国外典型高速/高超声速飞行器及其动力系统技术特点浅析  

Technology characteristics analysis on typical foreign hypersonic aircraft and propulsion system

作　　者：桂丰 李丹 张宇超 钟世林 李茜 GUI Feng;LI Dan;ZHANG Yu-chao;ZHONG Shi-lin;LI Qian(AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China;School of power and energy,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]中国航发四川燃气涡轮研究院,成都610500 [2]西北工业大学动力与能源学院,西安710072

出　　处：《燃气涡轮试验与研究》2022年第4期55-62,共8页Gas Turbine Experiment and Research

基　　金：基础加强计划重大研究(1912项目)。

摘　　要：从飞行器动力技术方面,梳理了国外典型高速/高超声速研发计划的任务剖面等情况,分析了典型高速/高超声速飞行器的飞行包线特点。在此基础上,归纳了高速/超声速飞机的尺寸、质量、发动机性能需求等,分析并得出未来高速/超声速飞机及动力必然朝着大飞机和大推力方向发展,以马赫数3.0+的高速涡轮基与亚燃冲压或双模态冲压发动机的组合形式是较为理想的高速飞行推进模式,研发推力14.71 kN量级及以上的高速涡轮发动机是未来TBCC发动机发展的必然趋势。The flight profiles in the foreign typical hypersonic aircraft development programs were collected and the flight envelope characteristics of hypersonic aircrafts were also analyzed. On this basis,the technology characteristics of hypersonic aircraft and engine were summarized, including geometry,mass, thrust, etc. The development trend was analyzed and concluded that the hypersonic aircraft and engine would be large-weight and high-thrust. And Turbine Based Combined Cycle(TBCC) engine which includes Mach 3.0 high speed turbine engine and ramjet or dual-mode ramjet engine is the ideal power system for hypersonic aircraft. And the development of high speed turbine engine with thrust over 14.71k N is required for TBCC engine in future.

关 键 词：推进系统 高速/高超声速飞行器 飞行剖面 飞行包线 推力需求 技术特点 组合发动机 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]