Package | Description |
---|---|
org.orekit.orbits |
This package provides classes to represent orbits.
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org.orekit.propagation |
Propagation
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org.orekit.propagation.analytical |
Top level package for analytical propagators.
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org.orekit.propagation.events |
This package provides interfaces and classes dealing with events occurring during propagation.
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org.orekit.propagation.integration |
Utilities for integration-based propagators (both numerical and semi-analytical).
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org.orekit.propagation.numerical |
Top level package for numerical propagators.
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Modifier and Type | Class | Description |
---|---|---|
class |
FieldCartesianOrbit<T extends org.hipparchus.RealFieldElement<T>> |
This class holds Cartesian orbital parameters.
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class |
FieldCircularOrbit<T extends org.hipparchus.RealFieldElement<T>> |
This class handles circular orbital parameters.
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class |
FieldEquinoctialOrbit<T extends org.hipparchus.RealFieldElement<T>> |
This class handles equinoctial orbital parameters, which can support both
circular and equatorial orbits.
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class |
FieldKeplerianOrbit<T extends org.hipparchus.RealFieldElement<T>> |
This class handles traditional Keplerian orbital parameters.
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Modifier and Type | Method | Description |
---|---|---|
abstract <T extends org.hipparchus.RealFieldElement<T>> |
OrbitType.convertType(FieldOrbit<T> orbit) |
Convert an orbit to the instance type.
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abstract <T extends org.hipparchus.RealFieldElement<T>> |
OrbitType.mapArrayToOrbit(T[] array,
T[] arrayDot,
PositionAngle type,
FieldAbsoluteDate<T> date,
double mu,
Frame frame) |
Convert state array to orbital parameters.
|
abstract FieldOrbit<T> |
FieldOrbit.shiftedBy(T dt) |
Get a time-shifted orbit.
|
Modifier and Type | Method | Description |
---|---|---|
abstract <T extends org.hipparchus.RealFieldElement<T>> |
OrbitType.convertType(FieldOrbit<T> orbit) |
Convert an orbit to the instance type.
|
abstract <T extends org.hipparchus.RealFieldElement<T>> |
OrbitType.mapOrbitToArray(FieldOrbit<T> orbit,
PositionAngle type,
T[] stateVector,
T[] stateVectorDot) |
Convert orbit to state array.
|
Modifier and Type | Method | Description |
---|---|---|
FieldCartesianOrbit<T> |
FieldCartesianOrbit.interpolate(FieldAbsoluteDate<T> date,
Stream<FieldOrbit<T>> sample) |
Get an interpolated instance.
|
FieldCircularOrbit<T> |
FieldCircularOrbit.interpolate(FieldAbsoluteDate<T> date,
Stream<FieldOrbit<T>> sample) |
Get an interpolated instance.
|
FieldEquinoctialOrbit<T> |
FieldEquinoctialOrbit.interpolate(FieldAbsoluteDate<T> date,
Stream<FieldOrbit<T>> sample) |
Get an interpolated instance.
|
FieldKeplerianOrbit<T> |
FieldKeplerianOrbit.interpolate(FieldAbsoluteDate<T> date,
Stream<FieldOrbit<T>> sample) |
Get an interpolated instance.
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Constructor | Description |
---|---|
FieldCartesianOrbit(FieldOrbit<T> op) |
Constructor from any kind of orbital parameters.
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FieldCircularOrbit(FieldOrbit<T> op) |
Constructor from any kind of orbital parameters.
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FieldEquinoctialOrbit(FieldOrbit<T> op) |
Constructor from any kind of orbital parameters.
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FieldKeplerianOrbit(FieldOrbit<T> op) |
Constructor from any kind of orbital parameters.
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Modifier and Type | Method | Description |
---|---|---|
FieldOrbit<T> |
FieldSpacecraftState.getOrbit() |
Gets the current orbit.
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Constructor | Description |
---|---|
FieldSpacecraftState(FieldOrbit<T> orbit) |
Build a spacecraft state from orbit only.
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FieldSpacecraftState(FieldOrbit<T> orbit,
Map<String,T[]> additional) |
Build a spacecraft state from orbit only.
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FieldSpacecraftState(FieldOrbit<T> orbit,
FieldAttitude<T> attitude) |
Build a spacecraft state from orbit and attitude provider.
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FieldSpacecraftState(FieldOrbit<T> orbit,
FieldAttitude<T> attitude,
Map<String,T[]> additional) |
Build a spacecraft state from orbit and attitude provider.
|
FieldSpacecraftState(FieldOrbit<T> orbit,
FieldAttitude<T> attitude,
T mass) |
Build a spacecraft state from orbit, attitude provider and mass.
|
FieldSpacecraftState(FieldOrbit<T> orbit,
FieldAttitude<T> attitude,
T mass,
Map<String,T[]> additional) |
Build a spacecraft state from orbit, attitude provider and mass.
|
FieldSpacecraftState(FieldOrbit<T> orbit,
T mass) |
Create a new instance from orbit and mass.
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FieldSpacecraftState(FieldOrbit<T> orbit,
T mass,
Map<String,T[]> additional) |
Create a new instance from orbit and mass.
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Modifier and Type | Method | Description |
---|---|---|
protected abstract FieldOrbit<T> |
FieldAbstractAnalyticalPropagator.propagateOrbit(FieldAbsoluteDate<T> date) |
Extrapolate an orbit up to a specific target date.
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protected FieldOrbit<T> |
FieldKeplerianPropagator.propagateOrbit(FieldAbsoluteDate<T> date) |
Extrapolate an orbit up to a specific target date.
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Constructor | Description |
---|---|
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
double referenceRadius,
double mu,
double c20,
double c30,
double c40,
double c50,
double c60) |
Build a propagator from FieldOrbit
|
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitudeProv,
double referenceRadius,
double mu,
double c20,
double c30,
double c40,
double c50,
double c60) |
Build a propagator from FieldOrbit
|
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitudeProv,
UnnormalizedSphericalHarmonicsProvider provider) |
Build a propagator from FieldOrbit
|
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitudeProv,
T mass,
double referenceRadius,
double mu,
double c20,
double c30,
double c40,
double c50,
double c60) |
Build a propagator from FieldOrbit
|
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitudeProv,
T mass,
UnnormalizedSphericalHarmonicsProvider provider) |
Build a propagator from FieldOrbit
|
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitude,
T mass,
UnnormalizedSphericalHarmonicsProvider provider,
UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics) |
Private helper constructor.
|
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
UnnormalizedSphericalHarmonicsProvider provider) |
Build a propagator from FieldOrbit
|
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
T mass,
double referenceRadius,
double mu,
double c20,
double c30,
double c40,
double c50,
double c60) |
Build a propagator from FieldOrbit
|
FieldEcksteinHechlerPropagator(FieldOrbit<T> initialOrbit,
T mass,
UnnormalizedSphericalHarmonicsProvider provider) |
Build a propagator from FieldOrbit
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FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit) |
Build a propagator from orbit only.
|
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit,
double mu) |
Build a propagator from orbit and central attraction coefficient μ.
|
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit,
AttitudeProvider attitudeProv) |
Build a propagator from orbit and attitude provider.
|
FieldKeplerianPropagator(FieldOrbit<T> initialFieldOrbit,
AttitudeProvider attitudeProv,
double mu) |
Build a propagator from orbit, attitude provider and central attraction
coefficient μ.
|
FieldKeplerianPropagator(FieldOrbit<T> initialOrbit,
AttitudeProvider attitudeProv,
double mu,
T mass) |
Build propagator from orbit, attitude provider, central attraction
coefficient μ and mass.
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Constructor | Description |
---|---|
FieldApsideDetector(FieldOrbit<T> orbit) |
Build a new instance.
|
FieldApsideDetector(T threshold,
FieldOrbit<T> orbit) |
Build a new instance.
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FieldNodeDetector(FieldOrbit<T> orbit,
Frame frame) |
Build a new instance.
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FieldNodeDetector(T threshold,
FieldOrbit<T> orbit,
Frame frame) |
Build a new instance.
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Modifier and Type | Method | Description |
---|---|---|
protected FieldOrbit<T> |
FieldIntegratedEphemeris.propagateOrbit(FieldAbsoluteDate<T> date) |
Extrapolate an orbit up to a specific target date.
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Modifier and Type | Method | Description |
---|---|---|
static <T extends org.hipparchus.RealFieldElement<T>> |
FieldNumericalPropagator.tolerances(T dP,
FieldOrbit<T> orbit,
OrbitType type) |
Estimate tolerance vectors for integrators.
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