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清华大学学报(自然科学版)  2023, Vol. 63 Issue (3): 386-393,413    DOI: 10.16511/j.cnki.qhdxxb.2022.26.039
  论文 本期目录 | 过刊浏览 | 高级检索 |
锥形减速结构流场热化学非平衡仿真
刘宇1,2, 赵淼1,2, 张章1,2, 贾贺1,2, 黄伟1,2
1. 北京空间机电研究所, 北京 100094;
2. 中国航天科技集团有限公司 航天进入减速与着陆技术实验室, 北京 100094
Simulation of thermochemical nonequilibrium flow around a conical deceleration structure
LIU Yu1,2, ZHAO Miao1,2, ZHANG Zhang1,2, JIA He1,2, HUANG Wei1,2
1. Beijing Institute of Aerospace Mechanics and Electricity, Beijing 100094, China;
2. Laboratory of Aerospace Entry, Descent, and Landing Technology, China Aerospace Science and Technology Corporation, Beijing 100094, China
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摘要 该文对充气式再入与减速技术(inflatable reentry and descent technology,IRDT)中使用的锥形减速结构流场进行了气动热仿真计算。计算模型基于有限体积法对N-S (Navier-Stokes)方程进行求解,使用非平衡双温度模型计算流场热化学反应。为了验证算法准确性,对钝体标准模型ELECTRE进行仿真计算,计算结果与飞行试验和文献结果基本相符。锥形减速结构仿真工况高度为70 km,来流Ma为13,仿真结果表明:激波后振动温度被激活,并逐渐升高至平动温度,同时空气中离解组元浓度逐渐升高;结构表面热流与压强在驻点附近沿径向快速降低,随后热流呈线性下降,压强近似为常量。对4种不同半锥角的锥形减速结构仿真结果进行了对比,结果显示: 50°、55°和60°半锥角激波位置及表面热流基本相同,65°半锥角激波距离前缘点更远,同时表面热流更低;4种半锥角驻点压强基本相同,外围压强随半锥角增加呈线性增加。仿真结果可为IRDT方案设计提供参考。
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刘宇
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关键词 锥形减速结构充气式减速气动热非平衡反应双温度模型数值仿真    
Abstract:[Objective] The conical deceleration structure is a typical shape in inflatable reentry and descent technology (IRDT). Compared with the traditional rigid deceleration structure, the inflatable deceleration structure represented by alumina fiber has lower heat resistance. Therefore, accurate thermal environment prediction is crucial for designing the IRDT system. Moreover, high pressure deforms the surface of the inflatable structure, so the surface pressure distribution is another issue that needs attention. The surface heat flux and pressure distribution of a conical deceleration structure under thermochemical reaction conditions are analyzed through numerical simulation. At the same time, the influence of different half-cone angles on the surface heat flow and pressure distribution is analyzed.[Methods] The numerical model is based on the integral Navier-Stokes (N-S) equation. The Park85 and the two-temperature nonequilibrium models are used to calculate the thermochemical reaction with a noncatalytic wall condition. The equations are solved using the finite volume method. The lower-upper symmetric Gauss-Seidel method is adopted for iteration. The blunt body standard model ELECTRE is used to validate the numerical model. The calculation case of a conical deceleration structure with a height of 70 km is investigated, and the inlet Mach number is 13. The variations in temperature and chemical component concentration along the stagnation line, as well as heat flow and pressure distributions on the structure surface are studied. In addition, the simulation of four conical deceleration structures with different half-cone angles is carried out to analyze the effect of the half-cone angle on the surface heat flow and pressure.[Results] The simulation results show that 1) the gas translational temperature after the shock wave is approximately 7000 K. Along the stagnation point line, the vibrational temperature gradually increases, and the two temperatures reach equilibrium near the stagnation point and decrease to the wall temperature. 2) The concentration of the N component in the shock layer is low and decreases to 0 at the stagnation point. The O and NO components gradually increase along the stagnation point line and reach the maximum near the stagnation point. 3) The surface heat flow and pressure are the highest at the stagnation point and decrease rapidly along the radial direction near the stagnation point. Then, the heat flow decreases linearly, and the pressure is approximately constant. 4) For different half-cone angle conical deceleration structures, the shock wave positions and surface heat flow distributions of the 50°, 55°, and 60° cases are basically identical. The shock wave position of the 65° case is farther from the leading edge, and the surface heat flux is lower. 5) Finally, the stagnation pressures of the four cases are basically identical, and the peripheral pressures increase linearly with increasing half-cone angle.[Conclusions] The surface heat flow and pressure distributions on the conical deceleration structure can be revealed by the numerical calculation. The change in the half-cone angle significantly impacts the surface heat flow and pressure distributions of the conical deceleration structure.
Key wordsconical deceleration structure    inflatable reentry and descent technology    aerothermodynamics    nonequilibrium reaction    two-tem[KG-*9]perature model    numerical simulation
收稿日期: 2021-12-18      出版日期: 2023-03-04
基金资助:国家自然科学基金资助项目(11602018)
作者简介: 刘宇(1986-),男,工程师。E-mail:413908179@qq.com
引用本文:   
刘宇, 赵淼, 张章, 贾贺, 黄伟. 锥形减速结构流场热化学非平衡仿真[J]. 清华大学学报(自然科学版), 2023, 63(3): 386-393,413.
LIU Yu, ZHAO Miao, ZHANG Zhang, JIA He, HUANG Wei. Simulation of thermochemical nonequilibrium flow around a conical deceleration structure. Journal of Tsinghua University(Science and Technology), 2023, 63(3): 386-393,413.
链接本文:  
http://jst.tsinghuajournals.com/CN/10.16511/j.cnki.qhdxxb.2022.26.039  或          http://jst.tsinghuajournals.com/CN/Y2023/V63/I3/386
  
  
  
  
  
  
  
  
  
  
  
  
  
[1] 黄伟, 曹旭, 张章. 充气式进入减速技术的发展[J]. 航天返回与遥感, 2019, 40(2):14-24. HUANG W, CAO X, ZHANG Z. The development of inflatable entry decelerator technology[J]. Spacecraft Recovery & Remote Sensing, 2019, 40(2):14-24. (in Chinese)
[2] REZA S, HUND R, KUSTAS F, et al. Aerocapture inflatable decelerator (AID) for planetary entry[C]//Proceedings of the 19th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar. Williamsburg, USA:AIAA, 2007:1-18.
[3] 卫剑征, 谭惠丰, 王伟志, 等. 充气式再入减速器研究最新进展[J]. 宇航学报, 2013, 34(7):881-890. WEI J Z, TAN H F, WANG W Z, et al. New trends in inflatable re-entry aeroshell[J]. Journal of Astronautics, 2013, 34(7):881-890. (in Chinese)
[4] WALTHER S, THAETER J, REIMERS C, et al. New space application opportunities based on the inflatable reentry & descent technology (IRDT)[C]//Proceedings of AIAA/ICAS International Air and Space Symposium and Exposition:The Next 100 Years. Dayton, USA:AIAA, 2003:1-7.
[5] OLDS A, BECK R E, BOSE D M, et al. IRVE-3 post-flight reconstruction[C]//Proceedings of AIAA Aerodynamic Decelerator Systems (ADS) Conference. Daytona Beach, USA:AIAA, 2013:1-24.
[6] 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. CAO X, LIAO H, XU W J, et al. Design and flight test of demonstration aircraft with inflatable reentry and descent technology[J]. Manned Spaceflight, 2018, 24(6):802-808. (in Chinese)
[7] 黄明星, 王伟志. 某型充气式再入减速热防护结构优化分析[J]. 航天返回与遥感, 2016, 37(1):22-31. HAUNG M X, WANG W Z. Optimization on a flexible thermal protection structure of inflatable reentry system[J]. Spacecraft Recovery & Remote Sensing, 2016, 37(1):22-31. (in Chinese)
[8] LEE D B, BERTIN J J, GOODRICH W D. Heat-transfer rate and pressure measurements obtained during Apollo orbital entries[R]. Washington DC:National Aeronautics and Space Ministration, 1970.
[9] KIMMEL R L, ADAMCZAK D W, BORG M P, et al. First and fifth hypersonic international flight research experimentation's flight and ground tests[J]. Journal of Spacecraft and Rockets, 2019, 56(2):421-431.
[10] MUYLAERT J, WALPOT L, SPEL M, et al. A review of European code validation studies in high enthalpy flow[C]//Proceedings of the 20th AIAA Advanced Measurement and Ground Testing Technology Conference. Albuquerque, USA:AIAA, 1998:1-15.
[11] MUYLAERT J, WALPOT L, HÄUSER J, et al. Standard model testing in the European High Enthalpy Facility F4 and extrapolation to flight[C]//Proceedings of the 28th Joint Propulsion Conference and Exhibit. Nashville, USA:AIAA, 1992:1-16.
[12] 董维中, 乐嘉陵, 高铁锁. 钝体标模高焓风洞试验和飞行试验相关性的数值分析[J]. 流体力学实验与测量, 2002, 16(2):1-8, 20. DONG W Z, LE J L, GAO T S. Numerical analysis for correlation of standard model testing in high enthalpy facility and flight test[J]. Experiments and Measurements in Fluid Mechanics, 2002, 16(2):1-8, 20. (in Chinese)
[13] HUGHES S, DILLMAN R A, STARR B R, et al. Inflatable re-entry vehicle experiment (IRVE) design overview[C]//Proceedings of the 18th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar. Munich, Germany:AIAA, 2005:1-14.
[14] 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. GAO Y H, HE W L. Research on aerodynamic heating characteristics of inflatable reentry decelerator[J]. Spacecraft Recovery & Remote Sensing, 2014, 35(4):17-25. (in Chinese)
[15] 周印佳, 张志贤, 付新卫, 等. 再入飞行器烧蚀热防护一体化计算方法[J]. 航空学报, 2021, 42(7):124520. ZHOU Y J, ZHANG Z X, FU X W, et al. Integrated computing method for ablative thermal protection system of reentry vehicles[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(7):124520. (in Chinese)
[16] 韩东, 方磊. 基于流线跟踪法的气动热工程计算研究[J]. 航空动力学报, 2009, 24(1):65-69. HAN D, FANG L. Study of aerodynamic heating predictions for hypersonic aircrafts by tracking the surface stream trace[J]. Journal of Aerospace Power, 2009, 24(1):65-69. (in Chinese)
[17] 粟斯尧, 石义雷, 柳森, 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. SU S Y, SHI Y L, LIU S, et al. Finite-rate surface catalysis effects on aero-heating environment of a reentry capsule[J]. Acta Aerodynamica Sinica, 2018, 36(5):878-884. (in Chinese)
[18] KOIKE T, TAKAHASHI Y, OSHIMA N, et al. Aerodynamic heating prediction of flare-type membrane inflatable reentry vehicle from low earth orbit[C]//Proceedings of 2018 AIAA Atmospheric Flight Mechanics Conference. Kissimmee, USA:AIAA, 2018:1-21.
[19] MAZAHERI A. High-energy atmospheric reentry test aerothermodynamic analysis[J]. Journal of Spacecraft and Rockets, 2013, 50(2):270-281.
[20] PALHARINI R C, AZEVEDO J L F, WHITE C. DSMC computations of SARA reentry capsule exposed to weakly ionized gas flow[C]//Proceedings of AIAA Scitech 2019 Forum. San Diego, USA:AIAA, 2019:1-19.
[21] 卞荫贵, 徐立功. 气动热力学[M]. 2版. 合肥:中国科学技术大学出版社, 2011. BIAN Y G, XU L G. Aerothermodynamics[M]. 2nd ed. Hefei:Press of University of Science and Technology of China, 2011. (in Chinese)
[22] PARK C. Assessment of two-temperature kinetic model for ionizing air[C]//Proceedings of the 22nd Thermophysics Conference. Honolulu, USA:AIAA, 1987:1-13.
[23] MCBRIDE B J, ZEHE M J, GORDON S. NASA Glenn coefficients for calculating thermodynamic properties of individual species[R]. Cleveland:Glenn Research Center, 2002.
[24] EHLERS J, GORDON S, HEIMEL S, et al. Thermodynamic properties to 6000K for 210 substances[R]. Cleveland:Lewis Research Center, 1963.
[25] YOON B, RASMUSSEN M L. Diffusion effects in hypersonic flows with a ternary mixture[J]. KSME International Journal, 1999, 13(5):432-442.
[26] WILKE C R. A viscosity equation for gas mixtures[J]. The Journal of Chemical Physics, 1950, 18(4):517-519.
[27] FORD D I, JOHNSON R E. Dependence of rate constants on vibrational temperatures:An arrhenius description[C]//Proceedings of the 26th Aerospace Sciences Meeting. Reno, USA:AIAA, 1988:1-5.
[28] RIBEIRO V G, ZABADAL J G, MONTICELLI 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.
[29] ABU TALIP M S, AKAMINE T, OSANA Y, et al. Cost effective implementation of flux limiter functions using partial reconfiguration[C]//Proceedings of the 8th International Symposium on Applied Reconfigurable Computing. Hong Kong, China:Springer, 2012:215-226.
[30] PARK C. On convergence of computation of chemically reacting flows[C]//Proceedings of the Space Sciences Meeting. Reno, USA:AIAA, 1985:1-17.
[31] PARK C. Review of chemical-kinetic problems of future NASA missions, I:Earth entries[J]. Journal of Thermophysics and Heat Transfer, 1993, 7(3):385-398.
[32] DUNN M G, KANG S. Theoretical and experimental studies of reentry plasmas[R]. Buffalo:Cornell Aeronautical Laboratory, 1973.
[33] 杨建龙, 刘猛, 阿嵘. 高超声速热化学非平衡对气动热环境影响[J]. 北京航空航天大学学报, 2017, 43(10):2063-2072. YANG J L, LIU M, A R. Influence of hypersonic thermo-chemical non-equilibrium on aerodynamic thermal environments[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(10):2063-2072. (in Chinese)
[34] 张敏捷, 向树红. 高超声速三维热化学非平衡流场的数值计算对比研究[J]. 航天器环境工程, 2016, 33(1):35-41. ZHANG M J, XIANG S H. A comparative study of the computation of 3D hypersonic flow in thermochemical nonequilibrium state[J]. Spacecraft Environment Engineering, 2016, 33(1):35-41. (in Chinese)
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