Class AbstractIntegratedPropagator
- java.lang.Object
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- org.orekit.propagation.AbstractPropagator
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- org.orekit.propagation.integration.AbstractIntegratedPropagator
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- All Implemented Interfaces:
Propagator
,PVCoordinatesProvider
- Direct Known Subclasses:
DSSTPropagator
,GLONASSNumericalPropagator
,NumericalPropagator
public abstract class AbstractIntegratedPropagator extends AbstractPropagator
Common handling ofPropagator
methods for both numerical and semi-analytical propagators.- Author:
- Luc Maisonobe
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Nested Class Summary
Nested Classes Modifier and Type Class Description static interface
AbstractIntegratedPropagator.MainStateEquations
Differential equations for the main state (orbit, attitude and mass).
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Field Summary
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Fields inherited from interface org.orekit.propagation.Propagator
DEFAULT_MASS
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Constructor Summary
Constructors Modifier Constructor Description protected
AbstractIntegratedPropagator(ODEIntegrator integrator, PropagationType propagationType)
Build a new instance.
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Method Summary
All Methods Instance Methods Abstract Methods Concrete Methods Modifier and Type Method Description void
addAdditionalDerivativesProvider(AdditionalDerivativesProvider provider)
Add a provider for user-specified state derivatives to be integrated along with the orbit propagation.void
addEventDetector(EventDetector detector)
Add an event detector.protected void
afterIntegration()
Method called just after integration.protected void
beforeIntegration(SpacecraftState initialState, AbsoluteDate tEnd)
Method called just before integration.void
clearEventsDetectors()
Remove all events detectors.protected abstract StateMapper
createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)
Create a mapper between raw double components and spacecraft state.List<AdditionalDerivativesProvider>
getAdditionalDerivativesProviders()
Get an unmodifiable list of providers for additional derivatives.int
getBasicDimension()
Get state vector dimension without additional parameters.int
getCalls()
Get the number of calls to the differential equations computation method.EphemerisGenerator
getEphemerisGenerator()
Set up an ephemeris generator that will monitor the propagation for building an ephemeris from it once completed.Collection<EventDetector>
getEventsDetectors()
Get all the events detectors that have been added.protected SpacecraftState
getInitialIntegrationState()
Get the initial state for integration.protected ODEIntegrator
getIntegrator()
Get the integrator used by the propagator.String
getIntegratorName()
Get the integrator's name.protected abstract AbstractIntegratedPropagator.MainStateEquations
getMainStateEquations(ODEIntegrator integ)
Get the differential equations to integrate (for main state only).String[]
getManagedAdditionalStates()
Get all the names of all managed states.double
getMu()
Get the central attraction coefficient μ.protected OrbitType
getOrbitType()
Get propagation parameter type.protected PositionAngleType
getPositionAngleType()
Get propagation parameter type.PropagationType
getPropagationType()
Get the propagation type.boolean
getResetAtEnd()
Getter for the resetting flag regarding initial state.protected AttitudeProvider
initializeAttitudeProviderForDerivatives()
Method called when initializing the attitude provider used when evaluating derivatives.protected void
initMapper()
Initialize the mapper.boolean
isAdditionalStateManaged(String name)
Check if an additional state is managed.SpacecraftState
propagate(AbsoluteDate target)
Propagate towards a target date.SpacecraftState
propagate(AbsoluteDate tStart, AbsoluteDate tEnd)
Propagate from a start date towards a target date.void
resetInitialState(SpacecraftState state, PropagationType stateType)
Reset initial state with a given propagation type.void
setAttitudeProvider(AttitudeProvider attitudeProvider)
Set attitude provider.void
setMu(double mu)
Set the central attraction coefficient μ.protected void
setOrbitType(OrbitType orbitType)
Set propagation orbit type.protected void
setPositionAngleType(PositionAngleType positionAngleType)
Set position angle type.void
setResetAtEnd(boolean resetAtEnd)
Allow/disallow resetting the initial state at end of propagation.protected void
setUpEventDetector(ODEIntegrator integ, EventDetector detector)
Wrap an Orekit event detector and register it to the integrator.protected void
setUpStmAndJacobianGenerators()
Set up State Transition Matrix and Jacobian matrix handling.protected void
setUpUserEventDetectors()
Set up all user defined event detectors.-
Methods inherited from class org.orekit.propagation.AbstractPropagator
addAdditionalStateProvider, createHarvester, getAdditionalStateProviders, getAttitudeProvider, getFrame, getHarvester, getInitialState, getMultiplexer, getStartDate, initializeAdditionalStates, initializePropagation, resetInitialState, setStartDate, setupMatricesComputation, stateChanged, updateAdditionalStates, updateUnmanagedStates
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Methods inherited from class java.lang.Object
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
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Methods inherited from interface org.orekit.propagation.Propagator
clearStepHandlers, getPosition, getPVCoordinates, setStepHandler, setStepHandler
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Constructor Detail
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AbstractIntegratedPropagator
protected AbstractIntegratedPropagator(ODEIntegrator integrator, PropagationType propagationType)
Build a new instance.- Parameters:
integrator
- numerical integrator to use for propagation.propagationType
- type of orbit to output (mean or osculating).
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Method Detail
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setResetAtEnd
public void setResetAtEnd(boolean resetAtEnd)
Allow/disallow resetting the initial state at end of propagation.By default, at the end of the propagation, the propagator resets the initial state to the final state, thus allowing a new propagation to be started from there without recomputing the part already performed. Calling this method with
resetAtEnd
set to false changes prevents such reset.- Parameters:
resetAtEnd
- if true, at end of each propagation, theinitial state
will be reset to the final state of the propagation, otherwise the initial state will be preserved- Since:
- 9.0
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getResetAtEnd
public boolean getResetAtEnd()
Getter for the resetting flag regarding initial state.- Returns:
- resetting flag
- Since:
- 12.0
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initializeAttitudeProviderForDerivatives
protected AttitudeProvider initializeAttitudeProviderForDerivatives()
Method called when initializing the attitude provider used when evaluating derivatives.- Returns:
- attitude provider for derivatives
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initMapper
protected void initMapper()
Initialize the mapper.
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getIntegratorName
public String getIntegratorName()
Get the integrator's name.- Returns:
- name of underlying integrator
- Since:
- 12.0
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setAttitudeProvider
public void setAttitudeProvider(AttitudeProvider attitudeProvider)
Set attitude provider.- Specified by:
setAttitudeProvider
in interfacePropagator
- Overrides:
setAttitudeProvider
in classAbstractPropagator
- Parameters:
attitudeProvider
- attitude provider
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setOrbitType
protected void setOrbitType(OrbitType orbitType)
Set propagation orbit type.- Parameters:
orbitType
- orbit type to use for propagation, null for propagating usingAbsolutePVCoordinates
rather thanOrbit
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getOrbitType
protected OrbitType getOrbitType()
Get propagation parameter type.- Returns:
- orbit type used for propagation, null for
propagating using
AbsolutePVCoordinates
rather thanOrbit
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getPropagationType
public PropagationType getPropagationType()
Get the propagation type.- Returns:
- propagation type.
- Since:
- 11.1
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setPositionAngleType
protected void setPositionAngleType(PositionAngleType positionAngleType)
Set position angle type.The position parameter type is meaningful only if
propagation orbit type
support it. As an example, it is not meaningful for propagation inCartesian
parameters.- Parameters:
positionAngleType
- angle type to use for propagation
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getPositionAngleType
protected PositionAngleType getPositionAngleType()
Get propagation parameter type.- Returns:
- angle type to use for propagation
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setMu
public void setMu(double mu)
Set the central attraction coefficient μ.- Parameters:
mu
- central attraction coefficient (m³/s²)
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getMu
public double getMu()
Get the central attraction coefficient μ.- Returns:
- mu central attraction coefficient (m³/s²)
- See Also:
setMu(double)
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getCalls
public int getCalls()
Get the number of calls to the differential equations computation method.The number of calls is reset each time the
propagate(AbsoluteDate)
method is called.- Returns:
- number of calls to the differential equations computation method
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isAdditionalStateManaged
public boolean isAdditionalStateManaged(String name)
Check if an additional state is managed.Managed states are states for which the propagators know how to compute its evolution. They correspond to additional states for which a
provider
has been registered by calling theaddAdditionalStateProvider
method.Additional states that are present in the
initial state
but have no evolution method registered are not considered as managed states. These unmanaged additional states are not lost during propagation, though. Their value are piecewise constant between state resets that may change them if some event handlerresetState
method is called at an event occurrence and happens to change the unmanaged additional state.- Specified by:
isAdditionalStateManaged
in interfacePropagator
- Overrides:
isAdditionalStateManaged
in classAbstractPropagator
- Parameters:
name
- name of the additional state- Returns:
- true if the additional state is managed
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getManagedAdditionalStates
public String[] getManagedAdditionalStates()
Get all the names of all managed states.- Specified by:
getManagedAdditionalStates
in interfacePropagator
- Overrides:
getManagedAdditionalStates
in classAbstractPropagator
- Returns:
- names of all managed states
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addAdditionalDerivativesProvider
public void addAdditionalDerivativesProvider(AdditionalDerivativesProvider provider)
Add a provider for user-specified state derivatives to be integrated along with the orbit propagation.- Parameters:
provider
- provider for additional derivatives- Since:
- 11.1
- See Also:
AbstractPropagator.addAdditionalStateProvider(org.orekit.propagation.AdditionalStateProvider)
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getAdditionalDerivativesProviders
public List<AdditionalDerivativesProvider> getAdditionalDerivativesProviders()
Get an unmodifiable list of providers for additional derivatives.- Returns:
- providers for the additional derivatives
- Since:
- 11.1
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addEventDetector
public void addEventDetector(EventDetector detector)
Add an event detector.- Parameters:
detector
- event detector to add- See Also:
Propagator.clearEventsDetectors()
,Propagator.getEventsDetectors()
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getEventsDetectors
public Collection<EventDetector> getEventsDetectors()
Get all the events detectors that have been added.- Returns:
- an unmodifiable collection of the added detectors
- See Also:
Propagator.addEventDetector(EventDetector)
,Propagator.clearEventsDetectors()
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clearEventsDetectors
public void clearEventsDetectors()
Remove all events detectors.
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setUpUserEventDetectors
protected void setUpUserEventDetectors()
Set up all user defined event detectors.
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setUpEventDetector
protected void setUpEventDetector(ODEIntegrator integ, EventDetector detector)
Wrap an Orekit event detector and register it to the integrator.- Parameters:
integ
- integrator into which event detector should be registereddetector
- event detector to wrap
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getEphemerisGenerator
public EphemerisGenerator getEphemerisGenerator()
Set up an ephemeris generator that will monitor the propagation for building an ephemeris from it once completed.This generator can be used when the user needs fast random access to the orbit state at any time between the initial and target times. A typical example is the implementation of search and iterative algorithms that may navigate forward and backward inside the propagation range before finding their result even if the propagator used is integration-based and only goes from one initial time to one target time.
Beware that when used with integration-based propagators, the generator will store all intermediate results. It is therefore memory intensive for long integration-based ranges and high precision/short time steps. When used with analytical propagators, the generator only stores start/stop time and a reference to the analytical propagator itself to call it back as needed, so it is less memory intensive.
The returned ephemeris generator will be initially empty, it will be filled with propagation data when a subsequent call to either
propagate(target)
orpropagate(start, target)
is called. The proper way to use this method is therefore to do:EphemerisGenerator generator = propagator.getEphemerisGenerator(); propagator.propagate(target); BoundedPropagator ephemeris = generator.getGeneratedEphemeris();
- Returns:
- ephemeris generator
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createMapper
protected abstract StateMapper createMapper(AbsoluteDate referenceDate, double mu, OrbitType orbitType, PositionAngleType positionAngleType, AttitudeProvider attitudeProvider, Frame frame)
Create a mapper between raw double components and spacecraft state. /** Simple constructor.The position parameter type is meaningful only if
propagation orbit type
support it. As an example, it is not meaningful for propagation inCartesian
parameters.- Parameters:
referenceDate
- reference datemu
- central attraction coefficient (m³/s²)orbitType
- orbit type to use for mappingpositionAngleType
- angle type to use for propagationattitudeProvider
- attitude providerframe
- inertial frame- Returns:
- new mapper
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getMainStateEquations
protected abstract AbstractIntegratedPropagator.MainStateEquations getMainStateEquations(ODEIntegrator integ)
Get the differential equations to integrate (for main state only).- Parameters:
integ
- numerical integrator to use for propagation.- Returns:
- differential equations for main state
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propagate
public SpacecraftState propagate(AbsoluteDate target)
Propagate towards a target date.Simple propagators use only the target date as the specification for computing the propagated state. More feature rich propagators can consider other information and provide different operating modes or G-stop facilities to stop at pinpointed events occurrences. In these cases, the target date is only a hint, not a mandatory objective.
- Specified by:
propagate
in interfacePropagator
- Overrides:
propagate
in classAbstractPropagator
- Parameters:
target
- target date towards which orbit state should be propagated- Returns:
- propagated state
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propagate
public SpacecraftState propagate(AbsoluteDate tStart, AbsoluteDate tEnd)
Propagate from a start date towards a target date.Those propagators use a start date and a target date to compute the propagated state. For propagators using event detection mechanism, if the provided start date is different from the initial state date, a first, simple propagation is performed, without processing any event computation. Then complete propagation is performed from start date to target date.
- Parameters:
tStart
- start date from which orbit state should be propagatedtEnd
- target date to which orbit state should be propagated- Returns:
- propagated state
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resetInitialState
public void resetInitialState(SpacecraftState state, PropagationType stateType)
Reset initial state with a given propagation type.By default this method returns the same as
AbstractPropagator.resetInitialState(SpacecraftState)
Its purpose is mostly to be derived in DSSTPropagator
- Parameters:
state
- new initial state to considerstateType
- type of the new state (mean or osculating)- Since:
- 12.1.3
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setUpStmAndJacobianGenerators
protected void setUpStmAndJacobianGenerators()
Set up State Transition Matrix and Jacobian matrix handling.- Since:
- 11.1
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getInitialIntegrationState
protected SpacecraftState getInitialIntegrationState()
Get the initial state for integration.- Returns:
- initial state for integration
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beforeIntegration
protected void beforeIntegration(SpacecraftState initialState, AbsoluteDate tEnd)
Method called just before integration.The default implementation does nothing, it may be specialized in subclasses.
- Parameters:
initialState
- initial statetEnd
- target date at which state should be propagated
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afterIntegration
protected void afterIntegration()
Method called just after integration.The default implementation does nothing, it may be specialized in subclasses.
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getBasicDimension
public int getBasicDimension()
Get state vector dimension without additional parameters.- Returns:
- state vector dimension without additional parameters.
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getIntegrator
protected ODEIntegrator getIntegrator()
Get the integrator used by the propagator.- Returns:
- the integrator.
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