| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 721550 | IFAC Proceedings Volumes | 2007 | 6 Pages |
Abstract
Modern aircrafts and missiles with high manoeuvrability present an interesting challenge to autopilot design, which has activated new investigations in estimating the potential and applicability of recent theoretical control methods as well as how they can meet industrial demands. In this paper, a multi-objective approach for autopilot design is introduced. The design requirements are formulated using several integral criteria. A hybrid-genetic algorithm (GA) is employed to solve the nonlinear optimization problem. The obtained results are verified using nonlinear simulations in SIMULINK® which shows performance, stability and robustness of the designed flight controller.
Related Topics
Physical Sciences and Engineering
Engineering
Computational Mechanics
