Package | Description |
---|---|
org.orekit.estimation.measurements.modifiers | |
org.orekit.forces |
This package provides the interface for force models that will be used by the
NumericalPropagator , as well as
some classical spacecraft models for surface forces (spherical, box and solar array ...). |
org.orekit.forces.drag |
This package provides all drag-related forces.
|
org.orekit.forces.gravity |
This package provides all gravity-related forces.
|
org.orekit.forces.maneuvers |
This package provides models of simple maneuvers.
|
org.orekit.forces.radiation |
This package provides all radiation pressure related forces.
|
org.orekit.propagation |
Propagation
|
org.orekit.propagation.analytical |
Top level package for analytical propagators.
|
org.orekit.propagation.events |
This package provides interfaces and classes dealing with events occurring during propagation.
|
org.orekit.propagation.events.handlers |
This package provides an interface and classes dealing with events occurrence only.
|
org.orekit.propagation.integration |
Utilities for integration-based propagators (both numerical and semi-analytical).
|
org.orekit.propagation.numerical |
Top level package for numerical propagators.
|
org.orekit.propagation.sampling |
This package provides interfaces and classes dealing with step handling during propagation.
|
Modifier and Type | Method | Description |
---|---|---|
FieldSpacecraftState<org.hipparchus.analysis.differentiation.DerivativeStructure> |
TroposphericDSConverter.getState(DiscreteTroposphericModel tropoModel) |
Get the state with the number of parameters consistent with tropospheric model.
|
Modifier and Type | Method | Description |
---|---|---|
org.hipparchus.analysis.differentiation.DerivativeStructure[] |
TroposphericDSConverter.getParameters(FieldSpacecraftState<org.hipparchus.analysis.differentiation.DerivativeStructure> state,
DiscreteTroposphericModel tropoModel) |
Get the tropospheric model parameters.
|
<T extends org.hipparchus.RealFieldElement<T>> |
RangeRateTroposphericDelayModifier.rangeRateErrorTroposphericModel(GroundStation station,
FieldSpacecraftState<T> state,
T[] parameters) |
Compute the measurement error due to Troposphere.
|
Modifier and Type | Method | Description |
---|---|---|
<T extends org.hipparchus.RealFieldElement<T>> |
AbstractParametricAcceleration.acceleration(FieldSpacecraftState<T> state,
T[] parameters) |
Compute acceleration.
|
<T extends org.hipparchus.RealFieldElement<T>> |
ForceModel.acceleration(FieldSpacecraftState<T> s,
T[] parameters) |
Compute acceleration.
|
default <T extends org.hipparchus.RealFieldElement<T>> |
ForceModel.addContribution(FieldSpacecraftState<T> s,
FieldTimeDerivativesEquations<T> adder) |
Compute the contribution of the force model to the perturbing
acceleration.
|
protected abstract <T extends org.hipparchus.RealFieldElement<T>> |
AbstractParametricAcceleration.signedAmplitude(FieldSpacecraftState<T> state,
T[] parameters) |
Compute the signed amplitude of the acceleration.
|
protected <T extends org.hipparchus.RealFieldElement<T>> |
HarmonicParametricAcceleration.signedAmplitude(FieldSpacecraftState<T> state,
T[] parameters) |
Compute the signed amplitude of the acceleration.
|
protected <T extends org.hipparchus.RealFieldElement<T>> |
PolynomialParametricAcceleration.signedAmplitude(FieldSpacecraftState<T> state,
T[] parameters) |
Compute the signed amplitude of the acceleration.
|
Modifier and Type | Method | Description |
---|---|---|
<T extends org.hipparchus.RealFieldElement<T>> |
DragForce.acceleration(FieldSpacecraftState<T> s,
T[] parameters) |
Compute acceleration.
|
Modifier and Type | Method | Description |
---|---|---|
<T extends org.hipparchus.RealFieldElement<T>> |
HolmesFeatherstoneAttractionModel.acceleration(FieldSpacecraftState<T> s,
T[] parameters) |
Compute acceleration.
|
<T extends org.hipparchus.RealFieldElement<T>> |
NewtonianAttraction.acceleration(FieldSpacecraftState<T> s,
T[] parameters) |
Compute acceleration.
|
<T extends org.hipparchus.RealFieldElement<T>> |
OceanTides.acceleration(FieldSpacecraftState<T> s,
T[] parameters) |
Compute acceleration.
|
<T extends org.hipparchus.RealFieldElement<T>> |
Relativity.acceleration(FieldSpacecraftState<T> s,
T[] parameters) |
Compute acceleration.
|
<T extends org.hipparchus.RealFieldElement<T>> |
SolidTides.acceleration(FieldSpacecraftState<T> s,
T[] parameters) |
Compute acceleration.
|
<T extends org.hipparchus.RealFieldElement<T>> |
ThirdBodyAttraction.acceleration(FieldSpacecraftState<T> s,
T[] parameters) |
Compute acceleration.
|
<T extends org.hipparchus.RealFieldElement<T>> |
NewtonianAttraction.addContribution(FieldSpacecraftState<T> s,
FieldTimeDerivativesEquations<T> adder) |
Compute the contribution of the force model to the perturbing
acceleration.
|
Modifier and Type | Method | Description |
---|---|---|
<T extends org.hipparchus.RealFieldElement<T>> |
ConstantThrustManeuver.acceleration(FieldSpacecraftState<T> s,
T[] parameters) |
Compute acceleration.
|
<T extends org.hipparchus.RealFieldElement<T>> |
ConstantThrustManeuver.addContribution(FieldSpacecraftState<T> s,
FieldTimeDerivativesEquations<T> adder) |
Compute the contribution of the force model to the perturbing
acceleration.
|
Modifier and Type | Method | Description |
---|---|---|
<T extends org.hipparchus.RealFieldElement<T>> |
SolarRadiationPressure.acceleration(FieldSpacecraftState<T> s,
T[] parameters) |
Compute acceleration.
|
Modifier and Type | Method | Description |
---|---|---|
FieldSpacecraftState<T> |
FieldSpacecraftState.addAdditionalState(String name,
T... value) |
Add an additional state.
|
FieldSpacecraftState<T> |
FieldAbstractPropagator.getInitialState() |
Get the propagator initial state.
|
FieldSpacecraftState<T> |
FieldPropagator.getInitialState() |
Get the propagator initial state.
|
FieldSpacecraftState<T> |
FieldSpacecraftState.interpolate(FieldAbsoluteDate<T> date,
Stream<FieldSpacecraftState<T>> sample) |
Get an interpolated instance.
|
FieldSpacecraftState<T> |
FieldAbstractPropagator.propagate(FieldAbsoluteDate<T> target) |
Propagate towards a target date.
|
FieldSpacecraftState<T> |
FieldPropagator.propagate(FieldAbsoluteDate<T> target) |
Propagate towards a target date.
|
FieldSpacecraftState<T> |
FieldPropagator.propagate(FieldAbsoluteDate<T> start,
FieldAbsoluteDate<T> target) |
Propagate from a start date towards a target date.
|
FieldSpacecraftState<T> |
FieldSpacecraftState.shiftedBy(double dt) |
Get a time-shifted state.
|
FieldSpacecraftState<T> |
FieldSpacecraftState.shiftedBy(T dt) |
Get a time-shifted state.
|
protected FieldSpacecraftState<T> |
FieldAbstractPropagator.updateAdditionalStates(FieldSpacecraftState<T> original) |
Update state by adding all additional states.
|
Modifier and Type | Method | Description |
---|---|---|
void |
FieldSpacecraftState.ensureCompatibleAdditionalStates(FieldSpacecraftState<T> state) |
Check if two instances have the same set of additional states available.
|
T[] |
FieldAdditionalStateProvider.getAdditionalState(FieldSpacecraftState<T> state) |
Get the additional state.
|
void |
FieldAbstractPropagator.resetInitialState(FieldSpacecraftState<T> state) |
Reset the propagator initial state.
|
void |
FieldPropagator.resetInitialState(FieldSpacecraftState<T> state) |
Reset the propagator initial state.
|
protected FieldSpacecraftState<T> |
FieldAbstractPropagator.updateAdditionalStates(FieldSpacecraftState<T> original) |
Update state by adding all additional states.
|
Modifier and Type | Method | Description |
---|---|---|
FieldSpacecraftState<T> |
FieldSpacecraftState.interpolate(FieldAbsoluteDate<T> date,
Stream<FieldSpacecraftState<T>> sample) |
Get an interpolated instance.
|
Modifier and Type | Method | Description |
---|---|---|
protected FieldSpacecraftState<T> |
FieldAbstractAnalyticalPropagator.acceptStep(org.orekit.propagation.analytical.FieldAbstractAnalyticalPropagator.FieldBasicStepInterpolator interpolator,
FieldAbsoluteDate<T> target,
double epsilon) |
Accept a step, triggering events and step handlers.
|
protected FieldSpacecraftState<T> |
FieldAbstractAnalyticalPropagator.basicPropagate(FieldAbsoluteDate<T> date) |
Propagate an orbit without any fancy features.
|
FieldSpacecraftState<T> |
FieldAbstractAnalyticalPropagator.propagate(FieldAbsoluteDate<T> start,
FieldAbsoluteDate<T> target) |
Propagate from a start date towards a target date.
|
Modifier and Type | Method | Description |
---|---|---|
void |
FieldEcksteinHechlerPropagator.resetInitialState(FieldSpacecraftState<T> state) |
Reset the propagator initial state.
|
void |
FieldKeplerianPropagator.resetInitialState(FieldSpacecraftState<T> state) |
Reset the propagator initial state.
|
protected abstract void |
FieldAbstractAnalyticalPropagator.resetIntermediateState(FieldSpacecraftState<T> state,
boolean forward) |
Reset an intermediate state.
|
protected void |
FieldEcksteinHechlerPropagator.resetIntermediateState(FieldSpacecraftState<T> state,
boolean forward) |
Reset an intermediate state.
|
protected void |
FieldKeplerianPropagator.resetIntermediateState(FieldSpacecraftState<T> state,
boolean forward) |
Reset an intermediate state.
|
Modifier and Type | Method | Description |
---|---|---|
FieldSpacecraftState<T> |
FieldEventState.EventOccurrence.getNewState() |
Get the new state for a reset action.
|
FieldSpacecraftState<T> |
FieldEventsLogger.FieldLoggedEvent.getState() |
Get the triggering state.
|
FieldSpacecraftState<T> |
FieldAbstractDetector.resetState(FieldSpacecraftState<T> oldState) |
Reset the state prior to continue propagation.
|
default FieldSpacecraftState<T> |
FieldEventDetector.resetState(FieldSpacecraftState<T> oldState) |
Reset the state prior to continue propagation.
|
Modifier and Type | Method | Description |
---|---|---|
FieldEventState.EventOccurrence<T> |
FieldEventState.doEvent(FieldSpacecraftState<T> state) |
Notify the user's listener of the event.
|
FieldEventHandler.Action |
FieldAbstractDetector.eventOccurred(FieldSpacecraftState<T> s,
boolean increasing) |
Handle the event.
|
FieldEventHandler.Action |
FieldEventDetector.eventOccurred(FieldSpacecraftState<T> s,
boolean increasing) |
Handle the event.
|
abstract T |
FieldAbstractDetector.g(FieldSpacecraftState<T> s) |
Compute the value of the switching function.
|
T |
FieldAltitudeDetector.g(FieldSpacecraftState<T> s) |
Compute the value of the switching function.
|
T |
FieldApsideDetector.g(FieldSpacecraftState<T> s) |
Compute the value of the switching function.
|
T |
FieldDateDetector.g(FieldSpacecraftState<T> s) |
Compute the value of the switching function.
|
T |
FieldEclipseDetector.g(FieldSpacecraftState<T> s) |
Compute the value of the switching function.
|
T |
FieldElevationDetector.g(FieldSpacecraftState<T> s) |
Compute the value of the switching function.
|
T |
FieldEventDetector.g(FieldSpacecraftState<T> s) |
Compute the value of the switching function.
|
T |
FieldNodeDetector.g(FieldSpacecraftState<T> s) |
Compute the value of the switching function.
|
void |
FieldAbstractDetector.init(FieldSpacecraftState<T> s0,
FieldAbsoluteDate<T> t) |
Initialize event handler at the start of a propagation.
|
default void |
FieldEventDetector.init(FieldSpacecraftState<T> s0,
FieldAbsoluteDate<T> t) |
Initialize event handler at the start of a propagation.
|
void |
FieldEventState.init(FieldSpacecraftState<T> s0,
FieldAbsoluteDate<T> t) |
Initialize event handler at the start of a propagation.
|
FieldSpacecraftState<T> |
FieldAbstractDetector.resetState(FieldSpacecraftState<T> oldState) |
Reset the state prior to continue propagation.
|
default FieldSpacecraftState<T> |
FieldEventDetector.resetState(FieldSpacecraftState<T> oldState) |
Reset the state prior to continue propagation.
|
boolean |
FieldEventState.tryAdvance(FieldSpacecraftState<T> state,
FieldOrekitStepInterpolator<T> interpolator) |
Try to accept the current history up to the given time.
|
Modifier and Type | Method | Description |
---|---|---|
default FieldSpacecraftState<T> |
FieldEventHandler.resetState(KK detector,
FieldSpacecraftState<T> oldState) |
Reset the state prior to continue propagation.
|
Modifier and Type | Method | Description |
---|---|---|
FieldEventHandler.Action |
FieldContinueOnEvent.eventOccurred(FieldSpacecraftState<T> s,
KK detector,
boolean increasing) |
Specific implementation of the eventOccurred interface.
|
FieldEventHandler.Action |
FieldEventHandler.eventOccurred(FieldSpacecraftState<T> s,
KK detector,
boolean increasing) |
eventOccurred method mirrors the same interface method as in
EventDetector
and its subclasses, but with an additional parameter that allows the calling
method to pass in an object from the detector which would have potential
additional data to allow the implementing class to determine the correct
return state. |
FieldEventHandler.Action |
FieldStopOnDecreasing.eventOccurred(FieldSpacecraftState<T> s,
KK detector,
boolean increasing) |
Handle a detection event and choose what to do next.
|
FieldEventHandler.Action |
FieldStopOnEvent.eventOccurred(FieldSpacecraftState<T> s,
KK detector,
boolean increasing) |
Specific implementation of the eventOccurred interface.
|
FieldEventHandler.Action |
FieldStopOnIncreasing.eventOccurred(FieldSpacecraftState<T> s,
KK detector,
boolean increasing) |
Handle a detection event and choose what to do next.
|
default void |
FieldEventHandler.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target) |
Initialize event handler at the start of a propagation.
|
default FieldSpacecraftState<T> |
FieldEventHandler.resetState(KK detector,
FieldSpacecraftState<T> oldState) |
Reset the state prior to continue propagation.
|
Modifier and Type | Method | Description |
---|---|---|
protected FieldSpacecraftState<T> |
FieldIntegratedEphemeris.basicPropagate(FieldAbsoluteDate<T> date) |
Propagate an orbit without any fancy features.
|
protected FieldSpacecraftState<T> |
FieldAbstractIntegratedPropagator.getInitialIntegrationState() |
Get the initial state for integration.
|
FieldSpacecraftState<T> |
FieldIntegratedEphemeris.getInitialState() |
Get the propagator initial state.
|
abstract FieldSpacecraftState<T> |
FieldStateMapper.mapArrayToState(FieldAbsoluteDate<T> date,
T[] y,
T[] yDot,
boolean meanOnly) |
Map the raw double components to a spacecraft state.
|
FieldSpacecraftState<T> |
FieldStateMapper.mapArrayToState(T t,
T[] y,
T[] yDot,
boolean meanOnly) |
Map the raw double components to a spacecraft state.
|
FieldSpacecraftState<T> |
FieldAbstractIntegratedPropagator.propagate(FieldAbsoluteDate<T> target) |
Propagate towards a target date.
|
protected FieldSpacecraftState<T> |
FieldAbstractIntegratedPropagator.propagate(FieldAbsoluteDate<T> tEnd,
boolean activateHandlers) |
Propagation with or without event detection.
|
FieldSpacecraftState<T> |
FieldAbstractIntegratedPropagator.propagate(FieldAbsoluteDate<T> tStart,
FieldAbsoluteDate<T> tEnd) |
Propagate from a start date towards a target date.
|
Modifier and Type | Method | Description |
---|---|---|
protected void |
FieldAbstractIntegratedPropagator.beforeIntegration(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> tEnd) |
Method called just before integration.
|
T[] |
FieldAbstractIntegratedPropagator.MainStateEquations.computeDerivatives(FieldSpacecraftState<T> state) |
Compute differential equations for main state.
|
T[] |
FieldAdditionalEquations.computeDerivatives(FieldSpacecraftState<T> s,
T[] pDot) |
Compute the derivatives related to the additional state parameters.
|
void |
FieldAbstractIntegratedPropagator.MainStateEquations.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target) |
Initialize the equations at the start of propagation.
|
default void |
FieldAdditionalEquations.init(FieldSpacecraftState<T> initialState,
FieldAbsoluteDate<T> target) |
Initialize the equations at the start of propagation.
|
abstract void |
FieldStateMapper.mapStateToArray(FieldSpacecraftState<T> state,
T[] y,
T[] yDot) |
Map a spacecraft state to raw double components.
|
void |
FieldIntegratedEphemeris.resetInitialState(FieldSpacecraftState<T> state) |
Reset the propagator initial state.
|
protected void |
FieldIntegratedEphemeris.resetIntermediateState(FieldSpacecraftState<T> state,
boolean forward) |
Reset an intermediate state.
|
Modifier and Type | Method | Description |
---|---|---|
void |
FieldNumericalPropagator.resetInitialState(FieldSpacecraftState<T> state) |
Reset the propagator initial state.
|
void |
FieldNumericalPropagator.setInitialState(FieldSpacecraftState<T> initialState) |
Set the initial state.
|
Modifier and Type | Method | Description |
---|---|---|
FieldSpacecraftState<T> |
FieldOrekitStepInterpolator.getCurrentState() |
Get the state at previous grid point date.
|
FieldSpacecraftState<T> |
FieldOrekitStepInterpolator.getInterpolatedState(FieldAbsoluteDate<T> date) |
Get the state at interpolated date.
|
FieldSpacecraftState<T> |
FieldOrekitStepInterpolator.getPreviousState() |
Get the state at previous grid point date.
|
Modifier and Type | Method | Description |
---|---|---|
void |
FieldOrekitFixedStepHandler.handleStep(FieldSpacecraftState<T> currentState,
boolean isLast) |
Handle the current step.
|
default void |
FieldOrekitFixedStepHandler.init(FieldSpacecraftState<T> s0,
FieldAbsoluteDate<T> t,
T step) |
Initialize step handler at the start of a propagation.
|
void |
FieldOrekitStepHandler.init(FieldSpacecraftState<T> s0,
FieldAbsoluteDate<T> t) |
Initialize step handler at the start of a propagation.
|
void |
FieldOrekitStepHandlerMultiplexer.init(FieldSpacecraftState<T> s0,
FieldAbsoluteDate<T> t) |
Initialize step handler at the start of a propagation.
|
void |
FieldOrekitStepNormalizer.init(FieldSpacecraftState<T> s0,
FieldAbsoluteDate<T> t) |
Initialize step handler at the start of a propagation.
|
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