Research On Thrust Control System Of A Double Pulse Solid Rocket Motor

With the rapid development of science and technology,the requirements of modern warfare on missiles are also constantly improving,which requires the missile to operate within a large airspace and a wide range of Mach numbers.This poses higher requirements for missile power plants,which traditional solid rocket motors can't meet.The double pulse solid rocket motor can continuously provide variable thrust for missile launch,growth and endurance flight,improving the comprehensive performance of missile weapon system.Due to the structural characteristics of the double pulse solid rocket motor itself,the motor works less efficiently.Therefore,in order to improve the comprehensive performance of the double pulse solid rocket motor,it is necessary to further research the characteristics of the thrust of a double-pulse solid rocket motor and thrust control technology.In this paper,the mathematical simulation and the experiment are used,the double pulse solid rocket motor thrust control theory and characteristics,thrust control system,thrust control algorithms and experiments were researched deeply.Its specific content is as follows:(1)The thrust control principle and mathematical properties of the double pulse solid rocket motor are researched.The mathematical model of thrust control system of the double pulse solid rocket motor is established.By analyzing the mathematical model,the characteristics of time-varying,nonlinear and negative overshoot of thrust control system for double pulse rocket motor are pointed out.At the same time,the influence of time-varying variability and time-varying working pressure on the adjustment time and overshoot of the double pulse solid rocket motor is analyzed.The influence of the negative overshoot phenomenon on the system is analyzed.(2)The thrust control system of double pulse solid rocket motor is studied.The overall structure and adjusting mechanism of the double pulse solid rocket motor are designed.Under the condition of reducing the interference of regulating mechanism on the gas flow,the installation strategy of adjusting mechanism is proposed.The function of throat area of nozzle and the number of steps of stepping motor was established,and the change rule was analyzed.The hardware circuit of thrust control system,software program and host computer test system are designed.The semi-physical simulation is used to verify the feasibility of the software.(3)The thrust control algorithm of the double pulse solid rocket motor is studied.Considering the nonlinearity and time-varying of thrust system of the double pulse solid motor,single neuron intelligent control algorithm with adaptive function is discussed.Adopting comparative research methods,the advantages and disadvantages of traditional PI control algorithm and single neuron PI control algorithm are analyzed.The response time andovershoot of the two algorithms are analyzed precisely by Matlab simulation.The simulation results show that single neuron PI control algorithm is more suitable for controlling the thrust of the double pulse solid rocket motor.(4)The ignition experiment program of the double pulse solid rocket motor was studied,and the ignition experiment of rocket motor was carried out.The problems of shape and position error,eccentricity,ablation and short working time of the control system were found.Due to the limitations of the ignition experiment,a thrust control experiment scheme b ased on nitrogen simulation is studied,which overcomes the short working time of the double pulse solid rocket motor.Nitrogen simulation experiments were carried out to verify the control system hardware and software reliability,verify the feasibility of the control algorithm to control thrust.