Remote Rotate The Rocket Control System Design And Placement Accuracy

With the developing of modern military technology, High-Velocity-Projectile(HVP), which had been used as a highly efficient saturation attack weapon, was more highly regarded in power countries. How to promote the accuracy of the HVP to satisfy the need of modern war is a severe problem that must be solved immediately. The side-jet-engine can be used as an implement to control the HVP.The jet engine is an implement that can produce instant control force. The force controlled by the electromagnetic valve, worked in the magnitude of millisecond. When HVP is rolling, the jets, positioned on the missile, turn on and off and the needed controlling force was developed.This paper aimed at a kind of low cost control system working on a type of HVP. The controlling force developed by the jets is working at the beginning of the initiative trajectory (0.385-3.385s) to control the attitude of the projectile to keep its axis on the direction of launch-direction, so as to reduce the effect of initial disturbance.This thesis has done the following research:1 .The mathematical model of rolling missile was established. The way that the jet engine works was introduce. Compared with the rudder control system, the paper introduced the character of the jet control system. Then the MATLAB was used to reveal the relation between the control force coefficient and the deviation of the missile.2.According to the different analysis method, two mathematical models were established. According to the analysis of the transient control force, the transient mathematical model was build. On the base of the analysis of the average control force, the average mathematical model was build.3.The transient mathematical model reveal aerodynamic coupling angle. The control system was enhanced for it.4.The transfer function was established on the base of the average mathematical model. The stability conclusion was deduced, and was applied to the object.5.The Monte Carlo method was applied to verify the effect of the control system. With each sort of disturbance, given the different type of disturbance, we test the controlled project and non-controlled project separately. And we gained satisfying result.The method of this thesis works on other general rolling missile as well as theobject of the paper.