/* Copyright 2013-2016 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 AffinagePleiades;
import org.hipparchus.geometry.euclidean.threed.Rotation;
import org.hipparchus.geometry.euclidean.threed.Vector3D;
import org.hipparchus.ode.nonstiff.DormandPrince853Integrator;
import org.hipparchus.util.FastMath;
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.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.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.time.AbsoluteDate;
import org.orekit.time.TimeScale;
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;
/**
* Orbit Model class to generate PV and Q
* @author jguinet
*
*/
public class OrbitModel {
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));
}
public 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);
}
public BodyShape createEarth()
throws OrekitException {
return new OneAxisEllipsoid(Constants.WGS84_EARTH_EQUATORIAL_RADIUS,
Constants.WGS84_EARTH_FLATTENING,
FramesFactory.getITRF(IERSConventions.IERS_2010, true));
}
public NormalizedSphericalHarmonicsProvider createGravityField()
throws OrekitException {
return GravityFieldFactory.getNormalizedProvider(12, 12);
}
public Orbit createOrbit(double mu,AbsoluteDate date)
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
Frame eme2000 = FramesFactory.getEME2000();
//return new CircularOrbit(7173352.811913891,
return new CircularOrbit(694000.0 + Constants.WGS84_EARTH_EQUATORIAL_RADIUS,//ajouter Rayon
-4.029194321683225E-4, 0.0013530362644647786,
FastMath.toRadians(98.2), //pleiades inclinaison 98.2
//FastMath.toRadians(-86.47),
FastMath.toRadians(-86.47+180),
FastMath.toRadians(135.9+0.3), PositionAngle.TRUE,
eme2000, date, mu);
}
public 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;
}
public List<TimeStampedPVCoordinates> orbitToPV(Orbit orbit, BodyShape earth,
AbsoluteDate minDate, AbsoluteDate maxDate,
double step)
throws OrekitException {
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;
}
public List<TimeStampedAngularCoordinates> orbitToQ(Orbit orbit, BodyShape earth,
AbsoluteDate minDate, AbsoluteDate maxDate,
double step)
throws OrekitException {
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;
}
}