Dither self adaptive system performance and closed loop response criterion

Abstract

The use of self adaptive technique to compensate for the varying parameters of a flight control system is desirable for high performance aircraft and space vehicles. The technique discussed in this study consists of using a sinusoidal signal to measure the change in the parameters and of compensating for the change by a gain adjustment. Analog and digital computer methods are used to investigate the performance of the system and the accuracy of the Amplitude Closed Loop Response Criterion for measuring damping ratio. The effects of varying airframe flexibility, center of gravity, frequency of the sinusoidal signal, and the Reference signal value are included. The applicability of the self adaptive technique for a particular vehicle depends on the dynamic characteristics of the airframe and on the desired maximum variations of the performance characteristics.