General Optimal Missile Autopilot Design by Structured Uncertainty Description and Tunable LQ Performance Index

摘要

In this paper, the structured uncertainty description of a non-minimum phase system in the linear quadratic Gaussian and loop transfer recovery process for a general optimal missile autopilot design is originally proposed. The general optimal autopilot with both feedforward and state-feedback controllers will be suitable for both minimum phase and non-minimum phase system. Since most advanced missiles are non-minimum phase systems, the structured uncertainty process confirms that Kaiman filter design is same for minimum phase and non-minimum phase systems. And then feedforward and state-feedback controllers are designed with a prescribed degree of stability in the recovery process. Finally, the numerical results for a coordinated bank-to-turn missile autopilot design will unveil the better time-domain responses for our proposed method.