多级固体火箭制导方案设计与仿真

高超音速飞行器的发射要求满足多项终端约束条件,多约束条件对于带关机控制的液体火箭发动机来说比较容易实现,对于耗尽关机型固体火箭,需通过能量管理来消耗多余能量,满足约束条件.在待增速度的计算中引入能量管理,通过弹道设计和制导方法来进行终端能量的管理,实现具有工程应用价值的闭路制导,对多级固体火箭制导方案设计问题进行深入的研究.通过数字仿真,综合比较不同制导方案的制导精度,获得最优制导方案,为多约束条件下选择高精度制导方案提供参考.

Guidance design and simulation for multi-stage solid rockets

The hypersonic vehicle launch mission needs to satisfy multiple constraints which are easy for the liquid vehicle. But for the solid-powered launch vehicle without burn control,energy management was applied to satisfy the constraints. This paper presented a closed loop guidance precept. The energy management of closed-guidance was performed by ballistic simulation and guidance design in the calculation of speed. It is effective to research the guidance programs of solid rocket. The optimal guidance program can be obtained by simulation analysis and comparing the accuracy of different guidance programs,and provided reference for choosing the high precision guidance program in the multiple constraint conditions.