A circular orbit and constant atmospheric density was assumed. A computer program which determines equilibrium attitudes and the associated eigenvalues of these attitudes is presented. Demonstration of the use of this program was made using the former Skylab satellite as an example.


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    Title :

    Equilibrium and stability of a satellite influenced by gravitational and aerodynamic torques


    Contributors:

    Publication date :

    1981-01-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English