固体火箭发动机热流测量方法及试验研究  

Heat flux measurement method and experimental research in SRM

作　　者：张翔宇[1] 刘佩进[1] 李鹏飞[1] 李江[1] 

机构地区：[1]西北工业大学燃烧热结构与内流场重点实验室,西安710072

出　　处：《固体火箭技术》2011年第1期131-134,共4页Journal of Solid Rocket Technology

基　　金：国家自然科学基金项目(50776073)

摘　　要：将一套创新设计的热流测量装置嵌入到可改变条件参数的固体火箭试验发动机中,进行了含铝复合推进剂试验。通过改变推进剂含铝量、燃烧产物冲刷速度和冲刷角度,测量了不同工况下两相燃烧产物的总传热热流密度。总传热规律与理论分析结果相吻合。试验证明,该装置能经受发动机内的高温强冲刷的苛刻条件。试验得到的总热流密度可为绝热层烧蚀研究中所需的传热边界提供数据参考,以及用于检验发动机燃烧产物传热数值模拟的精度等。该热流量试验方法具有较好的探索性和实用性,为后续开展一系列两相流冲刷下的传热特性研究提供了良好基础。A series of aluminized solid propellant combustion tests were carried out by using an innovativly designed instrument for heat flux measurement.The total heat flux of two-phase flow has been obtained under condition of changing the content of aluminum,altering eroding velocity and incidence angle of the combustion products.Experiments proved that the device was able to endure the harsh condition inside the engine and the test results coincided with theoretical analysis fairly.Heat-flux through the experimental measurements would provide the essential data for ablation of insulation and check the accuracy of numerical simulation of heat transfer between combustion products and the chamber.This instrument and test method provided a good exploratory development for heat-flux measurement in SRM and a foundation of further experiments under condition of two-phase flow impingement.

关 键 词：固体推进剂火箭发动机 热流测量 两相流冲刷 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]