| Modifier and Type | Method and Description |
|---|---|
void |
AssemblyBuilder.addPart(String partName,
String parentPartName,
Vector3D translation,
Rotation rotation)
This method adds a new part to the currently built assembly.
|
void |
Vehicle.addSolarPanel(Vector3D normalPanel,
double areaPanel)
Add a solar panel to the vehicle.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
GlobalAeroModel.computeSC(SpacecraftState state,
Frame frame,
Vector3D relativeVelocity)
Compute the surface drag coefficient (drag coefficient x area)
|
Vector3D |
GlobalAeroModel.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Method to compute the aero acceleration, based on the assembly.
|
Vector3D |
DragLiftModel.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Method to compute the aero acceleration, based on the assembly.
|
Vector3D |
AeroModel.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Method to compute the aero acceleration, based on the assembly.
|
protected static Vector3D |
AeroModel.forceOnFacet(SpacecraftState state,
IPart part,
Assembly assembly,
double density,
Vector3D relativeVelocity)
Method to compute the force for a plane model.
|
protected static Vector3D |
DirectRadiativeModel.forceOnFacet(SpacecraftState state,
IPart part,
Vector3D flux)
Method to compute the force for a plane model.
|
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)
Method to compute the force for a spherical model.
|
Vector3D |
MagneticMomentProvider.getMagneticMoment(AbsoluteDate date)
Get the magnetic moment at given date, in the main frame of the spacecraft
|
Vector3D |
MagneticMoment.getMagneticMoment(AbsoluteDate date)
Get the magnetic moment at given date, in the main frame of the spacecraft
|
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.
|
Vector3D |
SensorModel.getNormalisedTargetVectorInSensorFrame(AbsoluteDate date)
Computes the target vector at a date in the sensor's frame.
|
Vector3D[] |
SensorModel.getReferenceAxis(Frame frame,
AbsoluteDate date)
Computes the reference axis of the sensor in a given frame at a date
|
Vector3D |
DragCoefficient.getScAbs()
Get the absorption part in satellite frame.
|
Vector3D |
DragCoefficient.getScDiffAr()
Get the diffuse part (rear) in satellite frame.
|
Vector3D |
DragCoefficient.getScDiffAv()
Get the diffuse part (front) in satellite frame.
|
Vector3D |
DragCoefficient.getScSpec()
Get the specular part in satellite frame.
|
Vector3D |
SensorModel.getSightAxis(Frame frame,
AbsoluteDate date)
Computes the sight axis of the sensor in a given frame at a date
|
Vector3D |
SensorModel.getTargetVectorInSensorFrame(AbsoluteDate targetDate)
Computes the target vector at a date in the sensor's frame.
|
Vector3D |
SensorModel.getTargetVectorInSensorFrame(AbsoluteDate targetDate,
AbsoluteDate sensorDate)
Computes the target vector in the sensor's frame.
|
Vector3D |
DirectRadiativeModel.radiationPressureAcceleration(SpacecraftState state,
Vector3D flux)
Method to compute the radiation pressure acceleration, based on the
assembly.
|
Vector3D |
RediffusedRadiativeModel.rediffusedRadiationPressureAcceleration(SpacecraftState state,
ElementaryFlux[] flux)
Method to compute the rediffused radiation pressure acceleration, based on the assembly.
|
| Modifier and Type | Method and Description |
|---|---|
void |
GlobalAeroModel.addDDragAccDParam(SpacecraftState s,
Parameter param,
double density,
Vector3D relativeVelocity,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters (the ballistic
coefficient).
|
void |
DragLiftModel.addDDragAccDParam(SpacecraftState s,
Parameter param,
double density,
Vector3D relativeVelocity,
double[] dAccdParam)
Compute acceleration derivatives with respect to ballistic coefficient.
|
void |
AeroModel.addDDragAccDParam(SpacecraftState s,
Parameter param,
double density,
Vector3D relativeVelocity,
double[] dAccdParam)
Compute acceleration derivatives with respect to ballistic coefficient.
|
void |
GlobalAeroModel.addDDragAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel,
double density,
Vector3D acceleration,
Vector3D relativeVelocity,
boolean computeGradientPosition,
boolean computeGradientVelocity)
Compute acceleration derivatives with respect to state parameters (position and velocity).
|
void |
DragLiftModel.addDDragAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel,
double density,
Vector3D acceleration,
Vector3D relativeVelocity,
boolean computeGradientPosition,
boolean computeGradientVelocity)
Compute acceleration derivatives with respect to state parameters (position and velocity).
|
void |
AeroModel.addDDragAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel,
double density,
Vector3D acceleration,
Vector3D relativeVelocity,
boolean computeGradientPosition,
boolean computeGradientVelocity)
Compute acceleration derivatives with respect to state parameters (position and velocity).
|
void |
DirectRadiativeModel.addDSRPAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam,
Vector3D satSunVector)
Compute acceleration derivatives with respect to additional parameters.
|
void |
DirectRadiativeModel.addDSRPAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel,
Vector3D satSunVector)
Compute acceleration derivatives with respect to state parameters.
|
Vector3D |
GlobalAeroModel.computeSC(SpacecraftState state,
Frame frame,
Vector3D relativeVelocity)
Compute the surface drag coefficient (drag coefficient x area)
|
Vector3D |
GlobalAeroModel.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Method to compute the aero acceleration, based on the assembly.
|
Vector3D |
DragLiftModel.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Method to compute the aero acceleration, based on the assembly.
|
Vector3D |
AeroModel.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Method to compute the aero acceleration, based on the assembly.
|
Wrench |
AeroWrenchModel.dragWrench(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Compute the torque due to radiation pressire.
|
Wrench |
AeroWrenchModel.dragWrench(SpacecraftState state,
double density,
Vector3D relativeVelocity,
Vector3D origin,
Frame frame)
Compute the torque due to radiation pressire.
|
protected static Vector3D |
AeroModel.forceOnFacet(SpacecraftState state,
IPart part,
Assembly assembly,
double density,
Vector3D relativeVelocity)
Method to compute the force for a plane model.
|
protected static Vector3D |
DirectRadiativeModel.forceOnFacet(SpacecraftState state,
IPart part,
Vector3D flux)
Method to compute the force for a plane model.
|
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)
Method to compute the force for a spherical model.
|
DragCoefficient |
DragCoefficientProvider.getCoefficients(Vector3D relativeVelocity,
AtmosphereData atmoData,
Assembly assembly)
Provides drag coefficient (x surface).
|
DragCoefficient |
GlobalDragCoefficientProvider.getCoefficients(Vector3D relativeVelocity,
AtmosphereData atmoData,
Assembly assembly) |
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 |
DirectRadiativeModel.radiationPressureAcceleration(SpacecraftState state,
Vector3D flux)
Method to compute the radiation pressure acceleration, based on the
assembly.
|
Wrench |
DirectRadiativeWrenchModel.radiationWrench(SpacecraftState state,
Vector3D flux)
Compute the torque due to radiation pressire.
|
Wrench |
DirectRadiativeWrenchModel.radiationWrench(SpacecraftState state,
Vector3D flux,
Vector3D origin,
Frame frame)
Compute the torque due to radiation pressire.
|
void |
InertiaSimpleModel.updateMassCenter(Vector3D massCenter)
Updates the mass center.
|
| Constructor and Description |
|---|
DragCoefficient(Vector3D scAbsIn,
Vector3D scSpecIn,
Vector3D scDiffAvIn,
Vector3D scDiffArIn)
Constructor.
|
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.
|
MagneticMoment(Vector3D moment)
Create a magnetic moment expressed in spacecraft main frame (incl.
|
| Modifier and Type | Method and Description |
|---|---|
double |
ConstantWallGasTemperature.getWallGasTemperature(SpacecraftState state,
Vector3D relativeVelocity,
double theta)
Compute wall gas temperature.
|
double |
CookWallGasTemperature.getWallGasTemperature(SpacecraftState state,
Vector3D relativeVelocity,
double theta)
Compute wall gas temperature.
|
double |
WallGasTemperatureProvider.getWallGasTemperature(SpacecraftState state,
Vector3D relativeVelocity,
double theta)
Compute wall gas temperature.
|
double |
GinsWallGasTemperature.getWallGasTemperature(SpacecraftState state,
Vector3D relativeVelocity,
double theta)
Compute wall gas temperature.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
RadiativeApplicationPoint.getApplicationPoint()
Get the application point in the part frame
|
Vector3D |
AeroApplicationPoint.getApplicationPoint()
Get the application point in the given frame at the given date.
|
Vector3D |
SensorProperty.getInSightAxis() |
Vector3D |
AbstractInertiaProperty.getMassCenter() |
Vector3D |
IInertiaProperty.getMassCenter() |
Vector3D[] |
SensorProperty.getReferenceAxis() |
| 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 |
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). |
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 |
CrossSectionProviderProperty.getCrossSection(Vector3D direction)
Computes the cross section of the geometry from a direction
defined by a Vector3D.
|
double |
AeroGlobalProperty.getCrossSection(Vector3D velocityPartFrame)
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). |
void |
AbstractInertiaProperty.setMassCenter(Vector3D massCenter)
Sets the mass center.
|
void |
SensorProperty.setReferenceAxis(Vector3D[] refAxis)
Sets the reference axis
|
| Constructor and Description |
|---|
AbstractInertiaProperty(Vector3D massCenter,
Matrix3D inertiaMatrix,
MassProperty mass)
Constructor for the abstract inertia property.
|
AbstractInertiaProperty(Vector3D massCenter,
Matrix3D inertiaMatrix,
Vector3D inertiaReferencePoint,
MassProperty mass)
Constructor for the abstract inertia property.
|
AeroApplicationPoint(Vector3D applicationPoint)
Create a drag force application point property.
|
AeroSphereProperty(double inSphereRadius,
double density,
Vector3D relativeVelocity)
Constructor of this property.
|
InertiaSimpleProperty(Vector3D massCenter,
Matrix3D inertiaMatrix,
MassProperty mass)
Constructor for the simple inertia property
|
InertiaSimpleProperty(Vector3D massCenter,
Matrix3D inertiaMatrix,
Vector3D inertiaReferencePoint,
MassProperty mass)
Constructor for the simple inertia property; the inertia matrix is expressed with respect to a point
that can be different from the mass center.
|
RadiativeApplicationPoint(Vector3D applicationPoint)
Create a radiative force application point property.
|
SensorProperty(Vector3D sightAxis)
Constructor of the generic sensor property
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
Facet.getNormal() |
| Modifier and Type | Method and Description |
|---|---|
double |
Facet.getCrossSection(Vector3D direction)
Computes the cross section from the direction
defined by a Vector3D.
|
| Constructor and Description |
|---|
Facet(Vector3D inNormal,
double inArea)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
double |
VehicleSurfaceModel.getCrossSection(Vector3D direction)
Computes the cross section from the direction
defined by a Vector3D.
|
| Modifier and Type | Method and Description |
|---|---|
default Vector3D |
AttitudeLeg.computeSpinByFD(PVCoordinatesProvider pvProv,
Frame frame,
AbsoluteDate date,
double computationStep)
Compute the rotation rate vector at a given date by finite differences (using 2nd order centered finite
differences).
|
default Vector3D |
AttitudeProvider.computeSpinByFD(PVCoordinatesProvider pvProv,
Frame frame,
AbsoluteDate date,
double computationStep)
Compute the rotation rate vector at a given date by finite differences (using 2nd order centered finite
differences).
|
default Vector3D |
AttitudeLeg.computeSpinDerivativeByFD(PVCoordinatesProvider pvProv,
Frame frame,
AbsoluteDate date,
double computationStep)
Compute the rotation acceleration vector at a given date by finite differences (using 2nd order centered finite
differences).
|
default Vector3D |
AttitudeProvider.computeSpinDerivativeByFD(PVCoordinatesProvider pvProv,
Frame frame,
AbsoluteDate date,
double computationStep)
Compute the rotation acceleration vector at a given date by finite differences (using 2nd order centered finite
differences).
|
Vector3D |
SpinStabilized.getAxis()
Getter for the rotation axis in satellite frame.
|
Vector3D |
TwoDirectionsAttitude.getFirstAxis()
Deprecated.
Getter for the satellite axis aligned with the first direction.
|
Vector3D |
TwoDirectionAttitudeLaw.getFirstAxis()
Getter for the satellite axis aligned with the first direction.
|
Vector3D |
YawSteering.getPhasingAxis()
Getter for the satellite axis that must be roughly in Sun direction.
|
Vector3D |
Attitude.getRotationAcceleration()
Get the satellite rotation acceleration.
|
Vector3D |
TwoDirectionsAttitude.getSecondAxis()
Deprecated.
Getter for the satellite axis aligned at best with the second direction.
|
Vector3D |
TwoDirectionAttitudeLaw.getSecondAxis()
Getter for the satellite axis aligned at best with the second direction.
|
Vector3D |
Attitude.getSpin()
Get the satellite spin.
|
Vector3D |
TabulatedSlew.getSpinDerivatives(AbsoluteDate date,
Frame frame)
Get spin derivatives.
|
protected Vector3D |
LofOffsetPointing.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
protected Vector3D |
NadirPointing.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
protected Vector3D |
TargetGroundPointing.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
protected Vector3D |
BodyCenterGroundPointing.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
protected abstract Vector3D |
AbstractGroundPointing.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
protected Vector3D |
AbstractGroundPointingWrapper.getTargetPoint(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point in specified frame.
|
| Constructor and Description |
|---|
AbstractGroundPointing(BodyShape shapeIn,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec)
Simple constructor.
|
AbstractGroundPointing(BodyShape shapeIn,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec,
double targetVelocityDeltaT)
Simple constructor.
|
AbstractGroundPointingWrapper(AbstractGroundPointing pGroundPointingLaw,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec)
Creates a new instance with specified los axis in satellite frame.
|
AbstractGroundPointingWrapper(AbstractGroundPointing pGroundPointingLaw,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec,
double targetVelocityDeltaT)
Creates a new instance with specified los axis in satellite frame.
|
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.
|
BodyCenterGroundPointing(BodyShape shape,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec)
Constructor.
|
BodyCenterGroundPointing(BodyShape shape,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec,
double targetVelocityDeltaT)
Constructor.
|
CelestialBodyPointed(Frame pCelestialFrame,
PVCoordinatesProvider pPointedBody,
Vector3D pPhasingCel,
Vector3D pPointingSat,
Vector3D pPhasingSat)
Creates new instance.
|
DirectionTrackingOrientation(IDirection direction,
Vector3D satelliteAxis,
Vector3D satelliteFixedAxis)
Constructor.
|
LofOffsetPointing(BodyShape shape,
AttitudeProvider attLaw,
Vector3D satPointingVectorIn)
Creates new instance.
|
LofOffsetPointing(BodyShape shape,
AttitudeProvider attLaw,
Vector3D satPointingVectorIn,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec)
Constructor.
|
NadirPointing(BodyShape shape,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec)
Constructor.
|
NadirPointing(BodyShape shape,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec,
double deltaT)
Constructor.
|
SpinStabilized(AttitudeLaw pNonRotatingLaw,
AbsoluteDate pStart,
Vector3D pAxis,
double pRate)
Creates a new instance.
|
SunPointing(CelestialBody body,
Vector3D firstAxis,
Vector3D secondAxis)
Constructor of the sun pointing attitude law.
|
SunPointing(CelestialBody body,
Vector3D firstAxis,
Vector3D secondAxis,
CelestialBody sun)
Constructor of the sun pointing attitude law.
|
SunPointing(Vector3D firstAxis,
Vector3D secondAxis)
Constructor of the sun pointing attitude law.
|
SunPointing(Vector3D firstAxis,
Vector3D secondAxis,
CelestialBody sun)
Constructor of the sun pointing attitude law.
|
TargetGroundPointing(BodyShape shape,
GeodeticPoint targetGeoIn,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec)
Creates a new instance from body shape and target expressed in geodetic coordinates with
specified los axis in satellite frame.
|
TargetGroundPointing(BodyShape shape,
GeodeticPoint targetGeoIn,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec,
double targetVelocityDeltaT)
Creates a new instance from body shape and target expressed in geodetic coordinates with
specified los axis in satellite frame.
|
TargetGroundPointing(BodyShape shape,
Vector3D targetIn)
Creates a new instance from body shape and target expressed in cartesian coordinates.
|
TargetGroundPointing(BodyShape shape,
Vector3D targetIn,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec)
Creates a new instance from body shape and target expressed in cartesian coordinates with
specified los axis in satellite frame.
|
TargetGroundPointing(BodyShape shape,
Vector3D targetIn,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec,
double targetVelocityDeltaT)
Creates a new instance from body shape and target expressed in cartesian coordinates with
specified los axis in satellite frame.
|
TargetPointing(Frame bodyFrameIn,
Vector3D targetIn)
Creates a new instance from body frame and target expressed in cartesian coordinates.
|
TwoDirectionAttitudeLaw(IDirection firstDirection,
IDirection secondDirection,
Vector3D firstAxis,
Vector3D secondAxis)
Constructor with default step values for spin and spin derivatives computation using finite
differences (0.2s for spin, 0.001s for spin derivative).
|
TwoDirectionAttitudeLaw(IDirection firstDirection,
IDirection secondDirection,
Vector3D firstAxis,
Vector3D secondAxis,
double dtSpin,
double dtAcc)
Constructor.
|
TwoDirectionsAttitude(IDirection firstDirection,
IDirection secondDirection,
Vector3D firstAxis,
Vector3D secondAxis)
Deprecated.
Constructor with default step values for spin and spin derivatives computation using finite differences
(0.2s for spin, 0.001s for spin derivative).
|
TwoDirectionsAttitude(IDirection firstDirection,
IDirection secondDirection,
Vector3D firstAxis,
Vector3D secondAxis,
double dtSpin,
double dtAcc)
Deprecated.
Constructor.
|
YawCompensation(AbstractGroundPointing groundPointingLaw,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec)
Creates a new instance with specified los axis in satellite frame.
|
YawSteering(AbstractGroundPointing groundPointingLaw,
PVCoordinatesProvider sunIn,
Vector3D phasingAxisIn)
Creates a new instance.
|
YawSteering(AbstractGroundPointing groundPointingLaw,
PVCoordinatesProvider sunIn,
Vector3D phasingAxisIn,
Vector3D losInSatFrameVec,
Vector3D losNormalInSatFrameVec)
Constructor.
|
| Modifier and Type | Method and Description |
|---|---|
static Vector3D |
StellarAberrationCorrection.applyInverseTo(PVCoordinatesProvider transmitter,
Vector3D transmitterToTargetDir,
Frame frame,
AbsoluteDate date)
Return the direction in which the signal should be emitted to reach the Target due to stellar aberration.
Warning: The Observer transmits the signal to the target. |
static Vector3D |
StellarAberrationCorrection.applyTo(PVCoordinatesProvider observer,
Vector3D observerToTargetDir,
Frame frame,
AbsoluteDate date)
Return the Target apparent direction from Observer position due to stellar aberration.
The Observer receives the signal emitted by the Target. |
protected Vector3D |
GlintApproximatePointingDirection.getGlintPosition(Vector3D satPos,
Vector3D sunPos,
AbsoluteDate date)
Compute Glint position.
|
Vector3D |
GlintApproximatePointingDirection.getGlintVectorPosition(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Get the position vector of the glint point
|
Vector3D |
MomentumDirection.getVector(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
EarthCenterDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
VelocityDirection.getVector(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
ConstantVectorDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
ToCelestialBodyCenterDirection.getVector(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
NorthNormalToEclipticDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
NadirDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
GlintApproximatePointingDirection.getVector(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
EarthToCelestialBodyCenterDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
IDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
GroundVelocityDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
GenericTargetDirection.getVector(PVCoordinatesProvider origin,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
CrossProductDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the cross product of direction1 vector and dirction2 vector.
|
Vector3D |
CelestialBodyPolesAxisDirection.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Provides the direction vector at a given date in a given frame.
|
Vector3D |
EarthCenterDirection.getVector(PVCoordinatesProvider origin,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon)
Provides the direction vector (from origin to target) at entered date, taking into account the type of date
(emission or reception), corrected for light-time and stellar aberration pending the entered correction
parameter.
|
Vector3D |
ToCelestialBodyCenterDirection.getVector(PVCoordinatesProvider origin,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon)
Provides the direction vector (from origin to target) at entered date, taking into account the type of date
(emission or reception), corrected for light-time and stellar aberration pending the entered correction
parameter.
|
Vector3D |
EarthToCelestialBodyCenterDirection.getVector(PVCoordinatesProvider origin,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon)
Provides the direction vector (from origin to target) at entered date, taking into account the type of date
(emission or reception), corrected for light-time and stellar aberration pending the entered correction
parameter.
|
Vector3D |
GenericTargetDirection.getVector(PVCoordinatesProvider origin,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon)
Provides the direction vector (from origin to target) at entered date, taking into account the type of date
(emission or reception), corrected for light-time and stellar aberration pending the entered correction
parameter.
|
Vector3D |
ITargetDirection.getVector(PVCoordinatesProvider origin,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon)
Provides the direction vector (from origin to target) at entered date, taking into account the type of date
(emission or reception), corrected for light-time and stellar aberration pending the entered correction
parameter.
|
default Vector3D |
ITargetDirection.getVector(PVCoordinatesProvider origin,
PVCoordinatesProvider target,
ITargetDirection.SignalDirection signalDirection,
ITargetDirection.AberrationCorrection correction,
AbsoluteDate date,
VacuumSignalPropagationModel.FixedDate fixedDateType,
Frame frame,
double epsilon,
Frame referenceFrame)
Provides the direction vector (from origin to target) at entered date, taking into account the type of date
(emission or reception), corrected for light-time and stellar aberration pending the entered correction
parameter.
|
| Modifier and Type | Method and Description |
|---|---|
static Vector3D |
StellarAberrationCorrection.applyInverseTo(PVCoordinatesProvider transmitter,
Vector3D transmitterToTargetDir,
Frame frame,
AbsoluteDate date)
Return the direction in which the signal should be emitted to reach the Target due to stellar aberration.
Warning: The Observer transmits the signal to the target. |
static Vector3D |
StellarAberrationCorrection.applyTo(PVCoordinatesProvider observer,
Vector3D observerToTargetDir,
Frame frame,
AbsoluteDate date)
Return the Target apparent direction from Observer position due to stellar aberration.
The Observer receives the signal emitted by the Target. |
protected Vector3D |
GlintApproximatePointingDirection.getGlintPosition(Vector3D satPos,
Vector3D sunPos,
AbsoluteDate date)
Compute Glint position.
|
| Constructor and Description |
|---|
ConstantVectorDirection(Vector3D inVector,
Frame inFrame)
Build a direction from a frame and a vector constant in this frame
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
AbstractOrientationFunction.estimateRate(AbsoluteDate date,
double dt,
AbsoluteDateInterval interval)
Estimate the spin at a given date from the current
OrientationFunction using the
AngularCoordinates.estimateRate(Rotation, Rotation, double) method. |
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
OrientationAngleTransform.getAxis()
Returns the axis of the transform in the frame defined by the reference transform.
|
| Constructor and Description |
|---|
OrientationAngleTransform(Transform reference,
Vector3D axis,
OrientationAngleProvider orientationAngleProvider)
Constructor.
|
| Modifier and Type | Method and Description |
|---|---|
default Vector3D[] |
BodyShape.closestPointTo(Line line)
This method computes the two points, on the line and on the body, that are the closest to each other.
|
Vector3D[] |
OneAxisEllipsoid.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.
|
Vector3D[] |
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.
|
Vector3D |
GeodeticPoint.getEast()
Get the direction to the east of point, expressed in parent shape frame.
|
Vector3D[] |
OneAxisEllipsoid.getIntersectionPoints(Line line,
Frame frame,
AbsoluteDate date)
Compute the intersection points with a line.
|
Vector3D[] |
BodyShape.getIntersectionPoints(Line line,
Frame frame,
AbsoluteDate date)
Compute the intersection points with a line.
|
Vector3D |
GeodeticPoint.getNadir()
Get the direction below the point, expressed in parent shape frame.
|
Vector3D |
OneAxisEllipsoid.getNormal(Vector3D point)
Return the normal vector to the surface from the ellipsoid
|
Vector3D |
EllipsoidBodyShape.getNormal(Vector3D point)
Return the normal vector to the surface from the ellipsoid
|
Vector3D |
GeodeticPoint.getNorth()
Get the direction to the north of point, expressed in parent shape frame.
|
Vector3D |
IAUPole.getPole(AbsoluteDate date)
Get the body North pole direction with respect to a reference frame.
|
Vector3D |
UserIAUPole.getPole(AbsoluteDate date)
Get the body North pole direction with respect to a reference frame.
|
Vector3D |
IAUPole.getPole(AbsoluteDate date,
IAUPoleModelType iauPoleType)
Get the body North pole direction with respect to a reference frame.
|
Vector3D |
UserIAUPole.getPole(AbsoluteDate date,
IAUPoleModelType iauPoleType)
Get the body North pole direction with respect to a reference frame.
|
Vector3D |
IAUPole.getPoleDerivative(AbsoluteDate date)
Get the body North pole direction derivative with respect to a reference frame.
|
Vector3D |
UserIAUPole.getPoleDerivative(AbsoluteDate date)
Get the body North pole direction derivative with respect to a reference frame.
|
Vector3D |
IAUPole.getPoleDerivative(AbsoluteDate date,
IAUPoleModelType iauPoleType)
Get the body North pole direction derivative with respect to a reference frame.
|
Vector3D |
UserIAUPole.getPoleDerivative(AbsoluteDate date,
IAUPoleModelType iauPoleType)
Get the body North pole direction derivative with respect to a reference frame.
|
Vector3D |
GeodeticPoint.getSouth()
Get the direction to the south of point, expressed in parent shape frame.
|
Vector3D |
BasicBoardSun.getVector(PVCoordinatesProvider pvCoord,
AbsoluteDate date,
Frame frame)
Get the direction of the sun.
|
Vector3D |
GeodeticPoint.getWest()
Get the direction to the west of point, expressed in parent shape frame.
|
Vector3D |
GeodeticPoint.getZenith()
Get the direction above the point, expressed in parent shape frame.
|
Vector3D |
OneAxisEllipsoid.transform(GeodeticPoint point)
Transform a surface-relative point to a cartesian point.
|
Vector3D |
BodyShape.transform(GeodeticPoint point)
Transform a surface-relative point to a cartesian point.
|
Vector3D |
OneAxisEllipsoid.transformAndComputeJacobian(GeodeticPoint geodeticPoint,
double[][] jacobian)
Transform a surface-relative point to a cartesian point and compute the jacobian of
the transformation.
|
| Modifier and Type | Method and Description |
|---|---|
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 |
BodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Get the intersection point of a line with the surface of the body.
|
GeodeticPoint |
OneAxisEllipsoid.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date,
double altitude)
Get the intersection point of a line with the surface of the body for a given altitude.
|
GeodeticPoint |
BodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date,
double altitude)
Get the intersection point of a line with the surface of the body for a given altitude.
|
Vector3D |
OneAxisEllipsoid.getNormal(Vector3D point)
Return the normal vector to the surface from the ellipsoid
|
Vector3D |
EllipsoidBodyShape.getNormal(Vector3D point)
Return the normal vector to the surface from the ellipsoid
|
GeodeticPoint |
OneAxisEllipsoid.transform(Vector3D point,
Frame frame,
AbsoluteDate date)
Transform a cartesian point to a surface-relative point.
|
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.
|
GeodeticPoint |
OneAxisEllipsoid.transformFromZenith(Vector3D point,
Vector3D zenith,
Frame frame,
AbsoluteDate date)
Computes a geodetic point from a normal vector by using spherical coordinates.
|
GeodeticPoint |
BodyShape.transformFromZenith(Vector3D point,
Vector3D zenith,
Frame frame,
AbsoluteDate date)
Computes a geodetic point from a normal vector by using spherical coordinates.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D[] |
Triangle.closestPointTo(Line line)
Computes the points of the triangle and the line realizing the shortest distance.
|
Vector3D[] |
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.
|
Vector3D |
Triangle.getCenter()
Returns the triangle barycenter.
|
Vector3D |
Triangle.getIntersection(Line line)
Returns intersection point with triangle, null if there is no intersection or if line is included in triangle.
|
Vector3D[] |
FacetBodyShape.getIntersectionPoints(Line line,
Frame frame,
AbsoluteDate date)
Compute the intersection points with a line.
|
Vector3D |
Triangle.getNormal()
Returns the normal to the triangle.
|
Vector3D |
Intersection.getPoint()
Returns the intersection point in input frame.
|
Vector3D |
Vertex.getPosition()
Returns the vertex 3D position.
|
Vector3D |
FacetBodyShape.transform(GeodeticPoint point)
Transform a surface-relative point to a cartesian point.
|
| Modifier and Type | Method and Description |
|---|---|
static double |
Triangle.dotProduct(Vector3D v1,
Vector3D v2)
Fast dot product of two 3D vectors.
|
FieldData |
FacetBodyShape.getFieldData(SpacecraftState state,
IFieldOfView fieldOfView,
Vector3D lineOfSight)
Returns the field data as
FieldData for each state in provided list. |
Intersection |
FacetBodyShape.getIntersection(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Get the intersection point of a line with the surface of the body.
|
GeodeticPoint |
FacetBodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date)
Get the intersection point of a line with the surface of the body.
|
GeodeticPoint |
FacetBodyShape.getIntersectionPoint(Line line,
Vector3D close,
Frame frame,
AbsoluteDate date,
double altitude)
Get the intersection point of a line with the surface of the body for a given altitude.
|
double |
FacetBodyShape.getLocalAltitude(Vector3D direction)
Returns the altitude of body given provided direction in body frame.
|
List<Triangle> |
FacetBodyShape.getNeighbors(Vector3D pos,
double maxDistance)
Returns the neighbors of provided cartesian point whose center is closer than provided
distance.
|
List<Triangle> |
FacetBodyShape.getNeighbors(Vector3D pos,
int order)
Returns the neighbor triangles of provided cartesian point which are closer or equal to
provided
order of "neighborhood".
|
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.
|
boolean |
FacetBodyShape.isMasked(Triangle triangle,
Vector3D pos)
Returns true if the triangle is masked by another triangle as seen from the provided
position.
|
boolean |
FacetBodyShape.isVisible(Triangle triangle,
Vector3D pos,
IFieldOfView fieldOfView,
Transform t)
Returns true if the triangle is visible from the field of view, i.e.:
Is oriented toward the field of view
All points of the triangle are in the field of view
Triangle not masked by another facet
|
boolean |
Triangle.isVisible(Vector3D position)
Returns true if the triangle is visible from the provided position (culling test).
|
boolean |
Triangle.pointInTriangle(Vector3D point)
Check if the projection on triangle's plane of a point of space belongs to the triangle.
|
GeodeticPoint |
FacetBodyShape.transform(Vector3D point,
Frame frame,
AbsoluteDate date)
Transform a cartesian point to a surface-relative point.
|
GeodeticPoint |
FacetBodyShape.transformFromZenith(Vector3D point,
Vector3D zenith,
Frame frame,
AbsoluteDate date)
Computes a geodetic point from a normal vector by using spherical coordinates.
|
| Constructor and Description |
|---|
Intersection(Triangle triangle,
Vector3D point)
Constructor.
|
Vertex(int id,
Vector3D position)
Constructor.
|
| Constructor and Description |
|---|
CentralBodyMaskCircularFOVDetector(PVCoordinatesProvider occultedBody,
double occultedBodyRadius,
BodyShape occultingBody,
boolean totalEclipseFlag,
Vector3D center,
double halfAperture)
Constructor with default maxcheck and default threshold, creating a circularFOVDetector and
an EllipsoidEclipseDetector
|
CentralBodyMaskCircularFOVDetector(PVCoordinatesProvider occultedBody,
double occultedBodyRadius,
BodyShape occultingBody,
boolean totalEclipseFlag,
Vector3D center,
double halfAperture,
double maxCheck,
double threshold)
Constructor with user maxcheck and threshold creating a circularFOVDetector and an
EllipsoidEclipseDetector
|
CentralBodyMaskCircularFOVDetector(PVCoordinatesProvider occultedBody,
double occultedBodyRadius,
BodyShape occultingBody,
boolean totalEclipseFlag,
Vector3D center,
double halfAperture,
double maxCheck,
double threshold,
EventDetector.Action action)
Constructor with user maxcheck and threshold creating a circularFOVDetector and an
EllipsoidEclipseDetector
|
CentralBodyMaskCircularFOVDetector(PVCoordinatesProvider occultedBody,
double occultedBodyRadius,
BodyShape occultingBody,
boolean totalEclipseFlag,
Vector3D center,
double halfAperture,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Constructor with user maxcheck and threshold creating a circularFOVDetector and an
EllipsoidEclipseDetector
|
| Modifier and Type | Method and Description |
|---|---|
protected Vector3D |
AbstractDetectorWithTropoCorrection.getCorrectedVector(SpacecraftState s)
Compute the apparent vector from the station to the spacecraft with tropospheric effects.
|
Vector3D |
ExtremaSightAxisDetector.getSightAxis()
Get the sight axis
|
| Constructor and Description |
|---|
ExtremaSightAxisDetector(int extremumType,
PVCoordinatesProvider target,
Vector3D sightAxisDirection)
Constructor to use without assembly.
|
ExtremaSightAxisDetector(int extremumType,
PVCoordinatesProvider target,
Vector3D sightAxisDirection,
double maxCheck,
double threshold)
Constructor to use without assembly.
|
ExtremaSightAxisDetector(int extremumType,
PVCoordinatesProvider target,
Vector3D sightAxisDirection,
double maxCheck,
double threshold,
EventDetector.Action action)
Constructor to use without assembly.
|
ExtremaSightAxisDetector(int extremumType,
PVCoordinatesProvider target,
Vector3D sightAxisDirection,
double maxCheck,
double threshold,
EventDetector.Action action,
boolean remove)
Constructor to use without assembly.
|
ExtremaSightAxisDetector(PVCoordinatesProvider target,
Vector3D sightAxisDirection,
double maxCheck,
double threshold,
EventDetector.Action actionMin,
EventDetector.Action actionMax)
Constructor to use without assembly for both minimal and maximal angle detection.
|
ExtremaSightAxisDetector(PVCoordinatesProvider target,
Vector3D sightAxisDirection,
double maxCheck,
double threshold,
EventDetector.Action actionMin,
EventDetector.Action actionMax,
boolean removeMin,
boolean removeMax)
Constructor to use without assembly for both minimal and maximal angle detection.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D[] |
RectangleField.getSideAxis()
Get the 4 side axis of the field of view.
|
Vector3D[] |
PyramidalField.getSideAxis()
Get the side axis of the field of view.
|
Vector3D |
RectangleField.getU()
Get the U axis
|
Vector3D |
RectangleField.getV()
Get the V axis
|
Vector3D |
RectangleField.getW()
Get the W axis.
|
| Modifier and Type | Method and Description |
|---|---|
double |
FieldAngularFace.computeMinAngle(Vector3D direction)
Computes the minimal angle between this and a given direction.
|
double |
IFieldOfView.getAngularDistance(Vector3D direction)
Computes the angular distance between a vector and the border of the field.
|
double |
CircularField.getAngularDistance(Vector3D direction)
Computes the angular distance between a vector and the border of the field.
|
double |
OmnidirectionalField.getAngularDistance(Vector3D direction)
this method has no sense in the case of an omnidirectional field.
|
double |
AzimuthElevationField.getAngularDistance(Vector3D point)
Computes the angular distance between a vector and the border of the field.
|
double |
RectangleField.getAngularDistance(Vector3D direction)
Computes the angular distance between a vector and the border of the field.
|
double |
EllipticField.getAngularDistance(Vector3D direction)
Computes the angular distance between a vector and the border of the field.
|
double |
InvertField.getAngularDistance(Vector3D direction)
Computes the angular distance between a vector and the border of the field.
|
double |
BooleanField.getAngularDistance(Vector3D direction)
Computes the angular distance between a vector and the border of the field.
|
double |
PyramidalField.getAngularDistance(Vector3D direction)
Computes the angular distance between a vector and the border of the field.
|
double |
SectorField.getAngularDistance(Vector3D direction)
Computes the angular distance between a vector and the border of the field.
|
boolean |
IFieldOfView.isInTheField(Vector3D direction) |
boolean |
CircularField.isInTheField(Vector3D direction) |
boolean |
OmnidirectionalField.isInTheField(Vector3D direction)
Any vector being in the field, this method always return true
|
boolean |
AzimuthElevationField.isInTheField(Vector3D point) |
boolean |
RectangleField.isInTheField(Vector3D direction) |
boolean |
EllipticField.isInTheField(Vector3D direction) |
boolean |
InvertField.isInTheField(Vector3D direction) |
boolean |
BooleanField.isInTheField(Vector3D direction) |
boolean |
PyramidalField.isInTheField(Vector3D direction) |
boolean |
SectorField.isInTheField(Vector3D direction) |
| Constructor and Description |
|---|
CircularField(String name,
double halfAngularAperture,
Vector3D mainDirection)
Constructor for a circular field of view.
|
EllipticField(String name,
Vector3D origin,
Vector3D mainDirection,
Vector3D majorSemiAxisDirection,
double angleA,
double angleB)
Constructor for an elliptic field of view.
|
FieldAngularFace(Vector3D firstVector,
Vector3D secondVector)
Constructor.
|
PyramidalField(String name,
Vector3D[] directions)
Constructor for a pyramidal field of view.
|
PyramidalField(String name,
Vector3D[] directions,
boolean checkIntersectingFaces)
Constructor for a pyramidal field of view.
|
PyramidalField(String name,
Vector3D[] directions,
PolyhedronsSet polyhedronIn)
Constructor for a pyramidal field of view.
|
PyramidalField(String name,
Vector3D[] directions,
PolyhedronsSet polyhedronIn,
boolean checkIntersectingFaces)
Protected constructor for a pyramidal field of view.
|
RectangleField(String name,
Vector3D mainDirection,
Vector3D approximativeU,
double angularApertureU,
double angularApertureV)
Constructor for a field of view defined by a rectangle cone.
|
SectorField(String name,
Vector3D vectorPole,
Vector3D vectorV1,
Vector3D vectorV2)
Constructor for the "sector" field of view.
|
| Constructor and Description |
|---|
SatelliteTimeCoordinate(AbsoluteDate time,
Vector3D pos,
double clock)
Creates a new
SatelliteTimeCoordinate object with a given epoch
and position coordinate. |
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
EmpiricalForce.computeAcceleration(PVCoordinates pv,
LocalOrbitalFrame localFrameValidation,
Vector3D vectorS,
Frame frame,
SpacecraftState state)
Method to compute the acceleration.
|
Vector3D |
EmpiricalForce.computeAcceleration(SpacecraftState state)
Compute the acceleration due to the force.
|
Vector3D |
ForceModel.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
Vector3D |
EmpiricalForce.getVectorS() |
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
EmpiricalForce.computeAcceleration(PVCoordinates pv,
LocalOrbitalFrame localFrameValidation,
Vector3D vectorS,
Frame frame,
SpacecraftState state)
Method to compute the acceleration.
|
double[] |
EmpiricalForce.computeCosSin(PVCoordinates pv,
Vector3D vectorS)
Private method to compute the cos(nwt) and sin(nwt) values.
|
| 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,
IParamDiffFunction ax,
IParamDiffFunction ay,
IParamDiffFunction az,
IParamDiffFunction bx,
IParamDiffFunction by,
IParamDiffFunction bz,
IParamDiffFunction cx,
IParamDiffFunction cy,
IParamDiffFunction cz,
LOFType coeffsFrameLOFType)
Simple constructor for an empiric force using parameterizable functions for A; B and C coef
with a given LOF 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,
Parameter ax,
Parameter ay,
Parameter az,
Parameter bx,
Parameter by,
Parameter bz,
Parameter cx,
Parameter cy,
Parameter cz,
LOFType coeffsFrameLOFType)
Simple constructor for an empiric force using
Parameter for A; B and C coef
with a given LOF 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.
|
EmpiricalForce(int harmonicFactor,
Vector3D vectorS,
Vector3D a,
Vector3D b,
Vector3D c,
LOFType coeffsFrameLOFType)
Simple constructor for an empiric force.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
HarrisPriester.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 |
Atmosphere.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 |
AbstractDTM.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 |
SimpleExponentialAtmosphere.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the spacecraft velocity relative to the atmosphere.
|
| Modifier and Type | Method and Description |
|---|---|
AtmosphereData |
MSISE2000.getData(AbsoluteDate date,
Vector3D position,
Frame frame)
Get detailed atmospheric data.
|
AtmosphereData |
AbstractDTM.getData(AbsoluteDate date,
Vector3D position,
Frame frame)
Get detailed atmospheric data.
|
AtmosphereData |
ExtendedAtmosphere.getData(AbsoluteDate date,
Vector3D position,
Frame frame)
Get detailed atmospheric data.
|
double |
HarrisPriester.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 |
Atmosphere.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 |
AbstractDTM.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 |
SimpleExponentialAtmosphere.getDensity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the local density.
|
double |
HarrisPriester.getDensity(double sunRAsc,
double sunDecl,
Vector3D satPos,
double satAlt)
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 |
HarrisPriester.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 |
Atmosphere.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 |
AbstractDTM.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 |
SimpleExponentialAtmosphere.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 |
HarrisPriester.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 |
Atmosphere.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 |
AbstractDTM.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 |
SimpleExponentialAtmosphere.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.
|
Vector3D |
DragForce.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
Vector3D |
DragSensitive.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Compute the acceleration due to drag and the lift.
|
| Modifier and Type | Method and Description |
|---|---|
void |
DragSensitive.addDDragAccDParam(SpacecraftState s,
Parameter param,
double density,
Vector3D relativeVelocity,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters (the ballistic
coefficient).
|
void |
DragSensitive.addDDragAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel,
double density,
Vector3D acceleration,
Vector3D relativeVelocity,
boolean computeGradientPosition,
boolean computeGradientVelocity)
Compute acceleration derivatives with respect to state parameters (position and velocity).
|
Vector3D |
DragSensitive.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Compute the acceleration due to drag and the lift.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
AbstractBodyAttraction.computeAcceleration(SpacecraftState state)
Compute the acceleration due to the force.
|
Vector3D |
DirectBodyAttraction.computeAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute the acceleration due to the force.
|
Vector3D |
ThirdBodyAttraction.computeAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute the acceleration due to the force.
|
Vector3D |
GravityModel.computeAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute the acceleration due to the gravitational attraction, accounting for both central and non-central terms.
|
abstract Vector3D |
AbstractBodyAttraction.computeAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute the acceleration due to the force.
|
Vector3D |
AbstractHarmonicGravityModel.computeAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute the acceleration due to the gravitational attraction, accounting for both central and non-central terms.
|
static Vector3D |
GravityToolbox.computeBalminoAcceleration(PVCoordinates pv,
double[][] coefficientsC,
double[][] coefficientsS,
double muc,
double eqRadius,
int degree,
int order,
HelmholtzPolynomial helm)
Method to compute the acceleration, from Balmino algorithm (see
BalminoGravityModel). |
Vector3D |
ThirdBodyAttraction.computeCentralAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date)
Method to compute the acceleration.
|
protected Vector3D |
AbstractHarmonicGravityModel.computeCentralTermAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date,
Transform bodyFrameToPositionFrame)
Compute the acceleration due to the central term of the gravitational attraction.
|
static Vector3D |
GravityToolbox.computeCunninghamAcceleration(PVCoordinates pv,
double equatorialRadius,
double[][] coefC,
double[][] coefS,
int degree,
int order,
double mu)
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
DrozinerGravityModel). |
Vector3D |
DrozinerGravityModel.computeNonCentralTermsAcceleration(Vector3D pos,
AbsoluteDate date,
Transform bodyFrameToPositionFrame)
Compute the acceleration due to the non-central terms of the gravitational attraction.
|
Vector3D |
BalminoGravityModel.computeNonCentralTermsAcceleration(Vector3D pos,
AbsoluteDate date,
Transform bodyFrameToPositionFrame)
Compute the acceleration due to the non-central terms of the gravitational attraction.
|
protected abstract Vector3D |
AbstractHarmonicGravityModel.computeNonCentralTermsAcceleration(Vector3D pos,
AbsoluteDate date,
Transform bodyFrameToPositionFrame)
Compute the acceleration due to the non-central terms of the gravitational attraction.
|
Vector3D |
NewtonianGravityModel.computeNonCentralTermsAcceleration(Vector3D pos,
AbsoluteDate date,
Transform bodyFrameToPositionFrame)
Compute the acceleration due to the non-central terms of the gravitational attraction.
|
Vector3D |
CunninghamGravityModel.computeNonCentralTermsAcceleration(Vector3D pos,
AbsoluteDate date,
Transform bodyFrameToPositionFrame)
Compute the acceleration due to the non-central terms of the gravitational attraction.
|
| 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.
|
Vector3D |
DirectBodyAttraction.computeAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute the acceleration due to the force.
|
Vector3D |
ThirdBodyAttraction.computeAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute the acceleration due to the force.
|
Vector3D |
GravityModel.computeAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute the acceleration due to the gravitational attraction, accounting for both central and non-central terms.
|
abstract Vector3D |
AbstractBodyAttraction.computeAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute the acceleration due to the force.
|
Vector3D |
AbstractHarmonicGravityModel.computeAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute the acceleration due to the gravitational attraction, accounting for both central and non-central terms.
|
Vector3D |
ThirdBodyAttraction.computeCentralAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date)
Method to compute the acceleration.
|
protected Vector3D |
AbstractHarmonicGravityModel.computeCentralTermAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date,
Transform bodyFrameToPositionFrame)
Compute the acceleration due to the central term of the gravitational attraction.
|
double[][] |
AbstractHarmonicGravityModel.computeCentralTermDAccDPos(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute acceleration derivatives with respect to the state parameters for the central term.
|
double[][] |
GravityModel.computeDAccDPos(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute acceleration derivatives with respect to the position of the spacecraft.
|
double[][] |
AbstractHarmonicGravityModel.computeDAccDPos(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute acceleration derivatives with respect to the position of the spacecraft.
|
Vector3D |
DrozinerGravityModel.computeNonCentralTermsAcceleration(Vector3D pos,
AbsoluteDate date,
Transform bodyFrameToPositionFrame)
Compute the acceleration due to the non-central terms of the gravitational attraction.
|
Vector3D |
BalminoGravityModel.computeNonCentralTermsAcceleration(Vector3D pos,
AbsoluteDate date,
Transform bodyFrameToPositionFrame)
Compute the acceleration due to the non-central terms of the gravitational attraction.
|
protected abstract Vector3D |
AbstractHarmonicGravityModel.computeNonCentralTermsAcceleration(Vector3D pos,
AbsoluteDate date,
Transform bodyFrameToPositionFrame)
Compute the acceleration due to the non-central terms of the gravitational attraction.
|
Vector3D |
NewtonianGravityModel.computeNonCentralTermsAcceleration(Vector3D pos,
AbsoluteDate date,
Transform bodyFrameToPositionFrame)
Compute the acceleration due to the non-central terms of the gravitational attraction.
|
Vector3D |
CunninghamGravityModel.computeNonCentralTermsAcceleration(Vector3D pos,
AbsoluteDate date,
Transform bodyFrameToPositionFrame)
Compute the acceleration due to the non-central terms of the gravitational attraction.
|
double[][] |
DrozinerGravityModel.computeNonCentralTermsDAccDPos(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute acceleration derivatives with respect to the state parameters for the non-central terms.
|
double[][] |
BalminoGravityModel.computeNonCentralTermsDAccDPos(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute acceleration derivatives with respect to the state parameters for the non-central terms.
|
abstract double[][] |
AbstractHarmonicGravityModel.computeNonCentralTermsDAccDPos(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute acceleration derivatives with respect to the state parameters for the non-central terms.
|
double[][] |
NewtonianGravityModel.computeNonCentralTermsDAccDPos(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute acceleration derivatives with respect to the state parameters for the non-central terms.
|
double[][] |
CunninghamGravityModel.computeNonCentralTermsDAccDPos(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute acceleration derivatives with respect to the state parameters for the non-central terms.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
GridGravityModel.computeAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute the acceleration due to the gravitational attraction.
|
Vector3D |
AttractionDataPoint.getAcceleration()
Returns the XYZ acceleration.
|
Vector3D |
AttractionData.getCenterOfMass()
Returns the center of mass position of the body.
|
Vector3D |
AttractionDataPoint.getPosition()
Returns the position.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
GridGravityModel.computeAcceleration(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute the acceleration due to the gravitational attraction.
|
double[][] |
GridGravityModel.computeDAccDPos(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute acceleration derivatives with respect to the position of the spacecraft.
|
double |
GridGravityModel.computePotential(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute the potential due to the body attraction.
|
double[] |
GridSystem.getCoordinates(Vector3D position)
Returns coordinates in grid system for provided position.
|
boolean |
GridSystem.isInsideGrid(Vector3D position)
Returns true if provided position is within grid, false otherwise.
|
| Constructor and Description |
|---|
AttractionData(double gm,
Vector3D centerOfMass,
GridSystem grid,
AttractionDataPoint[] data)
Constructor.
|
AttractionDataPoint(SphericalCoordinates coordinates,
Vector3D acceleration,
double potential)
Constructor with spherical coordinates.
|
AttractionDataPoint(Vector3D position,
Vector3D acceleration,
double potential)
Constructor with 3D position.
|
| 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).
|
Vector3D |
AbstractTides.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
static Vector3D |
ReferencePointsDisplacement.poleTidesCorrections(AbsoluteDate date,
Vector3D point)
Computes the displacement of reference points due to the effect of the pole tides.
|
static Vector3D |
ReferencePointsDisplacement.solidEarthTidesCorrections(AbsoluteDate date,
Vector3D point,
Vector3D sun,
Vector3D moon)
Computes the displacement of reference points due to the effect of the solid Earth tides.
|
| Modifier and Type | Method and Description |
|---|---|
static Vector3D |
ReferencePointsDisplacement.poleTidesCorrections(AbsoluteDate date,
Vector3D point)
Computes the displacement of reference points due to the effect of the pole tides.
|
static Vector3D |
ReferencePointsDisplacement.solidEarthTidesCorrections(AbsoluteDate date,
Vector3D point,
Vector3D sun,
Vector3D moon)
Computes the displacement of reference points due to the effect of the solid Earth tides.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
VariablePotentialGravityModel.computeNonCentralTermsAcceleration(Vector3D pos,
AbsoluteDate date,
Transform bodyFrameToPositionFrame)
Compute the acceleration due to the non-central terms of the gravitational attraction.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
VariablePotentialGravityModel.computeNonCentralTermsAcceleration(Vector3D pos,
AbsoluteDate date,
Transform bodyFrameToPositionFrame)
Compute the acceleration due to the non-central terms of the gravitational attraction.
|
double[][] |
VariablePotentialGravityModel.computeNonCentralTermsDAccDPos(Vector3D pos,
Frame frame,
AbsoluteDate date)
Compute acceleration derivatives with respect to the state parameters for the non-central terms.
|
| Modifier and Type | Field and Description |
|---|---|
protected Vector3D |
ImpulseManeuver.deltaVSat
Velocity increment in the frame defined by the user.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
ConstantThrustError.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
Vector3D |
ContinuousThrustManeuver.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
Vector3D |
ImpulseManeuver.getDeltaVSat()
Get the velocity increment in satellite frame.
|
Vector3D |
ContinuousThrustManeuver.getDirection(SpacecraftState s)
Get the thrust direction.
|
Vector3D |
SmallManeuverAnalyticalModel.getInertialDV()
Get the inertial velocity increment of the maneuver.
|
Vector3D |
GatesModel.getMeanDeltaV(Vector3D deltaV)
Computes the mean ΔV vector of the distribution modeling the uncertainty on a
maneuver's magnitude and direction.
|
static Vector3D |
GatesModel.getMeanDeltaV(Vector3D deltaV,
double sigmaDirection)
Computes the mean ΔV vector of the distribution modeling the uncertainty on a
maneuver's magnitude and direction.
|
Vector3D |
ImpulseManeuver.getUsedDV()
Get the maneuver instantaneous consumption deltaV.
|
Vector3D |
ContinuousThrustManeuver.getUsedDV()
Get the maneuver instantaneous consumption deltaV.
|
| Modifier and Type | Method and Description |
|---|---|
SymmetricMatrix |
GatesModel.getCovarianceMatrix3x3(Vector3D deltaV)
Computes the covariance matrix modeling the uncertainty on a maneuver's magnitude and
direction.
|
static SymmetricMatrix |
GatesModel.getCovarianceMatrix3x3(Vector3D deltaV,
double sigmaMagnitude,
double sigmaDirection)
Computes the covariance matrix modeling the uncertainty on a maneuver's magnitude and
direction.
|
SymmetricMatrix |
GatesModel.getCovarianceMatrix6x6(Vector3D deltaV)
Computes the covariance matrix modeling the uncertainty on an object's position and velocity
induced by the uncertainty on a maneuver's magnitude and direction.
|
static SymmetricMatrix |
GatesModel.getCovarianceMatrix6x6(Vector3D deltaV,
double sigmaMagnitude,
double sigmaDirection)
Computes the covariance matrix modeling the uncertainty on an object's position and velocity
induced by the uncertainty on a maneuver's magnitude and direction.
|
Vector3D |
GatesModel.getMeanDeltaV(Vector3D deltaV)
Computes the mean ΔV vector of the distribution modeling the uncertainty on a
maneuver's magnitude and direction.
|
static Vector3D |
GatesModel.getMeanDeltaV(Vector3D deltaV,
double sigmaDirection)
Computes the mean ΔV vector of the distribution modeling the uncertainty on a
maneuver's magnitude and direction.
|
| Constructor and Description |
|---|
ContinuousThrustManeuver(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
Vector3D inDirection,
MassProvider massProvider,
TankProperty tank)
Constructor for a constant direction in satellite 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(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
Vector3D inDirection,
MassProvider massProvider,
TankProperty tank,
LOFType lofTyp)
Constructor for a constant direction in provided local orbital frame.
|
ContinuousThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
PropulsiveProperty engine,
Vector3D inDirection,
MassProvider massProvider,
TankProperty tank)
Constructor for a constant direction in satellite frame.
|
ContinuousThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
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,
Vector3D inDirection,
MassProvider massProvider,
TankProperty tank,
LOFType lofTyp)
Constructor for a constant direction in local orbital frame.
|
ImpulseManeuver(EventDetector inTrigger,
Vector3D inDeltaVSat,
double isp,
MassProvider massModel,
String part)
Build a new instance.
|
ImpulseManeuver(EventDetector inTrigger,
Vector3D inDeltaVSat,
double isp,
MassProvider massModel,
String part,
LOFType inLofType)
Build a new instance with a LocalOrbitalFrame.
|
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.
|
ImpulseManeuver(EventDetector inTrigger,
Vector3D inDeltaVSat,
PropulsiveProperty engine,
MassProvider massModel,
TankProperty tank)
Build a new instance using propulsive and engine property.
|
ImpulseManeuver(EventDetector inTrigger,
Vector3D inDeltaVSat,
PropulsiveProperty engine,
MassProvider massModel,
TankProperty tank,
LOFType inLofType)
Build a new instance with a LocalOrbitalFrame and using propulsive and engine property.
|
SmallManeuverAnalyticalModel(SpacecraftState state0In,
Frame frame,
Vector3D dV,
double isp,
String partNameIn)
Build a maneuver defined in user-specified frame.
|
SmallManeuverAnalyticalModel(SpacecraftState state0In,
Vector3D dV,
double isp,
String partNameIn)
Build a maneuver defined in spacecraft frame.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
RediffusedRadiationPressure.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
Vector3D |
SolarRadiationPressure.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
Vector3D |
ElementaryFlux.getDirFlux()
get the direction flux
|
Vector3D |
SolarRadiationPressure.getSolarFlux(SpacecraftState s)
Compute solar flux.
|
Vector3D |
RadiationSensitive.radiationPressureAcceleration(SpacecraftState state,
Vector3D flux)
Compute the acceleration due to radiation pressure.
|
Vector3D |
RediffusedRadiationSensitive.rediffusedRadiationPressureAcceleration(SpacecraftState state,
ElementaryFlux[] flux)
rediffused radiative pressure acceleration
|
| Modifier and Type | Method and Description |
|---|---|
void |
RadiationSensitive.addDSRPAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam,
Vector3D satSunVector)
Compute acceleration derivatives with respect to additional parameters.
|
void |
RadiationSensitive.addDSRPAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel,
Vector3D satSunVector)
Compute acceleration derivatives with respect to state parameters.
|
double |
SolarRadiationPressure.getLightningRatio(Vector3D satSunVector,
BodyShape occultingBody,
PVCoordinatesProvider pv,
Frame frame,
AbsoluteDate date)
Get the lightning ratio ([0-1]) for provided occulting body.
|
Vector3D |
RadiationSensitive.radiationPressureAcceleration(SpacecraftState state,
Vector3D flux)
Compute the acceleration due to radiation pressure.
|
| Constructor and Description |
|---|
ElementaryFlux(Vector3D edirFlux,
double eAlbedoPressure,
double eInfraRedPressure)
Constructor of elementary pressure
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
CoriolisRelativisticEffect.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
Vector3D |
LenseThirringRelativisticEffect.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
Vector3D |
SchwarzschildRelativisticEffect.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
| Modifier and Type | Method and Description |
|---|---|
protected abstract Vector3D |
LOFType.computeOmega(PVCoordinates pv)
Get the rotation rate vector expressed in inertial frame.
|
Vector3D |
TopocentricFrame.getDAzimuth(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get 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)
Get the elevation derivative of a point wrt the local point (dElevation) express in the
specified frame.
|
Vector3D |
TopocentricFrame.getEast()
Get the east direction of topocentric frame, expressed in parent shape frame.
|
Vector3D |
TopocentricFrame.getNadir()
Get the nadir direction of topocentric frame, expressed in parent shape frame.
|
Vector3D |
TopocentricFrame.getNorth()
Get the north direction of topocentric frame, expressed in parent shape frame.
|
Vector3D |
TopocentricFrame.getSouth()
Get the south direction of topocentric frame, expressed in parent shape frame.
|
Vector3D |
TopocentricFrame.getWest()
Get the west direction of topocentric frame, expressed in parent shape frame.
|
Vector3D |
TopocentricFrame.getZenith()
Get the zenith direction of topocentric frame, expressed in parent shape frame.
|
Vector3D |
TopocentricFrame.transformFromCardanToPosition(CardanMountPosition cardan)
Transform a Cardan mounting into Cartesian coordinates (only position) expressed in this local
topocentric frame.
|
Vector3D |
TopocentricFrame.transformFromTopocentricToPosition(TopocentricPosition topoCoord)
Transform topocentric set of coordinates frame into Cartesian position coordinates expressed in
this local topocentric.
|
| 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.
|
Vector3D |
TopocentricFrame.getDAzimuth(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get 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)
Get the elevation derivative of a point wrt the local point (dElevation) express in the
specified frame.
|
double |
TopocentricFrame.getElevation(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get the elevation of a point with regards to the local point.
|
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.getXangleCardan(Vector3D extPoint,
Frame frame,
AbsoluteDate date)
Get the Cardan x angle of a point.
|
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.
|
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.
|
| Constructor and Description |
|---|
TopocentricFrame(BodyShape bodyParentShape,
Vector3D cartesianPoint,
double frameOrientation,
String name)
This constructor builds a topocentric frame whose Z-axis is the zenith.
The angle in radians trigowise between the North direction (= "Reference azymuth") and the x-axis of the Topocentric Frame is frameOrientation. |
TopocentricFrame(BodyShape bodyParentShape,
Vector3D cartesianPoint,
String name)
This constructor builds an East oriented topocentric frame.
|
TopocentricFrame(BodyShape bodyParentShape,
Vector3D cartesianPoint,
Vector3D zenith,
double frameOrientation,
String name)
This constructor builds a topocentric frame whose zenith (topocentric Z-axis) is defined by the user.
The angle in radians trigowise between the North direction (= "Reference azimuth") and the x-axis of the topocentric frame is frameOrientation |
TopocentricFrame(BodyShape bodyParentShape,
Vector3D cartesianPoint,
Vector3D zenith,
String name)
This constructor builds an East oriented topocentric frame.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
Transform.getAcceleration()
Get the second time derivative of the translation.
|
Vector3D |
Transform.getRotationAcceleration()
Get the second time derivative of the rotation.
|
Vector3D |
Transform.getRotationRate()
Get the rotation rate of the "destination" frame in the "origin" one.
|
Vector3D |
HelmertTransformation.getRotationRate()
Returns the first time derivative of the rotation (norm representing angular rate).
|
Vector3D |
HelmertTransformation.getRotationVector()
Returns the global rotation vector (applying rotation is done by computing cross product).
|
Vector3D |
Transform.getTranslation()
Get the position of the "destination" frame in the "origin" one.
|
Vector3D |
Transform.getVelocity()
Get the velocity of the "destination" frame in the "origin" one.
|
Vector3D |
Transform.transformPosition(Vector3D position)
Transform a position vector (including translation effects).
|
Vector3D |
Transform.transformVector(Vector3D vector)
Transform a vector (ignoring translation effects).
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
Transform.transformPosition(Vector3D position)
Transform a position vector (including translation effects).
|
Vector3D |
Transform.transformVector(Vector3D vector)
Transform a vector (ignoring translation effects).
|
| Constructor and Description |
|---|
Transform(AbsoluteDate dateIn,
Rotation rotation,
Vector3D rotationRate)
Build a rotation transform.
|
Transform(AbsoluteDate dateIn,
Rotation rotation,
Vector3D rotationRate,
Vector3D rotationAcceleration)
Build a rotation transform.
|
Transform(AbsoluteDate dateIn,
Vector3D translation)
Build a translation transform.
|
Transform(AbsoluteDate dateIn,
Vector3D translation,
Vector3D velocity)
Build a translation transform, with its first time derivative.
|
Transform(AbsoluteDate dateIn,
Vector3D translation,
Vector3D velocity,
Vector3D acceleration)
Build a translation transform, with its first and second time derivatives.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
IDependentVectorVariable.value(T x)
Compute the value of the T-dependent 3D vector.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
LebedevGridPoint.getXYZ()
Gets the Cartesian coordinates of the point.
|
| Modifier and Type | Method and Description |
|---|---|
double |
HelmholtzPolynomial.computeHelmholtzPolynomial(Vector3D point)
Calculate the value of the polynomial in a given point.
|
| Modifier and Type | Field and Description |
|---|---|
static Vector3D |
Vector3D.MINUS_I
Opposite of the first canonical vector (coordinates: -1, 0, 0).
|
static Vector3D |
Vector3D.MINUS_J
Opposite of the second canonical vector (coordinates: 0, -1, 0).
|
static Vector3D |
Vector3D.MINUS_K
Opposite of the third canonical vector (coordinates: 0, 0, -1).
|
static Vector3D |
Vector3D.NaN
A vector with all coordinates set to NaN.
|
static Vector3D |
Vector3D.NEGATIVE_INFINITY
A vector with all coordinates set to negative infinity.
|
static Vector3D |
Vector3D.PLUS_I
First canonical vector (coordinates: 1, 0, 0).
|
static Vector3D |
Vector3D.PLUS_J
Second canonical vector (coordinates: 0, 1, 0).
|
static Vector3D |
Vector3D.PLUS_K
Third canonical vector (coordinates: 0, 0, 1).
|
static Vector3D |
Vector3D.POSITIVE_INFINITY
A vector with all coordinates set to positive infinity.
|
static Vector3D |
Vector3D.ZERO
Null vector (coordinates: 0, 0, 0).
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
Vector3D.add(double factor,
Vector<Euclidean3D> v)
Add a scaled vector to the instance.
|
Vector3D |
Vector3D.add(Vector<Euclidean3D> v)
Add a vector to the instance.
|
Vector3D |
Rotation.applyInverseTo(Vector3D u)
Apply the inverse of the rotation to a vector.
|
Vector3D |
Rotation.applyTo(Vector3D u)
Apply the rotation to a vector.
|
Vector3D |
Line.closestPoint(Line line)
Compute the point of the instance closest to another line.
|
Vector3D[] |
Plate.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
RightCircularCone.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
RightCircularCylinder.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
InfiniteRightCircularCylinder.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
SphericalCap.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
Parallelepiped.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
EllipticCone.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
InfiniteEllipticCylinder.closestPointTo(Line line)
Calculate closest point to a line
|
Vector3D[] |
EllipticCylinder.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
InfiniteEllipticCone.closestPointTo(Line line)
Calculate the closest point to a line
|
Vector3D[] |
Ellipsoid.closestPointTo(Line line)
This method computes the point on the line that is the closest to the ellipsoid.
|
Vector3D[] |
InfiniteRightCircularCone.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
Shape.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
RectangleCone.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
Sphere.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
LineSegment.closestPointTo(Line line)
Computation of the closest point to a line, and the associated point of the line;
|
Vector3D[] |
Plane.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
AbstractEllipse.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
InfiniteRectangleCylinder.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
InfiniteRectangleCone.closestPointTo(Line line)
Computes the points of the shape and the line realizing
the shortest distance.
|
Vector3D[] |
Line.closestPointTo(Line line)
Computes the points of this and another line realizing the shortest distance.
|
Vector3D |
InfiniteEllipticCylinder.closestPointTo(Vector3D point)
Computes the closest point on the cone to a user specified point
|
Vector3D |
InfiniteEllipticCone.closestPointTo(Vector3D point)
Computes the closest point on the cone to a user specified point
|
Vector3D |
IEllipsoid.closestPointTo(Vector3D point)
Computes the point, on the ellipsoid surface, that is the closest to a point of space.
|
Vector3D |
Ellipsoid.closestPointTo(Vector3D point)
Computes the point, on the ellipsoid surface, that is the closest to a point of space.
|
Vector3D |
Sphere.closestPointTo(Vector3D point)
Computes the point, on the ellipsoid surface, that is the closest to a point of space.
|
Vector3D |
AbstractEllipse.closestPointTo(Vector3D point)
Computes the point on the ellipse closest to a point.
|
static Vector3D |
AzimuthElevationCalculator.computeDAzimuth(Vector3D extTopo)
Compute the azimuth derivative of a point defined by its Cartesian coordinates in a Frame
whose x, y and "Reference Azimuth" axis are
in the same Plane.
|
static Vector3D |
AzimuthElevationCalculator.computeDElevation(Vector3D extTopo)
Compute the elevation derivative of a point defined by its Cartesian coordinates in a
Frame whose x, y and "Reference Azimuth" axis are in the same Plane.
|
Vector3D |
Vector3D.crossProduct(Vector<Euclidean3D> v)
Compute the cross-product of the instance with another vector.
|
static Vector3D |
Vector3D.crossProduct(Vector3D v1,
Vector3D v2)
Compute the cross-product of two vectors.
|
Vector3D |
RotationOrder.getA1()
Get the axis of the first rotation.
|
Vector3D |
RotationOrder.getA2()
Get the axis of the second rotation.
|
Vector3D |
RotationOrder.getA3()
Get the axis of the second rotation.
|
Vector3D |
InfiniteEllipticCylinder.getAffineLocalExpression(Vector3D myVector)
Express a Vector3D in spheroid local frame.
|
Vector3D |
InfiniteEllipticCone.getAffineLocalExpression(Vector3D myVector)
Express a Vector3D in spheroid local frame.
|
Vector3D |
Ellipsoid.getAffineLocalExpression(Vector3D myVector)
Express a Vector3D in ellipsoid local basis.
|
Vector3D |
InfiniteEllipticCylinder.getAffineStandardExpression(Vector3D myVector)
Express a Vector3D in standard basis.
|
Vector3D |
InfiniteEllipticCone.getAffineStandardExpression(Vector3D vector)
Express a Vector3D in standard basis.
|
Vector3D |
Ellipsoid.getAffineStandardExpression(Vector3D myVector)
Express a Vector3D in standard basis.
|
Vector3D |
Rotation.getAxis()
Get the normalized axis of the rotation.
|
Vector3D |
InfiniteRightCircularCone.getAxis() |
Vector3D |
InfiniteRectangleCone.getAxis() |
Vector3D |
Plate.getC1() |
Vector3D |
Plate.getC2() |
Vector3D |
Plate.getC3() |
Vector3D |
Plate.getC4() |
Vector3D |
SphericalCoordinates.getCartesianCoordinates()
Returns the cartesian coordinates.
|
Vector3D |
Plate.getCenter() |
Vector3D |
Parallelepiped.getCenter() |
Vector3D |
IEllipsoid.getCenter()
Get ellipsoids' center
|
Vector3D |
Ellipsoid.getCenter()
Get ellipsoid center
|
Vector3D |
Sphere.getCenter() |
Vector3D |
AbstractEllipse.getCenter() |
Vector3D[] |
Parallelepiped.getCorners() |
Vector3D |
RightCircularCone.getDirection() |
Vector3D |
RightCircularCylinder.getDirection() |
Vector3D |
InfiniteRightCircularCylinder.getDirection() |
Vector3D |
EllipticCone.getDirection() |
Vector3D |
InfiniteEllipticCylinder.getDirection()
This method returns the main axis of the cylinder
|
Vector3D |
EllipticCylinder.getDirection() |
Vector3D |
RectangleCone.getDirection() |
Vector3D |
LineSegment.getDirection() |
Vector3D |
InfiniteRectangleCylinder.getDirection() |
Vector3D |
Line.getDirection()
Get the normalized direction vector.
|
Vector3D |
Segment.getEnd()
Get the end point of the segment.
|
Vector3D |
LineSegment.getEnd() |
Vector3D[] |
Plate.getIntersectionPoints(Line line)
Compute the intersection points with a line.
|
Vector3D[] |
RightCircularCone.getIntersectionPoints(Line line)
Compute the intersection points with a line.
|
Vector3D[] |
RightCircularCylinder.getIntersectionPoints(Line line)
Compute the intersection points with a line.
|
Vector3D[] |
InfiniteRightCircularCylinder.getIntersectionPoints(Line line)
Compute the intersection points with a line.
|
Vector3D[] |
SphericalCap.getIntersectionPoints(Line line)
Returns a list of intersection points between the line and the spherical cap.
Only the border points are given. |
Vector3D[] |
Parallelepiped.getIntersectionPoints(Line line)
Compute the intersection points with a line.
|
Vector3D[] |
EllipticCone.getIntersectionPoints(Line line)
Compute the intersection points with a line.
|
Vector3D[] |
InfiniteEllipticCylinder.getIntersectionPoints(Line line)
This methods computes and returns the intersection points between a line and the cylinder.
|
Vector3D[] |
EllipticCylinder.getIntersectionPoints(Line line)
Compute the intersection points with a line.
|
Vector3D[] |
InfiniteEllipticCone.getIntersectionPoints(Line line)
This methods computes and returns the intersection points between a line and the cone.
|
Vector3D[] |
Ellipsoid.getIntersectionPoints(Line line)
If more than one intersection points are found, the closest to the line's origin is returned first.
|
Vector3D[] |
InfiniteRightCircularCone.getIntersectionPoints(Line line)
Compute the intersection points with a line.
|
Vector3D[] |
Shape.getIntersectionPoints(Line line)
Compute the intersection points with a line.
|
Vector3D[] |
RectangleCone.getIntersectionPoints(Line line)
Compute the intersection points with a line.
|
Vector3D[] |
Sphere.getIntersectionPoints(Line line)
Compute the intersection points with a line.
|
Vector3D[] |
Plane.getIntersectionPoints(Line line)
Compute the intersection points with a line.
|
Vector3D[] |
AbstractEllipse.getIntersectionPoints(Line line)
Compute the intersection points with a line.
|
Vector3D[] |
InfiniteRectangleCylinder.getIntersectionPoints(Line line)
Compute the intersection points with a line.
|
Vector3D[] |
InfiniteRectangleCone.getIntersectionPoints(Line line)
Compute the intersection points with a line.
|
Vector3D[] |
Line.getIntersectionPoints(Line line)
Compute the intersection points with another line if it exists.
|
Vector3D |
Plane.getNormal()
Get the normalized normal vector.
|
Vector3D |
AbstractEllipse.getNormal() |
Vector3D |
IEllipsoid.getNormal(Vector3D point)
Computes the normal vector to the surface in local basis
|
Vector3D |
Ellipsoid.getNormal(Vector3D point)
Computes the normal vector to the surface in local basis
|
Vector3D |
Sphere.getNormal(Vector3D point)
Computes the normal vector to the surface
|
Vector3D |
RightCircularCone.getOrigin() |
Vector3D |
RightCircularCylinder.getOrigin() |
Vector3D |
Screw.getOrigin() |
Vector3D |
InfiniteRightCircularCylinder.getOrigin() |
Vector3D |
EllipticCone.getOrigin() |
Vector3D |
InfiniteEllipticCylinder.getOrigin()
This method returns the position of the cylinder on the Oxy plane
|
Vector3D |
InfiniteCone.getOrigin() |
Vector3D |
EllipticCylinder.getOrigin() |
Vector3D |
InfiniteEllipticCone.getOrigin()
This method returns the origin of the cone
|
Vector3D |
InfiniteRightCircularCone.getOrigin() |
Vector3D |
RectangleCone.getOrigin() |
Vector3D |
LineSegment.getOrigin() |
Vector3D |
Plane.getOrigin()
Get the origin point of the plane frame.
|
Vector3D |
InfiniteRectangleCylinder.getOrigin() |
Vector3D |
InfiniteRectangleCone.getOrigin() |
Vector3D |
Line.getOrigin()
Get the line point closest to the origin.
|
Vector3D |
Plane.getPointAt(Vector2D plane,
double offset)
Get one point from the 3D-space.
|
Vector3D |
Screw.getRotation() |
Vector3D |
Ellipsoid.getSemiPrincipalX() |
Vector3D |
Ellipsoid.getSemiPrincipalY() |
Vector3D |
Ellipsoid.getSemiPrincipalZ() |
Vector3D |
Segment.getStart()
Get the start point of the segment.
|
Vector3D |
Screw.getTranslation() |
Vector3D |
Plate.getU() |
Vector3D |
Parallelepiped.getU() |
Vector3D |
EllipticCone.getU() |
Vector3D |
EllipticCylinder.getU() |
Vector3D |
RectangleCone.getU() |
Vector3D |
Plane.getU()
Get the plane first canonical vector.
|
Vector3D |
AbstractEllipse.getU() |
Vector3D |
InfiniteRectangleCylinder.getU() |
Vector3D |
InfiniteRectangleCone.getU() |
Vector3D |
Plate.getV() |
Vector3D |
Parallelepiped.getV() |
Vector3D |
EllipticCone.getV() |
Vector3D |
EllipticCylinder.getV() |
Vector3D |
RectangleCone.getV() |
Vector3D |
Plane.getV()
Get the plane second canonical vector.
|
Vector3D |
AbstractEllipse.getV() |
Vector3D |
InfiniteRectangleCylinder.getV() |
Vector3D |
InfiniteRectangleCone.getV() |
abstract Vector3D |
AbstractVector3DFunction.getVector3D(AbsoluteDate date)
Get the vector at a given date.
|
Vector3D |
Vector3DFunction.getVector3D(AbsoluteDate date)
Get the vector at a given date.
|
Vector3D |
InfiniteEllipticCylinder.getVectorialLocalExpression(Vector3D myVector)
Express a Vector3D in spheroid local frame.
|
Vector3D |
InfiniteEllipticCone.getVectorialLocalExpression(Vector3D myVector)
Express a Vector3D in spheroid local frame.
|
Vector3D |
Ellipsoid.getVectorialLocalExpression(Vector3D myVector)
Express a Vector3D in ellipsoid local basis.
|
Vector3D |
InfiniteEllipticCylinder.getVectorialStandardExpression(Vector3D myVector)
Express a Vector3D in standard basis.
|
Vector3D |
InfiniteEllipticCone.getVectorialStandardExpression(Vector3D vector)
Express a Vector3D in standard basis.
|
Vector3D |
Ellipsoid.getVectorialStandardExpression(Vector3D myVector)
Express a Vector3D in standard basis.
|
Vector3D |
Parallelepiped.getW() |
Vector3D |
Vector3D.getZero()
Get the null vector of the vectorial space or origin point of the affine space.
|
Vector3D |
AbstractVector3DFunction.integral(double x0,
double xf)
Returns the integral of the vector function in the given interval.
|
Vector3D |
Vector3DFunction.integral(double x0,
double xf)
Returns the integral of the vector function in the given interval.
|
Vector3D |
Plane.intersection(Line line)
Get the intersection of a line with the instance.
|
Vector3D |
Line.intersection(Line line)
Get the intersection point of the instance and another line.
|
static Vector3D |
Plane.intersection(Plane plane1,
Plane plane2,
Plane plane3)
Get the intersection point of three planes.
|
Vector3D |
SubLine.intersection(SubLine subLine,
boolean includeEndPoints)
Get the intersection of the instance and another sub-line.
|
static Vector3D |
Vector3D.inverseCrossProducts(Vector3D v1,
Vector3D c1,
Vector3D v2,
Vector3D c2,
double tolerance)
Find a vector from two known cross products.
|
Vector3D |
Matrix3D.multiply(Vector3D mult)
Computes the multiplication between a Matrix3D and a Vector3D
|
Vector3D |
Vector3D.negate()
Get the opposite of the instance.
|
Vector3D |
Vector3D.normalize()
Get a normalized vector aligned with the instance.
|
Vector3D |
Vector3D.orthogonal()
Get a vector orthogonal to the instance.
|
Vector3D |
Vector3DFormat.parse(String source)
Parses a string to produce a
Vector3D object. |
Vector3D |
Vector3DFormat.parse(String source,
ParsePosition pos)
Parses a string to produce a
Vector3D object. |
Vector3D |
Line.pointAt(double abscissa)
Get one point from the line.
|
Vector3D |
Line.pointOfMinAbscissa(Vector3D[] points)
Get the point with the lowest abscissa from an array of points.
|
Vector3D |
Vector3D.scalarMultiply(double a)
Multiply the instance by a scalar.
|
Vector3D |
Vector3D.subtract(double factor,
Vector<Euclidean3D> v)
Subtract a scaled vector from the instance.
|
Vector3D |
Vector3D.subtract(Vector<Euclidean3D> v)
Subtract a vector from the instance.
|
Vector3D |
Line.toSpace(Vector<Euclidean1D> point)
Transform a sub-space point into a space point.
|
Vector3D |
Plane.toSpace(Vector<Euclidean2D> point)
Transform an in-plane point into a 3D space point.
|
Vector3D |
FieldVector3D.toVector3D()
Convert to a constant vector without derivatives.
|
Vector3D |
Matrix3D.transposeAndMultiply(Vector3D vector)
Computes the multiplication of the transposed matrix of this Matrix3D with a Vector3D
|
| Modifier and Type | Method and Description |
|---|---|
List<Vector3D> |
PolyhedronsSet.BRep.getVertices()
Get the extracted vertices.
|
| Modifier and Type | Method and Description |
|---|---|
FieldVector3D<T> |
FieldVector3D.add(double factor,
Vector3D v)
Add a scaled vector to the instance.
|
FieldVector3D<T> |
FieldVector3D.add(T factor,
Vector3D v)
Add a scaled vector to the instance.
|
FieldVector3D<T> |
FieldVector3D.add(Vector3D v)
Add a vector to the instance.
|
static <T extends RealFieldElement<T>> |
FieldVector3D.angle(FieldVector3D<T> v1,
Vector3D v2)
Compute the angular separation between two vectors.
|
static <T extends RealFieldElement<T>> |
FieldVector3D.angle(Vector3D v1,
FieldVector3D<T> v2)
Compute the angular separation between two vectors.
|
static double |
Vector3D.angle(Vector3D v1,
Vector3D v2)
Compute the angular separation between two vectors.
|
FieldVector3D<T> |
FieldRotation.applyInverseTo(Vector3D u)
Apply the inverse of the rotation to a vector.
|
Vector3D |
Rotation.applyInverseTo(Vector3D u)
Apply the inverse of the rotation to a vector.
|
FieldVector3D<T> |
FieldRotation.applyTo(Vector3D u)
Apply the rotation to a vector.
|
Vector3D |
Rotation.applyTo(Vector3D u)
Apply the rotation to a vector.
|
Vector3D |
InfiniteEllipticCylinder.closestPointTo(Vector3D point)
Computes the closest point on the cone to a user specified point
|
Vector3D |
InfiniteEllipticCone.closestPointTo(Vector3D point)
Computes the closest point on the cone to a user specified point
|
Vector3D |
IEllipsoid.closestPointTo(Vector3D point)
Computes the point, on the ellipsoid surface, that is the closest to a point of space.
|
Vector3D |
Ellipsoid.closestPointTo(Vector3D point)
Computes the point, on the ellipsoid surface, that is the closest to a point of space.
|
Vector3D |
Sphere.closestPointTo(Vector3D point)
Computes the point, on the ellipsoid surface, that is the closest to a point of space.
|
Vector3D |
AbstractEllipse.closestPointTo(Vector3D point)
Computes the point on the ellipse closest to a point.
|
static Vector3D |
AzimuthElevationCalculator.computeDAzimuth(Vector3D extTopo)
Compute the azimuth derivative of a point defined by its Cartesian coordinates in a Frame
whose x, y and "Reference Azimuth" axis are
in the same Plane.
|
static Vector3D |
AzimuthElevationCalculator.computeDElevation(Vector3D extTopo)
Compute the elevation derivative of a point defined by its Cartesian coordinates in a
Frame whose x, y and "Reference Azimuth" axis are in the same Plane.
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boolean |
Plane.contains(Vector3D p)
Check if the instance contains a point.
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boolean |
Line.contains(Vector3D p)
Check if the instance contains a point.
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static Line |
Line.createLine(Vector3D point,
Vector3D direction)
Creates a Line object from a point of space and a direction vector.
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static Line |
Line.createLine(Vector3D point,
Vector3D direction,
Vector3D pointMinAbscissa)
Creates a Line object from a point of space, a direction vector and the point of minimum abscissa.
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static <T extends RealFieldElement<T>> |
FieldVector3D.crossProduct(FieldVector3D<T> v1,
Vector3D v2)
Compute the cross-product of two vectors.
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FieldVector3D<T> |
FieldVector3D.crossProduct(Vector3D v)
Compute the cross-product of the instance with another vector.
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static <T extends RealFieldElement<T>> |
FieldVector3D.crossProduct(Vector3D v1,
FieldVector3D<T> v2)
Compute the cross-product of two vectors.
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static Vector3D |
Vector3D.crossProduct(Vector3D v1,
Vector3D v2)
Compute the cross-product of two vectors.
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static Screw |
Screw.displace(Screw s,
Vector3D newOrigin)
Displace this screw, using Chasles
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Screw |
Screw.displace(Vector3D newOrigin)
Displace this screw, using Chasles
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static <T extends RealFieldElement<T>> |
FieldVector3D.distance(FieldVector3D<T> v1,
Vector3D v2)
Compute the distance between two vectors according to the L2 norm.
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T |
FieldVector3D.distance(Vector3D v)
Compute the distance between the instance and another vector according to the L2 norm.
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double |
Line.distance(Vector3D p)
Compute the distance between the instance and a point.
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static <T extends RealFieldElement<T>> |
FieldVector3D.distance(Vector3D v1,
FieldVector3D<T> v2)
Compute the distance between two vectors according to the L2 norm.
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static double |
Vector3D.distance(Vector3D v1,
Vector3D v2)
Compute the distance between two vectors according to the L2 norm.
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static <T extends RealFieldElement<T>> |
FieldVector3D.distance1(FieldVector3D<T> v1,
Vector3D v2)
Compute the distance between two vectors according to the L1 norm.
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T |
FieldVector3D.distance1(Vector3D v)
Compute the distance between the instance and another vector according to the L1 norm.
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static <T extends RealFieldElement<T>> |
FieldVector3D.distance1(Vector3D v1,
FieldVector3D<T> v2)
Compute the distance between two vectors according to the L1 norm.
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static double |
Vector3D.distance1(Vector3D v1,
Vector3D v2)
Compute the distance between two vectors according to the L1 norm.
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static <T extends RealFieldElement<T>> |
FieldVector3D.distanceInf(FieldVector3D<T> v1,
Vector3D v2)
Compute the distance between two vectors according to the L∞ norm.
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T |
FieldVector3D.distanceInf(Vector3D v)
Compute the distance between the instance and another vector according to the L∞ norm.
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static <T extends RealFieldElement<T>> |
FieldVector3D.distanceInf(Vector3D v1,
FieldVector3D<T> v2)
Compute the distance between two vectors according to the L∞ norm.
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static double |
Vector3D.distanceInf(Vector3D v1,
Vector3D v2)
Compute the distance between two vectors according to the L∞ norm.
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static <T extends RealFieldElement<T>> |
FieldVector3D.distanceSq(FieldVector3D<T> v1,
Vector3D v2)
Compute the square of the distance between two vectors.
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T |
FieldVector3D.distanceSq(Vector3D v)
Compute the square of the distance between the instance and another vector.
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static <T extends RealFieldElement<T>> |
FieldVector3D.distanceSq(Vector3D v1,
FieldVector3D<T> v2)
Compute the square of the distance between two vectors.
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static double |
Vector3D.distanceSq(Vector3D v1,
Vector3D v2)
Compute the square of the distance between two vectors.
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double |
InfiniteEllipticCylinder.distanceTo(Vector3D point) |
double |
InfiniteEllipticCone.distanceTo(Vector3D point) |
double |
Ellipsoid.distanceTo(Vector3D point)
Computes the distance to the closest point on the ellipsoid.
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double |
Sphere.distanceTo(Vector3D point)
Computes the distance to a point of space.
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double |
Plane.distanceTo(Vector3D point)
Computes the distance between this plane and a point of space.
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double |
AbstractEllipse.distanceTo(Vector3D point)
Computes the shortest distance from a point to the ellipse.
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static <T extends RealFieldElement<T>> |
FieldVector3D.dotProduct(FieldVector3D<T> v1,
Vector3D v2)
Compute the dot-product of two vectors.
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T |
FieldVector3D.dotProduct(Vector3D v)
Compute the dot-product of the instance and another vector.
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static <T extends RealFieldElement<T>> |
FieldVector3D.dotProduct(Vector3D v1,
FieldVector3D<T> v2)
Compute the dot-product of two vectors.
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static double |
Vector3D.dotProduct(Vector3D v1,
Vector3D v2)
Compute the dot-product of two vectors.
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SubHyperplane<Euclidean3D> |
PolyhedronsSet.firstIntersection(Vector3D point,
Line line)
Get the first sub-hyperplane crossed by a semi-infinite line.
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double |
Line.getAbscissa(Vector3D point)
Get the abscissa of a point with respect to the line.
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Vector3D |
InfiniteEllipticCylinder.getAffineLocalExpression(Vector3D myVector)
Express a Vector3D in spheroid local frame.
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Vector3D |
InfiniteEllipticCone.getAffineLocalExpression(Vector3D myVector)
Express a Vector3D in spheroid local frame.
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Vector3D |
Ellipsoid.getAffineLocalExpression(Vector3D myVector)
Express a Vector3D in ellipsoid local basis.
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Vector3D |
InfiniteEllipticCylinder.getAffineStandardExpression(Vector3D myVector)
Express a Vector3D in standard basis.
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Vector3D |
InfiniteEllipticCone.getAffineStandardExpression(Vector3D vector)
Express a Vector3D in standard basis.
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Vector3D |
Ellipsoid.getAffineStandardExpression(Vector3D myVector)
Express a Vector3D in standard basis.
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static double |
AzimuthElevationCalculator.getAzimuth(Vector3D point,
double frameOrientation)
Compute the Azimuth of a point defined by its Cartesian coordinates in a
Frame whose x, y and "Reference Azimuth" axis are in the same Plane
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double |
Plate.getCrossSection(Vector3D direction)
Computes the cross section from the direction
defined by a Vector3D.
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double |
RightCircularCylinder.getCrossSection(Vector3D crossDirection)
Computes the cross section from the direction
defined by a Vector3D.
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double |
RightCircularSurfaceCylinder.getCrossSection(Vector3D direction)
Computes the cross section from the direction
defined by a Vector3D.
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double |
Parallelepiped.getCrossSection(Vector3D direction)
Computes the cross section from the direction
defined by a Vector3D.
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double |
CrossSectionProvider.getCrossSection(Vector3D direction)
Computes the cross section from the direction
defined by a Vector3D.
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double |
RightParallelepiped.getCrossSection(Vector3D direction)
Computes the cross section from the direction
defined by a Vector3D.
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double |
Sphere.getCrossSection(Vector3D direction)
Computes the cross section from the direction
defined by a Vector3D.
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static double |
AzimuthElevationCalculator.getElevation(Vector3D point)
Compute the Elevation of a point defined by its Cartesian coordinates in a
Frame whose x, y and "Reference Azimuth" axis are in the same Plane
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double[] |
Ellipsoid.getEllipsoidicCoordinates(Vector3D point)
Convert from Cartesian to Ellipsoid coordinates
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Vector3D |
IEllipsoid.getNormal(Vector3D point)
Computes the normal vector to the surface in local basis
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Vector3D |
Ellipsoid.getNormal(Vector3D point)
Computes the normal vector to the surface in local basis
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Vector3D |
Sphere.getNormal(Vector3D point)
Computes the normal vector to the surface
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Vector3D |
InfiniteEllipticCylinder.getVectorialLocalExpression(Vector3D myVector)
Express a Vector3D in spheroid local frame.
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Vector3D |
InfiniteEllipticCone.getVectorialLocalExpression(Vector3D myVector)
Express a Vector3D in spheroid local frame.
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Vector3D |
Ellipsoid.getVectorialLocalExpression(Vector3D myVector)
Express a Vector3D in ellipsoid local basis.
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Vector3D |
InfiniteEllipticCylinder.getVectorialStandardExpression(Vector3D myVector)
Express a Vector3D in standard basis.
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Vector3D |
InfiniteEllipticCone.getVectorialStandardExpression(Vector3D vector)
Express a Vector3D in standard basis.
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Vector3D |
Ellipsoid.getVectorialStandardExpression(Vector3D myVector)
Express a Vector3D in standard basis.
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static Vector3D |
Vector3D.inverseCrossProducts(Vector3D v1,
Vector3D c1,
Vector3D v2,
Vector3D c2,
double tolerance)
Find a vector from two known cross products.
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boolean |
InfiniteEllipticCone.isInside(Vector3D point)
Return true if point is inside cone
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boolean |
InfiniteEllipticCone.isStrictlyInside(Vector3D point)
Return true if point is inside cone
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Vector3D |
Matrix3D.multiply(Vector3D mult)
Computes the multiplication between a Matrix3D and a Vector3D
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Vector3D |
Line.pointOfMinAbscissa(Vector3D[] points)
Get the point with the lowest abscissa from an array of points.
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void |
Plane.reset(Vector3D p,
Vector3D normal)
Reset the instance as if built from a point and a normal.
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void |
Line.reset(Vector3D p1,
Vector3D p2)
Reset the instance as if built from two points.
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PolyhedronsSet |
PolyhedronsSet.rotate(Vector3D center,
Rotation rotation)
Rotate the region around the specified point.
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Plane |
Plane.rotate(Vector3D center,
Rotation rotation)
Rotate the plane around the specified point.
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FieldVector3D<T> |
FieldVector3D.subtract(double factor,
Vector3D v)
Subtract a scaled vector from the instance.
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FieldVector3D<T> |
FieldVector3D.subtract(T factor,
Vector3D v)
Subtract a scaled vector from the instance.
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FieldVector3D<T> |
FieldVector3D.subtract(Vector3D v)
Subtract a vector from the instance.
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PolyhedronsSet |
PolyhedronsSet.translate(Vector3D translation)
Translate the region by the specified amount.
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Plane |
Plane.translate(Vector3D translation)
Translate the plane by the specified amount.
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Vector3D |
Matrix3D.transposeAndMultiply(Vector3D vector)
Computes the multiplication of the transposed matrix of this Matrix3D with a Vector3D
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| Constructor and Description |
|---|
AbstractEllipse(Vector3D inCenter,
Vector3D inNormal,
Vector3D inUvector,
double inRadiusA,
double inRadiusB)
Build an ellipse in the 3D space from its center, normal vector, approximative U vector of the local frame, and
two radiuses.
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Disk(Vector3D center,
Vector3D normal,
double radius)
Constructs the disk.
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Ellipse(Vector3D inCenter,
Vector3D inNormal,
Vector3D inUvector,
double inRadiusA,
double inRadiusB)
Build an ellipse in the 3D space from its center, normal vector, approximative U vector of the local frame, and
two radiuses.
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Ellipsoid(Vector3D myPosition,
Vector3D myRevAxis,
Vector3D myXAxis,
double myA,
double myB,
double myC)
This constructor builds a ellipsoid from its centers position, its revolution axis and its transverse and
conjugate radii.
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EllipticCone(Vector3D inOrigin,
Vector3D inDirection,
Vector3D inUvector,
double inAngleU,
double inAngleV,
double inHeight)
Build an oblique circular cone from its radius, the height, the origin (apex), the approximative u vector of the
local frame and direction of its axis.
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EllipticCylinder(Vector3D inOrigin,
Vector3D inDirection,
Vector3D inUvector,
double inRadiusA,
double inRadiusB,
double inHeight)
Build an oblique circular cylinder from its radiuses, the height, the origin, the approximative u vector of the
local frame and the direction of its axis.
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FieldVector3D(T a,
Vector3D u)
Multiplicative constructor
Build a vector from another one and a scale factor.
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FieldVector3D(T a1,
Vector3D u1,
T a2,
Vector3D u2)
Linear constructor
Build a vector from two other ones and corresponding scale factors.
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FieldVector3D(T a1,
Vector3D u1,
T a2,
Vector3D u2,
T a3,
Vector3D u3)
Linear constructor
Build a vector from three other ones and corresponding scale factors.
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FieldVector3D(T a1,
Vector3D u1,
T a2,
Vector3D u2,
T a3,
Vector3D u3,
T a4,
Vector3D u4)
Linear constructor
Build a vector from four other ones and corresponding scale factors.
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InfiniteEllipticCone(Vector3D aorigin,
Vector3D aDirection,
Vector3D aaxisU,
double aalpha,
double bbeta)
This is the constructor for the class InfiniteObliqueCircularCone.
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InfiniteEllipticCylinder(Vector3D myLocalOrigin,
Vector3D myDirection,
Vector3D myXAxis,
double myA,
double myB)
This is the constructor for the class InfiniteEllipticCylinder.
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InfiniteRectangleCone(Vector3D inOrigin,
Vector3D inDirection,
Vector3D inUvector,
double inAngleU,
double inAngleV)
Build an infinite rectangle cone from the position of its origin, its axis, a vector defining the orientation of
the rectangle and two angles
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InfiniteRectangleCylinder(Line inDirection,
Vector3D inUVector,
double inLength,
double inWidth)
Build an infinite rectangle cylinder from its dimensions, orientation and the origin and direction of its axis
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InfiniteRectangleCylinder(Vector3D inOrigin,
Vector3D inDirection,
Vector3D inUvector,
double inLength,
double inWidth)
Build an infinite rectangle cylinder from its dimensions, orientation and the origin and direction of its axis
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InfiniteRightCircularCone(Vector3D inOrigin,
Vector3D inDirection,
double inAngle)
Build an infinite elliptic cone from its angle, the position of its origin and its axis
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InfiniteRightCircularCylinder(Vector3D inOrigin,
Vector3D inDirection,
double inRadius)
Build an infinite right circular cylinder from its radius and the origin and direction of its axis
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Line(Vector3D p1,
Vector3D p2)
Build a line from two points.
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Line(Vector3D p1,
Vector3D p2,
Vector3D pMinAbscissa)
Build a line from three points, one of which is the point of minimum abscissa.
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LineSegment(Vector3D inOrigin,
Vector3D inDirection,
double inLength)
Build a line segment from its origin, direction and length.
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Matrix3D(Vector3D vector)
Constructor
Builds a cross product matrix M from a vector u such as : M(u) * v = u^v |
OutlineExtractor(Vector3D uIn,
Vector3D vIn)
Build an extractor for a specific projection plane.
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Parallelepiped(Vector3D inCenter,
Vector3D inU,
Vector3D inV,
double inLength,
double inWidth,
double inHeight)
Build a parallelepiped from the position of its center, two vectors to describe its local frame and dimensions.
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Plane(Line line,
Vector3D vector)
Build a plane from a line and a vector.
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Plane(Vector3D normal)
Build a plane normal to a given direction and containing the origin.
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Plane(Vector3D point,
Line line)
Build a plane from a line and a point out of the line.
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Plane(Vector3D p,
Vector3D normal)
Build a plane from a point and a normal.
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Plane(Vector3D p1,
Vector3D p2,
Vector3D p3)
Build a plane from three points.
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Plane(Vector3D p,
Vector3D v1,
Vector3D v2,
boolean isFrame)
Build a plane from a point and two vectors.
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Plate(Vector3D inCenter,
Vector3D inU,
Vector3D inV,
double inLength,
double inWidth)
Build a plate from the position of its center and two vectors to describe its local frame and dimensions.
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RectangleCone(Vector3D inOrigin,
Vector3D inDirection,
Vector3D inUvector,
double inLength,
double inWidth,
double inHeight)
Build a rectangle cone from its apex (origin), axis' direction, approximative U vector of the local frame and
dimensions.
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RightCircularCone(Vector3D inOrigin,
Vector3D inDirection,
double inAngle,
double inLength)
Build a elliptic cone from its radius, the height, the origin (apex) and direction of its axis
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RightCircularCylinder(Vector3D inOrigin,
Vector3D inDirection,
double inRadius,
double inHeight)
Build a right circular cylinder from its radius and the origin and direction of its axis
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Rotation(Vector3D axis,
double angle)
Build a rotation from an axis and an angle.
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Rotation(Vector3D u,
Vector3D v)
Build one of the rotations that transform one vector into another one.
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Rotation(Vector3D u1In,
Vector3D u2In,
Vector3D v1In,
Vector3D v2In)
Build the rotation that transforms a pair of vector into another pair.
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Screw(Vector3D inOrigin,
Vector3D inTranslation,
Vector3D inRotation)
Constructor
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Segment(Vector3D startIn,
Vector3D endIn)
Build a segment.
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Segment(Vector3D startIn,
Vector3D endIn,
Line lineIn)
Build a segment.
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Sphere(Vector3D inCenter,
double inRadius)
Build a sphere from its radius and the position of its center
|
SphericalCoordinates(Vector3D vector)
Build a new instance.
|
Spheroid(Vector3D myPosition,
Vector3D myRevAxis,
double equatorialRadius,
double polarRadius)
This constructor builds a spheroid from its centers position, its revolution axis and its equatorial and
polar radius.
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SubLine(Vector3D start,
Vector3D end)
Create a sub-line from two endpoints.
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Vector3D(double a,
Vector3D u)
Multiplicative constructor
Build a vector from another one and a scale factor.
|
Vector3D(double a1,
Vector3D u1,
double a2,
Vector3D u2)
Linear constructor
Build a vector from two other ones and corresponding scale factors.
|
Vector3D(double a1,
Vector3D u1,
double a2,
Vector3D u2,
double a3,
Vector3D u3)
Linear constructor
Build a vector from three other ones and corresponding scale factors.
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Vector3D(double a1,
Vector3D u1,
double a2,
Vector3D u2,
double a3,
Vector3D u3,
double a4,
Vector3D u4)
Linear constructor
Build a vector from four other ones and corresponding scale factors.
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| Constructor and Description |
|---|
BRep(List<Vector3D> verticesIn,
List<int[]> facetsIn)
Simple constructor.
|
PolyhedronsSet(List<Vector3D> vertices,
List<int[]> facets,
double tolerance)
Build a polyhedrons set from a Boundary REPresentation (B-rep) specified by connected vertices.
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| Modifier and Type | Method and Description |
|---|---|
static double |
AngleTools.getAngleBewteen2Vector3D(Vector3D vector1,
Vector3D vector2)
Computes the angle between 2 vectors 3D.
|
static double |
AngleTools.getOrientedAngleBewteen2Vector3D(Vector3D vector1,
Vector3D vector2,
Vector3D vector3)
Computes the oriented angle between 2 vectors 3D.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
GeoMagneticElements.getFieldVector()
Returns the magnetic field vector in the topocentric frame (North=X, East=Y, Nadir=Z) in nTesla.
|
| 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.
|
| Constructor and Description |
|---|
GeoMagneticElements(Vector3D bIn)
Construct a new element with the given field vector.
|
| Modifier and Type | Method and Description |
|---|---|
protected static void |
Orbit.fillHalfRow(double a,
Vector3D v,
double[] row,
int j)
Fill a Jacobian half row with a single vector.
|
protected static void |
Orbit.fillHalfRow(double a1,
Vector3D v1,
double a2,
Vector3D v2,
double[] row,
int j)
Fill a Jacobian half row with a linear combination of vectors.
|
protected static void |
Orbit.fillHalfRow(double a1,
Vector3D v1,
double a2,
Vector3D v2,
double a3,
Vector3D v3,
double[] row,
int j)
Fill a Jacobian half row with a linear combination of vectors.
|
protected static void |
Orbit.fillHalfRow(double a1,
Vector3D v1,
double a2,
Vector3D v2,
double a3,
Vector3D v3,
double a4,
Vector3D v4,
double[] row,
int j)
Fill a Jacobian half row with a linear combination of vectors.
|
protected static void |
Orbit.fillHalfRow(double a1,
Vector3D v1,
double a2,
Vector3D v2,
double a3,
Vector3D v3,
double a4,
Vector3D v4,
double a5,
Vector3D v5,
double[] row,
int j)
Fill a Jacobian half row with a linear combination of vectors.
|
protected static void |
Orbit.fillHalfRow(double a1,
Vector3D v1,
double a2,
Vector3D v2,
double a3,
Vector3D v3,
double a4,
Vector3D v4,
double a5,
Vector3D v5,
double a6,
Vector3D v6,
double[] row,
int j)
Fill a Jacobian half row with a linear combination of vectors.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
CartesianParameters.getPosition()
Get the position.
|
Vector3D |
CartesianParameters.getVelocity()
Get the velocity.
|
| Constructor and Description |
|---|
CartesianParameters(Vector3D position,
Vector3D velocity,
Vector3D acceleration,
double mu)
Constructor with position and velocity.
|
| Modifier and Type | Method and Description |
|---|---|
static Vector3D |
PVCoordinates.estimateVelocity(Vector3D start,
Vector3D end,
double dt)
Estimate velocity between two positions.
|
Vector3D |
PVCoordinates.getAcceleration()
Gets the acceleration.
|
Vector3D |
PVCoordinates.getAngularVelocity()
Get the angular velocity (spin) of this point as seen from the origin.
|
Vector3D |
PVCoordinates.getMomentum()
Gets the momentum.
|
Vector3D |
Position.getPosition()
Gets the position.
|
Vector3D |
CardanMountPV.getPosition()
Gets the position.
|
Vector3D |
PVCoordinates.getPosition()
Gets the position.
|
Vector3D |
TopocentricPV.getPosition()
Gets the position.
|
Vector3D |
CardanMountPosition.getPosition()
Gets the position.
|
Vector3D |
TopocentricPosition.getPosition()
Gets the position.
|
Vector3D |
CardanMountPV.getVelocity()
Gets the velocity.
|
Vector3D |
PVCoordinates.getVelocity()
Gets the velocity.
|
Vector3D |
TopocentricPV.getVelocity()
Gets the velocity.
|
Vector3D |
PV.getVelocity()
Gets the velocity.
|
| Modifier and Type | Method and Description |
|---|---|
static Vector3D |
PVCoordinates.estimateVelocity(Vector3D start,
Vector3D end,
double dt)
Estimate velocity between two positions.
|
| Constructor and Description |
|---|
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.
|
EphemerisPvHermite(SpacecraftState[] tabState,
int samples,
Vector3D[] tabAcc,
ISearchIndex algo)
Creates an instance of EphemerisPvHermite from a SpacecraftState table
|
EphemerisPvHermite(SpacecraftState[] tabState,
Vector3D[] tabAcc,
ISearchIndex algo)
Creates an instance of EphemerisPvHermite from a SpacecraftState table
with default number of samples = 2.
|
PVCoordinates(Vector3D positionIn,
Vector3D velocityIn)
Builds a PVCoordinates triplet with zero acceleration.
|
PVCoordinates(Vector3D positionIn,
Vector3D velocityIn,
Vector3D accelerationIn)
Builds a PVCoordinates triplet.
|
TimeStampedPVCoordinates(AbsoluteDate dateIn,
Vector3D position,
Vector3D velocity)
Build from position and velocity.
|
TimeStampedPVCoordinates(AbsoluteDate dateIn,
Vector3D position,
Vector3D velocity,
Vector3D acceleration)
Builds a TimeStampedPVCoordinates triplet.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
DihedralFieldOfViewDetector.getAxis1()
Get the direction of fov 1st dihedral axis.
|
Vector3D |
DihedralFieldOfViewDetector.getAxis2()
Get the direction of fov 2nd dihedral axis.
|
Vector3D |
CircularFieldOfViewDetector.getCenter()
Get the direction of fov center.
|
Vector3D |
DihedralFieldOfViewDetector.getCenter()
Get the direction of fov center.
|
| Constructor and Description |
|---|
CircularFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
double halfApertureIn,
double maxCheckIn)
Build a new instance.
|
CircularFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
double halfApertureIn,
double maxCheck,
double threshold)
Build a new instance.
|
CircularFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
double halfApertureIn,
double maxCheck,
double threshold,
EventDetector.Action entry,
EventDetector.Action exit)
Build a new instance with defined actions at fov entry and exit.
|
CircularFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
double halfApertureIn,
double maxCheck,
double threshold,
EventDetector.Action entry,
EventDetector.Action exit,
boolean removeEntry,
boolean removeExit)
Build a new instance with defined actions at fov entry and exit.
|
DihedralFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
Vector3D axis1,
double halfAperture1In,
Vector3D axis2,
double halfAperture2In,
double maxCheck)
Build a new instance.
|
DihedralFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
Vector3D axis1,
double halfAperture1In,
Vector3D axis2,
double halfAperture2In,
double maxCheck,
double epsilon)
Build a new instance.
|
DihedralFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
Vector3D axis1,
double halfAperture1In,
Vector3D axis2,
double halfAperture2In,
double maxCheck,
EventDetector.Action entry,
EventDetector.Action exit)
Build a new instance.
|
DihedralFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
Vector3D axis1,
double halfAperture1In,
Vector3D axis2,
double halfAperture2In,
double maxCheck,
EventDetector.Action entry,
EventDetector.Action exit,
boolean removeEntry,
boolean removeExit)
Build a new instance.
|
DihedralFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
Vector3D axis1,
double halfAperture1In,
Vector3D axis2,
double halfAperture2In,
double maxCheck,
EventDetector.Action entry,
EventDetector.Action exit,
boolean removeEntry,
boolean removeExit,
double epsilon)
Build a new instance.
|
DihedralFieldOfViewDetector(PVCoordinatesProvider pvTarget,
Vector3D centerIn,
Vector3D axis1,
double halfAperture1In,
Vector3D axis2,
double halfAperture2In,
double maxCheck,
EventDetector.Action entry,
EventDetector.Action exit,
double epsilon)
Build a new instance.
|
| Modifier and Type | Method and Description |
|---|---|
void |
TimeDerivativesEquations.addAcceleration(Vector3D gamma,
Frame frame)
Add the contribution of an acceleration expressed in some inertial frame.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
VacuumSignalPropagation.getdPropdT()
Getter for the propagation velocity vector (= propagation vector derivative wrt time) in the
reference frame.
|
Vector3D |
VacuumSignalPropagation.getdPropdT(Frame expressionFrame)
Getter for the propagation velocity vector (= propagation vector derivative wrt time) in the
given frame.
|
Vector3D |
VacuumSignalPropagation.getdTpropdPem()
Getter for the signal propagation partial derivatives vector wrt the emitter position in the
reference frame at the emitting date.
|
Vector3D |
VacuumSignalPropagation.getdTpropdPem(Frame expressionFrame)
Getter for the signal propagation partial derivatives vector wrt the emitter position in the
specified frame at the emitting date.
|
Vector3D |
VacuumSignalPropagation.getdTpropdPrec()
Getter for the signal propagation partial derivatives vector wrt the receiver position in the
reference frame at the reception date.
|
Vector3D |
VacuumSignalPropagation.getdTpropdPrec(Frame expressionFrame)
Getter for the signal propagation partial derivatives vector wrt the receiver position in the
specified frame at the reception date.
|
Vector3D |
VacuumSignalPropagation.getVector()
Getter for the propagation vector in the reference frame.
|
Vector3D |
VacuumSignalPropagation.getVector(Frame expressionFrame)
Getter for the propagation vector in the given frame.
|
| Modifier and Type | Method and Description |
|---|---|
abstract double |
VacuumSignalPropagationModel.ConvergenceAlgorithm.computeTprop(double oldTprop,
Vector3D velEmitterOrReceptor,
Vector3D propagation)
Recompute the signal propagation duration with the convergence algorithm.
|
| 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 |
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.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.derivativeValue(Parameter p,
AbsoluteDate date,
Vector3D satellite,
Frame satFrame)
Compute the derivative value with respect to the input parameter.
|
double |
IonosphericCorrection.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,
BodyShape earth,
Vector3D station,
Frame frameSta)
Constructor for the Bent ionospheric correction model.
|
| Modifier and Type | Method and Description |
|---|---|
double |
GeodPosition.getGeodeticAltitude(Vector3D position)
Compute geodetic altitude.
|
double |
GeodPosition.getGeodeticLatitude(Vector3D position)
Compute geodetic latitude.
|
double |
GeodPosition.getGeodeticLongitude(Vector3D position,
AbsoluteDate date)
Compute the geodetic longitude at a given date.
|
double |
GeodPosition.getTloc(Vector3D position,
Vector3D positionSun,
AbsoluteDate date)
Compute the local solar time at a given date.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
MSIS00Adapter.getVelocity(AbsoluteDate date,
Vector3D position,
Frame frame)
Get the spacecraft velocity relative to the atmosphere.
|
| 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)
Get the spacecraft velocity relative to the atmosphere.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
StelaAeroModel.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Return the drag acceleration in the CIRF frame.
|
| Modifier and Type | Method and Description |
|---|---|
void |
StelaAeroModel.addDDragAccDParam(SpacecraftState s,
Parameter param,
double density,
Vector3D relativeVelocity,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters (the ballistic
coefficient).
|
void |
StelaAeroModel.addDDragAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel,
double density,
Vector3D acceleration,
Vector3D relativeVelocity,
boolean computeGradientPosition,
boolean computeGradientVelocity)
Compute acceleration derivatives with respect to state parameters (position and velocity).
|
Vector3D |
StelaAeroModel.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Return the drag acceleration in the CIRF frame.
|
double |
StelaCd.getCd(Vector3D position)
Compute the value of the Cd coefficient depending on spacecraft altitude.
|
| 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.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
SRPSquaring.computeAcceleration(StelaEquinoctialOrbit orbit,
PVCoordinates satSunVector)
Compute the acceleration due to the force.
|
protected Vector3D |
SRPSquaring.getFlux(Orbit orbit,
PVCoordinates satSunVect)
Get the solar flux vector.
|
| 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 |
|---|---|
static Vector3D |
AngularCoordinates.estimateRate(Rotation start,
Rotation end,
double dt)
Estimate rotation rate between two orientations.
|
Vector3D |
AngularCoordinates.getRotationAcceleration()
Get the rotation acceleration.
|
Vector3D |
AngularCoordinates.getRotationRate()
Get the rotation rate.
|
| Constructor and Description |
|---|
AngularCoordinates(Rotation rotationIn,
Vector3D rotationRateIn)
Builds a rotation/rotation rate triplet (acceleration set to
ZERO). |
AngularCoordinates(Rotation rotationIn,
Vector3D rotationRateIn,
Vector3D rotationAccelerationIn)
Builds a rotation/rotation rate/rotation acceleration triplet.
|
AngularCoordinates(Rotation rotationIn,
Vector3D rotationRateIn,
Vector3D rotationAccelerationIn,
boolean projectVelocityAndAcceleration)
Builds a rotation/rotation rate/rotation acceleration triplet.
|
TimeStampedAngularCoordinates(AbsoluteDate dateIn,
Rotation rotation,
Vector3D rotationRate,
Vector3D rotationAcceleration)
Builds a rotation/rotation rate pair.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
SolarRadiationWrench.computeTorque(SpacecraftState s)
Compute the resulting torque at the mass centre of the spacecraft in the frame of the main part.
|
Vector3D |
DragWrench.computeTorque(SpacecraftState s)
Compute the resulting torque at the mass centre of the spacecraft in the frame of the main part.
|
Vector3D |
GravitationalAttractionWrench.computeTorque(SpacecraftState s)
Compute the resulting torque at the mass centre of the spacecraft in the frame of the main part.
|
Vector3D |
MagneticWrench.computeTorque(SpacecraftState s)
Compute the resulting torque at the mass centre of the spacecraft in the frame of the main part.
|
Vector3D |
GenericWrenchModel.computeTorque(SpacecraftState s)
Compute the resulting torque at the mass centre of the spacecraft in the frame of the main part.
|
Vector3D |
WrenchModel.computeTorque(SpacecraftState s)
Compute the resulting torque at the mass centre of the spacecraft in the frame of the main part.
|
Vector3D |
SolarRadiationWrench.computeTorque(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
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 |
MagneticWrench.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 |
WrenchModel.computeTorque(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
Vector3D |
Wrench.getForce() |
Vector3D |
Wrench.getOrigin() |
protected Vector3D |
SolarRadiationWrench.getSatSunVector(SpacecraftState state)
Compute sat-Sun vector in spacecraft state frame.
|
Vector3D |
Wrench.getTorque() |
Vector3D |
Wrench.getTorque(Vector3D origin)
Get the torque expressed in another point.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
SolarRadiationWrench.computeTorque(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
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 |
MagneticWrench.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 |
WrenchModel.computeTorque(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench.
|
Wrench |
SolarRadiationWrench.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 |
GravitationalAttractionWrench.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 |
GenericWrenchModel.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 |
Wrench.displace(Vector3D newOrigin)
Displace current wrench.
|
static Wrench |
Wrench.displace(Wrench wrench,
Vector3D newOrigin)
Displace current wrench.
|
Wrench |
DragWrenchSensitive.dragWrench(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Compute the torque due to radiation pressire.
|
Wrench |
DragWrenchSensitive.dragWrench(SpacecraftState state,
double density,
Vector3D relativeVelocity,
Vector3D origin,
Frame frame)
Compute the torque due to radiation pressire.
|
Vector3D |
Wrench.getTorque(Vector3D origin)
Get the torque expressed in another point.
|
Wrench |
RadiationWrenchSensitive.radiationWrench(SpacecraftState state,
Vector3D flux)
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.
|
| Constructor and Description |
|---|
GenericWrenchModel(ForceModel force,
Vector3D origin)
Create a generic wrench model.
|
Wrench(Vector3D origin,
Vector3D force,
Vector3D torque)
Create a wrench with given force and torque.
|
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