Class AbstractAnalyticalPropagator
- java.lang.Object
-
- org.orekit.propagation.AbstractPropagator
-
- org.orekit.propagation.analytical.AbstractAnalyticalPropagator
-
- All Implemented Interfaces:
Propagator
,PVCoordinatesProvider
- Direct Known Subclasses:
AdapterPropagator
,AggregateBoundedPropagator
,BrouwerLyddanePropagator
,EcksteinHechlerPropagator
,Ephemeris
,EphemerisSegmentPropagator
,GLONASSAnalyticalPropagator
,GNSSPropagator
,IntegratedEphemeris
,IntelsatElevenElementsPropagator
,KeplerianPropagator
,SBASPropagator
,TLEPropagator
public abstract class AbstractAnalyticalPropagator extends AbstractPropagator
Common handling ofPropagator
methods for analytical propagators.This abstract class allows to provide easily the full set of
Propagator
methods, including all propagation modes support and discrete events support for any simple propagation method. Only two methods must be implemented by derived classes:propagateOrbit(AbsoluteDate)
andgetMass(AbsoluteDate)
. The first method should perform straightforward propagation starting from some internally stored initial state up to the specified target date.- Author:
- Luc Maisonobe
-
-
Field Summary
-
Fields inherited from interface org.orekit.propagation.Propagator
DEFAULT_MASS
-
-
Constructor Summary
Constructors Modifier Constructor Description protected
AbstractAnalyticalPropagator(AttitudeProvider attitudeProvider)
Build a new instance.
-
Method Summary
All Methods Instance Methods Abstract Methods Concrete Methods Modifier and Type Method Description protected SpacecraftState
acceptStep(OrekitStepInterpolator interpolator, AbsoluteDate target)
Accept a step, triggering events and step handlers.<T extends EventDetector>
voidaddEventDetector(T detector)
Add an event detector.protected SpacecraftState
basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features.void
clearEventsDetectors()
Remove all events detectors.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 List<String>
getJacobiansColumnsNames()
Get the names of the parameters in the matrix returned byMatricesHarvester.getParametersJacobian(org.orekit.propagation.SpacecraftState)
.protected abstract double
getMass(AbsoluteDate date)
Get the mass.PVCoordinatesProvider
getPvProvider()
Get PV coordinates provider.SpacecraftState
propagate(AbsoluteDate start, AbsoluteDate target)
Propagate from a start date towards a target date.protected abstract Orbit
propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.protected abstract void
resetIntermediateState(SpacecraftState state, boolean forward)
Reset an intermediate state.-
Methods inherited from class org.orekit.propagation.AbstractPropagator
addAdditionalStateProvider, createHarvester, getAdditionalStateProviders, getAttitudeProvider, getFrame, getHarvester, getInitialState, getManagedAdditionalStates, getMultiplexer, getStartDate, initializeAdditionalStates, initializePropagation, isAdditionalStateManaged, propagate, resetInitialState, setAttitudeProvider, setStartDate, setupMatricesComputation, stateChanged, updateAdditionalStates, updateUnmanagedStates
-
Methods inherited from class java.lang.Object
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
-
Methods inherited from interface org.orekit.propagation.Propagator
clearStepHandlers, getPosition, getPVCoordinates, setStepHandler, setStepHandler
-
-
-
-
Constructor Detail
-
AbstractAnalyticalPropagator
protected AbstractAnalyticalPropagator(AttitudeProvider attitudeProvider)
Build a new instance.- Parameters:
attitudeProvider
- provider for attitude computation
-
-
Method Detail
-
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
-
addEventDetector
public <T extends EventDetector> void addEventDetector(T detector)
Add an event detector.- Type Parameters:
T
- class type for the generic version- Parameters:
detector
- event detector to add- See Also:
Propagator.clearEventsDetectors()
,Propagator.getEventsDetectors()
-
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()
-
clearEventsDetectors
public void clearEventsDetectors()
Remove all events detectors.
-
propagate
public SpacecraftState propagate(AbsoluteDate start, AbsoluteDate target)
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:
start
- start date from which orbit state should be propagatedtarget
- target date to which orbit state should be propagated- Returns:
- propagated state
-
acceptStep
protected SpacecraftState acceptStep(OrekitStepInterpolator interpolator, AbsoluteDate target) throws MathRuntimeException
Accept a step, triggering events and step handlers.- Parameters:
interpolator
- interpolator for the current steptarget
- final propagation time- Returns:
- state at the end of the step
- Throws:
MathRuntimeException
- if an event cannot be located
-
getMass
protected abstract double getMass(AbsoluteDate date)
Get the mass.- Parameters:
date
- target date for the orbit- Returns:
- mass mass
-
getPvProvider
public PVCoordinatesProvider getPvProvider()
Get PV coordinates provider.- Returns:
- PV coordinates provider
-
resetIntermediateState
protected abstract void resetIntermediateState(SpacecraftState state, boolean forward)
Reset an intermediate state.- Parameters:
state
- new intermediate state to considerforward
- if true, the intermediate state is valid for propagations after itself
-
propagateOrbit
protected abstract Orbit propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.- Parameters:
date
- target date for the orbit- Returns:
- extrapolated parameters
-
basicPropagate
protected SpacecraftState basicPropagate(AbsoluteDate date)
Propagate an orbit without any fancy features.This method is similar in spirit to the
propagate(org.orekit.time.AbsoluteDate, org.orekit.time.AbsoluteDate)
method, except that it does not call any handler during propagation, nor any discrete events, not additional states. It always stop exactly at the specified date.- Parameters:
date
- target date for propagation- Returns:
- state at specified date
-
getJacobiansColumnsNames
protected List<String> getJacobiansColumnsNames()
Get the names of the parameters in the matrix returned byMatricesHarvester.getParametersJacobian(org.orekit.propagation.SpacecraftState)
.- Returns:
- names of the parameters (i.e. columns) of the Jacobian matrix
- Since:
- 11.1
-
-