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目前的寻的导弹制导和控制问题的研究是以估算和控制可以分开,即滤波器和制导律可以分别设计的假设为基础的。但由于和导弹问题有关的动力学或测量是非线性的,因而这种分开的设计方法是不能实现的,故制导律的设计应考虑到滤波器的性能。在本研究中,一种使滤波器能观测性达到最大的倾斜转弯式导弹的拦截轨迹始终是仅对角度的测量值确定的。我们把性能指标选择为能观测性矩阵的迹。假定目标是等速直线运动,且把导弹看成一个质点。在与尾追状态相对应的发射几何关系中,导弹的最佳轨迹在与垂直平面夹角约为45°的平面内摆动。
Current research on missile guidance and control problems is based on the assumption that estimation and control can be separated, that is, filters and guidance laws can be separately designed. However, since the dynamics or measurements related to the missile issue are non-linear, such a separate design approach can not be achieved, so the design of the guidance law should take into account the performance of the filter. In the present study, the intercept trajectory of a tilted turn-by-turn missile that maximizes the observability of the filter is always determined only by the angle measurement. We chose the performance indicator as a trace of the observability matrix. Assume the target is a constant velocity linear motion, and the missile as a particle. In the launch geometry corresponding to tail chase, the optimal trajectory of the missile swings in a plane that forms an included angle of about 45 ° with the vertical plane.