高超声速飞行器主动质量引射热防护技术研究进展  

Research progress of thermal protection technique by activemass injection for hypersonic vehicle

作　　者：沈斌贤 曾磊[1] 刘骁[1] 周述光[1] 葛强 SHEN Binxian;ZENG Lei;LIU Xiao;ZHOU Shuguang;GE Qiang(Computational Aerodynamics Institute of China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000

出　　处：《空气动力学学报》2022年第6期1-13,共13页Acta Aerodynamica Sinica

基　　金：国家重点研发计划资助项目(2019YFA0405202);国家数值风洞工程(NNW)。

摘　　要：质量引射式热防护是解决未来长时间高超声速飞行器热防护问题的重要方案之一。本文介绍了发汗冷却、气膜冷却、逆向射流三种典型的主动质量引射热防护技术的作用机理,从冷却剂注入方式、流场特征及冷却效率三个方面比较了三种方案的特点。从应用的角度分析了三种方案现阶段的局限性,介绍了几种能够弥补各自缺陷的组合方案。最后从多场耦合分析方法、引射结构设计及优化、热防护系统的优化及效能评估三个方面对质量引射热防护的进一步发展提出展望。Thermal protection through mass injection is a high-efficiency and active thermal protection technique,which cooling the structure by injecting the stored coolant into the flow-field.The coolant not only absorbs the heats but also effects the flow structure and insulates the heats.The mass injection methods can be used in high heat flux,long-time flying conditions,which is one of the most potential cooling techniques for long-time hypersonic vehicles.The transpiration,film cooling and opposing jet are the typical mass injection techniques for thermal protection of hypersonic vehicles.In this paper,the cooling mechanism of three typical mass injection techniques is introduced.The mode of injection,the characteristics of flow field and the cooling efficiency of three techniques are compared.Therefore,the shortcomings of three techniques are analyzed which prevent them from applying to the vehicles.Several combinational schemes of mass injection techniques for each shortcoming are recommended.Finally,three expectations for further development of the mass injection techniques are proposed.The fluid-thermal-structural coupling method,design and optimization for injection structures and effectiveness evaluation for thermal protection system of the mass injection thermal protection techniques should be developed in future.

关 键 词：热防护 质量引射 发汗冷却 气膜冷却 逆向射流 

分 类 号：V435.14[航空宇航科学与技术—航空宇航推进理论与工程]