| Modifier and Type | Method and Description |
|---|---|
void |
AssemblyBuilder.initMainPartFrame(SpacecraftState state)
Sets up the main frame of the assembly from a "SpacecraftState" object.
|
void |
Assembly.initMainPartFrame(SpacecraftState state)
Initialize the main part's frame using a
SpacecraftState as an input argument. |
void |
MainPart.updateFrame(SpacecraftState s)
Update frame with provided spacecraft state.
|
void |
IPart.updateFrame(SpacecraftState s)
Update frame with provided spacecraft state.
|
void |
MobilePart.updateFrame(SpacecraftState s)
Update frame with provided spacecraft state.
|
void |
Part.updateFrame(SpacecraftState s)
Update frame with provided spacecraft state.
|
void |
Assembly.updateMainPartFrame(SpacecraftState state)
Updates the main part frame's transformation to its parent frame using a
Transform as an input argument. |
| Modifier and Type | Method and Description |
|---|---|
void |
RediffusedRadiativeModel.addDAccDParamRediffusedRadiativePressure(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives.
|
void |
RediffusedRadiativeModel.addDAccDStateRediffusedRadiativePressure(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives.
|
void |
DragLiftModel.addDDragAccDParam(SpacecraftState s,
Parameter param,
double density,
Vector3D relativeVelocity,
double[] dAccdParam)
Compute acceleration derivatives with respect to ballistic coefficient.
|
void |
AeroModel.addDDragAccDParam(SpacecraftState s,
Parameter param,
double density,
Vector3D relativeVelocity,
double[] dAccdParam)
Compute acceleration derivatives with respect to ballistic coefficient.
|
void |
GlobalAeroModel.addDDragAccDParam(SpacecraftState s,
Parameter param,
double density,
Vector3D relativeVelocity,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters (the 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 |
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 |
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 |
DirectRadiativeModel.addDSRPAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam,
Vector3D satSunVector)
Compute acceleration derivatives with respect to additional parameters.
|
void |
DirectRadiativeModel.addDSRPAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel,
Vector3D satSunVector)
Compute acceleration derivatives with respect to state parameters.
|
Vector3D |
GlobalAeroModel.computeSC(SpacecraftState state,
Frame frame,
Vector3D relativeVelocity)
Compute the surface drag coefficient (drag coefficient x area)
|
Vector3D |
DragLiftModel.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Method to compute the aero acceleration, based on the assembly.
|
Vector3D |
AeroModel.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Method to compute the aero acceleration, based on the assembly.
|
Vector3D |
GlobalAeroModel.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Method to compute the aero acceleration, based on the assembly.
|
Wrench |
AeroWrenchModel.dragWrench(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Compute the torque due to radiation pressire.
|
Wrench |
AeroWrenchModel.dragWrench(SpacecraftState state,
double density,
Vector3D relativeVelocity,
Vector3D origin,
Frame frame)
Compute the torque due to radiation pressire.
|
protected static Vector3D |
AeroModel.forceOnFacet(SpacecraftState state,
IPart part,
Assembly assembly,
double density,
Vector3D relativeVelocity)
Method to compute the force for a plane model.
|
protected static Vector3D |
DirectRadiativeModel.forceOnFacet(SpacecraftState state,
IPart part,
Vector3D flux)
Method to compute the force for a plane model.
|
protected static Vector3D |
AeroModel.forceOnSphere(SpacecraftState state,
IPart part,
double density,
Vector3D relativeVelocity,
Frame mainPartFrame)
Method to compute the force for the part model (cylinder, parallelepiped, sphere).
|
protected static Vector3D |
DirectRadiativeModel.forceOnSphere(SpacecraftState state,
IPart part,
Vector3D flux,
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 |
MassModel.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.
|
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.
|
| Modifier and Type | Method and Description |
|---|---|
static double |
AeroCoeffByAoA.angleOfAttackFromSpacecraftState(SpacecraftState state,
EllipsoidBodyShape earthShape)
Computes the angle of attack from the spacecraft state and the Earth shape.
|
protected double |
AeroCoeffByAltitude.computeXVariable(SpacecraftState state)
Computes the x variable from the spacecraft state.
|
protected abstract double |
AbstractAeroCoeff1D.computeXVariable(SpacecraftState state)
Computes the x variable from the spacecraft state.
|
protected double |
AeroCoeffByMach.computeXVariable(SpacecraftState state)
Computes the x variable from the spacecraft state.
|
protected double |
AeroCoeffByAoA.computeXVariable(SpacecraftState state)
Computes the x variable from the spacecraft state.
|
double |
AeroCoeffConstant.derivativeValue(Parameter p,
SpacecraftState s)
Compute the derivative value with respect to the input parameter.
|
double |
AbstractAeroCoeff1D.derivativeValue(Parameter p,
SpacecraftState s)
Compute the derivative value with respect to the input parameter.
|
double |
AeroCoeffByAoAAndMach.derivativeValue(Parameter p,
SpacecraftState s)
Compute the derivative value with respect to the input parameter.
|
static double |
AeroCoeffByMach.machFromSpacecraftState(SpacecraftState state,
Atmosphere atmosphere)
Computes the Mach number from the spacecraft state and an atmosphere model.
|
double |
AeroCoeffConstant.value(SpacecraftState state)
Getting the value of the function.
|
double |
AbstractAeroCoeff1D.value(SpacecraftState state)
Getting the value of the function.
|
double |
AeroCoeffByAoAAndMach.value(SpacecraftState state)
Getting the value of the function.
|
| Modifier and Type | Method and Description |
|---|---|
double |
CnCookModel.derivativeValue(Parameter p,
SpacecraftState state)
Compute the derivative value with respect to the input parameter.
|
double |
CtCookModel.derivativeValue(Parameter p,
SpacecraftState state)
Compute the derivative value with respect to the input parameter.
|
double |
AlphaProvider.getAlpha(SpacecraftState state)
Return alpha (energy accomodation coefficient) value.
|
double |
AlphaConstant.getAlpha(SpacecraftState state)
Return alpha (energy accomodation coefficient) value.
|
double |
AlphaCookModel.getAlpha(SpacecraftState state)
Return alpha (energy accomodation coefficient) value.
|
double |
CookWallGasTemperature.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 |
ConstantWallGasTemperature.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 |
CnCookModel.value(SpacecraftState state)
Getting the value of the function.
|
double |
CtCookModel.value(SpacecraftState state)
Getting the value of the function.
|
| Modifier and Type | Method and Description |
|---|---|
IDependentVariable<SpacecraftState> |
PropulsiveProperty.getIsp()
Getter for the isp as an
IDependentVariable object. |
IDependentVariable<SpacecraftState> |
PropulsiveProperty.getThrust()
Getter for the thrust as an
IDependentVariable object. |
| Modifier and Type | Method and Description |
|---|---|
void |
MassEquation.computeDerivatives(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the derivatives related to the additional state parameters.
|
double[] |
MassEquation.computeSecondDerivatives(SpacecraftState s)
Compute the second derivatives related to the additional state parameters.
|
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 |
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 |
RadiativeSphereProperty.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 |
AeroSphereProperty.getCrossSection(SpacecraftState state,
Vector3D relativeVelocity,
Frame mainPartFrame,
Frame partFrame)
Compute the cross section of main shape using the relative velocity in the
part (having the aero property) frame as the direction to provider to the
CrossSectionProvider.getCrossSection(Vector3D). |
double |
AeroCrossSectionProperty.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 and Description |
|---|
PropulsiveProperty(IDependentVariable<SpacecraftState> inThrust,
IDependentVariable<SpacecraftState> inIsp)
Constructor for the property with thrust and isp as
IDependentVariable. |
PropulsiveProperty(IDependentVariable<SpacecraftState> inThrust,
IDependentVariable<SpacecraftState> inIsp)
Constructor for the property with thrust and isp as
IDependentVariable. |
| Modifier and Type | Method and Description |
|---|---|
double |
AeroAttitudeLaw.getAngleOfAttack(SpacecraftState state)
Getter for the angle of attack.
|
double |
AeroAttitudeLaw.getRollVelocity(SpacecraftState state)
Getter for the roll velocity.
|
double |
AeroAttitudeLaw.getSideSlipAngle(SpacecraftState state)
Getter for the side slip angle.
|
| Modifier and Type | Method and Description |
|---|---|
Transform |
OrientationAngleTransform.getTransform(SpacecraftState state)
Get the
Transform corresponding to specified state. |
| Modifier and Type | Method and Description |
|---|---|
FieldData |
FacetCelestialBody.getFieldData(SpacecraftState state,
IFieldOfView fieldOfView,
Vector3D lineOfSight)
Returns the field data as
FieldData for each state in provided list. |
| Modifier and Type | Method and Description |
|---|---|
List<Triangle> |
FacetCelestialBody.getNeverVisibleTriangles(List<SpacecraftState> states,
IFieldOfView fieldOfView)
Returns the list of triangles never visible from the satellite field of view during the whole ephemeris.
|
List<SurfacePointedData> |
FacetCelestialBody.getSurfacePointedDataEphemeris(List<SpacecraftState> states,
Vector3D lineOfSight,
PVCoordinatesProvider sun,
double pixelFOV)
Returns the body surface pointed data as
SurfacePointedData for each state in provided list. |
List<Triangle> |
FacetCelestialBody.getVisibleAndEnlightenedTriangles(List<SpacecraftState> states,
PVCoordinatesProvider sun,
IFieldOfView fieldOfView)
Returns the list of triangles enlightened (by the Sun) and visible at least once during the whole ephemeris
from the satellite field of view.
|
| Modifier and Type | Method and Description |
|---|---|
SpacecraftState |
CodedEventsLogger.LoggedCodedEvent.getState()
Gets the
SpacecraftState that caused the coded event. |
SpacecraftState |
GenericCodingEventDetector.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation.
|
| Modifier and Type | Method and Description |
|---|---|
CodedEvent |
CodingEventDetector.buildCodedEvent(SpacecraftState s,
boolean increasing)
Build a
CodedEvent instance appropriate for the provided SpacecraftState. |
CodedEvent |
GenericCodingEventDetector.buildCodedEvent(SpacecraftState s,
boolean increasing)
Build a
CodedEvent instance appropriate for the provided SpacecraftState. |
CodedEvent |
CodingEventDetector.buildDelayedCodedEvent(SpacecraftState s,
boolean increasing)
Build a delayed
CodedEvent instance appropriate for the provided SpacecraftState. |
CodedEvent |
GenericCodingEventDetector.buildDelayedCodedEvent(SpacecraftState s,
boolean increasing)
Build a delayed
CodedEvent instance appropriate for the provided SpacecraftState. |
CodedEvent |
CodingEventDetector.buildOccurrenceCodedEvent(SpacecraftState s,
boolean increasing)
Build a
CodedEvent instance appropriate for the provided SpacecraftState. |
CodedEvent |
GenericCodingEventDetector.buildOccurrenceCodedEvent(SpacecraftState s,
boolean increasing)
Build a
CodedEvent instance appropriate for the provided SpacecraftState. |
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 |
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.
|
EventDetector.Action |
GenericCodingEventDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an 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.
|
double |
EarthZoneDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
CentralBodyMaskCircularFOVDetector.g(SpacecraftState s)
The switching function is the minimum value between the eclipse detector g function and the
circularFOVDetector
|
double |
GenericCodingEventDetector.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.
|
void |
EarthZoneDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
CentralBodyMaskCircularFOVDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
GenericCodingEventDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
CombinedPhenomenaDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
boolean |
GenericCodingEventDetector.isStateActive(SpacecraftState state)
Tells if the event state is "active" for the given input.
|
SpacecraftState |
GenericCodingEventDetector.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation.
|
| Modifier and Type | Method and Description |
|---|---|
Map<String,SpacecraftState> |
MultiEventsLogger.MultiLoggedEvent.getStates()
Get the triggering states.
|
Map<String,SpacecraftState> |
MultiCodedEventsLogger.MultiLoggedCodedEvent.getStates()
Gets the map of
SpacecraftState that caused the coded event. |
Map<String,SpacecraftState> |
MultiGenericCodingEventDetector.resetStates(Map<String,SpacecraftState> oldStates)
Reset the states (including additional states) prior to continue propagation.
|
| Modifier and Type | Method and Description |
|---|---|
CodedEvent |
MultiCodingEventDetector.buildCodedEvent(Map<String,SpacecraftState> s,
boolean increasing)
Build a
CodedEvent instance appropriate for the provided map of SpacecraftState. |
CodedEvent |
MultiGenericCodingEventDetector.buildCodedEvent(Map<String,SpacecraftState> states,
boolean increasing)
Build a
CodedEvent instance appropriate for the provided map of SpacecraftState. |
CodedEvent |
MultiCodingEventDetector.buildDelayedCodedEvent(Map<String,SpacecraftState> s,
boolean increasing)
Build a delayed
CodedEvent instance appropriate for the provided map of SpacecraftState. |
CodedEvent |
MultiGenericCodingEventDetector.buildDelayedCodedEvent(Map<String,SpacecraftState> states,
boolean increasing)
Build a delayed
CodedEvent instance appropriate for the provided map of SpacecraftState. |
CodedEvent |
MultiCodingEventDetector.buildOccurrenceCodedEvent(Map<String,SpacecraftState> s,
boolean increasing)
Build a
CodedEvent instance appropriate for the provided map of SpacecraftState. |
CodedEvent |
MultiGenericCodingEventDetector.buildOccurrenceCodedEvent(Map<String,SpacecraftState> states,
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)
Handle an event and choose what to do next.
|
double |
MultiGenericCodingEventDetector.g(Map<String,SpacecraftState> s)
Compute the value of the switching function.
|
void |
MultiGenericCodingEventDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
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)
Reset the states (including additional states) prior to continue propagation.
|
| Modifier and Type | Method and Description |
|---|---|
Map<String,SpacecraftState> |
SatToSatMutualVisibilityDetector.resetStates(Map<String,SpacecraftState> oldStates)
Reset the states (including additional states) prior to continue propagation.
|
| Modifier and Type | Method and Description |
|---|---|
EventDetector.Action |
MaskingDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle "masking" event and choose what to do next.
|
EventDetector.Action |
RFVisibilityDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next.
|
EventDetector.Action |
TargetInFieldOfViewDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next.
|
EventDetector.Action |
StationToSatMutualVisibilityDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an 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 |
SensorInhibitionDetector.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)
Handle an event and choose what to do next.
|
EventDetector.Action |
SatToSatMutualVisibilityDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next.
|
EventDetector.Action |
VisibilityFromStationDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle "visibility from station" event and choose what to do next.
|
double |
MaskingDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
RFVisibilityDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
TargetInFieldOfViewDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
StationToSatMutualVisibilityDetector.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 |
SensorInhibitionDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
SensorVisibilityDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
SatToSatMutualVisibilityDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
VisibilityFromStationDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
protected Vector3D |
AbstractDetectorWithTropoCorrection.getCorrectedVector(SpacecraftState s)
Compute the apparent vector from the station to the spacecraft with tropospheric effects.
|
void |
MaskingDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
TargetInFieldOfViewDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
StationToSatMutualVisibilityDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
ExtremaSightAxisDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
SensorInhibitionDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
SensorVisibilityDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
SatToSatMutualVisibilityDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
VisibilityFromStationDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
| Modifier and Type | Method and Description |
|---|---|
EventDetector.Action |
SatToSatMutualVisibilityDetector.eventOccurred(Map<String,SpacecraftState> s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next.
|
double |
SatToSatMutualVisibilityDetector.g(Map<String,SpacecraftState> s)
Compute the value of the switching function.
|
void |
SatToSatMutualVisibilityDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
Map<String,SpacecraftState> |
SatToSatMutualVisibilityDetector.resetStates(Map<String,SpacecraftState> oldStates)
Reset the states (including additional states) prior to continue propagation.
|
| Modifier and Type | Method and Description |
|---|---|
void |
ForceModel.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing
acceleration.
|
void |
EmpiricalForce.addContribution(SpacecraftState state,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing
acceleration.
|
void |
EmpiricalForce.addDAccDParam(SpacecraftState state,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
void |
EmpiricalForce.addDAccDState(SpacecraftState state,
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 |
ForceModel.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
Vector3D |
EmpiricalForce.computeAcceleration(SpacecraftState state)
Compute the acceleration due to the force.
|
| Modifier and Type | Method and Description |
|---|---|
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.
|
double |
DragForce.getMultiplicativeFactor(SpacecraftState state)
Getter for the multiplicative factor used at construction.
|
| Modifier and Type | Method and Description |
|---|---|
void |
NewtonianAttraction.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing
acceleration.
|
void |
CunninghamAttractionModel.addContribution(SpacecraftState state,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing
acceleration.
|
void |
BalminoAttractionModel.addContribution(SpacecraftState state,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing
acceleration.
|
void |
DrozinerAttractionModel.addContribution(SpacecraftState state,
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 |
NewtonianAttraction.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
void |
CunninghamAttractionModel.addDAccDParam(SpacecraftState state,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
void |
BalminoAttractionModel.addDAccDParam(SpacecraftState state,
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 |
NewtonianAttraction.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters.
|
void |
CunninghamAttractionModel.addDAccDState(SpacecraftState state,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters.
|
void |
BalminoAttractionModel.addDAccDState(SpacecraftState state,
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.
|
Vector3D |
NewtonianAttraction.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
Vector3D |
CunninghamAttractionModel.computeAcceleration(SpacecraftState state)
Compute the acceleration due to the force.
|
Vector3D |
BalminoAttractionModel.computeAcceleration(SpacecraftState state)
Compute the acceleration due to the force.
|
Vector3D |
DrozinerAttractionModel.computeAcceleration(SpacecraftState state)
Compute the acceleration due to the force.
|
Vector3D |
ThirdBodyAttraction.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
| Modifier and Type | Method and Description |
|---|---|
void |
GridAttractionModel.addContribution(SpacecraftState state,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing
acceleration.
|
void |
GridAttractionModel.addDAccDParam(SpacecraftState state,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
void |
GridAttractionModel.addDAccDState(SpacecraftState state,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters.
|
Vector3D |
GridAttractionModel.computeAcceleration(SpacecraftState state)
Compute the acceleration due to the force.
|
double |
GridAttractionModel.computePotential(SpacecraftState state)
Compute the potential due to the body attraction.
|
| Modifier and Type | Method and Description |
|---|---|
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.
|
| Modifier and Type | Method and Description |
|---|---|
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)
Compute acceleration derivatives with respect to state parameters.
|
Vector3D |
VariablePotentialAttractionModel.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
| Modifier and Type | Method and Description |
|---|---|
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.
|
| Modifier and Type | Method and Description |
|---|---|
void |
ConstantThrustError.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the constant thrust error model to the perturbing acceleration.
|
void |
ContinuousThrustManeuver.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing
acceleration.
|
void |
ConstantThrustError.addDAccDParam(SpacecraftState state,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
void |
ContinuousThrustManeuver.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
void |
ConstantThrustError.addDAccDState(SpacecraftState state,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters.
|
void |
ContinuousThrustManeuver.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters.
|
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.
|
Vector3D |
ContinuousThrustManeuver.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.
|
Vector3D |
ContinuousThrustManeuver.getDirection(SpacecraftState s)
Get the thrust direction.
|
double |
ContinuousThrustManeuver.getFlowRate(SpacecraftState s)
Get the flow rate.
|
double |
ContinuousThrustManeuver.getISP(SpacecraftState s)
Get the specific impulse.
|
double |
ContinuousThrustManeuver.getThrust(SpacecraftState s)
Get the thrust.
|
void |
ImpulseManeuver.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
ContinuousThrustManeuver.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation.
|
SpacecraftState |
ImpulseManeuver.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation.
|
| Constructor and Description |
|---|
SmallManeuverAnalyticalModel(SpacecraftState state0In,
Frame frame,
Vector3D dV,
double isp,
String partNameIn)
Build a maneuver defined in user-specified frame.
|
SmallManeuverAnalyticalModel(SpacecraftState state0In,
Vector3D dV,
double isp,
String partNameIn)
Build a maneuver defined in spacecraft frame.
|
| Constructor and Description |
|---|
ContinuousThrustManeuver(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> inDirection,
MassProvider massProvider,
TankProperty tank)
Constructor for a variable direction in satellite frame.
|
ContinuousThrustManeuver(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> inDirection,
MassProvider massProvider,
TankProperty tank,
Frame frameIn)
Constructor for a variable direction in provided frame.
|
ContinuousThrustManeuver(AbsoluteDate date,
double duration,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> inDirection,
MassProvider massProvider,
TankProperty tank,
LOFType lofTyp)
Constructor for a variable direction in provided local orbital frame.
|
ContinuousThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> inDirection,
MassProvider massProvider,
TankProperty tank)
Constructor for a variable direction in satellite frame.
|
ContinuousThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> inDirection,
MassProvider massProvider,
TankProperty tank,
Frame frameIn)
Constructor for a variable direction in provided frame.
|
ContinuousThrustManeuver(EventDetector startEventDetector,
EventDetector stopEventDetector,
PropulsiveProperty engine,
IDependentVectorVariable<SpacecraftState> inDirection,
MassProvider massProvider,
TankProperty tank,
LOFType lofTyp)
Constructor for a variable direction in local orbital frame.
|
| Modifier and Type | Method and Description |
|---|---|
SpacecraftState |
ImpulseDaManeuver.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation.
|
SpacecraftState |
ImpulseDeManeuver.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation.
|
SpacecraftState |
ImpulseDiManeuver.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation.
|
| Modifier and Type | Method and Description |
|---|---|
void |
ImpulseDaManeuver.computeDV(SpacecraftState state)
Method to compute the DV thanks to Keplerian parameters included in the Spacecraft state.
|
void |
ImpulseDeManeuver.computeDV(SpacecraftState state)
Method to compute the DV thanks to Keplerian parameters included in the Spacecraft state.
|
void |
ImpulseParKepManeuver.computeDV(SpacecraftState state)
Method to compute the DV thanks to Keplerian parameters included in the Spacecraft state.
|
void |
ImpulseDiManeuver.computeDV(SpacecraftState state)
Method to compute the DV thanks to Keplerian parameters included in the Spacecraft state.
|
SpacecraftState |
ImpulseDaManeuver.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation.
|
SpacecraftState |
ImpulseDeManeuver.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation.
|
SpacecraftState |
ImpulseDiManeuver.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation.
|
| Modifier and Type | Method and Description |
|---|---|
void |
SolarRadiationPressureCircular.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing
acceleration.
|
void |
RediffusedRadiationPressure.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing
acceleration.
|
void |
SolarRadiationPressureEllipsoid.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing
acceleration.
|
void |
SolarRadiationPressureCircular.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
void |
RediffusedRadiationPressure.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters.
|
void |
SolarRadiationPressureEllipsoid.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 |
SolarRadiationPressureCircular.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters.
|
void |
RediffusedRadiationPressure.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters.
|
void |
SolarRadiationPressureEllipsoid.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 |
SolarRadiationPressureCircular.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
Vector3D |
RediffusedRadiationPressure.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
Vector3D |
SolarRadiationPressureEllipsoid.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
Vector3D |
SolarRadiationPressureEllipsoid.getSolarFlux(SpacecraftState s)
Compute solar flux.
|
Vector3D |
RadiationSensitive.radiationPressureAcceleration(SpacecraftState state,
Vector3D flux)
Compute the acceleration due to radiation pressure.
|
Vector3D |
RediffusedRadiationSensitive.rediffusedRadiationPressureAcceleration(SpacecraftState state,
ElementaryFlux flux)
rediffused radiative pressure acceleration
|
| Modifier and Type | Method and Description |
|---|---|
void |
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.addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing
acceleration.
|
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.addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional 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.
|
void |
SchwarzschildRelativisticEffect.addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters.
|
Vector3D |
LenseThirringRelativisticEffect.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
Vector3D |
CoriolisRelativisticEffect.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
Vector3D |
SchwarzschildRelativisticEffect.computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force.
|
| Modifier and Type | Method and Description |
|---|---|
Transform |
TransformStateProvider.getTransform(SpacecraftState state)
Get the
Transform corresponding to specified state. |
| Modifier and Type | Method and Description |
|---|---|
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 |
LinearFunction.derivativeValue(Parameter p,
SpacecraftState state)
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 |
PiecewiseFunction.value(SpacecraftState s)
Getting the value of the function.
|
double |
IParameterizableFunction.value(SpacecraftState state)
Getting the value of the function.
|
double |
LinearFunction.value(SpacecraftState s)
Getting the value of the function.
|
double |
ConstantFunction.value(SpacecraftState s)
Getting the value of the function.
|
| Constructor and Description |
|---|
AbstractBoundedPVProvider(SpacecraftState[] tabState,
int order,
ISearchIndex algo)
Creates an instance of AbstractBoundedPVProvider from a SpacecraftState table
|
EphemerisPvHermite(SpacecraftState[] tabState,
int samples,
Vector3D[] tabAcc,
ISearchIndex algo)
Creates an instance of EphemerisPvHermite from a SpacecraftState table
|
EphemerisPvHermite(SpacecraftState[] tabState,
Vector3D[] tabAcc,
ISearchIndex algo)
Creates an instance of EphemerisPvHermite from a SpacecraftState table
with default number of samples = 2.
|
EphemerisPvLagrange(SpacecraftState[] tabState,
int order,
ISearchIndex algo)
Creates an instance of EphemerisPvLagrange from a spacecraftstate list
|
| Modifier and Type | Method and Description |
|---|---|
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 |
Propagator.getInitialState()
Get the propagator initial state.
|
SpacecraftState |
AbstractPropagator.getInitialState()
Get the propagator initial state.
|
SpacecraftState |
SpacecraftStateProvider.getSpacecraftState(AbsoluteDate date)
Get the
SpacecraftState at provided dat. |
SpacecraftState |
AbstractPropagator.getSpacecraftState(AbsoluteDate date)
Get the
SpacecraftState at provided dat. |
SpacecraftState |
SpacecraftState.interpolate(AbsoluteDate date,
Collection<SpacecraftState> sample)
Get an interpolated instance.
|
SpacecraftState |
Propagator.propagate(AbsoluteDate target)
Propagate towards a target date.
|
SpacecraftState |
AnalyticalIntegratedEphemeris.propagate(AbsoluteDate target)
Propagate towards a target date.
|
SpacecraftState |
AbstractPropagator.propagate(AbsoluteDate target)
Propagate towards a target date.
|
SpacecraftState |
Propagator.propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date.
|
SpacecraftState |
AnalyticalIntegratedEphemeris.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.
|
| Modifier and Type | Method and Description |
|---|---|
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.
|
| Modifier and Type | Method and Description |
|---|---|
void |
MultiPropagator.addInitialState(SpacecraftState initialState,
String satId)
Add a new spacecraft state to be propagated.
|
double |
SimpleMassModel.getTotalMass(SpacecraftState state)
Return the mass of the spacecraft following the order.
|
double |
MassProvider.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.
|
| Modifier and Type | Method and Description |
|---|---|
SpacecraftState |
SpacecraftState.interpolate(AbsoluteDate date,
Collection<SpacecraftState> sample)
Get an interpolated instance.
|
| Constructor and Description |
|---|
AnalyticalIntegratedEphemeris(List<AbsoluteDate> initialDatesIn,
List<AbsoluteDate> finalDatesIn,
List<SpacecraftState> initialStatesIn,
Propagator propagatorIn,
AttitudeProvider attForcesProvider,
AttitudeProvider attEventsProvider,
boolean isForwardIn)
Constructor.
|
| Modifier and Type | Method and Description |
|---|---|
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.
|
| Modifier and Type | Method and Description |
|---|---|
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.
|
| Constructor and Description |
|---|
J2DifferentialEffect(SpacecraftState original,
AdapterPropagator.DifferentialEffect directEffect,
boolean applyBeforeIn,
double referenceRadius,
double mu,
double j2)
Simple constructor.
|
J2DifferentialEffect(SpacecraftState original,
AdapterPropagator.DifferentialEffect directEffect,
boolean applyBeforeIn,
PotentialCoefficientsProvider gravityField)
Simple constructor.
|
| Modifier and Type | Method and Description |
|---|---|
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. |
| Modifier and Type | Method and Description |
|---|---|
SpacecraftState |
EventsLogger.LoggedEvent.getState()
Get the triggering state.
|
SpacecraftState |
EventState.reset(SpacecraftState oldState)
Let the event detector reset the state if it wants.
|
SpacecraftState |
IntervalOccurrenceDetector.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation.
|
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 |
NullMassPartDetector.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation.
|
| Modifier and Type | Method and Description |
|---|---|
Map<String,SpacecraftState> |
ThreeBodiesAngleDetector.resetStates(Map<String,SpacecraftState> oldStates)
Reset the states (including additional states) prior to continue propagation.
|
Map<String,SpacecraftState> |
ExtremaThreeBodiesAngleDetector.resetStates(Map<String,SpacecraftState> oldStates)
Reset the states (including additional states) prior to continue propagation.
|
| Modifier and Type | Method and Description |
|---|---|
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 |
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 |
AltitudeDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an altitude 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 |
ExtremaThreeBodiesAngleDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle a min or max angle event and choose what to do next.
|
EventDetector.Action |
IntervalOccurrenceDetector.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 |
ElevationDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an elevation 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 |
DistanceDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle a distance 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 |
ExtremaElevationDetector.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 |
AnomalyDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an anomaly 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 |
DihedralFieldOfViewDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an fov 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 |
BetaAngleDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handles a beta angle event and chooses 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.
|
EventDetector.Action |
EventDetector.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 |
EventShifter.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an 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 |
EclipseDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an eclipse 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 |
LocalTimeAngleDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle a local time angle event and choose what to do next.
|
EventDetector.Action |
ExtremaLongitudeDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an extrema distance 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 |
AlignmentDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle an alignment 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 |
SolarTimeAngleDetector.eventOccurred(SpacecraftState s,
boolean increasing,
boolean forward)
Handle a solar time angle event and choose what to do next.
|
double |
ThreeBodiesAngleDetector.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)
Compute the value of the switching function.
|
double |
AltitudeDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
ApparentElevationDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
ExtremaThreeBodiesAngleDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
IntervalOccurrenceDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
NodeDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
ElevationDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
NadirSolarIncidenceDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
DistanceDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
ApsideDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
ExtremaElevationDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
abstract double |
AbstractDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
AnomalyDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
AOLDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
DihedralFieldOfViewDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
LongitudeDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
BetaAngleDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
ExtremaDistanceDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
EventDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
LatitudeDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
EventShifter.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
CircularFieldOfViewDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
EclipseDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
NullMassDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
LocalTimeAngleDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
ExtremaLongitudeDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
NullMassPartDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
AlignmentDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
GroundMaskElevationDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
double |
SolarTimeAngleDetector.g(SpacecraftState s)
Compute the value of the switching function.
|
protected AbsoluteDate |
AbstractDetector.getSignalEmissionDate(PVCoordinatesProvider emitter,
SpacecraftState s,
double epsilon,
AbstractDetector.PropagationDelayType delayType)
Compute signal emission date which is date at which currently seen signal by spacecraft has been emitted by
emitter depending on
AbstractDetector.PropagationDelayType. |
protected AbsoluteDate |
AbstractDetector.getSignalReceptionDate(PVCoordinatesProvider receiver,
SpacecraftState s,
double epsilon,
AbstractDetector.PropagationDelayType delayType)
Compute signal reception date which is date at which currently seen signal by receiver has been emitted by
spacecraft (emitter) depending on
AbstractDetector.PropagationDelayType. |
void |
ThreeBodiesAngleDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
ExtremaLatitudeDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
ExtremaThreeBodiesAngleDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
IntervalOccurrenceDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
NadirSolarIncidenceDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
DistanceDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
ExtremaElevationDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
AbstractDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
AnomalyDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
AOLDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
LongitudeDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
BetaAngleDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
ExtremaDistanceDetector.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 |
LatitudeDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
EventShifter.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
LocalTimeAngleDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
ExtremaLongitudeDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
SolarTimeAngleDetector.init(SpacecraftState s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
protected void |
IntervalOccurrenceDetector.processEventOccurrence(SpacecraftState s,
boolean increasing,
boolean forward)
Process the event occurrence.
|
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 |
IntervalOccurrenceDetector.resetState(SpacecraftState oldState)
Reset the state (including additional states) prior to continue propagation.
|
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 |
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.
|
| Modifier and Type | Method and Description |
|---|---|
EventDetector.Action |
ThreeBodiesAngleDetector.eventOccurred(Map<String,SpacecraftState> s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next.
|
EventDetector.Action |
ExtremaThreeBodiesAngleDetector.eventOccurred(Map<String,SpacecraftState> s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next.
|
double |
ThreeBodiesAngleDetector.g(Map<String,SpacecraftState> s)
Compute the value of the switching function.
|
double |
ExtremaThreeBodiesAngleDetector.g(Map<String,SpacecraftState> s)
Compute the value of the switching function.
|
void |
ThreeBodiesAngleDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
ExtremaThreeBodiesAngleDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
Map<String,SpacecraftState> |
ThreeBodiesAngleDetector.resetStates(Map<String,SpacecraftState> oldStates)
Reset the states (including additional states) prior to continue propagation.
|
Map<String,SpacecraftState> |
ExtremaThreeBodiesAngleDetector.resetStates(Map<String,SpacecraftState> oldStates)
Reset the states (including additional states) prior to continue propagation.
|
| Modifier and Type | Method and Description |
|---|---|
Map<String,SpacecraftState> |
MultiAbstractDetector.resetStates(Map<String,SpacecraftState> oldStates)
Reset the states (including additional states) prior to continue propagation.
|
Map<String,SpacecraftState> |
MultiEventDetector.resetStates(Map<String,SpacecraftState> oldStates)
Reset the states (including additional states) prior to continue propagation.
|
Map<String,SpacecraftState> |
OneSatEventDetectorWrapper.resetStates(Map<String,SpacecraftState> oldStates)
Reset the states (including additional states) prior to continue propagation.
|
| Modifier and Type | Method and Description |
|---|---|
double |
OneSatEventDetectorWrapper.g(SpacecraftState s)
Compute the value of the switching function.
|
| Modifier and Type | Method and Description |
|---|---|
abstract EventDetector.Action |
MultiAbstractDetector.eventOccurred(Map<String,SpacecraftState> s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next.
|
EventDetector.Action |
MultiEventDetector.eventOccurred(Map<String,SpacecraftState> s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next.
|
EventDetector.Action |
OneSatEventDetectorWrapper.eventOccurred(Map<String,SpacecraftState> s,
boolean increasing,
boolean forward)
Handle an event and choose what to do next.
|
abstract double |
MultiAbstractDetector.g(Map<String,SpacecraftState> s)
Compute the value of the switching function.
|
double |
MultiEventDetector.g(Map<String,SpacecraftState> s)
Compute the value of the switching function.
|
double |
OneSatEventDetectorWrapper.g(Map<String,SpacecraftState> s)
Compute the value of the switching function.
|
void |
MultiAbstractDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
MultiEventDetector.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
void |
OneSatEventDetectorWrapper.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize event handler at the start of a propagation.
|
Map<String,SpacecraftState> |
MultiAbstractDetector.resetStates(Map<String,SpacecraftState> oldStates)
Reset the states (including additional states) prior to continue propagation.
|
Map<String,SpacecraftState> |
MultiEventDetector.resetStates(Map<String,SpacecraftState> oldStates)
Reset the states (including additional states) prior to continue propagation.
|
Map<String,SpacecraftState> |
OneSatEventDetectorWrapper.resetStates(Map<String,SpacecraftState> oldStates)
Reset the states (including additional states) prior to continue propagation.
|
| Modifier and Type | Method and Description |
|---|---|
SpacecraftState |
NumericalPropagator.getInitialState()
Get the propagator initial state.
|
SpacecraftState |
NumericalPropagator.getSpacecraftState(AbsoluteDate date)
Get the
SpacecraftState at provided dat. |
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 s0)
Set the initial value of the Jacobian with respect to state and parameter.
|
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 s,
Parameter parameter,
double[] dY1dP)
Set the initial value of the Jacobian with respect to state.
|
| Modifier and Type | Method and Description |
|---|---|
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 |
AdditionalEquations.computeDerivatives(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the derivatives related to the additional state parameters.
|
void |
PartialDerivativesEquations.computeDerivatives(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the derivatives related to the additional state parameters.
|
double[] |
AdditionalEquations.computeSecondDerivatives(SpacecraftState s)
Compute the second derivatives related to the additional state parameters.
|
double[] |
PartialDerivativesEquations.computeSecondDerivatives(SpacecraftState s)
Compute the second 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 s0)
Set the initial value of the Jacobian with respect to state and parameter.
|
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.
|
void |
JacobiansMapper.setInitialJacobians(SpacecraftState state,
double[][] dY1dY0,
double[][] dY1dP,
double[] p)
Set the Jacobian with respect to state into a one-dimensional additional state array.
|
SpacecraftState |
PartialDerivativesEquations.setInitialJacobians(SpacecraftState s,
Parameter parameter,
double[] dY1dP)
Set the initial value of the Jacobian with respect to state.
|
void |
NumericalPropagator.setInitialState(SpacecraftState initialStateIn)
Set the initial state.
|
| Modifier and Type | Method and Description |
|---|---|
SpacecraftState |
MultiStateVectorInfo.mapArrayToState(double[] y,
AbsoluteDate currentDate,
OrbitType orbitType,
PositionAngle angleType,
MultiAttitudeProvider attProviderForces,
MultiAttitudeProvider attProviderEvents,
String id)
Extract a given SpacecraftState from the state vector.
|
SpacecraftState |
MultiPartialDerivativesEquations.setInitialJacobians(SpacecraftState s,
double[][] dY1dY0)
Set the initial value of the Jacobian with respect to state.
|
SpacecraftState |
MultiPartialDerivativesEquations.setInitialJacobians(SpacecraftState s1,
double[][] dY1dY0,
double[][] dY1dP)
Set the initial value of the Jacobian with respect to state and parameter.
|
SpacecraftState |
MultiPartialDerivativesEquations.setInitialJacobians(SpacecraftState s0,
int paramDimension)
Set the initial value of the Jacobian with respect to state and parameter.
|
SpacecraftState |
MultiPartialDerivativesEquations.setInitialJacobians(SpacecraftState s,
Parameter parameter,
double[] dY1dP)
Set the initial value of the Jacobian with respect to state.
|
| Modifier and Type | Method and Description |
|---|---|
Map<String,SpacecraftState> |
MultiNumericalPropagator.getInitialStates()
Get the propagator initial states.
|
Map<String,SpacecraftState> |
MultiStateVectorInfo.mapArrayToStates(double[] y,
AbsoluteDate currentDate,
OrbitType orbitType,
PositionAngle angleType,
Map<String,MultiAttitudeProvider> attProvidersForces,
Map<String,MultiAttitudeProvider> attProvidersEvents,
Map<String,Double> mu,
Map<String,Frame> integrationFrame)
Convert state vector into a Map of SpacecraftState
|
Map<String,SpacecraftState> |
MultiNumericalPropagator.propagate(AbsoluteDate target)
Propagate towards a target date.
|
Map<String,SpacecraftState> |
MultiNumericalPropagator.propagate(AbsoluteDate start,
AbsoluteDate target)
Propagate from a start date towards a target date.
|
| Modifier and Type | Method and Description |
|---|---|
void |
MultiNumericalPropagator.addInitialState(SpacecraftState initialState,
String satId)
Add a new spacecraft state to be propagated.
|
void |
MultiPartialDerivativesEquations.computeDerivatives(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the derivatives related to the additional state parameters.
|
double[] |
MultiPartialDerivativesEquations.computeSecondDerivatives(SpacecraftState s)
Compute the second derivatives related to the additional state parameters.
|
SpacecraftState |
MultiPartialDerivativesEquations.setInitialJacobians(SpacecraftState s,
double[][] dY1dY0)
Set the initial value of the Jacobian with respect to state.
|
SpacecraftState |
MultiPartialDerivativesEquations.setInitialJacobians(SpacecraftState s1,
double[][] dY1dY0,
double[][] dY1dP)
Set the initial value of the Jacobian with respect to state and parameter.
|
SpacecraftState |
MultiPartialDerivativesEquations.setInitialJacobians(SpacecraftState s0,
int paramDimension)
Set the initial value of the Jacobian with respect to state and parameter.
|
SpacecraftState |
MultiPartialDerivativesEquations.setInitialJacobians(SpacecraftState s,
Parameter parameter,
double[] dY1dP)
Set the initial value of the Jacobian with respect to state.
|
| Modifier and Type | Method and Description |
|---|---|
void |
MultiStateVectorInfo.mapStatesToArray(Map<String,SpacecraftState> s,
OrbitType orbitType,
PositionAngle angleType,
double[] y)
Convert a map of SpacecraftState into a state vector.
|
| Constructor and Description |
|---|
MultiStateVectorInfo(Map<String,SpacecraftState> s,
Map<String,Double> mus,
Map<String,Frame> frames)
Build a MultiSatStateVectorInfo instance using the spacecraft states' map.
|
| Modifier and Type | Method and Description |
|---|---|
SpacecraftState |
Ephemeris.basicPropagate(AbsoluteDate date) |
protected SpacecraftState |
IntegratedEphemeris.basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features.
|
SpacecraftState |
Ephemeris.getInitialState()
Get the propagator initial state.
|
SpacecraftState |
IntegratedEphemeris.getInitialState()
Get the propagator initial state.
|
SpacecraftState |
Ephemeris.getSpacecraftState(AbsoluteDate date)
Get the
SpacecraftState at provided dat. |
| Modifier and Type | Method and Description |
|---|---|
void |
Ephemeris.resetInitialState(SpacecraftState state)
Try (and fail) to reset the initial state.
|
void |
IntegratedEphemeris.resetInitialState(SpacecraftState state)
Reset the propagator initial state.
|
| Constructor and Description |
|---|
Ephemeris(List<SpacecraftState> states,
int interpolationPoints)
Constructor with tabulated states.
|
| Modifier and Type | Method and Description |
|---|---|
protected SpacecraftState |
MultiIntegratedEphemeris.basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features.
|
SpacecraftState |
MultiIntegratedEphemeris.getInitialState()
Get the propagator initial state.
|
| Modifier and Type | Method and Description |
|---|---|
void |
MultiIntegratedEphemeris.resetInitialState(SpacecraftState state)
Reset the propagator initial state.
|
| Modifier and Type | Method and Description |
|---|---|
SpacecraftState |
AdaptedStepHandler.getInterpolatedState()
Get the interpolated state.
|
SpacecraftState |
BasicStepInterpolator.getInterpolatedState()
Get the interpolated state.
|
SpacecraftState |
PatriusStepInterpolator.getInterpolatedState()
Get the interpolated state.
|
| Modifier and Type | Method and Description |
|---|---|
void |
PatriusFixedStepHandler.handleStep(SpacecraftState currentState,
boolean isLast)
Handle the current step.
|
void |
PatriusStepHandler.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation.
|
void |
PatriusStepNormalizer.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation.
|
void |
PatriusFixedStepHandler.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation.
|
void |
PatriusStepHandlerMultiplexer.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation.
|
| Modifier and Type | Method and Description |
|---|---|
Map<String,SpacecraftState> |
MultiPatriusStepInterpolator.getInterpolatedStates()
Get all the interpolated states.
|
Map<String,SpacecraftState> |
MultiAdaptedStepHandler.getInterpolatedStates()
Get all the interpolated states.
|
| Modifier and Type | Method and Description |
|---|---|
void |
MultiPatriusFixedStepHandler.handleStep(Map<String,SpacecraftState> currentStates,
boolean isLast)
Handle the current step.
|
void |
MultiPatriusStepHandler.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation.
|
void |
MultiPatriusFixedStepHandler.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation.
|
void |
MultiPatriusStepNormalizer.init(Map<String,SpacecraftState> s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation.
|
| Modifier and Type | Method and Description |
|---|---|
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.
|
| Modifier and Type | Method and Description |
|---|---|
void |
StelaAeroModel.addDDragAccDParam(SpacecraftState s,
Parameter param,
double density,
Vector3D relativeVelocity,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters (the ballistic
coefficient).
|
void |
StelaAeroModel.addDDragAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel,
double density,
Vector3D acceleration,
Vector3D relativeVelocity,
boolean computeGradientPosition,
boolean computeGradientVelocity)
Compute acceleration derivatives with respect to state parameters (position and velocity).
|
Vector3D |
StelaAeroModel.dragAcceleration(SpacecraftState state,
double density,
Vector3D relativeVelocity)
Return the drag acceleration in the CIRF frame.
|
| Modifier and Type | Method and Description |
|---|---|
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 |
StelaBasicInterpolator.getInitialState() |
SpacecraftState |
StelaAbstractPropagator.getInitialState()
Get the propagator initial state.
|
SpacecraftState |
StelaBasicInterpolator.getInterpolatedState()
Get the interpolated state.
|
SpacecraftState |
StelaAbstractPropagator.getSpacecraftState(AbsoluteDate date)
Get the
SpacecraftState at provided dat. |
protected 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)
Propagate from a start date towards a target date.
|
protected abstract SpacecraftState |
StelaAbstractPropagator.propagateSpacecraftState(AbsoluteDate date)
Extrapolate a spacecraftState up to a specific target date.
|
protected SpacecraftState |
StelaGTOPropagator.propagateSpacecraftState(AbsoluteDate date)
Extrapolate a spacecraftState up to a specific target date.
|
protected 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.
|
protected SpacecraftState |
StelaGTOPropagator.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.
|
| Modifier and Type | Method and Description |
|---|---|
SpacecraftState |
StelaPartialDerivativesEquations.addInitialAdditionalState(SpacecraftState state) |
SpacecraftState |
StelaAdditionalEquations.addInitialAdditionalState(SpacecraftState state) |
void |
ForcesStepHandler.init(SpacecraftState s0,
AbsoluteDate t)
Initialize step handler at the start of a propagation.
|
protected 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.
|
protected SpacecraftState |
StelaGTOPropagator.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.
|
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.
|
| Modifier and Type | Method and Description |
|---|---|
Vector3D |
WrenchModel.computeTorque(SpacecraftState s)
Compute the resulting torque at the mass centre of the spacecraft in the frame of the main part.
|
Vector3D |
SolarRadiationWrench.computeTorque(SpacecraftState s)
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 |
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 |
MagneticWrench.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.
|
Vector3D |
SolarRadiationWrench.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 |
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 |
MagneticWrench.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 |
SolarRadiationWrench.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 |
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 |
MagneticWrench.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.
|
Wrench |
SolarRadiationWrench.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 |
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 |
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.
|
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