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[1]刘海娃.一种姿控动力装置热防护研究[J].火箭推进,2014,40(05):37-43.
　LIU Hai-wa.Investigation of thermal protection for attitude control propulsion device[J].Journal of Rocket Propulsion,2014,40(05):37-43.
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一种姿控动力装置热防护研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 40 期数: 2014年05期 页码: 37-43 栏目: 研究与设计 出版日期: 2014-10-28
Title:
Investigation of thermal protection for attitude control propulsion device
作者:
刘海娃
上海空间推进研究所，上海201112
Author(s):
LIU Hai-wa
Shanghai Institute of Space Propulsion, Shanghai 201112, China
关键词:
防热性能; 试验; 仿真计算
Keywords:
thermal protection function;  experiment;  simulation calculation
分类号:
V434-34
文献标志码:
A
摘要:
酚醛树脂作为一种烧蚀材料，凭借其耐高温的特性应用于航天器防热系统，其防热性能在工程实际中需进行考核。以某航天器一段包覆80纤维布/酚醛树脂的液路管路作为研究对象，以定热流为边界条件，采用仿真计算和热流试验的研究方法对空导管以及注水导管的温度场进行研究：仿真计算得出导管表面平衡温度分布以及导管表面具有代表性某点瞬态温度变化；为验证仿真计算的准确性，进行了热流试验，得出了导管表面以及水中温度测点的瞬态温度变化；根据热流试验的温度结果，分析比对了热流试验对仿真计算的验证情况。研究结果表明：80纤维布/酚醛树脂的防热性能符合温度指标要求；仿真结果和热流试验结果一致度良好，证明了仿真计算的合理性和准确性。
Abstract:
As one of the ablative materials, the phenolic resin is used in some thermal protection systems of space vehicles due to its great thermostability. However, its thermal protection function must be checked in actual engineering. In this paper, taking the liquid pipe with 80-fibre cloth/phenolic resin coating as research object, and the heat flux as thermal boundary condition, simulation calculation and heat flux experiment were adopted to research the temperature field of the empty pipe and the pipe injected with water. The simulation result indicates that the temperature distribution on the pipe surface is balanced and there is transient temperature change at a certain point on the pipe surface under the condition of water filled and empety pipe. To verify the result of simulation, a heat flux experiment was carried out, and the transient temperature change on pipe surface and the detecting point in water is obtained by experiment. The results of heat flux experiment and the simulation calculation was compared. The research results indicate that the 80-fibre cloth/phenolic resin's thermal protection performance can meet the temperature requirement of the attitude control propulsion device. The simulation and experiment results have perfect consistency. The rationality and validity of simulation calculation are demonstrated.

参考文献/References:

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备注/Memo

收稿日期：2014-02-11；修回日期：2014-04-29 基金项目：中国航天科技集团公司支撑项目（2010JY16） 作者简介：刘海娃（1980—），女，硕士，研究领域为航天器热控制技术

更新日期/Last Update: 1900-01-01