InstrumentAccelerometer2ThermosphericDensity

This program estimates neutral mass densities along the satellite trajectory based on accelerometer data. In order to determine the neutral mass density the accelerometer input should only reflect the accelerations due to drag (e.g. miscAccelerations:atmosphericDrag). Thus, influences from solar and Earth radiation pressure must be reduced beforehand.

Name	Type	Annotation
outputfileDensity	filename	MISCVALUE (kg/m^3)
satelliteModel	filename	satellite macro model
inputfileOrbit	filename
inputfileStarCamera	filename
inputfileAccelerometer	filename	add non-gravitational forces in satellite reference frame
thermosphere	thermosphere	used to compute temperature and wind
considerTemperature	boolean	compute drag and lift, otherwise simple drag coefficient is used
considerWind	boolean
earthRotation	earthRotation
ephemerides	ephemerides

This program is parallelized.