Structural Analysis of Corrugated-Core Sandwich Panels for Lightweight Thermal Protection System

WANG Qi; JI Ting-wu; XIE Gong-nan; ZHANG Wei-hong

doi:10.3879/j.issn.1000-0887.2013.02.007

Volume 34 Issue 2

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WANG Qi, JI Ting-wu, XIE Gong-nan, ZHANG Wei-hong. Structural Analysis of Corrugated-Core Sandwich Panels for Lightweight Thermal Protection System[J]. Applied Mathematics and Mechanics, 2013, 34(2): 172-182. doi: 10.3879/j.issn.1000-0887.2013.02.007

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Structural Analysis of Corrugated-Core Sandwich Panels for Lightweight Thermal Protection System

doi: 10.3879/j.issn.1000-0887.2013.02.007

Engineering Simulation and Aerospace Computing, School of Mechanical Engineering, Northwestern Polytechnical University, Xi’an 710072, P.R.China

Received Date: 2012-12-24
Rev Recd Date: 2012-01-15
Publish Date: 2013-02-15

Abstract

Abstract

Hypersonic aircrafts enter across the atmosphere with high flight speed and over a long period of time, resulting in an intense aerodynamic heating load. Thermal analysis of thermal protection system (TPS) is the base of thermalmechanical coupling analysis; and the characteristics of temperature distribution affect thermal stress of corrugated sandwich structure directly. The analysis process was divided into three steps. The insulation performance of the integrated thermal protection system (ITPS) was analyzed to get the temperature distribution firstly. Then a sequence coupled numerical method was used to simulate the thermomechanical coupling performance of ITPS. Finally the stress field and displacement field of the corrugated sandwich structure unit cell were obtained and results were discussed. The calculation results show that the structure with initial size and constraints only satisfy the use of lowpressure zone, and structure will fail when the pressure is greater than 15 000 Pa.
- thermal protection system,
- thermalmechanical coupling,
- lightweight,
- thermal stress

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References(20)

References

[1]	范绪箕.高速飞行器热结构分析与应用[M].北京: 国防工业出版社, 2009.(FANG Xu-ji. Thermal Structures Analysis and Application of Highspeed Vehicle [M].Beijing: National Defence Industry Press, 2009.(in Chinese))
[2]	杨亚政, 杨嘉陵, 方岱宁.高超声速飞行器热防护材料与结构的研究进展[J].应用数学和力学, 2008, 29(1): 47-56.(YANG Ya-zheng, YANG Jia-ling, FANG Dai-ning.Research progress on the thermal protection materials and structures in hypersonic vehicles[J]. Applied Mathematics and Mechanics(English Edition),2008, 29(1): 51-60.)
[3]	Bapanapalli S K, Martinez O A, Gogu C, Sankar B V, Haftka R T, Blosser M L.Analysis and design of corrugated core sandwich panels for thermal protection systems of space vehicles[C]//47th AIAA/ASME/ASCE/AHS/ASC Structure, Structure Dynamics and Materials Conference .Newport, Rhode Island, Paper, No 20061942, USA, 2006.
[4]	Martinez O A, Sankar B V, Haftka R, Blosser M, Bapanapalli S K.Micromechanical analysis of a composite corrugatedcore sandwich panel for integral thermal protection system[J]. AIAA Journal,2007, 45(9): 2323-2336.
[5]	Martinez O A, Sharma A, Sankar B V, Haftka R T, Blosser M L.Thermal force and moment determination of an integrated thermal protection system[J]. AIAA Journal, 2010, 48(1): 119-128.
[6]	Martinez O, Sankar B, Haftka R, Blosser M L.Two-dimensional orthotropic plate analysis for an integral thermal protection system[J].AIAA Journal,2012, 50(2): 387-398.
[7]	Gogu C, Bapanapalli S K, Haftka R T, Sankar B V.Comparison of materials for an integrated thermal protection system for spacecraft reentry[J]. AIAA J Spacecraft and Rockets,2009, 46(3): 501-513.
[8]	马忠辉.可重复使用运载器热防护系统性能分析研究[D].博士论文.西安: 西北工业大学,2003.(MA Zhong-hui.Reusable launch vehicle thermal protection system performance study[D].Ph D thesis.Xi’an: Northwestern Polytechnical University, 2003.(in Chinese))
[9]	赵剑, 谢宗蕻, 张磊.高温合金热防护系统设计与分析[J].宇航学报, 2008, 29(5): 16771683.(ZHAO Jian, XIE Zong-hong, ZHANG Lei.Design and analysis of super alloy metallic thermal protection system[J]. Journal of Astronautics,2008, 29(5):16771683.(in Chinese))
[10]	刘振祺, 梁伟, 杨嘉陵, 吴大方.MTPS蜂窝夹芯结构传热性能及热应力分析[J].航空学报, 2009, 30(1): 86-91.(LIU Zhen-qi, LIANG Wei, YANG Jia-ling, WU Da-fang.Analysis of thermal and mechanical properties of honeycomb structure of MTPS[J]. Acta Aeronautica et Astronautica Sinica,2009, 30(1):8691.(in Chinese))
[11]	陈立明, 戴政, 谷宇, 方岱宁.轻质多层热防护结构的一体化优化设计研究[J].力学学报, 2011, 43(2): 289-294.(CHEN Li-ming, DAI Zheng, GU Yu, FANG Dai-ning.Integrated optimization design of light-weight multilayer thermal protection structures[J]. Chinese Journal of Theoretical and Applied Mechanics,2011, 43(2): 289-294.(in Chinese))
[12]	李东辉, 夏新林, 艾青.多层高温隔热结构的传热特性[J].宇航材料工艺, 2011(1): 20-23.(LI Dong-hui, XIA Xin-lin, AI Qing.Heat transfer characteristics of high temperature multilayer thermal insulations[J]. Journal of Aerospace Materials and Technology,2011(1): 20-23.(in Chinese))
[13]	周祥发, 冯坚, 肖汉宁, 张长瑞, 姜勇刚.二氧化硅气凝胶隔热复合材料的性能及其瞬态传热模拟[J].国防科技大学学报, 2009, 31(2): 36-40.(ZHOU Xiang-fa, FENG Jian, XIAO Han-ning, ZHANG Chang-rui, JIANG Yong-gang.Performance and heat transfer simulation of silica aerogel composites[J]. Journal of National University of Defense Technology,2009, 31(2): 36-40.(in Chinese))
[14]	孙陈诚, 胡子君, 陈海坤, 王晓婷, 周洁洁.组合结构对多层反射纳米材料高温隔热性能的影响[J].宇航材料工艺, 2011(6): 44-46.(SUN Chen-cheng, HU Zi-jin, CHEN Hai-kun, WANG Xiao-ting, ZHOU Jie-jie.Effects of structure on high temperature insulation performance of multilayered nanoporous materials[J]. Journal of Aerospace Materials and Technology,2011(6): 44-46.(in Chinese))
[15]	Myers D E, Martin C J, Blosser M L.Parametric weight comparison of advanced metallic, ceramic tile, and ceramic blanket thermal protection systems[C]// NASA Technical Memorandum, Langley Research Center,Hampton, Virginia, 2000, NASA/TM2000210289.
[16]	Poteet C C, Abu-Khajeel H, Hsu S-Y.Preliminary thermalmechanical sizing of a metallic thermal protection system[J]. AIAA J Spacecraft and Rockets,2004, 41(2): 173-182.
[17]	杨世铭, 陶文铨.传热学[M].第3版.北京: 高等教育出版社, 1998.(YANG Shi-ming, TAO Wen-quan. Heat Transfer [M].3rd ed.Beijing: Higher Education Press, 1998.(in Chinese))
[18]	马玉娥.可重复使用运载器热防护系统热/力耦合数值计算研究[D].博士论文.西安: 西北工业大学,2005.(MA Yu-e.Study of thermomechanical coupled computation for thermal protection system of reusable launch vehicle[D].Ph D thesis.Xi’an: Northwestern Polytechnical University, 2005.(in Chinese))
[19]	王刚, 朱辉玉, 孙泉华, 樊菁.典型气动布局高超声速飞行的气动数值评估[C]//第三届高超声速科技学术会议, 江苏无锡, 2010.(WANG Gang, ZHU Hui-yu, SUN Quan-hua, FAN Jing.Numerical evaluation of typical hypersonic configurations on aerodynamics during hypersonic flight[C]// Third Hypersonic Technology Conference .Wuxi, Jiangsu, 2010.(in Chinese))
[20]	解维华, 张博明, 杜善义.重复使用飞行器金属热防护系统的有限元分析与设计[J].航空学报, 2006, 27(4): 650-656.(XIE Wei-hua, ZHANG Bo-ming, DU Shan-yi.Analysis and design of metallic thermal protection system for reusable launch vehicle[J]. Acta Aeronautica et Astronautica Sinica,2006, 27(4):650-656.(in Chinese))