泵压式发动机瞬态热试验方法  

Method for transient thermal test of turbopump-fed rocket engine

作　　者：邓婉 朱尚龙 李德富 王瑾 戚峰 DENG Wan;ZHU Shanglong;LI Defu;WANG Jin;QI Feng(Beijing Institute of Aerospace Systems Engineering,Beijing 100076,China)

机构地区：[1]北京宇航系统工程研究所

出　　处：《航天器环境工程》2020年第1期89-94,共6页Spacecraft Environment Engineering

摘　　要：上面级泵压式发动机结构复杂、在轨飞行时间短,因此其热设计的验证比较困难。文章针对发动机自身特点提出了瞬态热试验方法,通过对发动机复杂外形包络面规则化、分区构建绝热型热流计(“黑片”)热模型快速提取试验外热流,采用符合发动机外热流瞬态变化趋势的“光照区+地影区”分段阶梯式外热流加载策略。试验温度测量结果表明:发动机热控设计和热分析模型正确;在此基础上修正初温后可对在轨飞行温度给出更准确的预示。The turbopump-fed rocket engine used for the upper stage is complex in structure and has a limited flight time,which poses a challenge to the test validation of their thermal design.In view of to the characteristics of the engine,a transient thermal test method is proposed,with a regulation of the heat flux on the complex outline surfaces of the engine,to build up a thermal analysis model of adiabatic flux sensors(“blackplates”)for each sub area.The sectional stepwise heat flux loading strategy is applied in the thermal test to simulate sunshine and eclipse,respectively.The thermal design and the thermal analysis model of the engine are validated in accuracy by the temperature measurement results.Moreover,on the basis of the current thermal analysis model,the initial temperature is corrected for a better prediction of the temperature of the engine in flight.

关 键 词：泵压式发动机 瞬态热试验 外热流模拟 热分析模型 温度预示 

分 类 号：TK124[动力工程及工程热物理—工程热物理] V416.5[动力工程及工程热物理—热能工程]