DSSTTesseralContext (OREKIT 13.0-SNAPSHOT API)

java.lang.Object
- org.orekit.propagation.semianalytical.dsst.forces.ForceModelContext
- - org.orekit.propagation.semianalytical.dsst.forces.DSSTGravityContext
  - - org.orekit.propagation.semianalytical.dsst.forces.DSSTTesseralContext

```
public class DSSTTesseralContext
extends DSSTGravityContext
```
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

All Methods Instance Methods Concrete Methods Deprecated Methods
Modifier and Type	Method	Description
`double`	`getE2()`	Get ecc².
`double`	`getMoa()`	Deprecated. since 12.2 Use getMuoa() instead
`double`	`getOrbitPeriod()`	Get the Keplerian period.
`double`	`getRatio()`	Get the ratio of satellite period to central body rotation period.
`double`	`getTheta()`	Get Central body rotation angle θ.

Methods inherited from class org.orekit.propagation.semianalytical.dsst.forces.DSSTGravityContext
getA, getAlpha, getAx2oA, getBeta, getBoA, getBoABpo, getBodyFixedToInertialTransform, getChi, getChi2, getCo2AB, getGamma, getMeanMotion, getMuoa, getOoAB, getRoa

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
  - getMoa
```
@Deprecated
public double getMoa()
```
    Deprecated.
    since 12.2 Use getMuoa() instead
    
    Get μ / a .
    
    Returns:
    
    moa
  - 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
  - getRatio
```
public double getRatio()
```
    Get the ratio of satellite period to central body rotation period.
    
    Returns:
    
    ratio