nonlinear control, optimal control, missile autopilot design
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.
BYU ScholarsArchive Citation
McLain, Tim and Beard, Randal W., "Nonlinear Optimal Control Design of a Missile Autopilot" (1998). Faculty Publications. 2106.
Ira A. Fulton College of Engineering and Technology
© 2018 AIAA. All rights reserved. https://arc.aiaa.org/doi/abs/10.2514/6.1998-4321
Copyright Use Information