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[1]刘海娃.载人飞船连续偏航姿态下轨控机组热控设计[J].火箭推进,2018,44(05):10-15.
　LIU Haiwa.Thermal control design of divert thruster unit in manned spacecraft under continuous yaw attitude[J].Journal of Rocket Propulsion,2018,44(05):10-15.
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载人飞船连续偏航姿态下轨控机组热控设计

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 44 期数: 2018年05期 页码: 10-15 栏目: 研究与设计 出版日期: 2018-10-31
Title:
Thermal control design of divert thruster unit in manned spacecraft under continuous yaw attitude
文章编号:
1672-9374(2018)05-0010-06
作者:
刘海娃1; 2
1.上海空间推进研究所,上海201112；2.上海空间发动机工程技术研究中心,上海201112
Author(s):
LIU Haiwa1; 2
1.Shanghai Institute of Space Propulsion, Shanghai 201112, China；2.Shanghai Engineering Research Center of Space Engine, Shanghai 201112, China
关键词:
载人飞船;  轨控发动机机组;  连续偏航;  热分析;  热控设计
Keywords:
manned spacecraft;  divert thruster unit;  continuous yaw attitude;  thermal analysis;  thermal control design
分类号:
V434-34
文献标志码:
A
摘要:
为保证载人飞船在新的连续偏航姿态下轨控机组的热控状态满足各组件温度指标要求,利用I-deas/TMG软件对连续偏航飞行姿态、原热控状态下的轨控机组进行了高温工况在轨仿真分析,根据分析结果提出了高温工况下热控状态设计改进方案。对改进热控措施后的轨控机组进行多轮高温工况热分析计算和低温工况功率复核。结果表明:新热控措施能够保证轨控机组各组件在工作过程中温度均符合温控指标要求,可开展工程应用。
Abstract:
To meet components temperature requirements of the manned spacecraft divert thruster unit at continuous yaw attitude, original thermal control state on-orbit under high-temperature condition is analyzed through software I-deas/TMG. Thermal control design improvement concept is proposed based on the analysis result. Several rounds of thermal calculation and analysis are conducted for components under high-temperature condition with improved thermal control concept, as well as validation of working power under low-temperature condition. Results show that improved thermal control concept meets the temperature requirements of components of the divert thruster unit under continuous yaw attitude and engineering application is applicable.

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备注/Memo

收稿日期:2018-03-07
基金项目: 上海市科学技术委员会资助课题(13DZ2250600)
作者简介: 刘海娃(1980—),女,高级工程师,研究领域为航天器热控制设计

更新日期/Last Update: 1900-01-01