DrozinerAttractionModel.java
/* Copyright 2002-2016 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,
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* See the License for the specific language governing permissions and
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package org.orekit.forces.gravity;
import org.hipparchus.analysis.differentiation.DerivativeStructure;
import org.hipparchus.geometry.euclidean.threed.FieldRotation;
import org.hipparchus.geometry.euclidean.threed.FieldVector3D;
import org.hipparchus.geometry.euclidean.threed.Vector3D;
import org.hipparchus.util.FastMath;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitInternalError;
import org.orekit.errors.OrekitMessages;
import org.orekit.forces.AbstractForceModel;
import org.orekit.forces.gravity.potential.TideSystem;
import org.orekit.forces.gravity.potential.TideSystemProvider;
import org.orekit.forces.gravity.potential.UnnormalizedSphericalHarmonicsProvider;
import org.orekit.forces.gravity.potential.UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics;
import org.orekit.frames.Frame;
import org.orekit.frames.Transform;
import org.orekit.propagation.SpacecraftState;
import org.orekit.propagation.events.EventDetector;
import org.orekit.propagation.numerical.Jacobianizer;
import org.orekit.propagation.numerical.TimeDerivativesEquations;
import org.orekit.time.AbsoluteDate;
import org.orekit.utils.ParameterDriver;
import org.orekit.utils.ParameterObserver;
/** This class represents the gravitational field of a celestial body.
* <p>The algorithm implemented in this class has been designed by
* Andrzej Droziner (Institute of Mathematical Machines, Warsaw) in
* his 1976 paper: <em>An algorithm for recurrent calculation of gravitational
* acceleration</em> (artificial satellites, Vol. 12, No 2, June 1977).</p>
* <p>
* Note that this class can often not be used for high degrees (say
* above 90) as most modern gravity fields are provided as normalized
* coefficients and the un-normalization process to convert these
* coefficients underflows at degree and order 89. This class also
* does not provide analytical partial derivatives (it uses finite differences
* to compute them) and is much slower than {@link HolmesFeatherstoneAttractionModel}
* (even when no derivatives are computed). For all these reasons,
* it is recommended to use the {@link HolmesFeatherstoneAttractionModel
* Holmes-Featherstone model} rather than this class.
* </p>
* <p>
* This class uses finite differences to compute derivatives and the steps for
* finite differences are initialized in the {@link
* #DrozinerAttractionModel(Frame, UnnormalizedSphericalHarmonicsProvider,
* double) constructor}
* </p>
*
* @see HolmesFeatherstoneAttractionModel
*
* @author Fabien Maussion
* @author Luc Maisonobe
* @author Véronique Pommier-Maurussane
*/
public class DrozinerAttractionModel extends AbstractForceModel implements TideSystemProvider {
/** Central attraction scaling factor.
* <p>
* We use a power of 2 to avoid numeric noise introduction
* in the multiplications/divisions sequences.
* </p>
*/
private static final double MU_SCALE = FastMath.scalb(1.0, 32);
/** Drivers for force model parameters. */
private final ParameterDriver[] parametersDrivers;
/** Provider for the spherical harmonics. */
private final UnnormalizedSphericalHarmonicsProvider provider;
/** Central body attraction coefficient (m³/s²). */
private double mu;
/** Rotating body. */
private final Frame centralBodyFrame;
/** Helper class computing acceleration derivatives. */
private Jacobianizer jacobianizer;
/** Creates a new instance.
* @param centralBodyFrame rotating body frame
* @param provider provider for spherical harmonics
* @param hPosition step used for finite difference computation
* with respect to spacecraft position (m)
*/
public DrozinerAttractionModel(final Frame centralBodyFrame,
final UnnormalizedSphericalHarmonicsProvider provider,
final double hPosition) {
this.parametersDrivers = new ParameterDriver[1];
try {
parametersDrivers[0] = new ParameterDriver(NewtonianAttraction.CENTRAL_ATTRACTION_COEFFICIENT,
provider.getMu(), MU_SCALE, 0.0, Double.POSITIVE_INFINITY);
parametersDrivers[0].addObserver(new ParameterObserver() {
/** {@inheritDoc} */
@Override
public void valueChanged(final double previousValue, final ParameterDriver driver) {
DrozinerAttractionModel.this.mu = driver.getValue();
}
});
} catch (OrekitException oe) {
// this should never occur as valueChanged above never throws an exception
throw new OrekitInternalError(oe);
};
this.provider = provider;
this.mu = provider.getMu();
this.centralBodyFrame = centralBodyFrame;
this.jacobianizer = new Jacobianizer(this, mu, hPosition);
}
/** {@inheritDoc} */
public TideSystem getTideSystem() {
return provider.getTideSystem();
}
/** {@inheritDoc} */
public void addContribution(final SpacecraftState s, final TimeDerivativesEquations adder)
throws OrekitException {
// Get the position in body frame
final AbsoluteDate date = s.getDate();
final UnnormalizedSphericalHarmonics harmonics = provider.onDate(date);
final Transform bodyToInertial = centralBodyFrame.getTransformTo(s.getFrame(), date);
final Vector3D posInBody =
bodyToInertial.getInverse().transformVector(s.getPVCoordinates().getPosition());
final double xBody = posInBody.getX();
final double yBody = posInBody.getY();
final double zBody = posInBody.getZ();
// Computation of intermediate variables
final double r12 = xBody * xBody + yBody * yBody;
final double r1 = FastMath.sqrt(r12);
if (r1 <= 10e-2) {
throw new OrekitException(OrekitMessages.POLAR_TRAJECTORY, r1);
}
final double r2 = r12 + zBody * zBody;
final double r = FastMath.sqrt(r2);
final double equatorialRadius = provider.getAe();
if (r <= equatorialRadius) {
throw new OrekitException(OrekitMessages.TRAJECTORY_INSIDE_BRILLOUIN_SPHERE, r);
}
final double r3 = r2 * r;
final double aeOnr = equatorialRadius / r;
final double zOnr = zBody / r;
final double r1Onr = r1 / r;
// Definition of the first acceleration terms
final double mMuOnr3 = -mu / r3;
final double xDotDotk = xBody * mMuOnr3;
final double yDotDotk = yBody * mMuOnr3;
// Zonal part of acceleration
double sumA = 0.0;
double sumB = 0.0;
double bk1 = zOnr;
double bk0 = aeOnr * (3 * bk1 * bk1 - 1.0);
double jk = -harmonics.getUnnormalizedCnm(1, 0);
// first zonal term
sumA += jk * (2 * aeOnr * bk1 - zOnr * bk0);
sumB += jk * bk0;
// other terms
for (int k = 2; k <= provider.getMaxDegree(); k++) {
final double bk2 = bk1;
bk1 = bk0;
final double p = (1.0 + k) / k;
bk0 = aeOnr * ((1 + p) * zOnr * bk1 - (k * aeOnr * bk2) / (k - 1));
final double ak0 = p * aeOnr * bk1 - zOnr * bk0;
jk = -harmonics.getUnnormalizedCnm(k, 0);
sumA += jk * ak0;
sumB += jk * bk0;
}
// calculate the acceleration
final double p = -sumA / (r1Onr * r1Onr);
double aX = xDotDotk * p;
double aY = yDotDotk * p;
double aZ = mu * sumB / r2;
// Tessereal-sectorial part of acceleration
if (provider.getMaxOrder() > 0) {
// latitude and longitude in body frame
final double cosL = xBody / r1;
final double sinL = yBody / r1;
// intermediate variables
double betaKminus1 = aeOnr;
double cosjm1L = cosL;
double sinjm1L = sinL;
double sinjL = sinL;
double cosjL = cosL;
double betaK = 0;
double Bkj = 0.0;
double Bkm1j = 3 * betaKminus1 * zOnr * r1Onr;
double Bkm2j = 0;
double Bkminus1kminus1 = Bkm1j;
// first terms
final double c11 = harmonics.getUnnormalizedCnm(1, 1);
final double s11 = harmonics.getUnnormalizedSnm(1, 1);
double Gkj = c11 * cosL + s11 * sinL;
double Hkj = c11 * sinL - s11 * cosL;
double Akj = 2 * r1Onr * betaKminus1 - zOnr * Bkminus1kminus1;
double Dkj = (Akj + zOnr * Bkminus1kminus1) * 0.5;
double sum1 = Akj * Gkj;
double sum2 = Bkminus1kminus1 * Gkj;
double sum3 = Dkj * Hkj;
// the other terms
for (int j = 1; j <= provider.getMaxOrder(); ++j) {
double innerSum1 = 0.0;
double innerSum2 = 0.0;
double innerSum3 = 0.0;
for (int k = FastMath.max(2, j); k <= provider.getMaxDegree(); ++k) {
final double ckj = harmonics.getUnnormalizedCnm(k, j);
final double skj = harmonics.getUnnormalizedSnm(k, j);
Gkj = ckj * cosjL + skj * sinjL;
Hkj = ckj * sinjL - skj * cosjL;
if (j <= (k - 2)) {
Bkj = aeOnr * (zOnr * Bkm1j * (2.0 * k + 1.0) / (k - j) -
aeOnr * Bkm2j * (k + j) / (k - 1 - j));
Akj = aeOnr * Bkm1j * (k + 1.0) / (k - j) - zOnr * Bkj;
} else if (j == (k - 1)) {
betaK = aeOnr * (2.0 * k - 1.0) * r1Onr * betaKminus1;
Bkj = aeOnr * (2.0 * k + 1.0) * zOnr * Bkm1j - betaK;
Akj = aeOnr * (k + 1.0) * Bkm1j - zOnr * Bkj;
betaKminus1 = betaK;
} else if (j == k) {
Bkj = (2 * k + 1) * aeOnr * r1Onr * Bkminus1kminus1;
Akj = (k + 1) * r1Onr * betaK - zOnr * Bkj;
Bkminus1kminus1 = Bkj;
}
Dkj = (Akj + zOnr * Bkj) * j / (k + 1.0);
Bkm2j = Bkm1j;
Bkm1j = Bkj;
innerSum1 += Akj * Gkj;
innerSum2 += Bkj * Gkj;
innerSum3 += Dkj * Hkj;
}
sum1 += innerSum1;
sum2 += innerSum2;
sum3 += innerSum3;
sinjL = sinjm1L * cosL + cosjm1L * sinL;
cosjL = cosjm1L * cosL - sinjm1L * sinL;
sinjm1L = sinjL;
cosjm1L = cosjL;
}
// compute the acceleration
final double r2Onr12 = r2 / (r1 * r1);
final double p1 = r2Onr12 * xDotDotk;
final double p2 = r2Onr12 * yDotDotk;
aX += p1 * sum1 - p2 * sum3;
aY += p2 * sum1 + p1 * sum3;
aZ -= mu * sum2 / r2;
}
// provide the perturbing acceleration to the derivatives adder in inertial frame
final Vector3D accInInert =
bodyToInertial.transformVector(new Vector3D(aX, aY, aZ));
adder.addXYZAcceleration(accInInert.getX(), accInInert.getY(), accInInert.getZ());
}
/** {@inheritDoc} */
public FieldVector3D<DerivativeStructure> accelerationDerivatives(final AbsoluteDate date, final Frame frame,
final FieldVector3D<DerivativeStructure> position,
final FieldVector3D<DerivativeStructure> velocity,
final FieldRotation<DerivativeStructure> rotation,
final DerivativeStructure mass)
throws OrekitException {
return jacobianizer.accelerationDerivatives(date, frame, position, velocity, rotation, mass);
}
/** {@inheritDoc} */
public FieldVector3D<DerivativeStructure> accelerationDerivatives(final SpacecraftState s, final String paramName)
throws OrekitException {
return jacobianizer.accelerationDerivatives(s, paramName);
}
/** {@inheritDoc} */
public EventDetector[] getEventsDetectors() {
return new EventDetector[0];
}
/** {@inheritDoc} */
public ParameterDriver[] getParametersDrivers() {
return parametersDrivers.clone();
}
}