Optimal disturbance rejection in missile autopilot design using projective controls

A projective control approach used to design a normal acceleration command missile autopilot is presented. Projective controls are used to retain the eigenstructure of an H_∞ optimal state feedback controller using a low-order output feedback compensator and to retain the performance, robustness, and disturbance attenuation properties of the state feedback design. A free parameter matrix used in the projective control design is optimized to minimize the Frobenius-Hankel norm of the error dynamics between the optimal state feedback reference solution and the projective control