Keywords

nonlinear control, optimal control, missile autopilot design

Abstract

The application of a new nonlinear optimal 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-Bellman equation by Successive Galerkin Approximation. Using this approach, feedback controllers are computed by an iterative application of a numerical Galerkin-type PDE solver. Simulation results demonstrating the application of this approach to the design of a missile autopilot are presented.

Original Publication Citation

McLain, T. and Beard, R. Nonlinear Optimal Control Design of a Missile Autopilot, Proceedings of AIAA Guidance, Navigation, and Control Conference, AIAA-1998-4321, August 1998, Boston, Massachusetts.

Document Type

Peer-Reviewed Article

Publication Date

1998-8

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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