[1] 曹旭,廖航,许望晶,等. 充气式减速技术试验器的设计和飞行试验[J]. 载人航天. 2018, 24(6): 802-808.[2] Walther S, Thaeter J, Reimers C, et al. New Space Application Opportunities based on the Inflatable Reentry & Descent Technology (IRDT)[C]. Dayton: AIAA, 2003.[3] Olds A D, Beck R E, Bose D M, et al. IRVE-3 Post-Flight Reconstruction[C]. Daytona Beach: AIAA, 2013.[4] Litton D K, Bose D M, Cheatwood F M, et al. Inflatable Re-entry Vehicle Experiment (IRVE) - 4 Overview[C]. Dublin: AIAA, 2011.[5] Yamada K, Nagata Y, Abe T, et al. Reentry Demonstration of Flare-type Membrane Aeroshell for Atmospheric Entry Vehicle using a Sounding Rocket[C]. Daytona Beach: AIAA, 2013.[6] 常耀予,刘昕,刘飞,等. 美国充气减速飞行器近地轨道飞行试验分析[J]. 中国航天. 2023(5): 67-73.[7] 张思宇,余莉,曹旭,等. 再入返回器极端热载荷预测方法[J]. 航天返回与遥感. 2019, 40(2): 25-32.[8] 高艺航,贺卫亮. 充气式返回舱气动热特性研究[J]. 航天返回与遥感. 2014, 35(4): 17-25.[9] 彭治雨,石义雷,龚红明,等. 高超声速气动热预测技术及发展趋势[J]. 航空学报. 2015, 36(1): 325-345.[10] 粟斯尧,石义雷,森柳,等. 有限催化对返回舱气动热环境影响[J]. 空气动力学学报. 2018, 36(5): 878-884.[11] He Q, Sun S, Cao X, et al. Non-equilibrium modeling on the aerothermodynamic characteristics of hypersonic inflatable reentry vehicle[J]. Aerospace Science and Technology. 2023, 141: 108524.[12] Hollis B R. Surface Heating and Boundary-Layer Transition on a Hypersonic Inflatable Aerodynamic Decelerator[J]. Journal of Spacecraft and Rockets. 2018, 55(4): 856-876.[13]刘宏康,陈坚强,向星皓,等.改进 k?ω?γ转捩模式对不同雷诺数下HIAD的转捩预测[J].航空学报,2023,44(6):126868.[14] Guo J, Lin G, Bu X, et al. Effect of static shape deformation on aerodynamics and aerothermodynamics of hypersonic inflatable aerodynamic decelerator[J]. Acta Astronautica. 2017, 136: 421-433.[15] Mcbride B J, Zehe M J, Gordon S. NASA Glenn Coefficients for Calculating Thermodynamic Properties of Individual Species[R]. Cleveland, OH: Glenn Research Center, 2002.[16] Bokhyun Y, Maurice R. Diffusion effects in hypersonic flows with a ternary mixture[J]. Journal of Mechanical Science and Technology. 1999, 13(5): 432-442.[17] Wilke C R. A Viscosity Equation for Gas Mixtures[J]. The Journal of Chemical Physics. 1950, 18(4): 517-519.[18] Ribeiro V G, Zabadal J G, Monticell C O, et al. Estimating heat transfer coefficients for solid-gas interfaces using the Landau-Teller model[J]. Applied Mathematics and Computation. 2017, 301: 135-139.[19] Park C. On convergence of computation of chemically reacting flows[C]. Reno, NV: AIAA, 1985.[20] Gupta R N, Yos J M, Thompson R A, et al. A review of reaction rates and thermodynamic and transport properties for the 11-species air model for chemical and thermal nonequilibrium calculations to 30000 K[R]. Washington,D.C: NASA Langley Research Center, 1989.[21] Dunn M, Kang S. Theoretical and experimental studies of reentry plasma[R]. Buffalo: Cornell Aeronautical Laboratory, 1973.[22] 丁明松,董维中,高铁锁,等.局部催化特性差异对气动热环境影响的计算分析[J].航空学报,2018,39(3):121588.[23] Muylaert J, Walpot L, Haeuser J, et al. Standard model testing in the European High Enthalpy Facility F4 and extrapolation to flight[C]. Nashville, TN: AIAA, 1992.[24] 杨肖峰,桂业伟,波邱,等. 高焓CO2气流壁面两步催化机制对非平衡气动加热影响的数值模拟[J]. 国防科技大学学报. 2020, 42(1): 108-116.[25] 张翔,阎超,杨威,等. 高超声速飞行器气动热网格依赖性研究[J]. 战术导弹技术. 2016(3): 21-27.[26] Men'Shov I S, Nakamura Y. Numerical simulations and experimental comparisons for high-speed nonequilibrium air fows[J]. Fluid Dynamics Research. 2000, 27(5): 305-334. |