多层隔热材料热防护方法  

Thermal protection methods of multilayer heat insulation material

作　　者：张忠利[1] 周立新[1] 胡锦华 ZHANG Zhongli;ZHOU Lixin;HU Jinhua(Xi'an Aerospace Propulsion Institute,Xian 710100,China)

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2023年第2期51-56,共6页Journal of Rocket Propulsion

基　　金：国家联合基金(U1737112)。

摘　　要：基于运载火箭一二级发动机分离时热流密度约为9.6 MW/m^(2)、持续时间0.5 s,二级发动机工作时的喷管辐射热流密度为25~100 kW/m^(2)、持续时间120 s的边界条件,选取了2.0 mm厚的氧化锆陶瓷纤维板、5.0/8.0 mm厚的硅酸铝纤维毡、3.2/1.6 mm厚的阻燃型硅橡胶组成的两种隔热方案。应用一维非稳态方法仿真分析了两种隔热方案保护下发动机舱内部组件的壁温,依据隔热组件壁温及材料质量,提出了耐高温多层隔热材料热防护方案。使用液化气喷枪喷吹高温合金平板模拟燃烧室壁,模拟试验壁温测试值表明隔热方案可以满足热防护要求。Based on the boundary conditions that the separated heat flux of the 1st and 2nd stages of the launch vehicle is about 9.6 MW/m^(2)and the running time is 0.5 s,and the nozzle radiation heat flux of the 2nd stage engine is 25-100 kW/m^(2)and lasting time is about 120 s.Two thermal insulation schemes were selected,which were composed of 2.0 mm thick zirconia ceramic plate,5.0/8.0 mm thick aluminum silicate fiber felt and 3.2/1.6 mm thick flame retardant silicone rubber.One-dimensional unsteady state method was used to simulate and analyze the wall temperature of the components in the engine under the protection of two thermal insulation schemes.According to the wall temperature and material mass,the thermal protection scheme of high temperature resistant multilayer thermal insulation materials is put forward.Using LPG spray gun to inject super-alloy plate to simulate the combustion chamber wall,the wall temperature of simulation test shows that the thermal insulation scheme can meet the requirements of thermal protection.

关 键 词：运载火箭 液体火箭发动机 热防护 隔热材料 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]