A robust pitch pointing control law

Eigenstructure assignment and command generator tracking are applied to the design of a pitch pointing control law for the AFTI F-16 aircraft. The eigenvalues are chosen to obtain desired damping and rise time and the eigenvectors are chosen to decouple the pitch attitude and flight path angle. Then the design is modified to improve the multivariable phase and gain margins. Finally, a proportional and integral and delay model of a pilot is utilized to illustrate the interaction between the pilot and the aircraft. This output feedback and feedforward gain design differs from previous designs in that only proportional control is required.