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* 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.rugged;
import org.hipparchus.geometry.euclidean.threed.Rotation;
import org.hipparchus.geometry.euclidean.threed.RotationConvention;
import org.hipparchus.geometry.euclidean.threed.Vector3D;
import org.hipparchus.ode.nonstiff.DormandPrince853Integrator;
import org.hipparchus.util.FastMath;
import org.junit.Assert;
import java.lang.reflect.Field;
import java.lang.reflect.Modifier;
import java.util.ArrayList;
import java.util.List;
import org.orekit.attitudes.AttitudeProvider;
import org.orekit.attitudes.NadirPointing;
import org.orekit.attitudes.YawCompensation;
import org.orekit.bodies.BodyShape;
import org.orekit.bodies.CelestialBodyFactory;
import org.orekit.bodies.OneAxisEllipsoid;
import org.orekit.data.DataProvidersManager;
import org.orekit.errors.OrekitException;
import org.orekit.forces.gravity.HolmesFeatherstoneAttractionModel;
import org.orekit.forces.gravity.ThirdBodyAttraction;
import org.orekit.forces.gravity.potential.GravityFieldFactory;
import org.orekit.forces.gravity.potential.NormalizedSphericalHarmonicsProvider;
import org.orekit.frames.Frame;
import org.orekit.frames.FramesFactory;
import org.orekit.frames.Transform;
import org.orekit.orbits.CircularOrbit;
import org.orekit.orbits.FieldCartesianOrbit;
import org.orekit.orbits.FieldCircularOrbit;
import org.orekit.orbits.FieldEquinoctialOrbit;
import org.orekit.orbits.FieldKeplerianOrbit;
import org.orekit.orbits.Orbit;
import org.orekit.orbits.OrbitType;
import org.orekit.orbits.PositionAngle;
import org.orekit.propagation.Propagator;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.analytical.KeplerianPropagator;
import org.orekit.propagation.numerical.NumericalPropagator;
import org.orekit.propagation.sampling.OrekitFixedStepHandler;
import org.orekit.propagation.semianalytical.dsst.utilities.JacobiPolynomials;
import org.orekit.propagation.semianalytical.dsst.utilities.NewcombOperators;
import org.orekit.rugged.los.LOSBuilder;
import org.orekit.rugged.los.TimeDependentLOS;
import org.orekit.time.AbsoluteDate;
import org.orekit.time.TimeScale;
import org.orekit.time.TimeScalesFactory;
import org.orekit.utils.Constants;
import org.orekit.utils.IERSConventions;
import org.orekit.utils.PVCoordinates;
import org.orekit.utils.TimeStampedAngularCoordinates;
import org.orekit.utils.TimeStampedPVCoordinates;
/**
* @author Luc Maisonobe
* @author Guylaine Prat
*/
public class TestUtils {
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/**
* Clean up of factories for JUnit
* TBN: copied from Utils of Test suite of Orekit 9.0
* @since 2.0
*/
public static void clearFactories() {
clearFactoryMaps(CelestialBodyFactory.class);
CelestialBodyFactory.clearCelestialBodyLoaders();
clearFactoryMaps(FramesFactory.class);
clearFactoryMaps(TimeScalesFactory.class);
clearFactory(TimeScalesFactory.class, TimeScale.class);
clearFactoryMaps(FieldCartesianOrbit.class);
clearFactoryMaps(FieldKeplerianOrbit.class);
clearFactoryMaps(FieldCircularOrbit.class);
clearFactoryMaps(FieldEquinoctialOrbit.class);
clearFactoryMaps(JacobiPolynomials.class);
clearFactoryMaps(NewcombOperators.class);
for (final Class<?> c : NewcombOperators.class.getDeclaredClasses()) {
if (c.getName().endsWith("PolynomialsGenerator")) {
clearFactoryMaps(c);
}
}
FramesFactory.clearEOPHistoryLoaders();
FramesFactory.setEOPContinuityThreshold(5 * Constants.JULIAN_DAY);
TimeScalesFactory.clearUTCTAIOffsetsLoaders();
GravityFieldFactory.clearPotentialCoefficientsReaders();
GravityFieldFactory.clearOceanTidesReaders();
DataProvidersManager.getInstance().clearProviders();
DataProvidersManager.getInstance().clearLoadedDataNames();
}
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/** Clean up of factory map
* @param factoryClass
* @since 2.0
*/
private static void clearFactoryMaps(Class<?> factoryClass) {
try {
for (Field field : factoryClass.getDeclaredFields()) {
if (Modifier.isStatic(field.getModifiers()) &&
Map.class.isAssignableFrom(field.getType())) {
field.setAccessible(true);
((Map<?, ?>) field.get(null)).clear();
}
}
} catch (IllegalAccessException iae) {
Assert.fail(iae.getMessage());
}
}
/** Clean up of a factory
* @param factoryClass
* @param cachedFieldsClass
* @since 2.0
*/
private static void clearFactory(Class<?> factoryClass, Class<?> cachedFieldsClass) {
try {
for (Field field : factoryClass.getDeclaredFields()) {
if (Modifier.isStatic(field.getModifiers()) &&
cachedFieldsClass.isAssignableFrom(field.getType())) {
field.setAccessible(true);
field.set(null, null);
}
}
} catch (IllegalAccessException iae) {
Assert.fail(iae.getMessage());
}
}
/**
* Generate satellite ephemeris
*/
public static void addSatellitePV(TimeScale gps, Frame eme2000, Frame itrf,
ArrayList<TimeStampedPVCoordinates> satellitePVList,
String absDate,
double px, double py, double pz, double vx, double vy, double vz)
throws OrekitException {
AbsoluteDate ephemerisDate = new AbsoluteDate(absDate, gps);
Vector3D position = new Vector3D(px, py, pz);
Vector3D velocity = new Vector3D(vx, vy, vz);
PVCoordinates pvITRF = new PVCoordinates(position, velocity);
Transform transform = itrf.getTransformTo(eme2000, ephemerisDate);
Vector3D pEME2000 = transform.transformPosition(pvITRF.getPosition());
Vector3D vEME2000 = transform.transformVector(pvITRF.getVelocity());
satellitePVList.add(new TimeStampedPVCoordinates(ephemerisDate, pEME2000, vEME2000, Vector3D.ZERO));
}
/**
* Generate satellite attitudes
*/
public static void addSatelliteQ(TimeScale gps, ArrayList<TimeStampedAngularCoordinates> satelliteQList,
String absDate, double q0, double q1, double q2, double q3) {
AbsoluteDate attitudeDate = new AbsoluteDate(absDate, gps);
Rotation rotation = new Rotation(q0, q1, q2, q3, true);
TimeStampedAngularCoordinates pair =
new TimeStampedAngularCoordinates(attitudeDate, rotation, Vector3D.ZERO, Vector3D.ZERO);
satelliteQList.add(pair);
}
/** Create an Earth for Junit tests
* @return the Earth as the WGS84 ellipsoid
* @throws OrekitException
*/
public static BodyShape createEarth()
throws OrekitException {
return new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF(IERSConventions.IERS_2010, true));
}
/** Created a gravity field
* @return normalized spherical harmonics coefficients
* @throws OrekitException
*/
public static NormalizedSphericalHarmonicsProvider createGravityField()
throws OrekitException {
return GravityFieldFactory.getNormalizedProvider(12, 12);
}
/** Create an orbit
* @return the orbit
* @throws OrekitException
*/
public static Orbit createOrbit(double mu)
throws OrekitException {
// the following orbital parameters have been computed using
// Orekit tutorial about phasing, using the following configuration:
//
// orbit.date = 2012-01-01T00:00:00.000
// phasing.orbits.number = 143
// phasing.days.number = 10
// sun.synchronous.reference.latitude = 0
// sun.synchronous.reference.ascending = false
// sun.synchronous.mean.solar.time = 10:30:00
// gravity.field.degree = 12
// gravity.field.order = 12
AbsoluteDate date = new AbsoluteDate("2012-01-01T00:00:00.000", TimeScalesFactory.getUTC());
Frame eme2000 = FramesFactory.getEME2000();
return new CircularOrbit(7173352.811913891,
-4.029194321683225E-4, 0.0013530362644647786,
FastMath.toRadians(98.63218182243709),
FastMath.toRadians(77.55565567747836),
FastMath.PI, PositionAngle.TRUE,
eme2000, date, mu);
}
/** Create the propagator of an orbit.
* @return propagator of the orbit
* @throws OrekitException
*/
public static Propagator createPropagator(BodyShape earth,
NormalizedSphericalHarmonicsProvider gravityField,
Orbit orbit)
throws OrekitException {
AttitudeProvider yawCompensation = new YawCompensation(orbit.getFrame(), new NadirPointing(orbit.getFrame(), earth));
SpacecraftState state = new SpacecraftState(orbit,
yawCompensation.getAttitude(orbit,
orbit.getDate(),
orbit.getFrame()),
1180.0);
// numerical model for improving orbit
OrbitType type = OrbitType.CIRCULAR;
double[][] tolerances = NumericalPropagator.tolerances(0.1, orbit, type);
DormandPrince853Integrator integrator =
new DormandPrince853Integrator(1.0e-4 * orbit.getKeplerianPeriod(),
1.0e-1 * orbit.getKeplerianPeriod(),
tolerances[0], tolerances[1]);
integrator.setInitialStepSize(1.0e-2 * orbit.getKeplerianPeriod());
NumericalPropagator numericalPropagator = new NumericalPropagator(integrator);
numericalPropagator.addForceModel(new HolmesFeatherstoneAttractionModel(earth.getBodyFrame(), gravityField));
numericalPropagator.addForceModel(new ThirdBodyAttraction(CelestialBodyFactory.getSun()));
numericalPropagator.addForceModel(new ThirdBodyAttraction(CelestialBodyFactory.getMoon()));
numericalPropagator.setOrbitType(type);
numericalPropagator.setInitialState(state);
numericalPropagator.setAttitudeProvider(yawCompensation);
return numericalPropagator;
}
/** Create a perfect Line Of Sight list
* @return the perfect LOS list
*/
public static LOSBuilder createLOSPerfectLine(Vector3D center, Vector3D normal, double halfAperture, int n) {
List<Vector3D> list = new ArrayList<Vector3D>(n);
for (int i = 0; i < n; ++i) {
double alpha = (halfAperture * (2 * i + 1 - n)) / (n - 1);
list.add(new Rotation(normal, alpha, RotationConvention.VECTOR_OPERATOR).applyTo(center));
return new LOSBuilder(list);
/** Create a Line Of Sight which depends on time.
* @return the dependent of time LOS
*/
public static TimeDependentLOS createLOSCurvedLine(Vector3D center, Vector3D normal,
double halfAperture, double sagitta, int n) {
Vector3D u = Vector3D.crossProduct(center, normal);
List<Vector3D> list = new ArrayList<Vector3D>(n);
for (int i = 0; i < n; ++i) {
double x = (2.0 * i + 1.0 - n) / (n - 1);
double alpha = x * halfAperture;
double beta = x * x * sagitta;
list.add(new Rotation(normal, alpha, RotationConvention.VECTOR_OPERATOR).
applyTo(new Rotation(u, beta, RotationConvention.VECTOR_OPERATOR).
applyTo(center)));
}
return new LOSBuilder(list).build();
}
/** Propagate an orbit between 2 given dates
* @return a list of TimeStampedPVCoordinates
* @throws OrekitException
*/
public static List<TimeStampedPVCoordinates> orbitToPV(Orbit orbit, BodyShape earth,
AbsoluteDate minDate, AbsoluteDate maxDate,
double step)
Propagator propagator = new KeplerianPropagator(orbit);
propagator.setAttitudeProvider(new YawCompensation(orbit.getFrame(), new NadirPointing(orbit.getFrame(), earth)));
propagator.propagate(minDate);
final List<TimeStampedPVCoordinates> list = new ArrayList<TimeStampedPVCoordinates>();
propagator.setMasterMode(step, new OrekitFixedStepHandler() {
public void init(SpacecraftState s0, AbsoluteDate t) {
public void handleStep(SpacecraftState currentState, boolean isLast) {
list.add(new TimeStampedPVCoordinates(currentState.getDate(),
currentState.getPVCoordinates().getPosition(),
currentState.getPVCoordinates().getVelocity(),
Vector3D.ZERO));
}
});
propagator.propagate(maxDate);
return list;
}
/** Propagate an attitude between 2 given dates
* @return a list of TimeStampedAngularCoordinates
* @throws OrekitException
*/
public static List<TimeStampedAngularCoordinates> orbitToQ(Orbit orbit, BodyShape earth,
AbsoluteDate minDate, AbsoluteDate maxDate,
double step)
Propagator propagator = new KeplerianPropagator(orbit);
propagator.setAttitudeProvider(new YawCompensation(orbit.getFrame(), new NadirPointing(orbit.getFrame(), earth)));
propagator.propagate(minDate);
final List<TimeStampedAngularCoordinates> list = new ArrayList<TimeStampedAngularCoordinates>();
propagator.setMasterMode(step, new OrekitFixedStepHandler() {
public void init(SpacecraftState s0, AbsoluteDate t) {
public void handleStep(SpacecraftState currentState, boolean isLast) {
list.add(new TimeStampedAngularCoordinates(currentState.getDate(),
currentState.getAttitude().getRotation(),
Vector3D.ZERO, Vector3D.ZERO));
}
});
propagator.propagate(maxDate);
return list;
}
}