泵压式发动机精细化热分析技术  

Fine thermal analysis of turbopump-fed rocket engine

作　　者：邓婉 李德富 刘小旭 杨炜平 陈益 DENG Wan;LI Defu;LIU Xiaoxu;YANG Weiping;CHEN Yi(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,北京100076

出　　处：《航天器环境工程》2017年第1期49-55,共7页Spacecraft Environment Engineering

摘　　要：上面级泵压式发动机结构复杂、经历的热环境复杂多变,须通过严格的热控设计以保证飞行过程中发动机部组件温度在合适范围内,因此研究泵压式发动机的温度变化规律对发动机研制具有重要作用。文章在分析上面级泵压式发动机热环境特点的基础上,提出了泵压式发动机的热分析建模方法,采用热网络法进行了泵压式发动机精细化热环境分析。通过发动机热平衡试验验证了热分析模型和方法的正确性,获得了发动机在飞行过程中的温度变化规律,可为后续泵压式发动机热分析提供参考。The turbopump-fed rocket engine used for the upper stage has a complex structure,and alwayssubjects to extreme thermal environment variations.The thermal control system is usually designed to ensure allcomponents of the engine work in an appropriate temperature range.The knowledge of the heat transfercharacteristics of the turbopump-fed rocket engine is crucial to the development of the engine.On the basis ofanalyzing the thermal environment of the engine,the thermal modeling method of the engine is proposed,andthe thermal network method is employed to analyze the thermal environment characteristics of the engine.Theaccuracy of the thermal analysis method is evaluated by a comparison with the thermal balance test of the engine.After verification,the current thermal analysis model is used to analyze the thermal characteristics of the enginein the flight.The thermal analysis method developed in this paper can provide references for a further study ofthe thermal analysis of other turbopump-fed rocket engines.

关 键 词：泵压式发动机 热环境 热分析 

分 类 号：TK124[动力工程及工程热物理—工程热物理]