Investigation On Design Of Altitude Control System Of The Missile With Supersonic Speed At Minimum Altitude

The traditional design method of missile is combine fixed quantity and feed back control technology, in other words, PIDcontrol. Although PID control is successfully used in many fields, such as aerial navigation, spaceflight, missile and so on, the actual result of the PID control is not satisfied with the demand of some control system. Because of the many jamming problem must been solve when missile fly at minimum altitude, otherwise, the missile would bump into the sea under the circumstances of bad weather and wave. The demanding characteristic of missile altitude control system to solve the different anti-jamming problem is contradiction. And counter in reason the ambivalent anti-jamming problem is prerequisite. To counter the problem of hedgehopping over the sea, a kind of control scheme of PID + altimeter was proposed. The central contents in this paper is the design of the missile altitude control system, this research is practical.The main content of this paper is: first, the reference frame is defined, the movement equation and the transfer function of the body are proposed in portrait plane and the typical trajectory of the missile with supersonic at minimum altitude is given. So the module of the altitude stabilization loop is proposed. Second, the pitching and altitude stabilization loop are designed and simulated by traditional PID control theory, the problem lied in the application of the PID control theory is analyzed and the solution is proposed, that is PID+ integrated altitude control system. Third, the altitudemeasure is made by the integrated altitude control and the theory and form of the integrated altitude control is given. Then the characteristic analyze by simulation. Last the two simulation results of the different methods that are PID control, integrated control used in PID control are compared in this paper. The simulation result show that the method of integrated altitude control used in PID control is able to meet the need of altitude control system of the missile with supersonic speed at minimum altitude.The method of integrated altitude control used in PID control utilize the advantage of stabilization, easy realization of PID control and good precision, not radiation of the radio altimeter, overcome the bad anti-jamming of radio altimeter. The conclusion of the paper has real significance and bright in future, especially in the design altitude control system of the missile with supersonic speed at minimum altitude.