A trajectory-optimization process is described in which the optimum­ thrust equations are derived using the calculus of variations. The mag­nitude of the thrust is constrained within an upper and a lower bound, but the thrust direction is arbitrary. This formulation allows both the constant-thrust program and the variable-thrust program to be con­sidered. For the constant-thrust program, certain propulsion-system parameters are optimized for maximum final vehicle mass. This theory has been used to study interplanetary missions to Venus and Mars using a power-limited propulsion system. Both one-way and round­ trip rendezvous trajectories are considered. The analysis employs a two-body inverse-square force-field model of three dimensions. An iterative routine used to solve the two-point boundary-value problem is described in the Appendix.


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    Title :

    Interplanetary Trajectory Optimization with Powerlimited Propulsion Systems


    Contributors:

    Conference:

    Inst. of Aerospace Sciences Specialists Meeting on Vehicle Systems Optimization ; 1961 ; Garden City, NY, United States


    Publication date :

    1962-02-26


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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