Research On The Variable Structure Control Of Pitch Channel Of Winged Missile

As a tactical weapon, winged missile has reached astonishing effects in recent severalregional wars, been regarding as the represent of new class tactical weapon, its design wasalso highly focused on by countries around this word. With the excellent properties of highlyaccuracy, highly price-performance ratio and highly reliability, which is not employed bytraditional weapons, it was again caught the interests of the scientists. Secondly, the high-techit was owned could also be used in daily life and social production and make admirableeconomic and social impacts.With the flying development of high-tech, especially massive use of electronic-tech andcomputer science, new demand has been faced by traditional technology. It is apparently beenout of date to some extent when facing some new and more advanced demands to theories ofold traditional classical control science. So it was critical to use the achievements of state ofthe art to redesign the old control law with the hoping a new better one can be achieved.This thesis is mainly focused on the study of attitude control of light-disturbed,minor-cycled winged missile with using the theory of variable structure control. First,integrating the basic principles of the physical law and using a series of scientific methods,the easy analyzing and studying dynamical model of winged missile is built up. Then, on thebase of the first step, switching function and reaching law was designed and selected by usingknowledge of the sliding mode variable structure control. Finally, checking the validity of thesliding mode variable structure control law by using computer emulation technology. Thecontroller was proved to be correct by adopting computer emulation technology at last.The way in which the mathematical mode of the winged missile is built up and the controller is designed in this paper can be seen as the fundamental method and knowledge forfuture researching of the more complex system.