| Package | Description |
|---|---|
| fr.cnes.sirius.patrius.attitudes | |
| fr.cnes.sirius.patrius.attitudes.multi | |
| fr.cnes.sirius.patrius.attitudes.profiles | |
| fr.cnes.sirius.patrius.propagation |
| Modifier and Type | Method and Description |
|---|---|
Attitude |
TwoSpinBiasSlew.getAttitude(AbsoluteDate date,
Frame frame) |
Attitude |
AbstractIsisSpinBiasSlew.getAttitude(AbsoluteDate date,
Frame frame)
Compute the attitude.
|
Attitude |
Slew.getAttitude(AbsoluteDate date,
Frame frame)
Compute the attitude.
|
Attitude |
ConstantSpinSlew.getAttitude(AbsoluteDate date,
Frame frame) |
Attitude |
AttitudeLegLaw.getAttitude(Orbit orbit)
Compute the attitude corresponding to an orbital state.
|
Attitude |
RelativeTabulatedAttitudeLeg.getAttitude(Orbit orbit)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AbstractAttitudeLaw.getAttitude(Orbit orbit)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudesSequence.getAttitude(Orbit orbit)
Compute the attitude corresponding to an orbital state.
|
Attitude |
TabulatedAttitude.getAttitude(Orbit orbit)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AbstractSlew.getAttitude(Orbit orbit)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudeProvider.getAttitude(Orbit orbit)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudeLegsSequence.getAttitude(Orbit orbit)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudeLawLeg.getAttitude(Orbit orbit)
Compute the attitude corresponding to an orbital state.
|
Attitude |
RelativeTabulatedAttitudeLaw.getAttitude(Orbit orbit)
Compute the attitude corresponding to an orbital state.
|
Attitude |
LofOffsetPointing.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
YawCompensation.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
LofOffset.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudeLegLaw.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
RelativeTabulatedAttitudeLeg.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
YawSteering.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
BodyCenterPointing.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
SpinStabilized.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
CelestialBodyPointed.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
TwoDirectionsAttitude.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
GroundPointing.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudesSequence.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
TabulatedAttitude.getAttitude(PVCoordinatesProvider pvProvider,
AbsoluteDate date,
Frame inFrame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AbstractSlew.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Warning: provided
PVCoordinatesProvider is here not used. |
Attitude |
AttitudeProvider.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudeLegsSequence.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Gets the attitude from the sequence.
The AttitudeLeg matching the date is called to compute the attitude. |
Attitude |
ComposedAttitudeLaw.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
Attitude |
IsisSunPointing.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
TargetPointing.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudeLawLeg.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
Attitude |
ConstantAttitudeLaw.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
RelativeTabulatedAttitudeLaw.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
FixedRate.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AeroAttitudeLaw.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
GroundPointingWrapper.getBaseState(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the base system state at given date, without compensation.
|
Attitude |
AttitudeLegsSequence.getPreviousAttitude(PVCoordinatesProvider provider,
AbsoluteDate date,
Frame frame)
Returns attitude from previous leg (compared to leg matching provided date) from the
sequence.
|
Attitude |
FixedRate.getReferenceAttitude()
Get the reference attitude.
|
Attitude |
Attitude.interpolate(AbsoluteDate interpolationDate,
Collection<Attitude> sample)
Get an interpolated instance.
|
Attitude |
Attitude.interpolate(AbsoluteDate interpolationDate,
Collection<Attitude> sample,
boolean computeSpinDerivatives)
Interpolates attitude.
|
Attitude |
Attitude.shiftedBy(double dt)
Get a time-shifted attitude.
|
static Attitude |
Attitude.slerp(AbsoluteDate date,
Attitude attitude1,
Attitude attitude2,
Frame frame,
boolean computeSpinDerivative)
The slerp interpolation method is efficient but is less accurate than the interpolate method.
|
Attitude |
Attitude.withReferenceFrame(Frame newReferenceFrame)
Get a similar attitude with a specific reference frame.
|
Attitude |
Attitude.withReferenceFrame(Frame newReferenceFrame,
boolean spinDerivativesComputation)
Get a similar attitude with a specific reference frame.
|
| Modifier and Type | Method and Description |
|---|---|
SortedSet<Attitude> |
AbstractAttitudeEphemerisGenerator.generateEphemeris(AbsoluteDateInterval ephemerisInterval,
Frame frame)
Computes attitude ephemeris using a fixed or variable time step and choosing the interval of validity.
|
SortedSet<Attitude> |
AbstractAttitudeEphemerisGenerator.generateEphemeris(Frame frame)
Computes attitude ephemeris using a fixed or variable time step.
|
List<Attitude> |
TabulatedAttitude.getAttitudes()
Get the non-interpolated and rightly ordered attitudes.
|
| Modifier and Type | Method and Description |
|---|---|
int |
AttitudeChronologicalComparator.compare(Attitude o1,
Attitude o2)
Compare two Attitude instances.
|
TimeStampedAngularCoordinates |
YawCompensation.getCompensation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame orbitFrame,
Attitude base)
Compute the TimeStampedAngularCoordinates at a given time.
|
abstract TimeStampedAngularCoordinates |
GroundPointingWrapper.getCompensation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame,
Attitude base)
Compute the TimeStampedAngularCoordinates at a given time.
|
TimeStampedAngularCoordinates |
YawSteering.getCompensation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame orbitFrame,
Attitude base)
Compute the TimeStampedAngularCoordinates at a given time.
|
static Attitude |
Attitude.slerp(AbsoluteDate date,
Attitude attitude1,
Attitude attitude2,
Frame frame,
boolean computeSpinDerivative)
The slerp interpolation method is efficient but is less accurate than the interpolate method.
|
| Modifier and Type | Method and Description |
|---|---|
Attitude |
Attitude.interpolate(AbsoluteDate interpolationDate,
Collection<Attitude> sample)
Get an interpolated instance.
|
Attitude |
Attitude.interpolate(AbsoluteDate interpolationDate,
Collection<Attitude> sample,
boolean computeSpinDerivatives)
Interpolates attitude.
|
| Constructor and Description |
|---|
FixedRate(Attitude pReferenceAttitude)
Creates a new instance.
|
| Constructor and Description |
|---|
TabulatedAttitude(List<Attitude> inAttitudes)
Constructor with default number N of points used for interpolation.
|
TabulatedAttitude(List<Attitude> inAttitudes,
int nbInterpolationPoints)
Constructor with number of points used for interpolation
|
| Modifier and Type | Method and Description |
|---|---|
Attitude |
MultiAttitudeProviderWrapper.getAttitude(Map<String,Orbit> orbits)
Computes the attitude corresponding to several orbital states.
|
Attitude |
MultiAttitudeProvider.getAttitude(Map<String,Orbit> orbits)
Computes the attitude corresponding to several orbital states.
|
Attitude |
MultiAttitudeProviderWrapper.getAttitude(Map<String,PVCoordinatesProvider> pvProvs,
AbsoluteDate date,
Frame frame)
Computes the attitude corresponding to several orbital states.
|
Attitude |
MultiAttitudeProvider.getAttitude(Map<String,PVCoordinatesProvider> pvProvs,
AbsoluteDate date,
Frame frame)
Computes the attitude corresponding to several orbital states.
|
| Modifier and Type | Method and Description |
|---|---|
Attitude |
AttitudeProfilesSequence.getAttitude(Orbit orbit)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AbstractAttitudeProfile.getAttitude(Orbit orbit)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AbstractGuidanceProfile.getAttitude(Orbit orbit)
Compute the attitude corresponding to an orbital state.
|
Attitude |
QuaternionPolynomialProfile.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudeProfilesSequence.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Gets the attitude from the sequence.
The AttitudeProfile matching the date is called to compute the attitude. |
Attitude |
AngularVelocitiesPolynomialProfile.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate userDate,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AngularVelocitiesHarmonicProfile.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate userDate,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
QuaternionHarmonicProfile.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
| Modifier and Type | Method and Description |
|---|---|
Attitude |
SpacecraftState.getAttitude()
Get the default attitude : the attitude for forces computation.
|
Attitude |
SpacecraftState.getAttitude(Frame outputFrame)
Get the default attitude : the attitude for forces computation in given output frame.
|
Attitude |
SpacecraftState.getAttitude(LOFType lofType)
Get the default attitude : the attitude for forces computation in given local
orbital frame.
|
Attitude |
SpacecraftState.getAttitudeEvents()
Get the attitude for events computation.
|
Attitude |
SpacecraftState.getAttitudeEvents(Frame outputFrame)
Get the attitude for events computation in given output frame.
|
Attitude |
SpacecraftState.getAttitudeEvents(LOFType lofType)
Get the attitude for events computation in given local orbital frame.
|
Attitude |
SpacecraftState.getAttitudeForces()
Get the attitude for forces computation.
|
Attitude |
SpacecraftState.getAttitudeForces(Frame outputFrame)
Get the attitude for forces computation in given output frame.
|
Attitude |
SpacecraftState.getAttitudeForces(LOFType lofType)
Get the attitude for forces computation in given local orbital frame.
|
| Modifier and Type | Method and Description |
|---|---|
SpacecraftState |
SpacecraftState.addAttitude(Attitude newAttitude,
AttitudeEquation.AttitudeType type)
Add attitude to the additional states map.
|
| Constructor and Description |
|---|
SpacecraftState(double[] y,
OrbitType orbitType,
PositionAngle angleType,
AbsoluteDate date,
double mu,
Frame frame,
Map<String,AdditionalStateInfo> addStatesInfo,
Attitude attForces,
Attitude attEvents)
Build a spacecraft from an array (a state vector) and an additional states informations map.
|
SpacecraftState(Orbit orbitIn,
Attitude attitudeIn)
Build a spacecraft state from orbit and a single attitude.
|
SpacecraftState(Orbit orbitIn,
Attitude attForces,
Attitude attEvents)
Build a spacecraft state from orbit, attitude for forces and events computation.
|
SpacecraftState(Orbit orbitIn,
Attitude attForces,
Attitude attEvents,
Map<String,double[]> addStates)
Build a spacecraft state from orbit, attitude for forces and events computation and additional states map.
|
SpacecraftState(Orbit orbitIn,
Attitude attForces,
Attitude attEvents,
MassProvider massProvider)
Build a spacecraft state from orbit, attitude for forces and events computation and mass provider.
|
SpacecraftState(Orbit orbitIn,
Attitude attForces,
Attitude attEvents,
MassProvider massProvider,
Map<String,double[]> additionalStatesIn)
Build a spacecraft state from orbit, attitude for forces and events computation, mass provider and additional
states map.
|
SpacecraftState(Orbit orbitIn,
Attitude attitudeIn,
MassProvider massProvider)
Build a spacecraft state from orbit, attitude and mass provider.
|
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