Package org.orekit.forces.maneuvers.propulsion

Class PolynomialThrustSegment

java.lang.Object

org.orekit.forces.maneuvers.propulsion.PolynomialThrustSegment

All Implemented Interfaces:

ThrustVectorProvider

public class PolynomialThrustSegment
extends Object
implements ThrustVectorProvider

Thrust vector given as polynomials for the Cartesian coordinates.

Since:

12.0

Author:

Luc Maisonobe

Constructor Summary

Constructors

Constructor	Description
PolynomialThrustSegment(AbsoluteDate referenceDate, PolynomialFunction xThrust, PolynomialFunction yThrust, PolynomialFunction zThrust)	Simple constructor.

Method Summary

Modifier and Type	Method	Description
Vector3D	getThrustVector(AbsoluteDate date, double mass)	Get thrust vector at a specified date.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	getThrustVector(FieldAbsoluteDate<T> date, T mass)	Get thrust vector at a specified date.

Methods inherited from class java.lang.Object

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

Constructor Details

PolynomialThrustSegment

public PolynomialThrustSegment(AbsoluteDate referenceDate,
 PolynomialFunction xThrust,
 PolynomialFunction yThrust,
 PolynomialFunction zThrust)

Simple constructor.

Parameters:

referenceDate - reference date of the polynomials

xThrust - thrust along X direction (N)

yThrust - thrust along Y direction (N)

zThrust - thrust along Z direction (N)

Method Details

getThrustVector

public Vector3D getThrustVector(AbsoluteDate date,
 double mass)

Get thrust vector at a specified date.

Specified by:

getThrustVector in interface ThrustVectorProvider

Parameters:

date - date to consider

mass - current mass

Returns:

thrust at date (N)

getThrustVector

public <T extends CalculusFieldElement<T>>
FieldVector3D<T> getThrustVector(FieldAbsoluteDate<T> date,
 T mass)

Get thrust vector at a specified date.

Specified by:

getThrustVector in interface ThrustVectorProvider

Type Parameters:

T - type of the field elements

Parameters:

date - date to consider

mass - current mass

Returns:

thrust at date (N)