FieldTLEPropagator.java
/* Copyright 2002-2023 CS GROUP
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* 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
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*
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* Unless required by applicable law or agreed to in writing, software
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package org.orekit.propagation.analytical.tle;
import java.util.List;
import org.hipparchus.CalculusFieldElement;
import org.hipparchus.geometry.euclidean.threed.FieldVector3D;
import org.hipparchus.util.FastMath;
import org.hipparchus.util.MathUtils;
import org.orekit.annotation.DefaultDataContext;
import org.orekit.attitudes.AttitudeProvider;
import org.orekit.attitudes.FieldAttitude;
import org.orekit.attitudes.FrameAlignedProvider;
import org.orekit.data.DataContext;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitMessages;
import org.orekit.frames.Frame;
import org.orekit.orbits.FieldCartesianOrbit;
import org.orekit.orbits.FieldOrbit;
import org.orekit.propagation.FieldSpacecraftState;
import org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator;
import org.orekit.propagation.analytical.tle.generation.TleGenerationAlgorithm;
import org.orekit.time.FieldAbsoluteDate;
import org.orekit.time.TimeScale;
import org.orekit.utils.FieldPVCoordinates;
import org.orekit.utils.PVCoordinates;
import org.orekit.utils.ParameterDriver;
/** This class provides elements to propagate TLE's.
* <p>
* The models used are SGP4 and SDP4, initially proposed by NORAD as the unique convenient
* propagator for TLE's. Inputs and outputs of this propagator are only suited for
* NORAD two lines elements sets, since it uses estimations and mean values appropriate
* for TLE's only.
* </p>
* <p>
* Deep- or near- space propagator is selected internally according to NORAD recommendations
* so that the user has not to worry about the used computation methods. One instance is created
* for each TLE (this instance can only be get using {@link #selectExtrapolator(FieldTLE, CalculusFieldElement[])} method,
* and can compute {@link PVCoordinates position and velocity coordinates} at any
* time. Maximum accuracy is guaranteed in a 24h range period before and after the provided
* TLE epoch (of course this accuracy is not really measurable nor predictable: according to
* <a href="https://www.celestrak.com/">CelesTrak</a>, the precision is close to one kilometer
* and error won't probably rise above 2 km).
* </p>
* <p>This implementation is largely inspired from the paper and source code <a
* href="https://www.celestrak.com/publications/AIAA/2006-6753/">Revisiting Spacetrack
* Report #3</a> and is fully compliant with its results and tests cases.</p>
* @author Felix R. Hoots, Ronald L. Roehrich, December 1980 (original fortran)
* @author David A. Vallado, Paul Crawford, Richard Hujsak, T.S. Kelso (C++ translation and improvements)
* @author Fabien Maussion (java translation)
* @author Thomas Paulet (field translation)
* @since 11.0
* @see FieldTLE
* @param <T> type of the field elements
*/
public abstract class FieldTLEPropagator<T extends CalculusFieldElement<T>> extends FieldAbstractAnalyticalPropagator<T> {
// CHECKSTYLE: stop VisibilityModifier check
/** Initial state. */
protected FieldTLE<T> tle;
/** UTC time scale. */
protected final TimeScale utc;
/** final RAAN. */
protected T xnode;
/** final semi major axis. */
protected T a;
/** final eccentricity. */
protected T e;
/** final inclination. */
protected T i;
/** final perigee argument. */
protected T omega;
/** L from SPTRCK #3. */
protected T xl;
/** original recovered semi major axis. */
protected T a0dp;
/** original recovered mean motion. */
protected T xn0dp;
/** cosinus original inclination. */
protected T cosi0;
/** cos io squared. */
protected T theta2;
/** sinus original inclination. */
protected T sini0;
/** common parameter for mean anomaly (M) computation. */
protected T xmdot;
/** common parameter for perigee argument (omega) computation. */
protected T omgdot;
/** common parameter for raan (OMEGA) computation. */
protected T xnodot;
/** original eccentricity squared. */
protected T e0sq;
/** 1 - e2. */
protected T beta02;
/** sqrt (1 - e2). */
protected T beta0;
/** perigee, expressed in KM and ALTITUDE. */
protected T perige;
/** eta squared. */
protected T etasq;
/** original eccentricity * eta. */
protected T eeta;
/** s* new value for the contant s. */
protected T s4;
/** tsi from SPTRCK #3. */
protected T tsi;
/** eta from SPTRCK #3. */
protected T eta;
/** coef for SGP C3 computation. */
protected T coef;
/** coef for SGP C5 computation. */
protected T coef1;
/** C1 from SPTRCK #3. */
protected T c1;
/** C2 from SPTRCK #3. */
protected T c2;
/** C4 from SPTRCK #3. */
protected T c4;
/** common parameter for raan (OMEGA) computation. */
protected T xnodcf;
/** 3/2 * C1. */
protected T t2cof;
// CHECKSTYLE: resume VisibilityModifier check
/** TLE frame. */
private final Frame teme;
/** Spacecraft mass (kg). */
private final T mass;
/** Protected constructor for derived classes.
*
* <p>This constructor uses the {@link DataContext#getDefault() default data context}.
*
* @param initialTLE the unique TLE to propagate
* @param attitudeProvider provider for attitude computation
* @param mass spacecraft mass (kg)
* @param parameters SGP4 and SDP4 model parameters
* @see #FieldTLEPropagator(FieldTLE, AttitudeProvider, CalculusFieldElement, Frame, CalculusFieldElement[])
*/
@DefaultDataContext
protected FieldTLEPropagator(final FieldTLE<T> initialTLE,
final AttitudeProvider attitudeProvider,
final T mass,
final T[] parameters) {
this(initialTLE, attitudeProvider, mass,
DataContext.getDefault().getFrames().getTEME(), parameters);
}
/** Protected constructor for derived classes.
* @param initialTLE the unique TLE to propagate
* @param attitudeProvider provider for attitude computation
* @param mass spacecraft mass (kg)
* @param teme the TEME frame to use for propagation.
* @param parameters SGP4 and SDP4 model parameters
*/
protected FieldTLEPropagator(final FieldTLE<T> initialTLE,
final AttitudeProvider attitudeProvider,
final T mass,
final Frame teme,
final T[] parameters) {
super(initialTLE.getE().getField(), attitudeProvider);
setStartDate(initialTLE.getDate());
this.tle = initialTLE;
this.teme = teme;
this.mass = mass;
this.utc = initialTLE.getUtc();
initializeCommons(parameters);
sxpInitialize(parameters);
// set the initial state
final FieldOrbit<T> orbit = propagateOrbit(initialTLE.getDate(), parameters);
final FieldAttitude<T> attitude = attitudeProvider.getAttitude(orbit, orbit.getDate(), orbit.getFrame());
super.resetInitialState(new FieldSpacecraftState<>(orbit, attitude, mass));
}
/** Selects the extrapolator to use with the selected TLE.
*
* <p>This method uses the {@link DataContext#getDefault() default data context}.
*
* @param tle the TLE to propagate.
* @param parameters SGP4 and SDP4 model parameters
* @return the correct propagator.
* @param <T> elements type
* @see #selectExtrapolator(FieldTLE, Frame, CalculusFieldElement[])
*/
@DefaultDataContext
public static <T extends CalculusFieldElement<T>> FieldTLEPropagator<T> selectExtrapolator(final FieldTLE<T> tle, final T[] parameters) {
return selectExtrapolator(tle, DataContext.getDefault().getFrames().getTEME(), parameters);
}
/** Selects the extrapolator to use with the selected TLE.
*
*<p>This method uses the {@link DataContext#getDefault() default data context}.
*
* @param tle the TLE to propagate.
* @param teme TEME frame.
* @param parameters SGP4 and SDP4 model parameters
* @return the correct propagator.
* @param <T> elements type
*/
public static <T extends CalculusFieldElement<T>> FieldTLEPropagator<T> selectExtrapolator(final FieldTLE<T> tle, final Frame teme, final T[] parameters) {
return selectExtrapolator(
tle,
FrameAlignedProvider.of(teme),
tle.getE().getField().getZero().add(DEFAULT_MASS),
teme,
parameters);
}
/** Selects the extrapolator to use with the selected TLE.
*
* <p>This method uses the {@link DataContext#getDefault() default data context}.
*
* @param tle the TLE to propagate.
* @param attitudeProvider provider for attitude computation
* @param mass spacecraft mass (kg)
* @param parameters SGP4 and SDP4 model parameters
* @return the correct propagator.
* @param <T> elements type
* @see #selectExtrapolator(FieldTLE, AttitudeProvider, CalculusFieldElement, Frame, CalculusFieldElement[])
*/
@DefaultDataContext
public static <T extends CalculusFieldElement<T>> FieldTLEPropagator<T> selectExtrapolator(final FieldTLE<T> tle,
final AttitudeProvider attitudeProvider,
final T mass,
final T[] parameters) {
return selectExtrapolator(tle, attitudeProvider, mass,
DataContext.getDefault().getFrames().getTEME(), parameters);
}
/** Selects the extrapolator to use with the selected TLE.
*
* @param tle the TLE to propagate.
* @param attitudeProvider provider for attitude computation
* @param mass spacecraft mass (kg)
* @param teme the TEME frame to use for propagation.
* @param parameters SGP4 and SDP4 model parameters
* @return the correct propagator.
* @param <T> elements type
*/
public static <T extends CalculusFieldElement<T>> FieldTLEPropagator<T> selectExtrapolator(final FieldTLE<T> tle,
final AttitudeProvider attitudeProvider,
final T mass,
final Frame teme,
final T[] parameters) {
final T a1 = tle.getMeanMotion().multiply(60.0).reciprocal().multiply(TLEConstants.XKE).pow(TLEConstants.TWO_THIRD);
final T cosi0 = FastMath.cos(tle.getI());
final T temp1 = cosi0.multiply(cosi0.multiply(3.0)).subtract(1.0).multiply(1.5 * TLEConstants.CK2);
final T temp2 = tle.getE().multiply(tle.getE()).negate().add(1.0).pow(-1.5);
final T temp = temp1.multiply(temp2);
final T delta1 = temp.divide(a1.multiply(a1));
final T a0 = a1.multiply(delta1.multiply(delta1.multiply(
delta1.multiply(134.0 / 81.0).add(1.0)).add(TLEConstants.ONE_THIRD)).negate().add(1.0));
final T delta0 = temp.divide(a0.multiply(a0));
// recover original mean motion :
final T xn0dp = tle.getMeanMotion().multiply(60.0).divide(delta0.add(1.0));
// Period >= 225 minutes is deep space
if (MathUtils.TWO_PI / (xn0dp.multiply(TLEConstants.MINUTES_PER_DAY).getReal()) >= (1.0 / 6.4)) {
return new FieldDeepSDP4<>(tle, attitudeProvider, mass, teme, parameters);
} else {
return new FieldSGP4<>(tle, attitudeProvider, mass, teme, parameters);
}
}
/** Get the Earth gravity coefficient used for TLE propagation.
* @return the Earth gravity coefficient.
*/
public static double getMU() {
return TLEConstants.MU;
}
/** Get the extrapolated position and velocity from an initial TLE.
* @param date the final date
* @param parameters values of the model
* @return the final PVCoordinates
*/
public FieldPVCoordinates<T> getPVCoordinates(final FieldAbsoluteDate<T> date, final T[] parameters) {
sxpPropagate(date.durationFrom(tle.getDate()).divide(60.0), parameters);
// Compute PV with previous calculated parameters
return computePVCoordinates();
}
/** Computation of the first commons parameters.
* @param parameters SGP4 and SDP4 model parameters
*/
private void initializeCommons(final T[] parameters) {
final T zero = mass.getField().getZero();
final T bStar = parameters[0];
final T a1 = tle.getMeanMotion().multiply(60.0).reciprocal().multiply(TLEConstants.XKE).pow(TLEConstants.TWO_THIRD);
cosi0 = FastMath.cos(tle.getI());
theta2 = cosi0.multiply(cosi0);
final T x3thm1 = theta2.multiply(3.0).subtract(1.0);
e0sq = tle.getE().multiply(tle.getE());
beta02 = e0sq.negate().add(1.0);
beta0 = FastMath.sqrt(beta02);
final T tval = x3thm1.multiply(1.5 * TLEConstants.CK2).divide(beta0.multiply(beta02));
final T delta1 = tval.divide(a1.multiply(a1));
final T a0 = a1.multiply(delta1.multiply(
delta1.multiply(134.0 / 81.0).add(1.0).multiply(delta1).add(TLEConstants.ONE_THIRD)).negate().add(1.0));
final T delta0 = tval.divide(a0.multiply(a0));
// recover original mean motion and semi-major axis :
xn0dp = tle.getMeanMotion().multiply(60.0).divide(delta0.add(1.0));
a0dp = a0.divide(delta0.negate().add(1.0));
// Values of s and qms2t :
s4 = zero.add(TLEConstants.S); // unmodified value for s
T q0ms24 = zero.add(TLEConstants.QOMS2T); // unmodified value for q0ms2T
perige = a0dp.multiply(tle.getE().negate().add(1.0)).subtract(TLEConstants.NORMALIZED_EQUATORIAL_RADIUS).multiply(
TLEConstants.EARTH_RADIUS); // perige
// For perigee below 156 km, the values of s and qoms2t are changed :
if (perige.getReal() < 156.0) {
if (perige.getReal() <= 98.0) {
s4 = zero.add(20.0);
} else {
s4 = perige.subtract(78.0);
}
final T temp_val = s4.negate().add(120.0).multiply(TLEConstants.NORMALIZED_EQUATORIAL_RADIUS / TLEConstants.EARTH_RADIUS);
final T temp_val_squared = temp_val.multiply(temp_val);
q0ms24 = temp_val_squared.multiply(temp_val_squared);
s4 = s4.divide(TLEConstants.EARTH_RADIUS).add(TLEConstants.NORMALIZED_EQUATORIAL_RADIUS); // new value for q0ms2T and s
}
final T pinv = a0dp.multiply(beta02).reciprocal();
final T pinvsq = pinv.multiply(pinv);
tsi = a0dp.subtract(s4).reciprocal();
eta = a0dp.multiply(tle.getE()).multiply(tsi);
etasq = eta.multiply(eta);
eeta = tle.getE().multiply(eta);
final T psisq = etasq.negate().add(1.0).abs(); // abs because pow 3.5 needs positive value
final T tsi_squared = tsi.multiply(tsi);
coef = q0ms24.multiply(tsi_squared.multiply(tsi_squared));
coef1 = coef.divide(psisq.pow(3.5));
// C2 and C1 coefficients computation :
c2 = coef1.multiply(xn0dp).multiply(a0dp.multiply(
etasq.multiply(1.5).add(eeta.multiply(etasq.add(4.0))).add(1.0)).add(
tsi.divide(psisq).multiply(x3thm1).multiply(0.75 * TLEConstants.CK2).multiply(
etasq.multiply(etasq.add(8.0)).multiply(3.0).add(8.0))));
c1 = bStar.multiply(c2);
sini0 = FastMath.sin(tle.getI());
final T x1mth2 = theta2.negate().add(1.0);
// C4 coefficient computation :
c4 = xn0dp.multiply(coef1).multiply(a0dp).multiply(2.0).multiply(beta02).multiply(
eta.multiply(etasq.multiply(0.5).add(2.0)).add(tle.getE().multiply(etasq.multiply(2.0).add(0.5))).subtract(
tsi.divide(a0dp.multiply(psisq)).multiply(2 * TLEConstants.CK2).multiply(
x3thm1.multiply(-3).multiply(etasq.multiply(eeta.multiply(-0.5).add(1.5)).add(eeta.multiply(-2.0)).add(1.0)).add(
x1mth2.multiply(0.75).multiply(etasq.multiply(2.0).subtract(eeta.multiply(etasq.add(1.0)))).multiply(FastMath.cos(tle.getPerigeeArgument().multiply(2.0)))))));
final T theta4 = theta2.multiply(theta2);
final T temp1 = pinvsq.multiply(xn0dp).multiply(3 * TLEConstants.CK2);
final T temp2 = temp1.multiply(pinvsq).multiply(TLEConstants.CK2);
final T temp3 = pinvsq.multiply(pinvsq).multiply(xn0dp).multiply(1.25 * TLEConstants.CK4);
// atmospheric and gravitation coefs :(Mdf and OMEGAdf)
xmdot = xn0dp.add(
temp1.multiply(0.5).multiply(beta0).multiply(x3thm1)).add(
temp2.multiply(0.0625).multiply(beta0).multiply(
theta2.multiply(78.0).negate().add(13.0).add(theta4.multiply(137.0))));
final T x1m5th = theta2.multiply(5.0).negate().add(1.0);
omgdot = temp1.multiply(-0.5).multiply(x1m5th).add(
temp2.multiply(0.0625).multiply(theta2.multiply(114.0).negate().add(
theta4.multiply(395.0)).add(7.0))).add(
temp3.multiply(theta2.multiply(36.0).negate().add(theta4.multiply(49.0)).add(3.0)));
final T xhdot1 = temp1.negate().multiply(cosi0);
xnodot = xhdot1.add(temp2.multiply(0.5).multiply(theta2.multiply(19.0).negate().add(4.0)).add(
temp3.multiply(2.0).multiply(theta2.multiply(7.0).negate().add(3.0))).multiply(cosi0));
xnodcf = beta02.multiply(xhdot1).multiply(c1).multiply(3.5);
t2cof = c1.multiply(1.5);
}
/** Retrieves the position and velocity.
* @return the computed PVCoordinates.
*/
private FieldPVCoordinates<T> computePVCoordinates() {
final T zero = mass.getField().getZero();
// Long period periodics
final T axn = e.multiply(FastMath.cos(omega));
T temp = a.multiply(e.multiply(e).negate().add(1.0)).reciprocal();
final T xlcof = sini0.multiply(0.125 * TLEConstants.A3OVK2).multiply(
cosi0.multiply(5.0).add(3.0).divide(cosi0.add(1.0)));
final T aycof = sini0.multiply(0.25 * TLEConstants.A3OVK2);
final T xll = temp.multiply(xlcof).multiply(axn);
final T aynl = temp.multiply(aycof);
final T xlt = xl.add(xll);
final T ayn = e.multiply(FastMath.sin(omega)).add(aynl);
final T elsq = axn.multiply(axn).add(ayn.multiply(ayn));
final T capu = MathUtils.normalizeAngle(xlt.subtract(xnode), zero.getPi());
T epw = capu;
T ecosE = zero;
T esinE = zero;
T sinEPW = zero;
T cosEPW = zero;
// Dundee changes: items dependent on cosio get recomputed:
final T cosi0Sq = cosi0.multiply(cosi0);
final T x3thm1 = cosi0Sq.multiply(3.0).subtract(1.0);
final T x1mth2 = cosi0Sq.negate().add(1.0);
final T x7thm1 = cosi0Sq.multiply(7.0).subtract(1.0);
if (e.getReal() > (1 - 1e-6)) {
throw new OrekitException(OrekitMessages.TOO_LARGE_ECCENTRICITY_FOR_PROPAGATION_MODEL, e);
}
// Solve Kepler's' Equation.
final double newtonRaphsonEpsilon = 1e-12;
for (int j = 0; j < 10; j++) {
boolean doSecondOrderNewtonRaphson = true;
sinEPW = FastMath.sin( epw);
cosEPW = FastMath.cos( epw);
ecosE = axn.multiply(cosEPW).add(ayn.multiply(sinEPW));
esinE = axn.multiply(sinEPW).subtract(ayn.multiply(cosEPW));
final T f = capu.subtract(epw).add(esinE);
if (FastMath.abs(f.getReal()) < newtonRaphsonEpsilon) {
break;
}
final T fdot = ecosE.negate().add(1.0);
T delta_epw = f.divide(fdot);
if (j == 0) {
final T maxNewtonRaphson = e.abs().multiply(1.25);
doSecondOrderNewtonRaphson = false;
if (delta_epw.getReal() > maxNewtonRaphson.getReal()) {
delta_epw = maxNewtonRaphson;
} else if (delta_epw.getReal() < -maxNewtonRaphson.getReal()) {
delta_epw = maxNewtonRaphson.negate();
} else {
doSecondOrderNewtonRaphson = true;
}
}
if (doSecondOrderNewtonRaphson) {
delta_epw = f.divide(fdot.add(esinE.multiply(0.5).multiply(delta_epw)));
}
epw = epw.add(delta_epw);
}
// Short period preliminary quantities
temp = elsq.negate().add(1.0);
final T pl = a.multiply(temp);
final T r = a.multiply(ecosE.negate().add(1.0));
T temp2 = a.divide(r);
final T betal = FastMath.sqrt(temp);
temp = esinE.divide(betal.add(1.0));
final T cosu = temp2.multiply(cosEPW.subtract(axn).add(ayn.multiply(temp)));
final T sinu = temp2.multiply(sinEPW.subtract(ayn).subtract(axn.multiply(temp)));
final T u = FastMath.atan2(sinu, cosu);
final T sin2u = sinu.multiply(cosu).multiply(2.0);
final T cos2u = cosu.multiply(cosu).multiply(2.0).subtract(1.0);
final T temp1 = pl.reciprocal().multiply(TLEConstants.CK2);
temp2 = temp1.divide(pl);
// Update for short periodics
final T rk = r.multiply(temp2.multiply(betal).multiply(x3thm1).multiply(-1.5).add(1.0)).add(
temp1.multiply(x1mth2).multiply(cos2u).multiply(0.5));
final T uk = u.subtract(temp2.multiply(x7thm1).multiply(sin2u).multiply(0.25));
final T xnodek = xnode.add(temp2.multiply(cosi0).multiply(sin2u).multiply(1.5));
final T xinck = i.add(temp2.multiply(cosi0).multiply(sini0).multiply(cos2u).multiply(1.5));
// Orientation vectors
final T sinuk = FastMath.sin(uk);
final T cosuk = FastMath.cos(uk);
final T sinik = FastMath.sin(xinck);
final T cosik = FastMath.cos(xinck);
final T sinnok = FastMath.sin(xnodek);
final T cosnok = FastMath.cos(xnodek);
final T xmx = sinnok.negate().multiply(cosik);
final T xmy = cosnok.multiply(cosik);
final T ux = xmx.multiply(sinuk).add(cosnok.multiply(cosuk));
final T uy = xmy.multiply(sinuk).add(sinnok.multiply(cosuk));
final T uz = sinik.multiply(sinuk);
// Position and velocity
final T cr = rk.multiply(1000 * TLEConstants.EARTH_RADIUS);
final FieldVector3D<T> pos = new FieldVector3D<>(cr.multiply(ux), cr.multiply(uy), cr.multiply(uz));
final T rdot = FastMath.sqrt(a).multiply(esinE.divide(r)).multiply(TLEConstants.XKE);
final T rfdot = FastMath.sqrt(pl).divide(r).multiply(TLEConstants.XKE);
final T xn = a.multiply(FastMath.sqrt(a)).reciprocal().multiply(TLEConstants.XKE);
final T rdotk = rdot.subtract(xn.multiply(temp1).multiply(x1mth2).multiply(sin2u));
final T rfdotk = rfdot.add(xn.multiply(temp1).multiply(x1mth2.multiply(cos2u).add(x3thm1.multiply(1.5))));
final T vx = xmx.multiply(cosuk).subtract(cosnok.multiply(sinuk));
final T vy = xmy.multiply(cosuk).subtract(sinnok.multiply(sinuk));
final T vz = sinik.multiply(cosuk);
final double cv = 1000.0 * TLEConstants.EARTH_RADIUS / 60.0;
final FieldVector3D<T> vel = new FieldVector3D<>(rdotk.multiply(ux).add(rfdotk.multiply(vx)).multiply(cv),
rdotk.multiply(uy).add(rfdotk.multiply(vy)).multiply(cv),
rdotk.multiply(uz).add(rfdotk.multiply(vz)).multiply(cv));
return new FieldPVCoordinates<T>(pos, vel);
}
/** {@inheritDoc} */
@Override
public List<ParameterDriver> getParametersDrivers() {
return tle.getParametersDrivers();
}
/** Initialization proper to each propagator (SGP or SDP).
* @param parameters model parameters
*/
protected abstract void sxpInitialize(T[] parameters);
/** Propagation proper to each propagator (SGP or SDP).
* @param t the offset from initial epoch (min)
* @param parameters model parameters
*/
protected abstract void sxpPropagate(T t, T[] parameters);
/** {@inheritDoc}
* <p>
* For TLE propagator, calling this method is only recommended
* for covariance propagation when the new <code>state</code>
* differs from the previous one by only adding the additional
* state containing the derivatives.
* </p>
*/
public void resetInitialState(final FieldSpacecraftState<T> state) {
super.resetInitialState(state);
super.setStartDate(state.getDate());
final TleGenerationAlgorithm algorithm = TLEPropagator.getDefaultTleGenerationAlgorithm(utc, teme);
final FieldTLE<T> newTLE = algorithm.generate(state, tle);
this.tle = newTLE;
initializeCommons(tle.getParameters(state.getDate().getField()));
sxpInitialize(tle.getParameters(state.getDate().getField()));
}
/** {@inheritDoc} */
protected void resetIntermediateState(final FieldSpacecraftState<T> state, final boolean forward) {
throw new OrekitException(OrekitMessages.NON_RESETABLE_STATE);
}
/** {@inheritDoc} */
protected T getMass(final FieldAbsoluteDate<T> date) {
return mass;
}
/** {@inheritDoc} */
public FieldOrbit<T> propagateOrbit(final FieldAbsoluteDate<T> date, final T[] parameters) {
return new FieldCartesianOrbit<>(getPVCoordinates(date, parameters), teme, date, date.getField().getZero().add(TLEConstants.MU));
}
/** Get the underlying TLE.
* @return underlying TLE
*/
public FieldTLE<T> getTLE() {
return tle;
}
/** {@inheritDoc} */
public Frame getFrame() {
return teme;
}
}