Control System Design for the Digitized Grumman F - 14 Benchmark Control Problem

A particular H
^∞
design approach is coupled with multicriterion optimization to design a pitch axis controller for the F - 14, one of the CSS benchmark control problems. In this two-degree-of-freedom structure, the controller is designed via an H
^∞
method based on minimizing a weighted quadratic combination of the sensitivity and complementary sensitivity functions of the system. The pre-compensator is used to shape the output responses so as to cause the entire system to achieve the desired performance. The angle-of-attack α(t) model following error, constraints on the normalized pitch rate |q(jw)|
_nom
, and the effects of the wind gust and sensor noise on α and q are examined. The robustness of α(t) under the aircraft large parameter variations is also studied.