Class KeplerianPropagator
- java.lang.Object
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- org.orekit.propagation.AbstractPropagator
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- org.orekit.propagation.analytical.AbstractAnalyticalPropagator
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- org.orekit.propagation.analytical.KeplerianPropagator
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- All Implemented Interfaces:
Propagator
,PVCoordinatesProvider
public class KeplerianPropagator extends AbstractAnalyticalPropagator
Simple Keplerian orbit propagator.- Author:
- Guylaine Prat
- See Also:
Orbit
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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 Constructor Description KeplerianPropagator(Orbit initialOrbit)
Build a propagator from orbit only.KeplerianPropagator(Orbit initialOrbit, double mu)
Build a propagator from orbit and central attraction coefficient μ.KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv)
Build a propagator from orbit and attitude provider.KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mu)
Build a propagator from orbit, attitude provider and central attraction coefficient μ.KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mu, double mass)
Build propagator from orbit, attitude provider, central attraction coefficient μ and mass.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description protected AbstractMatricesHarvester
createHarvester(String stmName, RealMatrix initialStm, DoubleArrayDictionary initialJacobianColumns)
Create the harvester suitable for propagator.protected double
getMass(AbsoluteDate date)
Get the mass.protected Orbit
propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.void
resetInitialState(SpacecraftState state)
Reset the propagator initial state.protected void
resetIntermediateState(SpacecraftState state, boolean forward)
Reset an intermediate state.-
Methods inherited from class org.orekit.propagation.analytical.AbstractAnalyticalPropagator
acceptStep, addEventDetector, basicPropagate, clearEventsDetectors, getEphemerisGenerator, getEventsDetectors, getJacobiansColumnsNames, getPvProvider, propagate
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Methods inherited from class org.orekit.propagation.AbstractPropagator
addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getFrame, getHarvester, getInitialState, getManagedAdditionalStates, getMultiplexer, getStartDate, initializeAdditionalStates, initializePropagation, isAdditionalStateManaged, propagate, setAttitudeProvider, 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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KeplerianPropagator
public KeplerianPropagator(Orbit initialOrbit)
Build a propagator from orbit only.The central attraction coefficient μ is set to the same value used for the initial orbit definition. Mass and attitude provider are set to unspecified non-null arbitrary values.
- Parameters:
initialOrbit
- initial orbit- See Also:
KeplerianPropagator(Orbit, AttitudeProvider)
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KeplerianPropagator
public KeplerianPropagator(Orbit initialOrbit, double mu)
Build a propagator from orbit and central attraction coefficient μ.Mass and attitude provider are set to unspecified non-null arbitrary values.
- Parameters:
initialOrbit
- initial orbitmu
- central attraction coefficient (m³/s²)- See Also:
KeplerianPropagator(Orbit, AttitudeProvider, double)
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KeplerianPropagator
public KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv)
Build a propagator from orbit and attitude provider.The central attraction coefficient μ is set to the same value used for the initial orbit definition. Mass is set to an unspecified non-null arbitrary value.
- Parameters:
initialOrbit
- initial orbitattitudeProv
- attitude provider
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KeplerianPropagator
public KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mu)
Build a propagator from orbit, attitude provider and central attraction coefficient μ.Mass is set to an unspecified non-null arbitrary value.
- Parameters:
initialOrbit
- initial orbitattitudeProv
- attitude providermu
- central attraction coefficient (m³/s²)
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KeplerianPropagator
public KeplerianPropagator(Orbit initialOrbit, AttitudeProvider attitudeProv, double mu, double mass)
Build propagator from orbit, attitude provider, central attraction coefficient μ and mass.- Parameters:
initialOrbit
- initial orbitattitudeProv
- attitude providermu
- central attraction coefficient (m³/s²)mass
- spacecraft mass (kg)
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Method Detail
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resetInitialState
public void resetInitialState(SpacecraftState state)
Reset the propagator initial state.- Specified by:
resetInitialState
in interfacePropagator
- Overrides:
resetInitialState
in classAbstractPropagator
- Parameters:
state
- new initial state to consider
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resetIntermediateState
protected void resetIntermediateState(SpacecraftState state, boolean forward)
Reset an intermediate state.- Specified by:
resetIntermediateState
in classAbstractAnalyticalPropagator
- Parameters:
state
- new intermediate state to considerforward
- if true, the intermediate state is valid for propagations after itself
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propagateOrbit
protected Orbit propagateOrbit(AbsoluteDate date)
Extrapolate an orbit up to a specific target date.- Specified by:
propagateOrbit
in classAbstractAnalyticalPropagator
- Parameters:
date
- target date for the orbit- Returns:
- extrapolated parameters
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getMass
protected double getMass(AbsoluteDate date)
Get the mass.- Specified by:
getMass
in classAbstractAnalyticalPropagator
- Parameters:
date
- target date for the orbit- Returns:
- mass mass
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createHarvester
protected AbstractMatricesHarvester createHarvester(String stmName, RealMatrix initialStm, DoubleArrayDictionary initialJacobianColumns)
Create the harvester suitable for propagator.- Overrides:
createHarvester
in classAbstractPropagator
- Parameters:
stmName
- State Transition Matrix state nameinitialStm
- initial State Transition Matrix ∂Y/∂Y₀, if null (which is the most frequent case), assumed to be 6x6 identityinitialJacobianColumns
- initial columns of the Jacobians matrix with respect to parameters, if null or if some selected parameters are missing from the dictionary, the corresponding initial column is assumed to be 0- Returns:
- harvester to retrieve computed matrices during and after propagation
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