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Analytical Investigation of Acceleration Restrictiion in a Fighter Airplane with an Automatic Control System

James T. Matthews

出版	National Advisory Committee for Aeronautics, 1958
URL	http://books.google.com.hk/books?id=7X9DAQAAIAAJ&hl=&source=gbs_api
EBook	FULL_PUBLIC_DOMAIN

註釋

The flight conditions considered were airspeeds of 600 and 1,000 feet per second, at sea level and an altitude of 20,000 feet, and maneuver margins of 3.3, 13.3, and 23.3 percent of the mean aerodynamic chord. The most desirable transient responses (10 percent or less overshoot) to acceleration commands were obtained when pitching velocity was fed back in a manner that increased the damping of the airplane and pitching acceleration was fed back in a manner that increased the effective inertia of the airplane. In order to obtain satisfactory performance, all the systems investigated required a compensating network which reduced the phase lag of the power control in the vicinity of its natural frequency.