Package org.orekit.propagation.relative.yamanakaankersen

Class FieldYamanakaAnkersenEquations<T extends CalculusFieldElement<T>>

java.lang.Object

org.orekit.propagation.relative.yamanakaankersen.FieldYamanakaAnkersenEquations<T>

Type Parameters:

T - Any scalar field.

public class FieldYamanakaAnkersenEquations<T extends CalculusFieldElement<T>>
extends Object

This class implements the state transition matrices of the Yamanaka-Ankersen equations of relative motion between two spacecrafts. Matrices are state matrices in the derived LVLH CCSDS frame as described in the Reference paper. Transformation from transformed frame to target LVLH CCSDS Local Orbital Frame is performed in the YamanakaAnkersenProvider.

Source : Koji Yamanaka, Finn Ankersen, New State Transition Matrix for Relative Motion on an Arbitrary Elliptical Orbit, Journal of Guidance, Control, and Dynamics, Vol. 25, No.1, January-February 2002

Since:

14.0

Author:

Romain Cuvillon

Constructor Summary

Constructors

Constructor	Description
FieldYamanakaAnkersenEquations()	Constructor.

Method Summary

Modifier and Type	Method	Description
FieldYamanakaAnkersenMatrices<T>	computeMatrices(T timeSinceEpoch, T targetA, T targetE, T targetInitialTheta, T targetTheta, T mu)	Computes the state transition matrices provided by the Yamanaka-Ankersen equations at time t from an initial state.

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Constructor Details

FieldYamanakaAnkersenEquations

public FieldYamanakaAnkersenEquations()

Constructor.

Method Details

computeMatrices

public FieldYamanakaAnkersenMatrices<T> computeMatrices(T timeSinceEpoch,
 T targetA,
 T targetE,
 T targetInitialTheta,
 T targetTheta,
 T mu)

Computes the state transition matrices provided by the Yamanaka-Ankersen equations at time t from an initial state.

Parameters:

timeSinceEpoch - duration in seconds since epoch

targetA - semi-major axis of the target orbit

targetE - eccentricity of the target orbit

targetInitialTheta - true-anomaly of the target at epoch

targetTheta - current true-anomaly of the target

mu - gravitational constant

Returns:

state transition matrices at a given time t from an initial state