org.orekit.propagation.semianalytical.dsst.forces

Class FieldDSSTTesseralContext<T extends org.hipparchus.CalculusFieldElement<T>>

java.lang.Object

org.orekit.propagation.semianalytical.dsst.forces.FieldForceModelContext<T>

org.orekit.propagation.semianalytical.dsst.forces.FieldDSSTTesseralContext<T>

Type Parameters:

T - type of the field elements

public class FieldDSSTTesseralContext<T extends org.hipparchus.CalculusFieldElement<T>>
extends FieldForceModelContext<T>

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

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

getFieldAuxiliaryElements

Methods inherited from class java.lang.Object

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

Method Detail

getE2

public T getE2()

Get ecc².

Returns:

e2

getTheta

public T getTheta()

Get Central body rotation angle θ.

Returns:

theta

getAx2oA

public T getAx2oA()

Get ax2oA = 2 * a / A .

Returns:

ax2oA

getChi

public T getChi()

Get Χ = 1 / sqrt(1 - e²) = 1 / B.

Returns:

chi

getChi2

public T getChi2()

Get Χ².

Returns:

chi2

getBoA

public T getBoA()

Get B / A.

Returns:

BoA

getOoAB

public T getOoAB()

Get ooAB = 1 / (A * B).

Returns:

ooAB

getCo2AB

public T getCo2AB()

Get Co2AB = C / 2AB.

Returns:

Co2AB

getBoABpo

public T getBoABpo()

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

Returns:

BoABpo

getMoa

public T getMoa()

Get μ / a .

Returns:

moa

getRoa

public T getRoa()

Get roa = R / a.

Returns:

roa

getOrbitPeriod

public T 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 T 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 T getRatio()

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

Returns:

ratio