SolarRadiationPressure.java
- /* Copyright 2002-2022 CS GROUP
- * Licensed to CS GROUP (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.radiation;
- import java.util.ArrayList;
- import java.util.List;
- import java.util.Map;
- import org.hipparchus.CalculusFieldElement;
- import org.hipparchus.geometry.euclidean.threed.FieldVector3D;
- import org.hipparchus.geometry.euclidean.threed.Vector3D;
- import org.hipparchus.util.FastMath;
- import org.hipparchus.util.MathArrays;
- import org.hipparchus.util.Precision;
- import org.orekit.frames.Frame;
- import org.orekit.propagation.FieldSpacecraftState;
- import org.orekit.propagation.SpacecraftState;
- import org.orekit.time.AbsoluteDate;
- import org.orekit.time.FieldAbsoluteDate;
- import org.orekit.utils.Constants;
- import org.orekit.utils.ExtendedPVCoordinatesProvider;
- import org.orekit.utils.ParameterDriver;
- /** Solar radiation pressure force model.
- * <p>
- * Since Orekit 11.0, it is possible to take into account
- * the eclipses generated by Moon in the solar radiation
- * pressure force model using the
- * {@link #addOccultingBody(ExtendedPVCoordinatesProvider, double)}
- * method.
- * <p>
- * Example:<br>
- * <code> SolarRadiationPressure srp = </code>
- * <code> new SolarRadiationPressure(CelestialBodyFactory.getSun(), Constants.EIGEN5C_EARTH_EQUATORIAL_RADIUS,</code>
- * <code> new IsotropicRadiationClassicalConvention(50.0, 0.5, 0.5));</code><br>
- * <code> srp.addOccultingBody(CelestialBodyFactory.getMoon(), Constants.MOON_EQUATORIAL_RADIUS);</code><br>
- *
- * @author Fabien Maussion
- * @author Édouard Delente
- * @author Véronique Pommier-Maurussane
- * @author Pascal Parraud
- */
- public class SolarRadiationPressure extends AbstractRadiationForceModel {
- /** Reference distance for the solar radiation pressure (m). */
- private static final double D_REF = 149597870000.0;
- /** Reference solar radiation pressure at D_REF (N/m²). */
- private static final double P_REF = 4.56e-6;
- /** Margin to force recompute lighting ratio derivatives when we are really inside penumbra. */
- private static final double ANGULAR_MARGIN = 1.0e-10;
- /** Reference flux normalized for a 1m distance (N). */
- private final double kRef;
- /** Sun model. */
- private final ExtendedPVCoordinatesProvider sun;
- /** Spacecraft. */
- private final RadiationSensitive spacecraft;
- /** Simple constructor with default reference values.
- * <p>When this constructor is used, the reference values are:</p>
- * <ul>
- * <li>d<sub>ref</sub> = 149597870000.0 m</li>
- * <li>p<sub>ref</sub> = 4.56 10<sup>-6</sup> N/m²</li>
- * </ul>
- * @param sun Sun model
- * @param equatorialRadius spherical shape model (for umbra/penumbra computation)
- * @param spacecraft the object physical and geometrical information
- * @since 9.2
- */
- public SolarRadiationPressure(final ExtendedPVCoordinatesProvider sun, final double equatorialRadius,
- final RadiationSensitive spacecraft) {
- this(D_REF, P_REF, sun, equatorialRadius, spacecraft);
- }
- /** Complete constructor.
- * <p>Note that reference solar radiation pressure <code>pRef</code> in
- * N/m² is linked to solar flux SF in W/m² using
- * formula pRef = SF/c where c is the speed of light (299792458 m/s). So
- * at 1UA a 1367 W/m² solar flux is a 4.56 10<sup>-6</sup>
- * N/m² solar radiation pressure.</p>
- * @param dRef reference distance for the solar radiation pressure (m)
- * @param pRef reference solar radiation pressure at dRef (N/m²)
- * @param sun Sun model
- * @param equatorialRadius spherical shape model (for umbra/penumbra computation)
- * @param spacecraft the object physical and geometrical information
- * @since 9.2
- */
- public SolarRadiationPressure(final double dRef, final double pRef,
- final ExtendedPVCoordinatesProvider sun,
- final double equatorialRadius,
- final RadiationSensitive spacecraft) {
- super(sun, equatorialRadius);
- this.kRef = pRef * dRef * dRef;
- this.sun = sun;
- this.spacecraft = spacecraft;
- }
- /** {@inheritDoc} */
- @Override
- public Vector3D acceleration(final SpacecraftState s, final double[] parameters) {
- final AbsoluteDate date = s.getDate();
- final Frame frame = s.getFrame();
- final Vector3D position = s.getPVCoordinates().getPosition();
- final Vector3D sunSatVector = position.subtract(sun.getPVCoordinates(date, frame).getPosition());
- final double r2 = sunSatVector.getNormSq();
- // compute flux
- final double ratio = getTotalLightingRatio(position, frame, date);
- final double rawP = ratio * kRef / r2;
- final Vector3D flux = new Vector3D(rawP / FastMath.sqrt(r2), sunSatVector);
- return spacecraft.radiationPressureAcceleration(date, frame, position, s.getAttitude().getRotation(),
- s.getMass(), flux, parameters);
- }
- /** {@inheritDoc} */
- @Override
- public <T extends CalculusFieldElement<T>> FieldVector3D<T> acceleration(final FieldSpacecraftState<T> s,
- final T[] parameters) {
- final FieldAbsoluteDate<T> date = s.getDate();
- final Frame frame = s.getFrame();
- final FieldVector3D<T> position = s.getPVCoordinates().getPosition();
- final FieldVector3D<T> sunSatVector = position.subtract(sun.getPVCoordinates(date, frame).getPosition());
- final T r2 = sunSatVector.getNormSq();
- // compute flux
- final T ratio = getTotalLightingRatio(position, frame, date);
- final T rawP = ratio.multiply(kRef).divide(r2);
- final FieldVector3D<T> flux = new FieldVector3D<>(rawP.divide(r2.sqrt()), sunSatVector);
- return spacecraft.radiationPressureAcceleration(date, frame, position, s.getAttitude().getRotation(),
- s.getMass(), flux, parameters);
- }
- /** Get the lighting ratio ([0-1]).
- * Considers only central body as occulting body.
- * @param position the satellite's position in the selected frame.
- * @param frame in which is defined the position
- * @param date the date
- * @return lighting ratio
- * @since 7.1
- */
- public double getLightingRatio(final Vector3D position, final Frame frame, final AbsoluteDate date) {
- final Vector3D sunPosition = sun.getPVCoordinates(date, frame).getPosition();
- if (sunPosition.getNorm() < 2 * Constants.SUN_RADIUS) {
- // we are in fact computing a trajectory around Sun (or solar system barycenter),
- // not around a planet,we consider lighting ratio is always 1
- return 1.0;
- }
- // Compute useful angles
- final double[] angle = getEclipseAngles(sunPosition, position);
- // Sat-Sun / Sat-CentralBody angle
- final double sunSatCentralBodyAngle = angle[0];
- // Central Body apparent radius
- final double alphaCentral = angle[1];
- // Sun apparent radius
- final double alphaSun = angle[2];
- double result = 1.0;
- // Is the satellite in complete umbra ?
- if (sunSatCentralBodyAngle - alphaCentral + alphaSun <= ANGULAR_MARGIN) {
- result = 0.0;
- } else if (sunSatCentralBodyAngle - alphaCentral - alphaSun < -ANGULAR_MARGIN) {
- // Compute a lighting ratio in penumbra
- final double sEA2 = sunSatCentralBodyAngle * sunSatCentralBodyAngle;
- final double oo2sEA = 1.0 / (2. * sunSatCentralBodyAngle);
- final double aS2 = alphaSun * alphaSun;
- final double aE2 = alphaCentral * alphaCentral;
- final double aE2maS2 = aE2 - aS2;
- final double alpha1 = (sEA2 - aE2maS2) * oo2sEA;
- final double alpha2 = (sEA2 + aE2maS2) * oo2sEA;
- // Protection against numerical inaccuracy at boundaries
- final double almost0 = Precision.SAFE_MIN;
- final double almost1 = FastMath.nextDown(1.0);
- final double a1oaS = FastMath.min(almost1, FastMath.max(-almost1, alpha1 / alphaSun));
- final double aS2ma12 = FastMath.max(almost0, aS2 - alpha1 * alpha1);
- final double a2oaE = FastMath.min(almost1, FastMath.max(-almost1, alpha2 / alphaCentral));
- final double aE2ma22 = FastMath.max(almost0, aE2 - alpha2 * alpha2);
- final double P1 = aS2 * FastMath.acos(a1oaS) - alpha1 * FastMath.sqrt(aS2ma12);
- final double P2 = aE2 * FastMath.acos(a2oaE) - alpha2 * FastMath.sqrt(aE2ma22);
- result = 1. - (P1 + P2) / (FastMath.PI * aS2);
- }
- return result;
- }
- /** Get eclipse ratio between to bodies seen from a specific object.
- * Ratio is in [0-1].
- * @param position the satellite's position in the selected frame
- * @param occultingPosition the position of the occulting object
- * @param occultingRadius the mean radius of the occulting object
- * @param occultedPosition the position of the occulted object
- * @param occultedRadius the mean radius of the occulted object
- * @return eclipse ratio
- */
- public double getGeneralEclipseRatio(final Vector3D position,
- final Vector3D occultingPosition,
- final double occultingRadius,
- final Vector3D occultedPosition,
- final double occultedRadius) {
- // Compute useful angles
- final double[] angle = getGeneralEclipseAngles(position, occultingPosition, occultingRadius, occultedPosition, occultedRadius);
- // Sat-Occulted/ Sat-Occulting angle
- final double occultedSatOcculting = angle[0];
- // Occulting apparent radius
- final double alphaOcculting = angle[1];
- // Occulted apparent radius
- final double alphaOcculted = angle[2];
- double result = 1.0;
- // Is the satellite in complete umbra ?
- if (occultedSatOcculting - alphaOcculting + alphaOcculted <= ANGULAR_MARGIN) {
- result = 0.0;
- } else if (occultedSatOcculting - alphaOcculting - alphaOcculted < -ANGULAR_MARGIN) {
- // Compute an eclipse ratio in penumbra
- final double sEA2 = occultedSatOcculting * occultedSatOcculting;
- final double oo2sEA = 1.0 / (2. * occultedSatOcculting);
- final double aS2 = alphaOcculted * alphaOcculted;
- final double aE2 = alphaOcculting * alphaOcculting;
- final double aE2maS2 = aE2 - aS2;
- final double alpha1 = (sEA2 - aE2maS2) * oo2sEA;
- final double alpha2 = (sEA2 + aE2maS2) * oo2sEA;
- // Protection against numerical inaccuracy at boundaries
- final double almost0 = Precision.SAFE_MIN;
- final double almost1 = FastMath.nextDown(1.0);
- final double a1oaS = FastMath.min(almost1, FastMath.max(-almost1, alpha1 / alphaOcculted));
- final double aS2ma12 = FastMath.max(almost0, aS2 - alpha1 * alpha1);
- final double a2oaE = FastMath.min(almost1, FastMath.max(-almost1, alpha2 / alphaOcculting));
- final double aE2ma22 = FastMath.max(almost0, aE2 - alpha2 * alpha2);
- final double P1 = aS2 * FastMath.acos(a1oaS) - alpha1 * FastMath.sqrt(aS2ma12);
- final double P2 = aE2 * FastMath.acos(a2oaE) - alpha2 * FastMath.sqrt(aE2ma22);
- result = 1. - (P1 + P2) / (FastMath.PI * aS2);
- }
- return result;
- }
- /** Get the total lighting ratio ([0-1]).
- * This method considers every occulting bodies.
- * @param position the satellite's position in the selected frame.
- * @param frame in which is defined the position
- * @param date the date
- * @return lighting ratio
- */
- public double getTotalLightingRatio(final Vector3D position, final Frame frame, final AbsoluteDate date) {
- double result = 0.0;
- final Map<ExtendedPVCoordinatesProvider, Double> otherOccultingBodies = getOtherOccultingBodies();
- final Vector3D sunPosition = sun.getPVCoordinates(date, frame).getPosition();
- final int n = otherOccultingBodies.size() + 1;
- if (n > 1) {
- final Vector3D[] occultingBodyPositions = new Vector3D[n];
- final double[] occultingBodyRadiuses = new double[n];
- // Central body
- occultingBodyPositions[0] = new Vector3D(0.0, 0.0, 0.0);
- occultingBodyRadiuses[0] = getEquatorialRadius();
- // Other occulting bodies
- int k = 1;
- for (Map.Entry<ExtendedPVCoordinatesProvider, Double> entry : otherOccultingBodies.entrySet()) {
- occultingBodyPositions[k] = entry.getKey().getPVCoordinates(date, frame).getPosition();
- occultingBodyRadiuses[k] = entry.getValue();
- ++k;
- }
- for (int i = 0; i < n; ++i) {
- // Lighting ratio computations
- final double eclipseRatioI = getGeneralEclipseRatio(position,
- occultingBodyPositions[i],
- occultingBodyRadiuses[i],
- sunPosition,
- Constants.SUN_RADIUS);
- // First body totaly occults Sun, full eclipse is occuring.
- if (eclipseRatioI == 0.0) {
- return 0.0;
- }
- result += eclipseRatioI;
- // Mutual occulting body eclipse ratio computations between first and secondary bodies
- for (int j = i + 1; j < n; ++j) {
- final double eclipseRatioJ = getGeneralEclipseRatio(position,
- occultingBodyPositions[j],
- occultingBodyRadiuses[j],
- sunPosition,
- Constants.SUN_RADIUS);
- final double eclipseRatioIJ = getGeneralEclipseRatio(position,
- occultingBodyPositions[i],
- occultingBodyRadiuses[i],
- occultingBodyPositions[j],
- occultingBodyRadiuses[j]);
- final double alphaJ = getGeneralEclipseAngles(position,
- occultingBodyPositions[i],
- occultingBodyRadiuses[i],
- occultingBodyPositions[j],
- occultingBodyRadiuses[j])[2];
- final double alphaSun = getEclipseAngles(sunPosition, position)[2];
- final double alphaJSq = alphaJ * alphaJ;
- final double alphaSunSq = alphaSun * alphaSun;
- final double mutualEclipseCorrection = (1 - eclipseRatioIJ) * alphaJSq / alphaSunSq;
- // Secondary body totally occults Sun, no more computations are required, full eclipse is occuring.
- if (eclipseRatioJ == 0.0 ) {
- return 0.0;
- }
- // Secondary body partially occults Sun
- else if (eclipseRatioJ != 1) {
- result -= mutualEclipseCorrection;
- }
- }
- }
- // Final term
- result -= n - 1;
- } else {
- // only central body is considered
- result = getLightingRatio(position, frame, date);
- }
- return result;
- }
- /** Get the lighting ratio ([0-1]).
- * Considers only central body as occulting body.
- * @param position the satellite's position in the selected frame.
- * @param frame in which is defined the position
- * @param date the date
- * @param <T> extends CalculusFieldElement
- * @return lighting ratio
- * @since 7.1
- */
- public <T extends CalculusFieldElement<T>> T getLightingRatio(final FieldVector3D<T> position,
- final Frame frame,
- final FieldAbsoluteDate<T> date) {
- final T one = date.getField().getOne();
- final FieldVector3D<T> sunPosition = sun.getPVCoordinates(date, frame).getPosition();
- if (sunPosition.getNorm().getReal() < 2 * Constants.SUN_RADIUS) {
- // we are in fact computing a trajectory around Sun (or solar system barycenter),
- // not around a planet,we consider lighting ratio is always 1
- return one;
- }
- // Compute useful angles
- final T[] angle = getEclipseAngles(sunPosition, position);
- // Sat-Sun / Sat-CentralBody angle
- final T sunsatCentralBodyAngle = angle[0];
- // Central Body apparent radius
- final T alphaCentral = angle[1];
- // Sun apparent radius
- final T alphaSun = angle[2];
- T result = one;
- // Is the satellite in complete umbra ?
- if (sunsatCentralBodyAngle.getReal() - alphaCentral.getReal() + alphaSun.getReal() <= ANGULAR_MARGIN) {
- result = date.getField().getZero();
- } else if (sunsatCentralBodyAngle.getReal() - alphaCentral.getReal() - alphaSun.getReal() < -ANGULAR_MARGIN) {
- // Compute a lighting ratio in penumbra
- final T sEA2 = sunsatCentralBodyAngle.multiply(sunsatCentralBodyAngle);
- final T oo2sEA = sunsatCentralBodyAngle.multiply(2).reciprocal();
- final T aS2 = alphaSun.multiply(alphaSun);
- final T aE2 = alphaCentral.multiply(alphaCentral);
- final T aE2maS2 = aE2.subtract(aS2);
- final T alpha1 = sEA2.subtract(aE2maS2).multiply(oo2sEA);
- final T alpha2 = sEA2.add(aE2maS2).multiply(oo2sEA);
- // Protection against numerical inaccuracy at boundaries
- final double almost0 = Precision.SAFE_MIN;
- final double almost1 = FastMath.nextDown(1.0);
- final T a1oaS = min(almost1, max(-almost1, alpha1.divide(alphaSun)));
- final T aS2ma12 = max(almost0, aS2.subtract(alpha1.multiply(alpha1)));
- final T a2oaE = min(almost1, max(-almost1, alpha2.divide(alphaCentral)));
- final T aE2ma22 = max(almost0, aE2.subtract(alpha2.multiply(alpha2)));
- final T P1 = aS2.multiply(a1oaS.acos()).subtract(alpha1.multiply(aS2ma12.sqrt()));
- final T P2 = aE2.multiply(a2oaE.acos()).subtract(alpha2.multiply(aE2ma22.sqrt()));
- result = one.subtract(P1.add(P2).divide(aS2.multiply(one.getPi())));
- }
- return result;
- }
- /** Get eclipse ratio between to bodies seen from a specific object.
- * Ratio is in [0-1].
- * @param position the satellite's position in the selected frame
- * @param occultingPosition the position of the occulting object
- * @param occultingRadius the mean radius of the occulting object
- * @param occultedPosition the position of the occulted object
- * @param occultedRadius the mean radius of the occulted object
- * @param <T> extends RealFieldElement
- * @return eclipse ratio
- */
- public <T extends CalculusFieldElement<T>> T getGeneralEclipseRatio(final FieldVector3D<T> position,
- final FieldVector3D<T> occultingPosition,
- final T occultingRadius,
- final FieldVector3D<T> occultedPosition,
- final T occultedRadius) {
- final T one = occultingRadius.getField().getOne();
- // Compute useful angles
- final T[] angle = getGeneralEclipseAngles(position, occultingPosition, occultingRadius, occultedPosition, occultedRadius);
- // Sat-Occulted/ Sat-Occulting angle
- final T occultedSatOcculting = angle[0];
- // Occulting apparent radius
- final T alphaOcculting = angle[1];
- // Occulted apparent radius
- final T alphaOcculted = angle[2];
- T result = one;
- // Is the satellite in complete umbra ?
- if (occultedSatOcculting.getReal() - alphaOcculting.getReal() + alphaOcculted.getReal() <= ANGULAR_MARGIN) {
- result = occultingRadius.getField().getZero();
- } else if (occultedSatOcculting.getReal() - alphaOcculting.getReal() - alphaOcculted.getReal() < -ANGULAR_MARGIN) {
- // Compute a lighting ratio in penumbra
- final T sEA2 = occultedSatOcculting.multiply(occultedSatOcculting);
- final T oo2sEA = occultedSatOcculting.multiply(2).reciprocal();
- final T aS2 = alphaOcculted.multiply(alphaOcculted);
- final T aE2 = alphaOcculting.multiply(alphaOcculting);
- final T aE2maS2 = aE2.subtract(aS2);
- final T alpha1 = sEA2.subtract(aE2maS2).multiply(oo2sEA);
- final T alpha2 = sEA2.add(aE2maS2).multiply(oo2sEA);
- // Protection against numerical inaccuracy at boundaries
- final double almost0 = Precision.SAFE_MIN;
- final double almost1 = FastMath.nextDown(1.0);
- final T a1oaS = min(almost1, max(-almost1, alpha1.divide(alphaOcculted)));
- final T aS2ma12 = max(almost0, aS2.subtract(alpha1.multiply(alpha1)));
- final T a2oaE = min(almost1, max(-almost1, alpha2.divide(alphaOcculting)));
- final T aE2ma22 = max(almost0, aE2.subtract(alpha2.multiply(alpha2)));
- final T P1 = aS2.multiply(a1oaS.acos()).subtract(alpha1.multiply(aS2ma12.sqrt()));
- final T P2 = aE2.multiply(a2oaE.acos()).subtract(alpha2.multiply(aE2ma22.sqrt()));
- result = one.subtract(P1.add(P2).divide(aS2.multiply(one.getPi())));
- }
- return result;
- }
- /** Get the total lighting ratio ([0-1]).
- * This method considers every occulting bodies.
- * @param position the satellite's position in the selected frame.
- * @param frame in which is defined the position
- * @param date the date
- * @param <T> extends RealFieldElement
- * @return lighting rati
- */
- public <T extends CalculusFieldElement<T>> T getTotalLightingRatio(final FieldVector3D<T> position, final Frame frame, final FieldAbsoluteDate<T> date) {
- final T zero = position.getAlpha().getField().getZero();
- T result = zero;
- final Map<ExtendedPVCoordinatesProvider, Double> otherOccultingBodies = getOtherOccultingBodies();
- final FieldVector3D<T> sunPosition = sun.getPVCoordinates(date, frame).getPosition();
- final int n = otherOccultingBodies.size() + 1;
- if (n > 1) {
- final List<FieldVector3D<T>> occultingBodyPositions = new ArrayList<FieldVector3D<T>>(n);
- final T[] occultingBodyRadiuses = MathArrays.buildArray(zero.getField(), n);
- // Central body
- occultingBodyPositions.add(0, new FieldVector3D<>(zero, zero, zero));
- occultingBodyRadiuses[0] = zero.add(getEquatorialRadius());
- // Other occulting bodies
- int k = 1;
- for (Map.Entry<ExtendedPVCoordinatesProvider, Double> entry: otherOccultingBodies.entrySet()) {
- occultingBodyPositions.add(k, entry.getKey().getPVCoordinates(date, frame).getPosition());
- occultingBodyRadiuses[k] = zero.newInstance(entry.getValue());
- ++k;
- }
- for (int i = 0; i < n; ++i) {
- // Lighting ratio computations
- final T eclipseRatioI = getGeneralEclipseRatio(position,
- occultingBodyPositions.get(i),
- occultingBodyRadiuses[i],
- sunPosition,
- zero.add(Constants.SUN_RADIUS));
- // First body totally occults Sun, full eclipse is occuring.
- if (eclipseRatioI.getReal() == 0.0) {
- return zero;
- }
- result = result.add(eclipseRatioI);
- // Mutual occulting body eclipse ratio computations between first and secondary bodies
- for (int j = i + 1; j < n; ++j) {
- final T eclipseRatioJ = getGeneralEclipseRatio(position,
- occultingBodyPositions.get(i),
- occultingBodyRadiuses[j],
- sunPosition,
- zero.add(Constants.SUN_RADIUS));
- final T eclipseRatioIJ = getGeneralEclipseRatio(position,
- occultingBodyPositions.get(i),
- occultingBodyRadiuses[i],
- occultingBodyPositions.get(j),
- occultingBodyRadiuses[j]);
- final T alphaJ = getGeneralEclipseAngles(position,
- occultingBodyPositions.get(i),
- occultingBodyRadiuses[i],
- occultingBodyPositions.get(j),
- occultingBodyRadiuses[j])[2];
- final T alphaSun = getEclipseAngles(sunPosition, position)[2];
- final T alphaJSq = alphaJ.multiply(alphaJ);
- final T alphaSunSq = alphaSun.multiply(alphaSun);
- final T mutualEclipseCorrection = eclipseRatioIJ.negate().add(1).multiply(alphaJSq).divide(alphaSunSq);
- // Secondary body totaly occults Sun, no more computations are required, full eclipse is occuring.
- if (eclipseRatioJ.getReal() == 0.0 ) {
- return zero;
- }
- // Secondary body partially occults Sun
- else if (eclipseRatioJ.getReal() != 1) {
- result = result.subtract(mutualEclipseCorrection);
- }
- }
- }
- // Final term
- result = result.subtract(n - 1);
- } else {
- // only central body is considered
- result = getLightingRatio(position, frame, date);
- }
- return result;
- }
- /** {@inheritDoc} */
- @Override
- public List<ParameterDriver> getParametersDrivers() {
- return spacecraft.getRadiationParametersDrivers();
- }
- /** Compute min of two values, one double and one field element.
- * @param d double value
- * @param f field element
- * @param <T> type fo the field elements
- * @return min value
- */
- private <T extends CalculusFieldElement<T>> T min(final double d, final T f) {
- return (f.getReal() > d) ? f.getField().getZero().newInstance(d) : f;
- }
- /** Compute max of two values, one double and one field element.
- * @param d double value
- * @param f field element
- * @param <T> type fo the field elements
- * @return max value
- */
- private <T extends CalculusFieldElement<T>> T max(final double d, final T f) {
- return (f.getReal() <= d) ? f.getField().getZero().newInstance(d) : f;
- }
- }