Study of optimal ascent trajectories
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© 1994 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. This paper presents a study of optimal launch trajectories that minimize fuel or equivalently maximize payload. A model of the Advanced Launch System (ALS) is used for numerical experiments. The three-degree-of-freedom equations of motion for the ALS are solved by the multiple shooting method to obtain highly accurate solutions. The numerical results are presented as the open-loop optimal controls for the ALS. A sudden jump in the velocity roll angle profile during the second stage of the trajectory is noticed. The optimality of this transition is studied using hodograph analysis.
author list (cited authors)
Park, S., Vadali, S., & Seywald, H.