论文部分内容阅读
针对空射巡航导弹(ALCM)投放后需要在指定的高度拉平,同时还必须满足空速不超过临界马赫数的条件,考虑到点火窗口约束,还需对终端空速和迎角进行精确控制问题,提出了一种下滑段多约束制导策略。该制导策略首先利用风廓线补偿风干扰,将空速约束转化为地速约束;然后建立了下滑段的线性化动力学方程,并设计了含偏置量的目标函数,从而获得了同时满足终端高度、弹道倾角、地速和迎角约束的最优法向加速度;最后将过程约束转化为法向加速度边界。仿真结果表明,该制导策略能够满足下滑段的所有约束,具有终端弹道参数散布小、鲁棒性好的特点。在此基础上,还分析了不同点火高度下的可投放区及其影响因素,为ALCM的应用和改进提供了理论依据。
For air-launched cruise missiles (ALCM) after launch need to level at a specified height, but also must meet the airspeed does not exceed the critical Mach number conditions, taking into account the ignition window constraints, the need for precise control of the terminal airspeed and angle of attack , A multi-constraint guidance strategy for sliding section is proposed. The guidance strategy firstly uses the wind profile to compensate the wind disturbance and converts the airspeed constraint into the ground-velocity constraint. Then, the linearization dynamic equation of the gliding segment is established, and the objective function with offset is designed. Thus, Terminal height, ballistic inclination, ground speed and angle of attack constraints of the optimal normal acceleration; finally the process constraints into the normal acceleration boundary. Simulation results show that the guidance strategy can meet all the constraints of the gliding segment, and has the characteristics of small dispersion of terminal trajectory parameters and good robustness. On this basis, it analyzes the deployable areas under different ignition altitudes and their influencing factors, which provides a theoretical basis for the application and improvement of ALCM.