Package org.orekit.propagation.numerical.cr3bp

Class STMEquations

java.lang.Object

org.orekit.propagation.numerical.cr3bp.STMEquations

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"

Constructor Summary

Constructors

Constructor	Description
STMEquations(CR3BPSystem syst)	Simple constructor.

Method Summary

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

Methods inherited from interface org.orekit.propagation.integration.AdditionalDerivativesProvider

init, yields

Constructor Detail

STMEquations

public STMEquations(CR3BPSystem syst)

Simple constructor.

Parameters:

syst - CR3BP System considered

Method Detail

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

combinedDerivatives

public CombinedDerivatives combinedDerivatives(SpacecraftState s)

Compute the derivatives related to the additional state (and optionally main state increments).

Specified by:

combinedDerivatives in interface AdditionalDerivativesProvider

Parameters:

s - current state information: date, kinematics, attitude, and additional states this equations depend on (according to the yields method)

Returns:

computed combined derivatives, which may include some incremental coupling effect to add to main state derivatives

getName

public String getName()

Get the name of the additional derivatives (which will become state once integrated).

Specified by:

getName in interface AdditionalDerivativesProvider

Returns:

name of the additional state (names containing "orekit" with any case are reserved for the library internal use)

getDimension

public int getDimension()

Get the dimension of the generated derivative.

Specified by:

getDimension in interface AdditionalDerivativesProvider

Returns:

dimension of the generated

getStateTransitionMatrix

public RealMatrix getStateTransitionMatrix(SpacecraftState s)

Method returning the State Transition Matrix.

Parameters:

s - SpacecraftState of the system

Returns:

phiM State Transition Matrix