Approximations are made to the point-mass equations of motion for flight within the atmosphere. Optimal controls are formulated for a reentry vehicle to execute a maximum-terminal-velocity turn to a specified heading while executing steep, descent trajectories. A Newton scheme is used repetitively to solve a nonlinear algebraic system for two parameters in the control equations to provide the on-line guidance. Trajectory comparisons from the repetitive solution of the optimal control problem, pure numerical optimization, and simulation of sample-data guidance show good agreement, if the atmospheric model is accurate. (ERA citation 11:038558)


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    Title :

    Optimal Descending, Hypersonic Turn to Heading


    Contributors:
    G. R. Eisler (author) / D. G. Hull (author)

    Publication date :

    1986


    Size :

    17 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Optimal descending, hypersonic turn to heading

    EISLER, G. / HULL, D. | AIAA | 1986


    Optimal descending, hypersonic turn to heading

    EISLER, G. RICHARD / HULL, DAVID G. | AIAA | 1987



    Time Optimal Turn to a Heading: An Analytic Solution

    Walden, R. | Online Contents | 1994