Research Of Missile Modeling And Attitude Control For Multi-missile Cooperation

Multi-missile cooperation is a new type of systematic combat method. In the multi-missile cooperation, all the missiles in the combat form a fighting network. Under the regulation and management of the network command center, different missiles communicate and exchange information with each other, so that an overall fighting objective can be achieved. By doing this, some impossible missions can be completed, like achieving tactical stealth, enhancing the capacity of electromagnetic countermeasure and moving target recognition. The flight and combat effectiveness of the missile are directly affected by the aerodynamic features. That is to say, achieving fast and precise attitude control is the basis for multi-missile cooperation. In this thesis, the problems of missile attitude control are researched from the following aspects:(1) On the basis of dynamic and kinematic equations of the missile, a quaternion model of missile attitude control is built. In this mathematic missile control model, the quaternions are used to describe the rotation of the missile in space. Furthermore, a control model with uncertain parameters is built by taking into account the parameter perturbation and outer uncertainties. This is the foundation of the control algorithms designed.(2) A double-layer controller is proposed for multi-missile formation control. And according to this controller, a simulation of 3-missile formation control is done, which gives the reference attitude angles for lower layer controller. To track the references, an adaptive sliding mode controller is designed for the control system stablished above. With good robustness, the controller can solve the tracking problems in missile attitude control. Furthermore, it is theoretically proved that the system is Lyapunov stable. Simulation results demonstrate that forced by the control law proposed, the attitude angles can track the references well.(3) For the missile attitude control system with parameter perturbation, a modified adaptive sliding mode attitude controller is proposed. Forced by this modified controller, the attitude angles of the control system with uncertain parameters can track the references well. The theoretical analysis proves that the system with this controller is Lyapunov stable, and the simulation experiment demonstrates the effectiveness of the control algorithm.(4) An unmanned autopilot control platform with a three-axis turntable and a missile model is researched. The control target is accomplished by programming with MFC on the autopilot system. Through this practical experiment, the actual control effect of the algorithm is verified. This experiment system can illustrate the attitude control process of the flying missile practically.