基于L-M算法的液体火箭推力室壁面热流密度测量方法  

Method to Measure Wall Heat Flux of Liquid Rocket Thrust Chambers Based on L-M Algorithm

作　　者：韩兆鹏 韩亚威 刘亚冰[1] 韦宝禧[1] 冮强[1] HAN Zhao-peng;HAN Ya-wei;LIU Ya-bing;WEI Bao-xi;GANG Qiang(Science and Technology on Scramjet Laboratory,Beijing Power Machinery Institute,Beijing 100074,China)

机构地区：[1]北京动力机械研究所高超声速冲压发动机技术重点实验室,北京100074

出　　处：《推进技术》2021年第7期1643-1651,共9页Journal of Propulsion Technology

摘　　要：为获取液体火箭推力室热防护方案构建的基础数据,结合单点瞬态法,提出了基于L-M算法测量壁面热流密度的方法。通过模拟热流密度分析算法中关键参数对求解精度的影响,给出关键参数的选取建议。在此基础上,对过氧化氢煤油推力室典型试验工况进行热流密度测量。结果表明:圆筒段末端壁面热流密度为3.35MW/m^(2),喉部位置单组元工况下壁面热流密度为2.21MW/m^(2),双组元工况下壁面热流密度为10.59MW/m^(2),热流密度变化过程与室压变化过程完全对应。变工况过程中近壁处燃气温度存在恢复过程,燃气温度稳定后,壁面热流密度也达到稳定状态。本文提出的方法可迅速、准确地测量推力室壁面热流密度。To obtain basic data for designing thermal protection of liquid rocket thrust chambers,a method to measure wall heat flux based on L-M algorithm was proposed,which could be implemented with the transient temperature data obtained by a thermocouple. And through simulation heat flux comparison and discussion,the key parameters’ value suggestion which would influence the solution accuracy was also given. Then,apply it in the typical hot firing test of a hydrogen peroxide biopropellant thrust chamber. The results indicate that wall heat flux at the end of cylinder is 3.35 MW/m^(2). The wall heat flux at throat is 2.21 MW/m^(2) in the monopropellant mode and 10.59 MW/m^(2) in the bipropellant mode,which matches the change process of chamber pressure well. The gas temperature near the wall will recover for a certain time when the test condition changes.After the gas temperature stabilizes,the wall heat flux also reaches a steady state. The proposed method can be used to measure the wall heat flux rapidly and accurately.

关 键 词：推力室 热防护 L-M算法 壁面热流密度 过氧化氢 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]