Class STMEquations
- java.lang.Object
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- org.orekit.propagation.numerical.cr3bp.STMEquations
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- All Implemented Interfaces:
AdditionalDerivativesProvider
public class STMEquations extends Object implements AdditionalDerivativesProvider
Class calculating the state transition matrix coefficient for CR3BP Computation.- Since:
- 10.2
- Author:
- Vincent Mouraux
- See Also:
- "Dynamical systems, the three-body problem, and space mission design, Koon, Lo, Marsden, Ross"
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Constructor Summary
Constructors Constructor Description STMEquations(CR3BPSystem syst)
Simple constructor.
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method Description CombinedDerivatives
combinedDerivatives(SpacecraftState s)
Compute the derivatives related to the additional state (and optionally main state increments).int
getDimension()
Get the dimension of the generated derivative.String
getName()
Get the name of the additional derivatives (which will become state once integrated).RealMatrix
getStateTransitionMatrix(SpacecraftState s)
Method returning the State Transition Matrix.SpacecraftState
setInitialPhi(SpacecraftState s)
Method adding the standard initial values of the additional state to the initial spacecraft state.-
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.integration.AdditionalDerivativesProvider
init, yields
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Constructor Detail
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STMEquations
public STMEquations(CR3BPSystem syst)
Simple constructor.- Parameters:
syst
- CR3BP System considered
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Method Detail
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setInitialPhi
public SpacecraftState setInitialPhi(SpacecraftState s)
Method adding the standard initial values of the additional state to the initial spacecraft state.- Parameters:
s
- Initial state of the system- Returns:
- s Initial augmented (with the additional equations) state
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combinedDerivatives
public CombinedDerivatives combinedDerivatives(SpacecraftState s)
Compute the derivatives related to the additional state (and optionally main state increments).- Specified by:
combinedDerivatives
in interfaceAdditionalDerivativesProvider
- Parameters:
s
- current state information: date, kinematics, attitude, and additional states this equations depend on (according to theyields
method)- Returns:
- computed combined derivatives, which may include some incremental coupling effect to add to main state derivatives
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getName
public String getName()
Get the name of the additional derivatives (which will become state once integrated).- Specified by:
getName
in interfaceAdditionalDerivativesProvider
- Returns:
- name of the additional state (names containing "orekit" with any case are reserved for the library internal use)
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getDimension
public int getDimension()
Get the dimension of the generated derivative.- Specified by:
getDimension
in interfaceAdditionalDerivativesProvider
- Returns:
- dimension of the generated
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getStateTransitionMatrix
public RealMatrix getStateTransitionMatrix(SpacecraftState s)
Method returning the State Transition Matrix.- Parameters:
s
- SpacecraftState of the system- Returns:
- phiM State Transition Matrix
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