基于LNG的高速飞机热管理系统设计建模与分析  

Design simulation of thermal management system for hypersonic aircraft based on liquid natural gas

作　　者：成超乾 于鹏 谢宗齐 李洋[3,7] 焦宗夏 CHENG Chaoqian;YU Peng;XIE Zongqi;LI Yang;JIAO Zongxia(School of Automation Science and Electrical Engineering,Beihang University,Beijing 100191,China;Ningbo Institute of Technology,Beihang University,Ningbo 315800,China;Research Institute for Frontier Science,Beihang University,Beijing 100191,China;Science and Technology on Aircraft Control Laboratory,Beihang University,Beijing 100191,China;Key Laboratory of Advanced Aircraft Utility Systems,Ministry of Industry and Information Technology,Beihang University,Beijing 100191,China;Beijing Aerospace Technology Institute,Beijing 100074,China;Tianmushan Laboratory,Hangzhou 311115,China)

机构地区：[1]北京航空航天大学自动化科学与电气工程学院,北京100191 [2]北京航空航天大学宁波创新研究院,宁波315800 [3]北京航空航天大学前沿科学技术创新研究院,北京100191 [4]北京航空航天大学飞行器控制一体化技术重点实验室,北京100191 [5]北京航空航天大学先进航空机载系统工业和信息化部重点实验室,北京100191 [6]北京空天技术研究所,北京100074 [7]天目山实验室,杭州311115

出　　处：《航空学报》2023年第10期102-116,共15页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(52272409);国家重点实验室基金(JSY6142219202105)。

摘　　要：针对高速飞机长时高速飞行过程中面临的机载热管理系统潜在超温问题,引入消耗性冷源液化天然气(LNG)设计了一种新型的热管理系统架构。面向最高巡航马赫数为7的完整飞行剖面,通过热管理系统动态仿真,对比分析了引入LNG前后,不同初始条件下机载设备、机身结构和发动机滑油冷却系统的温度。结果表明高速飞机通过引入LNG来提升热管理系统性能具有可行性。在未引入LNG并以燃油为主要热沉时,热管理系统在高速段和返航时由于热沉不足导致系统温控能力下降,机载系统可能存在长时间的超温现象。引入LNG后在高速段和返航时解决了超温问题,并得到了不同起飞环境温度下LNG的消耗量及引入LNG后的体积和重量代价,通过数据拟合得到LNG消耗量与起飞环境温度的经验公式,可为同类型系统设计提供了参考。To solve the overheated problem of the airborne Thermal Management System(TMS)on hypersonic air⁃craft.In this paper,when the hypersonic aircraft flies at high speed for a long time,designed a new type of TMS archi⁃tecture by introducing expendable heat sink Liquid Natural Gas(LNG).The maximum cruise speed of the flight profile is set to Mach number 7,the dynamic simulation of the TMS is carried out,analyzed the temperature of equipment,fuselage structure and engine oil when the hypersonic aircraft take off at different temperatures,compared the perfor⁃mance of TMS with and without LNG.The results show that the TMS equipped with LNG is feasible and the perfor⁃mance of TMS has been improved.If the TMS only use fuel and ram air as heat sink,not equipped with LNG,it will be overheated for a long time because the fuel heat sink is insufficient when hypersonic aircraft flies at high speed for a long time or return.After equipped with LNG,the overheated problem was solved.Meanwhile analyzed the consump⁃tion of LNG and the cost of aircraft volume and weight under different take-off temperatures.The empirical formula for LNG and take-off temperature are obtained by data fitting,It can provide a reference for the design of hypersonic air⁃craft’s TMS.

关 键 词：高速飞机 LNG 热管理系统 温控性能 代价评估 

分 类 号：V245[航空宇航科学与技术—飞行器设计]