To intercept an orbiting target by another satellite implies, that the two vehicles must arrive simultaneously to the same point in space. In the following a calculation procedure is presented for solving this coincidence problem. To facilitate the calculation of the unknown semi major axis of the interceptor's orbit, Lambert's Equation is rewritten in form of a power series which can be evaluated by a convenient differential correction technique instead of the usual trial and error method. (Author)


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    Title :

    Satellite Interception


    Contributors:

    Publication date :

    1960


    Size :

    2 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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