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山东大学学报 (工学版) ›› 2025, Vol. 55 ›› Issue (6): 100-107.doi: 10.6040/j.issn.1672-3961.0.2024.334

• 能动工程——热管理专题 • 上一篇    

航天器离心增益式渐开线热管设计及试验研究

宋云飞1,张红星1,周宇鹏1,杨昌鹏1,谢永奇2   

  1. 1.航天器热控全国重点实验室(北京空间飞行器总体设计部), 北京 100094;2.北京航空航天大学航空科学与工程学院, 北京 100191
  • 发布日期:2025-12-22
  • 作者简介:宋云飞(1995— ),男,吉林长春人,工程师,硕士,主要研究方向为航天器热设计. E-mail:18001376092@163.com

Design and experimental research of centrifugally-enhanced involute heat pipe for spacecraft

SONG Yunfei1, ZHANG Hongxing1, ZHOU Yupeng1, YANG Changpeng1, XIE Yongqi2   

  1. SONG Yunfei1, ZHANG Hongxing1, ZHOU Yupeng1, YANG Changpeng1, XIE Yongqi2(1. National Key Laboratory of Spacecraft Thermal Control(Beijing Institude of Spacecraft System Engineering), Beijing 100094, China;
    2. School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China
  • Published:2025-12-22

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摘要： 针对环扫式航天器旋转平台大热耗、高热流密度设备的散热路径优化问题,设计一种离心增益式渐开线热管。通过优化热管构型,降低平台快旋对热管启动的影响,利用旋转加速度提升热管的极限传热能力,搭建热管离心试验平台进行传热性能及启动性能验证。试验结果表明,渐开线热管在角速度为0~2.512 rad·s-1时均能正常启动工作,且随角速度增大,热管传热能力由170 W·m提升至421 W·m,热管启动所需功率增加至6.6 W,满足航天器旋转平台高效传热的应用需求,实现紧凑型旋转平台的全域高效散热。

关键词: 环扫式航天器, 角速度, 离心增益, 渐开线热管, 传热能力, 启动性能

Abstract: To address the thermal path optimization for high heat dissipation and high heat flux concentration devices on scanning-mode spacecraft rotating platforms, a centrifugally-enhanced involute heat pipe(CEIhp)was designed. By optimizing the heat pipe configuration, the impact of platform rapid rotation on the startup of the heat pipe was reduced, and the rotational acceleration was leveraged to enhance its maximum heat transfer capacity. A centrifugal test platform was established to validate both thermal transfer and startup performance of the CEIhp. Experimental results demonstrated that the CEIhp could successfully initiate operation across angular velocity of 0-2.512 rad·s-1. The heat transfer capacity of CEIhp increased from 170 W·m to 421 W·m as the angular velocity rose, with the startup power requirement escalating to 6.6 W. This achievement fulfilled the application requirements for efficient heat transfer on scanning-mode spacecraft rotating platforms and enabled full-range efficient thermal dissipation for compact rotating platforms.

Key words: scanning-mode spacecraft, angular velocity, centrifugally-enhanced, involute heat pipe, heat transfer capacity, startup performance

中图分类号: 

  • V444.3
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