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(jΩ)|_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.