基于再入轨迹和气动热环境的返回舱烧蚀研究

doi:10.7527/S1000-6893.2013.0167

Abstract

Abstract:

The ablation of a heat shield subjected to dynamic changes of the surface material depth and temperature can be reasonably predicted in the whole re-entry process. The approach of constructing a dynamic ablation process is presented by combining the reentry trajectory and aerodynamic heat with Newton-Raphson and tridiagonal matrices (TDMA) algorithms. A three degrees of freedom direct and skip re-entry trajectory model is established. The modified Newtonian flow theory,Fay-Riddell and Sutton-Grave theory are adopted to calculate respectively the aerodynamic parameters and stagnation heat flux. A one dimensional nonlinear heat conduction model is employed to simulate the process of thermal protective material ablation. The results of ablation prediction demonstrate that continuous dynamic change of the surface material depth and the temperature can be realized. The proposed method can be applied to more complicated structures of the flight vehicles and the results of it are shown to be reliable and reasonable by comparing them with those of the heat balance integral (HBI) method. This study provides a reference for further optimization of the design of thermal protection systems (TPS).

Key words: crew return vehicle, re-entry, aerodynamic heating, ablation, finite element method

CLC Number:

V411.8

WANG Jun, PEI Hailong, WANG Naizhou. Research on Ablation for Crew Return Vehicle Based on Re-entry Trajectory and Aerodynamic Heating Environment[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(1): 80-89.

References

[1] Greathouse J S, Kirk B S, Lillard R P, et al. Crew exploration vehicle (CEV) crew module shape selection and CEV aeroscience project overview, AIAA-2007-0603[R]. Reston: AIAA, 2007.
[2] Berry S A, Horvath T J, Lillard R P, et al.Aerothermal testing for project orion crew exploration vehicle, AIAA-2009-3842[R]. Reston: AIAA, 2009.
[3] Wu Z Q, Cheng H, Zhang W, et al. Effects of thermal environment on dynamic properties of aerospace vehicle panel structures[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(2): 334-342.(in Chinese) 吴振强, 程昊, 张伟, 等. 热环境对飞行器壁板结构动特性的影响[J]. 航空学报, 2013, 34(2): 334-342.
[4] Robinson J S, Wurster K E, Mills J C. Entry trajectory and aeroheating environment definition for capsule-shaped vehicles[J]. Journal of Spacecraft and Rockets, 2009, 46(1): 74-86.
[5] Engel C D, Praharaj S C. MINIVER upgrade for the AVID system, vol. I: LANMIN user's manual[R]. NASA CR-172212, 1983.
[6] Subrahmanyam P. High-fidelity aerothermal engineering analysis for planetary probes using DOTNET framework and OLAP cubes database[J]. International Journal of Aerospace Engineering, 2009(1): 1-21.
[7] Otero R E, Braun R D. The planetary entry systems synthesis tool: a conceptual design and analysis tool for EDL systems[C]//2010 IEEE Aerospace Conference, 2010: 1-16.
[8] Park C. Stagnation-region heating environment of the Galileo probe[J]. Journal of Thermophysics and Heat Transfer, 2009, 23(3): 417-424.
[9] Anderson J D. Hypersonic and high temperature gas dynamics[M]. New York: McGraw-Hill, 1989: 156-168.
[10] Wright M, Loomis M, Padadopoulos P. Aerothermal analysis of the project fire Ⅱ afterbody flow, AIAA-2001-3065[R]. Reston: AIAA, 2001.
[11] Bertin J J. Hypersonic aerothemodynamics[M]. Washington: AIAA, 1994: 231-267.
[12] Fay J A, Riddell F R. Theory of stagnation point heat transfer in dissociated air[J]. Journal of the Aeronautical Sciences, 1958, 2(25): 73-85.
[13] Milos F S, Chen Y K. Ablation predictions for carbonaceous materials using CEA and JANNAF-based species thermodynamics[C]//42th AIAA Thermophysics Conference, 2011: 3123-3139.
[14] Potts R L. Application of integral methods to ablation charring erosion, a review[J]. Journal of Spacecraft and Rockets, 1995, 32(2): 200-209.
[15] Hu R F, Wu Z N, Qi X, et al. Debris reentry and ablation prediction and ground risk assessment software system[J]. Acta Aeronautica et Astronautica Sinica, 2011, 32(3): 390-399. (in Chinese) 胡锐锋, 吴子牛, 曲溪, 等. 空间碎片再入烧蚀预测与地面安全评估软件系统[J]. 航空学报, 2011, 32(3): 390-399.
[16] Gupta R N, Yos J M, Thompson R A, et al. A review of reaction rates and thermodynamic and transport properties for an 11-species sir model for chemical and thermal non-equilibrium calculations to 300 000 K[R]. NASA RP-1232, 1990.
[17] Park C, Lee S H. Validation of multi-temperature nozzle flow code noznt[R]. AIAA-1993-2862, 1993.
[18] Quinn R D, Gong L. Real time aerodynamic heating and surface temperature calculations for hypersonic flight simulation[R]. NASA TM-4222, 1990.
[19] Spalding D B. Convective mass transfer[M]. New York: McGraw-Hill, 1963: 156-168.
[20] Milos F S, Rassky D J. Review of numerical procedures for computational surface thermochemistry[J]. Journal of Thermophysics and Heat Transfer, 1994, 8(1): 24-34.
[21] Potts R L. On heat integral solutions of carbonaceous ablator response during re-entry, AIAA-1984-1677[R]. Reston: AIAA, 1984.
[22] Arpaci V S. Conduction heat transfer[M]. Palo Alto: Addison-Wesely, 1966: 248-257.

Research on Ablation for Crew Return Vehicle Based on Re-entry Trajectory and Aerodynamic Heating Environment

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Zhiting GAO, Zhuang MA, Yanbo LIU. Effect of CVD-SiC array structure on ablation resistance of ZrB₂/SiC coatings [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(3): 428842-428842.
[2]	Siji WANG, Yuwei ZHANG, Kaiming HUANG, Biao LYU, Haifeng ZHAO, Hu WANG, Mingfu LIAO. An optimization method for helicopter power turbine rotor system based on improved particle swarm optimization algorithm [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(1): 228608-228608.
[3]	Zhifan YE, Jin ZHAO, Zhihui LI, Xiangchun SUN, Dongsheng WEN. Multiscale coupling simulation method for thermal protection material ablation based on thermochemical interfacial reactive model [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S2): 729469-729469.
[4]	Haoyu CHEN, Binwen WANG, Qiaozhi SONG, Xiaodong LI. Thermal flutter ground simulation test [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(8): 227295-227295.
[5]	Shengbo SHI, Bao LEI, Yuntian ZHANG, Li HU, Maoyuan LI, Jun LIANG. Prediction method of ablation and thermal response for a thermal protection coating with silicone rubber [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(23): 428141-428141.
[6]	Zhenyu MA, Xiaolong DENG, Xixiang YANG, Bingjie ZHU. Thermal⁃structure coupling characteristics of flexible envelopes for stratospheric airships at float conditions [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(19): 228337-228337.
[7]	Zhenkang ZHANG, Wanwu XU, Zhiyan LI, Wei YE. Uncertainty quantification analysis of blunt cone radiation equilibrium temperature [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(15): 528673-528673.
[8]	Laixiao LU, Changguan XU, Jianhua LIU, Meizhen QIN, Yingbo LYU, Yuqin YAN. Influence of initial stress state on bilateral rolling process of thin⁃walled part [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(10): 427415-427415.
[9]	Haoge LI, Hua YANG, Yuxin YANG, Weifang CHEN. Refinement optimization design for heat reduction on windward surface of hypersonic lifting body [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(S2): 124-137.
[10]	WU Zhiyuan, YAN Han, WU Linchao, MA Hui, QU Yegao, ZHANG Wenming. Vibration characteristics of rotating cracked-blade-flexible-disk coupling system [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 625442-625442.
[11]	ZHENG Hui, QIU Lei, YUAN Shenfang, YANG Xiaofei, LU Xulong, XUE Zhaopeng. Experimental method of guided wave monitoring for high temperature airflow damage of C/C thermal protection structures [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 225659-225659.
[12]	LIU Zhihui, NIU Junchuan, JIA Ruihao. Energy flow model for high-frequency vibration of beams in thermal-gradient environment [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(5): 425336-425336.
[13]	MU Hongpeng, LIU Zhidong, ZHOU Shuncheng, HAN Yunxiao, QIU Mingbo. Effects of different gap dielectric mode on EDM ablation milling [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(4): 525609-525609.
[14]	WAN Aoshuang, WANG Zhenming, LI Dinghe. Three-scale analysis of woven composite plates based on third-order shear computational continua method [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(12): 226614-226614.
[15]	JIN Yulin, LIU Zhiwen, CHEN Yushu. Fault simulation of blade-casing rubbing for dual-rotor system of aero-engines [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(12): 425072-425072.