Title

Nonlinear Stochastic Control Part Ii: Ascent Phase Control Of Reusable Launch Vehicles

Abstract

In designing a robust ascent phase control for reusable launch vehicles, uncertainties such as variations in aerodynamics, jet effects, hinge moments, mass property, and navigation processing, etc. have to be considered and normally time and labor intensive Monte Carlo simulations are used in order to achieve a desired tracking performance distribution. In this paper, a systematic stochastic control design method based upon a direct quadrature method of moments proposed in Part I [26] will be applied to the ascending phase attitude control problem. In conjunction with a nonlinear robust control and an offline optimization through nonlinear programming, any order of stationary statistical moments can be directly controlled. Two simulation scenarios of the X-33 ascent phase control have been used to demonstrate the capabilities of the proposed method and the results are validated by Monte Carlo runs. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

Publication Date

1-1-2009

Publication Title

AIAA Guidance, Navigation, and Control Conference and Exhibit

Number of Pages

-

Document Type

Article; Proceedings Paper

Personal Identifier

scopus

DOI Link

https://doi.org/10.2514/6.2009-5956

Socpus ID

78049252399 (Scopus)

Source API URL

https://api.elsevier.com/content/abstract/scopus_id/78049252399

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