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OREKIT (ORbits Extrapolation KIT) is a low level space dynamics library.
It provides basic elements (orbits, dates, attitude, frames ...) and
various algorithms to handle them (conversions, analytical and numerical
propagation, pointing ...).
/* Copyright 2002-2021 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.propagation;
import java.io.Serializable;
import java.util.ArrayList;
import java.util.Collections;
import java.util.HashMap;
import java.util.List;
import java.util.Map;
import java.util.stream.Stream;
import org.hipparchus.analysis.interpolation.HermiteInterpolator;
import org.hipparchus.exception.LocalizedCoreFormats;
import org.hipparchus.exception.MathIllegalStateException;
import org.hipparchus.geometry.euclidean.threed.Rotation;
import org.hipparchus.geometry.euclidean.threed.Vector3D;
import org.hipparchus.util.FastMath;
import org.orekit.attitudes.Attitude;
import org.orekit.attitudes.LofOffset;
import org.orekit.errors.OrekitException;
import org.orekit.errors.OrekitIllegalArgumentException;
import org.orekit.errors.OrekitIllegalStateException;
import org.orekit.errors.OrekitMessages;
import org.orekit.frames.Frame;
import org.orekit.frames.LOFType;
import org.orekit.frames.Transform;
import org.orekit.orbits.Orbit;
import org.orekit.time.AbsoluteDate;
import org.orekit.time.TimeInterpolable;
import org.orekit.time.TimeShiftable;
import org.orekit.time.TimeStamped;
import org.orekit.utils.AbsolutePVCoordinates;
import org.orekit.utils.TimeStampedAngularCoordinates;
import org.orekit.utils.TimeStampedPVCoordinates;
/** This class is the representation of a complete state holding orbit, attitude
* and mass information at a given date.
*
* It contains an {@link Orbit orbital state} at a current
* {@link AbsoluteDate} both handled by an {@link Orbit}, plus the current
* mass and attitude. Orbit and state are guaranteed to be consistent in terms
* of date and reference frame. The spacecraft state may also contain additional
* states, which are simply named double arrays which can hold any user-defined
* data.
*
*
* The state can be slightly shifted to close dates. This shift is based on
* a simple Keplerian model for orbit, a linear extrapolation for attitude
* taking the spin rate into account and no mass change. It is not
* intended as a replacement for proper orbit and attitude propagation but
* should be sufficient for either small time shifts or coarse accuracy.
*
*
* The instance SpacecraftState is guaranteed to be immutable.
*
* @see org.orekit.propagation.numerical.NumericalPropagator
* @author Fabien Maussion
* @author Véronique Pommier-Maurussane
* @author Luc Maisonobe
*/
public class SpacecraftState
implements TimeStamped, TimeShiftable, TimeInterpolable, Serializable {
/** Serializable UID. */
private static final long serialVersionUID = 20130407L;
/** Default mass. */
private static final double DEFAULT_MASS = 1000.0;
/**
* tolerance on date comparison in {@link #checkConsistency(Orbit, Attitude)}. 100 ns
* corresponds to sub-mm accuracy at LEO orbital velocities.
*/
private static final double DATE_INCONSISTENCY_THRESHOLD = 100e-9;
/** Orbital state. */
private final Orbit orbit;
/** Trajectory state, when it is not an orbit. */
private final AbsolutePVCoordinates absPva;
/** Attitude. */
private final Attitude attitude;
/** Current mass (kg). */
private final double mass;
/** Additional states. */
private final Map additional;
/** Build a spacecraft state from orbit only.
* Attitude and mass are set to unspecified non-null arbitrary values.
* @param orbit the orbit
*/
public SpacecraftState(final Orbit orbit) {
this(orbit,
new LofOffset(orbit.getFrame(), LOFType.LVLH_CCSDS).getAttitude(orbit, orbit.getDate(), orbit.getFrame()),
DEFAULT_MASS, null);
}
/** Build a spacecraft state from orbit and attitude provider.
* Mass is set to an unspecified non-null arbitrary value.
* @param orbit the orbit
* @param attitude attitude
* @exception IllegalArgumentException if orbit and attitude dates
* or frames are not equal
*/
public SpacecraftState(final Orbit orbit, final Attitude attitude)
throws IllegalArgumentException {
this(orbit, attitude, DEFAULT_MASS, null);
}
/** Create a new instance from orbit and mass.
* Attitude law is set to an unspecified default attitude.
* @param orbit the orbit
* @param mass the mass (kg)
*/
public SpacecraftState(final Orbit orbit, final double mass) {
this(orbit,
new LofOffset(orbit.getFrame(), LOFType.LVLH_CCSDS).getAttitude(orbit, orbit.getDate(), orbit.getFrame()),
mass, null);
}
/** Build a spacecraft state from orbit, attitude provider and mass.
* @param orbit the orbit
* @param attitude attitude
* @param mass the mass (kg)
* @exception IllegalArgumentException if orbit and attitude dates
* or frames are not equal
*/
public SpacecraftState(final Orbit orbit, final Attitude attitude, final double mass)
throws IllegalArgumentException {
this(orbit, attitude, mass, null);
}
/** Build a spacecraft state from orbit only.
* Attitude and mass are set to unspecified non-null arbitrary values.
* @param orbit the orbit
* @param additional additional states
*/
public SpacecraftState(final Orbit orbit, final Map additional) {
this(orbit,
new LofOffset(orbit.getFrame(), LOFType.LVLH_CCSDS).getAttitude(orbit, orbit.getDate(), orbit.getFrame()),
DEFAULT_MASS, additional);
}
/** Build a spacecraft state from orbit and attitude provider.
* Mass is set to an unspecified non-null arbitrary value.
* @param orbit the orbit
* @param attitude attitude
* @param additional additional states
* @exception IllegalArgumentException if orbit and attitude dates
* or frames are not equal
*/
public SpacecraftState(final Orbit orbit, final Attitude attitude, final Map additional)
throws IllegalArgumentException {
this(orbit, attitude, DEFAULT_MASS, additional);
}
/** Create a new instance from orbit and mass.
* Attitude law is set to an unspecified default attitude.
* @param orbit the orbit
* @param mass the mass (kg)
* @param additional additional states
*/
public SpacecraftState(final Orbit orbit, final double mass, final Map additional) {
this(orbit,
new LofOffset(orbit.getFrame(), LOFType.LVLH_CCSDS).getAttitude(orbit, orbit.getDate(), orbit.getFrame()),
mass, additional);
}
/** Build a spacecraft state from orbit, attitude provider and mass.
* @param orbit the orbit
* @param attitude attitude
* @param mass the mass (kg)
* @param additional additional states (may be null if no additional states are available)
* @exception IllegalArgumentException if orbit and attitude dates
* or frames are not equal
*/
public SpacecraftState(final Orbit orbit, final Attitude attitude,
final double mass, final Map additional)
throws IllegalArgumentException {
checkConsistency(orbit, attitude);
this.orbit = orbit;
this.absPva = null;
this.attitude = attitude;
this.mass = mass;
if (additional == null) {
this.additional = Collections.emptyMap();
} else {
this.additional = new HashMap(additional.size());
for (final Map.Entry entry : additional.entrySet()) {
this.additional.put(entry.getKey(), entry.getValue().clone());
}
}
}
/** Build a spacecraft state from orbit only.
* Attitude and mass are set to unspecified non-null arbitrary values.
* @param absPva position-velocity-acceleration
*/
public SpacecraftState(final AbsolutePVCoordinates absPva) {
this(absPva,
new LofOffset(absPva.getFrame(), LOFType.LVLH_CCSDS).getAttitude(absPva, absPva.getDate(), absPva.getFrame()),
DEFAULT_MASS, null);
}
/** Build a spacecraft state from orbit and attitude provider.
* Mass is set to an unspecified non-null arbitrary value.
* @param absPva position-velocity-acceleration
* @param attitude attitude
* @exception IllegalArgumentException if orbit and attitude dates
* or frames are not equal
*/
public SpacecraftState(final AbsolutePVCoordinates absPva, final Attitude attitude)
throws IllegalArgumentException {
this(absPva, attitude, DEFAULT_MASS, null);
}
/** Create a new instance from orbit and mass.
* Attitude law is set to an unspecified default attitude.
* @param absPva position-velocity-acceleration
* @param mass the mass (kg)
*/
public SpacecraftState(final AbsolutePVCoordinates absPva, final double mass) {
this(absPva,
new LofOffset(absPva.getFrame(), LOFType.LVLH_CCSDS).getAttitude(absPva, absPva.getDate(), absPva.getFrame()),
mass, null);
}
/** Build a spacecraft state from orbit, attitude provider and mass.
* @param absPva position-velocity-acceleration
* @param attitude attitude
* @param mass the mass (kg)
* @exception IllegalArgumentException if orbit and attitude dates
* or frames are not equal
*/
public SpacecraftState(final AbsolutePVCoordinates absPva, final Attitude attitude, final double mass)
throws IllegalArgumentException {
this(absPva, attitude, mass, null);
}
/** Build a spacecraft state from orbit only.
* Attitude and mass are set to unspecified non-null arbitrary values.
* @param absPva position-velocity-acceleration
* @param additional additional states
*/
public SpacecraftState(final AbsolutePVCoordinates absPva, final Map additional) {
this(absPva,
new LofOffset(absPva.getFrame(), LOFType.LVLH_CCSDS).getAttitude(absPva, absPva.getDate(), absPva.getFrame()),
DEFAULT_MASS, additional);
}
/** Build a spacecraft state from orbit and attitude provider.
* Mass is set to an unspecified non-null arbitrary value.
* @param absPva position-velocity-acceleration
* @param attitude attitude
* @param additional additional states
* @exception IllegalArgumentException if orbit and attitude dates
* or frames are not equal
*/
public SpacecraftState(final AbsolutePVCoordinates absPva, final Attitude attitude, final Map additional)
throws IllegalArgumentException {
this(absPva, attitude, DEFAULT_MASS, additional);
}
/** Create a new instance from orbit and mass.
* Attitude law is set to an unspecified default attitude.
* @param absPva position-velocity-acceleration
* @param mass the mass (kg)
* @param additional additional states
*/
public SpacecraftState(final AbsolutePVCoordinates absPva, final double mass, final Map additional) {
this(absPva,
new LofOffset(absPva.getFrame(), LOFType.LVLH_CCSDS).getAttitude(absPva, absPva.getDate(), absPva.getFrame()),
mass, additional);
}
/** Build a spacecraft state from orbit, attitude provider and mass.
* @param absPva position-velocity-acceleration
* @param attitude attitude
* @param mass the mass (kg)
* @param additional additional states (may be null if no additional states are available)
* @exception IllegalArgumentException if orbit and attitude dates
* or frames are not equal
*/
public SpacecraftState(final AbsolutePVCoordinates absPva, final Attitude attitude,
final double mass, final Map additional)
throws IllegalArgumentException {
checkConsistency(absPva, attitude);
this.orbit = null;
this.absPva = absPva;
this.attitude = attitude;
this.mass = mass;
if (additional == null) {
this.additional = Collections.emptyMap();
} else {
this.additional = new HashMap(additional.size());
for (final Map.Entry entry : additional.entrySet()) {
this.additional.put(entry.getKey(), entry.getValue().clone());
}
}
}
/** Add an additional state.
*
* {@link SpacecraftState SpacecraftState} instances are immutable,
* so this method does not change the instance, but rather
* creates a new instance, which has the same orbit, attitude, mass
* and additional states as the original instance, except it also
* has the specified state. If the original instance already had an
* additional state with the same name, it will be overridden. If it
* did not have any additional state with that name, the new instance
* will have one more additional state than the original instance.
*
* @param name name of the additional state
* @param value value of the additional state
* @return a new instance, with the additional state added
* @see #hasAdditionalState(String)
* @see #getAdditionalState(String)
* @see #getAdditionalStates()
*/
public SpacecraftState addAdditionalState(final String name, final double... value) {
final Map newMap = new HashMap(additional.size() + 1);
newMap.putAll(additional);
newMap.put(name, value.clone());
if (absPva == null) {
return new SpacecraftState(orbit, attitude, mass, newMap);
} else {
return new SpacecraftState(absPva, attitude, mass, newMap);
}
}
/** Check orbit and attitude dates are equal.
* @param orbit the orbit
* @param attitude attitude
* @exception IllegalArgumentException if orbit and attitude dates
* are not equal
*/
private static void checkConsistency(final Orbit orbit, final Attitude attitude)
throws IllegalArgumentException {
if (FastMath.abs(orbit.getDate().durationFrom(attitude.getDate())) >
DATE_INCONSISTENCY_THRESHOLD) {
throw new OrekitIllegalArgumentException(OrekitMessages.ORBIT_AND_ATTITUDE_DATES_MISMATCH,
orbit.getDate(), attitude.getDate());
}
if (orbit.getFrame() != attitude.getReferenceFrame()) {
throw new OrekitIllegalArgumentException(OrekitMessages.FRAMES_MISMATCH,
orbit.getFrame().getName(),
attitude.getReferenceFrame().getName());
}
}
/** Check if the state contains an orbit part.
*
* A state contains either an {@link AbsolutePVCoordinates absolute
* position-velocity-acceleration} or an {@link Orbit orbit}.
*
* @return true if state contains an orbit (in which case {@link #getOrbit()}
* will not throw an exception), or false if the state contains an
* absolut position-velocity-acceleration (in which case {@link #getAbsPVA()}
* will not throw an exception)
*/
public boolean isOrbitDefined() {
return orbit != null;
}
/** Check AbsolutePVCoordinates and attitude dates are equal.
* @param absPva position-velocity-acceleration
* @param attitude attitude
* @exception IllegalArgumentException if orbit and attitude dates
* are not equal
*/
private static void checkConsistency(final AbsolutePVCoordinates absPva, final Attitude attitude)
throws IllegalArgumentException {
if (FastMath.abs(absPva.getDate().durationFrom(attitude.getDate())) >
DATE_INCONSISTENCY_THRESHOLD) {
throw new OrekitIllegalArgumentException(OrekitMessages.ORBIT_AND_ATTITUDE_DATES_MISMATCH,
absPva.getDate(), attitude.getDate());
}
if (absPva.getFrame() != attitude.getReferenceFrame()) {
throw new OrekitIllegalArgumentException(OrekitMessages.FRAMES_MISMATCH,
absPva.getFrame().getName(),
attitude.getReferenceFrame().getName());
}
}
/** Get a time-shifted state.
*
* The state can be slightly shifted to close dates. This shift is based on
* simple models. For orbits, the model is a Keplerian one if no derivatives
* are available in the orbit, or Keplerian plus quadratic effect of the
* non-Keplerian acceleration if derivatives are available. For attitude,
* a polynomial model is used. Neither mass nor additional states change.
* Shifting is not intended as a replacement for proper orbit
* and attitude propagation but should be sufficient for small time shifts
* or coarse accuracy.
*
*
* As a rough order of magnitude, the following table shows the extrapolation
* errors obtained between this simple shift method and an {@link
* org.orekit.propagation.numerical.NumericalPropagator numerical
* propagator} for a low Earth Sun Synchronous Orbit, with a 20x20 gravity field,
* Sun and Moon third bodies attractions, drag and solar radiation pressure.
* Beware that these results will be different for other orbits.
*
*
* Extrapolation Error
* interpolation time (s)
* position error without derivatives (m) position error with derivatives (m) 60 18 1.1 120 72 9.1 300 447 140 600 1601 1067 900 3141 3307
* @param dt time shift in seconds
* @return a new state, shifted with respect to the instance (which is immutable)
* except for the mass and additional states which stay unchanged
*/
public SpacecraftState shiftedBy(final double dt) {
if (absPva == null) {
return new SpacecraftState(orbit.shiftedBy(dt), attitude.shiftedBy(dt),
mass, additional);
} else {
return new SpacecraftState(absPva.shiftedBy(dt), attitude.shiftedBy(dt),
mass, additional);
}
}
/** {@inheritDoc}
*
* The additional states that are interpolated are the ones already present
* in the instance. The sample instances must therefore have at least the same
* additional states has the instance. They may have more additional states,
* but the extra ones will be ignored.
*
*
* The instance and all the sample instances must be based on similar
* trajectory data, i.e. they must either all be based on orbits or all be based
* on absolute position-velocity-acceleration. Any inconsistency will trigger
* an {@link OrekitIllegalStateException}.
*
*
* As this implementation of interpolation is polynomial, it should be used only
* with small samples (about 10-20 points) in order to avoid Runge's phenomenon
* and numerical problems (including NaN appearing).
*
* @exception OrekitIllegalStateException if some instances are not based on
* similar trajectory data
*/
public SpacecraftState interpolate(final AbsoluteDate date,
final Stream sample) {
// prepare interpolators
final List orbits;
final List absPvas;
if (isOrbitDefined()) {
orbits = new ArrayList();
absPvas = null;
} else {
orbits = null;
absPvas = new ArrayList();
}
final List attitudes = new ArrayList();
final HermiteInterpolator massInterpolator = new HermiteInterpolator();
final Map additionalInterpolators =
new HashMap(additional.size());
for (final String name : additional.keySet()) {
additionalInterpolators.put(name, new HermiteInterpolator());
}
// extract sample data
sample.forEach(state -> {
final double deltaT = state.getDate().durationFrom(date);
if (isOrbitDefined()) {
orbits.add(state.getOrbit());
} else {
absPvas.add(state.getAbsPVA());
}
attitudes.add(state.getAttitude());
massInterpolator.addSamplePoint(deltaT,
new double[] {
state.getMass()
});
for (final Map.Entry entry : additionalInterpolators.entrySet()) {
entry.getValue().addSamplePoint(deltaT, state.getAdditionalState(entry.getKey()));
}
});
// perform interpolations
final Orbit interpolatedOrbit;
final AbsolutePVCoordinates interpolatedAbsPva;
if (isOrbitDefined()) {
interpolatedOrbit = orbit.interpolate(date, orbits);
interpolatedAbsPva = null;
} else {
interpolatedOrbit = null;
interpolatedAbsPva = absPva.interpolate(date, absPvas);
}
final Attitude interpolatedAttitude = attitude.interpolate(date, attitudes);
final double interpolatedMass = massInterpolator.value(0)[0];
final Map interpolatedAdditional;
if (additional.isEmpty()) {
interpolatedAdditional = null;
} else {
interpolatedAdditional = new HashMap(additional.size());
for (final Map.Entry entry : additionalInterpolators.entrySet()) {
interpolatedAdditional.put(entry.getKey(), entry.getValue().value(0));
}
}
// create the complete interpolated state
if (isOrbitDefined()) {
return new SpacecraftState(interpolatedOrbit, interpolatedAttitude,
interpolatedMass, interpolatedAdditional);
} else {
return new SpacecraftState(interpolatedAbsPva, interpolatedAttitude,
interpolatedMass, interpolatedAdditional);
}
}
/** Get the absolute position-velocity-acceleration.
*
* A state contains either an {@link AbsolutePVCoordinates absolute
* position-velocity-acceleration} or an {@link Orbit orbit}. Which
* one is present can be checked using {@link #isOrbitDefined()}.
*
* @return absolute position-velocity-acceleration
* @exception OrekitIllegalStateException if position-velocity-acceleration is null,
* which mean the state rather contains an {@link Orbit}
* @see #isOrbitDefined()
* @see #getOrbit()
*/
public AbsolutePVCoordinates getAbsPVA() throws OrekitIllegalStateException {
if (absPva == null) {
throw new OrekitIllegalStateException(OrekitMessages.UNDEFINED_ABSOLUTE_PVCOORDINATES);
}
return absPva;
}
/** Get the current orbit.
*
* A state contains either an {@link AbsolutePVCoordinates absolute
* position-velocity-acceleration} or an {@link Orbit orbit}. Which
* one is present can be checked using {@link #isOrbitDefined()}.
*
* @return the orbit
* @exception OrekitIllegalStateException if orbit is null,
* which means the state rather contains an {@link AbsolutePVCoordinates absolute
* position-velocity-acceleration}
* @see #isOrbitDefined()
* @see #getAbsPVA()
*/
public Orbit getOrbit() throws OrekitIllegalStateException {
if (orbit == null) {
throw new OrekitIllegalStateException(OrekitMessages.UNDEFINED_ORBIT);
}
return orbit;
}
/** Get the date.
* @return date
*/
public AbsoluteDate getDate() {
return (absPva == null) ? orbit.getDate() : absPva.getDate();
}
/** Get the defining frame.
* @return the frame in which state is defined
*/
public Frame getFrame() {
return (absPva == null) ? orbit.getFrame() : absPva.getFrame();
}
/** Check if an additional state is available.
* @param name name of the additional state
* @return true if the additional state is available
* @see #addAdditionalState(String, double[])
* @see #getAdditionalState(String)
* @see #getAdditionalStates()
*/
public boolean hasAdditionalState(final String name) {
return additional.containsKey(name);
}
/** Check if two instances have the same set of additional states available.
*
* Only the names and dimensions of the additional states are compared,
* not their values.
*
* @param state state to compare to instance
* @exception MathIllegalStateException if an additional state does not have
* the same dimension in both states
*/
public void ensureCompatibleAdditionalStates(final SpacecraftState state)
throws MathIllegalStateException {
// check instance additional states is a subset of the other one
for (final Map.Entry entry : additional.entrySet()) {
final double[] other = state.additional.get(entry.getKey());
if (other == null) {
throw new OrekitException(OrekitMessages.UNKNOWN_ADDITIONAL_STATE,
entry.getKey());
}
if (other.length != entry.getValue().length) {
throw new MathIllegalStateException(LocalizedCoreFormats.DIMENSIONS_MISMATCH,
other.length, entry.getValue().length);
}
}
if (state.additional.size() > additional.size()) {
// the other state has more additional states
for (final String name : state.additional.keySet()) {
if (!additional.containsKey(name)) {
throw new OrekitException(OrekitMessages.UNKNOWN_ADDITIONAL_STATE,
name);
}
}
}
}
/** Get an additional state.
* @param name name of the additional state
* @return value of the additional state
* @see #addAdditionalState(String, double[])
* @see #hasAdditionalState(String)
* @see #getAdditionalStates()
*/
public double[] getAdditionalState(final String name) {
if (!additional.containsKey(name)) {
throw new OrekitException(OrekitMessages.UNKNOWN_ADDITIONAL_STATE, name);
}
return additional.get(name).clone();
}
/** Get an unmodifiable map of additional states.
* @return unmodifiable map of additional states
* @see #addAdditionalState(String, double[])
* @see #hasAdditionalState(String)
* @see #getAdditionalState(String)
*/
public Map getAdditionalStates() {
return Collections.unmodifiableMap(additional);
}
/** Compute the transform from state defining frame to spacecraft frame.
* The spacecraft frame origin is at the point defined by the orbit
* (or absolute position-velocity-acceleration), and its orientation is
* defined by the attitude.
* @return transform from specified frame to current spacecraft frame
*/
public Transform toTransform() {
final TimeStampedPVCoordinates pv = getPVCoordinates();
return new Transform(pv.getDate(),
new Transform(pv.getDate(), pv.negate()),
new Transform(pv.getDate(), attitude.getOrientation()));
}
/** Get the central attraction coefficient.
* @return mu central attraction coefficient (m^3/s^2), or {code Double.NaN} if the
* state is contains an absolute position-velocity-acceleration rather than an orbit
*/
public double getMu() {
return (absPva == null) ? orbit.getMu() : Double.NaN;
}
/** Get the Keplerian period.
* The Keplerian period is computed directly from semi major axis
* and central acceleration constant.
* @return keplerian period in seconds, or {code Double.NaN} if the
* state is contains an absolute position-velocity-acceleration rather
* than an orbit
*/
public double getKeplerianPeriod() {
return (absPva == null) ? orbit.getKeplerianPeriod() : Double.NaN;
}
/** Get the Keplerian mean motion.
* The Keplerian mean motion is computed directly from semi major axis
* and central acceleration constant.
* @return keplerian mean motion in radians per second, or {code Double.NaN} if the
* state is contains an absolute position-velocity-acceleration rather
* than an orbit
*/
public double getKeplerianMeanMotion() {
return (absPva == null) ? orbit.getKeplerianMeanMotion() : Double.NaN;
}
/** Get the semi-major axis.
* @return semi-major axis (m), or {code Double.NaN} if the
* state is contains an absolute position-velocity-acceleration rather
* than an orbit
*/
public double getA() {
return (absPva == null) ? orbit.getA() : Double.NaN;
}
/** Get the first component of the eccentricity vector (as per equinoctial parameters).
* @return e cos(ω + Ω), first component of eccentricity vector, or {code Double.NaN} if the
* state is contains an absolute position-velocity-acceleration rather
* than an orbit
* @see #getE()
*/
public double getEquinoctialEx() {
return (absPva == null) ? orbit.getEquinoctialEx() : Double.NaN;
}
/** Get the second component of the eccentricity vector (as per equinoctial parameters).
* @return e sin(ω + Ω), second component of the eccentricity vector, or {code Double.NaN} if the
* state is contains an absolute position-velocity-acceleration rather
* than an orbit
* @see #getE()
*/
public double getEquinoctialEy() {
return (absPva == null) ? orbit.getEquinoctialEy() : Double.NaN;
}
/** Get the first component of the inclination vector (as per equinoctial parameters).
* @return tan(i/2) cos(Ω), first component of the inclination vector, or {code Double.NaN} if the
* state is contains an absolute position-velocity-acceleration rather
* than an orbit
* @see #getI()
*/
public double getHx() {
return (absPva == null) ? orbit.getHx() : Double.NaN;
}
/** Get the second component of the inclination vector (as per equinoctial parameters).
* @return tan(i/2) sin(Ω), second component of the inclination vector, or {code Double.NaN} if the
* state is contains an absolute position-velocity-acceleration rather
* than an orbit
* @see #getI()
*/
public double getHy() {
return (absPva == null) ? orbit.getHy() : Double.NaN;
}
/** Get the true latitude argument (as per equinoctial parameters).
* @return v + ω + Ω true longitude argument (rad), or {code Double.NaN} if the
* state is contains an absolute position-velocity-acceleration rather
* than an orbit
* @see #getLE()
* @see #getLM()
*/
public double getLv() {
return (absPva == null) ? orbit.getLv() : Double.NaN;
}
/** Get the eccentric latitude argument (as per equinoctial parameters).
* @return E + ω + Ω eccentric longitude argument (rad), or {code Double.NaN} if the
* state is contains an absolute position-velocity-acceleration rather
* than an orbit
* @see #getLv()
* @see #getLM()
*/
public double getLE() {
return (absPva == null) ? orbit.getLE() : Double.NaN;
}
/** Get the mean longitude argument (as per equinoctial parameters).
* @return M + ω + Ω mean latitude argument (rad), or {code Double.NaN} if the
* state is contains an absolute position-velocity-acceleration rather
* than an orbit
* @see #getLv()
* @see #getLE()
*/
public double getLM() {
return (absPva == null) ? orbit.getLM() : Double.NaN;
}
// Additional orbital elements
/** Get the eccentricity.
* @return eccentricity, or {code Double.NaN} if the
* state is contains an absolute position-velocity-acceleration rather
* than an orbit
* @see #getEquinoctialEx()
* @see #getEquinoctialEy()
*/
public double getE() {
return (absPva == null) ? orbit.getE() : Double.NaN;
}
/** Get the inclination.
* @return inclination (rad)
* @see #getHx()
* @see #getHy()
*/
public double getI() {
return (absPva == null) ? orbit.getI() : Double.NaN;
}
/** Get the {@link TimeStampedPVCoordinates} in orbit definition frame.
*
* Compute the position and velocity of the satellite. This method caches its
* results, and recompute them only when the method is called with a new value
* for mu. The result is provided as a reference to the internally cached
* {@link TimeStampedPVCoordinates}, so the caller is responsible to copy it in a separate
* {@link TimeStampedPVCoordinates} if it needs to keep the value for a while.
*
* @return pvCoordinates in orbit definition frame
*/
public TimeStampedPVCoordinates getPVCoordinates() {
return (absPva == null) ? orbit.getPVCoordinates() : absPva.getPVCoordinates();
}
/** Get the {@link TimeStampedPVCoordinates} in given output frame.
*
* Compute the position and velocity of the satellite. This method caches its
* results, and recompute them only when the method is called with a new value
* for mu. The result is provided as a reference to the internally cached
* {@link TimeStampedPVCoordinates}, so the caller is responsible to copy it in a separate
* {@link TimeStampedPVCoordinates} if it needs to keep the value for a while.
*
* @param outputFrame frame in which coordinates should be defined
* @return pvCoordinates in orbit definition frame
*/
public TimeStampedPVCoordinates getPVCoordinates(final Frame outputFrame) {
return (absPva == null) ? orbit.getPVCoordinates(outputFrame) : absPva.getPVCoordinates(outputFrame);
}
/** Get the attitude.
* @return the attitude.
*/
public Attitude getAttitude() {
return attitude;
}
/** Gets the current mass.
* @return the mass (kg)
*/
public double getMass() {
return mass;
}
/** Replace the instance with a data transfer object for serialization.
* @return data transfer object that will be serialized
*/
private Object writeReplace() {
return isOrbitDefined() ? new DTOO(this) : new DTOA(this);
}
/** Internal class used only for serialization. */
private static class DTOO implements Serializable {
/** Serializable UID. */
private static final long serialVersionUID = 20150916L;
/** Orbit. */
private final Orbit orbit;
/** Attitude and mass double values. */
private double[] d;
/** Additional states. */
private final Map additional;
/** Simple constructor.
* @param state instance to serialize
*/
private DTOO(final SpacecraftState state) {
this.orbit = state.orbit;
this.additional = state.additional.isEmpty() ? null : state.additional;
final Rotation rotation = state.attitude.getRotation();
final Vector3D spin = state.attitude.getSpin();
final Vector3D rotationAcceleration = state.attitude.getRotationAcceleration();
this.d = new double[] {
rotation.getQ0(), rotation.getQ1(), rotation.getQ2(), rotation.getQ3(),
spin.getX(), spin.getY(), spin.getZ(),
rotationAcceleration.getX(), rotationAcceleration.getY(), rotationAcceleration.getZ(),
state.mass
};
}
/** Replace the de-serialized data transfer object with a {@link SpacecraftState}.
* @return replacement {@link SpacecraftState}
*/
private Object readResolve() {
return new SpacecraftState(orbit,
new Attitude(orbit.getFrame(),
new TimeStampedAngularCoordinates(orbit.getDate(),
new Rotation(d[0], d[1], d[2], d[3], false),
new Vector3D(d[4], d[5], d[6]),
new Vector3D(d[7], d[8], d[9]))),
d[10], additional);
}
}
/** Internal class used only for serialization. */
private static class DTOA implements Serializable {
/** Serializable UID. */
private static final long serialVersionUID = 20150916L;
/** Absolute position-velocity-acceleration. */
private final AbsolutePVCoordinates absPva;
/** Attitude and mass double values. */
private double[] d;
/** Additional states. */
private final Map additional;
/** Simple constructor.
* @param state instance to serialize
*/
private DTOA(final SpacecraftState state) {
this.absPva = state.absPva;
this.additional = state.additional.isEmpty() ? null : state.additional;
final Rotation rotation = state.attitude.getRotation();
final Vector3D spin = state.attitude.getSpin();
final Vector3D rotationAcceleration = state.attitude.getRotationAcceleration();
this.d = new double[] {
rotation.getQ0(), rotation.getQ1(), rotation.getQ2(), rotation.getQ3(),
spin.getX(), spin.getY(), spin.getZ(),
rotationAcceleration.getX(), rotationAcceleration.getY(), rotationAcceleration.getZ(),
state.mass
};
}
/** Replace the deserialized data transfer object with a {@link SpacecraftState}.
* @return replacement {@link SpacecraftState}
*/
private Object readResolve() {
return new SpacecraftState(absPva,
new Attitude(absPva.getFrame(),
new TimeStampedAngularCoordinates(absPva.getDate(),
new Rotation(d[0], d[1], d[2], d[3], false),
new Vector3D(d[4], d[5], d[6]),
new Vector3D(d[7], d[8], d[9]))),
d[10], additional);
}
}
@Override
public String toString() {
return "SpacecraftState{" +
"orbit=" + orbit +
", attitude=" + attitude +
", mass=" + mass +
", additional=" + additional +
'}';
}
}