use of org.orekit.attitudes.BodyCenterPointing in project Orekit by CS-SI.
the class FieldSpacecraftStateTest method doTestShiftVsEcksteinHechlerError.
private <T extends RealFieldElement<T>> void doTestShiftVsEcksteinHechlerError(final Field<T> field) throws OrekitException {
T zero = field.getZero();
T mass = zero.add(2500.);
T a = zero.add(rOrbit.getA());
T e = zero.add(rOrbit.getE());
T i = zero.add(rOrbit.getI());
T pa = zero.add(1.9674147913622104);
T raan = zero.add(FastMath.toRadians(261));
T lv = zero.add(0);
final double ae = 6.378137e6;
final double c20 = -1.08263e-3;
final double c30 = 2.54e-6;
final double c40 = 1.62e-6;
final double c50 = 2.3e-7;
final double c60 = -5.5e-7;
// polynomial models for interpolation error in position, velocity, acceleration and attitude
// these models grow as follows
// interpolation time (s) position error (m) velocity error (m/s) acceleration error (m/s²) attitude error (°)
// 60 2 0.07 0.002 0.00002
// 120 12 0.3 0.005 0.00009
// 300 170 1.6 0.012 0.0009
// 600 1200 5.7 0.024 0.006
// 900 3600 10.6 0.034 0.02
// the expected maximum residuals with respect to these models are about 0.4m, 0.5mm/s, 8μm/s² and 3e-6°
PolynomialFunction pModel = new PolynomialFunction(new double[] { 1.5664070631933846e-01, 7.5504722733047560e-03, -8.2460562451009510e-05, 6.9546332080305580e-06, -1.7045365367533077e-09, -4.2187860791066264e-13 });
PolynomialFunction vModel = new PolynomialFunction(new double[] { -3.5472364019908720e-04, 1.6568103861124980e-05, 1.9637913327830596e-05, -3.4248792843039766e-09, -5.6565135131014254e-12, 1.4730170946808630e-15 });
PolynomialFunction aModel = new PolynomialFunction(new double[] { 3.0731707577766896e-06, 3.9770746399850350e-05, 1.9779039254538660e-09, 8.0263328220724900e-12, -1.5600835252366078e-14, 1.1785257001549687e-18 });
PolynomialFunction rModel = new PolynomialFunction(new double[] { -2.7689062063188115e-06, 1.7406542538258334e-07, 2.5109795349592287e-09, 2.0399322661074575e-11, 9.9126348912426750e-15, -3.5015638905729510e-18 });
FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, new DateComponents(2004, 01, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(a, e, i, pa, raan, lv, PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
BodyCenterPointing attitudeLaw = new BodyCenterPointing(orbit.getFrame(), earth);
FieldPropagator<T> propagator = new FieldEcksteinHechlerPropagator<>(orbit, attitudeLaw, mass, ae, mu, c20, c30, c40, c50, c60);
FieldAbsoluteDate<T> centerDate = orbit.getDate().shiftedBy(100.0);
FieldSpacecraftState<T> centerState = propagator.propagate(centerDate);
double maxResidualP = 0;
double maxResidualV = 0;
double maxResidualA = 0;
double maxResidualR = 0;
for (T dt = field.getZero(); dt.getReal() < 900.0; dt = dt.add(5)) {
FieldSpacecraftState<T> shifted = centerState.shiftedBy(dt);
FieldSpacecraftState<T> propagated = propagator.propagate(centerDate.shiftedBy(dt));
FieldPVCoordinates<T> dpv = new FieldPVCoordinates<>(propagated.getPVCoordinates(), shifted.getPVCoordinates());
double residualP = pModel.value(dt.getReal()) - dpv.getPosition().getNorm().getReal();
double residualV = vModel.value(dt.getReal()) - dpv.getVelocity().getNorm().getReal();
double residualA = aModel.value(dt.getReal()) - dpv.getAcceleration().getNorm().getReal();
double residualR = rModel.value(dt.getReal()) - FastMath.toDegrees(FieldRotation.distance(shifted.getAttitude().getRotation(), propagated.getAttitude().getRotation()).getReal());
maxResidualP = FastMath.max(maxResidualP, FastMath.abs(residualP));
maxResidualV = FastMath.max(maxResidualV, FastMath.abs(residualV));
maxResidualA = FastMath.max(maxResidualA, FastMath.abs(residualA));
maxResidualR = FastMath.max(maxResidualR, FastMath.abs(residualR));
}
Assert.assertEquals(0.40, maxResidualP, 0.01);
Assert.assertEquals(4.9e-4, maxResidualV, 1.0e-5);
Assert.assertEquals(2.8e-6, maxResidualR, 1.0e-1);
}
use of org.orekit.attitudes.BodyCenterPointing in project Orekit by CS-SI.
the class FieldSpacecraftStateTest method doTestTransform.
private <T extends RealFieldElement<T>> void doTestTransform(final Field<T> field) throws OrekitException {
T zero = field.getZero();
T a = zero.add(rOrbit.getA());
T e = zero.add(rOrbit.getE());
T i = zero.add(rOrbit.getI());
T pa = zero.add(1.9674147913622104);
T raan = zero.add(FastMath.toRadians(261));
T lv = zero.add(0);
T mass = zero.add(2500);
FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, new DateComponents(2004, 01, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(a, e, i, pa, raan, lv, PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
BodyCenterPointing attitudeLaw = new BodyCenterPointing(orbit.getFrame(), earth);
FieldKeplerianPropagator<T> propagator = new FieldKeplerianPropagator<>(orbit, attitudeLaw, mu, mass);
double maxDP = 0;
double maxDV = 0;
double maxDA = 0;
for (double t = 0; t < orbit.getKeplerianPeriod().getReal(); t += 60) {
final FieldSpacecraftState<T> state = propagator.propagate(orbit.getDate().shiftedBy(zero.add(t)));
final Transform transform = state.toSpacecraftState().toTransform().getInverse();
PVCoordinates pv = transform.transformPVCoordinates(PVCoordinates.ZERO);
PVCoordinates dPV = new PVCoordinates(pv, state.getPVCoordinates().toPVCoordinates());
Vector3D mZDirection = transform.transformVector(Vector3D.MINUS_K);
double alpha = Vector3D.angle(mZDirection, state.getPVCoordinates().toPVCoordinates().getPosition());
maxDP = FastMath.max(maxDP, dPV.getPosition().getNorm());
maxDV = FastMath.max(maxDV, dPV.getVelocity().getNorm());
maxDA = FastMath.max(maxDA, FastMath.toDegrees(alpha));
}
Assert.assertEquals(0.0, maxDP, 1.0e-6);
Assert.assertEquals(0.0, maxDV, 1.0e-9);
Assert.assertEquals(0.0, maxDA, 1.0e-12);
}
use of org.orekit.attitudes.BodyCenterPointing in project Orekit by CS-SI.
the class FieldSpacecraftStateTest method doTestAdditionalStates.
private <T extends RealFieldElement<T>> void doTestAdditionalStates(final Field<T> field) throws OrekitException {
T zero = field.getZero();
T a = zero.add(rOrbit.getA());
T e = zero.add(rOrbit.getE());
T i = zero.add(rOrbit.getI());
T pa = zero.add(1.9674147913622104);
T raan = zero.add(FastMath.toRadians(261));
T lv = zero.add(0);
T mass = zero.add(2500);
FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, new DateComponents(2004, 01, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(a, e, i, pa, raan, lv, PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
BodyCenterPointing attitudeLaw = new BodyCenterPointing(orbit.getFrame(), earth);
FieldKeplerianPropagator<T> propagator = new FieldKeplerianPropagator<>(orbit, attitudeLaw, mu, mass);
final FieldSpacecraftState<T> state = propagator.propagate(orbit.getDate().shiftedBy(60));
T[] add = MathArrays.buildArray(field, 2);
add[0] = zero.add(1.);
add[1] = zero.add(2.);
final FieldSpacecraftState<T> extended = state.addAdditionalState("test-1", add).addAdditionalState("test-2", zero.add(42.0));
Assert.assertEquals(0, state.getAdditionalStates().size());
Assert.assertFalse(state.hasAdditionalState("test-1"));
try {
state.getAdditionalState("test-1");
Assert.fail("an exception should have been thrown");
} catch (OrekitException oe) {
Assert.assertEquals(oe.getSpecifier(), OrekitMessages.UNKNOWN_ADDITIONAL_STATE);
Assert.assertEquals(oe.getParts()[0], "test-1");
}
try {
state.ensureCompatibleAdditionalStates(extended);
Assert.fail("an exception should have been thrown");
} catch (OrekitException oe) {
Assert.assertEquals(oe.getSpecifier(), OrekitMessages.UNKNOWN_ADDITIONAL_STATE);
Assert.assertTrue(oe.getParts()[0].toString().startsWith("test-"));
}
try {
extended.ensureCompatibleAdditionalStates(state);
Assert.fail("an exception should have been thrown");
} catch (OrekitException oe) {
Assert.assertEquals(oe.getSpecifier(), OrekitMessages.UNKNOWN_ADDITIONAL_STATE);
Assert.assertTrue(oe.getParts()[0].toString().startsWith("test-"));
}
try {
T[] kk = MathArrays.buildArray(field, 7);
extended.ensureCompatibleAdditionalStates(extended.addAdditionalState("test-2", kk));
Assert.fail("an exception should have been thrown");
} catch (MathIllegalStateException mise) {
Assert.assertEquals(LocalizedCoreFormats.DIMENSIONS_MISMATCH, mise.getSpecifier());
Assert.assertEquals(7, ((Integer) mise.getParts()[0]).intValue());
}
Assert.assertEquals(2, extended.getAdditionalStates().size());
Assert.assertTrue(extended.hasAdditionalState("test-1"));
Assert.assertTrue(extended.hasAdditionalState("test-2"));
Assert.assertEquals(1.0, extended.getAdditionalState("test-1")[0].getReal(), 1.0e-15);
Assert.assertEquals(2.0, extended.getAdditionalState("test-1")[1].getReal(), 1.0e-15);
Assert.assertEquals(42.0, extended.getAdditionalState("test-2")[0].getReal(), 1.0e-15);
// test various constructors
T[] dd = MathArrays.buildArray(field, 1);
dd[0] = zero.add(-6.0);
Map<String, T[]> map = new HashMap<String, T[]>();
map.put("test-3", dd);
FieldSpacecraftState<T> sO = new FieldSpacecraftState<>(state.getOrbit(), map);
Assert.assertEquals(-6.0, sO.getAdditionalState("test-3")[0].getReal(), 1.0e-15);
FieldSpacecraftState<T> sOA = new FieldSpacecraftState<>(state.getOrbit(), state.getAttitude(), map);
Assert.assertEquals(-6.0, sOA.getAdditionalState("test-3")[0].getReal(), 1.0e-15);
FieldSpacecraftState<T> sOM = new FieldSpacecraftState<>(state.getOrbit(), state.getMass(), map);
Assert.assertEquals(-6.0, sOM.getAdditionalState("test-3")[0].getReal(), 1.0e-15);
FieldSpacecraftState<T> sOAM = new FieldSpacecraftState<>(state.getOrbit(), state.getAttitude(), state.getMass(), map);
Assert.assertEquals(-6.0, sOAM.getAdditionalState("test-3")[0].getReal(), 1.0e-15);
FieldSpacecraftState<T> sFromDouble = new FieldSpacecraftState<>(field, sOAM.toSpacecraftState());
Assert.assertEquals(-6.0, sFromDouble.getAdditionalState("test-3")[0].getReal(), 1.0e-15);
}
use of org.orekit.attitudes.BodyCenterPointing in project Orekit by CS-SI.
the class FieldSpacecraftStateTest method doTestDatesConsistency.
private <T extends RealFieldElement<T>> void doTestDatesConsistency(final Field<T> field) throws OrekitException {
T zero = field.getZero();
T a = zero.add(rOrbit.getA());
T e = zero.add(rOrbit.getE());
T i = zero.add(rOrbit.getI());
T pa = zero.add(1.9674147913622104);
T raan = zero.add(FastMath.toRadians(261));
T lv = zero.add(0);
FieldAbsoluteDate<T> date = new FieldAbsoluteDate<>(field, new DateComponents(2004, 01, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
FieldKeplerianOrbit<T> orbit = new FieldKeplerianOrbit<>(a, e, i, pa, raan, lv, PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
BodyCenterPointing attitudeLaw = new BodyCenterPointing(orbit.getFrame(), earth);
new FieldSpacecraftState<>(orbit, attitudeLaw.getAttitude(orbit.shiftedBy(zero.add(10.0)), orbit.getDate().shiftedBy(10.0), orbit.getFrame()));
}
use of org.orekit.attitudes.BodyCenterPointing in project Orekit by CS-SI.
the class SpacecraftStateTest method setUp.
@Before
public void setUp() {
try {
Utils.setDataRoot("regular-data");
double mu = 3.9860047e14;
double ae = 6.378137e6;
double c20 = -1.08263e-3;
double c30 = 2.54e-6;
double c40 = 1.62e-6;
double c50 = 2.3e-7;
double c60 = -5.5e-7;
mass = 2500;
double a = 7187990.1979844316;
double e = 0.5e-4;
double i = 1.7105407051081795;
double omega = 1.9674147913622104;
double OMEGA = FastMath.toRadians(261);
double lv = 0;
AbsoluteDate date = new AbsoluteDate(new DateComponents(2004, 01, 01), TimeComponents.H00, TimeScalesFactory.getUTC());
orbit = new KeplerianOrbit(a, e, i, omega, OMEGA, lv, PositionAngle.TRUE, FramesFactory.getEME2000(), date, mu);
OneAxisEllipsoid earth = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, FramesFactory.getITRF(IERSConventions.IERS_2010, true));
attitudeLaw = new BodyCenterPointing(orbit.getFrame(), earth);
propagator = new EcksteinHechlerPropagator(orbit, attitudeLaw, mass, ae, mu, c20, c30, c40, c50, c60);
} catch (OrekitException oe) {
Assert.fail(oe.getLocalizedMessage());
}
}
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