This is a terminal guidance technique for satellite rendezvous utilizing a constant thrust rocket motor, a computer, and attitude control. For any given thrust level, this technique can reduce the relative range to any desired value in a minimum of time for an interceptor on a collision course. In this paper, a terminal guidance law is formulated and mechanized. The generalized range performance trajectories and system errors are presented.


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    Title :

    Conditional-Switching Terminal Guidance (A Terminal Guidance Technique for Satellite Rendezvous)


    Contributors:


    Publication date :

    1960-12-01


    Size :

    1247410 byte




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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