Abstract
A simple, two-phase guidance method based on a cubic-spline representation of the altitude-velocity profile, subject to a dynamic pressure constraint and with pay load as the cost function, is developed for the single-stage to low-Earth-orbit mission. The optimal cubic-spline parameters are determined off-line using a genetic algorithm and reoptimized on-line during the initial phase using a gradient search method. In the terminal phase, a perturbation guidance scheme based on linear quadratic regulator theory and gain scheduling is synthesized to keep the actual vehicle close to the optimal cubic-spline path. This method is applied to a generic booster, and its performance is compared with the optimal solution.
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