Abstract
In designing a flight control system of the aircraft where only the input and the output can be measured, it is desirable to use adaptive control synthesis approaches. However, most of those approaches can not apply to the plant with the limitation of input amplitude, because those studies are usually done without any lim- itation of input amplitude.
In this paper, we deal with the problem of constructing an adaptive flight control system for the aircraft with the angle limitation of control surface. First, by introducing the dispersion flter, two adaptive control schemes for a single-input single-output time-invariant discreate system with the limitation of input amplitude are proposed. Next, these schemes are applied to solve the problem of constructing an adaptive flight control system for both a supersonic aircraft and a VTOL aircraft. Simulation studies which construct an adaptive flight control system of these aircrafts are presented to show the effectiveness and the features of the proposed schemes.
