An Investigation of the Applicability of Linear Optimal Control Theory to Aircraft Control System Design.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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Using steady-state linear regulator theory a longitudinal feedback control system is found for a hypothetical high-performance aircraft that operates through a wide range of Mach number and dynamic pressure. The aircraft stability derivatives vary statistically and the aircraft measurement sensors are affected by body bending responses. Linear approximations of the optimal feedback law gains are programmed as functions of Mach number and dynamic pressure, and the normal-acceleration elevator-step-response of the closed-loop aircraft is simulated. The simulated step responses are compared to a normal acceleration step response criterion envelope that is specified in the 1970 Joint Automatic Control Conference JACC Design Challenge. Author
- Statistics and Probability