missile autopilot design, nonlinear robust control, Galerkin approximation
The application of a new nonlinear robust control strategy to the design of missile autopilots is presented. The control approach described and demonstrated here is based upon the numerical solution of the Hamilton-Jacobi-Isaacs equation by Successive Galerkin Approximation. Using this approach, feedback controllers are computed by an iterative application of a numerical Galerkin-type PDE solver. Application of this approach to the design of a pitch-axis autopilot for a missile having uncertain pitch moment and lift force is described.
Original Publication Citation
McLain, T. and Beard, R. Nonlinear Robust Missile Autopilot Design Using Successive Galerkin Approximation, Proceedings of the AIAA Guidance, Navigation, and Control Conference, AIAA-1999-3997, August 1999, Portland, Oregon.
BYU ScholarsArchive Citation
McLain, Timothy and Beard, Randal W., "Nonlinear Robust Missile Autopilot Design Using Successive Galerkin Approximation" (1999). All Faculty Publications. 1935.
Ira A. Fulton College of Engineering and Technology
©2017 AIAA. This is the author's submitted version of this article. The definitive version can be found at https://arc.aiaa.org/doi/abs/10.2514/6.1999-3997
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