Two orbit simulations, one representing the actual Geopotential Research Mission (GRM) orbit and the other representing the orbit estimated from orbit determination techniques, are presented. A computer algorithm was created to simulate GRM's drag compensation mechanism so the fuel expenditure and proof mass trajectories relative to the spacecraft centroid could be calculated for the mission. The results of the GRM DISCOS simulation demonstrated that the spacecraft can essentially be drag-free. The results showed that the centroid of the spacecraft can be controlled so that it will not deviate more than 1.0 mm in any direction from the centroid of the proof mass.


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    Title :

    Orbit Simulation Study of a Geopotential Research Mission Including Satellite-to-Satellite Tracking and Disturbance Compensation Systems


    Contributors:

    Publication date :

    1988


    Size :

    119 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English