Research On Solid Attitude Control Thrusters Of Kinetic Kill Vehicle

The kinetic kill vehicle (KKV) intercepts the target by derectly hitting which makeshigh requirements for the control precision of the attitude control system. The performanceof the attitude control thruster is very important for the control system as its actuator. Thisdissertation takes the solid attitude control thruster as research objects. A new kind of solidattitude control thruster is presented and threoretical and experimental research is done.Results of this dissertation have an important value for the structural design, performancetest and engineering application of the thrusters.The solid attitude control thruster is designed according to the form of valve-nozzle.The pressure dynamic performance and the flow rate of the two control chambers areanalyzed and the aerodynamic resistance of the piston is researched. Then the non-linearmathematic model in the process of movement is established.The aerodynamic resistance of the piston is analyzed by the flow law, numericalsimulation and experiment and the nonlinear equation between the resistance and the pistondisplacement is obtained. The pressure curves of the control chambers tested in experimentand the simulation results are compared to verify the correctness of the model. The delaytime of the thruster is analyzed and a test method is proposed by testing the piston’sposition signal with hall elements.The mathematic model is linearized and how the change of the gap between the nozzleand armature influences on the dynamic performance is researched. The impace that thetwo medium of compressed air and gas has on the thruster’s performance is also studied.The conclusion is reached that the two medium has little influence on the aerodynamicresistance and static force and appreciable impacted the dynamic performance. Thedetection system that is used to test the thruster’s performance is put forward.The thruster’s working efficiency is studied. The delay time and work efficiency aretaken as optimization indicators and the structure parameters are multi-objectiveoptimization designed by adaptive differential evolution algorithm. The optimizationstructure parameters are obtained after optimization.Two methods to test the dynamic force of the thruster are presented towards itscharacteristic. The mathematic models of the test systems are established and their dynamicresponse, the data process method and the test error are analyzed. The dynamic compensation is designed to improve the test effect. The merits and demerits of the twomethods are obtained by comparison.The attitude control sheme is simulated in the terminal guidance stage. The guidancelaw and the pulse width modulation control method are designed and the dithering problemof the PWM control is analyzed. The influence of the change and coherence of the delaytime on the control performance is researched and the model is simulated by the experimentresults. The results indicates that decreasing the delay time can improve control effect andthe problem of coherence has a big impact on control precision.