Steepest-descent method of trajectory optimization, developed by A.E. Bryson and H.J.Kelley, is used to compute optimum boost trajectories for lunar and interplanetary transfer missions; computer program PRES TO (Program for Rapid Earth-to-Space Trajectory Optimization) is used to solve two sample problems; in first, maximum payload is determined for 72-hr lunar transfer; in second, maximum burnout weight for 190-day trip to Mars is found. In English with French and German abstracts.


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    Title :

    Powered flight trajectory optimization for lunar and interplanetary transfer


    Additional title:

    Astronautica Acta


    Contributors:
    Rosenbaum, R. (author) / Willwerth, R.E. (author) / Chuck, W. (author)

    Published in:

    Publication date :

    1966


    Size :

    10 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Powered flight trajectory optimization for lunar and interplanetary transfer.

    Chuck, W. / Rosenbaum, R. / Willwerth, R. E. | NTRS | 1966


    Powered flight trajectory optimization for lunar and interplanetary transfer.

    Chuck, W. / Rosenbaum, R. / Willwerth, R. E. | NTRS | 1965



    Interplanetary trajectory optimization

    Damario, L. A. / Stanford, R. H. / Byrnes, D. V. | NTRS | 1981