Composite Control. Roll The Direct Force And The Aerodynamic Missile Jet

After the Gulf war, new generation anti-air missile, especially with the ability of anti ballistic trajectory missile (BTM), is being developed by more and more country. Many kinds of advanced technologies and methods have been adopted to improving the precision of interception in order to intercept and kill the warhead of BTM totally in the air. At present, the most effective method of destroying the warhead of BTM is the technology of directly hit kinetic kill, which can achieve precision control to the missile by adding the trajectory-control jet or attitude-control jet.The thesis tracks the research about the intercept technology oversea. The rolling missile model with attitude-control-system is established by referring to the figuration dimension of PAC-3. Using this model, the combined-control-system of aerodynamics and direct force produced by lateral jets. The main work and achievements are described as follows:1. At first, the rolling missile model had been established by referring to the figuration dimension of PAC-3. The motion model and dynamics model of the rolling missile was constructed, and the thrust performance of attitude control system were presented.2. Considering the difference of the rolling missile and the non-rolling missile, the mechanism of rolling missile control force and the control theory of rolling missile was analyzed rigorously. Then the Matlab was used to simulate and analyze the produced process of control signal and the influence of the amplification and the frequency of the linearization signal impacted on equivalent control force.3. Based on the average mathematical model, the transfer function of the rolling missile was deduced, and the stability conclusion was deduced and applied to the research object.4. The combined control system was designed. By means of control command decomposed forwardly, the combined control system was divided into tow parallel subsystems, namely the aerodynamics subsystem and the direct force subsystem. Modern control theory is applied to design the aerodynamics subsystem and the direct force subsystem. The simulation results show that the available load and the performance of the transit response improved obviously.5. In the end of this thesis, the six-degreed -of-freedom mathematic model and simulation model was established for the terminal guidance phase, and the trajectory simulation was carried out with the different initial condition when intercepting the airplane and the tactical ballistic missile. The results show that the performance of the combined control system designed in this thesis was superior to the traditional only aerodynamic control system, and the warhead of tactical ballistic missile with medium velocity could be intercepted.