侧窗探测动能拦截器轨控有限时间收敛制导律

Finite-time convergence guidance law of side windows detection kinetic kill vehicle with orbit control in terminal

临近空间动能拦截器多采用侧窗探测,为保证探测视场稳定,需使姿态定向且保证视线角稳定,但轨控发动机捷联在弹体上,只能输出大小和方向恒定的力,姿态定向使纵向平面和侧向平面的控制力存在耦合.针对上述问题,设计有限时间收敛制导律和伪速率(Pseudo rate, PSR)脉冲调制器.首先,构建侧窗约束下的三维轨控制导交战模型;其次,设计适应于姿态定向和视线角约束的新型制导算法,并严格证明其有限时间收敛特性;再次,为克服PWPF (Pulse width pulse frequency)将连续控制量转化为数字量时存在的相位滞后问题,设计PSR脉冲调制器;最后,分析不同制导律、目标机动特性和开关机门限等因素对制导精度的影响.数字仿真表明,所设计的制导算法能够使视线角度和角速率有限时间收敛,保证探测视场的稳定,具有较高的制导精度,对目标的机动具有较强的鲁棒性.

Side window detection is usually used in near space kinetic interceptors,which is needed to make the attitude orientation and the line of sight angle stable to ensure the stability of the view.However,the orbit control thruster straps down in the missile body,and the output size and direction are constant,which makes the control of longitudinal and lateral planes interact with each other.In this paper,a finite time convergence guidance law and a pseudo-rate pulse modulator are designed to solve the problem.Firstly,three-dimensional movement relationship between missile and target is established,which includes orbit control thruster.Secondly,the finite time convergence guidance law is designed and its finite time convergence characteristic is proved.What’s more,pseudo-rate pulse modulation is introduced to solve the problem of continuous input digitalization and phase lag by pulse width pulse fregucncy(PWPF).Finally,the influence of different guidance law,target maneuvering characteristics and switching machine threshold is analyzed.The simulation results show that the LOS angular rate converges to zero in finite time before the end of terminal guidance.The guidance law is robust to maneuver target,has higher guidance precision and can ensure the stability of the detection field of view.