Missile Ejection System Launch Attitude Adjustment Research

The multi-piston ejecting system of missile, which is powered by nitrogen, is studied in this dissertation. First, mathematical model and numerical simulation of the system are established. Then, aiming at the problem that the missile will incline while its centroid is not on the symmetry axis of the right and left piston, an automatic control system which can adjust the stance of the missile automatically is put forward, instead of traditional method which is adjusted by handwork.The program of the numerical simulation is designed in VB language. The change rule of the ejecting system and missile's movement parameter can be obtained after simulating the ejecting process of a special kind of missile. According to the feasibility of adjusting the stance of the missile by changing the throttle's hatch size, a design precept of the automatic control system is brought forward and the academic model of the control system is set up. Then the professional software of control system MATLAB/Simulink is used to simulate the systems with different control arithmetic, PID and fuzzy self-adapting PID. A series of response curves can be plotted, because of bringing in fuzzy logical control arithmetic, the system with fuzzy self-adapting PID has better system performance than the one with PID. The academic model, control arithmetic and control parameter of the control system which studied in this paper can supply reference to effective design of the automatic control system.