Keywords

missile autopilot design, nonlinear robust control, Galerkin approximation

Abstract

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.

Document Type

Conference Paper

Publication Date

1999-8

Publisher

AIAA

Language

English

College

Ira A. Fulton College of Engineering and Technology

Department

Mechanical Engineering

University Standing at Time of Publication

Assistant Professor

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