Class FieldDSSTTesseralContext<T extends CalculusFieldElement<T>>
- java.lang.Object
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- org.orekit.propagation.semianalytical.dsst.forces.FieldForceModelContext<T>
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- org.orekit.propagation.semianalytical.dsst.forces.FieldDSSTTesseralContext<T>
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- Type Parameters:
T
- type of the field elements
public class FieldDSSTTesseralContext<T extends CalculusFieldElement<T>> extends FieldForceModelContext<T>
This class is a container for the common "field" parameters used inDSSTTesseral
.It performs parameters initialization at each integration step for the Tesseral contribution to the central body gravitational perturbation.
- Since:
- 10.0
- Author:
- Bryan Cazabonne
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Method Summary
All Methods Instance Methods Concrete Methods Modifier and Type Method 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
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Method Detail
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getE2
public T getE2()
Get ecc².- Returns:
- e2
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getTheta
public T getTheta()
Get Central body rotation angle θ.- Returns:
- theta
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getAx2oA
public T getAx2oA()
Get ax2oA = 2 * a / A .- Returns:
- ax2oA
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getChi
public T getChi()
Get Χ = 1 / sqrt(1 - e²) = 1 / B.- Returns:
- chi
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getChi2
public T getChi2()
Get Χ².- Returns:
- chi2
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getBoA
public T getBoA()
Get B / A.- Returns:
- BoA
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getOoAB
public T getOoAB()
Get ooAB = 1 / (A * B).- Returns:
- ooAB
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getCo2AB
public T getCo2AB()
Get Co2AB = C / 2AB.- Returns:
- Co2AB
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getBoABpo
public T getBoABpo()
Get BoABpo = B / A(1 + B).- Returns:
- BoABpo
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getMoa
public T getMoa()
Get μ / a .- Returns:
- moa
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getRoa
public T getRoa()
Get roa = R / a.- Returns:
- roa
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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
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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
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getRatio
public T getRatio()
Get the ratio of satellite period to central body rotation period.- Returns:
- ratio
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