SetClassicElements

Declared in Spacecraft

Declaration

void SetClassicElements(
    double semiMajorAxis,
    double eccentricity,
    double inclination,
    double omegaAscension,
    double argumentOfPeriapsis,
    double trueAnomaly,
    string orbitingBody
);

Description

Sets the classic elements of a body to a series of parameters based on all of the required parameters.

Parameters

Name	Description
semiMajorAxis	[m] Semi Major Axis.
eccentricity	[-] The Eccentricity.
inclination	[rad] The Inclination.
omegaAscension	[rad] The Right Ascension.
argumentOfPeriapsis	[rad] The Periapsis Argument Node.
trueAnomaly	[rad] The True Anomaly.
orbitingBody	The name of the body orbiting.