Research On Control Method Of Supersonic Cruise Missile

Based on the background of altitude control, BTT control and IFPC(integrated flight/propulsion control) of supersonic cruise missile, this dissertation focused on the research of control method and the verification by six-degree-of-freedom simulation.For the aims of flight range extending and capacity strengthening in breakthrough defence system, nowadays the high-to-low cruise trajectory was mostly chose, with high performance demands of altitude control in trajectory of the cruise, the climb and the descending. Large difference is existence in parameters of missile body between high and low trajectory, so an inner-outer control configuration and the variable structure control method to design outer control system based on Lypunov stability theory were put forward in this dissertation. Variable structure control method has inherent flaw of chatter, so a combination of PD and variable structure control method to reduce chatter was took. The performance comparation with that of PD control method shows that the method which combines PD with variable structure control not only has fine robust stability against the variation of missile body parameter, but also reduces the chatter goodly.For the aims of improvement in missile's lift-drag ratio and maneuver ability, the nonaxisymmetrical configuration was mostly chose. But the distribution of inlet duct and the stable work of ramjet under this configuration demand angle of side slip must be restricted to a small range, so the BTT technology should be adopted on lateral high-maneuver, and high-kinematical coupling exists between pitch and yaw system. The weighted functions were determined by analysis of choosing principles and means, and a BTT missile autopilot was designed by mixed sensitivity robust H_∞method. The simulation and analysis on standard state point show that the choosen diagonal weighted functions based on expected performance not only make the pitch/yaw system dynamic decoupling and get expected performance, but also have fine robust stability against the variation of missile body parameter.Air inbreathing propulsion system work unstable and high interrelationships exist between flight and propulsion system on maneuver with large angle of attack, and the improvement of missile's flight performance need propulsion system provide designed thrust. The IFPC technology was discussed to resolve this concerned problem. Two design strategies were analyzed: centralized design and hierarchical design. The comparion of the two design strategies shows that the hierarchical one not only can meet expected performance, but also get a low order designed control system. From the analysis of some main kinds of IFPC design method, it is known that the mixed sensitivity robust H_∞method have the best prospect.Six-degree-of-freedom simulation and analysis show that the dynamic methmatic model is proper and the designed control system is effective. It is also validated that the control method adopted in this dissertation can meet flight performance.