fr.cnes.sirius.patrius.forces.gravity

Interface GravityModel

All Superinterfaces:

Serializable

All Known Implementing Classes:

AbstractGravityModel, AbstractHarmonicGravityModel, BalminoGravityModel, CunninghamGravityModel, DrozinerGravityModel, GridGravityModel, NewtonianGravityModel, VariablePotentialGravityModel

public interface GravityModel
extends Serializable

This interface represents a gravitational attraction model.

Since:

4.11

Author:

Alex Nardi

Method Summary

Modifier and Type	Method and Description
Vector3D	computeAcceleration(Vector3D positionInBodyFrame, AbsoluteDate date) Compute the acceleration due to the gravitational attraction.
double[][]	computeDAccDPos(Vector3D positionInBodyFrame, AbsoluteDate date) Compute acceleration derivatives with respect to the position of the spacecraft.
Frame	getBodyFrame() Get the central body frame.
double	getMu() Get the central attraction coefficient.
void	setMu(double muIn) Set the central attraction coefficient.

Method Detail

getMu

double getMu()

Get the central attraction coefficient.

Returns:

central attraction coefficient (m³/s²)

setMu

void setMu(double muIn)

Set the central attraction coefficient.

Parameters:

muIn - the central attraction coefficient.

getBodyFrame

Frame getBodyFrame()

Get the central body frame.

Returns:

the bodyFrame

computeAcceleration

Vector3D computeAcceleration(Vector3D positionInBodyFrame,
                             AbsoluteDate date)
                      throws PatriusException

Compute the acceleration due to the gravitational attraction.

Parameters:

positionInBodyFrame - the position expressed in the body frame

date - The date for which the computation needs to be performed

Returns:

acceleration in the body frame

Throws:

PatriusException - if some specific error occurs

computeDAccDPos

double[][] computeDAccDPos(Vector3D positionInBodyFrame,
                           AbsoluteDate date)
                    throws PatriusException

Compute acceleration derivatives with respect to the position of the spacecraft.

Parameters:

positionInBodyFrame - the position expressed in the body frame

date - The date for which the computation needs to be performed

Returns:

acceleration derivatives with respect to the position of the spacecraft in the body frame

Throws:

PatriusException - if derivatives cannot be computed