Research On Terminal Guidance And Control Of Interception For Maneuvering Targets

Precision-guided weapons play an increasingly important role in the modernwar. Among these techniques, guidance and control is the most importanttechnology. It determines the firing accuracy directly. Based on the background ofresearch on terminal guidance and control of interception for maneuvering targets, anew controller is designed, as well as a new paralle l approaching guidance law,which is used in the missile attitude control.Firstly, model of missile is given for the new control algorithms as well as theattitude control model including the pitch, yaw and roll channel of the missile.Meanwhile, the missile-target engagement geometry model for the new guidancelaw design is established in the two dimensional LOS (line of sight) coordinates.In addition, an advanced TD filter based on the Lyapunov theory is designedwhich can estimate system variables accurately without the controlled object model.The standard forms of ITAE optimal transfer function is introduced. According tothe optimal ITAE coefficients, the gains that is the outputs of the advanced TD filterare configured which feedback to the plant in order to adjust the system architecture.Then, a PID or variable structure controller is designed for eliminating the error scaused by the feedback data time delay, the estimation errors of the advanced TDobserver and the other system uncertainties. Simulation results show that the planthas a good performance with the designed controller, and another major advantageof the new control method is that it only requires the model order and gain of theplant without knowing the precise model and whether the model is linear.Finally, the observability problems and conditions for bearing-only targetmotion is presented. And an filter is used to estimate the position and velocity of amaneuverable target by observation stations. Then, a new parallel approachingguidance law based on analysis of the advantages and disadvantages of itstraditional guidance law which can intercept the high maneuverable targetaccurately in a straight trajectory with the missile normal acceleration less than thetargets’. And the new method only needs relative distance between target and missile, the angle of LOS and the rate of change,without measuring the targetvelocity vector and acceleration.