| Modifier and Type | Method and Description |
|---|---|
Frame |
MainPart.getFrame() |
Frame |
IPart.getFrame() |
| Modifier and Type | Method and Description |
|---|---|
Assembly |
Vehicle.createAssembly(Frame frame)
Create an
Assembly. |
Assembly |
Vehicle.createAssembly(Frame frame,
double cMass,
double cDrag,
double cSRP)
Create an
Assembly with multiplicative coefficients to take into account the change
in surface for drag or SRP during a propagation of the change of dry mass. |
| Modifier and Type | Method and Description |
|---|---|
Frame |
SensorModel.getNativeFrame(AbsoluteDate date)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
| Modifier and Type | Method and Description |
|---|---|
static Pair<BodyShape,Double> |
SensorModel.computeMinDistToMaskingBodies(AbsoluteDate spacecraftDate,
PVCoordinatesProvider orbit,
LinkTypeHandler.SignalPropagationRole spacecraftRole,
Frame spacecraftFrame,
Vector3D targetPosition,
List<BodyShape> maskingBodies,
AbstractSignalPropagationDetector.PropagationDelayType propagationDelayType,
double epsilonSignalPropagation,
int maxIterSignalPropagation)
Computes the minimal euclidian distance to the celestial body shapes.
|
Vector3D |
GlobalAeroModel.computeSC(SpacecraftState state,
Frame frame,
Vector3D relativeVelocity)
Compute the surface drag coefficient (drag coefficient x area)
|
Wrench |
AeroWrenchModel.dragWrench(SpacecraftState state,
double density,
Vector3D relativeVelocity,
Vector3D origin,
Frame frame)
Compute the torque due to radiation pressire.
|
protected static Vector3D |
AeroModel.forceOnSphere(SpacecraftState state,
IPart part,
double density,
Vector3D relativeVelocity,
Frame mainPartFrame)
Method to compute the force for the part model (cylinder, parallelepiped, sphere).
|
Matrix3D |
InertiaSimpleModel.getInertiaMatrix(Frame frame,
AbsoluteDate date)
Getter for the inertia matrix of the spacecraft,
expressed with respect to the MASS CENTER in a given frame.
|
Matrix3D |
InertiaComputedModel.getInertiaMatrix(Frame frame,
AbsoluteDate date)
Getter for the inertia matrix of the spacecraft,
expressed with respect to the MASS CENTER in a given frame.
|
Matrix3D |
IInertiaModel.getInertiaMatrix(Frame frame,
AbsoluteDate date)
Getter for the inertia matrix of the spacecraft,
expressed with respect to the MASS CENTER in a given frame.
|
Matrix3D |
InertiaSimpleModel.getInertiaMatrix(Frame frame,
AbsoluteDate date,
Vector3D inertiaReferencePoint)
Getter for the inertia matrix of the spacecraft,
once expressed with respect to a point
that can be different from the mass center.
|
Matrix3D |
InertiaComputedModel.getInertiaMatrix(Frame frame,
AbsoluteDate date,
Vector3D inertiaReferencePoint)
Getter for the inertia matrix of the spacecraft,
once expressed with respect to a point
that can be different from the mass center.
|
Matrix3D |
IInertiaModel.getInertiaMatrix(Frame frame,
AbsoluteDate date,
Vector3D inertiaReferencePoint)
Getter for the inertia matrix of the spacecraft,
once expressed with respect to a point
that can be different from the mass center.
|
Vector3D |
InertiaSimpleModel.getMassCenter(Frame frame,
AbsoluteDate date)
Getter for the mass center.
|
Vector3D |
InertiaComputedModel.getMassCenter(Frame frame,
AbsoluteDate date)
Getter for the mass center.
|
Vector3D |
IInertiaModel.getMassCenter(Frame frame,
AbsoluteDate date)
Getter for the mass center.
|
PVCoordinates |
SensorModel.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the sensor part in the selected frame. |
Vector3D[] |
SensorModel.getReferenceAxis(Frame frame,
AbsoluteDate date)
Computes the reference axis of the sensor in a given frame at a date
|
Vector3D |
SensorModel.getSightAxis(Frame frame,
AbsoluteDate date)
Computes the sight axis of the sensor in a given frame at a date
|
Wrench |
DirectRadiativeWrenchModel.radiationWrench(SpacecraftState state,
Vector3D flux,
Vector3D origin,
Frame frame)
Compute the torque due to radiation pressire.
|
| Constructor and Description |
|---|
InertiaSimpleModel(double mass,
Vector3D massCenter,
Matrix3D inertiaMatrix,
Frame frame,
String partName)
Constructor for a simple inertia model.
|
InertiaSimpleModel(double mass,
Vector3D massCenter,
Matrix3D inertiaMatrix,
Vector3D inertiaReferencePoint,
Frame frame,
String partName)
Constructor for a simple inertia model; the inertia matrix is expressed with respect to a point
that can be different from the mass center.
|
| Constructor and Description |
|---|
CnCookModel(ExtendedAtmosphere atmos,
Facet afacet,
Frame afacetFrame,
double eps,
double wallGasTemp)
Constructor with constant wall gas temperature.
|
CnCookModel(ExtendedAtmosphere atmos,
Facet afacet,
Frame afacetFrame,
double eps,
WallGasTemperatureProvider wallGasTemp)
Constructor.
|
CtCookModel(ExtendedAtmosphere atmos,
Facet afacet,
Frame afacetFrame,
double eps)
Constructor.
|
| Modifier and Type | Method and Description |
|---|---|
double |
RadiativeSphereProperty.getCrossSection(SpacecraftState state,
Vector3D flux,
Frame partFrame)
Compute the cross section of main shape using the relative velocity in the
part (having the aero property) frame as the direction to provider to the
CrossSectionProvider.getCrossSection(Vector3D). |
double |
RadiativeCrossSectionProperty.getCrossSection(SpacecraftState state,
Vector3D flux,
Frame partFrame)
Compute the cross section of main shape using the relative velocity in the
part (having the aero property) frame as the direction to provider to the
CrossSectionProvider.getCrossSection(Vector3D). |
double |
AeroSphereProperty.getCrossSection(SpacecraftState state,
Vector3D relativeVelocity,
Frame mainPartFrame,
Frame partFrame)
Compute the cross section of main shape using the relative velocity in the
part (having the aero property) frame as the direction to provider to the
CrossSectionProvider.getCrossSection(Vector3D). |
double |
AeroCrossSectionProperty.getCrossSection(SpacecraftState state,
Vector3D relativeVelocity,
Frame mainPartFrame,
Frame partFrame)
Compute the cross section of main shape using the relative velocity in the
part (having the aero property) frame as the direction to provider to the
CrossSectionProvider.getCrossSection(Vector3D). |
| 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. a dynamic frame whose orientation is defined by an attitude provider. |
class |
OrientationFrame
This class is a special implementation of the
Frame class; it represents a dynamic orientation frame,
i.e. a dynamic frame whose orientation is defined by IOrientationLaw. |
| Modifier and Type | Method and Description |
|---|---|
Frame |
AbstractGroundPointing.getBodyFrame()
Getter for the body frame.
|
Frame |
LofOffset.getPseudoInertialFrame()
Getter for the inertial frame with respect to which orbit should be computed.
|
Frame |
TabulatedAttitude.getReferenceFrame()
Getter for the reference frame.
|
Frame |
ConstantAttitudeLaw.getReferenceFrame()
Getter for the reference frame.
|
Frame |
Attitude.getReferenceFrame()
Get the reference frame.
|
| Modifier and Type | Method and Description |
|---|---|
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.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.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 |
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).
|
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.
|
Attitude |
TabulatedSlew.getAttitude(AbsoluteDate date,
Frame frame)
Compute the attitude on the specified date.
|
Attitude |
TabulatedAttitude.getAttitude(AbsoluteDate date,
Frame frame)
Compute the attitude on the specified date.
|
Attitude |
Slew.getAttitude(AbsoluteDate date,
Frame frame)
Compute the attitude.
|
Attitude |
ConstantSpinSlew.getAttitude(AbsoluteDate date,
Frame frame)
Compute the attitude.
|
Attitude |
YawSteering.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 |
TwoDirectionAttitudeLaw.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 |
TabulatedSlew.getAttitude(PVCoordinatesProvider pvProvider,
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 |
StrictAttitudeLegsSequence.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 |
RelativeTabulatedAttitudeLeg.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 |
LofOffsetPointing.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 |
IsisSunPointing.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 |
FixedRate.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 |
ConstantAttitudeLaw.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 |
CelestialBodyPointed.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 |
AttitudesSequence.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 |
AttitudeLegLaw.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 |
AeroAttitudeLaw.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 |
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.
|
Rotation |
IOrientationLaw.getOrientation(AbsoluteDate date,
Frame frame)
Gets the rotation defining the orientation with respect to a given frame at a given date.
|
Rotation |
DirectionTrackingOrientation.getOrientation(AbsoluteDate date,
Frame frame)
Gets the rotation defining the orientation with respect to a given frame at a given date.
|
Attitude |
AbstractAttitudeEphemerisGenerator.getPreviousAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Returns attitude from previous leg (compared to leg matching provided date) from the
sequence.
|
Vector3D |
TabulatedSlew.getSpinDerivatives(AbsoluteDate date,
Frame frame)
Get spin derivatives.
|
protected Vector3D |
TargetGroundPointing.getTargetPosition(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target ground point position in specified frame.
|
protected Vector3D |
NadirPointing.getTargetPosition(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target ground point position in specified frame.
|
protected Vector3D |
LofOffsetPointing.getTargetPosition(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target ground point position in specified frame.
|
protected Vector3D |
BodyCenterGroundPointing.getTargetPosition(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target ground point position in specified frame.
|
protected Vector3D |
AbstractGroundPointingWrapper.getTargetPosition(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target ground point position in specified frame.
|
protected abstract Vector3D |
AbstractGroundPointing.getTargetPosition(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target ground point position in specified frame.
|
TimeStampedPVCoordinates |
NadirPointing.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.
|
protected TimeStampedPVCoordinates |
AbstractGroundPointing.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.
|
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.
|
| Constructor and Description |
|---|
Attitude(AbsoluteDate date,
Frame referenceFrameIn,
AngularCoordinates orientationIn)
Creates a new instance.
|
Attitude(AbsoluteDate date,
Frame referenceFrameIn,
Rotation attitude,
Vector3D spin)
Creates a new instance.
|
Attitude(AbsoluteDate date,
Frame referenceFrameIn,
Rotation attitude,
Vector3D spin,
Vector3D acceleration)
Creates a new instance.
|
Attitude(double[] y,
AbsoluteDate date,
Frame referenceFrameIn)
Creates a new instance from an array containing a quaternion and a spin vector.
|
Attitude(Frame referenceFrameIn,
TimeStampedAngularCoordinates orientationIn)
Creates a new instance.
|
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.
|
ConstantAttitudeLaw(Frame referenceFrameIn,
Rotation rotationIn)
Creates new instance.
|
ConstantSpinSlew(Attitude initAtt,
Attitude finalAtt,
double spin,
String natureIn,
Frame pivotFrame)
Constructor for slew with an angular velocity constraint.
|
ConstantSpinSlew(Attitude initAtt,
Attitude finalAtt,
String natureIn,
Frame pivotFrame)
Constructor for slew with a duration constraint.
|
LofOffset(Frame inertialFrameIn,
LOFType typeIn)
Create a LOF-aligned attitude.
|
LofOffset(Frame pInertialFrame,
LOFType typeIn,
RotationOrder order,
double alpha1,
double alpha2,
double alpha3)
Creates new instance.
|
OrientationTransformProvider(IOrientationLaw law,
Frame frame)
Protected constructor.
|
OrientationTransformProvider(IOrientationLaw law,
Frame frame,
double spinDeltaT)
Protected constructor.
|
RelativeTabulatedAttitudeLaw(AbsoluteDate refDate,
List<Pair<Double,AngularCoordinates>> angularCoordinates,
Frame frame,
RelativeTabulatedAttitudeLaw.AroundAttitudeType lawBefore,
RelativeTabulatedAttitudeLaw.AroundAttitudeType lawAfter)
Create a RelativeTabulatedAttitudeLaw object with list of Angular Coordinates (during the interval of validity),
a law before the interval and a law after the interval.
|
RelativeTabulatedAttitudeLaw(Frame frame,
AbsoluteDate refDate,
List<Pair<Double,Rotation>> orientations,
RelativeTabulatedAttitudeLaw.AroundAttitudeType lawBefore,
RelativeTabulatedAttitudeLaw.AroundAttitudeType lawAfter)
Create a RelativeTabulatedAttitudeLaw object with list of rotations (during the interval of validity),
a law before the interval and a law after the interval.
|
RelativeTabulatedAttitudeLeg(AbsoluteDate referenceDate,
Frame frame,
List<Pair<Double,AngularCoordinates>> angularCoordinates)
Build a RelativeTabulatedAttitudeLeg with a reference date, a list of angular coordinates
associated with a double representing the time elapsed since the reference date.
|
RelativeTabulatedAttitudeLeg(AbsoluteDate referenceDate,
Frame frame,
List<Pair<Double,AngularCoordinates>> angularCoordinates,
String natureIn)
Build a RelativeTabulatedAttitudeLeg with a reference date, a list of angular coordinates
associated with a double representing the time elapsed since the reference date.
|
RelativeTabulatedAttitudeLeg(AbsoluteDate referenceDate,
List<Pair<Double,AngularCoordinates>> angularCoordinates,
int nbInterpolationPoints,
Frame frame)
Build a RelativeTabulatedAttitudeLeg with a reference date, a list of angular coordinates
associated with a double representing the time elapsed since the reference date
and a number of points used for interpolation.
|
RelativeTabulatedAttitudeLeg(AbsoluteDate referenceDate,
List<Pair<Double,AngularCoordinates>> angularCoordinates,
int nbInterpolationPoints,
Frame frame,
String natureIn)
Build a RelativeTabulatedAttitudeLeg with a reference date, a list of angular coordinates
associated with a double representing the time elapsed since the reference date and a number
of points used for interpolation.
|
RelativeTabulatedAttitudeLeg(AbsoluteDate referenceDate,
List<Pair<Double,Rotation>> orientations,
Frame frame)
Build a RelativeTabulatedAttitudeLeg with a reference date, a list of Rotations
associated with a double representing the time elapsed since the reference date.
|
RelativeTabulatedAttitudeLeg(AbsoluteDate referenceDate,
List<Pair<Double,Rotation>> orientations,
Frame frame,
int nbInterpolationPoints)
Build a RelativeTabulatedAttitudeLeg with a reference date, a list of Rotations
associated with a double representing the time elapsed since the reference date
and a number of points used for interpolation.
|
RelativeTabulatedAttitudeLeg(AbsoluteDate referenceDate,
List<Pair<Double,Rotation>> orientations,
Frame frame,
int nbInterpolationPoints,
String natureIn)
Build a RelativeTabulatedAttitudeLeg with a reference date, a list of Rotations associated
with a double representing the time elapsed since the reference date and a number of points
used for interpolation.
|
RelativeTabulatedAttitudeLeg(AbsoluteDate referenceDate,
List<Pair<Double,Rotation>> orientations,
Frame frame,
String natureIn)
Build a RelativeTabulatedAttitudeLeg with a reference date, a list of Rotations associated
with a double representing the time elapsed since the reference date.
|
TargetPointing(Frame bodyFrameIn,
Vector3D targetIn)
Creates a new instance from body frame and target expressed in cartesian coordinates.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
ConstantVectorDirection.getFrame() |
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
GlintApproximatePointingDirection.getGlintVectorPosition(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Get the position vector of the glint point
|
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 |
ToCelestialPointDirection.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 |
MomentumDirection.getLine(PVCoordinatesProvider origin,
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 |
GlintApproximatePointingDirection.getLine(PVCoordinatesProvider origin,
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 |
EarthToCelestialPointDirection.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 pvCoord,
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 |
ConstantVectorDirection.getLine(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the line containing the given origin point and directed by the direction vector
|
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 |
ToCelestialPointDirection.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.
|
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 |
EarthToCelestialPointDirection.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 |
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.
|
PVCoordinates |
ToCelestialPointDirection.getTargetPVCoordinates(AbsoluteDate date,
Frame frame)
Provides the target point at a given date in a given frame, represented by the
associated PVCoordinates object.
|
PVCoordinates |
ITargetDirection.getTargetPVCoordinates(AbsoluteDate date,
Frame frame)
Provides the target point at a given date in a given frame, represented by the
associated PVCoordinates object.
|
PVCoordinates |
GenericTargetDirection.getTargetPVCoordinates(AbsoluteDate date,
Frame frame)
Provides the target point at a given date in a given frame, represented by the
associated PVCoordinates object.
|
PVCoordinates |
EarthToCelestialPointDirection.getTargetPVCoordinates(AbsoluteDate date,
Frame frame)
Provides the target point at a given date in a given frame, represented by the
associated PVCoordinates object.
|
PVCoordinates |
EarthCenterDirection.getTargetPVCoordinates(AbsoluteDate date,
Frame frame)
Provides the target point at a given date in a given frame, represented by the
associated PVCoordinates object.
|
Vector3D |
VelocityDirection.getVector(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
ToCelestialPointDirection.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 |
MomentumDirection.getVector(PVCoordinatesProvider origin,
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 |
GlintApproximatePointingDirection.getVector(PVCoordinatesProvider origin,
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 |
EarthToCelestialPointDirection.getVector(PVCoordinatesProvider pvCoord,
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 |
CrossProductDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the cross product of direction1 vector and dirction2 vector.
|
Vector3D |
ConstantVectorDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
CelestialBodyPolesAxisDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
default 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.
|
Vector3D |
EarthToCelestialPointDirection.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.
|
| Constructor and Description |
|---|
ConstantVectorDirection(Vector3D inVector,
Frame inFrame)
Build a direction from a frame and a vector constant in this frame
|
MomentumDirection(Frame bodyCenteredFrame)
Build a direction from the celestial body around witch the orbit is defined.
|
MomentumDirection(Frame bodyCenteredFrame,
PVCoordinatesProvider pvProvider)
Build a direction from a
PVCoordinatesProvider. |
VelocityDirection(Frame referenceFrame)
Build a Direction defined for any PVCoordinatesProvider origin by its velocity vector with respect to a reference
frame.
|
| 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 | Field and Description |
|---|---|
protected Frame |
AbstractAngularVelocitiesAttitudeProfile.refFrame
Frame of initial rotation and Fourier series.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
QuaternionPolynomialProfile.getReferenceFrame()
Returns the reference frame of the polynomial functions.
|
Frame |
QuaternionDatePolynomialProfile.getReferenceFrame()
Returns the reference frame of the polynomial functions.
|
| Modifier and Type | Method and Description |
|---|---|
Attitude |
AngularVelocitiesPolynomialSlew.getAttitude(AbsoluteDate date,
Frame frame)
Compute the attitude.
|
Attitude |
QuaternionPolynomialProfile.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
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.
|
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.
|
Attitude |
AngularVelocitiesPolynomialProfile.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 | Field and Description |
|---|---|
protected Frame |
MeeusSun.MODEL.inertialSunFrame
Sun inertially oriented frame.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
EarthEphemeris.getNativeFrame(AbsoluteDate date)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
Frame |
Earth.getNativeFrame(AbsoluteDate date)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
Frame |
BSPCelestialBodyLoader.SSBEphemeris.getNativeFrame(AbsoluteDate date)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
default Frame |
BodyPoint.getNativeFrame(AbsoluteDate date)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
Frame |
AbstractCelestialPoint.getNativeFrame(AbsoluteDate date)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
Frame |
AbstractBodyShape.getNativeFrame(AbsoluteDate date)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
| Modifier and Type | Method and Description |
|---|---|
EllipsoidPoint |
EllipsoidBodyShape.buildPoint(Vector3D position,
Frame frame,
AbsoluteDate date,
String name)
Build a
BodyPoint from position in provided frame at provided date. |
BodyPoint |
BodyShape.buildPoint(Vector3D position,
Frame frame,
AbsoluteDate date,
String name)
Build a
BodyPoint from position in provided frame at provided date. |
EllipsoidPoint |
AbstractEllipsoidBodyShape.buildPoint(Vector3D position,
Frame frame,
AbsoluteDate date,
String name)
Build a
BodyPoint from position in provided frame at provided date. |
EllipsoidPoint[] |
EllipsoidBodyShape.closestPointTo(Line line,
Frame frame,
AbsoluteDate date)
This method computes the two points, on the line and on the body, that are the closest to each other.
|
BodyPoint[] |
BodyShape.closestPointTo(Line line,
Frame frame,
AbsoluteDate date)
This method computes the two points, on the line and on the body, that are the closest to each other.
|
EllipsoidPoint[] |
AbstractEllipsoidBodyShape.closestPointTo(Line line,
Frame frame,
AbsoluteDate date)
This method computes the two points, on the line and on the body, that are the closest to each other.
|
EllipsoidPoint |
EllipsoidBodyShape.closestPointTo(Vector3D point,
Frame frame,
AbsoluteDate date)
Computes the point on body surface that is the closest to provided point.
|
BodyPoint |
BodyShape.closestPointTo(Vector3D point,
Frame frame,
AbsoluteDate date)
Computes the point on body surface that is the closest to provided point.
|
EllipsoidPoint |
AbstractEllipsoidBodyShape.closestPointTo(Vector3D point,
Frame frame,
AbsoluteDate date)
Computes the point on body surface that is the closest to provided point.
|
double[] |
LLHCoordinatesSystem.computeLLHRates(BodyShape bodyShape,
PVCoordinates pv,
Frame frame,
AbsoluteDate date)
Computes the rates in LLH coordinates (longitude, latitude, height) from the provided
PVCoordinates and date using finite differences.
|
double |
BodyShape.distanceTo(Line line,
Frame frame,
AbsoluteDate date)
Computes the distance to a line.
|
double |
AbstractEllipsoidBodyShape.distanceTo(Line line,
Frame frame,
AbsoluteDate date)
Computes the distance to a line.
|
EllipsoidPoint |
EllipsoidBodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Getter for the intersection point of a line with the surface of the body.
|
BodyPoint |
BodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Getter for the intersection point of a line with the surface of the body.
|
EllipsoidPoint |
AbstractEllipsoidBodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Getter for the intersection point of a line with the surface of the body.
|
EllipsoidPoint |
ThreeAxisEllipsoid.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date,
double altitude)
Getter for the intersection point of a line with the surface of the body for a given altitude.
|
EllipsoidPoint |
OneAxisEllipsoid.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date,
double altitude)
Getter for the intersection point of a line with the surface of the body for a given altitude.
|
EllipsoidPoint |
EllipsoidBodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date,
double altitude)
Getter for the intersection point of a line with the surface of the body for a given altitude.
|
BodyPoint |
BodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date,
double altitude)
Getter for the intersection point of a line with the surface of the body for a given altitude.
|
EllipsoidPoint |
EllipsoidBodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date,
String name)
Getwter for the intersection point of a line with the surface of the body.
|
BodyPoint |
BodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date,
String name)
Getwter for the intersection point of a line with the surface of the body.
|
EllipsoidPoint |
AbstractEllipsoidBodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date,
String name)
Getwter for the intersection point of a line with the surface of the body.
|
EllipsoidPoint[] |
EllipsoidBodyShape.getIntersectionPoints(Line line,
Frame frame,
AbsoluteDate date)
Compute the intersection points with a line.
|
BodyPoint[] |
BodyShape.getIntersectionPoints(Line line,
Frame frame,
AbsoluteDate date)
Compute the intersection points with a line.
|
EllipsoidPoint[] |
AbstractEllipsoidBodyShape.getIntersectionPoints(Line line,
Frame frame,
AbsoluteDate date)
Compute the intersection points with a line.
|
Line |
BasicBoardSun.getLine(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Get the line from the position in pvCoord to the Sun.
|
default Vector3D |
BodyPoint.getNormal(AbsoluteDate date,
Frame frame)
Returns the normal direction expressed in the provided frame.
|
TimeStampedAngularCoordinates |
CelestialBodyTabulatedOrientation.getOrientation(AbsoluteDate date,
Frame frame)
Getter for the celestial body orientation at the specified date.
|
PVCoordinates |
EarthEphemeris.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
PVCoordinates |
Earth.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
PVCoordinates |
BSPCelestialBodyLoader.SSBEphemeris.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
default PVCoordinates |
BodyPoint.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
PVCoordinates |
AbstractCelestialPoint.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
PVCoordinates |
AbstractBodyShape.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
Vector3D |
BasicBoardSun.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Get the direction of the sun.
|
EllipsoidPoint |
OneAxisEllipsoid.transformAndComputeJacobian(Vector3D point,
Frame frame,
AbsoluteDate date,
double[][] jacobian)
Deprecated.
since 4.13, use
LLHCoordinatesSystem.jacobianFromCartesian(BodyPoint) with
ELLIPSODETIC coordinates instead. |
| Constructor and Description |
|---|
AbstractCelestialBody(String name,
double gm,
CelestialBodyOrientation celestialBodyOrientation,
Frame parentFrame)
Constructor without ephemeris.
|
AbstractCelestialBody(String name,
double gm,
CelestialBodyOrientation celestialBodyOrientation,
Frame parentFrame,
CelestialBodyEphemeris ephemeris)
Constructor.
|
AbstractCelestialBody(String name,
GravityModel gravityModel,
CelestialBodyOrientation celestialBodyOrientation,
Frame parentFrame,
BSPEphemerisLoader.SpiceJ2000ConventionEnum convention,
CelestialBodyEphemeris ephemeris)
Constructor.
|
AbstractCelestialPoint(String name,
double gm,
CelestialBodyEphemeris ephemeris,
Frame parentFrame,
BSPEphemerisLoader.SpiceJ2000ConventionEnum convention)
Constructor with parent frame.
|
AbstractCelestialPoint(String name,
double gm,
Frame parentFrame,
CelestialBodyEphemeris ephemeris)
Constructor.
|
AbstractIAUCelestialBody(String name,
double gm,
CelestialBodyIAUOrientation celestialBodyIAUOrientation,
Frame parentFrame)
Constructor without ephemeris.
|
AbstractIAUCelestialBody(String name,
double gm,
CelestialBodyIAUOrientation celestialBodyIAUOrientation,
Frame parentFrame,
CelestialBodyEphemeris ephemeris)
Constructor.
|
AbstractIAUCelestialBody(String name,
GravityModel gravityModel,
CelestialBodyIAUOrientation celestialBodyIAUOrientation,
Frame parentFrame,
BSPEphemerisLoader.SpiceJ2000ConventionEnum convention,
CelestialBodyEphemeris ephemeris)
Constructor.
|
BasicCelestialPoint(String name,
double gm,
CelestialBodyEphemeris ephemeris,
Frame parentFrame,
BSPEphemerisLoader.SpiceJ2000ConventionEnum convention)
Constructor.
|
BasicCelestialPoint(String name,
PVCoordinatesProvider aPVCoordinateProvider,
double gm,
Frame parentFrame)
Constructor.
|
BasicCelestialPoint(String name,
PVCoordinatesProvider aPVCoordinateProvider,
double gm,
Frame parentFrame,
BSPEphemerisLoader.SpiceJ2000ConventionEnum spiceJ2000Convention)
Constructor.
|
EllipsoidPoint(EllipsoidBodyShape bodyShape,
Vector3D position,
Frame frame,
AbsoluteDate date,
String name)
Constructor from a position expressed in any given frame.
|
UserCelestialBody(String name,
PVCoordinatesProvider aPVCoordinateProvider,
double gm,
CelestialBodyOrientation celestialBodyOrientation,
Frame parentFrame,
BodyShape shape)
Constructor.
|
UserCelestialBody(String name,
PVCoordinatesProvider aPVCoordinateProvider,
double gm,
CelestialBodyOrientation celestialBodyOrientation,
Frame parentFrame,
BodyShape shape,
BSPEphemerisLoader.SpiceJ2000ConventionEnum spiceJ2000Convention)
Constructor.
|
UserCelestialBody(String name,
PVCoordinatesProvider aPVCoordinateProvider,
GravityModel gravityModel,
CelestialBodyOrientation celestialBodyOrientation,
Frame parentFrame,
BodyShape shape)
Constructor.
|
UserCelestialBody(String name,
PVCoordinatesProvider aPVCoordinateProvider,
GravityModel gravityModel,
CelestialBodyOrientation orientation,
Frame parentFrame,
BodyShape shape,
BSPEphemerisLoader.SpiceJ2000ConventionEnum spiceJ2000Convention)
Constructor.
|
UserCelestialBodyLoader(PVCoordinatesProvider pvCoordinatesProvider,
double gm,
CelestialBodyOrientation celestialBodyOrientation,
Frame parentFrame,
BodyShape shape)
Constructor.
|
UserCelestialBodyLoader(PVCoordinatesProvider pvCoordinatesProvider,
double gm,
CelestialBodyOrientation celestialBodyOrientation,
Frame parentFrame,
BodyShape shape,
BSPEphemerisLoader.SpiceJ2000ConventionEnum spiceJ2000Convention)
Complete constructor.
|
UserIAUCelestialBody(String name,
PVCoordinatesProvider aPVCoordinateProvider,
double gm,
CelestialBodyIAUOrientation celestialBodyIAUOrientation,
Frame parentFrame,
BodyShape shape)
Constructor.
|
UserIAUCelestialBody(String name,
PVCoordinatesProvider aPVCoordinateProvider,
double gm,
CelestialBodyIAUOrientation celestialBodyIAUOrientation,
Frame parentFrame,
BodyShape shape,
BSPEphemerisLoader.SpiceJ2000ConventionEnum spiceJ2000Convention)
Constructor.
|
UserIAUCelestialBody(String name,
PVCoordinatesProvider aPVCoordinateProvider,
GravityModel gravityModel,
CelestialBodyIAUOrientation celestialBodyIAUOrientation,
Frame parentFrame,
BodyShape shape)
Constructor.
|
UserIAUCelestialBody(String name,
PVCoordinatesProvider aPVCoordinateProvider,
GravityModel gravityModel,
CelestialBodyIAUOrientation iauOrientation,
Frame parentFrame,
BodyShape shape,
BSPEphemerisLoader.SpiceJ2000ConventionEnum spiceJ2000Convention)
Constructor.
|
| Modifier and Type | Method and Description |
|---|---|
void |
BSPEphemerisLoader.linkFramesTrees(Frame patriusFrame,
String bspBodyName)
Link a BSP IAU frame (given its name) to a PATRIUS frame.
|
| Modifier and Type | Method and Description |
|---|---|
FacetPoint |
FacetBodyShape.buildPoint(Vector3D position,
Frame frame,
AbsoluteDate date,
String nameIn)
Build a
BodyPoint from position in provided frame at provided date. |
FacetPoint[] |
FacetBodyShape.closestPointTo(Line line,
Frame frame,
AbsoluteDate date)
This method computes the two points, on the line and on the body, that are the closest to each other.
|
FacetPoint |
FacetBodyShape.closestPointTo(Vector3D point,
Frame frame,
AbsoluteDate date)
Computes the point on body surface that is the closest to provided point.
|
double |
FacetBodyShape.distanceTo(Line line,
Frame frame,
AbsoluteDate date)
Computes the distance to a line.
|
Intersection |
FacetBodyShape.getIntersection(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Getter for the intersection point of a line with the surface of the body.
|
FacetPoint |
FacetBodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Getter for the intersection point of a line with the surface of the body.
|
FacetPoint |
FacetBodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date,
double altitude)
Getter for the intersection point of a line with the surface of the body for a given altitude.
|
FacetPoint |
FacetBodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date,
String nameIn)
Getwter for the intersection point of a line with the surface of the body.
|
FacetPoint[] |
FacetBodyShape.getIntersectionPoints(Line line,
Frame frame,
AbsoluteDate date)
Compute the intersection points with a line.
|
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 |
|---|
FacetPoint(FacetBodyShape bodyShape,
Vector3D position,
Frame frame,
AbsoluteDate date,
String name)
Constructor from a position expressed in any given frame.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
AbstractOrbitalCovariance.getFrame()
Gets the frame of the covariance.
|
Frame |
BasicOrbitalCovarianceProvider.getNativeFrame(AbsoluteDate date)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
| Modifier and Type | Method and Description |
|---|---|
default PVCoordinates |
OrbitalCovarianceProvider.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
T |
AbstractOrbitalCovariance.transformTo(Frame destFrame)
Transforms this orbital covariance to the specified frame.
|
T |
AbstractOrbitalCovariance.transformTo(Frame destFrame,
OrbitType destOrbitType)
Transforms this orbital covariance to the specified frame, orbit type.
|
OrbitalCovariance |
OrbitalCovariance.transformTo(Frame destFrame,
OrbitType destOrbitType,
PositionAngle destPositionAngle)
Transforms this orbital covariance to the specified frame, orbit type and position angle
type.
|
MultiOrbitalCovariance |
MultiOrbitalCovariance.transformTo(Frame destFrame,
OrbitType destOrbitType,
PositionAngle destPositionAngle)
Transforms this orbital covariance to the specified frame, orbit type and position angle
type.
|
abstract T |
AbstractOrbitalCovariance.transformTo(Frame destFrame,
OrbitType destOrbitType,
PositionAngle destPositionAngle)
Transforms this orbital covariance to the specified frame, orbit type and position angle
type.
|
| Constructor and Description |
|---|
AbstractOrbitalCovariance(Covariance covarianceIn,
Frame frameIn,
OrbitType orbitTypeIn,
PositionAngle positionAngleIn)
Creates a new instance from the supplied covariance, frame, orbit type and position angle
type.
|
AbstractOrbitalCovariance(SymmetricPositiveMatrix covarianceIn,
Frame frameIn,
OrbitType orbitTypeIn,
PositionAngle positionAngleIn)
Creates a new instance from the supplied covariance matrix, frame, orbit type and position
angle type.
|
MultiOrbitalCovariance(Covariance covariance,
Collection<Orbit> orbits,
int[] nbAdditionalParametersIn,
Frame frame,
OrbitType orbitType,
PositionAngle positionAngle)
Creates a new instance that associates a covariance matrix with multiple orbits, the
covariance being defined in the specified frame, orbit type and position angle type.
|
MultiOrbitalCovariance(SymmetricPositiveMatrix covarianceMatrix,
Collection<Orbit> orbits,
int[] nbAdditionalParametersIn,
Frame frame,
OrbitType orbitType,
PositionAngle positionAngle)
Creates a new instance that associates a covariance matrix with multiple orbits, the
covariance being defined in the specified frame, orbit type and position angle type.
|
OrbitalCovariance(Covariance covariance,
Orbit orbit,
Frame frame,
OrbitType orbitType,
PositionAngle positionAngle)
Creates a new instance that associates a covariance matrix with a given orbit, the covariance
being defined in the specified frame, orbit type and position angle type.
|
OrbitalCovariance(SymmetricPositiveMatrix covarianceMatrix,
Orbit orbit,
Frame frame,
OrbitType orbitType,
PositionAngle positionAngle)
Creates a new instance that associates a covariance matrix with a given orbit, the covariance
being defined in the specified frame, orbit type and position angle type.
|
| Modifier and Type | Field and Description |
|---|---|
protected Frame |
PlaneCrossingDetector.referenceFrame
Frame for plane definition.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
ExtremaThreeBodiesAngleDetector.findFirstCommonPseudoInertial(SpacecraftState s1,
SpacecraftState s2,
SpacecraftState s3)
Returns the first common pseudo inertial ancestor between the frames of 3 SpacecraftStates
|
Frame |
AOLDetector.getAOLFrame()
Get the reference frame.
|
Frame |
SurfaceDistanceDetector.getBodyFixedFrame()
Getter for the body fixed frame.
|
Frame |
LongitudeDetector.getBodyFrame()
Returns central body frame.
|
Frame |
ExtremaLongitudeDetector.getBodyFrame()
Returns the body frame.
|
Frame |
ExtremaLatitudeDetector.getBodyFrame()
Returns the body frame.
|
Frame |
PlaneCrossingDetector.getFrame()
Getter for the frame for plane definition.
|
Frame |
EarthZoneDetector.getFrame()
Getter for the frame.
|
Frame |
AbstractSignalPropagationDetector.getInertialFrame()
Getter for the inertial frame used for signal propagation computation.
|
| Modifier and Type | Method and Description |
|---|---|
void |
AngularMomentumExcessDetector.setAttitudeRepresentedFrame(Frame frame)
Define the frame represented by the attitude law
|
void |
FlightDomainExcessDetector.setAttitudeRepresentedFrame(Frame desiredRepFrame,
Frame satAttFrame)
Define the frame represented by the attitude law and the desired flight domain represented frame
|
void |
AngularMomentumExcessDetector.setInertia(RealMatrix inertia,
Frame frame)
Define the inertia matrix (from CoM and in vehicle axis)
|
void |
VisibilityFromStationDetector.setPropagationDelayType(AbstractSignalPropagationDetector.PropagationDelayType propagationDelayType,
Frame frame)
Setter for the propagation delay computation type.
|
void |
TargetInFieldOfViewDetector.setPropagationDelayType(AbstractSignalPropagationDetector.PropagationDelayType propagationDelayType,
Frame frame) |
void |
StationToSatMutualVisibilityDetector.setPropagationDelayType(AbstractSignalPropagationDetector.PropagationDelayType propagationDelayType,
Frame frame)
Setter for the propagation delay computation type.
|
void |
SolarTimeAngleDetector.setPropagationDelayType(AbstractSignalPropagationDetector.PropagationDelayType propagationDelayType,
Frame frameIn) |
void |
SensorVisibilityDetector.setPropagationDelayType(AbstractSignalPropagationDetector.PropagationDelayType propagationDelayType,
Frame frame)
Setter for the propagation delay computation type.
|
void |
BetaAngleDetector.setPropagationDelayType(AbstractSignalPropagationDetector.PropagationDelayType propagationDelayType,
Frame frame) |
void |
ApparentElevationDetector.setPropagationDelayType(AbstractSignalPropagationDetector.PropagationDelayType propagationDelayType,
Frame frame) |
void |
AbstractSignalPropagationDetector.setPropagationDelayType(AbstractSignalPropagationDetector.PropagationDelayType propagationDelayTypeIn,
Frame frameIn)
Setter for the propagation delay computation type.
|
void |
AbstractEclipseDetector.setPropagationDelayType(AbstractSignalPropagationDetector.PropagationDelayType propagationDelayType,
Frame frame)
Setter for the propagation delay computation type.
|
| Constructor and Description |
|---|
AngularMomentumExcessDetector(double momentum,
Frame inertial,
int slopeSelectionIn)
Constructor for an AngularMomentumExcessDetector instance.
|
AngularMomentumExcessDetector(double momentum,
Frame inertial,
int slopeSelectionIn,
double maxCheck,
double threshold)
Constructor for an AngularMomentumExcessDetector instance with complementary parameters.
|
AngularMomentumExcessDetector(double momentum,
Frame inertial,
int slopeSelectionIn,
double maxCheck,
double threshold,
EventDetector.Action ascending,
EventDetector.Action descending)
Constructor for an AngularMomentumExcessDetector instance with complementary parameters.
|
AOLDetector(double angle,
PositionAngle type,
Frame equator)
Constructor for an AOLDetector instance.
|
AOLDetector(double angle,
PositionAngle type,
Frame equator,
double maxCheck,
double threshold)
Constructor for an AOLDetector instance with complementary parameters.
|
AOLDetector(double angle,
PositionAngle type,
Frame equator,
double maxCheck,
double threshold,
EventDetector.Action action)
Constructor for an AOLDetector instance with complementary parameters.
|
AOLDetector(double angle,
PositionAngle type,
Frame equator,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Constructor for an AOLDetector instance with complementary parameters.
|
CenteredAolPassageDetector(double aol,
PositionAngle positionAngle,
MeanOsculatingElementsProvider provider,
Frame frame)
Constructor
|
CenteredAolPassageDetector(double aol,
PositionAngle positionAngle,
MeanOsculatingElementsProvider provider,
Frame frame,
double maxCheck,
double threshold)
Constructor with complementary parameters
|
CenteredAolPassageDetector(double aol,
PositionAngle positionAngle,
MeanOsculatingElementsProvider provider,
Frame frame,
double maxCheck,
double threshold,
EventDetector.Action action)
Constructor with complementary parameters
|
DotProductDetector(IDirection target,
boolean normalizePos,
boolean normalizeTarget,
double dotProduct,
Frame projectionFrame,
int slopeSelectionIn)
Constructor for an DotProductPassageDetector instance.
|
DotProductDetector(IDirection target,
boolean normalizePos,
boolean normalizeTarget,
double dotProduct,
Frame projectionFrame,
int slopeSelectionIn,
double maxCheck,
double threshold)
Constructor for an DotProductPassageDetector instance with complementary parameters.
|
DotProductDetector(IDirection 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.
|
DotProductDetector(IDirection referenceDirection,
IDirection targetDirection,
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.
|
DotProductDetector(PVCoordinatesProvider target,
boolean normalizePos,
boolean normalizeTarget,
double dotProduct,
Frame projectionFrame,
int slopeSelectionIn)
Constructor for an DotProductPassageDetector instance.
|
DotProductDetector(PVCoordinatesProvider target,
boolean normalizePos,
boolean normalizeTarget,
double dotProduct,
Frame projectionFrame,
int slopeSelectionIn,
double maxCheck,
double threshold)
Constructor for an DotProductPassageDetector instance with complementary parameters.
|
DotProductDetector(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.
|
EarthZoneDetector(List<Vector3D[]> directionsList,
Frame bodyFrame)
Constructor for the earth zones entering detector with default maxCheck and convergence threshold.
|
EarthZoneDetector(List<Vector3D[]> directionsList,
Frame bodyFrame,
double maxCheck,
double threshold)
Constructor for the earth zones entering detector.
|
EarthZoneDetector(List<Vector3D[]> directionsList,
Frame bodyFrame,
double maxCheck,
double threshold,
EventDetector.Action entry,
EventDetector.Action exit)
Constructor for the earth zones entering detector.
|
EarthZoneDetector(List<Vector3D[]> directionsList,
Frame bodyFrame,
double maxCheck,
double threshold,
EventDetector.Action entry,
EventDetector.Action exit,
boolean removeEntry,
boolean removeExit)
Constructor.
|
ExtremaLatitudeDetector(int extremumType,
Frame bodyFrame)
Constructor for a ExtremaLatitudeDetector instance.
|
ExtremaLatitudeDetector(int extremumType,
Frame bodyFrame,
double maxCheck,
double threshold)
Constructor for a ExtremaLatitudeDetector instance.
|
ExtremaLatitudeDetector(int extremumType,
Frame bodyFrame,
double maxCheck,
double threshold,
EventDetector.Action action)
Constructor for a ExtremaLatitudeDetector instance.
|
ExtremaLatitudeDetector(int extremumType,
Frame bodyFrame,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Constructor for a ExtremaLatitudeDetector instance.
|
ExtremaLongitudeDetector(int extremumType,
Frame bodyFrame)
Constructor for a ExtremaLongitudeDetector instance.
|
ExtremaLongitudeDetector(int extremumType,
Frame bodyFrame,
double maxCheck,
double threshold)
Constructor for a ExtremaLongitudeDetector instance.
|
ExtremaLongitudeDetector(int extremumType,
Frame bodyFrame,
double maxCheck,
double threshold,
EventDetector.Action action)
Constructor for a ExtremaLongitudeDetector instance.
|
ExtremaLongitudeDetector(int extremumType,
Frame bodyFrame,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Constructor for a ExtremaLongitudeDetector instance.
|
FlightDomainExcessDetector(RotationOrder order,
double[][] angMinMax,
Frame refFrame)
Constructor for an FlightDomainExcessDetector instance.
|
FlightDomainExcessDetector(RotationOrder order,
double[][] angMinMax,
Frame refFrame,
double maxCheck,
double threshold)
Constructor for an FlightDomainExcessDetector instance with complementary parameters.
|
FlightDomainExcessDetector(RotationOrder order,
double[][] angMinMax,
Frame refFrame,
double maxCheck,
double threshold,
EventDetector.Action ascending,
EventDetector.Action descending)
Constructor for an FlightDomainExcessDetector instance with complementary parameters.
|
LongitudeDetector(double longitudeToDetect,
Frame bodyFrame)
Constructor for the longitude detector.
|
LongitudeDetector(double longitudeToDetect,
Frame bodyFrame,
double maxCheck,
double threshold)
Constructor for the longitude detector.
|
LongitudeDetector(double longitudeToDetect,
Frame bodyFrame,
double maxCheck,
double threshold,
EventDetector.Action action)
Constructor for the longitude detector.
|
LongitudeDetector(double longitudeToDetect,
Frame bodyFrame,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Constructor for the longitude detector.
|
LongitudeDetector(double longitudeToDetect,
Frame bodyFrame,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove,
int slopeSelection)
Complete constructor for the longitude detector.
|
NodeDetector(Frame frameIn,
double maxCheck,
double threshold,
EventDetector.Action ascendingNode,
EventDetector.Action descendingNode)
Build a new instance for both ascending and descending node detection.
|
NodeDetector(Frame frameIn,
double maxCheckIn,
double threshold,
EventDetector.Action ascendingNode,
EventDetector.Action descendingNode,
boolean removeAscendingNode,
boolean removeDescendingNode)
Build a new instance for both ascending and descending node detection.
|
NodeDetector(Frame frameIn,
int slopeSelection,
double maxCheck,
double threshold)
Build a new instance.
|
NodeDetector(Frame frameIn,
int slopeSelection,
double maxCheck,
double threshold,
EventDetector.Action action)
Build a new instance.
|
NodeDetector(Frame frameIn,
int slopeSelection,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean removeCrossingNode)
Build a new instance.
|
NodeDetector(Orbit orbit,
Frame frameIn,
int slopeSelection)
Build a new instance.
|
NodeDetector(Orbit orbit,
Frame frameIn,
int slopeSelection,
double threshold)
Build a new instance.
|
PlaneCrossingDetector(Vector3D normalVector,
Frame referenceFrame,
EventDetector.Action ascendingCrossing,
EventDetector.Action descendingCrossing,
boolean removeIncreasingCrossing,
boolean removeDecreasingCrossing,
double maxCheckIn,
double thresholdIn)
Constructor with default coordinates (0,0,0) for reference point and actions to be performed in both directions.
|
PlaneCrossingDetector(Vector3D normalVector,
Frame referenceFrame,
int slopeSelection,
EventDetector.Action action,
boolean removeCrossing,
double maxCheckIn,
double thresholdIn)
Constructor with default coordinates (0,0,0) for reference point and one detection in the given direction.
|
PlaneCrossingDetector(Vector3D point,
Vector3D normalVector,
Frame referenceFrame,
EventDetector.Action increasingCrossing,
EventDetector.Action decreasingCrossing,
boolean removeAscendingCrossing,
boolean removeDescendingCrossing,
double maxCheckIn,
double thresholdIn)
Constructor for case with different actions at increasing crossing and decreasing crossing.
|
PlaneCrossingDetector(Vector3D point,
Vector3D normalVector,
Frame referenceFrame,
int slopeSelection,
EventDetector.Action action,
boolean removeCrossing,
double maxCheckIn,
double thresholdIn)
Constructor for case with action at descending or ascending crossing.
|
| Modifier and Type | Method and Description |
|---|---|
void |
AdaptedEventDetector.reinitialize(Map<String,AdditionalStateInfo> info,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
AttitudeProvider attProviderForces,
AttitudeProvider attProviderEvents,
AbsoluteDate referenceDateIn,
double muIn,
Frame integrationFrameIn)
Reinitialize reference data.
|
| Modifier and Type | Method and Description |
|---|---|
void |
AdaptedMultiEventDetector.reinitialize(OrbitType orbitType,
PositionAngle angleType,
Map<String,MultiAttitudeProvider> attProvidersForces,
Map<String,MultiAttitudeProvider> attProvidersEvents,
AbsoluteDate referenceDate,
Map<String,Double> muMap,
Map<String,Frame> framesMap,
MultiStateVectorInfo stateVectorInfo)
Reinitialize data.
|
| Constructor and Description |
|---|
AdaptedEventDetector(EventDetector detectorIn,
Map<String,AdditionalStateInfo> info,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
AttitudeProvider attProviderForces,
AttitudeProvider attProviderEvents,
AbsoluteDate referenceDateIn,
double muIn,
Frame integrationFrameIn)
Build a wrapped event detector.
|
| Constructor and Description |
|---|
AdaptedMultiEventDetector(MultiEventDetector detector,
OrbitType orbitType,
PositionAngle angleType,
Map<String,MultiAttitudeProvider> attProvidersForces,
Map<String,MultiAttitudeProvider> attProvidersEvents,
AbsoluteDate referenceDate,
Map<String,Double> muMap,
Map<String,Frame> framesMap,
MultiStateVectorInfo stateVectorInfo)
Build a wrapped multi-sat event detector.
|
| Modifier and Type | Method and Description |
|---|---|
IDirection[] |
PyramidalField.computeSideDirections(Frame frame)
Retrieve the directions delimiting the pyramidal field of view.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
EmpiricalForce.getLocalFrame() |
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
EmpiricalForce.computeAcceleration(PVCoordinates pv,
LocalOrbitalFrame localFrameValidation,
Vector3D vectorS,
Frame frame,
SpacecraftState state)
Method to compute the acceleration.
|
| Constructor and Description |
|---|
EmpiricalForce(int harmonicFactor,
Vector3D vectorS,
IParamDiffFunction ax,
IParamDiffFunction ay,
IParamDiffFunction az,
IParamDiffFunction bx,
IParamDiffFunction by,
IParamDiffFunction bz,
IParamDiffFunction cx,
IParamDiffFunction cy,
IParamDiffFunction cz,
Frame coeffsFrame)
Simple constructor for an empiric force using parameterizable functions for A; B and C coef
with a given frame.
|
EmpiricalForce(int harmonicFactor,
Vector3D vectorS,
Parameter ax,
Parameter ay,
Parameter az,
Parameter bx,
Parameter by,
Parameter bz,
Parameter cx,
Parameter cy,
Parameter cz,
Frame coeffsFrame)
Simple constructor for an empiric force using
Parameter for A; B and C coef
with a given frame. |
EmpiricalForce(int harmonicFactor,
Vector3D vectorS,
Vector3D a,
Vector3D b,
Vector3D c,
Frame coeffsFrame)
Simple constructor for an empiric force, assigning a generic frame to the A, B, C coefficients
frame.
|
| Modifier and Type | Method and Description |
|---|---|
AtmosphereData |
MSISE2000.getData(AbsoluteDate date,
Vector3D position,
Frame frame)
Get detailed atmospheric data.
|
AtmosphereData |
ExtendedAtmosphere.getData(AbsoluteDate date,
Vector3D position,
Frame frame)
Get detailed atmospheric data.
|
AtmosphereData |
AbstractDTM.getData(AbsoluteDate date,
Vector3D position,
Frame frame)
Get detailed atmospheric data.
|
double |
US76.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Getter for the local density for altitude in interval [0, 1E6]m.
|
double |
SimpleExponentialAtmosphere.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
MSISE2000.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
JB2006.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
HarrisPriester.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Getter for the local density.
|
double |
Atmosphere.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
AbstractDTM.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Getter for the local density.
|
double |
US76.getPress(AbsoluteDate date,
Vector3D position,
Frame frame)
Getter for the local pressure for altitude in interval [0, 1E6]m.
|
double |
MSISE2000.getPressure(AbsoluteDate date,
Vector3D position,
Frame frame)
Getter for the pressure.
|
double |
US76.getSpeedOfSound(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local speed of sound.
|
double |
SimpleExponentialAtmosphere.getSpeedOfSound(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local speed of sound.
|
double |
MSISE2000.getSpeedOfSound(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local speed of sound.
|
double |
JB2006.getSpeedOfSound(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local speed of sound.
|
double |
HarrisPriester.getSpeedOfSound(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local speed of sound.
|
double |
Atmosphere.getSpeedOfSound(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local speed of sound.
|
double |
AbstractDTM.getSpeedOfSound(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local speed of sound.
|
double |
US76.getTemp(AbsoluteDate date,
Vector3D position,
Frame frame)
Getter for the local temperature for altitude in interval [0, 1E6]m.
|
Vector3D |
US76.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the spacecraft velocity relative to the atmosphere.
|
Vector3D |
SimpleExponentialAtmosphere.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the spacecraft velocity relative to the atmosphere.
|
Vector3D |
MSISE2000.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the spacecraft velocity relative to the atmosphere.
|
Vector3D |
JB2006.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the inertial velocity of atmosphere molecules.
|
Vector3D |
HarrisPriester.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Getter for the inertial velocity of atmosphere molecules.
|
Vector3D |
Atmosphere.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the spacecraft velocity relative to the atmosphere.
|
Vector3D |
AbstractDTM.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Getter for the inertial velocity of atmosphere molecules.
|
| Modifier and Type | Method and Description |
|---|---|
static Vector3D |
DragForce.computeAcceleration(PVCoordinates pv,
Frame frame,
Atmosphere atm,
AbsoluteDate date,
double kD,
double mass)
Method to compute the acceleration.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
GravityModel.getBodyFrame()
Get the central body frame.
|
Frame |
AbstractGravityModel.getBodyFrame()
Get the central body frame.
|
| Modifier and Type | Method and Description |
|---|---|
void |
AbstractBodyAttraction.addDAccDParam(Vector3D pos,
Frame frame,
AbsoluteDate date,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
void |
AbstractBodyAttraction.addDAccDState(Vector3D pos,
Frame frame,
AbsoluteDate date,
double[][] dAccdPos)
Compute acceleration derivatives with respect to the position of the spacecraft.
|
| Constructor and Description |
|---|
AbstractGravityModel(Frame bodyFrameIn,
Parameter mu)
Constructor.
|
AbstractHarmonicGravityModel(Frame bodyFrameIn,
Parameter mu)
Constructor.
|
BalminoGravityModel(Frame frame,
double ae,
double mu,
double[][] cCoefs,
double[][] sCoefs)
Create an instance of a normalized gravity computation model using normalized coefficients.
|
BalminoGravityModel(Frame frame,
double ae,
double mu,
double[][] cCoefs,
double[][] sCoefs,
int degreePD,
int orderPD)
Create an instance of a normalized gravity computation model using normalized coefficients.
|
BalminoGravityModel(Frame frame,
Parameter ae,
Parameter mu,
double[][] cCoefs,
double[][] sCoefs)
Create an instance of a normalized gravity computation model using normalized coefficients.
|
BalminoGravityModel(Frame frame,
Parameter ae,
Parameter mu,
double[][] cCoefs,
double[][] sCoefs,
int degreePD,
int orderPD)
Create an instance of a normalized gravity computation model using normalized coefficients.
|
BalminoGravityModel(Frame frame,
Parameter ae,
Parameter mu,
double[][] cCoefs,
double[][] sCoefs,
int degreePD,
int orderPD,
boolean centralTermContributionIn)
Create an instance of a normalized gravity computation model using normalized coefficients.
|
CunninghamGravityModel(Frame centralBodyFrame,
double equatorialRadius,
double mu,
double[][] cIn,
double[][] sIn)
Creates a new instance.
|
CunninghamGravityModel(Frame centralBodyFrame,
double equatorialRadius,
double mu,
double[][] cIn,
double[][] sIn,
int degreePD,
int orderPD)
Creates a new instance.
|
CunninghamGravityModel(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
double[][] cIn,
double[][] sIn)
Creates a new instance using
Parameter. |
CunninghamGravityModel(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
double[][] cIn,
double[][] sIn,
int degreePD,
int orderPD)
Creates a new instance using
Parameter. |
CunninghamGravityModel(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
double[][] cIn,
double[][] sIn,
int degreePD,
int orderPD,
boolean centralTermContributionIn)
Creates a new instance using
Parameter. |
DrozinerGravityModel(Frame centralBodyFrameIn,
double equatorialRadius,
double mu,
double[][] cCoefs,
double[][] sCoefs)
Creates a new instance.
|
DrozinerGravityModel(Frame centralBodyFrameIn,
Parameter equatorialRadius,
Parameter mu,
double[][] cCoefs,
double[][] sCoefs)
Creates a new instance using
Parameter. |
DrozinerGravityModel(Frame centralBodyFrameIn,
Parameter equatorialRadius,
Parameter mu,
double[][] cCoefs,
double[][] sCoefs,
boolean centralTermContributionIn)
Creates a new instance using
Parameter. |
NewtonianGravityModel(Frame centralBodyFrame,
double mu)
Simple constructor.
|
NewtonianGravityModel(Frame centralBodyFrame,
double mu,
boolean computePD)
Simple constructor.
|
NewtonianGravityModel(Frame centralBodyFrame,
Parameter mu)
Simple constructor using
Parameter. |
NewtonianGravityModel(Frame centralBodyFrame,
Parameter mu,
boolean computePD)
Simple constructor using
Parameter. |
| Modifier and Type | Method and Description |
|---|---|
double |
GridGravityModel.computePotential(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute the potential due to the body attraction.
|
| Constructor and Description |
|---|
GridGravityModel(GridAttractionProvider attractionProvider,
TrivariateGridInterpolator interpolator,
GravityModel backupModel,
Frame bodyFrameIn)
Constructor.
|
| Modifier and Type | Field and Description |
|---|---|
protected Frame |
AbstractTides.bodyFrame
Frame for the central body.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
AbstractTides.computeAcceleration(PVCoordinates pv,
Frame frame,
AbsoluteDate date)
Method to compute the acceleration, from Balmino algorithm (see BalminoAttractionModel class).
|
| Constructor and Description |
|---|
AbstractTides(Frame centralBodyFrame,
double equatorialRadius,
double mu,
int degree,
int order)
Build a new instance.
|
AbstractTides(Frame centralBodyFrame,
double equatorialRadius,
double mu,
int degree,
int order,
int degreePD,
int orderPD)
Build a new instance.
|
AbstractTides(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
int degree,
int order)
Build a new instance using
Parameter. |
AbstractTides(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
int degree,
int order,
int degreePD,
int orderPD)
Build a new instance using
Parameter. |
OceanTides(Frame centralBodyFrame,
double equatorialRadius,
double mu,
double density,
int degree,
int order,
boolean withAdmittance,
IOceanTidesDataProvider tidesData)
Constructor.
|
OceanTides(Frame centralBodyFrame,
double equatorialRadius,
double mu,
double density,
int degree,
int order,
int degreePD,
int orderPD,
boolean withAdmittance,
IOceanTidesDataProvider tidesData)
Constructor.
|
OceanTides(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
Parameter density,
int degree,
int order,
boolean withAdmittance,
IOceanTidesDataProvider tidesData)
Constructor using
Parameter. |
OceanTides(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
Parameter density,
int degree,
int order,
int degreePD,
int orderPD,
boolean withAdmittance,
IOceanTidesDataProvider tidesData)
Constructor using
Parameter. |
PoleTides(Frame centralBodyFrame,
double equatorialRadius,
double mu,
boolean solidTidesFlag,
boolean oceanicTidesFlag)
Constructor.
|
PoleTides(Frame centralBodyFrame,
double equatorialRadius,
double mu,
boolean solidTidesFlag,
boolean oceanicTidesFlag,
boolean computePD)
Constructor.
|
PoleTides(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
boolean solidTidesFlag,
boolean oceanicTidesFlag)
Constructor.
|
PoleTides(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
boolean solidTidesFlag,
boolean oceanicTidesFlag,
boolean computePD)
Constructor.
|
TerrestrialTides(Frame centralBodyFrame,
double equatorialRadius,
double mu)
Creates a new instance.
|
TerrestrialTides(Frame centralBodyFrame,
double equatorialRadius,
double mu,
boolean computePD)
Creates a new instance.
|
TerrestrialTides(Frame centralBodyFrame,
double equatorialRadius,
double mu,
List<CelestialPoint> celestialPoints,
boolean thirdBodyAttDegree3,
boolean frequencyCorr,
boolean ellipticityCorr,
ITerrestrialTidesDataProvider terrestrialData)
Creates a new instance.
|
TerrestrialTides(Frame centralBodyFrame,
double equatorialRadius,
double mu,
List<CelestialPoint> celestialPoints,
boolean thirdBodyAttDegree3,
boolean frequencyCorr,
boolean ellipticityCorr,
ITerrestrialTidesDataProvider terrestrialData,
boolean computePD)
Creates a new instance.
|
TerrestrialTides(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu)
Creates a new instance.
|
TerrestrialTides(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
boolean computePD)
Creates a new instance.
|
TerrestrialTides(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
List<CelestialPoint> celestialPoints,
boolean thirdBodyAttDegree3,
boolean frequencyCorr,
boolean ellipticityCorr,
ITerrestrialTidesDataProvider terrestrialData)
Creates a new instance using
Parameter. |
TerrestrialTides(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
List<CelestialPoint> celestialPoints,
boolean thirdBodyAttDegree3,
boolean frequencyCorr,
boolean ellipticityCorr,
ITerrestrialTidesDataProvider terrestrialData,
boolean computePD)
Creates a new instance using
Parameter. |
| Constructor and Description |
|---|
VariablePotentialGravityModel(Frame centralBodyFrame,
VariablePotentialCoefficientsProvider provider,
int degree,
int order)
Variable gravity field force model constructor (static part only).
|
VariablePotentialGravityModel(Frame centralBodyFrame,
VariablePotentialCoefficientsProvider provider,
int degree,
int order,
int degreePD,
int orderPD)
Variable gravity field force model constructor (static part only).
|
VariablePotentialGravityModel(Frame centralBodyFrame,
VariablePotentialCoefficientsProvider provider,
int degree,
int order,
int variableDegree,
int variableOrder,
boolean computeOptionalOnce)
Variable gravity field force model constructor.
|
VariablePotentialGravityModel(Frame centralBodyFrame,
VariablePotentialCoefficientsProvider provider,
int degree,
int order,
int variableDegree,
int variableOrder,
int degreePD,
int orderPD,
boolean computeOptionalOnce)
Variable gravity field force model constructor.
|
VariablePotentialGravityModel(Frame centralBodyFrame,
VariablePotentialCoefficientsProvider provider,
int degree,
int order,
int variableDegree,
int variableOrder,
int degreePD,
int orderPD,
boolean computeVariableCoefficientsOnce,
boolean centralTermContributionIn)
Variable gravity field force model constructor.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
ImpulseManeuver.getFrame()
Get the frame of the velocity increment.
|
Frame |
ContinuousThrustManeuver.getFrame()
Get the frame of the acceleration inDirection.
|
Frame |
SmallManeuverAnalyticalModel.getInertialFrame()
Get the inertial frame in which the velocity increment is defined.
|
| Constructor and Description |
|---|
ConstantThrustError(AbsoluteDate date,
double duration,
Frame frame,
double cx,
double cy,
double cz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx fy = cy fz = cz Errors components are expressed in provided frame. |
ConstantThrustError(AbsoluteDate date,
double duration,
Frame frame,
double ax,
double bx,
double ay,
double by,
double az,
double bz,
AbsoluteDate date0)
Create a constant thrust error model whose x, y and z components are linear functions:
fx = ax*t + bx fy = ay*t + by fz = az*t + bz Errors components are expressed in provided frame. |
ConstantThrustError(AbsoluteDate date,
double duration,
Frame frame,
IParamDiffFunction fx,
IParamDiffFunction fy,
IParamDiffFunction fz)
Create a constant thrust error model whose x, y and z components are parameterizable and differentiable function.
|
ConstantThrustError(AbsoluteDate date,
double duration,
Frame frame,
Parameter cx,
Parameter cy,
Parameter cz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx fy = cy fz = cz Errors components are expressed in provided frame. |
ConstantThrustError(AbsoluteDate date,
double duration,
Frame frame,
Parameter ax,
Parameter bx,
Parameter ay,
Parameter by,
Parameter az,
Parameter bz,
AbsoluteDate date0)
Create a constant thrust error model whose x, y and z components are linear functions:
fx = ax*t + bx fy = ay*t + by fz = az*t + bz Errors components are expressed in provided frame. |
ConstantThrustError(EventDetector startEventDetector,
EventDetector stopEventDetector,
Frame frame,
IParamDiffFunction fx,
IParamDiffFunction fy,
IParamDiffFunction fz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx fy = cy fz = cz Errors components are expressed in provided frame. |
ConstantThrustError(EventDetector startEventDetector,
EventDetector stopEventDetector,
Frame frame,
Parameter cx,
Parameter cy,
Parameter cz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx fy = cy fz = cz Errors components are expressed in provided frame. |
ContinuousThrustManeuver(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> inDirection,
MassProvider massProvider,
TankProperty tank,
Frame frameIn)
Constructor for a variable direction in provided frame.
|
ContinuousThrustManeuver(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
Vector3D inDirection,
MassProvider massProvider,
TankProperty tank,
Frame frameIn)
Constructor for a constant direction in provided frame.
|
ContinuousThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> inDirection,
MassProvider massProvider,
TankProperty tank,
Frame frameIn)
Constructor for a variable direction in provided frame.
|
ContinuousThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
PropulsiveProperty engine,
Vector3D inDirection,
MassProvider massProvider,
TankProperty tank,
Frame frameIn)
Constructor for a constant direction in provided frame.
|
ImpulseManeuver(EventDetector inTrigger,
Vector3D inDeltaVSat,
Frame inFrame,
double isp,
MassProvider massModel,
String part)
Build a new instance.
|
ImpulseManeuver(EventDetector inTrigger,
Vector3D inDeltaVSat,
Frame inFrame,
PropulsiveProperty engine,
MassProvider massModel,
TankProperty tank)
Build a new instance using propulsive and engine property.
|
SmallManeuverAnalyticalModel(SpacecraftState state0In,
Frame frame,
Vector3D dV,
double isp,
String partNameIn)
Build a maneuver defined in user-specified frame.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
SolarRadiationPressure.getInertialFrame()
Getter for the inertial frame used for signal propagation computation.
|
Frame |
LightingRatio.getInertialFrame()
Getter for the inertial frame used for signal propagation computation.
|
| Modifier and Type | Method and Description |
|---|---|
double |
SolarRadiationPressure.getLightingRatio(Vector3D satSunVector,
BodyShape occultingBody,
PVCoordinatesProvider pv,
Frame frame,
AbsoluteDate date)
Get the lighting ratio ([0-1]) for provided occulting body.
|
void |
SolarRadiationPressure.setPropagationDelayType(AbstractSignalPropagationDetector.PropagationDelayType propagationDelayTypeIn,
Frame frameIn)
Setter for the propagation delay computation type.
|
void |
LightingRatio.setPropagationDelayType(AbstractSignalPropagationDetector.PropagationDelayType propagationDelayTypeIn,
Frame frameIn)
Setter for the propagation delay computation type.
|
| Constructor and Description |
|---|
LenseThirringRelativisticEffect(double mu,
Frame frame)
Constructor and with partial derivative computation by default.
|
LenseThirringRelativisticEffect(double mu,
Frame frame,
boolean computePartialDerivativesPos,
boolean computePartialDerivativesVel)
Constructor.
|
| Modifier and Type | Class and Description |
|---|---|
class |
CelestialBodyFrame
Frame centered on a
CelestialPoint. |
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 |
PredefinedFrame
Base class for the predefined frames that are managed by
FramesFactory. |
class |
SynodicFrame
Synodic frame.
|
class |
TopocentricFrame
Topocentric frame.
|
class |
TranslatedFrame
Frame which differs from a reference frame by translation provided by a
PVCoordinatesProvider. |
class |
TwoDirectionFrame
Class for frames built with two directions and the two axes they correspond to.
|
class |
UpdatableFrame
Frame whose transform from its parent can be updated.
|
| Modifier and Type | Method and Description |
|---|---|
protected Frame |
Frame.getAncestor(int n)
Get the nth ancestor of the frame.
|
Frame |
Frame.getFirstCommonPseudoInertialAncestor(Frame frame)
Returns the first pseudo-inertial common ancestor between this and provided frame.
|
Frame |
Frame.getFirstPseudoInertialAncestor()
Returns the first pseudo-inertial ancestor in the frame tree.
|
static Frame |
FramesFactory.getFrame(PredefinedFrameType factoryKey)
Get one of the predefined frames.
|
Frame |
Frame.getFrozenFrame(Frame reference,
AbsoluteDate freezingDate,
String frozenName)
Get a new version of the instance, frozen with respect to a reference frame.
|
Frame |
Frame.getFrozenFrame(Frame reference,
String frozenName)
Get a new version of the instance, frozen with respect to a reference frame.
|
static Frame |
FramesFactory.getH0MinusN(String name,
AbsoluteDate h0MinusN,
double longitude)
Get the "H0 - n" reference frame.
|
static Frame |
FramesFactory.getH0MinusN(String name,
AbsoluteDate h0,
double n,
double longitude)
Get the "H0 - n" reference frame.
|
Frame |
Frame.getNativeFrame(AbsoluteDate date)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
static Frame |
OrphanFrame.getNewOrphanFrame(String name)
This method creates an Orphan Frame.
|
Frame |
Frame.getParent()
Get the parent frame.
|
| Modifier and Type | Method and Description |
|---|---|
double |
TopocentricFrame.getAzimuth(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Getter for the azimuth of a point with regards to the topocentric frame center point.
|
double |
TopocentricFrame.getAzimuthRate(PVCoordinates extPV,
Frame frame,
AbsoluteDate date)
Getter for the azimuth rate of a point.
|
Vector3D |
TopocentricFrame.getDAzimuth(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Getter for the azimuth derivative of a point wrt the local point (dAzimuth) express in the specified frame.
|
Vector3D |
TopocentricFrame.getDElevation(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Getter for the elevation derivative of a point wrt the local point (dElevation) express in the specified frame.
|
Vector3D |
TopocentricFrame.getDXangleCardan(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Getter for the Cardan x angle derivative of a point wrt the local point (dXangleCardan) express in the specified
frame.
|
Vector3D |
TopocentricFrame.getDYangleCardan(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Getter for the Cardan y angle derivative of a point wrt the local point (dYangleCardan) express in the specified
frame.
|
double |
TopocentricFrame.getElevation(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Getter for the elevation of a point with regards to the local point.
|
double |
TopocentricFrame.getElevationRate(PVCoordinates extPV,
Frame frame,
AbsoluteDate date)
Getter for the elevation rate of a point.
|
Frame |
Frame.getFirstCommonPseudoInertialAncestor(Frame frame)
Returns the first pseudo-inertial common ancestor between this and provided frame.
|
Frame |
Frame.getFrozenFrame(Frame reference,
AbsoluteDate freezingDate,
String frozenName)
Get a new version of the instance, frozen with respect to a reference frame.
|
Frame |
Frame.getFrozenFrame(Frame reference,
String frozenName)
Get a new version of the instance, frozen with respect to a reference frame.
|
PVCoordinates |
Frame.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the frame origin in the selected frame. |
double |
TopocentricFrame.getRange(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Getter for the range of a point with regards to the topocentric frame center point.
|
double |
TopocentricFrame.getRangeRate(PVCoordinates extPV,
Frame frame,
AbsoluteDate date)
Getter for the range rate of a point with regards to the topocentric frame center point.
|
RealMatrix |
Frame.getTransformJacobian(Frame to,
AbsoluteDate date)
Compute the Jacobian from current frame to target frame at provided date.
|
Transform |
Frame.getTransformTo(Frame destination,
AbsoluteDate date)
Get the transform from the instance to another frame.
|
Transform |
Frame.getTransformTo(Frame destination,
AbsoluteDate date,
boolean computeSpinDerivatives)
Get the transform from the instance to another frame.
|
Transform |
Frame.getTransformTo(Frame destination,
AbsoluteDate date,
FramesConfiguration config)
Get the transform from the instance to another frame.
|
Transform |
Frame.getTransformTo(Frame destination,
AbsoluteDate date,
FramesConfiguration config,
boolean computeSpinDerivatives)
Get the transform from the instance to another frame.
|
double |
TopocentricFrame.getXangleCardan(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Getter for the Cardan x angle of a point.
|
double |
TopocentricFrame.getXangleCardanRate(PVCoordinates extPV,
Frame frame,
AbsoluteDate date)
Getter for the Cardan x angle rate.
|
double |
TopocentricFrame.getYangleCardan(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Getter for the Cardan y angle of a point with regards to the projection point on the plane defined by the zenith
and the west axis.
|
double |
TopocentricFrame.getYangleCardanRate(PVCoordinates extPV,
Frame frame,
AbsoluteDate date)
Getter for the Cardan y angle rate.
|
boolean |
Frame.isChildOf(Frame potentialAncestor)
Determine if a Frame is a child of another one.
|
void |
Frame.setReferential(Frame referentialIn)
Deprecated.
since 4.16, the concept of referential frame is erroneous. All methods using it should be avoided.
The referential frame moves with respect to the frame. To continue to use the ideas behind the notion
of a referential frame, better use the
getFrozenFrame(Frame, String) method. |
CardanMountPosition |
TopocentricFrame.transformFromPositionToCardan(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Transform a Cartesian position coordinates into Cardan mounting in this local topocentric frame.
|
TopocentricPosition |
TopocentricFrame.transformFromPositionToTopocentric(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Transform a Cartesian position coordinates into topocentric coordinates in this local topocentric frame.
|
CardanMountPV |
TopocentricFrame.transformFromPVToCardan(PVCoordinates extPV,
Frame frame,
AbsoluteDate date)
Transform a Cartesian position coordinates into Cardan mounting in this local topocentric frame.
|
TopocentricPV |
TopocentricFrame.transformFromPVToTopocentric(PVCoordinates extPV,
Frame frame,
AbsoluteDate date)
Transform a Cartesian position and velocity coordinates into topocentric coordinates in this local topocentric
frame.
|
void |
UpdatableFrame.updateTransform(Frame f1,
Frame f2,
Transform f1Tof2,
AbsoluteDate date)
Update the transform from parent frame implicitly according to two other
frames.
|
| Constructor and Description |
|---|
CelestialBodyFrame(Frame parent,
TransformProvider transformProvider,
String name,
boolean pseudoInertial,
CelestialPoint celestialPoint)
Generic constructor.
|
CelestialBodyFrame(Frame parent,
TransformProvider transformProvider,
String name,
CelestialPoint celestialPoint)
Constructor.
|
CelestialBodyFrame(Frame parent,
Transform transform,
String name,
boolean pseudoInertial,
CelestialPoint celestialPoint)
Constructor.
|
CelestialBodyFrame(Frame parent,
Transform transform,
String name,
CelestialPoint celestialPoint)
Constructor.
|
Frame(Frame parentIn,
TransformProvider transformProviderIn,
String nameIn)
Build a non-inertial frame from its transform with respect to its parent.
|
Frame(Frame parentIn,
TransformProvider transformProviderIn,
String nameIn,
boolean pseudoInertialIn)
Build a frame from its transform with respect to its parent.
|
Frame(Frame parentIn,
Transform transformIn,
String nameIn)
Build a non-inertial frame from its transform with respect to its parent.
|
Frame(Frame parentIn,
Transform transformIn,
String nameIn,
boolean pseudoInertialIn)
Build a frame from its transform with respect to its parent.
|
FrozenFrame(Frame coordinate,
Frame reference,
String name)
Build a non-inertial frame that has zero linear/angular velocity to a given reference frame.
|
LocalOrbitalFrame(Frame parent,
LOFType type,
PVCoordinatesProvider provider,
String name)
Build a new instance.
|
PredefinedFrame(Frame parent,
TransformProvider transformProvider,
boolean pseudoInertial,
PredefinedFrameType factoryKeyIn)
Simple constructor.
|
TranslatedFrame(Frame parent,
PVCoordinatesProvider center,
String name,
boolean pseudoInertial)
Constructor.
|
TwoDirectionFrame(Frame parentFrame,
PVCoordinatesProvider provider,
String nameIn,
IDirection firstDir,
IDirection secondDir,
Vector3D frameFirstAxis,
Vector3D frameSecondAxis)
Build a new instance with default finite difference delta value
|
TwoDirectionFrame(Frame parentFrame,
PVCoordinatesProvider provider,
String nameIn,
IDirection firstDir,
IDirection secondDir,
Vector3D frameFirstAxis,
Vector3D frameSecondAxis,
double dH)
Build a new instance.
|
UpdatableFrame(Frame parent,
Transform transform,
String name)
Build a non-inertial frame from its transform with respect to its parent.
|
UpdatableFrame(Frame parent,
Transform transform,
String name,
boolean pseudoInertial)
Build a frame from its transform with respect to its parent.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
RFStationAntenna.getFrame()
Returns ground station topocentric frame.
|
Frame |
RFStationAntenna.getNativeFrame(AbsoluteDate date)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
Frame |
GeometricStationAntenna.getNativeFrame(AbsoluteDate date)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinates |
RFStationAntenna.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
PVCoordinates |
GeometricStationAntenna.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the station antenna in the selected frame. |
| Modifier and Type | Method and Description |
|---|---|
GeoMagneticElements |
GeoMagneticField.calculateField(Vector3D point,
Frame frame,
AbsoluteDate date)
Calculate the magnetic field at the specified point identified by the coordinates of the point and the reference
point.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
Orbit.getFrame()
Get the frame in which the orbital parameters are defined.
|
Frame |
Orbit.getNativeFrame(AbsoluteDate dateIn)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
| Modifier and Type | Method and Description |
|---|---|
abstract Orbit |
OrbitType.convertOrbit(Orbit initOrbit,
Frame frame)
Convert an orbit from a given orbit type to an other in a wished frame.
|
protected static void |
Orbit.ensurePseudoInertialFrame(Frame frame)
Ensure the defining frame is a pseudo-inertial frame.
|
RealMatrix |
Orbit.getJacobian(double dt,
Frame initFrame,
Frame destFrame,
OrbitType initOrbitType,
OrbitType destOrbitType,
PositionAngle initAngleType,
PositionAngle destAngleType)
Computes the Jacobian of the transformation between the specified frames, orbit types and
position angle types with respect to this orbit and specified time shift.
|
RealMatrix |
Orbit.getJacobian(Frame initFrame,
Frame destFrame,
OrbitType initOrbitType,
OrbitType destOrbitType,
PositionAngle initAngleType,
PositionAngle destAngleType)
Computes the Jacobian of the transformation between the specified frames, orbit types and
position angle types with respect to this orbit.
|
PVCoordinates |
Orbit.getPVCoordinates(AbsoluteDate otherDate,
Frame otherFrame)
Get the
PVCoordinates of the body in the selected frame. |
PVCoordinates |
Orbit.getPVCoordinates(Frame outputFrame)
Get the
PVCoordinates in a specified frame. |
abstract Orbit |
OrbitType.mapArrayToOrbit(double[] array,
PositionAngle type,
AbsoluteDate date,
double mu,
Frame frame)
Convert state array to orbital parameters.
|
| Constructor and Description |
|---|
AlternateEquinoctialOrbit(double n,
double ex,
double ey,
double hx,
double hy,
double l,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
AlternateEquinoctialOrbit(IOrbitalParameters parametersIn,
Frame frame,
AbsoluteDate date)
Creates a new instance.
|
AlternateEquinoctialOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from cartesian parameters.
|
ApsisOrbit(double peri,
double apo,
double i,
double pa,
double raan,
double anomaly,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
ApsisOrbit(IOrbitalParameters parametersIn,
Frame frame,
AbsoluteDate date)
Creates a new instance.
|
ApsisOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from cartesian parameters.
|
CartesianOrbit(IOrbitalParameters parametersIn,
Frame frame,
AbsoluteDate date)
Creates a new instance.
|
CartesianOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from cartesian parameters.
|
CircularOrbit(double a,
double ex,
double ey,
double i,
double raan,
double alpha,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
CircularOrbit(IOrbitalParameters parametersIn,
Frame frame,
AbsoluteDate date)
Creates a new instance.
|
CircularOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from cartesian parameters.
|
EquatorialOrbit(double a,
double e,
double pomega,
double ix,
double iy,
double anomaly,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
EquatorialOrbit(IOrbitalParameters parametersIn,
Frame frame,
AbsoluteDate date)
Creates a new instance.
|
EquatorialOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from cartesian parameters.
|
EquinoctialOrbit(double a,
double ex,
double ey,
double hx,
double hy,
double l,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
EquinoctialOrbit(IOrbitalParameters parametersIn,
Frame frame,
AbsoluteDate date)
Creates a new instance.
|
EquinoctialOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from cartesian parameters.
|
KeplerianOrbit(double a,
double e,
double i,
double pa,
double raan,
double anomaly,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
KeplerianOrbit(IOrbitalParameters parametersIn,
Frame frame,
AbsoluteDate date)
Creates a new instance.
|
KeplerianOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from cartesian parameters.
|
Orbit(Frame frameIn,
AbsoluteDate dateIn,
double muIn)
Default constructor.
|
Orbit(PVCoordinates pvCoordinatesIn,
Frame frameIn,
AbsoluteDate dateIn,
double muIn)
Set the orbit from Cartesian parameters.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
AbstractBoundedPVProvider.getFrame()
Getter for the reference frame.
|
Frame |
PVCoordinatesProvider.getNativeFrame(AbsoluteDate date)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
Frame |
GNSSPVCoordinates.getNativeFrame(AbsoluteDate date)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
Frame |
ConstantPVCoordinatesProvider.getNativeFrame(AbsoluteDate date) |
Frame |
AbstractBoundedPVProvider.getNativeFrame(AbsoluteDate date)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinates |
PVCoordinatesProvider.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
PVCoordinates |
GNSSPVCoordinates.getPVCoordinates(AbsoluteDate date,
Frame frame)
Geometric computation of the position to a date.
|
PVCoordinates |
EphemerisPvLagrange.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
PVCoordinates |
EphemerisPvHermite.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
PVCoordinates |
ConstantPVCoordinatesProvider.getPVCoordinates(AbsoluteDate date,
Frame frameIn) |
protected PVCoordinates |
AbstractEphemerisPvHermiteLagrange.getPVCoordinates(AbsoluteDate date,
Frame frame,
Vector3D[] tAcc,
boolean velocityAsDerivative)
Common method to get PV coordinates using Hermite interpolation, either in a "Lagrange-like" manner, or in a
traditional manner.
|
| Constructor and Description |
|---|
AbstractBoundedPVProvider(PVCoordinates[] tabPV,
int order,
Frame frame,
AbsoluteDate[] tabDate,
ISearchIndex algo)
Instantiation of AbstractBoundedPVProvider attributes.
|
AbstractEphemerisPvHermiteLagrange(PVCoordinates[] tabPV,
int order,
Frame frame,
AbsoluteDate[] tabDate,
ISearchIndex algo)
Instantiation of AbstractEphemerisPvHermiteLagrange attributes.
|
ConstantPVCoordinatesProvider(PVCoordinates coordinatesIn,
Frame frameIn)
Simple constructor.
|
ConstantPVCoordinatesProvider(Vector3D positionIn,
Frame frameIn)
Builds an instance from the position vector only.
|
EphemerisPvHermite(PVCoordinates[] tabPV,
int samples,
Vector3D[] tabAcc,
Frame frame,
AbsoluteDate[] tabDate,
ISearchIndex algo)
Creates an instance of EphemerisPvHermite.
|
EphemerisPvHermite(PVCoordinates[] tabPV,
Vector3D[] tabAcc,
Frame frame,
AbsoluteDate[] tabDate,
ISearchIndex algo)
Creates an instance of EphemerisPvHermite with default number of samples = 2.
|
EphemerisPvLagrange(PVCoordinates[] tabPV,
int order,
Frame frame,
AbsoluteDate[] tabDate,
ISearchIndex algo)
Creates an instance of EphemerisPvLagrange
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
SpacecraftState.getFrame()
Get the inertial frame.
|
Frame |
Propagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
AnalyticalIntegratedEphemeris.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
AbstractPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
MultiPropagator.getFrame(String satId)
Get the frame in which the orbit is propagated.
|
default Frame |
Propagator.getNativeFrame(AbsoluteDate date)
Get the native frame, i.e. the raw frame in which PVCoordinates are expressed before transformation to user
output frame.
|
| Modifier and Type | Method and Description |
|---|---|
Attitude |
SpacecraftState.getAttitude(Frame outputFrame)
Get the default attitude : the attitude for forces computation in given output frame.
|
Attitude |
SpacecraftState.getAttitudeEvents(Frame outputFrame)
Get the attitude for events computation in given output frame.
|
Attitude |
SpacecraftState.getAttitudeForces(Frame outputFrame)
Get the attitude for forces computation in given output frame.
|
default PVCoordinates |
SpacecraftStateProvider.getPVCoordinates(AbsoluteDate date,
Frame frame)
Default implementation for PVCoordinatesProvider feature using the
SpacecraftState
object's orbit. |
PVCoordinates |
AbstractPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame)
Default implementation for PVCoordinatesProvider feature using the
SpacecraftState
object's orbit. |
PVCoordinates |
SpacecraftState.getPVCoordinates(Frame outputFrame)
Get the
PVCoordinates in given output frame. |
void |
BoundedPropagator.setOrbitFrame(Frame frameIn)
Set propagation frame.
|
void |
AbstractPropagator.setOrbitFrame(Frame frame)
Set propagation frame.
|
Transform |
SpacecraftState.toTransform(Frame frame)
Compute the transform from specified frame to spacecraft frame.
|
Transform |
SpacecraftState.toTransform(Frame frame,
LOFType lofType)
Compute the transform from specified frame to local orbital frame.
|
Transform |
SpacecraftState.toTransformEvents(Frame frame)
Compute the transform from specified reference frame to spacecraft frame.
|
Transform |
SpacecraftState.toTransformForces(Frame frame)
Compute the transform from specified frame to spacecraft frame.
|
| 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.
|
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(double[] y,
OrbitType orbitType,
PositionAngle angleType,
AbsoluteDate date,
double mu,
Frame frame,
Map<String,AdditionalStateInfo> addStatesInfo,
AttitudeProvider attProviderForces,
AttitudeProvider attProviderEvents)
Build a spacecraft from an array (a state vector) and an additional states informations map.
|
| Modifier and Type | Method and Description |
|---|---|
protected Orbit |
LiuMeanOsculatingConverter.convertFrame(Orbit orbit,
Frame outputFrame)
Convert provided orbit in output frame.
|
protected Orbit |
AbstractLyddanePropagator.convertFrame(Orbit orbit,
Frame outputFrame)
Convert provided orbit in output frame.
|
protected Orbit |
AbstractLyddanePropagator.propagateOrbit(AbsoluteDate date,
Orbit secularOrbit,
Frame outputFrame,
AbstractLyddanePropagator.LyddaneParametersType returnType,
AbstractLyddanePropagator.SubModel fixConvLoop)
Propagate orbit to provided date.
|
| Constructor and Description |
|---|
AbstractLyddanePropagator(Orbit secularOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
double c30In,
double c40In,
double c50In,
Frame frameIn,
ParametersType parametersTypeIn,
AttitudeProvider attitudeProvForces,
AttitudeProvider attitudeProvEvents,
MassProvider massProvider)
Generic constructor.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProvForces,
AttitudeProvider attitudeProvEvents,
double referenceRadiusIn,
double muIn,
Frame frame,
double c20In,
double c30In,
double c40In,
double c50In,
double c60In,
MassProvider massProvider,
ParametersType paramsType)
Build a propagator from orbit, attitude provider, mass and potential.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProvForces,
AttitudeProvider attitudeProvEvents,
double referenceRadiusIn,
double muIn,
Frame frame,
double c20In,
double c30In,
double c40In,
double c50In,
double c60In,
ParametersType paramsType)
Build a propagator from orbit, attitude provider for forces and events computation and
potential.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double referenceRadiusIn,
double muIn,
Frame frame,
double c20In,
double c30In,
double c40In,
double c50In,
double c60In,
MassProvider massProvider,
ParametersType paramsType)
Build a propagator from orbit, attitude provider, mass and potential.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double referenceRadiusIn,
double muIn,
Frame frame,
double c20In,
double c30In,
double c40In,
double c50In,
double c60In,
ParametersType paramsType)
Build a propagator from orbit, attitude provider and potential.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
Frame frame,
double c20In,
double c30In,
double c40In,
double c50In,
double c60In,
MassProvider massProvider,
ParametersType paramsType)
Build a propagator from orbit, mass and potential.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
Frame frame,
double c20In,
double c30In,
double c40In,
double c50In,
double c60In,
ParametersType paramsType)
Build a propagator from orbit and potential.
|
J2SecularPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
Frame frameIn)
Constructor without attitude provider and mass provider.
|
J2SecularPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
Frame frameIn,
AttitudeProvider attitudeProvider)
Constructor without mass provider.
|
J2SecularPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
Frame frameIn,
AttitudeProvider attitudeProvForces,
AttitudeProvider attitudeProvEvents)
Constructor without mass provider.
|
J2SecularPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
Frame frameIn,
AttitudeProvider attitudeProvForces,
AttitudeProvider attitudeProvEvents,
MassProvider massProvider)
Generic constructor.
|
J2SecularPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
Frame frameIn,
AttitudeProvider attitudeProvider,
MassProvider massProvider)
Generic constructor.
|
J2SecularPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
Frame frameIn,
MassProvider massProvider)
Constructor without attitude provider.
|
LiuMeanOsculatingConverter(double referenceRadius,
double mu,
double j2,
Frame frame)
Constructor.
|
LyddaneLongPeriodPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
double c30In,
double c40In,
double c50In,
Frame frameIn,
ParametersType parametersTypeIn)
Constructor without attitude provider and mass provider.
|
LyddaneLongPeriodPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
double c30In,
double c40In,
double c50In,
Frame frameIn,
ParametersType parametersTypeIn,
AttitudeProvider attitudeProvider)
Constructor without mass provider.
|
LyddaneLongPeriodPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
double c30In,
double c40In,
double c50In,
Frame frameIn,
ParametersType parametersTypeIn,
AttitudeProvider attitudeProvForces,
AttitudeProvider attitudeProvEvents)
Constructor without mass provider.
|
LyddaneLongPeriodPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
double c30In,
double c40In,
double c50In,
Frame frameIn,
ParametersType parametersTypeIn,
AttitudeProvider attitudeProvForces,
AttitudeProvider attitudeProvEvents,
MassProvider massProvider)
Generic constructor.
|
LyddaneLongPeriodPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
double c30In,
double c40In,
double c50In,
Frame frameIn,
ParametersType parametersTypeIn,
AttitudeProvider attitudeProvider,
MassProvider massProvider)
Generic constructor.
|
LyddaneLongPeriodPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
double c30In,
double c40In,
double c50In,
Frame frameIn,
ParametersType parametersTypeIn,
MassProvider massProvider)
Constructor without attitude provider.
|
LyddaneSecularPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
double c30In,
double c40In,
double c50In,
Frame frameIn,
ParametersType parametersTypeIn)
Constructor without attitude provider and mass provider.
|
LyddaneSecularPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
double c30In,
double c40In,
double c50In,
Frame frameIn,
ParametersType parametersTypeIn,
AttitudeProvider attitudeProvider)
Constructor without mass provider.
|
LyddaneSecularPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
double c30In,
double c40In,
double c50In,
Frame frameIn,
ParametersType parametersTypeIn,
AttitudeProvider attitudeProvForces,
AttitudeProvider attitudeProvEvents)
Constructor without mass provider.
|
LyddaneSecularPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
double c30In,
double c40In,
double c50In,
Frame frameIn,
ParametersType parametersTypeIn,
AttitudeProvider attitudeProvForces,
AttitudeProvider attitudeProvEvents,
MassProvider massProvider)
Generic constructor.
|
LyddaneSecularPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
double c30In,
double c40In,
double c50In,
Frame frameIn,
ParametersType parametersTypeIn,
AttitudeProvider attitudeProvider,
MassProvider massProvider)
Generic constructor.
|
LyddaneSecularPropagator(Orbit initialOrbit,
double referenceRadiusIn,
double muIn,
double c20In,
double c30In,
double c40In,
double c50In,
Frame frameIn,
ParametersType parametersTypeIn,
MassProvider massProvider)
Constructor without attitude provider.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
MultiAnalyticalPropagator.getFrame(String satId)
Get the frame in which the orbit is propagated.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
TLEPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
| Modifier and Type | Method and Description |
|---|---|
protected Frame |
PartialDerivativesEquations.getFrame()
Returns the propagator frame.
|
Frame |
NumericalPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
protected abstract Frame |
AbstractPartialDerivativesEquations.getFrame()
Returns the propagator frame.
|
Frame |
JacobiansMapper.getPropagationFrame()
Getter for the propagation frame.
|
| Modifier and Type | Method and Description |
|---|---|
void |
TimeDerivativesEquations.addAcceleration(Vector3D gamma,
Frame frame)
Add the contribution of an acceleration expressed in some inertial frame.
|
void |
JacobiansMapper.getParametersJacobian(Parameter parameter,
SpacecraftState state,
double[] dYdP,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
Frame frameIn)
Get the Jacobian with respect to provided parameter
parameter. |
double[] |
JacobiansMapper.getParametersJacobian(Parameter parameter,
SpacecraftState state,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
Frame frameIn)
Get the Jacobian with respect to provided parameter
parameter. |
void |
JacobiansMapper.getParametersJacobian(SpacecraftState state,
double[][] dYdP,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
Frame frameIn)
Get the Jacobian with respect to parameters.
|
double[][] |
JacobiansMapper.getParametersJacobian(SpacecraftState state,
OrbitType orbitTypeOut,
PositionAngle angleTypeOut,
Frame frameOut)
Get the Jacobian with respect to parameters.
|
PVCoordinates |
NumericalPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame)
Default implementation for PVCoordinatesProvider feature using the
SpacecraftState
object's orbit. |
void |
JacobiansMapper.getStateJacobian(SpacecraftState state,
double[][] dYdY0,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
Frame frameIn)
Get the Jacobian with respect to state.
|
double[][] |
JacobiansMapper.getStateJacobian(SpacecraftState state,
OrbitType orbitTypeOut,
PositionAngle angleTypeOut,
Frame frameOut)
Get the Jacobian with respect to state.
|
void |
ModeHandler.initialize(OrbitType orbit,
PositionAngle angle,
AttitudeProvider attitudeProviderForces,
AttitudeProvider attitudeProviderEvents,
Map<String,AdditionalStateInfo> additionalStateInfos,
boolean activateHandlers,
AbsoluteDate reference,
Frame frame,
double mu)
Initialize the mode handler.
|
| Constructor and Description |
|---|
JacobiansMapper(String nameIn,
List<Parameter> list,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
Frame frame)
Simple constructor.
|
NumericalPropagator(FirstOrderIntegrator integratorIn,
Frame propagationFrameIn)
Create a new instance of NumericalPropagator, based on orbit definition mu.
|
NumericalPropagator(FirstOrderIntegrator integratorIn,
Frame propagationFrameIn,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn)
Create a new instance of NumericalPropagator, based on orbit definition mu.
|
| Modifier and Type | Method and Description |
|---|---|
protected Frame |
MultiPartialDerivativesEquations.getFrame()
Returns the propagator frame.
|
Frame |
MultiNumericalPropagator.getFrame(String satId)
Get the frame in which the orbit is propagated.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinates |
MultiNumericalPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame,
String satId)
Get the
PVCoordinates of the body in the selected frame. |
| Modifier and Type | Method and Description |
|---|---|
void |
MultiModeHandler.initialize(OrbitType orbit,
PositionAngle angle,
Map<String,MultiAttitudeProvider> attitudeProvidersForces,
Map<String,MultiAttitudeProvider> attitudeProvidersEvents,
MultiStateVectorInfo stateVectorInfo,
boolean activateHandlers,
AbsoluteDate reference,
Map<String,Frame> frame,
Map<String,Double> mu)
Initialize the mode handler.
|
void |
MultiEphemerisModeHandler.initialize(OrbitType orbit,
PositionAngle angle,
Map<String,MultiAttitudeProvider> attitudeProvidersForces,
Map<String,MultiAttitudeProvider> attitudeProvidersEvents,
MultiStateVectorInfo stateVectorInfo,
boolean activateHandlers,
AbsoluteDate reference,
Map<String,Frame> frame,
Map<String,Double> mu)
Initialize the mode handler.
|
Map<String,SpacecraftState> |
MultiStateVectorInfo.mapArrayToStates(double[] y,
AbsoluteDate currentDate,
OrbitType orbitType,
PositionAngle angleType,
Map<String,MultiAttitudeProvider> attProvidersForces,
Map<String,MultiAttitudeProvider> attProvidersEvents,
Map<String,Double> mu,
Map<String,Frame> integrationFrame)
Convert state vector into a Map of SpacecraftState
|
| Constructor and Description |
|---|
MultiNumericalPropagator(FirstOrderIntegrator integratorIn,
Map<String,Frame> propagationFrameMapIn)
Create a new instance of MultiNumericalPropagator.
|
MultiNumericalPropagator(FirstOrderIntegrator integratorIn,
Map<String,Frame> propagationFrameMapIn,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn)
Create a new instance of MultiNumericalPropagator.
|
MultiStateVectorInfo(Map<String,SpacecraftState> s,
Map<String,Frame> frames,
Map<String,SpacecraftStateProvider> addStateProviders)
Build a MultiSatStateVectorInfo instance using the spacecraft states' map.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
PVEphemeris.getFrame()
Getter for the frame in which the time-stamped PVCoordinates are defined.
|
Frame |
PVEphemeris.getNativeFrame(AbsoluteDate date)
Getter for the frame in which the time-stamped PVCoordinates are defined.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinates |
PVEphemeris.getPVCoordinates(AbsoluteDate date,
Frame frameOut)
Default implementation for PVCoordinatesProvider feature using the
SpacecraftState
object's orbit. |
PVCoordinates |
IntegratedEphemeris.getPVCoordinates(AbsoluteDate date,
Frame frame)
Default implementation for PVCoordinatesProvider feature using the
SpacecraftState
object's orbit. |
PVCoordinates |
Ephemeris.getPVCoordinates(AbsoluteDate date,
Frame frame)
Default implementation for PVCoordinatesProvider feature using the
SpacecraftState
object's orbit. |
void |
PVEphemeris.setOrbitFrame(Frame frameIn)
Set propagation frame.
|
| Constructor and Description |
|---|
IntegratedEphemeris(List<AbsoluteDate> startDatesIn,
List<AbsoluteDate> minDatesIn,
List<AbsoluteDate> maxDatesIn,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
AttitudeProvider attitudeForcesProvider,
AttitudeProvider attitudeEventsProvider,
Map<String,AdditionalStateInfo> additionalStateInfos,
List<ContinuousOutputModel> modelsIn,
Frame referenceFrameIn,
double muIn)
Creates a new instance of IntegratedEphemeris.
|
IntegratedEphemeris(List<AbsoluteDate> startDatesIn,
List<AbsoluteDate> minDatesIn,
List<AbsoluteDate> maxDatesIn,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
AttitudeProvider attitudeProvider,
Map<String,AdditionalStateInfo> additionalStateInfos,
List<ContinuousOutputModel> modelsIn,
Frame referenceFrameIn,
double muIn)
Creates a new instance of IntegratedEphemeris.
|
PVEphemeris(List<TimeStampedPVCoordinates> pvts,
int order,
Frame frame,
double mu,
CartesianDerivativesFilter filter)
Standard constructor.
|
PVEphemeris(List<TimeStampedPVCoordinates> pvts,
int order,
Frame frame,
double mu,
CartesianDerivativesFilter filter,
AttitudeProvider attitudeProvider)
Standard constructor.
|
PVEphemeris(List<TimeStampedPVCoordinates> pvts,
int order,
Frame frame,
double mu,
CartesianDerivativesFilter filter,
AttitudeProvider attitudeProvider,
boolean acceptOutOfOptimalRange)
Standard constructor.
|
PVEphemeris(List<TimeStampedPVCoordinates> pvts,
int order,
Frame frame,
double mu,
CartesianDerivativesFilter filter,
AttitudeProvider attitudeProvider,
boolean acceptOutOfOptimalRange,
int cacheSize)
Standard constructor.
|
PVEphemeris(List<TimeStampedPVCoordinates> pvts,
int order,
Frame frame,
double mu,
CartesianDerivativesFilter filter,
AttitudeProvider attitudeProvider,
boolean acceptOutOfOptimalRange,
int cacheSize,
boolean computeAcceleration)
Full constructor.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinates |
MultiIntegratedEphemeris.getPVCoordinates(AbsoluteDate date,
Frame frame)
Default implementation for PVCoordinatesProvider feature using the
SpacecraftState
object's orbit. |
| Constructor and Description |
|---|
MultiIntegratedEphemeris(List<AbsoluteDate> startDatesIn,
List<AbsoluteDate> minDatesIn,
List<AbsoluteDate> maxDatesIn,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
MultiAttitudeProvider multiAttitudeProviderForcesIn,
MultiAttitudeProvider multiAttitudeProviderEventsIn,
MultiStateVectorInfo stateInfos,
List<ContinuousOutputModel> modelsIn,
Frame referenceFrameIn,
String satIdIn)
Creates a new instance of IntegratedEphemeris.
|
| Modifier and Type | Method and Description |
|---|---|
void |
AdaptedStepHandler.initialize(OrbitType orbit,
PositionAngle angle,
AttitudeProvider attitudeProviderForces,
AttitudeProvider attitudeProviderEvents,
Map<String,AdditionalStateInfo> additionalStateInfos,
boolean activateHandlers,
AbsoluteDate reference,
Frame frame,
double mu)
Initialize the mode handler.
|
| Modifier and Type | Method and Description |
|---|---|
void |
MultiAdaptedStepHandler.initialize(OrbitType orbit,
PositionAngle angle,
Map<String,MultiAttitudeProvider> attProvidersForces,
Map<String,MultiAttitudeProvider> attProvidersEvents,
MultiStateVectorInfo stateVectorInfo,
boolean activateHandlers,
AbsoluteDate reference,
Map<String,Frame> frameMap,
Map<String,Double> muMap)
Initialize the mode handler.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
VacuumSignalPropagation.getFrame()
Getter for the reference frame.
|
| Modifier and Type | Method and Description |
|---|---|
RealMatrix |
VacuumSignalPropagation.getdPropdPem(Frame expressionFrame)
Deprecated.
as of 4.13
|
RealMatrix |
VacuumSignalPropagation.getdPropdPrec(Frame expressionFrame)
Deprecated.
as of 4.13
|
Vector3D |
VacuumSignalPropagation.getdPropdT(Frame expressionFrame)
Deprecated.
as of 4.13, use
VacuumSignalPropagation.getdPropdT() instead |
Vector3D |
VacuumSignalPropagation.getdTpropdPem(Frame expressionFrame)
Deprecated.
as of 4.13, use
VacuumSignalPropagation.getdTpropdPem() instead |
Vector3D |
VacuumSignalPropagation.getdTpropdPrec(Frame expressionFrame)
Deprecated.
as of 4.13, use
VacuumSignalPropagation.getdTpropdPrec() instead |
static AbsoluteDate |
VacuumSignalPropagationModel.getSignalEmissionDate(PVCoordinatesProvider emitter,
PVCoordinatesProvider orbit,
AbsoluteDate date,
double epsilon,
AbstractSignalPropagationDetector.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
AbstractSignalPropagationDetector.PropagationDelayType. |
static AbsoluteDate |
VacuumSignalPropagationModel.getSignalEmissionDate(PVCoordinatesProvider emitter,
PVCoordinatesProvider orbit,
AbsoluteDate date,
double epsilon,
AbstractSignalPropagationDetector.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
AbstractSignalPropagationDetector.PropagationDelayType. |
static AbsoluteDate |
VacuumSignalPropagationModel.getSignalReceptionDate(PVCoordinatesProvider receiver,
PVCoordinatesProvider orbit,
AbsoluteDate date,
double epsilon,
AbstractSignalPropagationDetector.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
AbstractSignalPropagationDetector.PropagationDelayType. |
static AbsoluteDate |
VacuumSignalPropagationModel.getSignalReceptionDate(PVCoordinatesProvider receiver,
PVCoordinatesProvider orbit,
AbsoluteDate date,
double epsilon,
AbstractSignalPropagationDetector.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
AbstractSignalPropagationDetector.PropagationDelayType. |
Vector3D |
VacuumSignalPropagation.getVector(Frame expressionFrame)
Deprecated.
as of 4.13, use
VacuumSignalPropagation.getVector() instead |
| Constructor and Description |
|---|
VacuumSignalPropagation(PVCoordinates emitterPV,
PVCoordinates receiverPV,
AbsoluteDate inEmissionDate,
AbsoluteDate inReceptionDate,
Frame refFrame,
VacuumSignalPropagationModel.FixedDate fixedDate)
Signal propagation constructor.
|
VacuumSignalPropagationModel(Frame frameIn)
Constructor of the signal propagation model.
|
VacuumSignalPropagationModel(Frame frameIn,
double thresholdIn)
Constructor of the signal propagation model.
|
VacuumSignalPropagationModel(Frame frameIn,
double thresholdIn,
int maxIterIn)
Constructor of the signal propagation model.
|
VacuumSignalPropagationModel(Frame frameIn,
double thresholdIn,
VacuumSignalPropagationModel.ConvergenceAlgorithm convAlgo)
Constructor of the signal propagation model.
|
VacuumSignalPropagationModel(Frame frameIn,
double thresholdIn,
VacuumSignalPropagationModel.ConvergenceAlgorithm convAlgo,
int maxIterIn)
Constructor of the signal propagation model.
|
VacuumSignalPropagationModel(Frame frameIn,
VacuumSignalPropagationModel.ConvergenceAlgorithm convAlgo)
Constructor of the signal propagation model.
|
| Modifier and Type | Method and Description |
|---|---|
double |
BentModel.computeElectronicCont(AbsoluteDate date,
Vector3D satellite,
Frame frameSat)
Computation of the electric content between the station and the satellite at a date.
|
double |
IonosphericCorrection.computeSignalDelay(double frequency,
AbsoluteDate date,
Vector3D satellite,
Frame satFrame)
Calculates the ionospheric signal delay for the signal path from the position
of the transmitter and the receiver and the current date.
|
double |
BentModel.computeSignalDelay(double freq,
AbsoluteDate date,
Vector3D satellite,
Frame frameSat)
Calculates the ionospheric signal delay for the signal path from the position
of the transmitter and the receiver and the current date.
|
double |
IonosphericCorrection.derivativeValue(Parameter p,
AbsoluteDate date,
Vector3D satellite,
Frame satFrame)
Compute the derivative value with respect to the input parameter.
|
double |
BentModel.derivativeValue(Parameter p,
AbsoluteDate date,
Vector3D satellite,
Frame satFrame)
Compute the derivative value with respect to the input parameter.
|
| Constructor and Description |
|---|
BentModel(R12Provider r12Provider,
SolarActivityDataProvider solarActivity,
USKProvider uskProvider,
EllipsoidBodyShape earth,
Vector3D station,
Frame frameSta)
Constructor for the Bent ionospheric correction model.
|
| Modifier and Type | Method and Description |
|---|---|
JacchiaOutput |
Jacchia77.getData(AbsoluteDate date,
Vector3D position,
Frame frame)
Getter for the atmospheric model output container.
|
double |
Jacchia77.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Getter for the density at the local point.
|
double |
Jacchia77.getMeanMolarMass(AbsoluteDate date,
Vector3D position,
Frame frame)
Getter for the mean molar mass at the local point.
|
double |
Jacchia77.getSpeedOfSound(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local speed of sound.
|
double |
Jacchia77.getTemperature(AbsoluteDate date,
Vector3D position,
Frame frame)
Getter for the temperature at the local point.
|
Vector3D |
Jacchia77.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the spacecraft velocity relative to the atmosphere.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
NonInertialContribution.computeOmega(AbsoluteDate date,
Frame frame1,
Frame frame2)
Compute rotation vector of frame2 with respect to frame1 expressed in frame2,
which is the rotation vector from frame1 to frame2.
|
Vector3D |
NonInertialContribution.computeOmegaDerivative(AbsoluteDate date,
Frame frame1,
Frame frame2,
double dt)
Compute rotation vector derivative from frame1 to frame2 using finite differences.
|
| Constructor and Description |
|---|
NonInertialContribution(int quadPointsIn,
Frame referenceSystemIn)
Constructor.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinates |
StelaEquinoctialOrbit.getPVCoordinates(AbsoluteDate otherDate,
Frame otherFrame)
Get the
PVCoordinates of the body in the selected frame. |
| Constructor and Description |
|---|
StelaEquinoctialOrbit(double aIn,
double exIn,
double eyIn,
double ixIn,
double iyIn,
double lMIn,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
StelaEquinoctialOrbit(double aIn,
double exIn,
double eyIn,
double ixIn,
double iyIn,
double lMIn,
Frame frame,
AbsoluteDate date,
double mu,
boolean isCorrectedIn)
Creates a new instance.
|
StelaEquinoctialOrbit(IOrbitalParameters params,
Frame frame,
AbsoluteDate date)
Creates a new instance.
|
StelaEquinoctialOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from cartesian parameters.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
StelaAbstractPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinates |
StelaAbstractPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame)
Default implementation for PVCoordinatesProvider feature using the
SpacecraftState
object's orbit. |
void |
StelaAbstractPropagator.setOrbitFrame(Frame frame)
Set propagation frame.
|
| Modifier and Type | Method and Description |
|---|---|
double |
LocalTimeAngle.computeMeanLocalTimeAngle(AbsoluteDate date,
Vector3D pos,
Frame frame)
Compute mean local time angle in TIRF frame in the range [-Π, Π[.
|
double |
LocalTimeAngle.computeRAANFromTrueLocalTime(AbsoluteDate date,
double trueLocalTime,
Frame frame)
Compute RAAN from true local time angle
|
double |
LocalTimeAngle.computeTrueLocalTimeAngle(AbsoluteDate date,
Vector3D pos,
Frame frame)
Compute true local time angle in TIRF frame in the range [-Π, Π[.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
WrenchModel.computeTorque(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
Vector3D |
SolarRadiationWrench.computeTorque(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
Vector3D |
MagneticWrench.computeTorque(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
Vector3D |
GravitationalAttractionWrench.computeTorque(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
Vector3D |
GenericWrenchModel.computeTorque(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
Vector3D |
DragWrench.computeTorque(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
Wrench |
WrenchModel.computeWrench(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
Wrench |
SolarRadiationWrench.computeWrench(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
Wrench |
MagneticWrench.computeWrench(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
Wrench |
GravitationalAttractionWrench.computeWrench(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
Wrench |
GenericWrenchModel.computeWrench(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
Wrench |
DragWrench.computeWrench(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
Wrench |
DragWrenchSensitive.dragWrench(SpacecraftState state,
double density,
Vector3D relativeVelocity,
Vector3D origin,
Frame frame)
Compute the torque due to radiation pressire.
|
Wrench |
RadiationWrenchSensitive.radiationWrench(SpacecraftState state,
Vector3D flux,
Vector3D origin,
Frame frame)
Compute the torque due to radiation pressire.
|
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