(),
stateBefore.getAttitude().getRotation().getQ0(),
1.0E-16);
stateBefore.getAttitude().getRotation().getQ0(),
1.0E-16);
Assert.assertEquals(before.getAttitude(stateBefore.getOrbit(), stateBefore.getDate(), stateBefore.getFrame()).getRotation().getQ1(),
stateBefore.getAttitude().getRotation().getQ1(),
1.0E-16);
stateBefore.getAttitude().getRotation().getQ1(),
1.0E-16);
Assert.assertEquals(before.getAttitude(stateBefore.getOrbit(), stateBefore.getDate(), stateBefore.getFrame()).getRotation().getQ2(),
stateBefore.getAttitude().getRotation().getQ2(),
1.0E-16);
stateBefore.getAttitude().getRotation().getQ2(),
1.0E-16);
Assert.assertEquals(before.getAttitude(stateBefore.getOrbit(), stateBefore.getDate(), stateBefore.getFrame()).getRotation().getQ3(),
stateBefore.getAttitude().getRotation().getQ3(),
1.0E-16);
stateBefore.getAttitude().getRotation().getQ3(),
1.0E-16);
Assert.assertEquals(after.getAttitude(stateAfter.getOrbit(), stateAfter.getDate(), stateAfter.getFrame()).getRotation().getQ0(),
stateAfter.getAttitude().getRotation().getQ0(),
1.0E-16);
stateAfter.getAttitude().getRotation().getQ0(),
1.0E-16);
Assert.assertEquals(after.getAttitude(stateAfter.getOrbit(), stateAfter.getDate(), stateAfter.getFrame()).getRotation().getQ1(),
stateAfter.getAttitude().getRotation().getQ1(),
1.0E-16);
stateAfter.getAttitude().getRotation().getQ1(),
1.0E-16);
Assert.assertEquals(after.getAttitude(stateAfter.getOrbit(), stateAfter.getDate(), stateAfter.getFrame()).getRotation().getQ2(),
stateAfter.getAttitude().getRotation().getQ2(),
1.0E-16);
stateAfter.getAttitude().getRotation().getQ2(),
1.0E-16);
Assert.assertEquals(after.getAttitude(stateAfter.getOrbit(), stateAfter.getDate(), stateAfter.getFrame()).getRotation().getQ3(),
stateAfter.getAttitude().getRotation().getQ3(),
1.0E-16);
stateAfter.getAttitude().getRotation().getQ3(),
1.0E-16);
}
private static class Handler implements AttitudesSequence.SwitchHandler {
......
......@@ -225,7 +225,7 @@ public class LofOffsetPointingTest {
final TimeStampedPVCoordinates pvD = provider.getTargetPV(orbit, date, frame);
final TimeStampedFieldPVCoordinates<T> pvF = provider.getTargetPV(orbitF, dateF, frame);
Assert.assertEquals(0.0, Vector3D.distance(pvD.getPosition(), pvF.getPosition().toVector3D()), 6.0e-9);
Assert.assertEquals(0.0, Vector3D.distance(pvD.getVelocity(), pvF.getVelocity().toVector3D()), 5.0e-13);
Assert.assertEquals(0.0, Vector3D.distance(pvD.getAcceleration(), pvF.getAcceleration().toVector3D()), 2.0e-6);
......
......@@ -25,32 +25,32 @@ import org.orekit.time.TimeScale;
import org.orekit.time.TimeScalesFactory;
public class CR3BPFactoryTest {
@Test
public void getSunJupiterCR3BP() {
AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
TimeScale timeScale = TimeScalesFactory.getUTC();
CR3BPSystem sunJupiterCR3BP = CR3BPFactory.getSunJupiterCR3BP(date, timeScale);
Assert.assertNotNull(sunJupiterCR3BP);
CR3BPSystem sunJupiterCR3BP = CR3BPFactory.getSunJupiterCR3BP(date, timeScale);
Assert.assertNotNull(sunJupiterCR3BP);
}
@Test
public void getEarthMoonCR3BP() {
CR3BPSystem earthMoonCR3BP = CR3BPFactory.getEarthMoonCR3BP();
Assert.assertNotNull(earthMoonCR3BP);
CR3BPSystem earthMoonCR3BP = CR3BPFactory.getEarthMoonCR3BP();
Assert.assertNotNull(earthMoonCR3BP);
}
@Test
public void getSunEarthCR3BP() {
AbsoluteDate date = AbsoluteDate.J2000_EPOCH;
TimeScale timeScale = TimeScalesFactory.getUTC();
CR3BPSystem sunEarthCR3BP = CR3BPFactory.getSunEarthCR3BP(date, timeScale);
Assert.assertNotNull(sunEarthCR3BP);
CR3BPSystem sunEarthCR3BP = CR3BPFactory.getSunEarthCR3BP(date, timeScale);
Assert.assertNotNull(sunEarthCR3BP);
}
@Before
public void setUp() {
Utils.setDataRoot("regular-data");
Utils.setDataRoot("regular-data");
}
}
......@@ -36,130 +36,130 @@ public class CR3BPSystemTest {
@Before
public void setUp() {
Utils.setDataRoot("cr3bp:regular-data");
Utils.setDataRoot("cr3bp:regular-data");
}
@Test
public void testCR3BPSystem() {