| Modifier and Type | Method and Description |
|---|---|
OrbitType |
AbstractOrbitalCovariance.getOrbitType()
Gets the orbit type of covariance.
|
| Modifier and Type | Method and Description |
|---|---|
protected void |
AbstractOrbitalCovariance.checkParameterDescriptors(int startIndex,
OrbitType expectedOrbitType)
Starting from the specified index, checks that the first six parameter descriptors associated
with the covariance have an orbital
coordinate descriptor which is mapped to an OrbitalCoordinate instance with the
expected state vector index.
|
protected static List<ParameterDescriptor> |
AbstractOrbitalCovariance.convertParameterDescriptors(Collection<ParameterDescriptor> parameterDescriptors,
OrbitType destOrbitType,
PositionAngle destPositionAngle)
Returns an updated list of parameter descriptors where the orbital coordinates mapped to the
orbital coordinate descriptors were
all converted to the specified orbit type and position angle type.
|
T |
AbstractOrbitalCovariance.transformTo(Frame destFrame,
OrbitType destOrbitType)
Transforms this orbital covariance to the specified frame, orbit type.
|
OrbitalCovariance |
OrbitalCovariance.transformTo(Frame destFrame,
OrbitType destOrbitType,
PositionAngle destPositionAngle)
Transforms this orbital covariance to the specified frame, orbit type and position angle
type.
|
MultiOrbitalCovariance |
MultiOrbitalCovariance.transformTo(Frame destFrame,
OrbitType destOrbitType,
PositionAngle destPositionAngle)
Transforms this orbital covariance to the specified frame, orbit type and position angle
type.
|
abstract T |
AbstractOrbitalCovariance.transformTo(Frame destFrame,
OrbitType destOrbitType,
PositionAngle destPositionAngle)
Transforms this orbital covariance to the specified frame, orbit type and position angle
type.
|
T |
AbstractOrbitalCovariance.transformTo(OrbitType destOrbitType)
Transforms this orbital covariance to the specified orbit type.
|
T |
AbstractOrbitalCovariance.transformTo(OrbitType destOrbitType,
PositionAngle destPositionAngle)
Transforms this orbital covariance to the specified orbit type and position angle type.
|
| Constructor and Description |
|---|
AbstractOrbitalCovariance(Covariance covarianceIn,
Frame frameIn,
OrbitType orbitTypeIn,
PositionAngle positionAngleIn)
Creates a new instance from the supplied covariance, frame, orbit type and position angle
type.
|
AbstractOrbitalCovariance(SymmetricPositiveMatrix covarianceIn,
Frame frameIn,
OrbitType orbitTypeIn,
PositionAngle positionAngleIn)
Creates a new instance from the supplied covariance matrix, frame, orbit type and position
angle type.
|
MultiOrbitalCovariance(Covariance covariance,
Collection<Orbit> orbits,
int[] nbAdditionalParametersIn,
Frame frame,
OrbitType orbitType,
PositionAngle positionAngle)
Creates a new instance that associates a covariance matrix with multiple orbits, the
covariance being defined in the specified frame, orbit type and position angle type.
|
MultiOrbitalCovariance(SymmetricPositiveMatrix covarianceMatrix,
Collection<Orbit> orbits,
int[] nbAdditionalParametersIn,
Frame frame,
OrbitType orbitType,
PositionAngle positionAngle)
Creates a new instance that associates a covariance matrix with multiple orbits, the
covariance being defined in the specified frame, orbit type and position angle type.
|
OrbitalCovariance(Covariance covariance,
Orbit orbit,
Frame frame,
OrbitType orbitType,
PositionAngle positionAngle)
Creates a new instance that associates a covariance matrix with a given orbit, the covariance
being defined in the specified frame, orbit type and position angle type.
|
OrbitalCovariance(SymmetricPositiveMatrix covarianceMatrix,
Orbit orbit,
Frame frame,
OrbitType orbitType,
PositionAngle positionAngle)
Creates a new instance that associates a covariance matrix with a given orbit, the covariance
being defined in the specified frame, orbit type and position angle type.
|
| 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.
|
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 |
|---|
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.
|
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 |
|---|---|
static List<ParameterDescriptor> |
ParameterUtils.buildOrbitalParameterDescriptors(OrbitType orbitType,
PositionAngle positionAngle)
Builds the parameter descriptors associated with a given orbit type and position angle type,
each representing one of the orbital coordinates.
|
static List<Parameter> |
ParameterUtils.buildOrbitalParameters(OrbitType orbitType,
PositionAngle positionAngle)
Builds the parameters associated with a given orbit type and position angle type, each one
representing one of the orbital coordinates.
|
| Modifier and Type | Method and Description |
|---|---|
abstract OrbitType |
Orbit.getType()
Get the orbit type.
|
OrbitType |
KeplerianOrbit.getType()
Get the orbit type.
|
OrbitType |
EquinoctialOrbit.getType()
Get the orbit type.
|
OrbitType |
EquatorialOrbit.getType()
Get the orbit type.
|
OrbitType |
CircularOrbit.getType()
Get the orbit type.
|
OrbitType |
CartesianOrbit.getType()
Get the orbit type.
|
OrbitType |
ApsisOrbit.getType()
Get the orbit type.
|
OrbitType |
AlternateEquinoctialOrbit.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(double dt,
Frame initFrame,
Frame destFrame,
OrbitType initOrbitType,
OrbitType destOrbitType,
PositionAngle initAngleType,
PositionAngle destAngleType)
Computes the Jacobian of the transformation between the specified frames, orbit types and
position angle types with respect to this orbit and specified time shift.
|
RealMatrix |
Orbit.getJacobian(Frame initFrame,
Frame destFrame,
OrbitType initOrbitType,
OrbitType destOrbitType,
PositionAngle initAngleType,
PositionAngle destAngleType)
Computes the Jacobian of the transformation between the specified frames, orbit types and
position angle types with respect to this orbit.
|
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 |
|---|---|
OrbitType |
OrbitalCoordinate.getOrbitType()
Gets the orbit type to which this orbital coordinate is related.
|
OrbitType |
KeplerianCoordinate.getOrbitType()
Gets the orbit type to which this orbital coordinate is related.
|
OrbitType |
EquinoctialCoordinate.getOrbitType()
Gets the orbit type to which this orbital coordinate is related.
|
OrbitType |
EquatorialCoordinate.getOrbitType()
Gets the orbit type to which this orbital coordinate is related.
|
OrbitType |
CircularCoordinate.getOrbitType()
Gets the orbit type to which this orbital coordinate is related.
|
OrbitType |
CartesianCoordinate.getOrbitType()
Gets the orbit type to which this orbital coordinate is related.
|
OrbitType |
ApsisRadiusCoordinate.getOrbitType()
Gets the orbit type to which this orbital coordinate is related.
|
OrbitType |
ApsisAltitudeCoordinate.getOrbitType()
Gets the orbit type to which this orbital coordinate is related.
|
OrbitType |
AlternateEquinoctialCoordinate.getOrbitType()
Gets the orbit type to which this orbital coordinate is related.
|
| Modifier and Type | Method and Description |
|---|---|
default OrbitalCoordinate |
OrbitalCoordinate.convertTo(OrbitType orbitType,
PositionAngle positionAngle)
Gets the coordinate type associated with the same state vector index in a given orbit type
and position angle type.
|
| 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 |
|---|---|
protected OrbitType |
PartialDerivativesEquations.getOrbitType()
Returns the propagator orbit type.
|
OrbitType |
NumericalPropagator.getOrbitType()
Get propagation parameter type.
|
OrbitType |
JacobiansMapper.getOrbitType()
Getter for the orbit type.
|
protected abstract OrbitType |
AbstractPartialDerivativesEquations.getOrbitType()
Returns the propagator orbit type.
|
| Modifier and Type | Method and Description |
|---|---|
void |
JacobiansMapper.getParametersJacobian(Parameter parameter,
SpacecraftState state,
double[] dYdP,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
Frame frameIn)
Get the Jacobian with respect to provided parameter
parameter. |
double[] |
JacobiansMapper.getParametersJacobian(Parameter parameter,
SpacecraftState state,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
Frame frameIn)
Get the Jacobian with respect to provided parameter
parameter. |
void |
JacobiansMapper.getParametersJacobian(SpacecraftState state,
double[][] dYdP,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
Frame frameIn)
Get the Jacobian with respect to parameters.
|
double[][] |
JacobiansMapper.getParametersJacobian(SpacecraftState state,
OrbitType orbitTypeOut,
PositionAngle angleTypeOut,
Frame frameOut)
Get the Jacobian with respect to parameters.
|
void |
JacobiansMapper.getStateJacobian(SpacecraftState state,
double[][] dYdY0,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
Frame frameIn)
Get the Jacobian with respect to state.
|
double[][] |
JacobiansMapper.getStateJacobian(SpacecraftState state,
OrbitType orbitTypeOut,
PositionAngle angleTypeOut,
Frame frameOut)
Get the Jacobian with respect to state.
|
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.
|
static double[][] |
NumericalPropagator.tolerances(double dP,
Orbit orbit,
OrbitType type)
Estimate tolerance vectors for integrators.
|
| Constructor and Description |
|---|
JacobiansMapper(String nameIn,
List<Parameter> list,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
Frame frame)
Simple constructor.
|
NumericalPropagator(FirstOrderIntegrator integratorIn,
Frame propagationFrameIn,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn)
Create a new instance of NumericalPropagator, based on orbit definition mu.
|
| Modifier and Type | Method and Description |
|---|---|
protected OrbitType |
MultiPartialDerivativesEquations.getOrbitType()
Returns the propagator orbit type.
|
OrbitType |
MultiNumericalPropagator.getOrbitType()
Get propagation parameter type.
|
| Modifier and Type | Method and Description |
|---|---|
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.
|
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.
|
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.
|
| Constructor and Description |
|---|
MultiNumericalPropagator(FirstOrderIntegrator integratorIn,
Map<String,Frame> propagationFrameMapIn,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn)
Create a new instance of MultiNumericalPropagator.
|
| 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.
|
IntegratedEphemeris(List<AbsoluteDate> startDatesIn,
List<AbsoluteDate> minDatesIn,
List<AbsoluteDate> maxDatesIn,
OrbitType orbitTypeIn,
PositionAngle angleTypeIn,
AttitudeProvider attitudeProvider,
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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