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Nonlinear Robust Missile Autopilot Design Using Successive Galerkin Approximation (1999)
| Content Provider | CiteSeerX |
|---|---|
| Author | Mclain, Timothy W. Beard, Randal W. |
| Description | 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 pitchaxis autopilot for a missile having uncertain pitch moment and lift force is described. INTRODUCTION The dynamics of guided launch vehicles are inherently nonlinear due to inertial coupling, gravitational forces, aerodynamic effects, and actuator limits. Though autopilot designs are typically based on linearized dynamic models, modern missile systems often operate in flight regimes where nonlinearities significantly affect dynamic response. Much of the recently published missile control literature focuses on the application of linear robust... in Proceedings of the AIAA Guidance, Navigation, and Control Conference |
| File Format | |
| Language | English |
| Publisher Date | 1999-01-01 |
| Access Restriction | Open |
| Content Type | Text |
| Resource Type | Article |
