Design of Decoupled Longitudinal Flight Control Laws Utilizing Eigensystem Assignment

Eigenstructure assignment and command generator tracking are applied to the design of pitch pointing and vertical translation control laws for the AFTI F-16 aircraft. The desired eigenvectors are chosen based upon performance and sensitivity considerations. Feedforward command tracking gains are computed to ensure steady state following to the pilot´s command. An interesting feature of the design is that both modes may be implemented using the same feedback gains. Furthermore, the aircraft exhibits a conventional response with acceptable handling qualities when a flaperon failure occurs.