| Modifier and Type | Method and Description |
|---|---|
Frame |
IPart.getFrame() |
Frame |
MainPart.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 |
|---|---|
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).
|
protected static Vector3D |
DirectRadiativeModel.forceOnSphere(SpacecraftState state,
IPart part,
Vector3D flux,
Frame mainPartFrame)
Method to compute the force for a spherical model.
|
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 |
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 |
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 |
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 |
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.
|
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.
|
Vector3D |
InertiaSimpleModel.getMassCenter(Frame frame,
AbsoluteDate date)
Getter for the mass center.
|
Vector3D |
IInertiaModel.getMassCenter(Frame frame,
AbsoluteDate date)
Getter for the mass center.
|
Vector3D |
InertiaComputedModel.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.getRefrenceAxis(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 mainPartFrame,
Frame partFrame) |
double |
AeroSphereProperty.getCrossSection(SpacecraftState state,
Vector3D relativeVelocity,
Frame mainPartFrame,
Frame partFrame) |
double |
RadiativeCrossSectionProperty.getCrossSection(SpacecraftState state,
Vector3D flux,
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. |
class |
OrientationFrame
This class is a special implementation of the
Frame class; it represents a dynamic orientation frame,
i.e. |
| Modifier and Type | Field and Description |
|---|---|
protected Frame |
AbstractIsisSpinBiasSlew.refFrame
Reference frame.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
GroundPointing.getBodyFrame()
Get the body frame.
|
Frame |
LofOffset.getPseudoInertialFrame()
Getter for the inertial frame with respect to which orbit should be computed.
|
Frame |
ConstantAttitudeLaw.getReferenceFrame()
Getter for the reference frame.
|
Frame |
Attitude.getReferenceFrame()
Get the reference frame.
|
| Modifier and Type | Method and Description |
|---|---|
SortedSet<Attitude> |
AbstractAttitudeEphemerisGenerator.generateEphemeris(AbsoluteDateInterval ephemerisInterval,
Frame frame)
Computes attitude ephemeris using a fixed or variable time step and choosing the interval of validity.
|
SortedSet<Attitude> |
AbstractAttitudeEphemerisGenerator.generateEphemeris(Frame frame)
Computes attitude ephemeris using a fixed or variable time step.
|
Attitude |
TwoSpinBiasSlew.getAttitude(AbsoluteDate date,
Frame frame) |
Attitude |
AbstractIsisSpinBiasSlew.getAttitude(AbsoluteDate date,
Frame frame)
Compute the attitude.
|
Attitude |
Slew.getAttitude(AbsoluteDate date,
Frame frame)
Compute the attitude.
|
Attitude |
ConstantSpinSlew.getAttitude(AbsoluteDate date,
Frame frame) |
Attitude |
AttitudesSequence.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 |
FixedRate.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 |
AeroAttitudeLaw.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
ComposedAttitudeLaw.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
Attitude |
BodyCenterPointing.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 |
SpinStabilized.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
TabulatedAttitude.getAttitude(PVCoordinatesProvider pvProvider,
AbsoluteDate date,
Frame inFrame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudeLegsSequence.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Gets the attitude from the sequence.
The AttitudeLeg matching the date is called to compute the attitude. |
Attitude |
IsisSunPointing.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
CelestialBodyPointed.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
RelativeTabulatedAttitudeLeg.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
YawSteering.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
ConstantAttitudeLaw.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudeLawLeg.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
Attitude |
AbstractSlew.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
Attitude |
TwoDirectionsAttitude.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
GroundPointing.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AttitudeLegLaw.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 |
AttitudeProvider.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
GroundPointingWrapper.getBaseState(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the base system state at given date, without compensation.
|
TimeStampedAngularCoordinates |
YawCompensation.getCompensation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame orbitFrame,
Attitude base)
Compute the TimeStampedAngularCoordinates at a given time.
|
TimeStampedAngularCoordinates |
YawSteering.getCompensation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame orbitFrame,
Attitude base)
Compute the TimeStampedAngularCoordinates at a given time.
|
abstract TimeStampedAngularCoordinates |
GroundPointingWrapper.getCompensation(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame,
Attitude base)
Compute the TimeStampedAngularCoordinates at a given time.
|
Attitude |
AttitudeLegsSequence.getOldAttitudeOnTransition(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Returns the attitude at a transition date for the old attitude law (the law previous to
the valid transition law).
|
Rotation |
DirectionTrackingOrientation.getOrientation(AbsoluteDate date,
Frame frame) |
Rotation |
IOrientationLaw.getOrientation(AbsoluteDate date,
Frame frame)
Gets the rotation defining the orientation with respect to a given frame at a given date.
|
Vector3D |
TwoSpinBiasSlew.getSpinDerivatives(AbsoluteDate date,
Frame frame)
get the spin derivatives (default implementation : finite differences differentiator).
|
Vector3DFunction |
TwoSpinBiasSlew.getSpinFunction(Frame frame,
AbsoluteDate zeroAbscissa) |
protected Vector3D |
BodyCenterGroundPointing.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
protected Vector3D |
LofOffsetPointing.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
protected Vector3D |
TargetGroundPointing.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
protected Vector3D |
NadirPointing.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
protected abstract Vector3D |
GroundPointing.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
protected Vector3D |
GroundPointingWrapper.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
TimeStampedPVCoordinates |
NadirPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame) |
protected TimeStampedPVCoordinates |
GroundPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
protected TimeStampedPVCoordinates |
GroundPointingWrapper.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,
AttitudeLaw attitudeLaw,
Frame referenceFrame)
Constructor of the dynamic spacecraft frame.
|
AttitudeTransformProvider(AttitudeLaw law,
PVCoordinatesProvider pv,
Frame frame)
Protected constructor.
|
BodyCenterPointing(Frame bodyFrameIn)
Creates new instance.
|
CelestialBodyPointed(Frame pCelestialFrame,
PVCoordinatesProvider pPointedBody,
Vector3D pPhasingCel,
Vector3D pPointingSat,
Vector3D pPhasingSat)
Creates new instance.
|
ConstantAttitudeLaw(Frame referenceFrameIn,
Rotation rotationIn)
Creates new instance.
|
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.
|
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,
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,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.
|
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 |
EarthToCelestialBodyCenterDirection.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) |
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 |
VelocityDirection.getLine(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
|
Line |
ToCelestialBodyCenterDirection.getLine(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
|
Line |
MomentumDirection.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 |
ConstantVectorDirection.getLine(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the line containing the given origin point and directed by the direction vector
|
Line |
NadirDirection.getLine(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame) |
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 |
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 |
IDirection.getLine(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the line containing the origin (given PV coordinates) and directed by the direction vector.
|
PVCoordinates |
EarthToCelestialBodyCenterDirection.getTargetPVCoordinates(AbsoluteDate date,
Frame frame)
Provides the target point at a given date in a given frame, represented by the
associated PVCoordinates object
|
PVCoordinates |
ToCelestialBodyCenterDirection.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 |
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 |
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 |
EarthToCelestialBodyCenterDirection.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) |
Vector3D |
CelestialBodyPolesAxisDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
VelocityDirection.getVector(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
ToCelestialBodyCenterDirection.getVector(PVCoordinatesProvider origin,
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 |
GenericTargetDirection.getVector(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
ConstantVectorDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
NadirDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame) |
Vector3D |
GlintApproximatePointingDirection.getVector(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
EarthCenterDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
CrossProductDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the cross product of direction1 vector and dirction2 vector.
|
Vector3D |
IDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
| Constructor and Description |
|---|
ConstantVectorDirection(Vector3D inVector,
Frame inFrame)
Build a direction from a frame and a vector constant in this frame
|
VelocityDirection(Frame referenceFrame)
Build a Direction defined for any PVCoordinatesProvider origin by its velocity vector with respect to a reference
frame.
|
| Modifier and Type | Field and Description |
|---|---|
protected Frame |
MeeusSun.MODEL.inertialSunFrame
Sun inertially oriented frame.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
OneAxisEllipsoid.getBodyFrame()
Get the body frame related to body shape.
|
Frame |
ExtendedOneAxisEllipsoid.getBodyFrame() |
Frame |
BodyShape.getBodyFrame()
Get body frame related to body shape.
|
Frame |
AbstractCelestialBody.getBodyOrientedFrame()
Get a body oriented, body centered frame.
|
Frame |
CelestialBody.getBodyOrientedFrame()
Get a body oriented, body centered frame.
|
Frame |
AbstractCelestialBody.getInertiallyOrientedFrame()
Get an inertially oriented, body centered frame.
|
Frame |
CelestialBody.getInertiallyOrientedFrame()
Get an inertially oriented, body centered frame.
|
| Modifier and Type | Method and Description |
|---|---|
double |
ExtendedOneAxisEllipsoid.distanceTo(Line line,
Frame frame,
AbsoluteDate date) |
double |
GeometricBodyShape.distanceTo(Line line,
Frame frame,
AbsoluteDate date)
Computes the distance to a line.
|
GeodeticPoint |
OneAxisEllipsoid.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Get the intersection point of a line with the surface of the body.
|
GeodeticPoint |
ExtendedOneAxisEllipsoid.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date) |
GeodeticPoint |
BodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Get the intersection point of a line with the surface of the body.
|
Vector3D[] |
ExtendedOneAxisEllipsoid.getIntersectionPoints(Line line,
Frame frame,
AbsoluteDate date) |
Vector3D[] |
GeometricBodyShape.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.
|
double |
ExtendedOneAxisEllipsoid.getLocalRadius(Vector3D position,
Frame frame,
AbsoluteDate date,
PVCoordinatesProvider occultedBody)
Calculate the apparent radius.
|
double |
GeometricBodyShape.getLocalRadius(Vector3D position,
Frame frame,
AbsoluteDate date,
PVCoordinatesProvider occultedBody)
Calculate the apparent radius.
|
PVCoordinates |
MeeusSun.getPVCoordinates(AbsoluteDate date,
Frame frame) |
PVCoordinates |
UserCelestialBody.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
PVCoordinates |
ExtendedOneAxisEllipsoid.getPVCoordinates(AbsoluteDate date,
Frame frame) |
PVCoordinates |
MeeusMoon.getPVCoordinates(AbsoluteDate date,
Frame frame) |
abstract PVCoordinates |
AbstractCelestialBody.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.
|
GeodeticPoint |
OneAxisEllipsoid.transform(Vector3D point,
Frame frame,
AbsoluteDate date)
Transform a cartesian point to a surface-relative point.
|
GeodeticPoint |
ExtendedOneAxisEllipsoid.transform(Vector3D point,
Frame frame,
AbsoluteDate date) |
GeodeticPoint |
BodyShape.transform(Vector3D point,
Frame frame,
AbsoluteDate date)
Transform a cartesian point to a surface-relative point.
|
GeodeticPoint |
OneAxisEllipsoid.transformAndComputeJacobian(Vector3D point,
Frame frame,
AbsoluteDate date,
double[][] jacobian)
Transform a cartesian point to a surface-relative point and compute the jacobian of
the transformation.
|
static void |
MeeusSun.updateTransform(AbsoluteDate date,
Frame frame)
Update cached transform from
FramesFactory.getMOD(boolean) to provided frame. |
| Constructor and Description |
|---|
AbstractCelestialBody(String nameIn,
double gmIn,
IAUPole iauPoleIn,
Frame definingFrameIn,
String inertialFrameName,
String bodyFrameName)
Build an instance and the underlying frame.
|
ExtendedOneAxisEllipsoid(double ae,
double f,
Frame bodyFrame,
String name)
Constructor for the body spheroid.
|
OneAxisEllipsoid(double aeIn,
double f,
Frame bodyFrameIn)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
EarthZoneDetector.getFrame()
Get the frame.
|
| Constructor and Description |
|---|
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.
|
| 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 |
DTM2000.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 |
MSISE2000.getData(AbsoluteDate date,
Vector3D position,
Frame frame)
Get detailed atmospheric data.
|
double |
SimpleExponentialAtmosphere.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
HarrisPriester.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 |
DTM2000.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
US76.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density for altitude in interval [0, 1E6] m
|
double |
MSISE2000.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
Atmosphere.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
US76.getPress(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local pressure for altitude in interval [0, 1E6] m
|
double |
MSISE2000.getPressure(AbsoluteDate date,
Vector3D position,
Frame frame)
Returns pressure.
|
double |
SimpleExponentialAtmosphere.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 |
JB2006.getSpeedOfSound(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local speed of sound.
|
double |
DTM2000.getSpeedOfSound(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local speed of sound.
|
double |
US76.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 |
Atmosphere.getSpeedOfSound(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local speed of sound.
|
double |
US76.getTemp(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local temperature for altitude in interval [0, 1E6] m
|
Vector3D |
SimpleExponentialAtmosphere.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the spacecraft velocity relative to the atmosphere.
|
Vector3D |
HarrisPriester.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the inertial velocity of atmosphere molecules.
|
Vector3D |
JB2006.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the inertial velocity of atmosphere molecules.
|
Vector3D |
DTM2000.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the inertial velocity of atmosphere molecules.
|
Vector3D |
US76.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 |
Atmosphere.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the spacecraft velocity relative to the atmosphere.
|
| 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 |
BalminoAttractionModel.getBodyFrame()
Get the central body frame
|
Frame |
CunninghamAttractionModel.getBodyFrame()
Get the central body frame
|
Frame |
DrozinerAttractionModel.getCentralBodyFrame()
Get the central body frame
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
ThirdBodyAttraction.computeAcceleration(PVCoordinates pv,
Frame frame,
AbsoluteDate date)
Method to compute the acceleration.
|
Vector3D |
NewtonianAttraction.computeAcceleration(PVCoordinates pv,
Frame frame,
AbsoluteDate date)
Method to compute the acceleration.
|
static Vector3D |
GravityToolbox.computeDrozinerAcceleration(PVCoordinates pv,
Frame frame,
double[][] coefficientsC,
double[][] coefficientsS,
double muc,
double eqRadius,
double threshold,
int degree,
int order)
Method to compute the acceleration, from Droziner algorithm (see
DrozinerAttractionModel). |
| Constructor and Description |
|---|
BalminoAttractionModel(Frame frame,
double ae,
double mu,
double[][] cCoefs,
double[][] sCoefs)
Create an instance of a normalized gravity computation model using normalized coefficients.
|
BalminoAttractionModel(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.
|
BalminoAttractionModel(Frame frame,
Parameter ae,
Parameter mu,
double[][] cCoefs,
double[][] sCoefs)
Create an instance of a normalized gravity computation model using normalized coefficients.
|
BalminoAttractionModel(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.
|
CunninghamAttractionModel(Frame centralBodyFrame,
double equatorialRadius,
double mu,
double[][] cIn,
double[][] sIn)
Creates a new instance.
|
CunninghamAttractionModel(Frame centralBodyFrame,
double equatorialRadius,
double mu,
double[][] cIn,
double[][] sIn,
int degreePD,
int orderPD)
Creates a new instance.
|
CunninghamAttractionModel(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
double[][] cIn,
double[][] sIn)
Creates a new instance using
Parameter. |
CunninghamAttractionModel(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
double[][] cIn,
double[][] sIn,
int degreePD,
int orderPD)
Creates a new instance using
Parameter. |
DrozinerAttractionModel(Frame centralBodyFrameIn,
double equatorialRadius,
double mu,
double[][] cCoefs,
double[][] sCoefs)
Creates a new instance.
|
DrozinerAttractionModel(Frame centralBodyFrameIn,
double equatorialRadius,
double mu,
double[][] cCoefs,
double[][] sCoefs,
boolean computePDPos,
boolean computePDVel)
Creates a new instance.
|
DrozinerAttractionModel(Frame centralBodyFrameIn,
Parameter equatorialRadius,
Parameter mu,
double[][] cCoefs,
double[][] sCoefs)
Creates a new instance using
Parameter. |
DrozinerAttractionModel(Frame centralBodyFrameIn,
Parameter equatorialRadius,
Parameter mu,
double[][] cCoefs,
double[][] sCoefs,
boolean computePDPos,
boolean computePDVel)
Creates a new instance using
Parameter. |
| 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. |
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<CelestialBody> bodies,
boolean thirdBodyAttDegree3,
boolean frequencyCorr,
boolean ellipticityCorr,
ITerrestrialTidesDataProvider terrestrialData)
Creates a new instance.
|
TerrestrialTides(Frame centralBodyFrame,
double equatorialRadius,
double mu,
List<CelestialBody> bodies,
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<CelestialBody> bodies,
boolean thirdBodyAttDegree3,
boolean frequencyCorr,
boolean ellipticityCorr,
ITerrestrialTidesDataProvider terrestrialData)
Creates a new instance using
Parameter. |
TerrestrialTides(Frame centralBodyFrame,
Parameter equatorialRadius,
Parameter mu,
List<CelestialBody> bodies,
boolean thirdBodyAttDegree3,
boolean frequencyCorr,
boolean ellipticityCorr,
ITerrestrialTidesDataProvider terrestrialData,
boolean computePD)
Creates a new instance using
Parameter. |
| Constructor and Description |
|---|
VariablePotentialAttractionModel(Frame centralBodyFrame,
VariablePotentialCoefficientsProvider provider,
int degree,
int order)
Variable gravity field force model constructor (static part only).
|
VariablePotentialAttractionModel(Frame centralBodyFrame,
VariablePotentialCoefficientsProvider provider,
int degree,
int order,
int degreePD,
int orderPD)
Variable gravity field force model constructor (static part only).
|
VariablePotentialAttractionModel(Frame centralBodyFrame,
VariablePotentialCoefficientsProvider provider,
int degree,
int order,
int degreeOptional,
int orderOptional,
boolean computeOptionalOnce)
Variable gravity field force model constructor.
|
VariablePotentialAttractionModel(Frame centralBodyFrame,
VariablePotentialCoefficientsProvider provider,
int degree,
int order,
int degreePD,
int orderPD,
int degreeOptional,
int orderOptional,
int degreeOptionalPD,
int orderOptionalPD,
boolean computeOptionalOnce)
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 |
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 |
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 |
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 |
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 |
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 |
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 |
RediffusedRadiationPressure.getInBodyFrame()
Getter for the boby frame used at construction.
|
| Modifier and Type | Method and Description |
|---|---|
static double |
SolarRadiationPressureEllipsoid.getLightningRatio(PVCoordinatesProvider sun,
Vector3D satSunVector,
GeometricBodyShape earthModel,
Vector3D position,
Frame frame,
AbsoluteDate date)
Get the lightning ratio ([0-1]).
|
double |
SolarRadiationPressureCircular.getLightningRatio(Vector3D position,
Frame frame,
AbsoluteDate date)
Get the lightning ratio ([0-1]).
|
| Constructor and Description |
|---|
RediffusedFlux(int nCorona,
int nMeridian,
Frame bodyFrame,
CelestialBody sunProvider,
PVCoordinatesProvider satProvider,
AbsoluteDate d,
IEmissivityModel model)
Default constructor of rediffused flux.
|
RediffusedFlux(int nCorona,
int nMeridian,
Frame bodyFrame,
CelestialBody sun,
PVCoordinatesProvider satProvider,
AbsoluteDate dDate,
IEmissivityModel model,
boolean inIr,
boolean inAlbedo)
Generic constructor of rediffused flux.
|
RediffusedRadiationPressure(CelestialBody inSun,
Frame inBodyFrame,
int inCorona,
int inMeridian,
IEmissivityModel inEmissivityModel,
RediffusedRadiationSensitive inModel)
Constructor.
|
RediffusedRadiationPressure(CelestialBody inSun,
Frame inBodyFrame,
int inCorona,
int inMeridian,
IEmissivityModel inEmissivityModel,
RediffusedRadiationSensitive inModel,
boolean computePD)
Constructor.
|
| 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 |
FactoryManagedFrame
Base class for the predefined frames that are managed by
FramesFactory. |
class |
H0MinusNFrame
"H0 - n" reference frame.
|
class |
LocalOrbitalFrame
Class for frames moving with an orbiting satellite.
|
class |
TopocentricFrame
Topocentric frame.
|
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.
|
static Frame |
FramesFactory.getFrame(Predefined 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.
|
static Frame |
FramesFactory.getGCRF()
Get the unique GCRF 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.
|
static Frame |
FramesFactory.getICRF()
Get the unique ICRF frame.
|
static Frame |
OrphanFrame.getNewOrphanFrame(String name)
This method creates an Orphan Frame.
|
Frame |
Frame.getParent()
Get the parent frame.
|
protected static Frame |
Frame.getRoot()
Get the unique root frame.
|
| Modifier and Type | Method and Description |
|---|---|
double |
TopocentricFrame.getAzimuth(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get the azimuth of a point with regards to the topocentric frame center point.
|
double |
TopocentricFrame.getAzimuthRate(PVCoordinates extPV,
Frame frame,
AbsoluteDate date)
Get the azimuth rate of a point.
|
double |
TopocentricFrame.getElevation(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get the elevation of a point with regards to the local point.
|
double |
TopocentricFrame.getElevationRate(PVCoordinates extPV,
Frame frame,
AbsoluteDate date)
Get the elevation rate of a point.
|
Frame |
Frame.getFrozenFrame(Frame reference,
AbsoluteDate freezingDate,
String frozenName)
Get a new version of the instance, frozen with respect to a reference frame.
|
PVCoordinates |
TopocentricFrame.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the topocentric frame origin in the selected frame. |
double |
TopocentricFrame.getRange(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get the range of a point with regards to the topocentric frame center point.
|
double |
TopocentricFrame.getRangeRate(PVCoordinates extPV,
Frame frame,
AbsoluteDate date)
Get 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)
Get the Cardan x angle of a point.
|
double |
TopocentricFrame.getXangleCardanRate(PVCoordinates extPV,
Frame frame,
AbsoluteDate date)
Get the Cardan x angle rate.
|
double |
TopocentricFrame.getYangleCardan(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get 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)
Get the Cardan y angle rate.
|
boolean |
Frame.isChildOf(Frame potentialAncestor)
Determine if a Frame is a child of another one.
|
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 |
|---|
FactoryManagedFrame(Frame parent,
TransformProvider transformProvider,
boolean pseudoInertial,
Predefined factoryKeyIn)
Simple 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.
|
LocalOrbitalFrame(Frame parent,
LOFType type,
PVCoordinatesProvider provider,
String name)
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.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinates |
RFStationAntenna.getPVCoordinates(AbsoluteDate date,
Frame 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 |
|---|---|
static AngularVelocitiesHarmonicProfile |
GuidanceProfileBuilder.computeAngularVelocitiesHarmonicProfile(AttitudeLawLeg attitude,
PVCoordinatesProvider provider,
Frame frame,
AbsoluteDate tref,
double period,
int order,
KinematicsToolkit.IntegrationType integType,
double integStep)
Compute the angular velocities harmonic guidance profile.
|
Attitude |
QuaternionPolynomialProfile.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AngularVelocitiesPolynomialProfile.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate userDate,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
QuaternionHarmonicProfile.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
Attitude |
AngularVelocitiesHarmonicProfile.getAttitude(PVCoordinatesProvider pvProv,
AbsoluteDate userDate,
Frame frame)
Compute the attitude corresponding to an orbital state.
|
| Constructor and Description |
|---|
AngularVelocitiesHarmonicProfile(AbsoluteDate origin,
Rotation initialRotation,
Frame frame,
FourierSeries xAngle,
FourierSeries yAngle,
FourierSeries zAngle,
AbsoluteDateInterval timeInterval,
KinematicsToolkit.IntegrationType integType,
double integStep)
Create a harmonic, angular velocities guidance profile.
|
AngularVelocitiesPolynomialProfile(Frame frame,
AbsoluteDateInterval timeInterval,
List<AngularVelocitiesPolynomialSegment> polynomials)
Create a polynomial, angular velocity guidance profile.
|
QuaternionHarmonicProfile(AbsoluteDate origin,
Frame frame,
FourierSeries q0,
FourierSeries q1,
FourierSeries q2,
FourierSeries q3,
AbsoluteDateInterval timeInterval)
Create a harmonic, quaternion guidance profile.
|
QuaternionPolynomialProfile(Frame frame,
AbsoluteDateInterval timeInterval,
List<QuaternionPolynomialSegment> polynomials)
Create a polynomial, quaternion guidance profile.
|
| 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.
|
| 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.
|
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 |
|---|
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()
Get the reference frame
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinates |
EphemerisPvLagrange.getPVCoordinates(AbsoluteDate date,
Frame frame)
Frame can be null : by default the frame of expression is the frame used at instantiation
(which is the frame of the first spacecraft state when instantiation is done from a table of spacecraft states).
|
PVCoordinates |
AlmanacPVCoordinates.getPVCoordinates(AbsoluteDate date,
Frame frame)
Geometric computation of the position to a date.
|
PVCoordinates |
PVCoordinatesProvider.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. |
| Constructor and Description |
|---|
AbstractBoundedPVProvider(PVCoordinates[] tabPV,
int order,
Frame frame,
AbsoluteDate[] tabDate,
ISearchIndex algo)
Instantiation of AbstractBoundedPVProvider attributes.
|
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
|
| Constructor and Description |
|---|
ProjectionEllipsoid(double ae,
double f,
Frame bodyFrame,
String name)
Constructor for the body ellipsoid.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
AnalyticalIntegratedEphemeris.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
Propagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
AbstractPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
Frame |
SpacecraftState.getFrame()
Get the inertial frame.
|
Frame |
MultiPropagator.getFrame(String satId)
Get the frame in which the orbit is propagated.
|
| 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.
|
PVCoordinates |
AbstractPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
PVCoordinates |
SpacecraftState.getPVCoordinates(Frame outputFrame)
Get the
PVCoordinates in given output frame. |
void |
Propagator.setOrbitFrame(Frame frame)
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 |
|---|
PVCoordinatePropagator(PVCoordinatesProvider pvCoordProvider,
AbsoluteDate initDate,
double mu,
Frame frame)
Creates an instance of PVCoordinatePropagator without attitude and additional state providers
|
PVCoordinatePropagator(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,
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 |
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)
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.
|
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 |
|---|---|
SymmetricMatrix |
OrbitCovariance.getCovarianceMatrix(Orbit refOrbit,
OrbitType outCovType,
Frame outFrame)
Covariance matrix getter.
|
| Constructor and Description |
|---|
OrbitCovariance(AbsoluteDate covDate,
Frame refFrame,
OrbitType coordType,
RealMatrix covMat)
Simple constructor
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
TLEPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
AOLDetector.getAOLFrame()
Get the reference frame.
|
Frame |
LongitudeDetector.getBodyFrame()
Returns central body frame.
|
Frame |
ExtremaLongitudeDetector.getBodyFrame()
Returns the body frame.
|
Frame |
ExtremaLatitudeDetector.getBodyFrame()
Returns the body frame.
|
Frame |
NodeDetector.getFrame()
Get the frame in which the equator is defined.
|
| Modifier and Type | Method and Description |
|---|---|
double |
VariableRadiusProvider.getLocalRadius(Vector3D position,
Frame frame,
AbsoluteDate date,
PVCoordinatesProvider occultedBodyIn)
Calculate the apparent radius.
|
double |
ConstantRadiusProvider.getLocalRadius(Vector3D position,
Frame frame,
AbsoluteDate date,
PVCoordinatesProvider occultedBodyIn)
Calculate the apparent radius.
|
double |
LocalRadiusProvider.getLocalRadius(Vector3D position,
Frame frame,
AbsoluteDate date,
PVCoordinatesProvider occultedBodyIn)
Calculate the apparent radius.
|
| 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.
|
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.
|
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.
|
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.
|
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.
|
| Constructor and Description |
|---|
AdaptedMonoEventDetector(EventDetector detector,
OrbitType orbitType,
PositionAngle angleType,
AttitudeProvider attProviderForces,
AttitudeProvider attProviderEvents,
AbsoluteDate referenceDate,
double mu,
Frame integrationFrame,
MultiStateVectorInfo stateVectorInfo,
String satId)
Build a wrapped event detector.
|
| Constructor and Description |
|---|
AdaptedMultiEventDetector(MultiEventDetector detector,
OrbitType orbitType,
PositionAngle angleType,
Map<String,AttitudeProvider> attProvidersForces,
Map<String,AttitudeProvider> 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 |
|---|---|
Frame |
NumericalPropagator.getFrame()
Get the frame in which the orbit is propagated.
|
| Modifier and Type | Method and Description |
|---|---|
void |
TimeDerivativesEquations.addAcceleration(Vector3D gamma,
Frame frame)
Add the contribution of an acceleration expressed in some inertial frame.
|
PVCoordinates |
NumericalPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
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.
|
void |
NumericalPropagator.setOrbitFrame(Frame frame)
Set propagation frame.
|
| Modifier and Type | Method and Description |
|---|---|
Frame |
MultiNumericalPropagator.getFrame(String satId) |
| 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. |
SpacecraftState |
MultiStateVectorInfo.mapArrayToState(double[] y,
AbsoluteDate currentDate,
OrbitType orbitType,
PositionAngle angleType,
AttitudeProvider attProviderForces,
AttitudeProvider attProviderEvents,
double mu,
Frame integrationFrame,
String satId)
Extract a given SpacecraftState from the state vector.
|
void |
MultiNumericalPropagator.setOrbitFrame(String satId,
Frame frame)
Set a frame for propagation The initial state must have first been added using the
MultiNumericalPropagator.addInitialState(SpacecraftState, String) method before defining the associated
integration frame. |
| Modifier and Type | Method and Description |
|---|---|
void |
MultiEphemerisModeHandler.initialize(OrbitType orbit,
PositionAngle angle,
Map<String,AttitudeProvider> attitudeProvidersForces,
Map<String,AttitudeProvider> attitudeProvidersEvents,
MultiStateVectorInfo stateVectorInfo,
boolean activateHandlers,
AbsoluteDate reference,
Map<String,Frame> frame,
Map<String,Double> mu)
Initialize the mode handler.
|
void |
MultiModeHandler.initialize(OrbitType orbit,
PositionAngle angle,
Map<String,AttitudeProvider> attitudeProvidersForces,
Map<String,AttitudeProvider> 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,AttitudeProvider> attProvidersForces,
Map<String,AttitudeProvider> attProvidersEvents,
Map<String,Double> mu,
Map<String,Frame> integrationFrame)
Convert state vector into a Map of SpacecraftState
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinates |
Ephemeris.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
PVCoordinates |
IntegratedEphemeris.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected 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.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinates |
MultiIntegratedEphemeris.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
| Constructor and Description |
|---|
MultiIntegratedEphemeris(List<AbsoluteDate> startDatesIn,
List<AbsoluteDate> minDatesIn,
List<AbsoluteDate> maxDatesIn,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
AttitudeProvider attitudeProviderForces,
AttitudeProvider attitudeProviderEvents,
MultiStateVectorInfo stateInfos,
List<ContinuousOutputModel> modelsIn,
Frame referenceFrameIn,
double muIn,
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,AttitudeProvider> attProvidersForces,
Map<String,AttitudeProvider> 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 |
|---|---|
Vector3D |
SignalPropagation.getVector(Frame expressionFrame) |
| Constructor and Description |
|---|
SignalPropagation(Vector3D propagationVector,
AbsoluteDate inEmissionDate,
AbsoluteDate inReceptionDate,
Frame refFrame,
SignalPropagationModel.FixedDate fixedDate)
Constructor with computation of one of the dates
|
SignalPropagationModel(Frame frame,
double threshold)
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(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(AbsoluteDate date,
Vector3D satellite,
Frame frameSat) |
| Constructor and Description |
|---|
BentModel(R12Provider r12Provider,
SolarActivityDataProvider solarActivity,
USKProvider uskProvider,
BodyShape earth,
Vector3D inStation,
Frame inFrameSta,
double freq)
Constructor for the Bent ionospheric correction model.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinates |
MeeusMoonStela.getPVCoordinates(AbsoluteDate date,
Frame frame) |
static void |
MeeusMoonStela.updateTransform(AbsoluteDate date,
Frame frame)
Update cached transform from
FramesFactory.getMOD(boolean) to provided frame. |
| Modifier and Type | Method and Description |
|---|---|
AtmosphereData |
MSIS00Adapter.getData(AbsoluteDate date,
Vector3D position,
Frame frame)
Get detailed atmospheric data.
|
double |
MSIS00Adapter.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
MSIS00Adapter.getPressure(AbsoluteDate date,
Vector3D position,
Frame frame)
Returns pressure.
|
double |
MSIS00Adapter.getSpeedOfSound(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local speed of sound.
|
Vector3D |
MSIS00Adapter.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame) |
| 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) |
| 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)
Get the
PVCoordinates of the body in the selected frame. |
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.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 |
|---|---|
Frame |
UserEphemeris.getReferenceFrame() |
Frame |
IUserEphemeris.getReferenceFrame() |
| Modifier and Type | Method and Description |
|---|---|
PVCoordinates |
UserCelestialBody.getPVCoordinates(AbsoluteDate date,
Frame frame)
Computes the PV coordinates at a date using linear interpolator.
|
PVCoordinates |
UserCelestialBody.getPVCoordinatesLagrange4(AbsoluteDate date,
Frame frame)
Computes the PV coordinates at a date using Lagrange 4 interpolator.
|
| Constructor and Description |
|---|
UserEphemeris(String ephemerisFile,
DateComponents referenceEpoch,
TimeScale timeScale,
Frame frame)
Constructor.
|
| Modifier and Type | Method and Description |
|---|---|
PVCoordinates |
BasicPVCoordinatesProvider.getPVCoordinates(AbsoluteDate date,
Frame inFrame)
Get the
PVCoordinates of the body in the selected frame. |
| Constructor and Description |
|---|
BasicPVCoordinatesProvider(PVCoordinates inCoordinates,
Frame inFrame)
Build a direction from an origin and a target described by their
PVCoordinatesProvider
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
DragWrench.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 |
MagneticWrench.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 |
WrenchModel.computeTorque(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
Wrench |
DragWrench.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 |
MagneticWrench.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 |
WrenchModel.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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