The development of the gradient technique, for trajectory optimization has made it possible to determine rapidly the thrust-attitude history that maximizes the performance of a rocket booster. However, it would be unnecessarily complicated to design a booster autopilot to follow the exact optimum thrust-attitude history. To simplify the autopilot, many boosters are limited to a tilt program that is composed of constant-pitch-rate segments. The approach suggested in this note is to fit a linear-segment curve to the nonlinear thrust-attitude history that is obtained from the optimization program. (Author)


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    Titel :

    Rapid Determination of Near-Optimum Linear Pitch Programs for Rocket Boosters


    Beteiligte:
    R. Rosenbaum (Autor:in)

    Erscheinungsdatum :

    1967


    Format / Umfang :

    3 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch