Abstract
An adaptive, general-purpose, constraint-solving guidance algorithm has been developed by the authors in response to the requirements for the advanced launch system. The algorithm can be used for all mission phases for a wide range of space transportation vehicles without code modification because of the general formulation of the nonlinear programming problem, and the general trajectory simulation used to predict constraint values. The approach allows onboard retargeting for severe weather and changes in payload or mission parameters, increasing flight reliability and dependability, while reducing the amount of preflight analysis that must be performed. The algorithm is described in general in this paper. Three-degree-of-freedom closed-loop simulation results are presented for application of the algorithm to advanced launch system ascent, re-entry of a low lift-todrag vehicle, and Mars aerobraking. Flight processor throughput requirement data are shown for each of these applications.
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