public interface TimeDerivativesEquations
The aim of this interface is to gather the contributions of various perturbing
forces expressed as accelerations into one set of time-derivatives of
Orbit
plus one mass derivatives. It implements Gauss
equations for different kind of parameters.
An implementation of this interface is automatically provided by integration-based
propagators
, which are either semi-analytical or numerical propagators.
ForceModel
,
NumericalPropagator
Modifier and Type | Method and Description |
---|---|
void |
addKeplerContribution(double mu)
Add the contribution of the Kepler evolution.
|
void |
addMassDerivative(double q)
Add the contribution of the flow rate (dm/dt).
|
void |
addNonKeplerianAcceleration(Vector3D gamma)
Add the contribution of a non-Keplerian acceleration.
|
void addKeplerContribution(double mu)
Since the Kepler evolution is the most important, it should be added after all the other ones, in order to improve numerical accuracy.
mu
- central body gravitational constantvoid addNonKeplerianAcceleration(Vector3D gamma)
gamma
- acceleration vector in the same inertial frame the spacecraft state is defined in (m/s²)void addMassDerivative(double q)
q
- the flow rate, must be negative (dm/dt)IllegalArgumentException
- if flow-rate is positiveCopyright © 2002-2019 CS Systèmes d'information. All rights reserved.