[1] Lu FK, Marren DE,Advanced Hypersonic Test Facilities: Progress in Astronautics and Aeronautics[M],Reston, Virginia, American Institute of Aeronautics and Astronautics, Inc., 2002, 198.
[2] Jiang ZL and Chue SM, Theories and Technologies of Hypervelocity Shock Tunnels, Cambridge University Press, United Kingdom, 2023.
[3] 姜宗林, 中国高超风洞的理论创新与工程实践[J], 工程研究 — 跨学科视野中的工程, 2022, 14(6): 469-482.
[4] Kuo YH, Dissociation effects in hypersonic viscous flows[J] , Journal of the Aeronautical Sciences, 1957, 24(5): 345–350.
[5] Anderson J, Hypersonic and High-Temperature Gas Dynamics[M], New York: McGraw-Hill Book Company, 1989.
[6] 郭永怀, 现代空气动力学的问题[M], 郭永怀文集, 北京, 科学出版社, 2009.
[7] Bertin JJ, Cummings RM, Fifty years of hypersonics: where we’ve been, where we’re going[J], Progress in Aerospace Sciences, 2003, 39(6-7):511–536.
[8] Bertin JJ, Cummings RM, Critical hypersonic aerothermodynamic phenomena[J], Annual Review of Fluid Mechanics, 2006, 38(1): 129–157.
[9] Jiang ZL, Yu HR, Theories and technologies for duplicating hypersonic flight conditions for ground testing[J], National Science Review, 2017, 4(3): 290–296.
[10] Jiang ZL, Li J, Hu Z, et al., On theory and methods for advanced detonation-driven hypervelocity shock tunnels[J], National Science Review, 2020, 7(7): 1198–120
[11] Brauckmann GJ, Paulson John WJ, Weilmuenster K J, Experimental and computational analysis of Shuttle Orbiter hypersonic trim anomaly[J], Journal of Spacecraft and Rockets, 1995, 32(5): 758–764.
[12] Peebles C, Road to Mach 10: Lessons Learned from the X-43A Flight Research Program[M], American Institute of Aeronautics and Astronautics, Inc., 2008.
[13] Holden MS, Extension of LENS shock tunnel test time and lower Mach number capability, AIAA SciTech 2015, AIAA 2015-2017.
[14] 姜宗林, 俞鸿儒, 高超声速激波风洞研究进展[J], 力学进展, 2009, 39(6): 766-776.
[15] 姜宗林, 李进平, 胡宗民等, 高超声速飞行复现风洞理论与方法[J], 力学学报, 2018, 50(6): 1283-1291.
[16] 姜宗林, 高超声速高焓风洞试验技术研究进展[J], 空气动力学学报, 2019, 37(3): 347-355.
[17] Stalker RJ, A study of the free-piston shock tunnel, AIAA J 5: 2160-2165, 1967.
[18] Itoh K et al., Improvement of a free piston driver for a high-enthalpy shock tunnel, Shock Waves, 1998, 8: 215-233.
[19] Holden MS, Recent advances in hypersonic test facilities and experimental research, AIAA Paper 93-5005, 1993.
[20] Bird GA, A note on combustion driven tubes,Royal Aircraft Establishment,AGARD Rep. 1957-5, 146
[21] Yu HR, Recent developments in shock tune application, in Takayama eds. Proc of the 1989 National Symp on Shock Wave Phenomena, Sagamihara, Japan, Tohoku Print, Sendai, 1989, 1-9.
[22] 俞鸿儒, 李斌, 陈宏, 激波管氢氧爆轰驱动技术的发展进程[J], 力学进展, 2005, 35(3): 315-322.
[23] Yu HR, Esser B, Lenarts M et al., Gaseous detonation driver for a shock tunnel[J], Shock Waves, 1992, 2(4):245-254.
[24] Chue SM, Tsai CY, Bakos RJ et al., NASA’s HYPULSE facility at GASL - A dual mode, dual driver reflected-shock/expansion tunnel, In: Lu and Marren eds: Advanced Hypersonic Test Facilities, Progress in Astronautics and Aeronautics, Vol. 198, 2002.
[25] Bakos R, Calleja J, Erdos J, et al., An experimental and computational study leading to new test capabilities for the HYPULSE facility with a detonation driver[C], Advanced Measurement and Ground Testing Conference, New Orleans, LA. Reston, Virginia: AIAA, 1996: 2193.
[26] 李进平, 冯珩, 姜宗林, 爆轰驱动激波管缝合激波马赫数计算[J], 空气动力学学报, 2008, 26(3): 291-296.
[27] 姜宗林, 李进平, 赵伟, 长试验时间爆轰驱动激波风洞技术研究[J], 力学学报, 2012, 44(5): 824-831.
[28] Nettleton MA, Gaseous Detonation, Their Nature, effects and Control, Chapman and Hall, London, 1987.
[29] Zel’dovich YB, Distribution of pressure and velocity in detonation products, J of experiments and Theoretical Physics, 1942, 12:389.
[30] Taylor GI, The dynamics of the combustion products behind planar and spherical detonation fronts in explosive, Proc Roy Soc (London), 1950, A200, 235-247.
[31] Coatest PB and Gaydon AD, A simple shock tube with detonation driver gas, Proc Roy Soc (London), 1965, A283, 18-32.
[32] 陈宏, 冯珩, 俞鸿儒, 用于激波管/风洞的双爆轰驱动段[J], 中国科学G辑: 物理学、力学、天文学, 2004, 34(2): 183-191.
[33] Jiang ZL, Zhao W, Wang C, Forward-running detonation drivers for high-enthalpy shock tunnels[J]. AIAA Journal, 2002, 40(10): 2009-2016.
[34] Jiang ZL, Wu B, Gao YL, Development of the detonation-driven expansion tube for orbital speed experiments[J]. Science China Technological Sciences, 2015, 58(4): 695-700.
[35] 高云亮, 赵伟, 姜宗林, 爆轰驱动高焓激波膨胀管性能研究[J], 力学学报, 2008, 40(4): 473-478.
[36] 周凯, 苑朝凯, 胡宗民, JF-16膨胀管流场分析及升级改造[J], 航空学报, 2016, 37(11): 3296-3303.
[37] 周凯, 汪球, 胡宗民, 爆轰驱动膨胀管性能研究[J], 航空学报, 2016, 37(3): 810-816.
[38] Jiang ZL, Hu ZM, Wang YP, Advances in critical technologies for hypersonic and high-enthalpy wind tunnel[J], Chinese Journal of Aeronautics, 2020, 33(12): 3027-3038.
[39] Wang YP and Jiang ZL, Impulse force-measurement system, Shock Waves (2020) 30:603–613
[40] Nie SJ, Wang YP, Jiang ZL, Force measurement using strain-gauge balance in shock tunnel based on deep learning, Chinese Journal of Aeronautics, (2023), 36(8): 43–53.
[41] Meng BQ,Han GL,Luo CT,Jiang ZL,Numerical investigation of the axial impulse load during the startup in the shock tunnel, Aerospace Science and Technology, 2018, 73: 332-342.
[42] Meng BQ,Han GL,Luo CT,Jiang ZL and Zhang DL,Aerodynamic measurement of a large aircraft model in hypersonic flow. Chinese Physics B,2017,26(11):114702.
[43] Han GL, Qi L and Jiang ZL, Analytic investigation on error of heat flux measurement and data processing for large curvature models in hypersonic shock tunnels. Applied Mathematics Letters, 2022(134): 108342.
[44] Qi L, Han GL, Jiang ZL, Optimal design of E-type coaxial thermocouples for transient heat measurements in shock tunnels. Applied Thermal Engineering, 2023, 218: 119388.
[45] Qi L, Han GL, Hu ZM, Wang C and Jiang ZL, Numerical investigations of the lateral heat transfer in coaxial thermocouples. Numerical Heat Transfer, Part A: Applications, 2022, 82(6): 280-298.