Adaptive Control Method Of Rotating Missiles

Self-adapting control method for a kind of rotary missile抯 automatic pilot is studied in this dissertation. (1) Without considering the real change of the missile抯 autogiration frequency, we can design a simpler control system. By mixing the guiding signal and basis signal the control signal is picked up, which is proportional to the guiding signal. Furthermore we add a linearization signal to this control signal and get a PWM signal to control the rudder, producing an average control force which is proportional to the guiding signal. (2) Actually the frequency of the missile抯 autogiration is changing when the missile is flying, then the average control force is not exactly proportional enough to the guiding signal. So we make the frequency of the linearization signal change with the frequency of the missile抯 autogiration. Then the linearity of the average control force can be improved. (3) The uncertain changing of the missile抯 rotating frequency bring indeterminacy to the missile抯 dynamic model, so an ideal dynamic model is introduced to this system as a reference model. And then comparing this reference model with the real model, we can get an errOr system. So a variable structure controller is designed to make the error approach zero and the influence on the system caused by the indeterminacy can be removed. (4) Along with the development of computer, digitalization is a new research direction of the automatic pilot. Those models mentioned above are digitized and good simulation results are got.