助推-滑翔式导弹总体参数设计方法初探

Preliminary Investigation of Parameter Design Method for Boost-Glide Missile

以两级固体推进剂火箭发动机助推、弹头直接入轨,而后全程在大气层内滑翔飞行的助推-滑翔式导弹为研究对象,对导弹总体参数设计进行研究,给出一种适用于助推-滑翔式导弹的总体参数设计方法。根据助推-滑翔式导弹的弹道特点,通过分段分析弹道特性,推导出导弹总体参数与关机点理想速度间的关系式。通过仿真分析,建立滑翔起点参数与关机点参数间的关系模型;考虑平衡滑翔条件,得到滑翔射程公式。基于以上公式和模型,给出助推-滑翔式导弹射程与关机点参数之间的解析关系,初步建立了助推-滑翔式导弹总体参数的设计方法。

Based on two class solid propellant missile whose warhead orbits directly and then glides in the aerosphere all along, missile parameter design is studied, and a parameter design method for boost-glide missile is proposed. According to the characteristic of boost-glide trajectory, the trajectory is divided into several parts and each part is studied： the relationship between missile parameters and the theoretical velocity is deducted; through simulation, the model used to describe the relationship between parameters of glide starting point and that of engine shutdown point is established; considering the balanced glide condition, the formula to estimate the glide range is obtained. Based on the models, the analytical expression between the missile range and the parameters of the engine shutdown point is given, and the parameter design method for glide missile is established preliminarily.