Design And Verification Of The Adaptive Control System For A Boost-Glide Missile

The future war will be full of automation and informationization.The boost-glide missile is an advanced weapon with high precision and flexible operation,which has strong penetration capability and plays an important role in the battle.It is difficult to obtain the flight state of the boost-glide missile precisely,which affects the further improvement of guidance and control systems.In order to precisely obtain angle of attack and angle of sideslip of the boost-glide missile and simplify complex design of the control system,the design and verification of the adaptive control system for a boost-glide missile based on calculated flight parameters are carried out.A small solid propellant boost-glide test rocket is designed and manufactured,and the designed adaptive control system is verified by hardware-in-the-loop simulation and preliminary flight test,which has certain theoretical value and engineering application significance.The design method of the adaptive control system based on calculated flight parameters for a boost-glide missile is studied.The resolution model of flight parameters is established for the 9-hole layout scheme,so the angle of attack and angle of sideslip can be calculated online for the adaptive control system.The flight trajectory is designed by angle of attack and angle of sideslip,so the command attitude angle can be obtained.The command attitude angle is compensated according to the difference among angle of attack,angle of sideslip calculated online by the calculation algorithm with command angle of attack and command angle of sideslip.Then the command attitude angle with compensation is tracked to control the flight attitude and trajectory of the missile.The differential term of proportional-integral-differential(PID)controller is improved that the attitude angular rate is introduced into the differential term to design the control law.The six-degree-of-freedom nonlinear motion model of the missile is established,so the control parameters can be optimized offline by phases with genetic algorithm.Then the control parameters will be switched online according to the flight phases to ensure certain adaptive ability to the change of flight environment.An adaptive control parameter adjustment method based on frozen coefficient method is studied.Based on frozen coefficient method,the three-channel transfer function of the missile is derived,and the control parameters optimized offline by genetic algorithm are taken as the initial value to analyze the performance indicators in time domain and frequency domain.The control parameters are adjusted near the initial value to ensure the attitude control precision meets the designed requirements and has an ideal global control effect.The test and verification method of the adaptive control system for a boost-glide missile based on flight parameters is studied.The work flow and work scheme of test and verification are designed for the adaptive system,and the hardware-in-the-loop simulation and preliminary flight test are carried out.A small solid propellant boost-glide test rocket is designed and manufactured,the components of the adaptive control system are plugged into the simulation loop to test.The flight test is planned into three levels,to fly without control,to fly with adaptive control,to fly with adaptive control based on flight parameters.The first level flight test has been completed,which verifies the work logic and the reliability of the electrical control system.It is a foundation for subsequent flight tests and the verification of new algorithms.The work in this paper can provide a reference for calculation of flight parameters,adaptive control,hardware-in-the-loop simulation and flight test of the boost-glide missile.