高超声速飞行器机体/推进一体化设计的启示
收稿日期: 2014-06-11
修回日期: 2014-10-08
网络出版日期: 2015-01-24
基金资助
国家级项目
Inspiration of hypersonic vehicle with airframe/propulsion integrated design
Received date: 2014-06-11
Revised date: 2014-10-08
Online published: 2015-01-24
Supported by
National Level Project
机体/推进一体化设计是吸气式高超声速飞行器的关键技术。飞行器的前体和后体既是主要的气动型面,又是发动机进气道的外压缩型面和尾喷管的膨胀型面,一体化设计直接影响飞行器的气动与发动机性能。本文阐述了吸气式高超声速飞行器的主要特点,梳理了飞行器的推阻匹配、升阻比特性、操稳匹配等主要气动设计问题。通过对国外典型高超声速飞行器机体/推进一体化设计技术的综合分析,总结了前体/进气道、后体/尾喷管、边界层强制转捩装置等关键部件的气动设计方法,获得了有意义的启示,可为后续吸气式高超声速技术研究提供重要参考。
关键词： 高超声速飞行器; 机体/推进一体化设计; 前体/进气道; 后体/尾喷管; 强制转捩装置
罗金玲 , 李超 , 徐锦 . 高超声速飞行器机体/推进一体化设计的启示[J]. 航空学报, 2015 , 36(1) : 39 -48 . DOI: 10.7527/S1000-6893.2014.0226
Airframe/propulsion integrated design is the key technology for hypersonic vehicles. The fore-body and the after-body of vehicles are not only aerodynamic surface, but also either the external-compression surface of engine inlet or the expansion surface of rear nozzle. Hence airframe/propulsion integrated design directly affects aerodynamic characteristics and performances of propulsion. In this paper, the main characteristics of hypersonic vehicle is introduced and crucial aerodynamics issues such as thrust matching with drag and lift-to-drag ratio, as well as maneuverability matching with stability etc., are reviewed. Through a comprehensive analysis of airframe/propulsion integrated design techniques, based on foreign typical hypersonic vehicles and aerodynamic design methods of critical components, the fore-body/inlet integration, after-body/nozzle integration and forced boundary-layer transition device etc., are summarized and some valuable inspirations are obtained. The conclusions could provide important references for the investigation of air-breathing hypersonic technology.
[1] Wei Y Y, Liu P, Zhang D Q, et al. Development of foreign hypersonic technology and analysis of flight tests[J]. Winged Missiles Journal, 2010(5): 2-9 (in Chinese). 魏毅寅, 刘鹏, 张冬青, 等.国外高超声速技术发展及飞行试验情况分析[J].飞航导弹, 2010(5): 2-9.
[2] Joyce P J, Pomroy J B. The Hyper-X launch vehicle: challenges and design considerations for hypersonic flight testing, AIAA-2005-3333[R]. Reston: AIAA, 2005.
[3] Hank J M, Murphy J S, Mutzman R C. The X-51A scramjet engine flight demonstration program, AIAA-2008-2540[R]. Reston: AIAA, 2008.
[4] Mutzman R, S Murphy. X-51 development: a chief engineer's perspective[C]//17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston: AIAA, 2011.
[5] Richardson D. Causes sought for X-51A failure[J]. Jane's Missiles & Rockets, 2012.
[6] Jennings G. Waverider set for third hypersonic test-flight[J]. Jane's Missiles & Rockets, 2012.
[7] Richardson D. Fourth X-51A Waverider sustains Mach 5.1 for six minutes[J]. Jane's Missiles & Rockets, 2013.
[8] Luo J L, Xu M, Liu J. Research on lift and drag characteristics for the integrated configuration of hypersonic vehicle[J]. Journal of Astronautics, 2007, 28(6): 1478-1481 (in Chinese). 罗金玲, 徐敏, 刘杰. 一体化外形的高超声速飞行器升阻特性研究[J]. 宇航学报, 2007, 28(6): 1478-1481.
[9] Reubush D E, Nguyen L T, Rausch V L. Review of X-43A return to flight activities and current status, AIAA-2003-7085[R]. Reston: AIAA, 2003.
[10] Heiser W H, Pratt D T. Hypersonic airbreathing propulsion: AIAA education series[M]. Washington, D. C.: AIAA Inc., 1994: 39.
[11] Anderson J D. Hypersonic waveriders:where do we stand, AIAA-1993-0399[R]. Reston: AIAA, 1993.
[12] Berry S, Daryabeigi K. Boundary layer transition on X-43A, AIAA-2008-3736[R]. Reston: AIAA, 2008.
[13] Seddon J, Goldsmith E L. Intake aerodynamics[M]. London: Blackwell Science Ltd., 1985: 5-15.
[14] Engelund W C, Holland S D, Cockrell C E, Jr. Aerodynamic database development for the Hyper-X airframe integrated scramjet propulsion experiments, AIAA-2000-4006 [R]. Reston: AIAA, 2000.
[15] Berry S A, Auslender A H, Dilley A D. Hypersonic boundary-layer trip development for Hyper-X, AIAA-2000-4012[R]. Reston: AIAA, 2000.
[16] Wadhams T P, MacLean M G, Holden M S. A review of transition studies on full-scale flight vehicles at duplicated flight conditions in the LENS tunnels and comparisons with prediction methods and flight measurement, AIAA-2010-1246[R]. Reston: AIAA, 2010.
/
| 〈 |
|
〉 |
CJA