Class FieldSpacecraftState<T extends CalculusFieldElement<T>>
- java.lang.Object
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- org.orekit.propagation.FieldSpacecraftState<T>
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- Type Parameters:
T
- type of the field elements
- All Implemented Interfaces:
FieldTimeShiftable<FieldSpacecraftState<T>,T>
,FieldTimeStamped<T>
,TimeShiftable<FieldSpacecraftState<T>>
public class FieldSpacecraftState<T extends CalculusFieldElement<T>> extends Object implements FieldTimeStamped<T>, FieldTimeShiftable<FieldSpacecraftState<T>,T>
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
FieldOrbit
, or aFieldAbsolutePVCoordinates
if there is no definite central body, plus the current mass and attitude at the intrinsicFieldAbsoluteDate
. 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
FieldOrbit
andFieldAbsolutePVCoordinates
. 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
FieldSpacecraftState
is guaranteed to be immutable.- Author:
- Fabien Maussion, Véronique Pommier-Maurussane, Luc Maisonobe, Vincent Mouraux
- See Also:
NumericalPropagator
,SpacecraftState
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Constructor Summary
Constructors Constructor Description FieldSpacecraftState(Field<T> field, SpacecraftState state)
Convert aFieldSpacecraftState
.FieldSpacecraftState(FieldOrbit<T> orbit)
Build a spacecraft state from orbit only.FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude)
Build a spacecraft state from orbit and attitude.FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, FieldArrayDictionary<T> additional)
Build a spacecraft state from orbit attitude and additional states.FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T mass)
Build a spacecraft state from orbit, attitude and mass.FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T mass, FieldArrayDictionary<T> additional)
Build a spacecraft state from orbit, attitude, mass and additional states.FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T mass, FieldArrayDictionary<T> additional, FieldArrayDictionary<T> additionalDot)
Build a spacecraft state from orbit, attitude, mass, additional states and derivatives.FieldSpacecraftState(FieldOrbit<T> orbit, FieldArrayDictionary<T> additional)
Build a spacecraft state from orbit and additional states.FieldSpacecraftState(FieldOrbit<T> orbit, T mass)
Create a new instance from orbit and mass.FieldSpacecraftState(FieldOrbit<T> orbit, T mass, FieldArrayDictionary<T> additional)
Create a new instance from orbit, mass and additional states.FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva)
Build a spacecraft state from orbit only.FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude)
Build a spacecraft state from orbit and attitude.FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, FieldArrayDictionary<T> additional)
Build a spacecraft state from orbit and attitude.FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, T mass)
Build a spacecraft state from orbit, attitude and mass.FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, T mass, FieldArrayDictionary<T> additional)
Build a spacecraft state from orbit, attitude and mass.FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, T mass, FieldArrayDictionary<T> additional, FieldArrayDictionary<T> additionalDot)
Build a spacecraft state from orbit, attitude and mass.FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldArrayDictionary<T> additional)
Build a spacecraft state from orbit only.FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, T mass)
Create a new instance from orbit and mass.FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, T mass, FieldArrayDictionary<T> additional)
Create a new instance from orbit and mass.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description FieldSpacecraftState<T>
addAdditionalState(String name, T... value)
Add an additional state.FieldSpacecraftState<T>
addAdditionalStateDerivative(String name, T... value)
Add an additional state derivative.void
ensureCompatibleAdditionalStates(FieldSpacecraftState<T> state)
Check if two instances have the same set of additional states available.T
getA()
Get the semi-major axis.FieldAbsolutePVCoordinates<T>
getAbsPVA()
Get the absolute position-velocity-acceleration.T[]
getAdditionalState(String name)
Get an additional state.T[]
getAdditionalStateDerivative(String name)
Get an additional state derivative.FieldArrayDictionary<T>
getAdditionalStatesDerivatives()
Get an unmodifiable map of additional states derivatives.FieldArrayDictionary<T>
getAdditionalStatesValues()
Get an unmodifiable map of additional states.FieldAttitude<T>
getAttitude()
Get the attitude.FieldAbsoluteDate<T>
getDate()
Get the date.T
getE()
Get the eccentricity.T
getEquinoctialEx()
Get the first component of the eccentricity vector (as per equinoctial parameters).T
getEquinoctialEy()
Get the second component of the eccentricity vector (as per equinoctial parameters).Frame
getFrame()
Get the defining frame.T
getHx()
Get the first component of the inclination vector (as per equinoctial parameters).T
getHy()
Get the second component of the inclination vector (as per equinoctial parameters).T
getI()
Get the inclination.T
getKeplerianMeanMotion()
Get the Keplerian mean motion.T
getKeplerianPeriod()
Get the Keplerian period.T
getLE()
Get the eccentric latitude argument (as per equinoctial parameters).T
getLM()
Get the mean longitude argument (as per equinoctial parameters).T
getLv()
Get the true latitude argument (as per equinoctial parameters).T
getMass()
Gets the current mass.T
getMu()
Get the central attraction coefficient.FieldOrbit<T>
getOrbit()
Get the current orbit.FieldVector3D<T>
getPosition()
Get the position in orbit definition frame.FieldVector3D<T>
getPosition(Frame outputFrame)
Get the position in given output frame.TimeStampedFieldPVCoordinates<T>
getPVCoordinates()
Get theTimeStampedFieldPVCoordinates
in orbit definition frame.TimeStampedFieldPVCoordinates<T>
getPVCoordinates(Frame outputFrame)
Get theTimeStampedFieldPVCoordinates
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.FieldSpacecraftState<T>
shiftedBy(double dt)
Get a time-shifted state.FieldSpacecraftState<T>
shiftedBy(T dt)
Get a time-shifted state.SpacecraftState
toSpacecraftState()
To convert a FieldSpacecraftState instance into a SpacecraftState instance.FieldStaticTransform<T>
toStaticTransform()
Compute the static transform from state defining frame to spacecraft frame.String
toString()
FieldTransform<T>
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
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Methods inherited from interface org.orekit.time.FieldTimeStamped
durationFrom
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Constructor Detail
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FieldSpacecraftState
public FieldSpacecraftState(FieldOrbit<T> orbit)
Build a spacecraft state from orbit only.FieldAttitude and mass are set to unspecified non-null arbitrary values.
- Parameters:
orbit
- the orbit
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FieldSpacecraftState
public FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude) throws IllegalArgumentException
Build a spacecraft state from orbit and attitude.Mass is set to an unspecified non-null arbitrary value.
- Parameters:
orbit
- the orbitattitude
- attitude- Throws:
IllegalArgumentException
- if orbit and attitude dates or frames are not equal
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FieldSpacecraftState
public FieldSpacecraftState(FieldOrbit<T> orbit, T mass)
Create a new instance from orbit and mass.FieldAttitude law is set to an unspecified default attitude.
- Parameters:
orbit
- the orbitmass
- the mass (kg)
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FieldSpacecraftState
public FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T 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
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FieldSpacecraftState
public FieldSpacecraftState(FieldOrbit<T> orbit, FieldArrayDictionary<T> additional)
Build a spacecraft state from orbit and additional states.FieldAttitude and mass are set to unspecified non-null arbitrary values.
- Parameters:
orbit
- the orbitadditional
- additional states- Since:
- 11.1
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FieldSpacecraftState
public FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, FieldArrayDictionary<T> 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 orbitattitude
- attitudeadditional
- additional states- Throws:
IllegalArgumentException
- if orbit and attitude dates or frames are not equal- Since:
- 11.1
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FieldSpacecraftState
public FieldSpacecraftState(FieldOrbit<T> orbit, T mass, FieldArrayDictionary<T> additional)
Create a new instance from orbit, mass and additional states.FieldAttitude law is set to an unspecified default attitude.
- Parameters:
orbit
- the orbitmass
- the mass (kg)additional
- additional states- Since:
- 11.1
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FieldSpacecraftState
public FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T mass, FieldArrayDictionary<T> additional)
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)- Since:
- 11.1
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FieldSpacecraftState
public FieldSpacecraftState(FieldOrbit<T> orbit, FieldAttitude<T> attitude, T mass, FieldArrayDictionary<T> additional, FieldArrayDictionary<T> 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 derivative sare available)- Throws:
IllegalArgumentException
- if orbit and attitude dates or frames are not equal- Since:
- 11.1
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FieldSpacecraftState
public FieldSpacecraftState(Field<T> field, SpacecraftState state)
Convert aFieldSpacecraftState
.- Parameters:
field
- field to which the elements belongstate
- state to convert
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FieldSpacecraftState
public FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva)
Build a spacecraft state from orbit only.Attitude and mass are set to unspecified non-null arbitrary values.
- Parameters:
absPva
- position-velocity-acceleration
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FieldSpacecraftState
public FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude) throws IllegalArgumentException
Build a spacecraft state from orbit and attitude.Mass is set to an unspecified non-null arbitrary value.
- Parameters:
absPva
- position-velocity-accelerationattitude
- attitude- Throws:
IllegalArgumentException
- if orbit and attitude dates or frames are not equal
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FieldSpacecraftState
public FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, T mass)
Create a new instance from orbit and mass.Attitude law is set to an unspecified default attitude.
- Parameters:
absPva
- position-velocity-accelerationmass
- the mass (kg)
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FieldSpacecraftState
public FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, T mass) throws IllegalArgumentException
Build a spacecraft state from orbit, attitude and mass.- Parameters:
absPva
- position-velocity-accelerationattitude
- attitudemass
- the mass (kg)- Throws:
IllegalArgumentException
- if orbit and attitude dates or frames are not equal
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FieldSpacecraftState
public FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldArrayDictionary<T> additional)
Build a spacecraft state from orbit only.Attitude and mass are set to unspecified non-null arbitrary values.
- Parameters:
absPva
- position-velocity-accelerationadditional
- additional states- Since:
- 11.1
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FieldSpacecraftState
public FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, FieldArrayDictionary<T> additional) throws IllegalArgumentException
Build a spacecraft state from orbit and attitude.Mass is set to an unspecified non-null arbitrary value.
- Parameters:
absPva
- position-velocity-accelerationattitude
- attitudeadditional
- additional states- Throws:
IllegalArgumentException
- if orbit and attitude dates or frames are not equal- Since:
- 11.1
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FieldSpacecraftState
public FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, T mass, FieldArrayDictionary<T> additional)
Create a new instance from orbit and mass.Attitude law is set to an unspecified default attitude.
- Parameters:
absPva
- position-velocity-accelerationmass
- the mass (kg)additional
- additional states- Since:
- 11.1
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FieldSpacecraftState
public FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, T mass, FieldArrayDictionary<T> additional)
Build a spacecraft state from orbit, attitude and mass.- Parameters:
absPva
- position-velocity-accelerationattitude
- attitudemass
- the mass (kg)additional
- additional states (may be null if no additional states are available)- Since:
- 11.1
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FieldSpacecraftState
public FieldSpacecraftState(FieldAbsolutePVCoordinates<T> absPva, FieldAttitude<T> attitude, T mass, FieldArrayDictionary<T> additional, FieldArrayDictionary<T> additionalDot) throws IllegalArgumentException
Build a spacecraft state from orbit, attitude and mass.- Parameters:
absPva
- position-velocity-accelerationattitude
- 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
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Method Detail
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addAdditionalState
@SafeVarargs public final FieldSpacecraftState<T> addAdditionalState(String name, T... 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 statevalue
- value of the additional state- Returns:
- a new instance, with the additional state added
- See Also:
hasAdditionalState(String)
,getAdditionalState(String)
,getAdditionalStatesValues()
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addAdditionalStateDerivative
@SafeVarargs public final FieldSpacecraftState<T> addAdditionalStateDerivative(String name, T... value)
Add an additional state derivative.FieldSpacecraftState
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 derivativevalue
- value of the additional state derivative- Returns:
- a new instance, with the additional state derivative added
- See Also:
hasAdditionalStateDerivative(String)
,getAdditionalStateDerivative(String)
,getAdditionalStatesDerivatives()
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isOrbitDefined
public boolean isOrbitDefined()
Check if the state contains an orbit part.A state contains either an
absolute position-velocity-acceleration
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 position-velocity-acceleration (in which casegetAbsPVA()
will not throw an exception)
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shiftedBy
public FieldSpacecraftState<T> shiftedBy(double dt)
Get a time-shifted state.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 neither mass nor additional states changes. It 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<T extends CalculusFieldElement<T>>
- Parameters:
dt
- time shift in seconds- Returns:
- a new state, shifted with respect to the instance (which is immutable) except for the mass which stay unchanged
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shiftedBy
public FieldSpacecraftState<T> shiftedBy(T dt)
Get a time-shifted state.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 neither mass nor additional states changes. It 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 interfaceFieldTimeShiftable<FieldSpacecraftState<T extends CalculusFieldElement<T>>,T extends CalculusFieldElement<T>>
- Parameters:
dt
- time shift in seconds- Returns:
- a new state, shifted with respect to the instance (which is immutable) except for the mass which stay unchanged
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getAbsPVA
public FieldAbsolutePVCoordinates<T> getAbsPVA() throws OrekitIllegalStateException
Get the absolute position-velocity-acceleration.A state contains either an
absolute position-velocity-acceleration
or anorbit
. Which one is present can be checked usingisOrbitDefined()
.- Returns:
- absolute position-velocity-acceleration
- Throws:
OrekitIllegalStateException
- if position-velocity-acceleration is null, which mean the state rather contains anFieldOrbit
- See Also:
isOrbitDefined()
,getOrbit()
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getOrbit
public FieldOrbit<T> getOrbit() throws OrekitIllegalStateException
Get the current orbit.A state contains either an
absolute position-velocity-acceleration
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 position-velocity-acceleration
- See Also:
isOrbitDefined()
,getAbsPVA()
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getDate
public FieldAbsoluteDate<T> getDate()
Get the date.- Specified by:
getDate
in interfaceFieldTimeStamped<T extends CalculusFieldElement<T>>
- Returns:
- date attached to the object
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getFrame
public Frame getFrame()
Get the defining frame.- Returns:
- the frame in which state is defined
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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, CalculusFieldElement...)
,getAdditionalState(String)
,getAdditionalStatesValues()
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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
- See Also:
addAdditionalStateDerivative(String, CalculusFieldElement...)
,getAdditionalStateDerivative(String)
,getAdditionalStatesDerivatives()
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ensureCompatibleAdditionalStates
public void ensureCompatibleAdditionalStates(FieldSpacecraftState<T> state) throws MathIllegalArgumentException
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:
MathIllegalArgumentException
- if an additional state does not have the same dimension in both states
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getAdditionalState
public T[] getAdditionalState(String name)
Get an additional state.- Parameters:
name
- name of the additional state- Returns:
- value of the additional state
- See Also:
addAdditionalState(String, CalculusFieldElement...)
,hasAdditionalState(String)
,getAdditionalStatesValues()
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getAdditionalStateDerivative
public T[] 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, CalculusFieldElement...)
,hasAdditionalStateDerivative(String)
,getAdditionalStatesDerivatives()
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getAdditionalStatesValues
public FieldArrayDictionary<T> getAdditionalStatesValues()
Get an unmodifiable map of additional states.- Returns:
- unmodifiable map of additional states
- Since:
- 11.1
- See Also:
addAdditionalState(String, CalculusFieldElement...)
,hasAdditionalState(String)
,getAdditionalState(String)
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getAdditionalStatesDerivatives
public FieldArrayDictionary<T> getAdditionalStatesDerivatives()
Get an unmodifiable map of additional states derivatives.- Returns:
- unmodifiable map of additional states derivatives
- Since:
- 11.1
- See Also:
addAdditionalStateDerivative(String, CalculusFieldElement...)
,hasAdditionalStateDerivative(String)
,getAdditionalStateDerivative(String)
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toTransform
public FieldTransform<T> toTransform()
Compute the transform from state defining frame to spacecraft frame.The spacecraft frame origin is at the point defined by the orbit, and its orientation is defined by the attitude.
- Returns:
- transform from specified frame to current spacecraft frame
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toStaticTransform
public FieldStaticTransform<T> 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()
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getMu
public T 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
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getKeplerianPeriod
public T 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
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getKeplerianMeanMotion
public T 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
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getA
public T 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
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getEquinoctialEx
public T 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()
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getEquinoctialEy
public T 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()
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getHx
public T 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()
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getHy
public T 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()
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getLv
public T getLv()
Get the true latitude argument (as per equinoctial parameters).
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getLE
public T getLE()
Get the eccentric latitude argument (as per equinoctial parameters).
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getLM
public T getLM()
Get the mean longitude argument (as per equinoctial parameters).
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getE
public T 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()
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getPosition
public FieldVector3D<T> getPosition()
Get the position in orbit definition frame.- Returns:
- position in orbit definition frame
- Since:
- 12.0
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getPVCoordinates
public TimeStampedFieldPVCoordinates<T> getPVCoordinates()
Get theTimeStampedFieldPVCoordinates
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
TimeStampedFieldPVCoordinates
, so the caller is responsible to copy it in a separateTimeStampedFieldPVCoordinates
if it needs to keep the value for a while.- Returns:
- pvCoordinates in orbit definition frame
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getPosition
public FieldVector3D<T> 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)
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getPVCoordinates
public TimeStampedFieldPVCoordinates<T> getPVCoordinates(Frame outputFrame)
Get theTimeStampedFieldPVCoordinates
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
TimeStampedFieldPVCoordinates
, so the caller is responsible to copy it in a separateTimeStampedFieldPVCoordinates
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
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getAttitude
public FieldAttitude<T> getAttitude()
Get the attitude.- Returns:
- the attitude.
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getMass
public T getMass()
Gets the current mass.- Returns:
- the mass (kg)
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toSpacecraftState
public SpacecraftState toSpacecraftState()
To convert a FieldSpacecraftState instance into a SpacecraftState instance.- Returns:
- SpacecraftState instance with the same properties
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