Class DSSTTesseralContext
- java.lang.Object
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- org.orekit.propagation.semianalytical.dsst.forces.ForceModelContext
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- org.orekit.propagation.semianalytical.dsst.forces.DSSTTesseralContext
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public class DSSTTesseralContext extends ForceModelContext
This class is a container for the common 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 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
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Method Detail
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getE2
public double getE2()
Get ecc².- Returns:
- e2
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getTheta
public double getTheta()
Get Central body rotation angle θ.- Returns:
- theta
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getAx2oA
public double getAx2oA()
Get ax2oA = 2 * a / A .- Returns:
- ax2oA
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getChi
public double getChi()
Get Χ = 1 / sqrt(1 - e²) = 1 / B.- Returns:
- chi
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getChi2
public double getChi2()
Get Χ².- Returns:
- chi2
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getBoA
public double getBoA()
Get B / A.- Returns:
- BoA
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getOoAB
public double getOoAB()
Get ooAB = 1 / (A * B).- Returns:
- ooAB
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getCo2AB
public double getCo2AB()
Get Co2AB = C / 2AB.- Returns:
- Co2AB
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getBoABpo
public double getBoABpo()
Get BoABpo = B / A(1 + B).- Returns:
- BoABpo
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getMoa
public double getMoa()
Get μ / a .- Returns:
- moa
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getRoa
public double getRoa()
Get roa = R / a.- Returns:
- roa
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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
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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
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getRatio
public double getRatio()
Get the ratio of satellite period to central body rotation period.- Returns:
- ratio
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