diff --git a/src/changes/changes.xml b/src/changes/changes.xml
index 381c47c7ecffc8f77cb5b8df3918b6bc1b54d2e6..1cedfe1a28156002a80b80fc6b3f1f76228702e6 100644
--- a/src/changes/changes.xml
+++ b/src/changes/changes.xml
@@ -21,6 +21,10 @@
</properties>
<body>
<release version="10.0" date="TBD" description="TBD">
+ <action dev="maxime" type="fix" issue="514">
+ Deprecated unused DerivativeStructure acceleration computation methods.
+ In interfaces radiationPressureAcceleration and dragAcceleration, and all their implementations and their tests.
+ </action>
<action dev="luc" type="add" issue="536">
Take target radius into account in CircularFieldOfViewDetector and FieldOfViewDetector.
</action>
diff --git a/src/main/java/org/orekit/forces/BoxAndSolarArraySpacecraft.java b/src/main/java/org/orekit/forces/BoxAndSolarArraySpacecraft.java
index 1f43683aef73283acd60c69a0807c8b414ae49a4..761faa335a7f8d1b2d9f74ffb64128674dad4bb2 100644
--- a/src/main/java/org/orekit/forces/BoxAndSolarArraySpacecraft.java
+++ b/src/main/java/org/orekit/forces/BoxAndSolarArraySpacecraft.java
@@ -123,7 +123,10 @@ public class BoxAndSolarArraySpacecraft implements RadiationSensitive, DragSensi
/** Sun model. */
private final PVCoordinatesProvider sun;
- /** Factory for the DerivativeStructure instances. */
+ /** Factory for the DerivativeStructure instances.
+ * @deprecated Attribute not used anymore, should have been deleted in 9.0 but was left over. To be deleted in the next major version.
+ */
+ @Deprecated
private final DSFactory factory;
/** Build a spacecraft model with best lighting of solar array.
@@ -697,7 +700,9 @@ public class BoxAndSolarArraySpacecraft implements RadiationSensitive, DragSensi
* @param position position of spacecraft in reference frame
* @param rotation orientation (attitude) of the spacecraft with respect to reference frame
* @return solar array normal in spacecraft frame
+ * @deprecated Method not used anymore, should have been deleted in 9.0 but was left over. To be deleted in the next major version.
*/
+ @Deprecated
public synchronized FieldVector3D<DerivativeStructure> getNormal(final AbsoluteDate date, final Frame frame,
final FieldVector3D<DerivativeStructure> position,
final FieldRotation<DerivativeStructure> rotation) {
@@ -772,6 +777,7 @@ public class BoxAndSolarArraySpacecraft implements RadiationSensitive, DragSensi
/** {@inheritDoc} */
@Override
+ @Deprecated
public FieldVector3D<DerivativeStructure> dragAcceleration(final AbsoluteDate date, final Frame frame,
final Vector3D position, final Rotation rotation,
final double mass, final double density,
@@ -877,6 +883,7 @@ public class BoxAndSolarArraySpacecraft implements RadiationSensitive, DragSensi
/** {@inheritDoc} */
@Override
+ @Deprecated
public FieldVector3D<DerivativeStructure> radiationPressureAcceleration(final AbsoluteDate date, final Frame frame,
final Vector3D position, final Rotation rotation,
final double mass, final Vector3D flux,
@@ -1095,7 +1102,9 @@ public class BoxAndSolarArraySpacecraft implements RadiationSensitive, DragSensi
* @param specularReflectionCoeffDS specular reflection coefficient
* @param diffuseReflectionCoeffDS diffuse reflection coefficient
* @return contribution of the facet to force in spacecraft frame
+ * @deprecated Method not used anymore, should have been deleted in 9.0 but was left over. To be deleted in the next major version.
*/
+ @Deprecated
private FieldVector3D<DerivativeStructure> facetRadiationAcceleration(final Vector3D normal, final double area,
final Vector3D fluxSat, final double dot,
final DerivativeStructure specularReflectionCoeffDS,
diff --git a/src/main/java/org/orekit/forces/drag/DragSensitive.java b/src/main/java/org/orekit/forces/drag/DragSensitive.java
index ed3c3d0ac821267cd6686d445c05de139630e880..4a030a39b49d7d48f9aff21ccd0b84555fb16215 100644
--- a/src/main/java/org/orekit/forces/drag/DragSensitive.java
+++ b/src/main/java/org/orekit/forces/drag/DragSensitive.java
@@ -113,7 +113,9 @@ public interface DragSensitive {
* @param parameters values of the force model parameters
* @param paramName name of the parameter with respect to which derivatives are required
* @return spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)
+ * @deprecated Method not used anymore, should have been deleted in 9.0 but was left over. To be deleted in the next major version.
*/
+ @Deprecated
FieldVector3D<DerivativeStructure> dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position,
Rotation rotation, double mass,
double density, Vector3D relativeVelocity,
diff --git a/src/main/java/org/orekit/forces/drag/IsotropicDrag.java b/src/main/java/org/orekit/forces/drag/IsotropicDrag.java
index 2fd87a90deb03ce9ac870426381fa9b90103aa51..4c08abb9510672fa09c5015c4f7f2b200707bb2e 100644
--- a/src/main/java/org/orekit/forces/drag/IsotropicDrag.java
+++ b/src/main/java/org/orekit/forces/drag/IsotropicDrag.java
@@ -124,6 +124,7 @@ public class IsotropicDrag implements DragSensitive {
/** {@inheritDoc} */
@Override
+ @Deprecated
public FieldVector3D<DerivativeStructure> dragAcceleration(final AbsoluteDate date, final Frame frame, final Vector3D position,
final Rotation rotation, final double mass,
final double density, final Vector3D relativeVelocity,
diff --git a/src/main/java/org/orekit/forces/radiation/IsotropicRadiationCNES95Convention.java b/src/main/java/org/orekit/forces/radiation/IsotropicRadiationCNES95Convention.java
index 6dca8b7a9caffbe3c9736536d68ebb38d6825993..4212b931a7c47d8e8f5dd1311058f0904f896b65 100644
--- a/src/main/java/org/orekit/forces/radiation/IsotropicRadiationCNES95Convention.java
+++ b/src/main/java/org/orekit/forces/radiation/IsotropicRadiationCNES95Convention.java
@@ -137,6 +137,7 @@ public class IsotropicRadiationCNES95Convention implements RadiationSensitive {
/** {@inheritDoc} */
@Override
+ @Deprecated
public FieldVector3D<DerivativeStructure> radiationPressureAcceleration(final AbsoluteDate date, final Frame frame, final Vector3D position,
final Rotation rotation, final double mass,
final Vector3D flux, final double[] parameters,
diff --git a/src/main/java/org/orekit/forces/radiation/IsotropicRadiationClassicalConvention.java b/src/main/java/org/orekit/forces/radiation/IsotropicRadiationClassicalConvention.java
index 28eb0eaaf37548f88e539e8283864ca9297c1c67..f1cac9a0d85bc5c2f47c9ed6d8c9b368a3dc03aa 100644
--- a/src/main/java/org/orekit/forces/radiation/IsotropicRadiationClassicalConvention.java
+++ b/src/main/java/org/orekit/forces/radiation/IsotropicRadiationClassicalConvention.java
@@ -125,6 +125,7 @@ public class IsotropicRadiationClassicalConvention implements RadiationSensitive
/** {@inheritDoc} */
@Override
+ @Deprecated
public FieldVector3D<DerivativeStructure> radiationPressureAcceleration(final AbsoluteDate date, final Frame frame, final Vector3D position,
final Rotation rotation, final double mass,
final Vector3D flux, final double[] parameters,
diff --git a/src/main/java/org/orekit/forces/radiation/IsotropicRadiationSingleCoefficient.java b/src/main/java/org/orekit/forces/radiation/IsotropicRadiationSingleCoefficient.java
index 0c69e2c8bb6277fa91b666b609a40a496b963634..4a62427961b22a1ee52dfef61b13bfe6ec848993 100644
--- a/src/main/java/org/orekit/forces/radiation/IsotropicRadiationSingleCoefficient.java
+++ b/src/main/java/org/orekit/forces/radiation/IsotropicRadiationSingleCoefficient.java
@@ -126,6 +126,7 @@ public class IsotropicRadiationSingleCoefficient implements RadiationSensitive {
/** {@inheritDoc} */
@Override
+ @Deprecated
public FieldVector3D<DerivativeStructure> radiationPressureAcceleration(final AbsoluteDate date, final Frame frame, final Vector3D position,
final Rotation rotation, final double mass,
final Vector3D flux, final double[] parameters,
diff --git a/src/main/java/org/orekit/forces/radiation/RadiationSensitive.java b/src/main/java/org/orekit/forces/radiation/RadiationSensitive.java
index 615f9cbe4f51a18624664f844cb7de7b02759d81..8beb3465f25bfe3fe7db5038736498befe8399e4 100644
--- a/src/main/java/org/orekit/forces/radiation/RadiationSensitive.java
+++ b/src/main/java/org/orekit/forces/radiation/RadiationSensitive.java
@@ -86,7 +86,9 @@ public interface RadiationSensitive {
* @param parameters values of the force model parameters
* @param paramName name of the parameter with respect to which derivatives are required
* @return spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)
+ * @deprecated Method not used anymore, should have been deleted in 9.0 but was left over. To be deleted in the next major version.
*/
+ @Deprecated
FieldVector3D<DerivativeStructure> radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position,
Rotation rotation, double mass, Vector3D flux,
double[] parameters,
diff --git a/src/test/java/org/orekit/forces/BoxAndSolarArraySpacecraftTest.java b/src/test/java/org/orekit/forces/BoxAndSolarArraySpacecraftTest.java
index 3b61915e140d0e11508a596633990752b17f6837..b6435969e66776f618b2161e6f8c835ce96e6ff6 100644
--- a/src/test/java/org/orekit/forces/BoxAndSolarArraySpacecraftTest.java
+++ b/src/test/java/org/orekit/forces/BoxAndSolarArraySpacecraftTest.java
@@ -20,6 +20,7 @@ package org.orekit.forces;
import java.util.List;
import org.hipparchus.Field;
+import org.hipparchus.RealFieldElement;
import org.hipparchus.analysis.differentiation.DSFactory;
import org.hipparchus.analysis.differentiation.DerivativeStructure;
import org.hipparchus.geometry.euclidean.threed.FieldRotation;
@@ -29,6 +30,7 @@ import org.hipparchus.geometry.euclidean.threed.Vector3D;
import org.hipparchus.util.Decimal64;
import org.hipparchus.util.Decimal64Field;
import org.hipparchus.util.FastMath;
+import org.hipparchus.util.MathArrays;
import org.hipparchus.util.Precision;
import org.junit.Assert;
import org.junit.Before;
@@ -56,6 +58,7 @@ import org.orekit.time.DateComponents;
import org.orekit.time.FieldAbsoluteDate;
import org.orekit.time.TimeComponents;
import org.orekit.time.TimeScalesFactory;
+import org.orekit.utils.Constants;
import org.orekit.utils.ParameterDriver;
import org.orekit.utils.TimeStampedPVCoordinates;
@@ -524,6 +527,7 @@ public class BoxAndSolarArraySpacecraftTest {
}
@Test
+ @Deprecated
public void testWrongParameterDrag() {
SpacecraftState state = propagator.getInitialState();
CelestialBody sun = CelestialBodyFactory.getSun();
@@ -545,6 +549,7 @@ public class BoxAndSolarArraySpacecraftTest {
}
@Test
+ @Deprecated
public void testMissingParameterLift() {
SpacecraftState state = propagator.getInitialState();
CelestialBody sun = CelestialBodyFactory.getSun();
@@ -568,6 +573,7 @@ public class BoxAndSolarArraySpacecraftTest {
}
@Test
+ @Deprecated
public void testPresentParameterLift() {
SpacecraftState state = propagator.getInitialState();
CelestialBody sun = CelestialBodyFactory.getSun();
@@ -583,6 +589,7 @@ public class BoxAndSolarArraySpacecraftTest {
}
@Test
+ @Deprecated
public void testWrongParameterLift() {
SpacecraftState state = propagator.getInitialState();
CelestialBody sun = CelestialBodyFactory.getSun();
@@ -607,6 +614,7 @@ public class BoxAndSolarArraySpacecraftTest {
}
@Test
+ @Deprecated
public void testWrongParameterRadiation() {
SpacecraftState state = propagator.getInitialState();
CelestialBody sun = CelestialBodyFactory.getSun();
@@ -627,46 +635,61 @@ public class BoxAndSolarArraySpacecraftTest {
}
}
+ /** Test solar array radiation acceleration with zero flux. */
@Test
public void testNullIllumination() {
SpacecraftState state = propagator.getInitialState();
CelestialBody sun = CelestialBodyFactory.getSun();
BoxAndSolarArraySpacecraft s =
new BoxAndSolarArraySpacecraft(0, 0, 0, sun, 20.0, Vector3D.PLUS_J, 0.0, 1.0, 0.0);
- FieldVector3D<DerivativeStructure> a =
- s.radiationPressureAcceleration(state.getDate(), state.getFrame(),
- state.getPVCoordinates().getPosition(),
- state.getAttitude().getRotation(),
- state.getMass(), new Vector3D(Precision.SAFE_MIN / 2,
- Vector3D.PLUS_I),
- getRadiationParameters(s),
- RadiationSensitive.ABSORPTION_COEFFICIENT);
+
+ // "Field" the inputs using Decimal64
+ Field<Decimal64> field = Decimal64Field.getInstance();
+ Decimal64[] srpParam = getRadiationParameters(s, field);
+
+ FieldAbsoluteDate<Decimal64> date = new FieldAbsoluteDate<>(field, state.getDate());
+ FieldVector3D<Decimal64> position = new FieldVector3D<Decimal64>(field.getOne(), state.getPVCoordinates().getPosition());
+ FieldRotation<Decimal64> rotation = new FieldRotation<>(field, state.getAttitude().getRotation());
+ Decimal64 mass = new Decimal64(state.getMass());
+ FieldVector3D<Decimal64> flux = new FieldVector3D<Decimal64>(field.getOne(),
+ new Vector3D(Precision.SAFE_MIN / 2, Vector3D.PLUS_I));
+
+
+ FieldVector3D<Decimal64> a = s.radiationPressureAcceleration(date, state.getFrame(),
+ position, rotation, mass,
+ flux, srpParam);
Assert.assertEquals(0.0, a.getNorm().getReal(), Double.MIN_VALUE);
}
+ /** Test forward/backward acceleration due to solar array radiation pressure. */
@Test
public void testBackwardIllumination() {
SpacecraftState state = propagator.getInitialState();
CelestialBody sun = CelestialBodyFactory.getSun();
BoxAndSolarArraySpacecraft s =
new BoxAndSolarArraySpacecraft(0, 0, 0, sun, 20.0, Vector3D.PLUS_J, 0.0, 1.0, 0.0);
- Vector3D n = s.getNormal(state.getDate(), state.getFrame(),
- state.getPVCoordinates().getPosition(),
- state.getAttitude().getRotation());
- FieldVector3D<DerivativeStructure> aPlus =
- s.radiationPressureAcceleration(state.getDate(), state.getFrame(),
- state.getPVCoordinates().getPosition(),
- state.getAttitude().getRotation(),
- state.getMass(), n,
- getRadiationParameters(s),
- RadiationSensitive.ABSORPTION_COEFFICIENT);
- FieldVector3D<DerivativeStructure> aMinus =
- s.radiationPressureAcceleration(state.getDate(), state.getFrame(),
- state.getPVCoordinates().getPosition(),
- state.getAttitude().getRotation(),
- state.getMass(), n.negate(),
- getRadiationParameters(s),
- RadiationSensitive.ABSORPTION_COEFFICIENT);
+
+ // "Field" the inputs using Decimal64
+ Field<Decimal64> field = Decimal64Field.getInstance();
+ Decimal64[] srpParam = getRadiationParameters(s, field);
+
+ FieldAbsoluteDate<Decimal64> date = new FieldAbsoluteDate<>(field, state.getDate());
+ FieldVector3D<Decimal64> position = new FieldVector3D<Decimal64>(field.getOne(), state.getPVCoordinates().getPosition());
+ FieldRotation<Decimal64> rotation = new FieldRotation<>(field, state.getAttitude().getRotation());
+ Decimal64 mass = new Decimal64(state.getMass());
+
+ // Flux equal to SA normal
+ FieldVector3D<Decimal64> flux = s.getNormal(date, state.getFrame(), position, rotation);
+
+ // Forward flux
+ FieldVector3D<Decimal64> aPlus = s.radiationPressureAcceleration(date, state.getFrame(),
+ position, rotation, mass,
+ flux, srpParam);
+ // Backward flux
+ FieldVector3D<Decimal64> aMinus = s.radiationPressureAcceleration(date, state.getFrame(),
+ position, rotation, mass,
+ flux.negate(), srpParam);
+
Assert.assertEquals(0.0, aPlus.add(aMinus).getNorm().getReal(), Double.MIN_VALUE);
}
@@ -705,6 +728,7 @@ public class BoxAndSolarArraySpacecraftTest {
}
@Test
+ @Deprecated
public void testNormalOptimalRotationDS() {
AbsoluteDate initialDate = propagator.getInitialState().getDate();
CelestialBody sun = CelestialBodyFactory.getSun();
@@ -761,6 +785,7 @@ public class BoxAndSolarArraySpacecraftTest {
}
@Test
+ @Deprecated
public void testNormalFixedRateDS() {
AbsoluteDate initialDate = propagator.getInitialState().getDate();
CelestialBody sun = CelestialBodyFactory.getSun();
@@ -806,6 +831,7 @@ public class BoxAndSolarArraySpacecraftTest {
}
@Test
+ @Deprecated
public void testNormalSunAlignedDS() {
BoxAndSolarArraySpacecraft s =
new BoxAndSolarArraySpacecraft(0, 0, 0,
@@ -818,7 +844,75 @@ public class BoxAndSolarArraySpacecraftTest {
FieldRotation.getIdentity(factory.getDerivativeField()));
Assert.assertEquals(0, FieldVector3D.dotProduct(normal, Vector3D.PLUS_J).getReal(), 1.0e-16);
}
+
+ /** Test the functions computing drag and SRP acceleration and giving FieldVector3D outputs.
+ * By comparing the "double" value with a "Decimal64" implementation.
+ */
+ @Test
+ public void testFieldAcceleration() {
+
+ AbsoluteDate initialDate = propagator.getInitialState().getDate();
+ CelestialBody sun = CelestialBodyFactory.getSun();
+
+ // Assuming simple Earth rotation model, constant density and flux
+ Vector3D earthRot = new Vector3D(0., 0., Constants.GRIM5C1_EARTH_ANGULAR_VELOCITY);
+ double density = 1.e-3;
+ double refFlux = 4.56e-6;
+
+
+ // Build a S/C box with non-nil coefficients so that the computation of the acceleration does not
+ // avoid any line of code
+ BoxAndSolarArraySpacecraft s =
+ new BoxAndSolarArraySpacecraft(1., 2., 3., sun, 20.0, Vector3D.PLUS_J, 2.0, 0.3, 0.5, 0.4);
+
+ for (double dt = 0; dt < 4000; dt += 60) {
+ AbsoluteDate date = initialDate.shiftedBy(dt);
+ SpacecraftState state = propagator.propagate(date);
+
+ // Data used in acceleration computation
+ Vector3D position = state.getPVCoordinates().getPosition();
+ Vector3D velocity = state.getPVCoordinates().getVelocity();
+ Vector3D vAtm = Vector3D.crossProduct(earthRot, position);
+ Vector3D relativeVelocity = vAtm.subtract(velocity);
+
+ Frame frame = state.getFrame();
+ Rotation rotation = state.getAttitude().getRotation();
+ double mass = state.getMass();
+ Vector3D flux = position.subtract(sun.getPVCoordinates(date, frame).getPosition()).normalize().scalarMultiply(refFlux);
+
+ // Acceleration in double
+ Vector3D aDrag = s.dragAcceleration(date, frame, position, rotation, mass,
+ density, relativeVelocity,
+ getDragParameters(s));
+ Vector3D aSrp = s.radiationPressureAcceleration(date, frame, position, rotation, mass,
+ flux, getRadiationParameters(s));
+
+ // "Field" the inputs using Decimal64
+ Field<Decimal64> field = Decimal64Field.getInstance();
+
+ FieldAbsoluteDate<Decimal64> dateF = new FieldAbsoluteDate<>(field, date);
+ FieldVector3D<Decimal64> positionF = new FieldVector3D<Decimal64>(field.getOne(), position);
+ FieldRotation<Decimal64> rotationF = new FieldRotation<>(field, rotation);
+ Decimal64 massF = new Decimal64(mass);
+ FieldVector3D<Decimal64> fluxF = new FieldVector3D<Decimal64>(field.getOne(), flux);
+ Decimal64 densityF = new Decimal64(density);
+ FieldVector3D<Decimal64> relativeVelocityF = new FieldVector3D<Decimal64>(field.getOne(), relativeVelocity);
+
+
+ // Acceleration in Decimal64
+ FieldVector3D<Decimal64> aDragF = s.dragAcceleration(dateF, frame,
+ positionF, rotationF, massF, densityF,
+ relativeVelocityF, getDragParameters(s, field));
+ FieldVector3D<Decimal64> aSrpF = s.radiationPressureAcceleration(dateF, frame,
+ positionF, rotationF, massF,
+ fluxF, getRadiationParameters(s, field));
+ // Compare double and Decimal64 accelerations
+ Assert.assertEquals(0.0, Vector3D.distance(aDrag, aDragF.toVector3D()), Precision.EPSILON);
+ Assert.assertEquals(0.0, Vector3D.distance(aSrp, aSrpF.toVector3D()), Precision.EPSILON);
+ }
+ }
+ /** Get drag parameters as double[]. */
private double[] getDragParameters(final BoxAndSolarArraySpacecraft basa) {
final ParameterDriver[] drivers = basa.getDragParametersDrivers();
final double[] parameters = new double[drivers.length];
@@ -828,6 +922,7 @@ public class BoxAndSolarArraySpacecraftTest {
return parameters;
}
+ /** Get radiation parameters as double[]. */
private double[] getRadiationParameters(final BoxAndSolarArraySpacecraft basa) {
final ParameterDriver[] drivers = basa.getRadiationParametersDrivers();
final double[] parameters = new double[drivers.length];
@@ -836,6 +931,28 @@ public class BoxAndSolarArraySpacecraftTest {
}
return parameters;
}
+
+ /** Get drag parameters as field[]. */
+ private <T extends RealFieldElement<T>> T[] getDragParameters(final BoxAndSolarArraySpacecraft basa,
+ final Field<T> field) {
+ final ParameterDriver[] drivers = basa.getDragParametersDrivers();
+ final T[] parameters = MathArrays.buildArray(field, drivers.length);
+ for (int i = 0; i < drivers.length; ++i) {
+ parameters[i] = field.getZero().add(drivers[i].getValue());
+ }
+ return parameters;
+ }
+
+ /** Get radiation parameters as field[]. */
+ private <T extends RealFieldElement<T>> T[] getRadiationParameters(final BoxAndSolarArraySpacecraft basa,
+ final Field<T> field) {
+ final ParameterDriver[] drivers = basa.getRadiationParametersDrivers();
+ final T[] parameters = MathArrays.buildArray(field, drivers.length);
+ for (int i = 0; i < drivers.length; ++i) {
+ parameters[i] = field.getZero().add(drivers[i].getValue());
+ }
+ return parameters;
+ }
@Before
public void setUp() {
diff --git a/src/test/java/org/orekit/forces/radiation/SolarRadiationPressureTest.java b/src/test/java/org/orekit/forces/radiation/SolarRadiationPressureTest.java
index 5be799f9c49223ad6bddb1c71558144a6b71b606..12701886a95bb6d00187172856c3bc8cd1d7968f 100644
--- a/src/test/java/org/orekit/forces/radiation/SolarRadiationPressureTest.java
+++ b/src/test/java/org/orekit/forces/radiation/SolarRadiationPressureTest.java
@@ -201,6 +201,10 @@ public class SolarRadiationPressureTest extends AbstractLegacyForceModelTest {
Assert.assertTrue(3==count);
}
+ /** Test parameter derivatives with class IsotropicRadiationCNES95Convention.
+ * @deprecated remove code after FIXME in next major version
+ */
+ @Deprecated
@Test
public void testParameterDerivativeIsotropicSingle() {
@@ -236,7 +240,11 @@ public class SolarRadiationPressureTest extends AbstractLegacyForceModelTest {
}
}
+ /** Test parameter derivatives with class IsotropicRadiationClassicalConvention.
+ * @deprecated remove code after FIXME in next major version
+ */
@Test
+ @Deprecated
public void testParameterDerivativeIsotropicClassical() {
final Vector3D pos = new Vector3D(6.46885878304673824e+06, -1.88050918456274318e+06, -1.32931592294715829e+04);
@@ -255,6 +263,7 @@ public class SolarRadiationPressureTest extends AbstractLegacyForceModelTest {
checkParameterDerivative(state, forceModel, RadiationSensitive.ABSORPTION_COEFFICIENT, 0.25, 6.7e-16);
checkParameterDerivative(state, forceModel, RadiationSensitive.REFLECTION_COEFFICIENT, 0.25, 5.1e-16);
+ // FIXME: To remove
try {
rs.radiationPressureAcceleration(state.getDate(), state.getFrame(),
state.getPVCoordinates().getPosition(),
@@ -269,7 +278,11 @@ public class SolarRadiationPressureTest extends AbstractLegacyForceModelTest {
}
+ /** Test parameter derivatives with class IsotropicRadiationCNES95Convention.
+ * @deprecated remove code after FIXME in next major version
+ */
@Test
+ @Deprecated
public void testParameterDerivativeIsotropicCnes() {
final Vector3D pos = new Vector3D(6.46885878304673824e+06, -1.88050918456274318e+06, -1.32931592294715829e+04);
@@ -287,7 +300,8 @@ public class SolarRadiationPressureTest extends AbstractLegacyForceModelTest {
checkParameterDerivative(state, forceModel, RadiationSensitive.ABSORPTION_COEFFICIENT, 0.25, 2.5e-15);
checkParameterDerivative(state, forceModel, RadiationSensitive.REFLECTION_COEFFICIENT, 0.25, 2.0e-14);
-
+
+ // FIXME: To remove
try {
rs.radiationPressureAcceleration(state.getDate(), state.getFrame(),
state.getPVCoordinates().getPosition(),