org.orekit.propagation

Class SpacecraftState

java.lang.Object

org.orekit.propagation.SpacecraftState

All Implemented Interfaces:

Serializable, TimeShiftable<SpacecraftState>, TimeStamped

public class SpacecraftState
extends Object
implements TimeStamped, TimeShiftable<SpacecraftState>, Serializable

This class is the representation of a complete state holding orbit, attitude and mass information at a given date, meant primarily for propagation.

It contains an Orbit, or an AbsolutePVCoordinates if there is no definite central body, plus the current mass and attitude at the intrinsic AbsoluteDate. Quantities 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 actual shift varies between Orbit and AbsolutePVCoordinates. For attitude it is a linear extrapolation 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.

Author:

Fabien Maussion, Véronique Pommier-Maurussane, Luc Maisonobe

See Also:

NumericalPropagator, Serialized Form

Field Summary

Fields

Modifier and Type	Field and Description
static double	DEFAULT_MASS Default mass.

Constructor Summary

Constructors

Constructor and Description
SpacecraftState(AbsolutePVCoordinates absPva) Build a spacecraft state from position-velocity-acceleration only.
SpacecraftState(AbsolutePVCoordinates absPva, Attitude attitude) Build a spacecraft state from position-velocity-acceleration and attitude.
SpacecraftState(AbsolutePVCoordinates absPva, Attitude attitude, double mass) Build a spacecraft state from position-velocity-acceleration, attitude and mass.
SpacecraftState(AbsolutePVCoordinates absPva, Attitude attitude, DoubleArrayDictionary additional) Build a spacecraft state from position-velocity-acceleration, attitude and additional states.
SpacecraftState(AbsolutePVCoordinates absPva, Attitude attitude, double mass, DoubleArrayDictionary additional) Build a spacecraft state from position-velocity-acceleration, attitude, mass and additional states.
SpacecraftState(AbsolutePVCoordinates absPva, Attitude attitude, double mass, DoubleArrayDictionary additional, DoubleArrayDictionary additionalDot) Build a spacecraft state from position-velocity-acceleration, attitude, mass and additional states and derivatives.
SpacecraftState(AbsolutePVCoordinates absPva, double mass) Create a new instance from position-velocity-acceleration and mass.
SpacecraftState(AbsolutePVCoordinates absPva, DoubleArrayDictionary additional) Build a spacecraft state from position-velocity-acceleration and additional states.
SpacecraftState(AbsolutePVCoordinates absPva, double mass, DoubleArrayDictionary additional) Create a new instance from position-velocity-acceleration, mass and additional states.
SpacecraftState(Orbit orbit) Build a spacecraft state from orbit only.
SpacecraftState(Orbit orbit, Attitude attitude) Build a spacecraft state from orbit and attitude.
SpacecraftState(Orbit orbit, Attitude attitude, double mass) Build a spacecraft state from orbit, attitude and mass.
SpacecraftState(Orbit orbit, Attitude attitude, DoubleArrayDictionary additional) Build a spacecraft state from orbit, attitude and additional states.
SpacecraftState(Orbit orbit, Attitude attitude, double mass, DoubleArrayDictionary additional) Build a spacecraft state from orbit, attitude, mass and additional states.
SpacecraftState(Orbit orbit, Attitude attitude, double mass, DoubleArrayDictionary additional, DoubleArrayDictionary additionalDot) Build a spacecraft state from orbit, attitude, mass, additional states and derivatives.
SpacecraftState(Orbit orbit, double mass) Create a new instance from orbit and mass.
SpacecraftState(Orbit orbit, DoubleArrayDictionary additional) Build a spacecraft state from orbit and additional states.
SpacecraftState(Orbit orbit, double mass, DoubleArrayDictionary additional) Create a new instance from orbit, mass and additional states.

Method Summary

Modifier and Type	Method and Description
SpacecraftState	addAdditionalState(String name, double... value) Add an additional state.
SpacecraftState	addAdditionalStateDerivative(String name, double... value) Add an additional state derivative.
void	ensureCompatibleAdditionalStates(SpacecraftState state) Check if two instances have the same set of additional states available.
double	getA() Get the semi-major axis.
AbsolutePVCoordinates	getAbsPVA() Get the absolute position-velocity-acceleration.
double[]	getAdditionalState(String name) Get an additional state.
double[]	getAdditionalStateDerivative(String name) Get an additional state derivative.
DoubleArrayDictionary	getAdditionalStatesDerivatives() Get an unmodifiable map of additional states derivatives.
DoubleArrayDictionary	getAdditionalStatesValues() Get an unmodifiable map of additional states.
Attitude	getAttitude() Get the attitude.
AbsoluteDate	getDate() Get the date.
double	getE() Get the eccentricity.
double	getEquinoctialEx() Get the first component of the eccentricity vector (as per equinoctial parameters).
double	getEquinoctialEy() Get the second component of the eccentricity vector (as per equinoctial parameters).
Frame	getFrame() Get the defining frame.
double	getHx() Get the first component of the inclination vector (as per equinoctial parameters).
double	getHy() Get the second component of the inclination vector (as per equinoctial parameters).
double	getI() Get the inclination.
double	getKeplerianMeanMotion() Get the Keplerian mean motion.
double	getKeplerianPeriod() Get the Keplerian period.
double	getLE() Get the eccentric latitude argument (as per equinoctial parameters).
double	getLM() Get the mean longitude argument (as per equinoctial parameters).
double	getLv() Get the true latitude argument (as per equinoctial parameters).
double	getMass() Gets the current mass.
double	getMu() Get the central attraction coefficient.
Orbit	getOrbit() Get the current orbit.
org.hipparchus.geometry.euclidean.threed.Vector3D	getPosition() Get the position in orbit definition frame.
org.hipparchus.geometry.euclidean.threed.Vector3D	getPosition(Frame outputFrame) Get the position in given output frame.
TimeStampedPVCoordinates	getPVCoordinates() Get the TimeStampedPVCoordinates in orbit definition frame.
TimeStampedPVCoordinates	getPVCoordinates(Frame outputFrame) Get the TimeStampedPVCoordinates in given output frame.
boolean	hasAdditionalState(String name) Check if an additional state is available.
boolean	hasAdditionalStateDerivative(String name) Check if an additional state derivative is available.
boolean	isOrbitDefined() Check if the state contains an orbit part.
SpacecraftState	shiftedBy(double dt) Get a time-shifted state.
StaticTransform	toStaticTransform() Compute the static transform from state defining frame to spacecraft frame.
String	toString()
Transform	toTransform() Compute the transform from state defining frame to spacecraft frame.

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, wait, wait, wait

Methods inherited from interface org.orekit.time.TimeStamped

durationFrom

Field Detail

DEFAULT_MASS

public static final double DEFAULT_MASS

Default mass.

See Also:

Constant Field Values

Constructor Detail

SpacecraftState

public SpacecraftState(Orbit orbit)

Build a spacecraft state from orbit only.

Attitude and mass are set to unspecified non-null arbitrary values.

Parameters:

orbit - the orbit

SpacecraftState

public SpacecraftState(Orbit orbit,
                       Attitude attitude)
                throws IllegalArgumentException

Build a spacecraft state from orbit and attitude.

Mass is set to an unspecified non-null arbitrary value.

Parameters:

orbit - the orbit

attitude - attitude

Throws:

IllegalArgumentException - if orbit and attitude dates or frames are not equal

SpacecraftState

public SpacecraftState(Orbit orbit,
                       double mass)

Create a new instance from orbit and mass.

Attitude law is set to an unspecified default attitude.

Parameters:

orbit - the orbit

mass - the mass (kg)

SpacecraftState

public SpacecraftState(Orbit orbit,
                       Attitude attitude,
                       double mass)
                throws IllegalArgumentException

Build a spacecraft state from orbit, attitude and mass.

Parameters:

orbit - the orbit

attitude - attitude

mass - the mass (kg)

Throws:

IllegalArgumentException - if orbit and attitude dates or frames are not equal

SpacecraftState

public SpacecraftState(Orbit orbit,
                       DoubleArrayDictionary additional)

Build a spacecraft state from orbit and additional states.

Attitude and mass are set to unspecified non-null arbitrary values.

Parameters:

orbit - the orbit

additional - additional states

Since:

11.1

SpacecraftState

public SpacecraftState(Orbit orbit,
                       Attitude attitude,
                       DoubleArrayDictionary additional)
                throws IllegalArgumentException

Build a spacecraft state from orbit, attitude and additional states.

Mass is set to an unspecified non-null arbitrary value.

Parameters:

orbit - the orbit

attitude - attitude

additional - additional states

Throws:

IllegalArgumentException - if orbit and attitude dates or frames are not equal

Since:

11.1

SpacecraftState

public SpacecraftState(Orbit orbit,
                       double mass,
                       DoubleArrayDictionary additional)

Create a new instance from orbit, mass and additional states.

Attitude law is set to an unspecified default attitude.

Parameters:

orbit - the orbit

mass - the mass (kg)

additional - additional states

Since:

11.1

SpacecraftState

public SpacecraftState(Orbit orbit,
                       Attitude attitude,
                       double mass,
                       DoubleArrayDictionary additional)
                throws IllegalArgumentException

Build a spacecraft state from orbit, attitude, mass and additional states.

Parameters:

orbit - the orbit

attitude - attitude

mass - the mass (kg)

additional - additional states (may be null if no additional states are available)

Throws:

IllegalArgumentException - if orbit and attitude dates or frames are not equal

Since:

11.1

SpacecraftState

public SpacecraftState(Orbit orbit,
                       Attitude attitude,
                       double mass,
                       DoubleArrayDictionary additional,
                       DoubleArrayDictionary additionalDot)
                throws IllegalArgumentException

Build a spacecraft state from orbit, attitude, mass, additional states and derivatives.

Parameters:

orbit - the orbit

attitude - attitude

mass - the mass (kg)

additional - additional states (may be null if no additional states are available)

additionalDot - additional states derivatives (may be null if no additional states derivatives are available)

Throws:

IllegalArgumentException - if orbit and attitude dates or frames are not equal

Since:

11.1

SpacecraftState

public SpacecraftState(AbsolutePVCoordinates absPva)

Build a spacecraft state from position-velocity-acceleration only.

Attitude and mass are set to unspecified non-null arbitrary values.

Parameters:

absPva - position-velocity-acceleration

SpacecraftState

public SpacecraftState(AbsolutePVCoordinates absPva,
                       Attitude attitude)
                throws IllegalArgumentException

Build a spacecraft state from position-velocity-acceleration and attitude.

Mass is set to an unspecified non-null arbitrary value.

Parameters:

absPva - position-velocity-acceleration

attitude - attitude

Throws:

IllegalArgumentException - if orbit and attitude dates or frames are not equal

SpacecraftState

public SpacecraftState(AbsolutePVCoordinates absPva,
                       double mass)

Create a new instance from position-velocity-acceleration and mass.

Attitude law is set to an unspecified default attitude.

Parameters:

absPva - position-velocity-acceleration

mass - the mass (kg)

SpacecraftState

public SpacecraftState(AbsolutePVCoordinates absPva,
                       Attitude attitude,
                       double mass)
                throws IllegalArgumentException

Build a spacecraft state from position-velocity-acceleration, attitude and mass.

Parameters:

absPva - position-velocity-acceleration

attitude - attitude

mass - the mass (kg)

Throws:

IllegalArgumentException - if orbit and attitude dates or frames are not equal

SpacecraftState

public SpacecraftState(AbsolutePVCoordinates absPva,
                       DoubleArrayDictionary additional)

Build a spacecraft state from position-velocity-acceleration and additional states.

Attitude and mass are set to unspecified non-null arbitrary values.

Parameters:

absPva - position-velocity-acceleration

additional - additional states

Since:

11.1

SpacecraftState

public SpacecraftState(AbsolutePVCoordinates absPva,
                       Attitude attitude,
                       DoubleArrayDictionary additional)
                throws IllegalArgumentException

Build a spacecraft state from position-velocity-acceleration, attitude and additional states.

Mass is set to an unspecified non-null arbitrary value.

Parameters:

absPva - position-velocity-acceleration

attitude - attitude

additional - additional states

Throws:

IllegalArgumentException - if orbit and attitude dates or frames are not equal

Since:

11.1

SpacecraftState

public SpacecraftState(AbsolutePVCoordinates absPva,
                       double mass,
                       DoubleArrayDictionary additional)

Create a new instance from position-velocity-acceleration, mass and additional states.

Attitude law is set to an unspecified default attitude.

Parameters:

absPva - position-velocity-acceleration

mass - the mass (kg)

additional - additional states

Since:

11.1

SpacecraftState

public SpacecraftState(AbsolutePVCoordinates absPva,
                       Attitude attitude,
                       double mass,
                       DoubleArrayDictionary additional)
                throws IllegalArgumentException

Build a spacecraft state from position-velocity-acceleration, attitude, mass and additional states.

Parameters:

absPva - position-velocity-acceleration

attitude - attitude

mass - the mass (kg)

additional - additional states (may be null if no additional states are available)

Throws:

IllegalArgumentException - if orbit and attitude dates or frames are not equal

Since:

11.1

SpacecraftState

public SpacecraftState(AbsolutePVCoordinates absPva,
                       Attitude attitude,
                       double mass,
                       DoubleArrayDictionary additional,
                       DoubleArrayDictionary additionalDot)
                throws IllegalArgumentException

Build a spacecraft state from position-velocity-acceleration, attitude, mass and additional states and derivatives.

Parameters:

absPva - position-velocity-acceleration

attitude - attitude

mass - the mass (kg)

additional - additional states (may be null if no additional states are available)

additionalDot - additional states derivatives(may be null if no additional states derivatives are available)

Throws:

IllegalArgumentException - if orbit and attitude dates or frames are not equal

Since:

11.1

Method Detail

addAdditionalState

public SpacecraftState addAdditionalState(String name,
                                          double... value)

Add an additional state.

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.

Parameters:

name - name of the additional state (names containing "orekit" with any case are reserved for the library internal use)

value - value of the additional state

Returns:

a new instance, with the additional state added

See Also:

hasAdditionalState(String), getAdditionalState(String), getAdditionalStatesValues()

addAdditionalStateDerivative

public SpacecraftState addAdditionalStateDerivative(String name,
                                                    double... value)

Add an additional state derivative.

SpacecraftState instances are immutable, so this method does not change the instance, but rather creates a new instance, which has the same components as the original instance, except it also has the specified state derivative. If the original instance already had an additional state derivative with the same name, it will be overridden. If it did not have any additional state derivative with that name, the new instance will have one more additional state derivative than the original instance.

Parameters:

name - name of the additional state derivative (names containing "orekit" with any case are reserved for the library internal use)

value - value of the additional state derivative

Returns:

a new instance, with the additional state added

Since:

11.1

See Also:

hasAdditionalStateDerivative(String), getAdditionalStateDerivative(String), getAdditionalStatesDerivatives()

isOrbitDefined

public boolean isOrbitDefined()

Check if the state contains an orbit part.

A state contains either an absolute position-velocity-acceleration or an orbit.

Returns:

true if state contains an orbit (in which case getOrbit() will not throw an exception), or false if the state contains an absolut position-velocity-acceleration (in which case getAbsPVA() will not throw an exception)

shiftedBy

public SpacecraftState shiftedBy(double dt)

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 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

Specified by:

shiftedBy in interface TimeShiftable<SpacecraftState>

Parameters:

dt - time shift in seconds

Returns:

a new state, shifted with respect to the instance (which is immutable) except for the mass and additional states which stay unchanged

getAbsPVA

public AbsolutePVCoordinates getAbsPVA()
                                throws OrekitIllegalStateException

Get the absolute position-velocity-acceleration.

A state contains either an absolute position-velocity-acceleration or an orbit. Which one is present can be checked using isOrbitDefined().

Returns:

absolute position-velocity-acceleration

Throws:

OrekitIllegalStateException - if position-velocity-acceleration is null, which mean the state rather contains an Orbit

See Also:

isOrbitDefined(), getOrbit()

getOrbit

public Orbit getOrbit()
               throws OrekitIllegalStateException

Get the current orbit.

A state contains either an absolute position-velocity-acceleration or an orbit. Which one is present can be checked using isOrbitDefined().

Returns:

the orbit

Throws:

OrekitIllegalStateException - if orbit is null, which means the state rather contains an absolute position-velocity-acceleration

See Also:

isOrbitDefined(), getAbsPVA()

getDate

public AbsoluteDate getDate()

Get the date.

Specified by:

getDate in interface TimeStamped

Returns:

date attached to the object

getFrame

public Frame getFrame()

Get the defining frame.

Returns:

the frame in which state is defined

hasAdditionalState

public boolean hasAdditionalState(String name)

Check if an additional state is available.

Parameters:

name - name of the additional state

Returns:

true if the additional state is available

See Also:

addAdditionalState(String, double[]), getAdditionalState(String), getAdditionalStatesValues()

hasAdditionalStateDerivative

public boolean hasAdditionalStateDerivative(String name)

Check if an additional state derivative is available.

Parameters:

name - name of the additional state derivative

Returns:

true if the additional state derivative is available

Since:

11.1

See Also:

addAdditionalStateDerivative(String, double[]), getAdditionalStateDerivative(String), getAdditionalStatesDerivatives()

ensureCompatibleAdditionalStates

public void ensureCompatibleAdditionalStates(SpacecraftState state)
                                      throws org.hipparchus.exception.MathIllegalStateException

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.

Parameters:

state - state to compare to instance

Throws:

org.hipparchus.exception.MathIllegalStateException - if an additional state does not have the same dimension in both states

getAdditionalState

public double[] getAdditionalState(String name)

Get an additional state.

Parameters:

name - name of the additional state

Returns:

value of the additional state

See Also:

addAdditionalState(String, double[]), hasAdditionalState(String), getAdditionalStatesValues()

getAdditionalStateDerivative

public double[] getAdditionalStateDerivative(String name)

Get an additional state derivative.

Parameters:

name - name of the additional state derivative

Returns:

value of the additional state derivative

Since:

11.1

See Also:

addAdditionalStateDerivative(String, double[]), hasAdditionalStateDerivative(String), getAdditionalStatesDerivatives()

getAdditionalStatesValues

public DoubleArrayDictionary getAdditionalStatesValues()

Get an unmodifiable map of additional states.

Returns:

unmodifiable map of additional states

Since:

11.1

See Also:

addAdditionalState(String, double[]), hasAdditionalState(String), getAdditionalState(String)

getAdditionalStatesDerivatives

public DoubleArrayDictionary getAdditionalStatesDerivatives()

Get an unmodifiable map of additional states derivatives.

Returns:

unmodifiable map of additional states derivatives

Since:

11.1

See Also:

addAdditionalStateDerivative(String, double[]), hasAdditionalStateDerivative(String), getAdditionalStateDerivative(String)

toTransform

public Transform toTransform()

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.

Returns:

transform from specified frame to current spacecraft frame

toStaticTransform

public StaticTransform toStaticTransform()

Compute the static transform from state defining frame to spacecraft frame.

Returns:

static transform from specified frame to current spacecraft frame

Since:

12.0

See Also:

toTransform()

getMu

public double getMu()

Get the central attraction coefficient.

Returns:

mu central attraction coefficient (m^3/s^2), or {code Double.NaN} if the state contains an absolute position-velocity-acceleration rather than an orbit

getKeplerianPeriod

public double getKeplerianPeriod()

Get the Keplerian period.

The Keplerian period is computed directly from semi major axis and central acceleration constant.

Returns:

Keplerian period in seconds, or {code Double.NaN} if the state contains an absolute position-velocity-acceleration rather than an orbit

getKeplerianMeanMotion

public double getKeplerianMeanMotion()

Get the Keplerian mean motion.

The Keplerian mean motion is computed directly from semi major axis and central acceleration constant.

Returns:

Keplerian mean motion in radians per second, or {code Double.NaN} if the state contains an absolute position-velocity-acceleration rather than an orbit

getA

public double getA()

Get the semi-major axis.

Returns:

semi-major axis (m), or {code Double.NaN} if the state contains an absolute position-velocity-acceleration rather than an orbit

getEquinoctialEx

public double getEquinoctialEx()

Get the first component of the eccentricity vector (as per equinoctial parameters).

Returns:

e cos(ω + Ω), first component of eccentricity vector, or {code Double.NaN} if the state contains an absolute position-velocity-acceleration rather than an orbit

See Also:

getE()

getEquinoctialEy

public double getEquinoctialEy()

Get the second component of the eccentricity vector (as per equinoctial parameters).

Returns:

e sin(ω + Ω), second component of the eccentricity vector, or {code Double.NaN} if the state contains an absolute position-velocity-acceleration rather than an orbit

See Also:

getE()

getHx

public double getHx()

Get the first component of the inclination vector (as per equinoctial parameters).

Returns:

tan(i/2) cos(Ω), first component of the inclination vector, or {code Double.NaN} if the state contains an absolute position-velocity-acceleration rather than an orbit

See Also:

getI()

getHy

public double getHy()

Get the second component of the inclination vector (as per equinoctial parameters).

Returns:

tan(i/2) sin(Ω), second component of the inclination vector, or {code Double.NaN} if the state contains an absolute position-velocity-acceleration rather than an orbit

See Also:

getI()

getLv

public double getLv()

Get the true latitude argument (as per equinoctial parameters).

Returns:

v + ω + Ω true longitude argument (rad), or {code Double.NaN} if the state contains an absolute position-velocity-acceleration rather than an orbit

See Also:

getLE(), getLM()

getLE

public double getLE()

Get the eccentric latitude argument (as per equinoctial parameters).

Returns:

E + ω + Ω eccentric longitude argument (rad), or {code Double.NaN} if the state contains an absolute position-velocity-acceleration rather than an orbit

See Also:

getLv(), getLM()

getLM

public double getLM()

Get the mean longitude argument (as per equinoctial parameters).

Returns:

M + ω + Ω mean latitude argument (rad), or {code Double.NaN} if the state contains an absolute position-velocity-acceleration rather than an orbit

See Also:

getLv(), getLE()

getE

public double getE()

Get the eccentricity.

Returns:

eccentricity, or {code Double.NaN} if the state contains an absolute position-velocity-acceleration rather than an orbit

See Also:

getEquinoctialEx(), getEquinoctialEy()

getI

public double getI()

Get the inclination.

Returns:

inclination (rad)

See Also:

getHx(), getHy()

getPosition

public org.hipparchus.geometry.euclidean.threed.Vector3D getPosition()

Get the position in orbit definition frame.

Returns:

position in orbit definition frame

Since:

12.0

See Also:

getPVCoordinates()

getPVCoordinates

public TimeStampedPVCoordinates getPVCoordinates()

Get the 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 TimeStampedPVCoordinates, so the caller is responsible to copy it in a separate TimeStampedPVCoordinates if it needs to keep the value for a while.

Returns:

pvCoordinates in orbit definition frame

getPosition

public org.hipparchus.geometry.euclidean.threed.Vector3D getPosition(Frame outputFrame)

Get the position in given output frame.

Parameters:

outputFrame - frame in which position should be defined

Returns:

position in given output frame

Since:

12.0

See Also:

getPVCoordinates(Frame)

getPVCoordinates

public TimeStampedPVCoordinates getPVCoordinates(Frame outputFrame)

Get the 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 TimeStampedPVCoordinates, so the caller is responsible to copy it in a separate TimeStampedPVCoordinates if it needs to keep the value for a while.

Parameters:

outputFrame - frame in which coordinates should be defined

Returns:

pvCoordinates in orbit definition frame

getAttitude

public Attitude getAttitude()

Get the attitude.

Returns:

the attitude.

getMass

public double getMass()

Gets the current mass.

Returns:

the mass (kg)

toString

public String toString()

Overrides:

toString in class Object