基于超燃冲压发动机的HIFiRE项目飞行试验研究进展  

Research progress on flight tests of HIFiRE project based on scramjet

作　　者：邓帆 尘军[3] 谢峰 刘辉[3] DENG Fan;CHEN Jun;XIE Feng;LIU Hui(General Control Department, One Space Science and Technology Corporation Limited, Beijing 100080, China;Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, China Aerospace Science and Technolgy Corporation, Beijing 100076, China;Hypersonic Aerodynamics Research Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China;University Department of Mechanical Engineering of Sheffield, Sheffield S13JD, United Kingdom)

机构地区：[1]北京零壹空间科技有限公司总体控制部,北京100080 [2]谢菲尔德大学机械工程学院 [3]中国航天科技集团有限公司中国运载火箭技术研究院空间物理重点实验室,北京100076 [4]中国空气动力研究与发展中心超高速空气动力研究所,四川绵阳621000

出　　处：《航空动力学报》2018年第3期683-695,共13页Journal of Aerospace Power

基　　金：留学基金委航天国际化创新型人才培养项目(留金法[2015]5138)

摘　　要：飞行器在临近空间内的气动特性及发动机性能一直是各国高超声速项目研究的重点,为探索边界层转捩、激波边界层相互作用以及气动加热效应,美澳牵头于2006年联合启动了HIFiRE项目,采用探空火箭发射进行重点技术验证的模式开展了系列创新性研究。项目重点关注20~38km空域,4~8速域飞行马赫数,试验方案通过单项验证、系统集成的思路逐步深入,将一体化设计的乘波体从无动力滑翔推进到有动力巡航,最终完成带超燃冲压发动机高升阻比飞行器的总体性能测试。研究结果表明:(1)试验飞行器的边界层转捩高度在35~25km;(2)乘波体飞行器在飞行马赫数为7时最大升阻比为5.6;(3)超燃冲压发动机的飞行试验中,在86.2kPa的恒定动压下,飞行马赫数从5.5加速到8.5,试验中发动机实现了从亚燃到超燃的模态转换。The aerodynamic characteristics and engine performance of the vehicle in the nearspace have been the focus of the research on the hypersonic projects in various countries.To explore the boundary layer transition,the shock boundary layer interaction and the aerodynamic heating effect,America and Australia led a project called HIFiRE in 2006 and inves-tigated a series of innovation for this kind of vehicles by using sounding rocket to verify key techniques.Height range 20-38 km and speed range flight Mach number 4-8 were the major concerns.Flight test scheme was arranged with the method of single technology verification and system integration. With the combination of propulsion system,the gliding waverider carried out cruise flight,at last,overall performance of high lift-to-drag ratio vehicle with scramjet was tested at hypersonic speed.The results showed that：（1）the boundary layer transition height of the test vehicle was in the range of 35~25 km;（2）the maximum lift-to-drag ratio of waverider-body vehicle at flight Mach number 7 was 5.6;（3）during the flight test of scramjet,the speed of the vehicle was accelerated from flight Mach number 5.5 to flight Mach number 8.5 at a constant dynamic pressure of 86.2 kPa,and the engine realized mode transition from sub combustion to super combustion.

关 键 词：HIFiRE项目 乘波体 超燃冲压发动机 气动/推进一体化 巡航飞行器 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程] V423.9