Modifier and Type | Method and Description |
---|---|
OrbitType |
EquinoctialOrbit.getType()
Get the orbit type.
|
OrbitType |
AlternateEquinoctialOrbit.getType()
Get the orbit type.
|
OrbitType |
KeplerianOrbit.getType()
Get the orbit type.
|
OrbitType |
CartesianOrbit.getType()
Get the orbit type.
|
OrbitType |
EquatorialOrbit.getType()
Get the orbit type.
|
abstract OrbitType |
Orbit.getType()
Get the orbit type.
|
OrbitType |
ApsisOrbit.getType()
Get the orbit type.
|
OrbitType |
CircularOrbit.getType()
Get the orbit type.
|
static OrbitType |
OrbitType.valueOf(String name)
Returns the enum constant of this type with the specified name.
|
static OrbitType[] |
OrbitType.values()
Returns an array containing the constants of this enum type, in
the order they are declared.
|
Modifier and Type | Method and Description |
---|---|
RealMatrix |
Orbit.getJacobian(OrbitType numerator,
OrbitType denominator)
Get coordinate conversion jacobian.
|
RealMatrix |
Orbit.getJacobian(OrbitType numerator,
OrbitType denominator,
PositionAngle positionAngle)
Get coordinate conversion jacobian.
|
Modifier and Type | Method and Description |
---|---|
void |
SpacecraftState.mapStateToArray(OrbitType orbitType,
PositionAngle angleType,
double[] stateVector)
Convert SpacecraftState to state vector.
|
Constructor and Description |
---|
SpacecraftState(double[] y,
OrbitType orbitType,
PositionAngle angleType,
AbsoluteDate date,
double mu,
Frame frame,
Map<String,AdditionalStateInfo> addStatesInfo,
Attitude attForces,
Attitude attEvents)
Build a spacecraft from an array (a state vector) and an additional states informations map.
|
SpacecraftState(double[] y,
OrbitType orbitType,
PositionAngle angleType,
AbsoluteDate date,
double mu,
Frame frame,
Map<String,AdditionalStateInfo> addStatesInfo,
AttitudeProvider attProviderForces,
AttitudeProvider attProviderEvents)
Build a spacecraft from an array (a state vector) and an additional states informations map.
|
Modifier and Type | Method and Description |
---|---|
SymmetricMatrix |
OrbitCovariance.getCovarianceMatrix(Orbit refOrbit,
OrbitType covTypeOut,
Frame frameOut)
Covariance matrix getter.
|
Constructor and Description |
---|
OrbitCovariance(AbsoluteDate covDate,
Frame refFrame,
OrbitType coordType,
RealMatrix covMat)
Simple constructor
|
OrbitCovariance(Orbit orbit,
OrbitType coordType,
RealMatrix covMat)
Simple constructor.
|
Modifier and Type | Method and Description |
---|---|
void |
AdaptedEventDetector.reinitialize(Map<String,AdditionalStateInfo> info,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
AttitudeProvider attProviderForces,
AttitudeProvider attProviderEvents,
AbsoluteDate referenceDateIn,
double muIn,
Frame integrationFrameIn)
Reinitialize reference data.
|
Constructor and Description |
---|
AdaptedEventDetector(EventDetector detectorIn,
Map<String,AdditionalStateInfo> info,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
AttitudeProvider attProviderForces,
AttitudeProvider attProviderEvents,
AbsoluteDate referenceDateIn,
double muIn,
Frame integrationFrameIn)
Build a wrapped event detector.
|
Modifier and Type | Method and Description |
---|---|
void |
AdaptedMultiEventDetector.reinitialize(OrbitType orbitType,
PositionAngle angleType,
Map<String,MultiAttitudeProvider> attProvidersForces,
Map<String,MultiAttitudeProvider> attProvidersEvents,
AbsoluteDate referenceDate,
Map<String,Double> muMap,
Map<String,Frame> framesMap,
MultiStateVectorInfo stateVectorInfo)
Reinitialize data.
|
void |
AdaptedMonoEventDetector.reinitialize(OrbitType orbitType,
PositionAngle angleType,
MultiAttitudeProvider attProviderForces,
MultiAttitudeProvider attProviderEvents,
AbsoluteDate referenceDate,
MultiStateVectorInfo stateVectorInfo,
String satId)
Reinitialize data.
|
Constructor and Description |
---|
AdaptedMonoEventDetector(EventDetector detector,
OrbitType orbitType,
PositionAngle angleType,
MultiAttitudeProvider attProviderForces,
MultiAttitudeProvider attProviderEvents,
AbsoluteDate referenceDate,
MultiStateVectorInfo stateVectorInfo,
String satId)
Build a wrapped event detector.
|
AdaptedMultiEventDetector(MultiEventDetector detector,
OrbitType orbitType,
PositionAngle angleType,
Map<String,MultiAttitudeProvider> attProvidersForces,
Map<String,MultiAttitudeProvider> attProvidersEvents,
AbsoluteDate referenceDate,
Map<String,Double> muMap,
Map<String,Frame> framesMap,
MultiStateVectorInfo stateVectorInfo)
Build a wrapped multi-sat event detector.
|
Modifier and Type | Method and Description |
---|---|
OrbitType |
NumericalPropagator.getOrbitType()
Get propagation parameter type.
|
Modifier and Type | Method and Description |
---|---|
void |
ModeHandler.initialize(OrbitType orbit,
PositionAngle angle,
AttitudeProvider attitudeProviderForces,
AttitudeProvider attitudeProviderEvents,
Map<String,AdditionalStateInfo> additionalStateInfos,
boolean activateHandlers,
AbsoluteDate reference,
Frame frame,
double mu)
Initialize the mode handler.
|
void |
NumericalPropagator.setOrbitType(OrbitType orbitTypeIn)
Set propagation orbit type.
|
static double[][] |
NumericalPropagator.tolerances(double dP,
Orbit orbit,
OrbitType type)
Estimate tolerance vectors for integrators.
|
Modifier and Type | Method and Description |
---|---|
OrbitType |
MultiNumericalPropagator.getOrbitType()
Get propagation parameter type.
|
Modifier and Type | Method and Description |
---|---|
void |
MultiEphemerisModeHandler.initialize(OrbitType orbit,
PositionAngle angle,
Map<String,MultiAttitudeProvider> attitudeProvidersForces,
Map<String,MultiAttitudeProvider> attitudeProvidersEvents,
MultiStateVectorInfo stateVectorInfo,
boolean activateHandlers,
AbsoluteDate reference,
Map<String,Frame> frame,
Map<String,Double> mu)
Initialize the mode handler.
|
void |
MultiModeHandler.initialize(OrbitType orbit,
PositionAngle angle,
Map<String,MultiAttitudeProvider> attitudeProvidersForces,
Map<String,MultiAttitudeProvider> attitudeProvidersEvents,
MultiStateVectorInfo stateVectorInfo,
boolean activateHandlers,
AbsoluteDate reference,
Map<String,Frame> frame,
Map<String,Double> mu)
Initialize the mode handler.
|
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.
|
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
|
void |
MultiStateVectorInfo.mapStatesToArray(Map<String,SpacecraftState> s,
OrbitType orbitType,
PositionAngle angleType,
double[] y)
Convert a map of SpacecraftState into a state vector.
|
void |
MultiNumericalPropagator.setOrbitType(OrbitType orbitTypeIn)
Set propagation orbit type.
|
Constructor and Description |
---|
IntegratedEphemeris(List<AbsoluteDate> startDatesIn,
List<AbsoluteDate> minDatesIn,
List<AbsoluteDate> maxDatesIn,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
AttitudeProvider attitudeForcesProvider,
AttitudeProvider attitudeEventsProvider,
Map<String,AdditionalStateInfo> additionalStateInfos,
List<ContinuousOutputModel> modelsIn,
Frame referenceFrameIn,
double muIn)
Creates a new instance of IntegratedEphemeris.
|
Constructor and Description |
---|
MultiIntegratedEphemeris(List<AbsoluteDate> startDatesIn,
List<AbsoluteDate> minDatesIn,
List<AbsoluteDate> maxDatesIn,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
MultiAttitudeProvider multiAttitudeProviderForcesIn,
MultiAttitudeProvider multiAttitudeProviderEventsIn,
MultiStateVectorInfo stateInfos,
List<ContinuousOutputModel> modelsIn,
Frame referenceFrameIn,
String satIdIn)
Creates a new instance of IntegratedEphemeris.
|
Modifier and Type | Method and Description |
---|---|
void |
AdaptedStepHandler.initialize(OrbitType orbit,
PositionAngle angle,
AttitudeProvider attitudeProviderForces,
AttitudeProvider attitudeProviderEvents,
Map<String,AdditionalStateInfo> additionalStateInfos,
boolean activateHandlers,
AbsoluteDate reference,
Frame frame,
double mu)
Initialize the mode handler.
|
Modifier and Type | Method and Description |
---|---|
void |
MultiAdaptedStepHandler.initialize(OrbitType orbit,
PositionAngle angle,
Map<String,MultiAttitudeProvider> attProvidersForces,
Map<String,MultiAttitudeProvider> attProvidersEvents,
MultiStateVectorInfo stateVectorInfo,
boolean activateHandlers,
AbsoluteDate reference,
Map<String,Frame> frameMap,
Map<String,Double> muMap)
Initialize the mode handler.
|
Modifier and Type | Method and Description |
---|---|
OrbitType |
StelaEquinoctialOrbit.getType()
Get the orbit type.
|
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