Development of Hypersonic Inlet-Vehicle Integrative Design Technology
-
摘要: 对高超声速进气道与飞行器一体化设计技术和发展进行了研究，包含轴对称压缩、二维压缩、侧压以及内压缩进气道在高超声速飞行器上的典型布局设计方案.对高超声速可调进气道类型进行了概述，基于轴对称类型调节、二元平面类型调节以及三维内转调节进气道的典型案例给出了其各自的设计特点，并进一步对宽域飞行和组合动力飞行器采用的多通道可调节高超声速进气道研究进展进行了简述，最后分析了高超声速进气道设计须面对和解决的技术难题.Abstract: An overview of hypersonic inlet-vehicle integrative design technology has been studied systematically. The classical inlets of hypersonic vehicle contain different configurations. The hypersonic inlets include axisymmetric inlets, two-dimensional inlets, sidewall compression inlets and inward-turning inlets. The hypersonic variable geometry inlets which include variant types were reviewed. Their respective design features were introduced based on different examples including axisymmetric inlets, two-demensional planar inlets, and three-demensional inward-turing inlets. The multiple-duct variable geometry inlets for wide-range flying vehicles and airbreathing vehicles with combining engines were also summarized. At last, the engineering roadblock and technology method were suggested for hypersonic inlet design.
-
Key words:
- hypersonic /
- scramjet /
- inlet /
- integrative design /
- variable geometry inlet
-
图 11 X-43A带前体转捩装置的进气道模型
Figure 11. X-43A inlet test model with forebody transition trips
图 15 弯曲激波压缩侧压进气道构型
Figure 15. Configuration of curved shock sidewall compression inlet
-
[1] McClinton C R, Randall T. Voland Hyper-X program status[R]. ISABE 2001-1071. [2] Moses P L. X-43C plans and status[R]. AIAA 2003-7084, 2003. [3] Novelli P, Serre L, Koschel W, et al. European efforts towards mastering hypersonic propulsion[R]. AIAA 2003-2604, 2003. [4] 刘桐林. 俄罗斯高超声速技术飞行试验计划(一)~(四)[J]. 飞航导弹, 2000(4): 23-30, 2000(5): 27-30, 39, 2000(6): 17-23, 2000(7): 18-23. [5] Hank J M, Murphy J S, Mutzman R C. The X-51A scramjet engine flight demonstration program[R]. AIAA 2008-2540, 2008. [6] 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. https://www.cnki.com.cn/Article/CJFDTOTAL-FHDD201005000.htm [7] Ferlemann S, McClinton C, Rock K, et al. Hyper-X Mach 7 scramjet design, ground test and flight results[R]. AIAA 2005-3322, 2005. [8] McClinton C, Roudakov A, Semenov V, et al. Comparative flow path analysis and design assessment of an axisymmetric hydrogen fueled scramjet flight test engine at a Mach number of 6.5[R]. AIAA 96-4571, 1996. [9] Voland R T, Auslender A H, Smart M K, et al. CIAM/NASA Mach 6.5 scramjet flight and ground test[R]. AIAA 99-4848, 1999. [10] Rodriguez C G. CFD analysis of the NASA/CIAM scram-jet[R]. AIAA 2002-4128, 2002. [11] Andrews E H, Mackley E A. NASA's hypersonic research engine project: a review[R]. NASA-TM-107759, 1994. [12] Foelsche R O, Leylegian J C, Betti A A, et al. Progress on the development of a freeflight atmospheric scramjet test technique[R]. AIAA 2005-3297, 2005. [13] Thomas S R, Palac D T, Trefny C J, et al. Performance evaluation of the NASA GTX RBCC flowpath[R]. NASA/TM 2001-210953, 2001. [14] DeBonis J R, Trefny C J, Steffen Jr C J. Inlet development for a rocket based combined cycle, single stage to orbit vehicle using computational fluid dynamics[R]. AIAA 99-2239, 1999. [15] Longstaff R, Bond A. The Skylon project[R]. AIAA 2011-2244, 2011. [16] Mehta U B, Aftosmis M J, Bowles J V, et al. Skylon aerodynamics and SABRE plumes[R]. AIAA 2015-3605, 2015. [17] 牛文, 李文杰. Skylon飞行器与SABRE发动机研究[J]. 飞航导弹, 2013(3): 70-75. https://www.cnki.com.cn/Article/CJFDTOTAL-FHDD201303022.htm [18] Smart M K, Hass N E, Paull A. Flight data analysis of the HyShot 2 scramjet flight experiment[J]. AIAA Journal, 2006, 44(10): 2366-2375. doi: 10.2514/1.20661 [19] Boyce R R, Gerard S, Paull A. The HyShot scramjet flight experiment-flight data and CFD calculations com-pared[R]. AIAA 2003-7029, 2003. [20] Huebner L D, Rock K E, Ruf E G, et al. Hyper-X flight engine ground testing for X-43 flight risk reduction[R]. AIAA 2001-1809, 2001. [21] Berry S A, DiFulvio M, Kowalkowski M K. Forced boundary-layer transition on X-43(Hyper-X) in NASA LaRC 31-inch Mach 10 air tunnel[R]. NASA/TM 2000-210315, 2000. [22] Harsha P T, Keel L C. X-43A vehicle design and manufacture[R]. AIAA 2005-3334, 2005. [23] Joyce P J, Pomroy J B, Grindle L. The Hyper-X launch vehicle: challenges and design considerations for hypersonic flight testing[R]. AIAA 2005-3333, 2005. [24] Hank J M, Murphy J S, Mutzman R C. The X-51A scramjet engine flight demonstration program[R]. AIAA 2008-2540, 2008. [25] 孙强, 王健, 马会民. X-51A超燃冲压发动机的研制历程[J]. 飞航导弹, 2011(1): 67-71. https://www.cnki.com.cn/Article/CJFDTOTAL-FHDD201101016.htm [26] Borg M P, Schneider S P, Juliano T J. Effect of freestream noise on roughness-induced transition for the X-51A forebody[R]. AIAA 2008-592, 2008. [27] Corda S, Anderson Jr J D. Viscous optimized hypersonic waveriders designed from axisymmetric flow fields[R]. AIAA 88-0369, 1988. [28] 耿永兵, 刘宏, 丁海河, 等. 轴对称近似等熵压缩流场的乘波前体优化设计[J]. 推进技术, 2006, 27(5): 404-409. doi: 10.3321/j.issn:1001-4055.2006.05.005Geng Y B, Liu H, Ding H H, et al. Optimized design of waverider forebody derived from asymmetric near-isentropic compression flow fields[J]. Journal of Propulsion Technology, 2006, 27(5): 404-409(in Chinese). doi: 10.3321/j.issn:1001-4055.2006.05.005 [29] Haney J W, Beaulieu W D. Waverider inlet integration issues[R]. AIAA 94-0383, 1994. [30] 贺旭照, 倪鸿礼. 密切曲面锥乘波体-设计方法与性能分析[J]. 力学学报, 2011, 43(6): 1077-1082. https://www.cnki.com.cn/Article/CJFDTOTAL-LXXB201106013.htmHe X Z, Ni H L. Osculating curved cone waverider: design methods and performance analysis[J]. Chinese Journal of Theoretical and Applied Mechanics, 2011, 43(6): 1077-1082(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-LXXB201106013.htm [31] Haney J W, Beaulieu W D. Waverider inlet integration issues[R]. AIAA 94-0383, 1994. [32] 吴颖川, 贺元元, 余安远, 等. 展向截断曲面乘波压缩进气道气动布局[J]. 航空动力学报, 2013, 28(7): 1570-1575. https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201307018.htmWu Y C, He Y Y, Yu A Y, et al. Aerodynamic layout of spanwise truncated curved waveri-der compression inlet[J]. Journal of Aerospace Power, 2013, 28(7): 1570-1575(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201307018.htm [33] Eggers T, Novell P, Haupt M. Design studies of the JAPHAR experimental vehicle for dual mode ramjet demonstration[R]. AIAA 2001-1921, 2001. [34] Hohn O, Gülhan A. Experimental investigation on the influence of sidewall compression on the flowfield of a scramjet inlet at Mach 7[R]. AIAA 2011-2350, 2011. [35] 金志光. 超燃冲压发动机高超侧压式进气道设计方法研究[D]. 南京: 南京航空航天大学, 2006. [36] 范晓樯, 李桦, 易仕和, 等. 侧压式进气道与飞行器机体气功一体化设计及实验[J]. 推进技术, 2004, 25(6): 499-502. doi: 10.3321/j.issn:1001-4055.2004.06.005Fan X Q, Li H, Yi S H, et al. Experiment of aerodynamic performance for hypersonic vehicle intergrate with sidewall compression inlet[J]. Journal of Propulsion Technology, 2004, 25(6): 499-502(in Chinese). doi: 10.3321/j.issn:1001-4055.2004.06.005 [37] 张林, 张堃元, 王磊, 等. 高超声速弯曲激波压缩侧压式进气道数值研究[J]. 航空动力学报, 2015, 30(2): 281-288. https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201502004.htmZhang L, Zhang K Y, Wang L, et al. Numerical investigation of hypersonic curved shock sidewall compression inlet[J]. Journal of Aerospace Power, 2015, 30(2): 281-288(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201502004.htm [38] Siebenhaar A, Bulman M J. The strutjet engine-the overlooked option for space launch[R]. AIAA 95-3124, 1995. [39] Holland S D. Internal aerodynamics of a generic three-dimensional scramjet inlet at Mach 10[R]. NASA-TP-3476, 1995. [40] Billig F S, Baurle R A, Tam C J, et al. Design and analysis of streamline traced hypersonic inlets[R]. AIAA 99-4974, 1999. [41] Jacobsen L S, Tam C J, Behdadnia R, et al. Starting and operation of a streamline-traced busemann inlet at Mach 4[R]. AIAA 2006-4508, 2006. [42] Billig F S, Baurle R A, Tam C J, et al. Design and analysis of streamline traced hypersonic inlets[R]. AIAA 99-4974, 1999. [43] Matthews A J, Jones T V. Design and test of a modular waverider hypersonic intake[R]. AIAA 2005-3379, 2005. [44] Smart M K, White J A. Computational investigation of the Performance and back-pressure limits of a hypersonic inlet[R]. AIAA 2002-0508, 2002. [45] 谭慧俊, 黄河峡, 卜焕先, 等. 一种高超声速内转式进气道的内通道设计方法: 中国, CN105205220A[P]. 2015-12-30. [46] 尤延铖, 梁德旺. 基于内乘波概念的三维变截面高超声速进气道[J]. 中国科学E辑: 技术科学, 2009, 39(8): 1483-1494. https://www.cnki.com.cn/Article/CJFDTOTAL-JEXK200908016.htmYou Y C, Liang D W. Design concept of three-dimensional section controllable internal waverider hypersonic inlet[J]. Science in China(Series E: Technological Sciences), 2009, 39(8): 1483-1494(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-JEXK200908016.htm [47] You Y C, Liang D W, Cai K. Numerical research of three-dimensional sections controllable internal waverider hypersonic inlet[R]. AIAA 2008-4708, 2008. [48] Xiao Y B, Yue L J, Chenr L, et al. Iso-contraction-ratio methodology for the design of hypersonic inward turning inlets with shape transition[R]. AIAA 2012-5978, 2012. [49] Walker S H, Rodgers F C, Esposita A L. The hypersonic collaborative Australia/united states experiment (HyCAUSE)[R]. AIAA 2005-3254, 2005. [50] Kothari A P. Designs of and methodology for inward or outward, and partially inward or outward turning flow hypersonic air-breathing and rocket-based-combined-cycle vehicles: US, 6164596[P]. 2000-12-26. [51] Gollan R J, Smart M K. Design of modular shape-transition inlets for a conical hypersonic vehicle[R]. AIAA 2010-940, 2010. [52] Smart M K, Ruf E G. Free-jet testing of a REST scramjet at off-design conditions[R]. AIAA 2006-2955, 2006. [53] 向先宏, 王成鹏, 程克明. 基于类咽式进气道的高超声速飞行器一体化设计[J]. 宇航学报, 2012, 33(1): 19-26. doi: 10.3873/j.issn.1000-1328.2012.01.003Xiang X H, Wang C P, Cheng K M. Integrative design of airbreathing hypersonic vehicle based on sim-jaws inlet[J]. Journal of Astronautics, 2012, 33(1): 19-26(in Chinese). doi: 10.3873/j.issn.1000-1328.2012.01.003 [54] Walker S, Tang M, Morris S, et al. Falcon HTV-3X-A reusable hypersonic test bed[R]. AIAA 2008-2544, 2008. [55] Walker S H, Rodgers F. Falcon hypersonic technology overview[R]. AIAA 2005-3253, 2005. [56] 南向军, 张堃元, 金志光. 乘波前体两侧高超声速内收缩进气道一体化设计[J]. 航空学报, 2012, 33(8): 1417-1426. https://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201208010.htmNan X J, Zhang K Y, Jin Z G. Integrated design of waverider forebody and hypersonic inward turning inlets[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(8): 1417-1426(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201208010.htm [57] Bowcutt K G, Smith T R, Kothari A P, et al. The Hypersonic space and global transportation system: a concept for routine and affordable access to space[R]. AIAA 2011-2295, 2011. [58] 武卉, 牛文. 美国积极发展高超声速武器[J]. 飞航导弹, 2014(8): 6-9. https://www.cnki.com.cn/Article/CJFDTOTAL-FHDD201408004.htm [59] Kojima T, Tanatsugu N, Sato T, et al. Development study on axisymmetric air inlet for ATREX engine[R]. AIAA 2001-1895, 2001. [60] Sawai S, Sato T, Kobayashi H, et al. Flight test plan for ATREX engine development[R]. AIAA 2003-7027, 2003. [61] Kobayashi H, Tanatsugu N, Sato T, et al. Experimental study of multi-row disk inlets for hypersonic air breathing propulsion[R]. AIAA 2004-861, 2004. [62] Siebenhaar A, Bulman M J. Strutjet rocket-based combined-cycle engine[R]. NAS8-40891, 1999. [63] Taguchi H, Futamura H, Shimodaira K, et al. Design study on hypersonic engine components for TBCC space planes[R]. AIAA 2003-7006, 2003. [64] Huebner L D, Rock K E, Ruf E G, et al. Hyper-X flight engine ground testing for X-43 flight risk reduction[R]. AIAA 2001-1809, 2001. [65] Boudreau A H. Status of the air force hytech pro-gram[R]. AIAA 2003-6947, 2003. [66] Serre L, Falempin F. Promethee-the French military hypersonic propulsion program[R]. AIAA 2003-6950, 2003. [67] Albertson C W, Emami S, Trexler C A. Mach 4 test results of a dual-flowpath, turbine based combined cycle inlet[R]. AIAA 2006-8138, 2006. [68] Sanders B W, Weir L J. Aerodynamic design of a dual-flow Mach 7 hypersonic inlet system for a turbine-based combined-cycle hypersonic propulsion system[R]. NASA/CR 2008-215214, 2008. [69] Saunders J D, Stueber T J, Thomas S R, et al. Testing of the NASA Hypersonics project combined cycle engine large scale inlet mode transition experiment (CCE LlMX)[R]. NASA/TM 2012-217217, 2012. [70] Jacobsen L S, Tam C J, Behdadnia R, et al. Starting and operation of a streamline-traced Busemann inlet at Mach 4[R]. AIAA 2006-4508, 2006. [71] Walker S, Tang M, Mamplata C. TBCC propulsion for a Mach 6 hypersonic airplane[R]. AIAA 2009-7238, 2009. [72] Siebenhaar A, Bogar T J. Integration and vehicle performance assessment of the Aerojet "Trijet" combined-cycle engine[R]. AIAA 2009-7420, 2009. [73] Bulman M J, Siebenhaar A. Combined cycle propulsion: Aerojet innovations for practical hypersonic vehicles[R]. AIAA 2011-2397, 2011. [74] 韦宝禧, 凌文辉, 冮强, 等. TRRE发动机关键技术分析及推进性能探索研究[J]. 推进技术, 2017, 38(2): 298-305. https://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201702008.htmWei B X, Ling W H, Gang Q, et al. Analysis of key technologies and propulsion performance research of trre engine[J]. Journal of Propulsion Technology, 2017, 38(2): 298-305(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-TJJS201702008.htm -
下载:
点击查看大图
图(42)
计量
- 文章访问数: 128
- HTML全文浏览量: 28
- PDF下载量: 19
- 被引次数: 0
邮件订阅
RSS