The purpose of this study was to determine the feasibility of launching a Delta Clipper-like vehicle on an optimal, non-coplanar trajectory to rendezvous with an earth orbiting object in one orbit or less. The focus of the research was to determine what such a trajectory would look like, and to determine the cost, in payload mass, of flying such a trajectory. A model for the ascent trajectory was developed using the dynamics equations of motion, an atmosphere model, and an aerodynamic model for the DC-Y concept vehicle. A boundary value problem was posed and solved for a coplanar rendezvous. The non-coplanar solutions were obtained through extrapolation from the coplanar solution.


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    Title :

    Optimal Non-Coplanar Launch to Quick Rendezvous


    Contributors:
    G. B. Sears (author)

    Publication date :

    1997


    Size :

    79 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Optimal non-coplanar launch to quick rendezvous

    Sears, Gregory / Wiesel, William | AIAA | 1998


    Optimal Non-Coplanar Launch to Quick Rendezvous

    Sears, G. / Wiesel, W. / AIAA et al. | British Library Conference Proceedings | 1998