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Uses of SpacecraftState in fr.cnes.sirius.patrius.assembly |
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Methods in fr.cnes.sirius.patrius.assembly with parameters of type SpacecraftState | |
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void |
Assembly.initMainPartFrame(SpacecraftState state)
Initialize the main part's frame using a SpacecraftState as an input argument. |
void |
AssemblyBuilder.initMainPartFrame(SpacecraftState state)
Sets up the main frame of the assembly from a "SpacecraftState" object. |
void |
Assembly.updateMainPartFrame(SpacecraftState state)
Updates the main part frame's transformation to its parent frame using a Transform as an input argument. |
Uses of SpacecraftState in fr.cnes.sirius.patrius.assembly.models |
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Methods in fr.cnes.sirius.patrius.assembly.models with parameters of type SpacecraftState | |
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void |
RediffusedRadiativeModel.addDAccDParamRediffusedRadiativePressure(SpacecraftState s,
Parameter param,
double[] dAccdParam)
|
void |
RediffusedRadiativeModel.addDAccDStateRediffusedRadiativePressure(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
|
void |
DragLiftModel.addDDragAccDParam(SpacecraftState s,
Parameter param,
double density,
Vector3D relativeVelocity,
double[] dAccdParam)
Compute acceleration derivatives with respect to ballistic coefficient. |
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 |
AeroModel.addDDragAccDParam(SpacecraftState s,
Parameter param,
double density,
Vector3D relativeVelocity,
double[] dAccdParam)
Compute acceleration derivatives with respect to ballistic coefficient. |
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 |
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 |
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 |
DragLiftModel.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Method to compute the aero acceleration, based on the assembly. |
Vector3D |
GlobalAeroModel.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)
|
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,
Frame mainPartFrame)
Method to compute the force for a spherical model. |
double |
InertiaSimpleModel.getTotalMass(SpacecraftState state)
Return the mass of the spacecraft following the order. |
double |
InertiaComputedModel.getTotalMass(SpacecraftState state)
Return the mass of the spacecraft following the order. |
double |
MassModel.getTotalMass(SpacecraftState state)
Return the mass of the spacecraft following the order. |
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. |
Vector3D |
RediffusedRadiativeModel.rediffusedRadiationPressureAcceleration(SpacecraftState state,
ElementaryFlux flux)
Method to compute the rediffused radiation pressure acceleration, based on the assembly. |
Uses of SpacecraftState in fr.cnes.sirius.patrius.assembly.models.cook |
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Methods in fr.cnes.sirius.patrius.assembly.models.cook with parameters of type SpacecraftState | |
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double |
CtCookModel.derivativeValue(Parameter p,
SpacecraftState state)
Compute the derivative value with respect to the input parameter. |
double |
CnCookModel.derivativeValue(Parameter p,
SpacecraftState state)
Compute the derivative value with respect to the input parameter. |
double |
AlphaConstant.getAlpha(SpacecraftState state)
Return alpha (energy accomodation coefficient) value. |
double |
AlphaCookModel.getAlpha(SpacecraftState state)
Return alpha (energy accomodation coefficient) value. |
double |
AlphaProvider.getAlpha(SpacecraftState state)
Return alpha (energy accomodation coefficient) value. |
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. |
double |
CtCookModel.value(SpacecraftState state)
Getting the value of the function. |
double |
CnCookModel.value(SpacecraftState state)
Getting the value of the function. |
Uses of SpacecraftState in fr.cnes.sirius.patrius.assembly.properties |
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Methods in fr.cnes.sirius.patrius.assembly.properties that return types with arguments of type SpacecraftState | |
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IDependentVariable<SpacecraftState> |
PropulsiveProperty.getIsp()
Getter for the isp as an IDependentVariable object. |
IDependentVariable<SpacecraftState> |
PropulsiveProperty.getThrust()
Getter for the thrust as an IDependentVariable object. |
Methods in fr.cnes.sirius.patrius.assembly.properties with parameters of type SpacecraftState | |
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void |
MassEquation.computeDerivatives(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the derivatives related to the additional state parameters. |
double |
AeroSphereProperty.getCrossSection(SpacecraftState state,
Vector3D relativeVelocity,
Frame mainPartFrame,
Frame partFrame)
|
double |
RadiativeSphereProperty.getCrossSection(SpacecraftState state,
Vector3D flux,
Frame mainPartFrame,
Frame partFrame)
|
double |
RadiativeCrossSectionProperty.getCrossSection(SpacecraftState state,
Vector3D flux,
Frame mainPartFrame,
Frame partFrame)
Compute the cross section of main shape using the relative velocity in the part (having the aero property) frame as the direction to provider to the CrossSectionProvider.getCrossSection(Vector3D) . |
double |
AeroCrossSectionProperty.getCrossSection(SpacecraftState state,
Vector3D relativeVelocity,
Frame mainPartFrame,
Frame partFrame)
Compute the cross section of main shape using the relative velocity in the part (having the aero property) frame as the direction to provider to the CrossSectionProvider.getCrossSection(Vector3D) . |
double |
AeroCrossSectionProperty.getDragForceDerivativeValue(Parameter parameter,
SpacecraftState s)
Get the drag force coefficient derivative value with respect to the given parameter. |
double |
PropulsiveProperty.getIsp(SpacecraftState state)
Getter for isp (s) as function of input SpacecraftState . |
double |
PropulsiveProperty.getThrust(SpacecraftState state)
Getter for thrust force (N) as function of input SpacecraftState . |
Constructor parameters in fr.cnes.sirius.patrius.assembly.properties with type arguments of type SpacecraftState | |
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PropulsiveProperty(String inName,
IDependentVariable<SpacecraftState> inThrust,
IDependentVariable<SpacecraftState> inIsp)
Constructor for the property with thrust and isp as IDependentVariable . |
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PropulsiveProperty(String inName,
IDependentVariable<SpacecraftState> inThrust,
IDependentVariable<SpacecraftState> inIsp)
Constructor for the property with thrust and isp as IDependentVariable . |
Uses of SpacecraftState in fr.cnes.sirius.patrius.events |
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Methods in fr.cnes.sirius.patrius.events that return SpacecraftState | |
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SpacecraftState |
CodedEventsLogger.LoggedCodedEvent.getState()
Gets the SpacecraftState that caused the coded event. |
SpacecraftState |
GenericCodingEventDetector.resetState(SpacecraftState oldState)
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Methods in fr.cnes.sirius.patrius.events with parameters of type SpacecraftState | |
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CodedEvent |
CodingEventDetector.buildCodedEvent(SpacecraftState s,
boolean increasing)
Build a CodedEvent instance appropriate for the provided SpacecraftState . |
CodedEvent |
GenericCodingEventDetector.buildCodedEvent(SpacecraftState s,
boolean increasing)
|
CodedEvent |
CodingEventDetector.buildDelayedCodedEvent(SpacecraftState s,
boolean increasing)
Build a delayed CodedEvent instance appropriate for the provided SpacecraftState . |
CodedEvent |
GenericCodingEventDetector.buildDelayedCodedEvent(SpacecraftState s,
boolean increasing)
|
CodedEvent |
CodingEventDetector.buildOccurrenceCodedEvent(SpacecraftState s,
boolean increasing)
Build a CodedEvent instance appropriate for the provided SpacecraftState . |
CodedEvent |
GenericCodingEventDetector.buildOccurrenceCodedEvent(SpacecraftState s,
boolean increasing)
|
Map<CodingEventDetector,PhenomenaList> |
CodedEventsLogger.buildPhenomenaListMap(AbsoluteDateInterval definitionInterval,
SpacecraftState duringState)
Builds a map of PhenomenaList , one list per CodingEventDetector instance. |
EventDetector.Action |
EarthZoneDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle the event and choose what to do next. |
EventDetector.Action |
CombinedPhenomenaDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next. |
EventDetector.Action |
GenericCodingEventDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
|
EventDetector.Action |
CentralBodyMaskCircularFOVDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle a target in field of view outside eclipse reaching event and choose what to do next. |
double |
EarthZoneDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
CombinedPhenomenaDetector.g(SpacecraftState s)
Compute the value of the switching function for a combination (AND or OR) of two phenomena. After computing the switching function of each detector and, if necessary, changing its sign to apply a general convention (g>0 if the phenomenon associated to an event is active), it returns one between the two g functions, according to the boolean operator. |
double |
GenericCodingEventDetector.g(SpacecraftState s)
|
double |
CentralBodyMaskCircularFOVDetector.g(SpacecraftState s)
The switching function is the minimum value between the eclipse detector g function and the circularFOVDetector |
void |
EarthZoneDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
CombinedPhenomenaDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
GenericCodingEventDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
boolean |
GenericCodingEventDetector.isStateActive(SpacecraftState state)
Tells if the event state is "active" for the given input. |
SpacecraftState |
GenericCodingEventDetector.resetState(SpacecraftState oldState)
|
Uses of SpacecraftState in fr.cnes.sirius.patrius.events.multi |
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Methods in fr.cnes.sirius.patrius.events.multi that return types with arguments of type SpacecraftState | |
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Map<String,SpacecraftState> |
MultiCodedEventsLogger.MultiLoggedCodedEvent.getStates()
Gets the map of SpacecraftState that caused the coded event. |
Map<String,SpacecraftState> |
MultiEventsLogger.MultiLoggedEvent.getStates()
Get the triggering states. |
Map<String,SpacecraftState> |
MultiGenericCodingEventDetector.resetStates(Map<String,SpacecraftState> oldStates)
|
Method parameters in fr.cnes.sirius.patrius.events.multi with type arguments of type SpacecraftState | |
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CodedEvent |
MultiGenericCodingEventDetector.buildCodedEvent(Map<String,SpacecraftState> states,
boolean increasing)
|
CodedEvent |
MultiCodingEventDetector.buildCodedEvent(Map<String,SpacecraftState> s,
boolean increasing)
Build a CodedEvent instance appropriate for the provided map of SpacecraftState . |
CodedEvent |
MultiGenericCodingEventDetector.buildDelayedCodedEvent(Map<String,SpacecraftState> states,
boolean increasing)
|
CodedEvent |
MultiCodingEventDetector.buildDelayedCodedEvent(Map<String,SpacecraftState> s,
boolean increasing)
Build a delayed CodedEvent instance appropriate for the provided map of SpacecraftState . |
CodedEvent |
MultiGenericCodingEventDetector.buildOccurrenceCodedEvent(Map<String,SpacecraftState> states,
boolean increasing)
|
CodedEvent |
MultiCodingEventDetector.buildOccurrenceCodedEvent(Map<String,SpacecraftState> s,
boolean increasing)
Build a CodedEvent instance appropriate for the provided map of SpacecraftState . |
Map<MultiCodingEventDetector,PhenomenaList> |
MultiCodedEventsLogger.buildPhenomenaListMap(AbsoluteDateInterval definitionInterval,
Map<String,SpacecraftState> duringState)
Builds a map of PhenomenaList , one list per MultiCodingEventDetector instance. |
EventDetector.Action |
MultiGenericCodingEventDetector.eventOccurred(Map<String,SpacecraftState> s,
boolean increasing,
boolean forward)
|
double |
MultiGenericCodingEventDetector.g(Map<String,SpacecraftState> s)
|
void |
MultiGenericCodingEventDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
|
boolean |
MultiGenericCodingEventDetector.isStateActive(Map<String,SpacecraftState> states)
Tells if the multi event state is "active" for the given input. |
Map<String,SpacecraftState> |
MultiGenericCodingEventDetector.resetStates(Map<String,SpacecraftState> oldStates)
|
Uses of SpacecraftState in fr.cnes.sirius.patrius.events.sensor |
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Methods in fr.cnes.sirius.patrius.events.sensor that return types with arguments of type SpacecraftState | |
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Map<String,SpacecraftState> |
SatToSatMutualVisibilityDetector.resetStates(Map<String,SpacecraftState> oldStates)
|
Methods in fr.cnes.sirius.patrius.events.sensor with parameters of type SpacecraftState | |
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EventDetector.Action |
SatToSatMutualVisibilityDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
|
EventDetector.Action |
MaskingDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle "masking" event and choose what to do next. |
EventDetector.Action |
ExtremaSightAxisDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next. |
EventDetector.Action |
SensorVisibilityDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
|
EventDetector.Action |
VisibilityFromStationDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle "visibility from station" event and choose what to do next. |
EventDetector.Action |
TargetInFieldOfViewDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
|
EventDetector.Action |
RFVisibilityDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
|
EventDetector.Action |
StationToSatMutualVisibilityDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
|
EventDetector.Action |
SensorInhibitionDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
|
double |
SatToSatMutualVisibilityDetector.g(SpacecraftState s)
|
double |
MaskingDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
ExtremaSightAxisDetector.g(SpacecraftState s)
The switching function is specific case of the extrema three bodies angle detector. |
double |
SensorVisibilityDetector.g(SpacecraftState s)
|
double |
VisibilityFromStationDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
TargetInFieldOfViewDetector.g(SpacecraftState s)
|
double |
RFVisibilityDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
StationToSatMutualVisibilityDetector.g(SpacecraftState s)
|
double |
SensorInhibitionDetector.g(SpacecraftState s)
|
protected Vector3D |
AbstractDetectorWithTropoCorrection.getCorrectedVector(SpacecraftState s)
Compute the apparent vector from the station to the spacecraft with tropospheric effects. |
void |
SatToSatMutualVisibilityDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
MaskingDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
void |
ExtremaSightAxisDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
SensorVisibilityDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
VisibilityFromStationDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
void |
TargetInFieldOfViewDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
StationToSatMutualVisibilityDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
SensorInhibitionDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
Method parameters in fr.cnes.sirius.patrius.events.sensor with type arguments of type SpacecraftState | |
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EventDetector.Action |
SatToSatMutualVisibilityDetector.eventOccurred(Map<String,SpacecraftState> s,
boolean increasing,
boolean forward)
|
double |
SatToSatMutualVisibilityDetector.g(Map<String,SpacecraftState> s)
|
void |
SatToSatMutualVisibilityDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
|
Map<String,SpacecraftState> |
SatToSatMutualVisibilityDetector.resetStates(Map<String,SpacecraftState> oldStates)
|
Uses of SpacecraftState in fr.cnes.sirius.patrius.forces |
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Methods in fr.cnes.sirius.patrius.forces with parameters of type SpacecraftState | |
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void |
ConstantThrustManeuver.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
void |
EmpiricalForce.addContribution(SpacecraftState state,
TimeDerivativesEquations adder)
|
void |
VariableThrustManeuver.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
void |
ConstantThrustManeuver.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
EmpiricalForce.addDAccDParam(SpacecraftState state,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
VariableThrustManeuver.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
ConstantThrustManeuver.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
void |
EmpiricalForce.addDAccDState(SpacecraftState state,
double[][] dAccdPos,
double[][] dAccdVel)
|
void |
VariableThrustManeuver.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
Vector3D |
EmpiricalForce.computeAcceleration(PVCoordinates pv,
LocalOrbitalFrame localFrameValidation,
Vector3D vectorS,
Frame frame,
SpacecraftState state)
Method to compute the acceleration. |
Vector3D |
ConstantThrustManeuver.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force. |
Vector3D |
EmpiricalForce.computeAcceleration(SpacecraftState state)
|
Vector3D |
VariableThrustManeuver.computeAcceleration(SpacecraftState s)
|
Vector3D |
VariableThrustManeuver.getDirection(SpacecraftState s)
Get the thrust direction. |
double |
VariableThrustManeuver.getFlowRate(SpacecraftState s)
Get the flow rate. |
double |
VariableThrustManeuver.getISP(SpacecraftState s)
Get the specific impulse. |
double |
VariableThrustManeuver.getThrust(SpacecraftState s)
Get the thrust. |
Constructor parameters in fr.cnes.sirius.patrius.forces with type arguments of type SpacecraftState | |
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VariableThrustManeuver(AbsoluteDate date,
double duration,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName)
Constructor for a variable direction in spacecraft frame, thrust and ISP. |
|
VariableThrustManeuver(AbsoluteDate date,
double duration,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName)
Constructor for a variable direction in spacecraft frame, thrust and ISP. |
|
VariableThrustManeuver(AbsoluteDate date,
double duration,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName)
Constructor for a variable direction in spacecraft frame, thrust and ISP. |
|
VariableThrustManeuver(AbsoluteDate date,
double duration,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName,
Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP. |
|
VariableThrustManeuver(AbsoluteDate date,
double duration,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName,
Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP. |
|
VariableThrustManeuver(AbsoluteDate date,
double duration,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName,
Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP. |
|
VariableThrustManeuver(AbsoluteDate date,
double duration,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName,
LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame, thrust and ISP expressed in a LocalOrbitalFrame . |
|
VariableThrustManeuver(AbsoluteDate date,
double duration,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName,
LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame, thrust and ISP expressed in a LocalOrbitalFrame . |
|
VariableThrustManeuver(AbsoluteDate date,
double duration,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName,
LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame, thrust and ISP expressed in a LocalOrbitalFrame . |
|
VariableThrustManeuver(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
TankProperty tank)
Constructor for a variable direction in spacecraft frame, thrust and ISP, using PropulsiveProperty and TankProperty . |
|
VariableThrustManeuver(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
TankProperty tank,
Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP, using PropulsiveProperty and TankProperty . |
|
VariableThrustManeuver(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
TankProperty tank,
LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame, thrust and ISP expressed in a LocalOrbitalFrame , using PropulsiveProperty and TankProperty . |
|
VariableThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName)
Constructor for a variable direction in spacecraft frame, thrust and ISP. |
|
VariableThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName)
Constructor for a variable direction in spacecraft frame, thrust and ISP. |
|
VariableThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName)
Constructor for a variable direction in spacecraft frame, thrust and ISP. |
|
VariableThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName,
Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP. |
|
VariableThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName,
Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP. |
|
VariableThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName,
Frame refFrame)
Constructor for a variable direction in provided frame, thrust and ISP. |
|
VariableThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName,
LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame, thrust and ISP expressed in a LocalOrbitalFrame . |
|
VariableThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName,
LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame, thrust and ISP expressed in a LocalOrbitalFrame . |
|
VariableThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
IDependentVariable<SpacecraftState> variableThrust,
IDependentVariable<SpacecraftState> variableIsp,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
String partName,
LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame, thrust and ISP expressed in a LocalOrbitalFrame . |
|
VariableThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
TankProperty tank)
Constructor for a variable direction in spacecraft frame, thrust and ISP, using PropulsiveProperty
and TankProperty . |
|
VariableThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
TankProperty tank,
Frame refFrame)
Constructor for a variable direction in spacecraft frame, thrust and ISP, using PropulsiveProperty
and TankProperty . |
|
VariableThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> variableDirection,
MassProvider massModel,
TankProperty tank,
LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame, thrust and ISP expressed in a LocalOrbitalFrame . |
Uses of SpacecraftState in fr.cnes.sirius.patrius.forces.radiation |
---|
Methods in fr.cnes.sirius.patrius.forces.radiation with parameters of type SpacecraftState | |
---|---|
void |
PatriusSolarRadiationPressure.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
|
void |
PatriusSolarRadiationPressure.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
|
void |
PatriusSolarRadiationPressure.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
|
Vector3D |
PatriusSolarRadiationPressure.computeAcceleration(SpacecraftState s)
|
Uses of SpacecraftState in fr.cnes.sirius.patrius.propagation |
---|
Methods in fr.cnes.sirius.patrius.propagation that return types with arguments of type SpacecraftState | |
---|---|
Map<String,SpacecraftState> |
MultiPropagator.getInitialStates()
Get the propagator initial states. |
Map<String,SpacecraftState> |
MultiPropagator.propagate(AbsoluteDate target)
Propagate towards a target date. |
Map<String,SpacecraftState> |
MultiPropagator.propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date. |
Methods in fr.cnes.sirius.patrius.propagation with parameters of type SpacecraftState | |
---|---|
void |
MultiPropagator.addInitialState(SpacecraftState initialState,
String satId)
Add a new spacecraft state to be propagated. |
Uses of SpacecraftState in fr.cnes.sirius.patrius.propagation.events.multi |
---|
Methods in fr.cnes.sirius.patrius.propagation.events.multi that return types with arguments of type SpacecraftState | |
---|---|
Map<String,SpacecraftState> |
OneSatEventDetectorWrapper.resetStates(Map<String,SpacecraftState> oldStates)
|
Map<String,SpacecraftState> |
MultiAbstractDetector.resetStates(Map<String,SpacecraftState> oldStates)
|
Method parameters in fr.cnes.sirius.patrius.propagation.events.multi with type arguments of type SpacecraftState | |
---|---|
EventDetector.Action |
OneSatEventDetectorWrapper.eventOccurred(Map<String,SpacecraftState> s,
boolean increasing,
boolean forward)
|
abstract EventDetector.Action |
MultiAbstractDetector.eventOccurred(Map<String,SpacecraftState> s,
boolean increasing,
boolean forward)
|
double |
OneSatEventDetectorWrapper.g(Map<String,SpacecraftState> s)
|
abstract double |
MultiAbstractDetector.g(Map<String,SpacecraftState> s)
|
void |
OneSatEventDetectorWrapper.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
|
void |
MultiAbstractDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
|
Map<String,SpacecraftState> |
OneSatEventDetectorWrapper.resetStates(Map<String,SpacecraftState> oldStates)
|
Map<String,SpacecraftState> |
MultiAbstractDetector.resetStates(Map<String,SpacecraftState> oldStates)
|
Uses of SpacecraftState in fr.cnes.sirius.patrius.propagation.numerical.multi |
---|
Methods in fr.cnes.sirius.patrius.propagation.numerical.multi that return SpacecraftState | |
---|---|
SpacecraftState |
MultiStateVectorInfo.mapArrayToState(double[] y,
AbsoluteDate currentDate,
OrbitType orbitType,
PositionAngle angleType,
AttitudeProvider attProviderForces,
AttitudeProvider attProviderEvents,
double mu,
Frame integrationFrame,
String satId)
Extract a given SpacecraftState from the state vector. |
Methods in fr.cnes.sirius.patrius.propagation.numerical.multi that return types with arguments of type SpacecraftState | |
---|---|
Map<String,SpacecraftState> |
MultiNumericalPropagator.getInitialStates()
|
Map<String,SpacecraftState> |
MultiStateVectorInfo.mapArrayToStates(double[] y,
AbsoluteDate currentDate,
OrbitType orbitType,
PositionAngle angleType,
Map<String,AttitudeProvider> attProvidersForces,
Map<String,AttitudeProvider> attProvidersEvents,
Map<String,Double> mu,
Map<String,Frame> integrationFrame)
Convert state vector into a Map of SpacecraftState |
Map<String,SpacecraftState> |
MultiNumericalPropagator.propagate(AbsoluteDate target)
|
Map<String,SpacecraftState> |
MultiNumericalPropagator.propagate(AbsoluteDate start,
AbsoluteDate target)
|
Methods in fr.cnes.sirius.patrius.propagation.numerical.multi with parameters of type SpacecraftState | |
---|---|
void |
MultiNumericalPropagator.addInitialState(SpacecraftState initialState,
String satId)
|
Method parameters in fr.cnes.sirius.patrius.propagation.numerical.multi with type arguments of type SpacecraftState | |
---|---|
void |
MultiStateVectorInfo.mapStatesToArray(Map<String,SpacecraftState> s,
OrbitType orbitType,
PositionAngle angleType,
double[] y)
Convert a map of SpacecraftState into a state vector. |
Constructor parameters in fr.cnes.sirius.patrius.propagation.numerical.multi with type arguments of type SpacecraftState | |
---|---|
MultiStateVectorInfo(Map<String,SpacecraftState> s)
Build a MultiSatStateVectorInfo instance using the spacecraft states' map. |
Uses of SpacecraftState in fr.cnes.sirius.patrius.propagation.precomputed.multi |
---|
Methods in fr.cnes.sirius.patrius.propagation.precomputed.multi that return SpacecraftState | |
---|---|
protected SpacecraftState |
MultiIntegratedEphemeris.basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features. |
SpacecraftState |
MultiIntegratedEphemeris.getInitialState()
Get the propagator initial state. |
Methods in fr.cnes.sirius.patrius.propagation.precomputed.multi with parameters of type SpacecraftState | |
---|---|
void |
MultiIntegratedEphemeris.resetInitialState(SpacecraftState state)
Reset the propagator initial state. |
Uses of SpacecraftState in fr.cnes.sirius.patrius.propagation.sampling.multi |
---|
Methods in fr.cnes.sirius.patrius.propagation.sampling.multi that return types with arguments of type SpacecraftState | |
---|---|
Map<String,SpacecraftState> |
MultiOrekitStepInterpolator.getInterpolatedStates()
Get all the interpolated states. |
Map<String,SpacecraftState> |
MultiAdaptedStepHandler.getInterpolatedStates()
Get all the interpolated states. |
Method parameters in fr.cnes.sirius.patrius.propagation.sampling.multi with type arguments of type SpacecraftState | |
---|---|
void |
MultiOrekitFixedStepHandler.handleStep(Map<String,SpacecraftState> currentStates,
boolean isLast)
Handle the current step. |
void |
MultiOrekitStepNormalizer.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
void |
MultiOrekitStepHandler.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
void |
MultiOrekitFixedStepHandler.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
Uses of SpacecraftState in fr.cnes.sirius.patrius.stela |
---|
Methods in fr.cnes.sirius.patrius.stela with parameters of type SpacecraftState | |
---|---|
EventDetector.Action |
PerigeeAltitudeDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an altitude event and choose what to do next. |
double |
PerigeeAltitudeDetector.g(SpacecraftState s)
Compute the value of the switching function. |
Uses of SpacecraftState in fr.cnes.sirius.patrius.stela.forces.drag |
---|
Methods in fr.cnes.sirius.patrius.stela.forces.drag with parameters of type SpacecraftState | |
---|---|
void |
StelaAeroModel.addDDragAccDParam(SpacecraftState s,
Parameter param,
double density,
Vector3D relativeVelocity,
double[] dAccdParam)
|
void |
StelaAeroModel.addDDragAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel,
double density,
Vector3D acceleration,
Vector3D relativeVelocity,
boolean computeGradientPosition,
boolean computeGradientVelocity)
|
Vector3D |
StelaAeroModel.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Return the drag acceleration in the CIRF frame. |
Uses of SpacecraftState in fr.cnes.sirius.patrius.stela.propagation |
---|
Methods in fr.cnes.sirius.patrius.stela.propagation that return SpacecraftState | |
---|---|
protected SpacecraftState |
StelaAbstractPropagator.acceptStep(AbsoluteDate target,
double epsilon)
Accept a step, triggering events and step handlers. |
SpacecraftState |
StelaPartialDerivativesEquations.addInitialAdditionalState(SpacecraftState state)
|
SpacecraftState |
StelaAdditionalEquations.addInitialAdditionalState(SpacecraftState state)
|
protected SpacecraftState |
StelaAbstractPropagator.basicPropagate(AbsoluteDate date)
Propagate a SpacecraftState without any fancy features. |
SpacecraftState |
StelaAbstractPropagator.getInitialState()
Get the propagator initial state. |
SpacecraftState |
StelaBasicInterpolator.getInitialState()
|
SpacecraftState |
StelaBasicInterpolator.getInterpolatedState()
Get the interpolated state. |
SpacecraftState |
StelaAbstractPropagator.goAhead(double stepSize,
double dt,
AbsoluteDate target)
go one step ahead |
SpacecraftState |
StelaAbstractPropagator.propagate(AbsoluteDate target)
Propagate towards a target date. |
SpacecraftState |
StelaAbstractPropagator.propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date. |
SpacecraftState |
StelaGTOPropagator.propagate(AbsoluteDate start,
AbsoluteDate target)
|
protected abstract SpacecraftState |
StelaAbstractPropagator.propagateSpacecraftState(AbsoluteDate date)
Extrapolate a spacecraftState up to a specific target date. |
protected SpacecraftState |
StelaGTOPropagator.propagateSpacecraftState(AbsoluteDate date)
|
SpacecraftState |
StelaAbstractPropagator.propagationManagement(SpacecraftState state,
double stepSize,
double dt,
AbsoluteDate target)
Manages the current step, method to override when user wants to deal with exceptions during the propagation. |
SpacecraftState |
StelaGTOPropagator.propagationManagement(SpacecraftState state,
double stepSize,
double dt,
AbsoluteDate target)
|
Methods in fr.cnes.sirius.patrius.stela.propagation with parameters of type SpacecraftState | |
---|---|
SpacecraftState |
StelaPartialDerivativesEquations.addInitialAdditionalState(SpacecraftState state)
|
SpacecraftState |
StelaAdditionalEquations.addInitialAdditionalState(SpacecraftState state)
|
void |
ForcesStepHandler.init(SpacecraftState s0,
AbsoluteDate t)
|
SpacecraftState |
StelaAbstractPropagator.propagationManagement(SpacecraftState state,
double stepSize,
double dt,
AbsoluteDate target)
Manages the current step, method to override when user wants to deal with exceptions during the propagation. |
SpacecraftState |
StelaGTOPropagator.propagationManagement(SpacecraftState state,
double stepSize,
double dt,
AbsoluteDate target)
|
void |
StelaAbstractPropagator.resetInitialState(SpacecraftState state)
Reset the propagator initial state. |
void |
StelaGTOPropagator.setInitialState(SpacecraftState initialState,
double massIn,
boolean isOsculatingIn)
Set the initial state. |
void |
StelaBasicInterpolator.storeSC(SpacecraftState initialStateIn,
SpacecraftState targetState)
Store the current dates and spacecraft states. |
Uses of SpacecraftState in fr.cnes.sirius.patrius.wrenches |
---|
Methods in fr.cnes.sirius.patrius.wrenches with parameters of type SpacecraftState | |
---|---|
Vector3D |
SolarRadiationWrench.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 |
DragWrench.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 |
MagneticWrench.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 |
GravitationalAttractionWrench.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 |
GenericWrenchModel.computeTorque(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench. |
Vector3D |
MagneticWrench.computeTorque(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench. |
Wrench |
SolarRadiationWrench.computeWrench(SpacecraftState s)
Compute the resulting wrench at the mass centre of the spacecraft in the frame of the main part. |
Wrench |
GravitationalAttractionWrench.computeWrench(SpacecraftState s)
Compute the resulting wrench at the mass centre of the spacecraft in the frame of the main part. |
Wrench |
DragWrench.computeWrench(SpacecraftState s)
Compute the resulting wrench at the mass centre of the spacecraft in the frame of the main part. |
Wrench |
GenericWrenchModel.computeWrench(SpacecraftState s)
Compute the resulting wrench at the mass centre of the spacecraft in the frame of the main part. |
Wrench |
MagneticWrench.computeWrench(SpacecraftState s)
Compute the resulting wrench at the mass centre of the spacecraft in the frame of the main part. |
Wrench |
SolarRadiationWrench.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 |
DragWrench.computeWrench(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench. |
Wrench |
GenericWrenchModel.computeWrench(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench. |
Wrench |
MagneticWrench.computeWrench(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench. |
Wrench |
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. |
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. |
Uses of SpacecraftState in fr.cnes.sirius.validate.files |
---|
Method parameters in fr.cnes.sirius.validate.files with type arguments of type SpacecraftState | |
---|---|
static void |
ResultsFileWriter.writeResultsToVTS(String thematic,
String useCase,
String orbitComment,
String attitudeComment,
List<SpacecraftState> results)
Method to write the attitudes and positions files used by VTS visualization tool. |
Uses of SpacecraftState in org.orekit.forces |
---|
Methods in org.orekit.forces with parameters of type SpacecraftState | |
---|---|
void |
ForceModel.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
Vector3D |
ForceModel.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force. |
Uses of SpacecraftState in org.orekit.forces.drag |
---|
Methods in org.orekit.forces.drag with parameters of type SpacecraftState | |
---|---|
void |
DragForce.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the drag to the perturbing acceleration. |
void |
DragForce.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
DragForce.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
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 |
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. |
Uses of SpacecraftState in org.orekit.forces.gravity |
---|
Methods in org.orekit.forces.gravity with parameters of type SpacecraftState | |
---|---|
void |
BalminoAttractionModel.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
void |
DrozinerAttractionModel.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
void |
ThirdBodyAttraction.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
void |
CunninghamAttractionModel.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
void |
NewtonianAttraction.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
void |
BalminoAttractionModel.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
ThirdBodyAttraction.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
CunninghamAttractionModel.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
NewtonianAttraction.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
BalminoAttractionModel.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
void |
ThirdBodyAttraction.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
void |
CunninghamAttractionModel.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
void |
NewtonianAttraction.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
Vector3D |
BalminoAttractionModel.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force. |
Vector3D |
DrozinerAttractionModel.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force. |
Vector3D |
ThirdBodyAttraction.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force. |
Vector3D |
CunninghamAttractionModel.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force. |
Vector3D |
NewtonianAttraction.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force. |
Uses of SpacecraftState in org.orekit.forces.gravity.tides |
---|
Methods in org.orekit.forces.gravity.tides with parameters of type SpacecraftState | |
---|---|
void |
AbstractTides.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
void |
AbstractTides.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
AbstractTides.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
Vector3D |
AbstractTides.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force. |
Uses of SpacecraftState in org.orekit.forces.gravity.variations |
---|
Methods in org.orekit.forces.gravity.variations with parameters of type SpacecraftState | |
---|---|
void |
VariablePotentialAttractionModel.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
void |
VariablePotentialAttractionModel.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
VariablePotentialAttractionModel.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
|
Vector3D |
VariablePotentialAttractionModel.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force. |
Uses of SpacecraftState in org.orekit.forces.maneuvers |
---|
Methods in org.orekit.forces.maneuvers that return SpacecraftState | |
---|---|
SpacecraftState |
SmallManeuverAnalyticalModel.apply(SpacecraftState state1)
Compute the effect of the maneuver on a spacecraft state. |
SpacecraftState |
ImpulseManeuver.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation. |
Methods in org.orekit.forces.maneuvers with parameters of type SpacecraftState | |
---|---|
void |
ConstantThrustError.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the constant thrust error model to the perturbing acceleration. |
void |
ConstantThrustError.addDAccDParam(SpacecraftState state,
Parameter param,
double[] dAccdParam)
|
void |
ConstantThrustError.addDAccDState(SpacecraftState state,
double[][] dAccdPos,
double[][] dAccdVel)
|
SpacecraftState |
SmallManeuverAnalyticalModel.apply(SpacecraftState state1)
Compute the effect of the maneuver on a spacecraft state. |
Vector3D |
ConstantThrustError.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force. |
EventDetector.Action |
ImpulseManeuver.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next. |
double |
ImpulseManeuver.g(SpacecraftState s)
Compute the value of the switching function. |
void |
ImpulseManeuver.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
SpacecraftState |
ImpulseManeuver.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation. |
Constructors in org.orekit.forces.maneuvers with parameters of type SpacecraftState | |
---|---|
SmallManeuverAnalyticalModel(SpacecraftState state0,
Frame frame,
Vector3D dV,
double isp,
String partName)
Build a maneuver defined in user-specified frame. |
|
SmallManeuverAnalyticalModel(SpacecraftState state0,
Vector3D dV,
double isp,
String partName)
Build a maneuver defined in spacecraft frame. |
Uses of SpacecraftState in org.orekit.forces.radiation |
---|
Methods in org.orekit.forces.radiation with parameters of type SpacecraftState | |
---|---|
void |
RediffusedRadiationPressure.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
void |
SolarRadiationPressure.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
void |
RediffusedRadiationPressure.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
SolarRadiationPressure.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
RediffusedRadiationSensitive.addDAccDParamRediffusedRadiativePressure(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives. |
void |
RediffusedRadiationPressure.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
void |
SolarRadiationPressure.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
void |
RediffusedRadiationSensitive.addDAccDStateRediffusedRadiativePressure(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives. |
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. |
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 |
RadiationSensitive.radiationPressureAcceleration(SpacecraftState state,
Vector3D flux)
Compute the acceleration due to radiation pressure. |
Vector3D |
RediffusedRadiationSensitive.rediffusedRadiationPressureAcceleration(SpacecraftState state,
ElementaryFlux flux)
rediffused radiative pressure acceleration |
Uses of SpacecraftState in org.orekit.forces.relativistic |
---|
Methods in org.orekit.forces.relativistic with parameters of type SpacecraftState | |
---|---|
void |
SchwarzschildRelativisticEffect.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
void |
LenseThirringRelativisticEffect.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
void |
CoriolisRelativisticEffect.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
void |
SchwarzschildRelativisticEffect.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
LenseThirringRelativisticEffect.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
CoriolisRelativisticEffect.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
SchwarzschildRelativisticEffect.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
void |
LenseThirringRelativisticEffect.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
void |
CoriolisRelativisticEffect.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
Vector3D |
SchwarzschildRelativisticEffect.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force. |
Vector3D |
LenseThirringRelativisticEffect.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force. |
Vector3D |
CoriolisRelativisticEffect.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force. |
Uses of SpacecraftState in org.orekit.parameter |
---|
Methods in org.orekit.parameter with parameters of type SpacecraftState | |
---|---|
void |
IJacobiansParameterizable.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
IJacobiansParameterizable.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
double |
PiecewiseFunction.derivativeValue(Parameter p,
SpacecraftState s)
Compute the derivative value with respect to the input parameter. |
double |
IParamDiffFunction.derivativeValue(Parameter p,
SpacecraftState s)
Compute the derivative value with respect to the input parameter. |
double |
ConstantFunction.derivativeValue(Parameter p,
SpacecraftState state)
Compute the derivative value with respect to the input parameter. |
double |
LinearFunction.derivativeValue(Parameter p,
SpacecraftState state)
Compute the derivative value with respect to the input parameter. |
double |
IParameterizableFunction.value(SpacecraftState state)
Getting the value of the function. |
double |
PiecewiseFunction.value(SpacecraftState s)
Getting the value of the function. |
double |
ConstantFunction.value(SpacecraftState s)
Getting the value of the function. |
double |
LinearFunction.value(SpacecraftState s)
Getting the value of the function. |
Uses of SpacecraftState in org.orekit.propagation |
---|
Methods in org.orekit.propagation that return SpacecraftState | |
---|---|
protected SpacecraftState |
AbstractPropagator.acceptStep(AbsoluteDate target,
double epsilon)
Accept a step, triggering events and step handlers. |
SpacecraftState |
SpacecraftState.addAdditionalState(String name,
double[] state)
Add an additional state to the additional states map. |
SpacecraftState |
SpacecraftState.addAttitude(Attitude newAttitude,
AttitudeEquation.AttitudeType type)
Add attitude to the additional states map. |
SpacecraftState |
SpacecraftState.addAttitudeToAdditionalStates(AttitudeEquation.AttitudeType attitudeType)
Add attitude to the additional states map. |
SpacecraftState |
SpacecraftState.addMassProvider(MassProvider massProvider)
Add the values of mass parts from MassProvider to additional states map. |
protected SpacecraftState |
AbstractPropagator.basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features. |
SpacecraftState |
OsculatingToMeanElementsConverter.convert()
Convert an osculating orbit into a mean orbit, in DSST sense. |
SpacecraftState |
Propagator.getInitialState()
Get the propagator initial state. |
SpacecraftState |
AbstractPropagator.getInitialState()
Get the propagator initial state. |
SpacecraftState |
SpacecraftState.interpolate(AbsoluteDate date,
Collection<SpacecraftState> sample)
Get an interpolated instance. |
SpacecraftState |
AnalyticalIntegratedEphemeris.propagate(AbsoluteDate target)
Propagate towards a target date. |
SpacecraftState |
Propagator.propagate(AbsoluteDate target)
Propagate towards a target date. |
SpacecraftState |
AbstractPropagator.propagate(AbsoluteDate target)
Propagate towards a target date. |
SpacecraftState |
AnalyticalIntegratedEphemeris.propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date. |
SpacecraftState |
Propagator.propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date. |
SpacecraftState |
AbstractPropagator.propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date. |
SpacecraftState |
SpacecraftState.shiftedBy(double dt)
Get a time-shifted state. |
SpacecraftState |
SpacecraftState.updateMass(String partName,
double newMass)
Update the mass of the given part. |
SpacecraftState |
SpacecraftState.updateOrbit(Orbit newOrbit)
Update the orbit. |
Methods in org.orekit.propagation with parameters of type SpacecraftState | |
---|---|
double |
MassProvider.getTotalMass(SpacecraftState state)
Return the mass of the spacecraft following the order. |
double |
SimpleMassModel.getTotalMass(SpacecraftState state)
Return the mass of the spacecraft following the order. |
void |
Propagator.resetInitialState(SpacecraftState state)
Reset the propagator initial state. |
void |
AbstractPropagator.resetInitialState(SpacecraftState state)
Reset the propagator initial state. |
Method parameters in org.orekit.propagation with type arguments of type SpacecraftState | |
---|---|
SpacecraftState |
SpacecraftState.interpolate(AbsoluteDate date,
Collection<SpacecraftState> sample)
Get an interpolated instance. |
Constructors in org.orekit.propagation with parameters of type SpacecraftState | |
---|---|
OsculatingToMeanElementsConverter(SpacecraftState state,
int satelliteRevolution,
Propagator propagator)
Constructor. |
Constructor parameters in org.orekit.propagation with type arguments of type SpacecraftState | |
---|---|
AnalyticalIntegratedEphemeris(List<AbsoluteDate> initialDates,
List<AbsoluteDate> finalDates,
List<SpacecraftState> initialStates,
AbstractPropagator propagator,
AttitudeProvider attForcesProvider,
AttitudeProvider attEventsProvider,
boolean isForward)
Constructor. |
Uses of SpacecraftState in org.orekit.propagation.analytical |
---|
Methods in org.orekit.propagation.analytical that return SpacecraftState | |
---|---|
SpacecraftState |
AdapterPropagator.DifferentialEffect.apply(SpacecraftState original)
Apply the effect to a spacecraft state . |
SpacecraftState |
J2DifferentialEffect.apply(SpacecraftState state1)
Apply the effect to a spacecraft state . |
protected SpacecraftState |
AdapterPropagator.basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features. |
SpacecraftState |
AdapterPropagator.getInitialState()
Get the propagator initial state. |
Methods in org.orekit.propagation.analytical with parameters of type SpacecraftState | |
---|---|
SpacecraftState |
AdapterPropagator.DifferentialEffect.apply(SpacecraftState original)
Apply the effect to a spacecraft state . |
SpacecraftState |
J2DifferentialEffect.apply(SpacecraftState state1)
Apply the effect to a spacecraft state . |
void |
AnalyticalEphemerisModeHandler.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
void |
AdapterPropagator.resetInitialState(SpacecraftState state)
Reset the propagator initial state. |
void |
EcksteinHechlerPropagator.resetInitialState(SpacecraftState state)
Reset the propagator initial state. |
void |
AbstractLyddanePropagator.resetInitialState(SpacecraftState state)
Reset the propagator initial state. |
void |
KeplerianPropagator.resetInitialState(SpacecraftState state)
Reset the propagator initial state. |
void |
J2SecularPropagator.resetInitialState(SpacecraftState state)
Reset the propagator initial state. |
Constructors in org.orekit.propagation.analytical with parameters of type SpacecraftState | |
---|---|
J2DifferentialEffect(SpacecraftState original,
AdapterPropagator.DifferentialEffect directEffect,
boolean applyBefore,
double referenceRadius,
double mu,
double j2)
Simple constructor. |
|
J2DifferentialEffect(SpacecraftState original,
AdapterPropagator.DifferentialEffect directEffect,
boolean applyBefore,
PotentialCoefficientsProvider gravityField)
Simple constructor. |
Uses of SpacecraftState in org.orekit.propagation.analytical.tle |
---|
Method parameters in org.orekit.propagation.analytical.tle with type arguments of type SpacecraftState | |
---|---|
TLE |
AbstractTLEFitter.toTLE(List<SpacecraftState> states,
double positionTolerance,
boolean positionOnly,
boolean withBStar)
Find the TLE elements that minimize the mean square error for a sample of states . |
Uses of SpacecraftState in org.orekit.propagation.events |
---|
Methods in org.orekit.propagation.events that return SpacecraftState | |
---|---|
SpacecraftState |
EventsLogger.LoggedEvent.getState()
Get the triggering state. |
SpacecraftState |
EventState.reset(SpacecraftState oldState)
Let the event detector reset the state if it wants. |
SpacecraftState |
AbstractDetector.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation. |
SpacecraftState |
EventDetector.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation. |
SpacecraftState |
NthOccurrenceDetector.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation. |
SpacecraftState |
NullMassPartDetector.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation. |
Methods in org.orekit.propagation.events that return types with arguments of type SpacecraftState | |
---|---|
Map<String,SpacecraftState> |
ThreeBodiesAngleDetector.resetStates(Map<String,SpacecraftState> oldStates)
|
Map<String,SpacecraftState> |
ExtremaThreeBodiesAngleDetector.resetStates(Map<String,SpacecraftState> oldStates)
|
Methods in org.orekit.propagation.events with parameters of type SpacecraftState | |
---|---|
boolean |
EventState.evaluateStep(SpacecraftState state)
Evaluate the impact of the proposed step on the event handler. |
EventDetector.Action |
ThreeBodiesAngleDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an angle event and choose what to do next. |
EventDetector.Action |
ExtremaDistanceDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an extrema distance event and choose what to do next. |
abstract EventDetector.Action |
AbstractDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next. |
EventDetector.Action |
EventDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next. |
EventDetector.Action |
NodeDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle a node crossing event and choose what to do next. |
EventDetector.Action |
NthOccurrenceDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next. |
EventDetector.Action |
LatitudeDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle a latitude reaching event and choose what to do next. |
EventDetector.Action |
DistanceDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle a distance event and choose what to do next. |
EventDetector.Action |
DihedralFieldOfViewDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an fov event and choose what to do next. |
EventDetector.Action |
LocalTimeAngleDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle a local time angle event and choose what to do next. |
EventDetector.Action |
AltitudeDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an altitude event and choose what to do next. |
EventDetector.Action |
ApsideDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an apside crossing event and choose what to do next. |
EventDetector.Action |
EventShifter.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next. |
EventDetector.Action |
SolarTimeAngleDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle a solar time angle event and choose what to do next. |
EventDetector.Action |
ExtremaThreeBodiesAngleDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle a min or max angle event and choose what to do next. |
EventDetector.Action |
CircularFieldOfViewDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an fov event and choose what to do next. |
EventDetector.Action |
BetaAngleDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handles a beta angle event and chooses what to do next. |
EventDetector.Action |
EclipseDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an eclipse event and choose what to do next. |
EventDetector.Action |
NadirSolarIncidenceDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle a solar incidence event and choose what to do next. |
EventDetector.Action |
ElevationDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an elevation event and choose what to do next. |
EventDetector.Action |
DateDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle a date event and choose what to do next. |
EventDetector.Action |
ExtremaLatitudeDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an extrema latitude event and choose what to do next. |
EventDetector.Action |
GroundMaskElevationDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an azimuth-elevation event and choose what to do next. |
EventDetector.Action |
AOLDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an AOL event and choose what to do next. |
EventDetector.Action |
AlignmentDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an alignment event and choose what to do next. |
EventDetector.Action |
ExtremaElevationDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an extrema distance event and choose what to do next. |
EventDetector.Action |
NullMassDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
If the global mass of the satellite becomes negative, the propagation is stopped. |
EventDetector.Action |
ExtremaLongitudeDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an extrema distance event and choose what to do next. |
EventDetector.Action |
LongitudeDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle a longitude reaching event and choose what to do next. |
EventDetector.Action |
ApparentElevationDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an apparent elevation event and choose what to do next. |
EventDetector.Action |
NullMassPartDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
If the mass of the element becomes negative, a reset_state is performed. |
EventDetector.Action |
AnomalyDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an anomaly event and choose what to do next. |
double |
ThreeBodiesAngleDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
ExtremaDistanceDetector.g(SpacecraftState s)
|
abstract double |
AbstractDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
EventDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
NodeDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
NthOccurrenceDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
LatitudeDetector.g(SpacecraftState s)
|
double |
DistanceDetector.g(SpacecraftState s)
|
double |
DihedralFieldOfViewDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
LocalTimeAngleDetector.g(SpacecraftState s)
|
double |
AltitudeDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
ApsideDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
EventShifter.g(SpacecraftState s)
Compute the value of the switching function. |
double |
SolarTimeAngleDetector.g(SpacecraftState s)
|
double |
ExtremaThreeBodiesAngleDetector.g(SpacecraftState s)
|
double |
CircularFieldOfViewDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
BetaAngleDetector.g(SpacecraftState s)
|
double |
EclipseDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
NadirSolarIncidenceDetector.g(SpacecraftState s)
|
double |
ElevationDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
DateDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
ExtremaLatitudeDetector.g(SpacecraftState s)
|
double |
GroundMaskElevationDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
AOLDetector.g(SpacecraftState s)
|
double |
AlignmentDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
ExtremaElevationDetector.g(SpacecraftState s)
|
double |
NullMassDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
ExtremaLongitudeDetector.g(SpacecraftState s)
|
double |
LongitudeDetector.g(SpacecraftState s)
|
double |
ApparentElevationDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
NullMassPartDetector.g(SpacecraftState s)
Compute the value of the switching function. |
double |
AnomalyDetector.g(SpacecraftState s)
|
void |
ThreeBodiesAngleDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
ExtremaDistanceDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
AbstractDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
void |
EventDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
void |
NthOccurrenceDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
void |
LatitudeDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
DistanceDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
LocalTimeAngleDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
EventShifter.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
void |
SolarTimeAngleDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
ExtremaThreeBodiesAngleDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
BetaAngleDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
NadirSolarIncidenceDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
ExtremaLatitudeDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
AOLDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
ExtremaElevationDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
ExtremaLongitudeDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
LongitudeDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
AnomalyDetector.init(SpacecraftState s0,
AbsoluteDate t)
|
void |
EventState.reinitializeBegin(SpacecraftState state0)
Reinitialize the beginning of the step. |
SpacecraftState |
EventState.reset(SpacecraftState oldState)
Let the event detector reset the state if it wants. |
SpacecraftState |
AbstractDetector.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation. |
SpacecraftState |
EventDetector.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation. |
SpacecraftState |
NthOccurrenceDetector.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation. |
SpacecraftState |
NullMassPartDetector.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation. |
void |
EventState.stepAccepted(SpacecraftState state)
Acknowledge the fact the step has been accepted by the propagator. |
void |
EventState.storeState(SpacecraftState state,
boolean forceUpdate)
Reinitialize event state with provided time and state. |
Method parameters in org.orekit.propagation.events with type arguments of type SpacecraftState | |
---|---|
EventDetector.Action |
ThreeBodiesAngleDetector.eventOccurred(Map<String,SpacecraftState> s,
boolean increasing,
boolean forward)
|
EventDetector.Action |
ExtremaThreeBodiesAngleDetector.eventOccurred(Map<String,SpacecraftState> s,
boolean increasing,
boolean forward)
|
double |
ThreeBodiesAngleDetector.g(Map<String,SpacecraftState> s)
|
double |
ExtremaThreeBodiesAngleDetector.g(Map<String,SpacecraftState> s)
|
void |
ThreeBodiesAngleDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
|
void |
ExtremaThreeBodiesAngleDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
|
Map<String,SpacecraftState> |
ThreeBodiesAngleDetector.resetStates(Map<String,SpacecraftState> oldStates)
|
Map<String,SpacecraftState> |
ExtremaThreeBodiesAngleDetector.resetStates(Map<String,SpacecraftState> oldStates)
|
Uses of SpacecraftState in org.orekit.propagation.events.multi |
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Methods in org.orekit.propagation.events.multi that return types with arguments of type SpacecraftState | |
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Map<String,SpacecraftState> |
MultiEventDetector.resetStates(Map<String,SpacecraftState> oldStates)
Reset the states (including additional states) prior to continue propagation. |
Method parameters in org.orekit.propagation.events.multi with type arguments of type SpacecraftState | |
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EventDetector.Action |
MultiEventDetector.eventOccurred(Map<String,SpacecraftState> s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next. |
double |
MultiEventDetector.g(Map<String,SpacecraftState> s)
Compute the value of the switching function. |
void |
MultiEventDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation. |
Map<String,SpacecraftState> |
MultiEventDetector.resetStates(Map<String,SpacecraftState> oldStates)
Reset the states (including additional states) prior to continue propagation. |
Uses of SpacecraftState in org.orekit.propagation.numerical |
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Methods in org.orekit.propagation.numerical that return SpacecraftState | |
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SpacecraftState |
NumericalPropagator.getInitialState()
Get the propagator initial state. |
SpacecraftState |
NumericalPropagator.propagate(AbsoluteDate target)
Propagate towards a target date. |
SpacecraftState |
NumericalPropagator.propagate(AbsoluteDate tStart,
AbsoluteDate tEnd)
Propagate from a start date towards a target date. |
SpacecraftState |
PartialDerivativesEquations.setInitialJacobians(SpacecraftState s,
double[][] dY1dY0)
Set the initial value of the Jacobian with respect to state. |
SpacecraftState |
PartialDerivativesEquations.setInitialJacobians(SpacecraftState s1,
double[][] dY1dY0,
double[][] dY1dP)
Set the initial value of the Jacobian with respect to state and parameter. |
SpacecraftState |
PartialDerivativesEquations.setInitialJacobians(SpacecraftState s0,
int paramDimension)
Set the initial value of the Jacobian with respect to state and parameter. |
SpacecraftState |
PartialDerivativesEquations.setInitialJacobians(SpacecraftState s,
Parameter parameter,
double[] dY1dP)
Set the initial value of the Jacobian with respect to state. |
Methods in org.orekit.propagation.numerical with parameters of type SpacecraftState | |
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void |
Jacobianizer.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
Jacobianizer.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
void |
PartialDerivativesEquations.computeDerivatives(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the derivatives related to the additional state parameters. |
void |
AdditionalEquations.computeDerivatives(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the derivatives related to the additional state parameters. |
double[] |
JacobiansMapper.getParametersJacobian(Parameter parameter,
SpacecraftState state)
Get the Jacobian with respect to provided parameter parameter . |
void |
JacobiansMapper.getParametersJacobian(Parameter parameter,
SpacecraftState state,
double[] dYdP)
Get the Jacobian with respect to provided parameter parameter . |
double[][] |
JacobiansMapper.getParametersJacobian(SpacecraftState state)
Get the Jacobian with respect to parameters. |
void |
JacobiansMapper.getParametersJacobian(SpacecraftState state,
double[][] dYdP)
Get the Jacobian with respect to parameters. |
double[][] |
JacobiansMapper.getStateJacobian(SpacecraftState state)
Get the Jacobian with respect to state. |
void |
JacobiansMapper.getStateJacobian(SpacecraftState state,
double[][] dYdY0)
Get the Jacobian with respect to state. |
void |
NumericalPropagator.resetInitialState(SpacecraftState state)
Reset the propagator initial state. |
SpacecraftState |
PartialDerivativesEquations.setInitialJacobians(SpacecraftState s,
double[][] dY1dY0)
Set the initial value of the Jacobian with respect to state. |
SpacecraftState |
PartialDerivativesEquations.setInitialJacobians(SpacecraftState s1,
double[][] dY1dY0,
double[][] dY1dP)
Set the initial value of the Jacobian with respect to state and parameter. |
SpacecraftState |
PartialDerivativesEquations.setInitialJacobians(SpacecraftState s0,
int paramDimension)
Set the initial value of the Jacobian with respect to state and parameter. |
SpacecraftState |
PartialDerivativesEquations.setInitialJacobians(SpacecraftState s,
Parameter parameter,
double[] dY1dP)
Set the initial value of the Jacobian with respect to state. |
void |
NumericalPropagator.setInitialState(SpacecraftState initialState)
Set the initial state. |
Uses of SpacecraftState in org.orekit.propagation.precomputed |
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Fields in org.orekit.propagation.precomputed declared as SpacecraftState | |
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protected SpacecraftState[] |
AbstractEphemeris.stateTab
The SpacecraftStates array, chronologically sorted. |
Methods in org.orekit.propagation.precomputed that return SpacecraftState | |
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protected SpacecraftState |
IntegratedEphemeris.basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features. |
SpacecraftState |
Ephemeris.basicPropagate(AbsoluteDate date)
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protected SpacecraftState |
AbstractEphemeris.basicPropagate(AbsoluteDate date)
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protected SpacecraftState |
AbstractEphemeris.checkBounds(double date)
Returns spacecraftstate on bounds if duration is on bounds. |
static SpacecraftState[] |
AbstractEphemeris.generateSpacecraftState(PVCoordinatesProvider pvProv,
AttitudeProvider attProvForces,
AttitudeProvider attProvEvents,
double step,
AbsoluteDateInterval ptsInterval,
Frame frame,
double mu)
Creates a spacecraft array with constant step size. |
SpacecraftState |
IntegratedEphemeris.getInitialState()
Get the propagator initial state. |
SpacecraftState |
Ephemeris.getInitialState()
Get the propagator initial state. |
SpacecraftState |
AbstractEphemeris.getInitialState()
Get the propagator initial state. |
protected SpacecraftState |
LagrangeEphemeris.getInterpolatedSpacecraftState(AbsoluteDate date)
Deprecated. Get the interpolated spacecraft state. |
protected SpacecraftState |
HermiteEphemeris.getInterpolatedSpacecraftState(AbsoluteDate date)
Deprecated. Get the interpolated spacecraft state. |
protected abstract SpacecraftState |
AbstractEphemeris.getInterpolatedSpacecraftState(AbsoluteDate date)
Get the interpolated spacecraft state. |
Methods in org.orekit.propagation.precomputed with parameters of type SpacecraftState | |
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protected Attitude[] |
AbstractEphemeris.attitudesInterpolation(SpacecraftState[] tab,
int order,
int i0,
AbsoluteDate date)
This method is called only if attitudes are supported. |
protected double[] |
AbstractEphemeris.convertTab(SpacecraftState[] tab,
int order)
Convert the SpacecraftState[] into a double[] which represents the duration from the first state date. |
protected int |
AbstractEphemeris.indexValidity(SpacecraftState[] tab,
int index)
Checks if interpolation is valid : meaning if 0<= index +1 -interpOrder/2 or index + interpOrder/2 <= maximalIndex |
protected AbsoluteDateInterval |
AbstractEphemeris.intervalValidity(SpacecraftState[] tab)
Corrects the min and max dates with the constraint of the number of interpolations points required. |
void |
IntegratedEphemeris.resetInitialState(SpacecraftState state)
Reset the propagator initial state. |
void |
Ephemeris.resetInitialState(SpacecraftState state)
Try (and fail) to reset the initial state. |
void |
AbstractEphemeris.resetInitialState(SpacecraftState state)
Reset the propagator initial state. |
Constructors in org.orekit.propagation.precomputed with parameters of type SpacecraftState | |
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AbstractEphemeris(SpacecraftState[] tab)
Simple constructor of class AbstractEphemeris, with interpolation order equal to 2. |
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AbstractEphemeris(SpacecraftState[] tab,
int order)
Simple constructor of class AbstractEphemeris with defined interpolation order. |
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AbstractEphemeris(SpacecraftState[] tab,
int order,
ISearchIndex algo)
Constructor of class AbstractEphemeris where a search index algorithm is passed on the constructor. |
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AbstractEphemeris(SpacecraftState[] tab,
ISearchIndex algo)
Constructor of class AbstractEphemeris where a search index algorithm is passed on the constructor and the order is by default equal to 2. |
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HermiteEphemeris(SpacecraftState[] tab)
Deprecated. Constructor of class HermiteEphemeris, used by other constructors of this class. |
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HermiteEphemeris(SpacecraftState[] tab,
ISearchIndex algo)
Deprecated. Constructor of class HermiteEphemeris, where a search index algorithm is passed on the constructor. |
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HermiteEphemeris(SpacecraftState[] tabStates,
Vector3D[] tabAcc)
Deprecated. Constructor of class HermiteEphemeris, where a search index algorithm is passed on the constructor. |
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HermiteEphemeris(SpacecraftState[] tab,
Vector3D[] tabAcc,
ISearchIndex algo)
Deprecated. Constructor of class HermiteEphemeris, where a search index algorithm is passed on the constructor. |
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LagrangeEphemeris(SpacecraftState[] tabulatedStates)
Deprecated. Constructor for a 8th order Lagrange interpolator. |
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LagrangeEphemeris(SpacecraftState[] tab,
int order)
Deprecated. Constructor of class LagrangeEphemeris, used by other constructors of this class. |
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LagrangeEphemeris(SpacecraftState[] tab,
int order,
ISearchIndex algo)
Deprecated. Constructor of class LagrangeEphemeris, where a search index algorithm is passed on the constructor. |
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LagrangeEphemeris(SpacecraftState[] tab,
ISearchIndex algo)
Deprecated. Constructor for a 8th order Lagrange interpolator, where a search index algorithm is passed on the constructor. |
Constructor parameters in org.orekit.propagation.precomputed with type arguments of type SpacecraftState | |
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Ephemeris(List<SpacecraftState> states,
int interpolationPoints)
Constructor with tabulated states. |
Uses of SpacecraftState in org.orekit.propagation.sampling |
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Methods in org.orekit.propagation.sampling that return SpacecraftState | |
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SpacecraftState |
BasicStepInterpolator.getInterpolatedState()
Get the interpolated state. |
SpacecraftState |
OrekitStepInterpolator.getInterpolatedState()
Get the interpolated state. |
SpacecraftState |
AdaptedStepHandler.getInterpolatedState()
Get the interpolated state. |
Methods in org.orekit.propagation.sampling with parameters of type SpacecraftState | |
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void |
OrekitFixedStepHandler.handleStep(SpacecraftState currentState,
boolean isLast)
Handle the current step. |
void |
OrekitFixedStepHandler.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
void |
OrekitStepHandler.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
void |
OrekitStepNormalizer.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
void |
OrekitStepHandlerMultiplexer.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation. |
Uses of SpacecraftState in org.orekit.utils |
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Constructors in org.orekit.utils with parameters of type SpacecraftState | |
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AbstractBoundedPVProvider(SpacecraftState[] tabState,
int order,
ISearchIndex algo)
Creates an instance of AbstractBoundedPVProvider from a SpacecraftState table |
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EphemerisPvHermite(SpacecraftState[] tabState,
int order,
Vector3D[] tabAcc,
ISearchIndex algo)
Creates an instance of EphemerisPvHermite from a SpacecraftState table |
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EphemerisPvHermite(SpacecraftState[] tabState,
Vector3D[] tabAcc,
ISearchIndex algo)
Creates an instance of EphemerisPvHermite from a SpacecraftState table with default interpolation order = 2. |
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EphemerisPvLagrange(SpacecraftState[] tabState,
int order,
ISearchIndex algo)
Creates an instance of EphemerisPvLagrange from a spacecraftstate list |
Uses of SpacecraftState in org.orekit.wrenches |
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Methods in org.orekit.wrenches with parameters of type SpacecraftState | |
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Vector3D |
WrenchModel.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,
Vector3D origin,
Frame frame)
Compute the resulting wrench. |
Wrench |
WrenchModel.computeWrench(SpacecraftState s)
Compute the resulting wrench at the mass centre of the spacecraft in the frame of the main part. |
Wrench |
WrenchModel.computeWrench(SpacecraftState s,
Vector3D origin,
Frame frame)
Compute the resulting wrench. |
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