Steepest-ascent optimization technique involving control variables and control parameters is reviewed with emphasis on influence coefficients for booster staging times; operational computer program to solve optimization problems for boosters having from two to five stages is described; combinations of launching azimuth, lift-off weight, pitchover rate, and cutoff and ignition times of each stage may be used as control variables; problems are defined by choosing payoff quantity and desired terminal conditions from library of 22 terminal functions; two example problems are solved.


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    Title :

    Optimization of thrust direction histories and vehicle parameters for three-dimensional ascent trajectories


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Publication date :

    1966


    Size :

    9 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :