| Modifier and Type | Class and Description |
|---|---|
class |
SensorModel |
| Modifier and Type | Method and Description |
|---|---|
PVCoordinatesProvider |
SensorModel.getInhibitionTarget(int inhibitionFieldNumber)
Returns inhibition field number #i.
|
PVCoordinatesProvider |
SensorModel.getMainTarget()
Returns the main target.
|
PVCoordinatesProvider |
SensorModel.getMaskingBody()
Returns the last masking body.
|
PVCoordinatesProvider |
SensorModel.getMaskingSpacecraft()
Returns the last masking spacecraft.
|
| Modifier and Type | Method and Description |
|---|---|
void |
SensorModel.setMainTarget(PVCoordinatesProvider target,
ApparentRadiusProvider radius)
Sets the main target of the sensor property.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinatesProvider[] |
SensorProperty.getInhibitionTargets() |
PVCoordinatesProvider |
SensorProperty.getMainTarget() |
| Modifier and Type | Method and Description |
|---|---|
void |
SensorProperty.setInhibitionFieldsAndTargets(IFieldOfView[] fields,
PVCoordinatesProvider[] targets,
ApparentRadiusProvider[] targetRadiuses)
Sets the arrays of inhibition fields and the associated targets : the two array must
have the same length.
|
void |
SensorProperty.setMainTarget(PVCoordinatesProvider target,
ApparentRadiusProvider radius)
Sets the main target of the sensor
|
| Modifier and Type | Class and Description |
|---|---|
class |
AttitudeFrame
This class is a special implementation of the
Frame class; it represents a dynamic spacecraft frame,
i.e. |
class |
OrientationFrame
This class is a special implementation of the
Frame class; it represents a dynamic orientation frame,
i.e. |
| Modifier and Type | Field and Description |
|---|---|
protected PVCoordinatesProvider |
AbstractAttitudeEphemerisGenerator.provider
PV coordinate provider.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinatesProvider |
YawSteering.getSun()
Returns the Sun.
|
| Modifier and Type | Method and Description |
|---|---|
default Vector3D |
AttitudeLeg.computeSpinByFD(PVCoordinatesProvider pvProv,
Frame frame,
AbsoluteDate date,
double computationStep)
Compute the rotation rate vector at a given date by finite differences (using 2nd order centered finite
differences).
|
default Vector3D |
AttitudeProvider.computeSpinByFD(PVCoordinatesProvider pvProv,
Frame frame,
AbsoluteDate date,
double computationStep)
Compute the rotation rate vector at a given date by finite differences (using 2nd order centered finite
differences).
|
default Vector3D |
AttitudeLeg.computeSpinDerivativeByFD(PVCoordinatesProvider pvProv,
Frame frame,
AbsoluteDate date,
double computationStep)
Compute the rotation acceleration vector at a given date by finite differences (using 2nd order centered finite
differences).
|
default Vector3D |
AttitudeProvider.computeSpinDerivativeByFD(PVCoordinatesProvider pvProv,
Frame frame,
AbsoluteDate date,
double computationStep)
Compute the rotation acceleration vector at a given date by finite differences (using 2nd order centered finite
differences).
|
Attitude |
LofOffsetPointing.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 |
AttitudeProvider.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 |
AttitudeLegLaw.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
ComposedAttitudeLaw.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
TabulatedAttitude.getAttitude(PVCoordinatesProvider pvProvider,
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 |
LofOffset.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 |
StrictAttitudeLegsSequence.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 |
TwoDirectionsAttitude.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Deprecated.
Compute the attitude corresponding to an orbital state.
|
Attitude |
ConstantAttitudeLaw.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudeLawLeg.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 |
YawCompensation.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
IsisSunAndPseudoSpinPointing.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
TabulatedSlew.getAttitude(PVCoordinatesProvider pvProvider,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
IsisSunPointing.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
ConstantSpinSlew.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Warning: provided
PVCoordinatesProvider is here not used. |
Attitude |
TwoDirectionAttitudeLaw.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AbstractGroundPointing.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 |
CelestialBodyPointed.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 |
AbstractGroundPointingWrapper.getBaseState(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the base system state at given date, without compensation.
|
TimeStampedAngularCoordinates |
YawSteering.getCompensation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame orbitFrame,
Attitude base)
Compute the TimeStampedAngularCoordinates at a given time.
|
TimeStampedAngularCoordinates |
YawCompensation.getCompensation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame orbitFrame,
Attitude base)
Compute the TimeStampedAngularCoordinates at a given time.
|
abstract TimeStampedAngularCoordinates |
AbstractGroundPointingWrapper.getCompensation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame,
Attitude base)
Compute the TimeStampedAngularCoordinates at a given time.
|
Attitude |
AbstractAttitudeEphemerisGenerator.getPreviousAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Returns attitude from previous leg (compared to leg matching provided date) from the
sequence.
|
protected Vector3D |
LofOffsetPointing.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
protected Vector3D |
NadirPointing.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
protected Vector3D |
TargetGroundPointing.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
protected Vector3D |
BodyCenterGroundPointing.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
protected abstract Vector3D |
AbstractGroundPointing.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
protected Vector3D |
AbstractGroundPointingWrapper.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
TimeStampedPVCoordinates |
NadirPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
protected TimeStampedPVCoordinates |
AbstractGroundPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
protected TimeStampedPVCoordinates |
AbstractGroundPointingWrapper.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
double |
YawCompensation.getYawAngle(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the yaw compensation angle at date.
|
| Constructor and Description |
|---|
AbstractAttitudeEphemerisGenerator(StrictAttitudeLegsSequence<AttitudeLeg> legsSequence,
int transitionPoints,
PVCoordinatesProvider providerIn)
Simple constructor.
|
AttitudeFrame(PVCoordinatesProvider pvProvider,
AttitudeProvider attitudeProv,
Frame referenceFrame)
Constructor of the dynamic spacecraft frame.
|
AttitudeTransformProvider(AttitudeProvider attProvider,
PVCoordinatesProvider pv,
Frame frame)
Protected constructor.
|
CelestialBodyPointed(Frame pCelestialFrame,
PVCoordinatesProvider pPointedBody,
Vector3D pPhasingCel,
Vector3D pPointingSat,
Vector3D pPhasingSat)
Creates new instance.
|
FixedStepAttitudeEphemerisGenerator(StrictAttitudeLegsSequence legsSequence,
double fixedStep,
int transitions,
PVCoordinatesProvider providerIn)
Builds an attitude ephemeris generator using a fixed time step and choosing the treatment to apply to the
transition points of the sequence.
|
FixedStepAttitudeEphemerisGenerator(StrictAttitudeLegsSequence legsSequence,
double fixedStep,
PVCoordinatesProvider providerIn)
Builds an attitude ephemeris generator using a fixed time step and ignoring the attitude law transition points of
the sequence.
|
VariableStepAttitudeEphemerisGenerator(StrictAttitudeLegsSequence<AttitudeLeg> legsSequence,
double stepMin,
double stepMax,
double angDistMax,
int transitions,
PVCoordinatesProvider providerIn)
Builds an attitude ephemeris generator using a variable time step and
choosing the treatment to apply to the transition points of the sequence.
|
VariableStepAttitudeEphemerisGenerator(StrictAttitudeLegsSequence<AttitudeLeg> legsSequence,
double stepMin,
double stepMax,
double angDistMax,
PVCoordinatesProvider providerIn)
Builds an attitude ephemeris generator using a variable time step and
ignoring the attitude law transition points of the sequence.
|
YawSteering(AbstractGroundPointing groundPointingLaw,
PVCoordinatesProvider sunIn,
Vector3D phasingAxisIn)
Creates a new instance.
|
YawSteering(AbstractGroundPointing groundPointingLaw,
PVCoordinatesProvider sunIn,
Vector3D phasingAxisIn,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec)
Constructor.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinatesProvider |
EarthCenterDirection.getTargetPvProvider()
Provides the
PVCoordinatesProvider associated to the target object. |
PVCoordinatesProvider |
ToCelestialBodyCenterDirection.getTargetPvProvider()
Provides the
PVCoordinatesProvider associated to the target object. |
PVCoordinatesProvider |
EarthToCelestialBodyCenterDirection.getTargetPvProvider()
Provides the
PVCoordinatesProvider associated to the target object. |
PVCoordinatesProvider |
GenericTargetDirection.getTargetPvProvider()
Provides the
PVCoordinatesProvider associated to the target object. |
PVCoordinatesProvider |
ITargetDirection.getTargetPvProvider()
Provides the
PVCoordinatesProvider associated to the target object. |
| Modifier and Type | Method and Description |
|---|---|
static Vector3D |
StellarAberrationCorrection.applyInverseTo(PVCoordinatesProvider transmitter,
Vector3D transmitterToTargetDir,
Frame frame,
AbsoluteDate date)
Return the direction in which the signal should be emitted to reach the Target due to stellar aberration.
Warning: The Observer transmits the signal to the target. |
static Vector3D |
StellarAberrationCorrection.applyTo(PVCoordinatesProvider observer,
Vector3D observerToTargetDir,
Frame frame,
AbsoluteDate date)
Return the Target apparent direction from Observer position due to stellar aberration.
The Observer receives the signal emitted by the Target. |
Vector3D |
GlintApproximatePointingDirection.getGlintVectorPosition(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Get the position vector of the glint point
|
Line |
MomentumDirection.getLine(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
|
Line |
EarthCenterDirection.getLine(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
|
Line |
VelocityDirection.getLine(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
|
Line |
ConstantVectorDirection.getLine(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the line containing the given origin point and directed by the direction vector
|
Line |
ToCelestialBodyCenterDirection.getLine(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
|
Line |
NorthNormalToEclipticDirection.getLine(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
|
Line |
NadirDirection.getLine(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
|
Line |
GlintApproximatePointingDirection.getLine(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
|
Line |
EarthToCelestialBodyCenterDirection.getLine(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
|
Line |
IDirection.getLine(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
|
Line |
GroundVelocityDirection.getLine(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
|
Line |
GenericTargetDirection.getLine(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
|
Line |
CrossProductDirection.getLine(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the cross product of directions.
|
Line |
CelestialBodyPolesAxisDirection.getLine(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
|
Line |
EarthCenterDirection.getLine(PVCoordinatesProvider origin,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon)
Provides the half line containing both origin and target, taking into account the type of date (emission or
reception), corrected for light-time and stellar aberration pending the entered correction parameter.
|
Line |
ToCelestialBodyCenterDirection.getLine(PVCoordinatesProvider origin,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon)
Provides the half line containing both origin and target, taking into account the type of date (emission or
reception), corrected for light-time and stellar aberration pending the entered correction parameter.
|
Line |
EarthToCelestialBodyCenterDirection.getLine(PVCoordinatesProvider origin,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon)
Provides the half line containing both origin and target, taking into account the type of date (emission or
reception), corrected for light-time and stellar aberration pending the entered correction parameter.
|
Line |
GenericTargetDirection.getLine(PVCoordinatesProvider origin,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon)
Provides the half line containing both origin and target, taking into account the type of date (emission or
reception), corrected for light-time and stellar aberration pending the entered correction parameter.
|
Line |
ITargetDirection.getLine(PVCoordinatesProvider origin,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon)
Provides the half line containing both origin and target, taking into account the type of date (emission or
reception), corrected for light-time and stellar aberration pending the entered correction parameter.
|
Vector3D |
MomentumDirection.getVector(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
EarthCenterDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
VelocityDirection.getVector(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
ConstantVectorDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
ToCelestialBodyCenterDirection.getVector(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
NorthNormalToEclipticDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
NadirDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
GlintApproximatePointingDirection.getVector(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
EarthToCelestialBodyCenterDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
IDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
GroundVelocityDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
GenericTargetDirection.getVector(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
CrossProductDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the cross product of direction1 vector and dirction2 vector.
|
Vector3D |
CelestialBodyPolesAxisDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
EarthCenterDirection.getVector(PVCoordinatesProvider origin,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon)
Provides the direction vector (from origin to target) at entered date, taking into account the type of date
(emission or reception), corrected for light-time and stellar aberration pending the entered correction
parameter.
|
Vector3D |
ToCelestialBodyCenterDirection.getVector(PVCoordinatesProvider origin,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon)
Provides the direction vector (from origin to target) at entered date, taking into account the type of date
(emission or reception), corrected for light-time and stellar aberration pending the entered correction
parameter.
|
Vector3D |
EarthToCelestialBodyCenterDirection.getVector(PVCoordinatesProvider origin,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon)
Provides the direction vector (from origin to target) at entered date, taking into account the type of date
(emission or reception), corrected for light-time and stellar aberration pending the entered correction
parameter.
|
Vector3D |
GenericTargetDirection.getVector(PVCoordinatesProvider origin,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon)
Provides the direction vector (from origin to target) at entered date, taking into account the type of date
(emission or reception), corrected for light-time and stellar aberration pending the entered correction
parameter.
|
Vector3D |
ITargetDirection.getVector(PVCoordinatesProvider origin,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon)
Provides the direction vector (from origin to target) at entered date, taking into account the type of date
(emission or reception), corrected for light-time and stellar aberration pending the entered correction
parameter.
|
default Vector3D |
ITargetDirection.getVector(PVCoordinatesProvider origin,
PVCoordinatesProvider target,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon,
Frame referenceFrame)
Provides the direction vector (from origin to target) at entered date, taking into account the type of date
(emission or reception), corrected for light-time and stellar aberration pending the entered correction
parameter.
|
| Constructor and Description |
|---|
GenericTargetDirection(PVCoordinatesProvider inTarget)
Build a direction from a target described by its
PVCoordinatesProvider
|
GlintApproximatePointingDirection(EllipsoidBodyShape shape,
PVCoordinatesProvider sunPV)
Constructor with default solver (
BisectionSolver.BisectionSolver(double, double)). |
GlintApproximatePointingDirection(EllipsoidBodyShape shape,
PVCoordinatesProvider sunPV,
UnivariateSolver univariateSolver)
Constructor.
|
MomentumDirection(PVCoordinatesProvider pvProvider)
Build a direction from a
PVCoordinatesProvider. |
| Modifier and Type | Method and Description |
|---|---|
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 |
|---|---|
default double |
OrientationAngleProvider.computeSpinByFD(PVCoordinatesProvider pvProv,
AbsoluteDate date,
double computationStep)
Compute the orientation derivative at a given date by finite differences (using 2nd order centered finite
differences).
|
default double |
OrientationAngleLeg.computeSpinByFD(PVCoordinatesProvider pvProv,
AbsoluteDate date,
double computationStep)
Compute the orientation derivative at a given date by finite differences (using 2nd order centered finite
differences).
|
default double |
OrientationAngleProvider.computeSpinDerivativeByFD(PVCoordinatesProvider pvProv,
AbsoluteDate date,
double computationStep)
Compute the orientation acceleration vector at a given date by finite differences
(using 2nd order centered finite differences).
|
default double |
OrientationAngleLeg.computeSpinDerivativeByFD(PVCoordinatesProvider pvProv,
AbsoluteDate date,
double computationStep)
Compute the orientation acceleration vector at a given date by finite differences
(using 2nd order centered finite differences).
|
Double |
OrientationAngleProvider.getOrientationAngle(PVCoordinatesProvider pvProv,
AbsoluteDate date)
Compute the orientation angle corresponding to an orbital state.
|
Double |
ConstantOrientationAngleLeg.getOrientationAngle(PVCoordinatesProvider pvProv,
AbsoluteDate date)
Compute the orientation angle corresponding to an orbital state.
|
Double |
ConstantOrientationAngleLaw.getOrientationAngle(PVCoordinatesProvider pvProv,
AbsoluteDate date)
Compute the orientation angle corresponding to an orbital state.
|
Double |
OrientationAngleProfileSequence.getOrientationAngle(PVCoordinatesProvider pvProv,
AbsoluteDate date)
Compute the orientation angle corresponding to an orbital state.
|
Double |
OrientationAngleLawLeg.getOrientationAngle(PVCoordinatesProvider pvProv,
AbsoluteDate date)
Compute the orientation angle corresponding to an orbital state.
|
Double |
OrientationAngleLegsSequence.getOrientationAngle(PVCoordinatesProvider pvProv,
AbsoluteDate date)
Compute the orientation angle corresponding to an orbital state.
|
| Modifier and Type | Method and Description |
|---|---|
Attitude |
QuaternionHarmonicProfile.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AngularVelocitiesPolynomialProfile.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
QuaternionDatePolynomialProfile.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 |
QuaternionPolynomialProfile.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AbstractAngularVelocitiesAttitudeProfile.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
| Modifier and Type | Method and Description |
|---|---|
ConstantSpinSlew |
ConstantSpinSlewComputer.compute(PVCoordinatesProvider pvProv,
AttitudeProvider initialLaw,
AbsoluteDate initialDate,
AttitudeProvider finalLaw,
AbsoluteDate finalDate)
Compute the slew.
|
TabulatedSlew |
TwoSpinBiasSlewComputer.compute(PVCoordinatesProvider pvProv,
AttitudeProvider initialLaw,
AbsoluteDate initialDate,
AttitudeProvider finalLaw,
AbsoluteDate finalDate)
Compute the slew.
|
TabulatedSlew |
IsisSpinBiasSlewComputer.computeAnalytical(PVCoordinatesProvider pvProv,
AttitudeProvider initialLaw,
AbsoluteDate initialDateIn,
AttitudeProvider finalLaw,
AbsoluteDate finalDate)
Compute the slew (analytical version).
|
double |
IsisSpinBiasSlewComputer.computeDuration(PVCoordinatesProvider pvProv,
AttitudeProvider initialLaw,
AbsoluteDate initialDateIn,
AttitudeProvider finalLaw,
AbsoluteDate finalDate)
Computes the slew duration.
|
double |
TwoSpinBiasSlewComputer.computeDuration(PVCoordinatesProvider pvProv,
AttitudeProvider initialLaw,
AbsoluteDate initialDate,
AttitudeProvider finalLaw,
AbsoluteDate finalDate)
Computes the actual slew duration.
|
TabulatedSlew |
IsisSpinBiasSlewComputer.computeNumerical(PVCoordinatesProvider pvProv,
AttitudeProvider initialLaw,
AbsoluteDate initialDateIn,
AttitudeProvider finalLaw,
AbsoluteDate finalDate)
Compute the slew (numerical version).
|
| Modifier and Type | Interface and Description |
|---|---|
interface |
BodyShape
Extended interface for celestial bodies shapes : extends the OREKIT's BodyShape interface by adding
geometric methods.
|
interface |
CelestialBody
Interface for celestial bodies like Sun, Moon or solar system planets.
|
interface |
CelestialBodyEphemeris
Interface for celestial body ephemeris.
|
interface |
EllipsoidBodyShape
Extended interface for spheroid model to represent celestial bodies shape : extends the
StarConvexBodyShape interface by adding getters to access the spheroid parameters. |
interface |
StarConvexBodyShape
Extended interface for star-convex bodies shapes : extends the
BodyShape interface by
adding a method to get a GeodeticPoint of the shape from given latitude,longitude and
altitude. |
| Modifier and Type | Class and Description |
|---|---|
class |
AbstractCelestialBody
Abstract implementation of the
CelestialBody interface. |
class |
EarthEphemeris
Earth ephemeris.
|
class |
MeeusMoon
This class implements the Moon ephemerides according to the algorithm of Meeus.
|
class |
MeeusSun
This class implements the Sun ephemerides according to the algorithm of Meeus, it only provides
the position.
|
class |
OneAxisEllipsoid
Implementation of the EllipsoidBodyShape interface : this an extended spheroid model to represent celestial bodies
shapes.
|
class |
UserCelestialBody
User-defined celestial body.
|
| Modifier and Type | Method and Description |
|---|---|
double |
OneAxisEllipsoid.getApparentRadius(PVCoordinatesProvider pvObserver,
AbsoluteDate date,
PVCoordinatesProvider occultedBody,
AbstractDetector.PropagationDelayType propagationDelayType)
Compute the apparent radius (in meters) of the occulting body from the spacecraft (observer) position.
|
double |
BodyShape.getApparentRadius(PVCoordinatesProvider pvObserver,
AbsoluteDate date,
PVCoordinatesProvider occultedBody,
AbstractDetector.PropagationDelayType propagationDelayType)
Compute the apparent radius (in meters) of the occulting body from the spacecraft (observer) position.
|
Line |
BasicBoardSun.getLine(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Get the line from the position in pvCoord to the Sun.
|
Vector3D |
BasicBoardSun.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Get the direction of the sun.
|
| Constructor and Description |
|---|
UserCelestialBody(String name,
PVCoordinatesProvider aPVCoordinateProvider,
double gm,
IAUPole iauPole,
Frame parentFrame,
BodyShape shapeIn)
Build an instance and the underlying frame.
|
UserCelestialBody(String name,
PVCoordinatesProvider aPVCoordinateProvider,
GravityModel gravityModelIn,
IAUPole iauPole,
Frame parentFrame,
BodyShape shapeIn)
Build an instance and the underlying frame.
|
| Modifier and Type | Class and Description |
|---|---|
class |
FacetBodyShape
Facet body shape defined by a list of facets.
|
class |
StarConvexFacetBodyShape
Star-convex facet body shape defined by a list of facets.
|
| Modifier and Type | Method and Description |
|---|---|
double |
FacetBodyShape.getApparentRadius(PVCoordinatesProvider pvObserver,
AbsoluteDate date,
PVCoordinatesProvider occultedBody,
AbstractDetector.PropagationDelayType propagationDelayType)
Compute the apparent radius (in meters) of the occulting body from the spacecraft (observer) position.
|
List<Triangle> |
FacetBodyShape.getNeverEnlightenedTriangles(List<AbsoluteDate> dates,
PVCoordinatesProvider sun)
Returns the list of triangles never enlightened by the Sun at provided dates.
|
List<Triangle> |
FacetBodyShape.getVisibleAndEnlightenedTriangles(List<SpacecraftState> states,
PVCoordinatesProvider sun,
IFieldOfView fieldOfView)
Returns the list of triangles enlightened (by the Sun) and visible at least once during the
whole ephemeris
from the satellite field of view.
|
boolean |
FacetBodyShape.isInEclipse(AbsoluteDate date,
Vector3D position,
Frame frame,
PVCoordinatesProvider sun)
Returns true if provided position in provided frame at provided date in in eclipse or not.
|
| Constructor and Description |
|---|
CentralBodyMaskCircularFOVDetector(PVCoordinatesProvider occultedBody,
double occultedBodyRadius,
BodyShape occultingBody,
boolean totalEclipseFlag,
Vector3D center,
double halfAperture)
Constructor with default maxcheck and default threshold, creating a circularFOVDetector and
an EllipsoidEclipseDetector
|
CentralBodyMaskCircularFOVDetector(PVCoordinatesProvider occultedBody,
double occultedBodyRadius,
BodyShape occultingBody,
boolean totalEclipseFlag,
Vector3D center,
double halfAperture,
double maxCheck,
double threshold)
Constructor with user maxcheck and threshold creating a circularFOVDetector and an
EllipsoidEclipseDetector
|
CentralBodyMaskCircularFOVDetector(PVCoordinatesProvider occultedBody,
double occultedBodyRadius,
BodyShape occultingBody,
boolean totalEclipseFlag,
Vector3D center,
double halfAperture,
double maxCheck,
double threshold,
EventDetector.Action action)
Constructor with user maxcheck and threshold creating a circularFOVDetector and an
EllipsoidEclipseDetector
|
CentralBodyMaskCircularFOVDetector(PVCoordinatesProvider occultedBody,
double occultedBodyRadius,
BodyShape occultingBody,
boolean totalEclipseFlag,
Vector3D center,
double halfAperture,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Constructor with user maxcheck and threshold creating a circularFOVDetector and an
EllipsoidEclipseDetector
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinatesProvider |
ExtremaSightAxisDetector.getTargetPoint()
Get the target point.
|
| Constructor and Description |
|---|
ExtremaSightAxisDetector(int extremumType,
PVCoordinatesProvider target,
Assembly assembly,
String partName)
Constructor based on an Assembly containing at least one part with sensor property describing
the vehicle.
|
ExtremaSightAxisDetector(int extremumType,
PVCoordinatesProvider target,
Assembly assembly,
String partName,
double maxCheck,
double threshold)
Constructor based on an Assembly containing at least one part with sensor property describing
the vehicle.
|
ExtremaSightAxisDetector(int extremumType,
PVCoordinatesProvider target,
Assembly assembly,
String partName,
double maxCheck,
double threshold,
EventDetector.Action action)
Constructor for both minimal and maximal angle based on an Assembly containing at least one
part with sensor property describing the vehicle.
|
ExtremaSightAxisDetector(int extremumType,
PVCoordinatesProvider target,
Assembly assembly,
String partName,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Constructor for both minimal and maximal angle based on an Assembly containing at least one
part with sensor property describing the vehicle.
|
ExtremaSightAxisDetector(int extremumType,
PVCoordinatesProvider target,
Vector3D sightAxisDirection)
Constructor to use without assembly.
|
ExtremaSightAxisDetector(int extremumType,
PVCoordinatesProvider target,
Vector3D sightAxisDirection,
double maxCheck,
double threshold)
Constructor to use without assembly.
|
ExtremaSightAxisDetector(int extremumType,
PVCoordinatesProvider target,
Vector3D sightAxisDirection,
double maxCheck,
double threshold,
EventDetector.Action action)
Constructor to use without assembly.
|
ExtremaSightAxisDetector(int extremumType,
PVCoordinatesProvider target,
Vector3D sightAxisDirection,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Constructor to use without assembly.
|
ExtremaSightAxisDetector(PVCoordinatesProvider target,
Assembly assembly,
String partName,
double maxCheck,
double threshold,
EventDetector.Action actionMin,
EventDetector.Action actionMax)
Constructor for both minimal and maximal angle based on an Assembly containing at least one
part with sensor property describing the vehicle.
|
ExtremaSightAxisDetector(PVCoordinatesProvider target,
Assembly assembly,
String partName,
double maxCheck,
double threshold,
EventDetector.Action actionMin,
EventDetector.Action actionMax,
boolean removeMin,
boolean removeMax)
Constructor for both minimal and maximal angle based on an Assembly containing at least one
part with sensor property describing the vehicle.
|
ExtremaSightAxisDetector(PVCoordinatesProvider target,
Vector3D sightAxisDirection,
double maxCheck,
double threshold,
EventDetector.Action actionMin,
EventDetector.Action actionMax)
Constructor to use without assembly for both minimal and maximal angle detection.
|
ExtremaSightAxisDetector(PVCoordinatesProvider target,
Vector3D sightAxisDirection,
double maxCheck,
double threshold,
EventDetector.Action actionMin,
EventDetector.Action actionMax,
boolean removeMin,
boolean removeMax)
Constructor to use without assembly for both minimal and maximal angle detection.
|
| Modifier and Type | Field and Description |
|---|---|
protected PVCoordinatesProvider |
AbstractDTM.sun
Sun position.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinatesProvider |
AbstractDTM.getSun()
Getter for the sun position.
|
| Constructor and Description |
|---|
AbstractDTM(DTMInputParameters parameters,
PVCoordinatesProvider sunIn,
BodyShape earthIn,
String dataFile)
Simple constructor for independent computation.
|
DTM2000(DTMInputParameters parameters,
PVCoordinatesProvider sunIn,
BodyShape earthIn)
Simple constructor for independent computation.
|
DTM2012(DTMInputParameters parameters,
PVCoordinatesProvider sunIn,
BodyShape earthIn)
Simple constructor with PATRIUS data file.
|
DTM2012(DTMInputParameters parameters,
PVCoordinatesProvider sunIn,
BodyShape earthIn,
String dataFilename)
Constructor with user-provided data file.
|
HarrisPriester(PVCoordinatesProvider sunIn,
BodyShape earthIn)
Simple constructor for Modified Harris-Priester atmosphere model.
|
HarrisPriester(PVCoordinatesProvider sunIn,
BodyShape earthIn,
double nIn)
Constructor for Modified Harris-Priester atmosphere model.
|
HarrisPriester(PVCoordinatesProvider sunIn,
BodyShape earthIn,
double[][] tabAltRhoIn)
Constructor for Modified Harris-Priester atmosphere model.
|
HarrisPriester(PVCoordinatesProvider sunIn,
BodyShape earthIn,
double[][] tabAltRhoIn,
double nIn)
Constructor for Modified Harris-Priester atmosphere model.
|
JB2006(JB2006InputParameters parameters,
PVCoordinatesProvider sunIn,
BodyShape earthIn)
Constructor with space environment information for internal computation.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinatesProvider |
SolarRadiationPressure.getSunBody()
Getter for the Sun model used at construction.
|
| Modifier and Type | Method and Description |
|---|---|
double |
SolarRadiationPressure.getLightningRatio(Vector3D satSunVector,
BodyShape occultingBody,
PVCoordinatesProvider pv,
Frame frame,
AbsoluteDate date)
Get the lightning ratio ([0-1]) for provided occulting body.
|
| Constructor and Description |
|---|
RediffusedFlux(int nCorona,
int nMeridian,
Frame bodyFrame,
CelestialBody sunProvider,
PVCoordinatesProvider satProvider,
AbsoluteDate d,
IEmissivityModel model)
Default constructor of rediffused flux.
|
RediffusedFlux(int nCorona,
int nMeridian,
Frame bodyFrame,
CelestialBody sun,
PVCoordinatesProvider satProvider,
AbsoluteDate dDate,
IEmissivityModel model,
boolean inIr,
boolean inAlbedo)
Generic constructor of rediffused flux.
|
SolarRadiationPressure(double dRef,
double pRef,
PVCoordinatesProvider sunBody,
double sunRadiusIn,
BodyShape occultingBody,
Assembly assembly,
double multiplicativeFactorIn)
Creates a new instance.
|
SolarRadiationPressure(double dRef,
double pRef,
PVCoordinatesProvider sunBody,
double sunRadiusIn,
BodyShape occultingBody,
RadiationSensitive spacecraftModel)
Complete constructor.
|
SolarRadiationPressure(double dRef,
double pRef,
PVCoordinatesProvider sunBody,
double sunRadiusIn,
BodyShape occultingBody,
RadiationSensitive spacecraftModel,
boolean computePD)
Complete constructor.
|
SolarRadiationPressure(double dRef,
double pRef,
PVCoordinatesProvider sun,
double sunRadiusIn,
double occultingBodyRadius,
Frame occultingBodyFrame,
RadiationSensitive spacecraft,
boolean computePD)
Complete constructor.
|
SolarRadiationPressure(double dRef,
double pRef,
PVCoordinatesProvider sun,
double sunRadiusIn,
double occultingBodyRadius,
RadiationSensitive spacecraft)
Complete constructor.
|
SolarRadiationPressure(double dRef,
double pRef,
PVCoordinatesProvider sun,
double sunRadiusIn,
double occultingBodyRadius,
RadiationSensitive spacecraft,
boolean computePD)
Complete constructor.
|
SolarRadiationPressure(Parameter referenceFlux,
PVCoordinatesProvider sunBody,
BodyShape occultingBody,
RadiationSensitive spacecraftModel)
Complete constructor using
Parameter. |
SolarRadiationPressure(Parameter referenceFlux,
PVCoordinatesProvider sunBody,
double sunRadiusIn,
BodyShape occultingBody,
RadiationSensitive spacecraftModel,
boolean computePD)
Complete constructor using
Parameter. |
SolarRadiationPressure(Parameter refFluxParam,
PVCoordinatesProvider sun,
double sunRadiusIn,
double occultingBodyRadius,
Frame occultingBodyFrame,
RadiationSensitive spacecraft,
boolean computePD)
Complete constructor.
|
SolarRadiationPressure(Parameter refFluxParam,
PVCoordinatesProvider sun,
double occultingBodyRadius,
RadiationSensitive spacecraft)
Complete constructor.
|
SolarRadiationPressure(Parameter refFluxParam,
PVCoordinatesProvider sun,
double occultingBodyRadius,
RadiationSensitive spacecraft,
boolean computePD)
Complete constructor.
|
SolarRadiationPressure(PVCoordinatesProvider sunBody,
BodyShape occultingBody,
RadiationSensitive spacecraftModel)
Simple constructor with default reference values.
|
SolarRadiationPressure(PVCoordinatesProvider sunBody,
BodyShape occultingBody,
RadiationSensitive spacecraftModel,
boolean computePD)
Simple constructor with default reference values.
|
SolarRadiationPressure(PVCoordinatesProvider sun,
double occultingBodyRadius,
Frame occultingBodyFrame,
RadiationSensitive spacecraft,
boolean computePD)
Simple constructor with default reference values.
|
SolarRadiationPressure(PVCoordinatesProvider sun,
double occultingBodyRadius,
RadiationSensitive spacecraft)
Simple constructor with default reference values.
|
SolarRadiationPressure(PVCoordinatesProvider sun,
double occultingBodyRadius,
RadiationSensitive spacecraft,
boolean computePD)
Simple constructor with default reference values.
|
| Constructor and Description |
|---|
CoriolisRelativisticEffect(double sunMu,
PVCoordinatesProvider sunPV)
Constructor with partial derivative computation by default.
|
CoriolisRelativisticEffect(double sunMu,
PVCoordinatesProvider sunPV,
boolean computePartialDerivativesVel)
Constructor.
|
| Modifier and Type | Class and Description |
|---|---|
class |
CelestialBodyFrame
Frame centered on a
CelestialBody. |
class |
FactoryManagedFrame
Base class for the predefined frames that are managed by
FramesFactory. |
class |
Frame
Tridimensional references frames class.
|
class |
FrozenFrame
Provide a wrapper frame between a reference and a coordinate frame, so that it has no angular velocity
|
class |
H0MinusNFrame
"H0 - n" reference frame.
|
class |
LocalOrbitalFrame
Class for frames moving with an orbiting satellite.
|
class |
SynodicFrame
Synodic frame.
|
class |
TopocentricFrame
Topocentric frame.
|
class |
TranslatedFrame
Frame which differs from a reference frame by translation provided by a
PVCoordinatesProvider. |
class |
UpdatableFrame
Frame whose transform from its parent can be updated.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinatesProvider |
TranslatedFrame.getCenter()
Returns the center of this frame.
|
PVCoordinatesProvider |
LocalOrbitalFrame.getCenter()
Returns the center of the LOF.
|
| Modifier and Type | Method and Description |
|---|---|
void |
LocalOrbitalFrame.setCenter(PVCoordinatesProvider center) |
| Constructor and Description |
|---|
LocalOrbitalFrame(Frame parent,
LOFType type,
PVCoordinatesProvider provider,
String name)
Build a new instance.
|
TranslatedFrame(Frame parent,
PVCoordinatesProvider center,
String name)
Constructor.
|
| Modifier and Type | Class and Description |
|---|---|
class |
GeometricStationAntenna
Class representing an a geometric model for a ground station antenna.
It is used in reverse station visibility event detection. |
class |
RFStationAntenna
This class represents an RF antenna model for a ground station.
|
| Modifier and Type | Class and Description |
|---|---|
class |
AlternateEquinoctialOrbit
This class handles alternate equinoctial orbital parameters, which can support both circular and
equatorial orbits.
|
class |
ApsisOrbit
This class handles periapsis/apoapsis parameters.
|
class |
CartesianOrbit
This class holds cartesian orbital parameters.
|
class |
CircularOrbit
This class handles circular orbital parameters.
|
class |
EquatorialOrbit
This class handles non circular equatorial orbital parameters.
|
class |
EquinoctialOrbit
This class handles equinoctial orbital parameters, which can support both circular and equatorial
orbits.
|
class |
KeplerianOrbit
This class handles traditional keplerian orbital parameters.
|
class |
Orbit
This class handles orbital parameters.
|
| Modifier and Type | Class and Description |
|---|---|
class |
AbstractBoundedPVProvider
This abstract class shall be extended to provides a PVCoordinates provider based on manipulation of PVCoordinates
ephemeris.
|
class |
ConstantPVCoordinatesProvider
This class implements the
PVCoordinatesProvider to store the position and the velocity of an object and the
frame used for computation. |
class |
EphemerisPvHermite
This class extends
AbstractBoundedPVProvider which implements
PVCoordinatesProvider and so provides a position velocity for a
given date. |
class |
EphemerisPvLagrange
This class extends
AbstractBoundedPVProvider which implements
PVCoordinatesProvider and so provides a position velocity for a
given date. |
class |
GNSSPVCoordinates
This class implements the PVCoordinatesProvider to compute position velocity of a GPS, Galileo or
BeiDou constellation satellite from its almanac/broadcast model parameters.
|
| Modifier and Type | Class and Description |
|---|---|
class |
ProjectionEllipsoid
Deprecated.
as of 4.3. This class is replaced by
ProjectionEllipsoidUtils |
| Modifier and Type | Interface and Description |
|---|---|
interface |
BoundedPropagator
This interface is intended for ephemerides valid only during a time range.
|
interface |
Propagator
This interface provides a way to propagate an orbit at any time.
|
interface |
SpacecraftStateProvider
Interface for spacecraft state providers.
|
| Modifier and Type | Class and Description |
|---|---|
class |
AbstractPropagator
Common handling of
Propagator methods for analytical propagators. |
class |
AnalyticalIntegratedEphemeris
This class stores sequentially generated orbital parameters for
later retrieval.
|
class |
PVCoordinatesPropagator
This class is an analytical propagator which propagates states from the input PV, Attitude, and additional state
provider.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinatesProvider |
AbstractPropagator.getPvProvider()
Get PV coordinates provider.
|
| Constructor and Description |
|---|
PVCoordinatesPropagator(PVCoordinatesProvider pvCoordProvider,
AbsoluteDate initDate,
double mu,
Frame frame)
Creates an instance of PVCoordinatePropagator without attitude and additional state providers
|
PVCoordinatesPropagator(PVCoordinatesProvider pvCoordProvider,
AbsoluteDate initDate,
double mu,
Frame frame,
AttitudeProvider attProviderForces,
AttitudeProvider attProviderEvents,
List<AdditionalStateProvider> additionalStateProviders)
Creates an instance of PVCoordinatePropagator with
PV, attitude for forces, attitude for events, and additional state providers
given by the user.
|
| Modifier and Type | Class and Description |
|---|---|
class |
AbstractLyddanePropagator
Abstract Lyddane propagator.
|
class |
AdapterPropagator
Orbit propagator that adapts an underlying propagator, adding
differential effects. |
class |
EcksteinHechlerPropagator
This class propagates a
SpacecraftState using the
analytical Eckstein-Hechler model. |
class |
J2SecularPropagator
J2 secular propagator.
|
class |
KeplerianPropagator
Simple keplerian orbit propagator.
|
class |
LyddaneLongPeriodPropagator
Lyddane long period propagator.
|
class |
LyddaneSecularPropagator
Lyddane secular propagator.
|
| Modifier and Type | Class and Description |
|---|---|
class |
TLEPropagator
This class provides elements to propagate TLE's.
|
| Modifier and Type | Class and Description |
|---|---|
class |
Analytical2DPropagator
This class propagates an analytical 2D orbit model and extends the
AbstractPropagator
class. |
| Modifier and Type | Field and Description |
|---|---|
protected PVCoordinatesProvider |
DistanceDetector.body
Distant body.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinatesProvider |
ExtremaDotProductDetector.getBody() |
PVCoordinatesProvider |
ExtremaDistanceDetector.getBody() |
PVCoordinatesProvider |
DistanceDetector.getBody()
Returns the body whose distance is watched.
|
PVCoordinatesProvider |
ExtremaThreeBodiesAngleDetector.getFirstBody()
Get 1st body
|
PVCoordinatesProvider |
ThreeBodiesAngleDetector.getFirstBody()
Get 1st body.
|
PVCoordinatesProvider |
EclipseDetector.getOcculted()
Get the occulted body.
|
PVCoordinatesProvider |
EclipseDetector.getOcculting()
Get the occulting body.
|
PVCoordinatesProvider |
AlignmentDetector.getPVCoordinatesProvider()
Get the body to align.
|
PVCoordinatesProvider |
CircularFieldOfViewDetector.getPVTarget()
Get the position/velocity provider of the target .
|
PVCoordinatesProvider |
DihedralFieldOfViewDetector.getPVTarget()
Get the position/velocity provider of the target .
|
PVCoordinatesProvider |
ExtremaThreeBodiesAngleDetector.getSecondBody()
Get 2nd body
|
PVCoordinatesProvider |
ThreeBodiesAngleDetector.getSecondBody()
Get 2nd body.
|
PVCoordinatesProvider |
NadirSolarIncidenceDetector.getSun()
Returns Sun.
|
PVCoordinatesProvider |
ExtremaThreeBodiesAngleDetector.getThirdBody()
Get 3rd body
|
PVCoordinatesProvider |
ThreeBodiesAngleDetector.getThirdBody()
Get 3rd body.
|
| Modifier and Type | Method and Description |
|---|---|
double |
ApparentRadiusProvider.getApparentRadius(PVCoordinatesProvider pvObserver,
AbsoluteDate date,
PVCoordinatesProvider occultedBody,
AbstractDetector.PropagationDelayType propagationDelayType)
Compute the apparent radius (in meters) of the occulting body from the spacecraft (observer) position.
|
double |
VariableRadiusProvider.getApparentRadius(PVCoordinatesProvider pvObserver,
AbsoluteDate date,
PVCoordinatesProvider occultedBody,
AbstractDetector.PropagationDelayType propagationDelayType)
Compute the apparent radius (in meters) of the occulting body from the spacecraft (observer) position.
|
double |
ConstantRadiusProvider.getApparentRadius(PVCoordinatesProvider pvObserver,
AbsoluteDate date,
PVCoordinatesProvider occultedBody,
AbstractDetector.PropagationDelayType propagationDelayType)
Compute the apparent radius (in meters) of the occulting body from the spacecraft (observer) position.
|
protected AbsoluteDate |
AbstractDetector.getSignalEmissionDate(PVCoordinatesProvider emitter,
PVCoordinatesProvider orbit,
AbsoluteDate date)
Compute signal emission date which is the date at which the signal received by the spacecraft (receiver) has been
emitted by the emitter depending on
AbstractDetector.PropagationDelayType. |
protected AbsoluteDate |
AbstractDetector.getSignalReceptionDate(PVCoordinatesProvider receiver,
PVCoordinatesProvider orbit,
AbsoluteDate date)
Compute signal reception date which is the date at which the signal emitted by the spacecraft (emitter) has been
received by the receiver depending on
AbstractDetector.PropagationDelayType. |
void |
NadirSolarIncidenceDetector.setSun(PVCoordinatesProvider sun)
Sets the sun
PVCoordinatesProvider |
| Constructor and Description |
|---|
AlignmentDetector(Orbit orbit,
PVCoordinatesProvider bodyIn,
double alignAngleIn)
Build a new alignment detector.
|
AlignmentDetector(Orbit orbit,
PVCoordinatesProvider bodyIn,
double alignAngleIn,
double thresholdIn)
Build a new alignment detector.
|
AlignmentDetector(Orbit orbit,
PVCoordinatesProvider bodyIn,
double alignAngleIn,
double threshold,
EventDetector.Action actionStart,
EventDetector.Action actionEnd)
Build a new alignment detector.
|
AlignmentDetector(Orbit orbit,
PVCoordinatesProvider bodyIn,
double alignAngleIn,
double threshold,
EventDetector.Action actionStart,
EventDetector.Action actionEnd,
boolean removeStart,
boolean removeEnd)
Build a new alignment detector.
|
AlignmentDetector(PVCoordinatesProvider bodyIn,
double alignAngleIn,
double maxcheck,
double threshold,
EventDetector.Action actionStart,
EventDetector.Action actionEnd,
boolean removeStart,
boolean removeEnd)
Build a new alignment detector.
|
CircularFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
double halfApertureIn,
double maxCheckIn)
Build a new instance.
|
CircularFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
double halfApertureIn,
double maxCheck,
double threshold)
Build a new instance.
|
CircularFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
double halfApertureIn,
double maxCheck,
double threshold,
EventDetector.Action entry,
EventDetector.Action exit)
Build a new instance with defined actions at fov entry and exit.
|
CircularFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
double halfApertureIn,
double maxCheck,
double threshold,
EventDetector.Action entry,
EventDetector.Action exit,
boolean removeEntry,
boolean removeExit)
Build a new instance with defined actions at fov entry and exit.
|
DihedralFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
Vector3D axis1,
double halfAperture1In,
Vector3D axis2,
double halfAperture2In,
double maxCheck)
Build a new instance.
|
DihedralFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
Vector3D axis1,
double halfAperture1In,
Vector3D axis2,
double halfAperture2In,
double maxCheck,
double epsilon)
Build a new instance.
|
DihedralFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
Vector3D axis1,
double halfAperture1In,
Vector3D axis2,
double halfAperture2In,
double maxCheck,
EventDetector.Action entry,
EventDetector.Action exit)
Build a new instance.
|
DihedralFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
Vector3D axis1,
double halfAperture1In,
Vector3D axis2,
double halfAperture2In,
double maxCheck,
EventDetector.Action entry,
EventDetector.Action exit,
boolean removeEntry,
boolean removeExit)
Build a new instance.
|
DihedralFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
Vector3D axis1,
double halfAperture1In,
Vector3D axis2,
double halfAperture2In,
double maxCheck,
EventDetector.Action entry,
EventDetector.Action exit,
boolean removeEntry,
boolean removeExit,
double epsilon)
Build a new instance.
|
DihedralFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
Vector3D axis1,
double halfAperture1In,
Vector3D axis2,
double halfAperture2In,
double maxCheck,
EventDetector.Action entry,
EventDetector.Action exit,
double epsilon)
Build a new instance.
|
DistanceDetector(PVCoordinatesProvider bodyIn,
double distanceIn)
Constructor for a DistanceDetector instance.
|
DistanceDetector(PVCoordinatesProvider bodyIn,
double distanceIn,
double maxCheck,
double threshold)
Constructor for a DistanceDetector instance with additional maxCheck and threshold parameters
|
DistanceDetector(PVCoordinatesProvider bodyIn,
double distanceIn,
double maxCheck,
double threshold,
EventDetector.Action actionIncreasing,
EventDetector.Action actionDecreasing)
Constructor for a DistanceDetector instance with complimentary parameters.
|
DistanceDetector(PVCoordinatesProvider bodyIn,
double distanceIn,
double maxCheck,
double threshold,
EventDetector.Action actionIncreasing,
EventDetector.Action actionDecreasing,
boolean removeIncreasing,
boolean removeDecreasing)
Constructor for a DistanceDetector instance with complimentary parameters.
|
DistanceDetector(PVCoordinatesProvider bodyIn,
double distanceIn,
int slopeSelection,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Build a new altitude detector with slope selection.
|
DotProductPassageDetector(PVCoordinatesProvider target,
boolean normalizePos,
boolean normalizeTarget,
double dotProduct,
Frame projectionFrame,
int slopeSelectionIn)
Constructor for an DotProductPassageDetector instance.
|
DotProductPassageDetector(PVCoordinatesProvider target,
boolean normalizePos,
boolean normalizeTarget,
double dotProduct,
Frame projectionFrame,
int slopeSelectionIn,
double maxCheck,
double threshold)
Constructor for an DotProductPassageDetector instance with complementary parameters.
|
DotProductPassageDetector(PVCoordinatesProvider target,
boolean normalizePos,
boolean normalizeTarget,
double dotProduct,
Frame projectionFrame,
int slopeSelectionIn,
double maxCheck,
double threshold,
EventDetector.Action ascending,
EventDetector.Action descending)
Constructor for an DotProductPassageDetector instance with complementary parameters.
|
EclipseDetector(IDirection occulted,
PVCoordinatesProvider occulting,
double occultingRadius,
double maxCheck,
double threshold)
Build a new eclipse detector.
|
EclipseDetector(IDirection occulted,
PVCoordinatesProvider occulting,
double occultingRadius,
double maxCheck,
double threshold,
EventDetector.Action entry,
EventDetector.Action exit)
Build a new eclipse detector with defined actions when entering and exiting the eclipse.
|
EclipseDetector(IDirection occulted,
PVCoordinatesProvider occulting,
double occultingRadius,
double maxCheck,
double threshold,
EventDetector.Action entry,
EventDetector.Action exit,
boolean removeEntry,
boolean removeExit)
Build a new eclipse detector with defined actions when entering and exiting the eclipse.
|
EclipseDetector(PVCoordinatesProvider occulted,
double occultedRadiusIn,
BodyShape occultingBodyIn,
double lightingRatio,
double maxCheck,
double threshold)
Build a new eclipse detector based on a lighting ratio.
|
EclipseDetector(PVCoordinatesProvider occulted,
double occultedRadiusIn,
BodyShape occultingBodyIn,
double lightingRatio,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove,
int slopeSelection)
Build a new eclipse detector based on a lighting ratio and with slope selection.
|
EclipseDetector(PVCoordinatesProvider occulted,
double occultedRadiusIn,
BodyShape occultingBodyIn,
double lightingRatio,
double maxCheck,
double threshold,
EventDetector.Action entry,
EventDetector.Action exit)
Build a new eclipse detector based on a lighting ratio.
|
EclipseDetector(PVCoordinatesProvider occulted,
double occultedRadiusIn,
BodyShape occultingBodyIn,
double lightingRatio,
double maxCheck,
double threshold,
EventDetector.Action entry,
EventDetector.Action exit,
boolean removeEntry,
boolean removeExit)
Build a new eclipse detector based on a lighting ratio.
|
EclipseDetector(PVCoordinatesProvider occulted,
double occultedRadiusIn,
BodyShape occultingBodyIn,
double lightingRatio,
double maxCheck,
double threshold,
EventDetector.Action entry,
EventDetector.Action exit,
boolean removeEntry,
boolean removeExit,
int slopeSelection)
Build a new eclipse detector based on a lighting ratio and with slope selection.
|
EclipseDetector(PVCoordinatesProvider occulted,
double occultedRadiusIn,
BodyShape occultingBodyIn,
double lightingRatio,
double maxCheck,
double threshold,
int slopeSelection)
Build a new eclipse detector based on a lighting ratio and with slope selection.
|
EclipseDetector(PVCoordinatesProvider occulted,
double occultedRadiusIn,
PVCoordinatesProvider occulting,
double occultingRadius,
double lightingRatio,
double maxCheck,
double threshold)
Build a new eclipse detector based on a lighting ratio.
|
EclipseDetector(PVCoordinatesProvider occulted,
double occultedRadiusIn,
PVCoordinatesProvider occulting,
double occultingRadius,
double lightingRatio,
double maxCheck,
double threshold,
EventDetector.Action entry,
EventDetector.Action exit)
Build a new eclipse detector based on a lighting ratio.
|
EclipseDetector(PVCoordinatesProvider occulted,
double occultedRadiusIn,
PVCoordinatesProvider occulting,
double occultingRadius,
double lightingRatio,
double maxCheck,
double threshold,
EventDetector.Action entry,
EventDetector.Action exit,
boolean removeEntry,
boolean removeExit)
Build a new eclipse detector based on a lighting ratio.
|
EclipseDetector(PVCoordinatesProvider occulted,
double occultedRadiusIn,
PVCoordinatesProvider occulting,
double occultingRadius,
double lightingRatio,
int slopeSelection,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Constructor with slope selection.
|
ExtremaDistanceDetector(PVCoordinatesProvider dBody,
double maxCheck,
double threshold,
EventDetector.Action actionMin,
EventDetector.Action actionMax)
Constructor for both minimum and maximum distance .
|
ExtremaDistanceDetector(PVCoordinatesProvider dBody,
double maxCheck,
double threshold,
EventDetector.Action actionMin,
EventDetector.Action actionMax,
boolean removeMin,
boolean removeMax)
Constructor for both minimum and maximum distance .
|
ExtremaDistanceDetector(PVCoordinatesProvider dBody,
int extremumType)
Constructor for a ExtremaDistanceDetector instance.
|
ExtremaDistanceDetector(PVCoordinatesProvider dBody,
int extremumType,
double maxCheck,
double threshold)
Constructor for a ExtremaDistanceDetector instance with complimentary parameters.
|
ExtremaDistanceDetector(PVCoordinatesProvider dBody,
int extremumType,
double maxCheck,
double threshold,
EventDetector.Action action)
Constructor for a ExtremaDistanceDetector instance with specified action when extrema is
detected.
|
ExtremaDistanceDetector(PVCoordinatesProvider dBody,
int extremumType,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Constructor for a ExtremaDistanceDetector instance with specified action when extrema is
detected.
|
ExtremaDotProductDetector(PVCoordinatesProvider target,
boolean normalizePos,
boolean normalizeTarget,
Frame projectionFrame,
int extremumType)
Constructor for a ExtremaDotProductDetector instance.
|
ExtremaDotProductDetector(PVCoordinatesProvider target,
boolean normalizePos,
boolean normalizeTarget,
Frame projectionFrame,
int extremumType,
double maxCheck,
double threshold)
Constructor for a ExtremaDotProductDetector instance with complimentary parameters.
|
ExtremaDotProductDetector(PVCoordinatesProvider target,
boolean normalizePos,
boolean normalizeTarget,
Frame projectionFrame,
int extremumType,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Constructor for a ExtremaDotProductDetector instance with specified action when extrema is
detected.
|
ExtremaThreeBodiesAngleDetector(PVCoordinatesProvider bodyA,
PVCoordinatesProvider bodyB,
ExtremaThreeBodiesAngleDetector.BodyOrder bodyC,
double maxCheck,
double threshold,
EventDetector.Action actionMin,
EventDetector.Action actionMax)
Constructor for the min and max three bodies angle detector with specified action for both minimum and maximum.
|
ExtremaThreeBodiesAngleDetector(PVCoordinatesProvider bodyA,
PVCoordinatesProvider bodyB,
ExtremaThreeBodiesAngleDetector.BodyOrder bodyC,
double maxCheck,
double threshold,
EventDetector.Action actionMin,
EventDetector.Action actionMax,
boolean removeMin,
boolean removeMax)
Constructor for the min and max three bodies angle detector with specified action for both minimum and maximum.
|
ExtremaThreeBodiesAngleDetector(PVCoordinatesProvider bodyA,
PVCoordinatesProvider bodyB,
ExtremaThreeBodiesAngleDetector.BodyOrder bodyC,
int extremumType)
Simple constructor for the min and max three bodies angle detector.
|
ExtremaThreeBodiesAngleDetector(PVCoordinatesProvider bodyA,
PVCoordinatesProvider bodyB,
ExtremaThreeBodiesAngleDetector.BodyOrder bodyC,
int extremumType,
double maxCheck,
double threshold)
Constructor for the min and max three bodies angle detector with defined maximum check and convergence threshold.
|
ExtremaThreeBodiesAngleDetector(PVCoordinatesProvider bodyA,
PVCoordinatesProvider bodyB,
ExtremaThreeBodiesAngleDetector.BodyOrder bodyC,
int extremumType,
double maxCheck,
double threshold,
EventDetector.Action action)
Constructor for the min and max three bodies angle detector with specified action when extrema is detected.
|
ExtremaThreeBodiesAngleDetector(PVCoordinatesProvider bodyA,
PVCoordinatesProvider bodyB,
ExtremaThreeBodiesAngleDetector.BodyOrder bodyC,
int extremumType,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Constructor for the min and max three bodies angle detector with specified action when extrema is detected.
|
ExtremaThreeBodiesAngleDetector(PVCoordinatesProvider firstBody,
PVCoordinatesProvider secondBody,
PVCoordinatesProvider thirdBody,
double maxCheck,
double threshold,
EventDetector.Action actionMin,
EventDetector.Action actionMax)
Constructor for the min and max three bodies angle detector with specified action for both
minimum and maximum.
|
ExtremaThreeBodiesAngleDetector(PVCoordinatesProvider firstBody,
PVCoordinatesProvider secondBody,
PVCoordinatesProvider thirdBody,
double maxCheck,
double threshold,
EventDetector.Action actionMin,
EventDetector.Action actionMax,
boolean removeMin,
boolean removeMax)
Constructor for the min and max three bodies angle detector with specified action for both
minimum and maximum.
|
ExtremaThreeBodiesAngleDetector(PVCoordinatesProvider firstBody,
PVCoordinatesProvider secondBody,
PVCoordinatesProvider thirdBody,
int extremumType)
Constructor for the min and max three bodies angle detector.
|
ExtremaThreeBodiesAngleDetector(PVCoordinatesProvider firstBody,
PVCoordinatesProvider secondBody,
PVCoordinatesProvider thirdBody,
int extremumType,
double maxCheck,
double threshold)
Constructor for the min and max three bodies angle detector.
|
ExtremaThreeBodiesAngleDetector(PVCoordinatesProvider firstBody,
PVCoordinatesProvider secondBody,
PVCoordinatesProvider thirdBody,
int extremumType,
double maxCheck,
double threshold,
EventDetector.Action action)
Constructor for the min and max three bodies angle detector with specified action when
extrema is detected.
|
ExtremaThreeBodiesAngleDetector(PVCoordinatesProvider firstBody,
PVCoordinatesProvider secondBody,
PVCoordinatesProvider thirdBody,
int extremumType,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Constructor for the min and max three bodies angle detector with specified action when
extrema is detected.
|
ThreeBodiesAngleDetector(PVCoordinatesProvider firstBody,
PVCoordinatesProvider secondBody,
PVCoordinatesProvider thirdBody,
double angle)
Build a new three bodies angle detector.
|
ThreeBodiesAngleDetector(PVCoordinatesProvider firstBody,
PVCoordinatesProvider secondBody,
PVCoordinatesProvider thirdBody,
double angle,
double maxCheck,
double threshold)
Build a new three bodies angle detector with complimentary parameters.
|
ThreeBodiesAngleDetector(PVCoordinatesProvider firstBody,
PVCoordinatesProvider secondBody,
PVCoordinatesProvider thirdBody,
double angle,
double maxCheck,
double threshold,
EventDetector.Action action)
Build a new three bodies angle detector with complimentary parameters.
|
ThreeBodiesAngleDetector(PVCoordinatesProvider bodyA,
PVCoordinatesProvider bodyB,
ThreeBodiesAngleDetector.BodyOrder bodyC,
double angle)
Build a new three bodies angle detector with a position among the parameters.
|
ThreeBodiesAngleDetector(PVCoordinatesProvider bodyA,
PVCoordinatesProvider bodyB,
ThreeBodiesAngleDetector.BodyOrder bodyC,
double angle,
double maxCheck,
double threshold)
Build a new three bodies angle detector with complimentary parameters.
|
ThreeBodiesAngleDetector(PVCoordinatesProvider bodyA,
PVCoordinatesProvider bodyB,
ThreeBodiesAngleDetector.BodyOrder bodyC,
double angle,
double maxCheck,
double threshold,
EventDetector.Action action)
Build a new three bodies angle detector with complimentary parameters.
|
ThreeBodiesAngleDetector(PVCoordinatesProvider bodyA,
PVCoordinatesProvider bodyB,
ThreeBodiesAngleDetector.BodyOrder bodyC,
double angle,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Build a new three bodies angle detector with complimentary parameters.
|
| Modifier and Type | Class and Description |
|---|---|
class |
NumericalPropagator
This class propagates
SpacecraftState using numerical integration. |
| Modifier and Type | Class and Description |
|---|---|
class |
Ephemeris
This class is designed to accept and handle tabulated orbital entries.
|
class |
IntegratedEphemeris
This class stores sequentially generated orbital parameters for
later retrieval.
|
class |
PVEphemeris
This class is designed to accept and handle tabulated orbital entries described by
time-stamped PVCoordinates.Tabulated entries are classified and then extrapolated in a way to obtain continuous output, with accuracy and computation methods configured by the user. |
| Modifier and Type | Class and Description |
|---|---|
class |
MultiIntegratedEphemeris
This interface is copied from IntegratedEphemeris and adapted to multi propagation.
|
| Modifier and Type | Method and Description |
|---|---|
VacuumSignalPropagation |
VacuumSignalPropagationModel.computeSignalPropagation(PVCoordinatesProvider emitter,
PVCoordinatesProvider receiver,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType)
Computes the signal propagation object in the void at a particular date
|
static AbsoluteDate |
VacuumSignalPropagationModel.getSignalEmissionDate(PVCoordinatesProvider emitter,
PVCoordinatesProvider orbit,
AbsoluteDate date,
double epsilon,
AbstractDetector.PropagationDelayType propagationDelayType,
Frame inertialFrame)
Compute signal emission date which is the date at which the signal received by the spacecraft
(receiver) has been emitted by the emitter depending on
AbstractDetector.PropagationDelayType. |
static AbsoluteDate |
VacuumSignalPropagationModel.getSignalEmissionDate(PVCoordinatesProvider emitter,
PVCoordinatesProvider orbit,
AbsoluteDate date,
double epsilon,
AbstractDetector.PropagationDelayType propagationDelayType,
Frame inertialFrame,
int maxIterSignalPropagation)
Compute signal emission date which is the date at which the signal received by the spacecraft
(receiver) has been emitted by the emitter depending on
AbstractDetector.PropagationDelayType. |
static AbsoluteDate |
VacuumSignalPropagationModel.getSignalReceptionDate(PVCoordinatesProvider receiver,
PVCoordinatesProvider orbit,
AbsoluteDate date,
double epsilon,
AbstractDetector.PropagationDelayType propagationDelayType,
Frame inertialFrame)
Compute signal reception date which is the date at which the signal emitted by the spacecraft
(emitter) has been
received by the receiver depending on
AbstractDetector.PropagationDelayType. |
static AbsoluteDate |
VacuumSignalPropagationModel.getSignalReceptionDate(PVCoordinatesProvider receiver,
PVCoordinatesProvider orbit,
AbsoluteDate date,
double epsilon,
AbstractDetector.PropagationDelayType propagationDelayType,
Frame inertialFrame,
int maxIterSignalPropagation)
Compute signal reception date which is the date at which the signal emitted by the spacecraft
(emitter) has been received by the receiver depending on
AbstractDetector.PropagationDelayType. |
| Modifier and Type | Class and Description |
|---|---|
class |
MeeusMoonStela
This class implements the Moon ephemerides according to the algorithm of Meeus, it only provides
the position.
|
| Constructor and Description |
|---|
SRPPotential(PVCoordinatesProvider sun,
double m,
double s,
double c)
create a SRP Potential model using the sun and spacecraft characteristics.
|
SRPSquaring(RadiationSensitive radiativeSpacecraft,
int quadraturePoints,
PVCoordinatesProvider sunBody,
double earthRadius)
Create an instance with an assembly and a number of points.
|
SRPSquaring(RadiationSensitive radiativeSpacecraft,
int quadraturePoints,
PVCoordinatesProvider sunBody,
double earthRadius,
double dRef,
double pRef)
Create an instance with an assembly and a number of points.
|
SRPSquaring(RadiationSensitive radiativeSpacecraft,
int quadraturePoints,
PVCoordinatesProvider sunBody,
double earthRadius,
double dRef,
double pRef,
int orderFS)
Create an instance with an assembly and a number of points.
|
SRPSquaring(RadiationSensitive radiativeSpacecraft,
PVCoordinatesProvider sunBody,
double earthRadius)
Create an instance with an assembly and a number of points.
|
| Modifier and Type | Class and Description |
|---|---|
class |
StelaEquinoctialOrbit
This class handles Stela equinoctial orbital parameters, which can support both circular and
equatorial orbits.
|
| Modifier and Type | Class and Description |
|---|---|
class |
StelaAbstractPropagator
Common handling of
Propagator methods for analytical propagators. |
class |
StelaGTOPropagator
STELA propagator for Geostationnary Transfert Orbits (GTO).
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinatesProvider |
StelaAbstractPropagator.getPvProvider()
Get PV coordinates provider.
|
| Constructor and Description |
|---|
LocalTimeAngle(PVCoordinatesProvider sunEphemeris)
Constructor
|
| Constructor and Description |
|---|
SolarRadiationWrench(double distance,
double pressure,
double sunRadius,
PVCoordinatesProvider sunBody,
BodyShape shape,
RadiationWrenchSensitive spacecraftModel)
Complete constructor.
|
SolarRadiationWrench(Parameter distance,
Parameter pressure,
Parameter sunRadius,
PVCoordinatesProvider sunBody,
BodyShape shape,
RadiationWrenchSensitive spacecraftModel)
Complete constructor using
Parameter. |
SolarRadiationWrench(PVCoordinatesProvider sunBody,
BodyShape shape,
RadiationWrenchSensitive spacecraftModel)
Simple constructor with default reference values.
|
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