SimulateKeplerOrbit

This program simulates a Keplerian orbit at a given timeSeries starting from the given integrationConstants.

Name	Type	Annotation
outputfileOrbit	filename
timeSeries	timeSeries
GM	double	Geocentric gravitational constant
integrationConstants	choice
kepler	sequence
majorAxis	double	[m]
eccentricity	double	[-]
inclination	angle	[degree]
ascendingNode	angle	[degree]
argumentOfPerigee	angle	[degree]
meanAnomaly	angle	[degree]
time	time	integration constants are valid at this epoch
positionAndVelocity	sequence
position0x	double	[m] in CRF
position0y	double	[m] in CRF
position0z	double	[m] in CRF
velocity0x	double	[m/s]
velocity0y	double	[m/s]
velocity0z	double	[m/s]
time	time	integration constants are valid at this epoch