org.orekit.forces.maneuvers
Class ConstantThrustManeuver

java.lang.Object
  org.orekit.forces.maneuvers.ConstantThrustManeuver

All Implemented Interfaces:

java.io.Serializable, ForceModel

public class ConstantThrustManeuver
extends java.lang.Object
implements ForceModel

This class implements a simple maneuver with constant thrust.

The maneuver is defined by a direction in satelliteframe. The current attitude of the spacecraft, defined by the current spacecraft state, will be used to compute the thrust direction in inertial frame. A typical case for tangential maneuvers is to use a LOF aligned attitude law for state propagation and a velocity increment along the +X satellite axis.

Version:

$Revision:1665 $ $Date:2008-06-11 12:12:59 +0200 (mer., 11 juin 2008) $

Author:

Fabien Maussion, Véronique Pommier-Maurussane, Luc Maisonobe

See Also:

Serialized Form

Field Summary

static double

G0 Reference gravity acceleration constant (m/s2).

Constructor Summary

ConstantThrustManeuver(AbsoluteDate date, double duration, double thrust, double isp, org.apache.commons.math.geometry.Vector3D direction)
Simple constructor for a constant direction and constant thrust.

Method Summary

void	addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the force model to the perturbing acceleration.
EventDetector[]	getEventsDetectors() Get the discrete events related to the model.

Methods inherited from class java.lang.Object

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

Field Detail

G0

public static final double G0

Reference gravity acceleration constant (m/s²).

See Also:

Constant Field Values

Constructor Detail

ConstantThrustManeuver

public ConstantThrustManeuver(AbsoluteDate date,
                              double duration,
                              double thrust,
                              double isp,
                              org.apache.commons.math.geometry.Vector3D direction)

Simple constructor for a constant direction and constant thrust.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

thrust - the thrust force (N)

isp - engine specific impulse (s)

direction - the acceleration direction in satellite frame.

Method Detail

addContribution

public void addContribution(SpacecraftState s,
                            TimeDerivativesEquations adder)
                     throws OrekitException

Compute the contribution of the force model to the perturbing acceleration.

Specified by:

addContribution in interface ForceModel

Parameters:

s - current state information: date, kinematics, attitude

adder - object where the contribution should be added

Throws:

OrekitException - if some specific error occurs

getEventsDetectors

public EventDetector[] getEventsDetectors()

Get the discrete events related to the model.

Specified by:

getEventsDetectors in interface ForceModel

Returns:

array of events detectors or null if the model is not related to any discrete events