Package org.orekit.propagation.semianalytical.dsst.forces

Class DSSTTesseralContext

java.lang.Object

org.orekit.propagation.semianalytical.dsst.forces.ForceModelContext

org.orekit.propagation.semianalytical.dsst.forces.DSSTTesseralContext

public class DSSTTesseralContext
extends ForceModelContext

This class is a container for the common parameters used in DSSTTesseral.

It performs parameters initialization at each integration step for the Tesseral contribution to the central body gravitational perturbation.

Since:

10.0

Author:

Bryan Cazabonne

Method Summary

Modifier and Type	Method	Description
double	getAx2oA()	Get ax2oA = 2 * a / A .
double	getBoA()	Get B / A.
double	getBoABpo()	Get BoABpo = B / A(1 + B).
double	getChi()	Get Χ = 1 / sqrt(1 - e²) = 1 / B.
double	getChi2()	Get Χ².
double	getCo2AB()	Get Co2AB = C / 2AB.
double	getE2()	Get ecc².
double	getMeanMotion()	Get the Keplerian mean motion.
double	getMoa()	Get μ / a .
double	getOoAB()	Get ooAB = 1 / (A * B).
double	getOrbitPeriod()	Get the Keplerian period.
double	getRatio()	Get the ratio of satellite period to central body rotation period.
double	getRoa()	Get roa = R / a.
double	getTheta()	Get Central body rotation angle θ.

Methods inherited from class org.orekit.propagation.semianalytical.dsst.forces.ForceModelContext

getAuxiliaryElements

Methods inherited from class java.lang.Object

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

Method Detail

getE2

public double getE2()

Get ecc².

Returns:

e2

getTheta

public double getTheta()

Get Central body rotation angle θ.

Returns:

theta

getAx2oA

public double getAx2oA()

Get ax2oA = 2 * a / A .

Returns:

ax2oA

getChi

public double getChi()

Get Χ = 1 / sqrt(1 - e²) = 1 / B.

Returns:

chi

getChi2

public double getChi2()

Get Χ².

Returns:

chi2

getBoA

public double getBoA()

Get B / A.

Returns:

BoA

getOoAB

public double getOoAB()

Get ooAB = 1 / (A * B).

Returns:

ooAB

getCo2AB

public double getCo2AB()

Get Co2AB = C / 2AB.

Returns:

Co2AB

getBoABpo

public double getBoABpo()

Get BoABpo = B / A(1 + B).

Returns:

BoABpo

getMoa

public double getMoa()

Get μ / a .

Returns:

moa

getRoa

public double getRoa()

Get roa = R / a.

Returns:

roa

getOrbitPeriod

public double getOrbitPeriod()

Get the Keplerian period.

The Keplerian period is computed directly from semi major axis and central acceleration constant.

Returns:

Keplerian period in seconds, or positive infinity for hyperbolic orbits

getMeanMotion

public double getMeanMotion()

Get the Keplerian mean motion.

The Keplerian mean motion is computed directly from semi major axis and central acceleration constant.

Returns:

Keplerian mean motion in radians per second

getRatio

public double getRatio()

Get the ratio of satellite period to central body rotation period.

Returns:

ratio