Feedback Control Synthesis for Desired Lateral-Directional Flying Qualities of Military Airplanes

摘要

An original feedback control synthesis method is proposed for obtaining desired lateral-directional flying qualities of military airplanes. Inequality-type constraints imposed to the Dutch roll damping ratio and undamped frequency are considered to define desired levels of flying qualities. Using an appropriate proportional feedback, the desired domain in the damping-ratio/undamped-frequency plane is analytically transposed in the feedback gain plane. A robust operational point is defined in the desired domain of modal flying quality characteristics and the corresponding gain constants are determined. The analytical approach is sustained by relevant numerical applications.