高速飞行器新型半主动冷却装置温控机理分析
2024,46(4):29-36
郭庆阳
国防科技大学 空天科学学院, 湖南 长沙 410073，guoqingyang1226@sina.com
马锐
国防科技大学 空天科学学院, 湖南 长沙 410073
李世斌
国防科技大学 空天科学学院, 湖南 长沙 410073
国防科技大学 空天科学学院, 湖南 长沙 410073，guoqingyang1226@sina.com
马锐
国防科技大学 空天科学学院, 湖南 长沙 410073
李世斌
国防科技大学 空天科学学院, 湖南 长沙 410073
摘要：
针对先进飞行器特殊舱段高温构件的热控难题,提出一种新的半主动温控原理,基于该原理设计了一种新型半主动冷却装置,并对其进行了试验研究,分析并对比了不同工况下新型半主动冷却装置的换热性能及温控机理。结果表明,新型半主动冷却装置的热控性能明显更为优异,尤其是充装100%浸润气凝胶的半主动冷却装置,3 000 s时刻热端温度为272 ℃,比被动式换热工况下的温度低102 ℃,峰值效率最高达到68%；冷却装置出口压力越大,冷却工质到达沸点的时间也越长；填充浸润气凝胶能够有效延长冷却工质从吸热到蒸干的时长,质量较其他填充方式也更小。
针对先进飞行器特殊舱段高温构件的热控难题,提出一种新的半主动温控原理,基于该原理设计了一种新型半主动冷却装置,并对其进行了试验研究,分析并对比了不同工况下新型半主动冷却装置的换热性能及温控机理。结果表明,新型半主动冷却装置的热控性能明显更为优异,尤其是充装100%浸润气凝胶的半主动冷却装置,3 000 s时刻热端温度为272 ℃,比被动式换热工况下的温度低102 ℃,峰值效率最高达到68%；冷却装置出口压力越大,冷却工质到达沸点的时间也越长；填充浸润气凝胶能够有效延长冷却工质从吸热到蒸干的时长,质量较其他填充方式也更小。
基金项目：
国家自然科学基金资助项目(12372272)
国家自然科学基金资助项目(12372272)
Analysis of temperature control mechanism of a novel semi-active cooling device for high-speed flight vehicle
GUO Qingyang
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China,guoqingyang1226@sina.com
MA Rui
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
LI Shibin
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China,guoqingyang1226@sina.com
MA Rui
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
LI Shibin
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
Abstract：
Aiming at the thermal control problem of high temperature components in special cabin of advanced aircraft, a new semi-active temperature control principle was proposed. Based on this principle, a new semi-active cooling device was designed and its experimental study was conducted. The heat transfer performance and temperature control mechanism of the new semi-active cooling device under different working conditions were analyzed and compared. The results indicate that the thermal control performance of the new semi-active cooling device is significantly better, especially for the semi-active cooling device filled with 100% infiltrated aerogel, the hot end temperature is 272 ℃ at 3 000 s, which is 102 ℃ lower than that under the passive heat transfer condition, and the peak efficiency is up to 68%. With increasing of the outlet pressure of the cooling device, the time for the coolant to reach the boiling point is longer. Filling infiltration aerogel can effectively extend the duration from heat absorption to evaporation of the coolant, and it is also lighter in weight compared to other filling methods.
Aiming at the thermal control problem of high temperature components in special cabin of advanced aircraft, a new semi-active temperature control principle was proposed. Based on this principle, a new semi-active cooling device was designed and its experimental study was conducted. The heat transfer performance and temperature control mechanism of the new semi-active cooling device under different working conditions were analyzed and compared. The results indicate that the thermal control performance of the new semi-active cooling device is significantly better, especially for the semi-active cooling device filled with 100% infiltrated aerogel, the hot end temperature is 272 ℃ at 3 000 s, which is 102 ℃ lower than that under the passive heat transfer condition, and the peak efficiency is up to 68%. With increasing of the outlet pressure of the cooling device, the time for the coolant to reach the boiling point is longer. Filling infiltration aerogel can effectively extend the duration from heat absorption to evaporation of the coolant, and it is also lighter in weight compared to other filling methods.
收稿日期：
2022-10-13
2022-10-13
