/* Copyright 2002-2017 CS Systèmes d'Information
* Licensed to CS Systèmes d'Information (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.drag;
import java.util.List;
import org.hipparchus.Field;
import org.hipparchus.analysis.differentiation.DSFactory;
import org.hipparchus.analysis.differentiation.DerivativeStructure;
import org.hipparchus.geometry.euclidean.threed.FieldVector3D;
import org.hipparchus.geometry.euclidean.threed.Vector3D;
import org.hipparchus.ode.AbstractIntegrator;
import org.hipparchus.ode.nonstiff.AdaptiveStepsizeFieldIntegrator;
import org.hipparchus.ode.nonstiff.AdaptiveStepsizeIntegrator;
import org.hipparchus.ode.nonstiff.ClassicalRungeKuttaFieldIntegrator;
import org.hipparchus.ode.nonstiff.ClassicalRungeKuttaIntegrator;
import org.hipparchus.ode.nonstiff.DormandPrince853FieldIntegrator;
import org.hipparchus.ode.nonstiff.DormandPrince853Integrator;
import org.hipparchus.random.GaussianRandomGenerator;
import org.hipparchus.random.RandomGenerator;
import org.hipparchus.random.UncorrelatedRandomVectorGenerator;
import org.hipparchus.random.Well19937a;
import org.hipparchus.util.FastMath;
import org.junit.Assert;
import org.junit.Before;
import org.junit.Test;
import org.orekit.Utils;
import org.orekit.bodies.BodyShape;
import org.orekit.bodies.CelestialBodyFactory;
import org.orekit.bodies.OneAxisEllipsoid;
import org.orekit.errors.OrekitException;
import org.orekit.forces.AbstractForceModelTest;
import org.orekit.forces.BoxAndSolarArraySpacecraft;
import org.orekit.forces.drag.atmosphere.Atmosphere;
import org.orekit.forces.drag.atmosphere.HarrisPriester;
import org.orekit.forces.drag.atmosphere.SimpleExponentialAtmosphere;
import org.orekit.frames.Frame;
import org.orekit.frames.FramesFactory;
import org.orekit.orbits.CartesianOrbit;
import org.orekit.orbits.FieldKeplerianOrbit;
import org.orekit.orbits.KeplerianOrbit;
import org.orekit.orbits.Orbit;
import org.orekit.orbits.OrbitType;
import org.orekit.orbits.PositionAngle;
import org.orekit.propagation.FieldSpacecraftState;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.numerical.FieldNumericalPropagator;
import org.orekit.propagation.numerical.NumericalPropagator;
import org.orekit.propagation.numerical.PartialDerivativesEquations;
import org.orekit.time.AbsoluteDate;
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.FieldPVCoordinates;
import org.orekit.utils.IERSConventions;
import org.orekit.utils.PVCoordinates;
import org.orekit.utils.TimeStampedPVCoordinates;
public class DragForceTest extends AbstractForceModelTest {
@Test
@Deprecated
public void testDeprecatedMethods() throws OrekitException {
final DragSensitive ds = new IsotropicDrag(2.5, 1.2);
final List<String> names = ds.getDragParametersNames();
Assert.assertEquals(1, names.size());
Assert.assertEquals(DragSensitive.DRAG_COEFFICIENT, names.get(0));
Assert.assertEquals(1.2, ds.getDragCoefficient(), 1.0e-10);
ds.setDragCoefficient(10.0);
Assert.assertEquals(10.0, ds.getDragCoefficient(), 1.0e-10);
}
@Test
public void testParameterDerivativeSphere() throws OrekitException {
final Vector3D pos = new Vector3D(6.46885878304673824e+06, -1.88050918456274318e+06, -1.32931592294715829e+04);
final Vector3D vel = new Vector3D(2.14718074509906819e+03, 7.38239351251748485e+03, -1.14097953925384523e+01);
final SpacecraftState state =
new SpacecraftState(new CartesianOrbit(new PVCoordinates(pos, vel),
FramesFactory.getGCRF(),
new AbsoluteDate(2003, 3, 5, 0, 24, 0.0, TimeScalesFactory.getTAI()),
Constants.EIGEN5C_EARTH_MU));
final DragForce forceModel =
new DragForce(new HarrisPriester(CelestialBodyFactory.getSun(),
new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF(IERSConventions.IERS_2010, true))),
new IsotropicDrag(2.5, 1.2));
checkParameterDerivative(state, forceModel, DragSensitive.DRAG_COEFFICIENT, 1.0e-4, 2.0e-12);
}
@Test
public void testStateJacobianSphere()
throws OrekitException {
// initialization
AbsoluteDate date = new AbsoluteDate(new DateComponents(2003, 03, 01),
new TimeComponents(13, 59, 27.816),
TimeScalesFactory.getUTC());
double i = FastMath.toRadians(98.7);
double omega = FastMath.toRadians(93.0);
double OMEGA = FastMath.toRadians(15.0 * 22.5);
Orbit orbit = new KeplerianOrbit(7201009.7124401, 1e-3, i , omega, OMEGA,
0, PositionAngle.MEAN, FramesFactory.getEME2000(), date,
Constants.EIGEN5C_EARTH_MU);
OrbitType integrationType = OrbitType.CARTESIAN;
double[][] tolerances = NumericalPropagator.tolerances(0.01, orbit, integrationType);
NumericalPropagator propagator =
new NumericalPropagator(new DormandPrince853Integrator(1.0e-3, 120,
tolerances[0], tolerances[1]));
propagator.setOrbitType(integrationType);
final DragForce forceModel =
new DragForce(new HarrisPriester(CelestialBodyFactory.getSun(),
new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF(IERSConventions.IERS_2010, true))),
new IsotropicDrag(2.5, 1.2));
propagator.addForceModel(forceModel);
SpacecraftState state0 = new SpacecraftState(orbit);
checkStateJacobian(propagator, state0, date.shiftedBy(3.5 * 3600.0),
1e3, tolerances[0], 2.0e-8);
}
@Test
public void testParameterDerivativeBox() throws OrekitException {
final Vector3D pos = new Vector3D(6.46885878304673824e+06, -1.88050918456274318e+06, -1.32931592294715829e+04);
final Vector3D vel = new Vector3D(2.14718074509906819e+03, 7.38239351251748485e+03, -1.14097953925384523e+01);
final SpacecraftState state =
new SpacecraftState(new CartesianOrbit(new PVCoordinates(pos, vel),
FramesFactory.getGCRF(),
new AbsoluteDate(2003, 3, 5, 0, 24, 0.0, TimeScalesFactory.getTAI()),
Constants.EIGEN5C_EARTH_MU));
final DragForce forceModel =
new DragForce(new HarrisPriester(CelestialBodyFactory.getSun(),
new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF(IERSConventions.IERS_2010, true))),
new BoxAndSolarArraySpacecraft(1.5, 2.0, 1.8, CelestialBodyFactory.getSun(), 20.0,
Vector3D.PLUS_J, 1.2, 0.7, 0.2));
checkParameterDerivative(state, forceModel, DragSensitive.DRAG_COEFFICIENT, 1.0e-4, 2.0e-12);
}
@Test
public void testStateJacobianBox()
throws OrekitException {
// initialization
AbsoluteDate date = new AbsoluteDate(new DateComponents(2003, 03, 01),
new TimeComponents(13, 59, 27.816),
TimeScalesFactory.getUTC());
double i = FastMath.toRadians(98.7);
double omega = FastMath.toRadians(93.0);
double OMEGA = FastMath.toRadians(15.0 * 22.5);
Orbit orbit = new KeplerianOrbit(7201009.7124401, 1e-3, i , omega, OMEGA,
0, PositionAngle.MEAN, FramesFactory.getEME2000(), date,
Constants.EIGEN5C_EARTH_MU);
OrbitType integrationType = OrbitType.CARTESIAN;
double[][] tolerances = NumericalPropagator.tolerances(0.01, orbit, integrationType);
NumericalPropagator propagator =
new NumericalPropagator(new DormandPrince853Integrator(1.0e-3, 120,
tolerances[0], tolerances[1]));
propagator.setOrbitType(integrationType);
final DragForce forceModel =
new DragForce(new HarrisPriester(CelestialBodyFactory.getSun(),
new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF(IERSConventions.IERS_2010, true))),
new BoxAndSolarArraySpacecraft(1.5, 2.0, 1.8, CelestialBodyFactory.getSun(), 20.0,
Vector3D.PLUS_J, 1.2, 0.7, 0.2));
propagator.addForceModel(forceModel);
SpacecraftState state0 = new SpacecraftState(orbit);
checkStateJacobian(propagator, state0, date.shiftedBy(3.5 * 3600.0),
1e3, tolerances[0], 3.0e-8);
}
@Test
public void testIssue229() throws OrekitException {
AbsoluteDate initialDate = new AbsoluteDate(2004, 1, 1, 0, 0, 0., TimeScalesFactory.getUTC());
Frame frame = FramesFactory.getEME2000();
double rpe = 160.e3 + Constants.WGS84_EARTH_EQUATORIAL_RADIUS;
double rap = 2000.e3 + Constants.WGS84_EARTH_EQUATORIAL_RADIUS;
double inc = FastMath.toRadians(0.);
double aop = FastMath.toRadians(0.);
double raan = FastMath.toRadians(0.);
double mean = FastMath.toRadians(180.);
double mass = 100.;
KeplerianOrbit orbit = new KeplerianOrbit(0.5 * (rpe + rap), (rap - rpe) / (rpe + rap),
inc, aop, raan, mean, PositionAngle.MEAN,
frame, initialDate, Constants.EIGEN5C_EARTH_MU);
IsotropicDrag shape = new IsotropicDrag(10., 2.2);
Frame itrf = FramesFactory.getITRF(IERSConventions.IERS_2010, true);
BodyShape earthShape = new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS, Constants.WGS84_EARTH_FLATTENING, itrf);
Atmosphere atmosphere = new SimpleExponentialAtmosphere(earthShape, 2.6e-10, 200000, 26000);
double[][] tolerance = NumericalPropagator.tolerances(0.1, orbit, OrbitType.CARTESIAN);
AbstractIntegrator integrator = new DormandPrince853Integrator(1.0e-3, 300, tolerance[0], tolerance[1]);
NumericalPropagator propagator = new NumericalPropagator(integrator);
propagator.setOrbitType(OrbitType.CARTESIAN);
propagator.setMu(orbit.getMu());
propagator.addForceModel(new DragForce(atmosphere, shape));
PartialDerivativesEquations partials = new PartialDerivativesEquations("partials", propagator);
propagator.setInitialState(partials.setInitialJacobians(new SpacecraftState(orbit, mass), 6));
SpacecraftState state = propagator.propagate(new AbsoluteDate(2004, 1, 1, 1, 30, 0., TimeScalesFactory.getUTC()));
double delta = 0.1;
Orbit shifted = new CartesianOrbit(new TimeStampedPVCoordinates(orbit.getDate(),
orbit.getPVCoordinates().getPosition().add(new Vector3D(delta, 0, 0)),
orbit.getPVCoordinates().getVelocity()),
orbit.getFrame(), orbit.getMu());
propagator.setInitialState(partials.setInitialJacobians(new SpacecraftState(shifted, mass), 6));
SpacecraftState newState = propagator.propagate(new AbsoluteDate(2004, 1, 1, 1, 30, 0., TimeScalesFactory.getUTC()));
double[] dPVdX = new double[] {
(newState.getPVCoordinates().getPosition().getX() - state.getPVCoordinates().getPosition().getX()) / delta,
(newState.getPVCoordinates().getPosition().getY() - state.getPVCoordinates().getPosition().getY()) / delta,
(newState.getPVCoordinates().getPosition().getZ() - state.getPVCoordinates().getPosition().getZ()) / delta,
(newState.getPVCoordinates().getVelocity().getX() - state.getPVCoordinates().getVelocity().getX()) / delta,
(newState.getPVCoordinates().getVelocity().getY() - state.getPVCoordinates().getVelocity().getY()) / delta,
(newState.getPVCoordinates().getVelocity().getZ() - state.getPVCoordinates().getVelocity().getZ()) / delta,
};
double[][] dYdY0 = new double[6][6];
partials.getMapper().getStateJacobian(state, dYdY0);
for (int i = 0; i < 6; ++i) {
Assert.assertEquals(dPVdX[i], dYdY0[i][0], 6.2e-6 * FastMath.abs(dPVdX[i]));
}
}
/**Testing if the propagation between the FieldPropagation and the propagation
* is equivalent.
* Also testing if propagating X+dX with the propagation is equivalent to
* propagation X with the FieldPropagation and then applying the taylor
* expansion of dX to the result.*/
@Test
public void RealFieldTest() throws OrekitException {
DSFactory factory = new DSFactory(6, 4);
DerivativeStructure a_0 = factory.variable(0, 7e6);
DerivativeStructure e_0 = factory.variable(1, 0.01);
DerivativeStructure i_0 = factory.variable(2, 1.2);
DerivativeStructure R_0 = factory.variable(3, 0.7);
DerivativeStructure O_0 = factory.variable(4, 0.5);
DerivativeStructure n_0 = factory.variable(5, 0.1);
Field<DerivativeStructure> field = a_0.getField();
DerivativeStructure zero = field.getZero();
FieldAbsoluteDate<DerivativeStructure> J2000 = new FieldAbsoluteDate<DerivativeStructure>(field);
Frame EME = FramesFactory.getEME2000();
FieldKeplerianOrbit<DerivativeStructure> FKO = new FieldKeplerianOrbit<DerivativeStructure>(a_0, e_0, i_0, R_0, O_0, n_0,
PositionAngle.MEAN,
EME,
J2000,
Constants.EIGEN5C_EARTH_MU);
FieldSpacecraftState<DerivativeStructure> initialState = new FieldSpacecraftState<DerivativeStructure>(FKO);
SpacecraftState iSR = initialState.toSpacecraftState();
ClassicalRungeKuttaFieldIntegrator<DerivativeStructure> integrator =
new ClassicalRungeKuttaFieldIntegrator<DerivativeStructure>(field, zero.add(6));
ClassicalRungeKuttaIntegrator RIntegrator =
new ClassicalRungeKuttaIntegrator(6);
OrbitType type = OrbitType.EQUINOCTIAL;
FieldNumericalPropagator<DerivativeStructure> FNP = new FieldNumericalPropagator<>(field, integrator);
FNP.setOrbitType(type);
FNP.setInitialState(initialState);
NumericalPropagator NP = new NumericalPropagator(RIntegrator);
NP.setOrbitType(type);
NP.setInitialState(iSR);
final DragForce forceModel =
new DragForce(new HarrisPriester(CelestialBodyFactory.getSun(),
new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF(IERSConventions.IERS_2010, true))),
new BoxAndSolarArraySpacecraft(1.5, 2.0, 1.8, CelestialBodyFactory.getSun(), 20.0,
Vector3D.PLUS_J, 1.2, 0.7, 0.2));
FNP.addForceModel(forceModel);
NP.addForceModel(forceModel);
FieldAbsoluteDate<DerivativeStructure> target = J2000.shiftedBy(10000.);
FieldSpacecraftState<DerivativeStructure> finalState_DS = FNP.propagate(target);
SpacecraftState finalState_R = NP.propagate(target.toAbsoluteDate());
FieldPVCoordinates<DerivativeStructure> finPVC_DS = finalState_DS.getPVCoordinates();
PVCoordinates finPVC_R = finalState_R.getPVCoordinates();
Assert.assertEquals(finPVC_DS.toPVCoordinates().getPosition().getX(), finPVC_R.getPosition().getX(), FastMath.abs(finPVC_R.getPosition().getX()) * 1e-11);
Assert.assertEquals(finPVC_DS.toPVCoordinates().getPosition().getY(), finPVC_R.getPosition().getY(), FastMath.abs(finPVC_R.getPosition().getY()) * 1e-11);
Assert.assertEquals(finPVC_DS.toPVCoordinates().getPosition().getZ(), finPVC_R.getPosition().getZ(), FastMath.abs(finPVC_R.getPosition().getZ()) * 1e-11);
long number = 23091991;
RandomGenerator RG = new Well19937a(number);
GaussianRandomGenerator NGG = new GaussianRandomGenerator(RG);
UncorrelatedRandomVectorGenerator URVG = new UncorrelatedRandomVectorGenerator(new double[] {0.0 , 0.0 , 0.0 , 0.0 , 0.0 , 0.0 },
new double[] {1e3, 0.005, 0.005, 0.01, 0.01, 0.01},
NGG);
double a_R = a_0.getReal();
double e_R = e_0.getReal();
double i_R = i_0.getReal();
double R_R = R_0.getReal();
double O_R = O_0.getReal();
double n_R = n_0.getReal();
for (int ii = 0; ii < 1; ii++){
double[] rand_next = URVG.nextVector();
double a_shift = a_R + rand_next[0];
double e_shift = e_R + rand_next[1];
double i_shift = i_R + rand_next[2];
double R_shift = R_R + rand_next[3];
double O_shift = O_R + rand_next[4];
double n_shift = n_R + rand_next[5];
KeplerianOrbit shiftedOrb = new KeplerianOrbit(a_shift, e_shift, i_shift, R_shift, O_shift, n_shift,
PositionAngle.MEAN,
EME,
J2000.toAbsoluteDate(),
Constants.EIGEN5C_EARTH_MU
);
SpacecraftState shift_iSR = new SpacecraftState(shiftedOrb);
NumericalPropagator shift_NP = new NumericalPropagator(RIntegrator);
shift_NP.setInitialState(shift_iSR);
shift_NP.addForceModel(forceModel);
SpacecraftState finalState_shift = shift_NP.propagate(target.toAbsoluteDate());
PVCoordinates finPVC_shift = finalState_shift.getPVCoordinates();
//position check
FieldVector3D<DerivativeStructure> pos_DS = finPVC_DS.getPosition();
double x_DS = pos_DS.getX().taylor(rand_next[0],rand_next[1],rand_next[2],rand_next[3],rand_next[4],rand_next[5]);
double y_DS = pos_DS.getY().taylor(rand_next[0],rand_next[1],rand_next[2],rand_next[3],rand_next[4],rand_next[5]);
double z_DS = pos_DS.getZ().taylor(rand_next[0],rand_next[1],rand_next[2],rand_next[3],rand_next[4],rand_next[5]);
//System.out.println(pos_DS.getX().getPartialDerivative(1));
double x = finPVC_shift.getPosition().getX();
double y = finPVC_shift.getPosition().getY();
double z = finPVC_shift.getPosition().getZ();
Assert.assertEquals(x_DS, x, FastMath.abs(x - pos_DS.getX().getReal()) * 1e-5);
Assert.assertEquals(y_DS, y, FastMath.abs(y - pos_DS.getY().getReal()) * 1e-5);
Assert.assertEquals(z_DS, z, FastMath.abs(z - pos_DS.getZ().getReal()) * 1e-5);
//velocity check
FieldVector3D<DerivativeStructure> vel_DS = finPVC_DS.getVelocity();
double vx_DS = vel_DS.getX().taylor(rand_next[0],rand_next[1],rand_next[2],rand_next[3],rand_next[4],rand_next[5]);
double vy_DS = vel_DS.getY().taylor(rand_next[0],rand_next[1],rand_next[2],rand_next[3],rand_next[4],rand_next[5]);
double vz_DS = vel_DS.getZ().taylor(rand_next[0],rand_next[1],rand_next[2],rand_next[3],rand_next[4],rand_next[5]);
double vx = finPVC_shift.getVelocity().getX();
double vy = finPVC_shift.getVelocity().getY();
double vz = finPVC_shift.getVelocity().getZ();
Assert.assertEquals(vx_DS, vx, FastMath.abs(vx) * 1e-7);
Assert.assertEquals(vy_DS, vy, FastMath.abs(vy) * 1e-7);
Assert.assertEquals(vz_DS, vz, FastMath.abs(vz) * 1e-7);
//acceleration check
FieldVector3D<DerivativeStructure> acc_DS = finPVC_DS.getAcceleration();
double ax_DS = acc_DS.getX().taylor(rand_next[0],rand_next[1],rand_next[2],rand_next[3],rand_next[4],rand_next[5]);
double ay_DS = acc_DS.getY().taylor(rand_next[0],rand_next[1],rand_next[2],rand_next[3],rand_next[4],rand_next[5]);
double az_DS = acc_DS.getZ().taylor(rand_next[0],rand_next[1],rand_next[2],rand_next[3],rand_next[4],rand_next[5]);
double ax = finPVC_shift.getAcceleration().getX();
double ay = finPVC_shift.getAcceleration().getY();
double az = finPVC_shift.getAcceleration().getZ();
Assert.assertEquals(ax_DS, ax, FastMath.abs(ax) * 1e-5);
Assert.assertEquals(ay_DS, ay, FastMath.abs(ay) * 1e-5);
Assert.assertEquals(az_DS, az, FastMath.abs(az) * 1e-5);
}
}
/**Same test as the previous one but not adding the ForceModel to the NumericalPropagator
it is a test to validate the previous test.
(to test if the ForceModel it's actually
doing something in the Propagator and the FieldPropagator)*/
@Test
public void RealFieldExpectErrorTest() throws OrekitException {
DSFactory factory = new DSFactory(6, 5);
DerivativeStructure a_0 = factory.variable(0, 7e6);
DerivativeStructure e_0 = factory.variable(1, 0.01);
DerivativeStructure i_0 = factory.variable(2, 85 * FastMath.PI / 180);
DerivativeStructure R_0 = factory.variable(3, 0.7);
DerivativeStructure O_0 = factory.variable(4, 0.5);
DerivativeStructure n_0 = factory.variable(5, 0.1);
Field<DerivativeStructure> field = a_0.getField();
DerivativeStructure zero = field.getZero();
FieldAbsoluteDate<DerivativeStructure> J2000 = new FieldAbsoluteDate<DerivativeStructure>(field);
Frame EME = FramesFactory.getEME2000();
FieldKeplerianOrbit<DerivativeStructure> FKO = new FieldKeplerianOrbit<DerivativeStructure>(a_0, e_0, i_0, R_0, O_0, n_0,
PositionAngle.MEAN,
EME,
J2000,
Constants.EIGEN5C_EARTH_MU);
FieldSpacecraftState<DerivativeStructure> initialState = new FieldSpacecraftState<DerivativeStructure>(FKO);
SpacecraftState iSR = initialState.toSpacecraftState();
OrbitType type = OrbitType.KEPLERIAN;
double[][] tolerance = NumericalPropagator.tolerances(10.0, FKO.toOrbit(), type);
AdaptiveStepsizeFieldIntegrator<DerivativeStructure> integrator =
new DormandPrince853FieldIntegrator<DerivativeStructure>(field, 0.001, 200, tolerance[0], tolerance[1]);
integrator.setInitialStepSize(zero.add(60));
AdaptiveStepsizeIntegrator RIntegrator =
new DormandPrince853Integrator(0.001, 200, tolerance[0], tolerance[1]);
RIntegrator.setInitialStepSize(60);
FieldNumericalPropagator<DerivativeStructure> FNP = new FieldNumericalPropagator<>(field, integrator);
FNP.setOrbitType(type);
FNP.setInitialState(initialState);
NumericalPropagator NP = new NumericalPropagator(RIntegrator);
NP.setOrbitType(type);
NP.setInitialState(iSR);
final DragForce forceModel =
new DragForce(new HarrisPriester(CelestialBodyFactory.getSun(),
new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF(IERSConventions.IERS_2010, true))),
new BoxAndSolarArraySpacecraft(1.5, 2.0, 1.8, CelestialBodyFactory.getSun(), 20.0,
Vector3D.PLUS_J, 1.2, 0.7, 0.2));
FNP.addForceModel(forceModel);
//NOT ADDING THE FORCE MODEL TO THE NUMERICAL PROPAGATOR NP.addForceModel(forceModel);
FieldAbsoluteDate<DerivativeStructure> target = J2000.shiftedBy(10000.);
FieldSpacecraftState<DerivativeStructure> finalState_DS = FNP.propagate(target);
SpacecraftState finalState_R = NP.propagate(target.toAbsoluteDate());
FieldPVCoordinates<DerivativeStructure> finPVC_DS = finalState_DS.getPVCoordinates();
PVCoordinates finPVC_R = finalState_R.getPVCoordinates();
Assert.assertFalse(FastMath.abs(finPVC_DS.toPVCoordinates().getPosition().getX() - finPVC_R.getPosition().getX()) < FastMath.abs(finPVC_R.getPosition().getX()) * 1e-11);
Assert.assertFalse(FastMath.abs(finPVC_DS.toPVCoordinates().getPosition().getY() - finPVC_R.getPosition().getY()) < FastMath.abs(finPVC_R.getPosition().getY()) * 1e-11);
Assert.assertFalse(FastMath.abs(finPVC_DS.toPVCoordinates().getPosition().getZ() - finPVC_R.getPosition().getZ()) < FastMath.abs(finPVC_R.getPosition().getZ()) * 1e-11);
}
@Before
public void setUp() throws OrekitException {
Utils.setDataRoot("regular-data");
}
}