Package | Description |
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fr.cnes.sirius.patrius.attitudes | |
fr.cnes.sirius.patrius.forces | |
fr.cnes.sirius.patrius.forces.maneuvers | |
fr.cnes.sirius.patrius.frames | |
fr.cnes.sirius.patrius.propagation |
Modifier and Type | Method and Description |
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LOFType |
LofOffset.getLofType()
Getter for the type of Local Orbital Frame.
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Constructor and Description |
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LofOffset(Frame inertialFrameIn,
LOFType typeIn)
Create a LOF-aligned attitude.
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LofOffset(Frame pInertialFrame,
LOFType typeIn,
RotationOrder order,
double alpha1,
double alpha2,
double alpha3)
Creates new instance.
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LofOffset(LOFType typeIn)
Create a LOF-aligned attitude.
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LofOffset(LOFType typeIn,
RotationOrder order,
double alpha1,
double alpha2,
double alpha3)
Creates new instance.
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Constructor and Description |
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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.
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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,
LOFType coeffsFrameLOFType)
Simple constructor for an empiric force.
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Modifier and Type | Method and Description |
---|---|
LOFType |
ImpulseManeuver.getLofType() |
LOFType |
ContinuousThrustManeuver.getLofType() |
Constructor and Description |
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ConstantThrustError(AbsoluteDate date,
double duration,
LOFType lofType,
double cx,
double cy,
double cz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx fy = cy fz = cz Errors components are expressed in provided local orbital frame. |
ConstantThrustError(AbsoluteDate date,
double duration,
LOFType lofType,
double ax,
double bx,
double ay,
double by,
double az,
double bz,
AbsoluteDate date0)
Create a constant thrust error model whose x, y and z components are linear functions:
fx = ax*t + bx fy = ay*t + by fz = az*t + bz Errors components are expressed in provided local orbital frame. |
ConstantThrustError(AbsoluteDate date,
double duration,
LOFType lofType,
IParamDiffFunction fx,
IParamDiffFunction fy,
IParamDiffFunction fz)
Create a constant thrust error model whose x, y and z components are parameterizable and differentiable function.
|
ConstantThrustError(AbsoluteDate date,
double duration,
LOFType lofType,
Parameter cx,
Parameter cy,
Parameter cz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx fy = cy fz = cz Errors components are expressed in provided local orbital frame. |
ConstantThrustError(AbsoluteDate date,
double duration,
LOFType lofType,
Parameter ax,
Parameter bx,
Parameter ay,
Parameter by,
Parameter az,
Parameter bz,
AbsoluteDate date0)
Create a constant thrust error model whose x, y and z components are linear functions:
fx = ax*t + bx fy = ay*t + by fz = az*t + bz Errors components are expressed in provided local orbital frame. |
ConstantThrustError(EventDetector startEventDetector,
EventDetector stopEventDetector,
LOFType lofType,
IParamDiffFunction fx,
IParamDiffFunction fy,
IParamDiffFunction fz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx fy = cy fz = cz Errors components are expressed in provided local orbital frame. |
ConstantThrustError(EventDetector startEventDetector,
EventDetector stopEventDetector,
LOFType lofType,
Parameter cx,
Parameter cy,
Parameter cz)
Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx fy = cy fz = cz Errors components are expressed in provided local orbital frame. |
ContinuousThrustManeuver(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> inDirection,
MassProvider massProvider,
TankProperty tank,
LOFType lofTyp)
Constructor for a variable direction in provided local orbital 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.
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ContinuousThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> inDirection,
MassProvider massProvider,
TankProperty tank,
LOFType lofTyp)
Constructor for a variable direction in local orbital frame.
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ContinuousThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
PropulsiveProperty engine,
Vector3D inDirection,
MassProvider massProvider,
TankProperty tank,
LOFType lofTyp)
Constructor for a constant direction in local orbital frame.
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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,
PropulsiveProperty engine,
MassProvider massModel,
TankProperty tank,
LOFType inLofType)
Build a new instance with a LocalOrbitalFrame and using propulsive and engine property.
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Modifier and Type | Method and Description |
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static LOFType |
LOFType.valueOf(String name)
Returns the enum constant of this type with the specified name.
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static LOFType[] |
LOFType.values()
Returns an array containing the constants of this enum type, in
the order they are declared.
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Constructor and Description |
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LocalOrbitalFrame(Frame parent,
LOFType type,
PVCoordinatesProvider provider,
String name)
Build a new instance.
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Modifier and Type | Method and Description |
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Attitude |
SpacecraftState.getAttitude(LOFType lofType)
Get the default attitude : the attitude for forces computation in given local
orbital frame.
|
Attitude |
SpacecraftState.getAttitudeEvents(LOFType lofType)
Get the attitude for events computation in given local orbital frame.
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Attitude |
SpacecraftState.getAttitudeForces(LOFType lofType)
Get the attitude for forces computation in given local orbital frame.
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Transform |
SpacecraftState.toTransform(Frame frame,
LOFType lofType)
Compute the transform from specified frame to local orbital frame.
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Transform |
SpacecraftState.toTransform(LOFType lofType)
Compute the transform from orbit/attitude reference frame to local orbital frame.
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