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

Class DSSTThirdBodyDynamicContext

java.lang.Object

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

org.orekit.propagation.semianalytical.dsst.forces.DSSTThirdBodyDynamicContext

public class DSSTThirdBodyDynamicContext
extends ForceModelContext

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

It performs parameters initialization at each integration step for the third body attraction perturbation. These parameters change for each integration step.

Since:

11.3.3

Author:

Bryan Cazabonne

Constructor Summary

Constructors

Constructor	Description
DSSTThirdBodyDynamicContext(AuxiliaryElements aux, CelestialBody body, double[] parameters)	Constructor.

Method Summary

Modifier and Type	Method	Description
double	getA()	Get A = sqrt(μ * a).
double	getAlpha()	Get direction cosine α for central body.
double	getb()	Get b = 1 / (1 + sqrt(1 - e²)) = 1 / (1 + B).
double	getBB()	Get B².
double	getBBB()	Get B³.
double	getBeta()	Get direction cosine β for central body.
double	getBoA()	Get B / A.
double	getBoABpo()	Get BoABpo = B / A(1 + B).
double	getGamma()	Get direction cosine γ for central body.
double	getHXXX()	Get hXXX = h * Χ³.
double	getKXXX()	Get kXXX = h * Χ³.
double	getM2aoA()	Get m2aoA = -2 * a / A.
double	getMCo2AB()	Get mCo2AB = -C / 2AB.
double	getMeanMotion()	Get the Keplerian mean motion.
double	getMuoR3()	Get muoR3 = mu3 / R3.
double	getOoAB()	Get ooAB = 1 / (A * B).
double	getR3()	Get the distance from center of mass of the central body to the 3rd body.
double	getX()	Get Χ = 1 / sqrt(1 - e²) = 1 / B.
double	getXX()	Get Χ².

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

Constructor Details

DSSTThirdBodyDynamicContext

public DSSTThirdBodyDynamicContext(AuxiliaryElements aux,
 CelestialBody body,
 double[] parameters)

Constructor.

Parameters:

aux - auxiliary elements related to the current orbit

body - body the 3rd body to consider

parameters - values of the force model parameters

Method Details

getA

public double getA()

Get A = sqrt(μ * a).

Returns:

A

getR3

public double getR3()

Get the distance from center of mass of the central body to the 3rd body.

Returns:

the distance from center of mass of the central body to the 3rd body

getAlpha

public double getAlpha()

Get direction cosine α for central body.

Returns:

α

getBeta

public double getBeta()

Get direction cosine β for central body.

Returns:

β

getGamma

public double getGamma()

Get direction cosine γ for central body.

Returns:

γ

getBB

public double getBB()

Get B².

Returns:

B²

getBBB

public double getBBB()

Get B³.

Returns:

B³

getb

public double getb()

Get b = 1 / (1 + sqrt(1 - e²)) = 1 / (1 + B).

Returns:

b

getX

public double getX()

Get Χ = 1 / sqrt(1 - e²) = 1 / B.

Returns:

Χ

getXX

public double getXX()

Get Χ².

Returns:

Χ²

getM2aoA

public double getM2aoA()

Get m2aoA = -2 * a / A.

Returns:

m2aoA

getBoA

public double getBoA()

Get B / A.

Returns:

BoA

getOoAB

public double getOoAB()

Get ooAB = 1 / (A * B).

Returns:

ooAB

getMCo2AB

public double getMCo2AB()

Get mCo2AB = -C / 2AB.

Returns:

mCo2AB

getBoABpo

public double getBoABpo()

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

Returns:

BoABpo

getMuoR3

public double getMuoR3()

Get muoR3 = mu3 / R3.

Returns:

muoR3

getHXXX

public double getHXXX()

Get hXXX = h * Χ³.

Returns:

hXXX

getKXXX

public double getKXXX()

Get kXXX = h * Χ³.

Returns:

kXXX

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