摘要
长尾管的热防护问题是端面燃烧固体火箭发动机研制中最突出的技术关键之一。本文从理论分析、流场计算和实验研究三个方面研究了端面燃烧固体火箭发动机长尾管的热防护问题。揭示出造成长尾管内衬材料局部烧蚀增强的主要机理。数值计算给出了燃气在长尾管内的流线图、压力、温度、密度、湍动能以及湍动能的耗散率。测定了型号发动机在热试车时长尾管壳体外壁面温度分布,以及试车后内衬材料的烧蚀与碳化厚度。另外,还专门设计了模拟内衬材料烧蚀的实验发动机。
The thermal-protection of the duct is one of the most important problems in desiging end-burning solid rocket motors. The problem in three aspects is investigated: theoretical analysis, field numerical calculation and experiments. It is proved that a heat flux increment will occur in some region due to the reattachment of the combustion-gas stream. The streamline diagram, pressure, temperature, density, turbulent kinetic energy and its specific dissipation of the field are given. The temperature distribution of the duct externality and its ablation are measured. An experimental motor is designed to simulate the ablation of the heat-insulation material.
出处
《战术导弹技术》
1997年第4期39-49,共11页
Tactical Missile Technology
