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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    Title :

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


    Contributors:

    Publication date :

    1967


    Size :

    3 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English