Guidance And Control For Short-range Air-to-Ground Missiles

With the precision-guided weapons are widely used in modern wars, the higherperformance are required in system. How to further promote the performance of theprecision-guided weapons has been becoming a hot reseach topic. The design ofguidance and control systems have a direct impact on the perfomance of missiles.In this paper,the research and analysis for short-range air-to ground missles withactive homing system are considered.Firstly, the whole kinematics and dynamics model are built. Under somehypotheses, the subsystem models for pitch, yaw and roll channels of missiles arebuilt. Based on the decoulpoing design idea and by using proportional guidance lawand attitude autopilot,the guidance and control system are established.Then in order to make up for the weakness of traditional design method, theintegrated guidance and control design is raised. By using relative movment oftarget and missile, the guidance information is introducted into the subsystem modelfor each chanel, and then the intergrated guidance and control models for threechannels are bulit. By optimal control approach, the LQR controller withoutstate-constrait, which based on finite-time interval is establish. And in order toprevent the state-oscollation, the LQR controllers with state constraint based onfinite-time interval are built by Eular method. Furthermore, a gain-scheduled LQRcontrollers based on infinite-time interval was proposed,which has a strongadaptability. The result of simulation confirmed the correctness and usefulness ofthe integrated approach,which considered the aerodynamic parameters variation.Finally,6-DOF nonlinear simulation experiments are designed for the groundfixed and maneuvering target. Comparing with the traditional method,thenumerical simulation indicated that the maneuvering performance, the hit accuracyand the terminal attitude stability were promoted obviously by using integratedapproach.