Research On The Effect Of Disturbance Rejection Rate On Guidance Performance And Lyapunov Guidance Technology

Based on the demand of missile guidance and control technology,the research included the follow contents: the effect of the disturbance rejection rate(DRR)induced by the radome and seeker on the guidance system,the stability region research of the strapdown guidance system with miss distance constraint,dynamic stability for non-rolling and rolling missiles considering DRR and guidance technolog based on Lyapunov theory.Firstly,the mechanism of the DRR induced by the radome and seeker for phased array seeker is analysed,the guidance system model considering DRR is established.The stability condition of the guidance system is deduced,and the effect of DRR induced by the radome and seeker on the stability region of guidance system is studied.The influence of the DRR on the key parameters of the guidance system is analyzed,and the effects of DRR induced by the radome and seeker on the miss distance are studied.The results show that the superposition of the radome and seeker has different effects on the stability region and miss distance of the guidance system.The worst case is the positive feedback superposition,which will seriously affect the performance of the guidance system.In order to design a guidance system that satisfies the miss distance constraint,the stability condition of the guidance system considering DRR is deduced based on the phased array seeker guidance system.The stability regions of the DRR and the guidance system are compared and analyzed,the shortcoming of the traditional research methods of DRR is pointed out.On this basis,the dimensionless adjoint medel of the strapdown guidance system is established,and the method to determine the stability region of the guidance system under the constraint of miss distance is proposed and verified by numerical simulation.The results show that the stability region of the guidance system under the constraints of the terminal miss distance can satisfy the requirement of the miss distance and provide the design basis for the guidance system.In the tranditional method of DRR,the autopilot is equivalent to n-order dynamics,which ignores the differences between different structures of the auropilot.In order to solve this problem,a proportional navigation guidance/typical structure guidance system model is proposed,and the stability contion of the guidance system composed by the typical topological structure is deduced.The effects of DRR,the static stability,and the accelerometer position on the stability region of guidance system are studied.The results show that the stability of the guidance system is influenced by the DRR,the static stability of missile,the paprameters of autopilot and the position of the accelerometer.The influence of different autopilot structure is not same.In order to study the dynamic stability of of the rolling missiles considering DRR,the rolling-missile's guidance system model of typical topological structure considering DRR is established,and the system model is transformed into complex system,the stability conditions of the guidance system composed of the typical topological structure autopilot are deduced.Based on this,the influence of the system parameters on the stability region of tpical structure autopilot is studied.The design method of rolling missile's autopilot is proposed based on DRR constraint.The results show that the influence of DRR,rolling rate,total delay angle and accelerometer position on the stability region varies with the structure of the autopilot.The design method of autopilot for the rolling missiles based on the DRR index constraint can ensure the dynamic stability of rolling missile,and obtain good time domain performance.At the end of this paper,based on the Lyapunov theory,the general form of Lyapunov guidance law ignoring the dynamic of the seeker is deduced,and further the general form of Lyapunov guidance law considering the first-order dynamics of the seeker is deduced.The estimation of angular rate and its aceeleration based on the Kalman filter theory is studied.The results show that the Lyapnov guidance law which ignores the seeker dynamic has the similar performance to the traditional guidance law,and teLyapunov guidance law considering the first-order lag of the seeker is effective to reduce the required guidance time and ensure the short guidance time convergence of miss distance.