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 anAbsolutePVCoordinates
if there is no definite central body, plus the current mass and attitude at the intrinsicAbsoluteDate
. 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 userdefined data.The state can be slightly shifted to close dates. This actual shift varies between
Orbit
andAbsolutePVCoordinates
. 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 PommierMaurussane, Luc Maisonobe
 See Also:
NumericalPropagator
, Serialized Form


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

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

Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method 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 semimajor axis.AbsolutePVCoordinates
getAbsPVA()
Get the absolute positionvelocityacceleration.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.Vector3D
getPosition()
Get the position in orbit definition frame.Vector3D
getPosition(Frame outputFrame)
Get the position in given output frame.TimeStampedPVCoordinates
getPVCoordinates()
Get theTimeStampedPVCoordinates
in orbit definition frame.TimeStampedPVCoordinates
getPVCoordinates(Frame outputFrame)
Get theTimeStampedPVCoordinates
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 timeshifted state.SpacecraftState
shiftedBy(TimeOffset dt)
Get a timeshifted 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 nonnull 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 nonnull arbitrary value.
 Parameters:
orbit
 the orbitattitude
 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 orbitmass
 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 orbitattitude
 attitudemass
 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 nonnull arbitrary values.
 Parameters:
orbit
 the orbitadditional
 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 nonnull arbitrary value.
 Parameters:
orbit
 the orbitattitude
 attitudeadditional
 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 orbitmass
 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 orbitattitude
 attitudemass
 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 orbitattitude
 attitudemass
 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 positionvelocityacceleration only.Attitude and mass are set to unspecified nonnull arbitrary values.
 Parameters:
absPva
 positionvelocityacceleration

SpacecraftState
public SpacecraftState(AbsolutePVCoordinates absPva, Attitude attitude) throws IllegalArgumentException
Build a spacecraft state from positionvelocityacceleration and attitude.Mass is set to an unspecified nonnull arbitrary value.
 Parameters:
absPva
 positionvelocityaccelerationattitude
 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 positionvelocityacceleration and mass.Attitude law is set to an unspecified default attitude.
 Parameters:
absPva
 positionvelocityaccelerationmass
 the mass (kg)

SpacecraftState
public SpacecraftState(AbsolutePVCoordinates absPva, Attitude attitude, double mass) throws IllegalArgumentException
Build a spacecraft state from positionvelocityacceleration, attitude and mass. Parameters:
absPva
 positionvelocityaccelerationattitude
 attitudemass
 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 positionvelocityacceleration and additional states.Attitude and mass are set to unspecified nonnull arbitrary values.
 Parameters:
absPva
 positionvelocityaccelerationadditional
 additional states Since:
 11.1

SpacecraftState
public SpacecraftState(AbsolutePVCoordinates absPva, Attitude attitude, DoubleArrayDictionary additional) throws IllegalArgumentException
Build a spacecraft state from positionvelocityacceleration, attitude and additional states.Mass is set to an unspecified nonnull arbitrary value.
 Parameters:
absPva
 positionvelocityaccelerationattitude
 attitudeadditional
 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 positionvelocityacceleration, mass and additional states.Attitude law is set to an unspecified default attitude.
 Parameters:
absPva
 positionvelocityaccelerationmass
 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 positionvelocityacceleration, attitude, mass and additional states. Parameters:
absPva
 positionvelocityaccelerationattitude
 attitudemass
 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 positionvelocityacceleration, attitude, mass and additional states and derivatives. Parameters:
absPva
 positionvelocityaccelerationattitude
 attitudemass
 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 positionvelocityacceleration
or anorbit
. Returns:
 true if state contains an orbit (in which case
getOrbit()
will not throw an exception), or false if the state contains an absolut positionvelocityacceleration (in which casegetAbsPVA()
will not throw an exception)

shiftedBy
public SpacecraftState shiftedBy(double dt)
Get a timeshifted 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 nonKeplerian 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 interfaceTimeShiftable<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

shiftedBy
public SpacecraftState shiftedBy(TimeOffset dt)
Get a timeshifted 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 nonKeplerian 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 interfaceTimeShiftable<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
 Since:
 13.0

getAbsPVA
public AbsolutePVCoordinates getAbsPVA() throws OrekitIllegalStateException
Get the absolute positionvelocityacceleration.A state contains either an
absolute positionvelocityacceleration
or anorbit
. Which one is present can be checked usingisOrbitDefined()
. Returns:
 absolute positionvelocityacceleration
 Throws:
OrekitIllegalStateException
 if positionvelocityacceleration is null, which mean the state rather contains anOrbit
 See Also:
isOrbitDefined()
,getOrbit()

getOrbit
public Orbit getOrbit() throws OrekitIllegalStateException
Get the current orbit.A state contains either an
absolute positionvelocityacceleration
or anorbit
. Which one is present can be checked usingisOrbitDefined()
. Returns:
 the orbit
 Throws:
OrekitIllegalStateException
 if orbit is null, which means the state rather contains anabsolute positionvelocityacceleration
 See Also:
isOrbitDefined()
,getAbsPVA()

getDate
public AbsoluteDate getDate()
Get the date. Specified by:
getDate
in interfaceTimeStamped
 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 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:
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 positionvelocityacceleration), 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 positionvelocityacceleration 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 positionvelocityacceleration 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 positionvelocityacceleration rather than an orbit

getA
public double getA()
Get the semimajor axis. Returns:
 semimajor axis (m), or {code Double.NaN} if the state contains an absolute positionvelocityacceleration 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 positionvelocityacceleration 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 positionvelocityacceleration 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 positionvelocityacceleration 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 positionvelocityacceleration rather than an orbit
 See Also:
getI()

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

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

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

getE
public double getE()
Get the eccentricity. Returns:
 eccentricity, or {code Double.NaN} if the state contains an absolute positionvelocityacceleration rather than an orbit
 See Also:
getEquinoctialEx()
,getEquinoctialEy()

getI
public double getI()
Get the inclination.

getPosition
public 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 theTimeStampedPVCoordinates
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 separateTimeStampedPVCoordinates
if it needs to keep the value for a while. Returns:
 pvCoordinates in orbit definition frame

getPosition
public 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 theTimeStampedPVCoordinates
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 separateTimeStampedPVCoordinates
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)

