Aircraft flight controller tracking design using H-Infinity static output-feedback

Abstract

This paper presents an approach for designing compensators of specified structure for shaping the closed-loop step response that uses H-Infinity output-feedback design techniques. This approach results in controllers that take advantage of the wealth of experience in aircraft control design. Simplified conditions are presented, which only require the solution of two coupled matrix design equations. A new numerically efficient algorithm to solve the H-Infinity disturbance attenuation is given. An F-16 normal acceleration design example is solved to illustrate the power of the proposed approach.