航天飞行器轻质纳米材料高温隔热性能

吴大方; 任浩源; 王峰; 王怀涛

doi:10.7527/S1000-6893.2017.21636

航空学报 >

2018 , Vol. 39 >Issue 4: 221636 - 221636

DOI: https://doi.org/10.7527/S1000-6893.2017.21636

固体力学与飞行器总体设计

航天飞行器轻质纳米材料高温隔热性能

吴大方 ,
任浩源 ,
王峰 ,
王怀涛

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北京航空航天大学, 航空科学与工程学院, 北京 100083

收稿日期: 2017-07-31

修回日期: 2018-01-16

网络出版日期: 2018-01-16

基金资助

国家自然科学基金（11427802）

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High temperature thermal insulation performance of light nanomaterials for aerospace craft

WU Dafang ,
REN Haoyuan ,
WANG Feng ,
WANG Huaitao

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School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China

Received date: 2017-07-31

Revised date: 2018-01-16

Online published: 2018-01-16

Supported by

National Natural Science Foundation of China (11427802)

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摘要

纳米隔热材料是一种新型航天飞行器热防护材料。本文使用自行研制的高速飞行器热试验系统，对Al₂O₃纳米材料的高温隔热性能进行试验研究及数值计算，为高速航天器热防护系统的安全可靠性设计提供重要依据。研究结果表明，厚度仅为10 mm的Al₂O₃纳米材料板，当前表面温度为1 200℃时（1 800 s），前后表面的温度差高达880.9℃，后表面温度降低了73.4%，且隔热性能稳定。另外与某空天飞行器轻质陶瓷材料进行了隔热性能的对比试验，结果显示轻质陶瓷材料板的背壁温度要比Al₂O₃纳米材料板高56%。说明Al₂O₃纳米材料的高温隔热性能非常优异，在航天器和高超声速飞行器热防护中具有重要的应用价值。由扫描电镜（SEM）图像知，当温度超过1 200℃后，Al₂O₃纳米材料颗粒快速聚集生长，颗粒间的空洞尺寸显著增大，材料内部纤维出现熔融现象，裂纹数量增多、深度及宽度显著增大，影响材料表观导热率。另外，当温度高于1 200℃时，纳米材料板边界出现了较大的收缩变形和弯曲变形。基于试验结果可知，Al₂O₃纳米隔热材料应该在小于1 200℃的热环境中使用。

关键词： 纳米材料; 高温; 隔热性能; 航天飞行器; 热防护材料

本文引用格式

吴大方 , 任浩源 , 王峰 , 王怀涛 . 航天飞行器轻质纳米材料高温隔热性能[J]. 航空学报, 2018 , 39(4) : 221636 -221636 . DOI: 10.7527/S1000-6893.2017.21636

Abstract

The thermal insulation nanomaterial is a new thermal protection material with excellent thermal insulation performance for aerospace craft. Using the self-developed transient heating simulation system designed for high-speed aircraft, the high-temperature insulation performance of the Al₂O₃ nanomaterial is investigated with the experimental method and numerical simulation to provide important references for the thermal protection design of aerospace craft. The results show that for the Al₂O₃ nanomaterial plate with thickness of only 10 mm, when the front surface temperature was 1 200 ℃ (1 800 s), the temperature difference between the front and back surfaces was 880.9 ℃, the back surface temperature reduced by 73.4%, and the thermal insulation performance was stable. A comparison between the nanomaterial plate with the lightweight ceramic plate of a space vehicle shows that the temperature on the back surface of the ceramic plate was 56% higher than that of the nanomaterial plate. These results indicate that the Al₂O₃ nanomaterial has excellent thermal insulation performance, and is thus applicable in thermal protection of spacecraft and hypersonic vehicle. When the temperature was over 1 200 ℃, it was observed by Scanning Electron Microscope (SEM) that Al₂O₃ nanometric particles accreted rapidly, and the size of the cavities between particles increase significantly. The fibers inside the material were found melt, and the number, depth and width of cracks on the surface of the plate increased observably. These affected the thermal conductivity of the material surface. In addition, when the temperature was higher than 1 200 ℃, large deformation due to shrinkage and bending appeared on the edges of the nanomaterial plate. Experimental results demonstrate that the Al₂O₃ nanomaterial should be used at the temperature lower than 1 200 ℃.

Key words： nanomaterial; high temperature; thermal insulation performance; aerospace craft; thermal protection material

参考文献

[1] XIE G N, ZHANG R P, MANCA O. Thermal and thermomechanical performances of pyramidal core sandwich panels under aerodynamic heating[J]. Journal of Thermal Science and Engineering Applications, 2017, 9(1):014503.
[2] CHENG H M, XUE H F, HONG C Q, et al. Preparation, mechanical, thermal and ablative properties of lightweight needled carbon fibre felt/phenolic resin aerogel composite with a bird's nest structure[J].Composites Science and Technology, 2017, 140:63-72.
[3] XU Y H, HU X, YANG Y X, et al. Dynamic simulation of insulation material ablation process in solid propellant rocket motor[J]. Journal of Aerospace Engineering, 2015, 28(5):04014118.
[4] CARTA D, CORRIAS A, MOUNTJOY G, et al. Structural study of high porous nanocomposite aerogels[J]. Journal of Non-Crystalline Solids, 2007, 353:1785-1788.
[5] BAILLIS D, COQUARD R, MOURA L M. Heat transfer in cellulose-based aerogels:Analytical modelling and measurements[J]. Energy, 2015, 84:732-744.
[6] 胡子君, 李俊宁, 孙陈诚, 等.纳米超级隔热材料及其最新研究进展[J]. 中国材料进展, 2012, 31(8):25-31. HU Z J, LI J N, SUN C C, et al. Recent developments of nano-superinsulating materials[J]. Materials China, 2012, 31(8):25-31(in Chinese).
[7] FRICKE J, EMMERLING A. Aerogels-recent progress in production technique and novel applications[J]. Journal of Sol-Gel Science and Technology, 1998, 13(1-3):299-303.
[8] YUE C W, FENG J, FENG J Z, et al. Efficient gaseous thermal insulation aerogels from 2-dimension nitrogen-doped graphene sheets[J]. International Journal of Heat and Mass Transfer, 2017, 109:1026-1030.
[9] LIU H, XIA X L, AI Q, et al. Experimental investigations on temperature-dependent effective thermal conductivity of nanoporous silica earogel composite[J]. Experimental Thermal and Fluid Science, 2017, 84:67-77.
[10] HOSEINI A, MCCAGUE C, ANDISHEH-TADBIR M, et al. Aerogel blankets:From mathematical modeling to material characterization and experimental analysis[J]. International Journal of Heat and Mass Transfer, 2016, 93:1124-1131.
[11] HURWITZ F I, GALLAGHER M, OLIN T C, et al. Optimization of alumina and aluminosilicate aerogel structure for high-temperature performance[J]. International Journal of Applied Glass Science, 2014, 5(3):276-286.
[12] BI C, TANG G H, HU Z J. Heat conduction modeling in 3-D ordered structures for prediction of aerogel thermal conductivity[J]. International Journal of Heat and Mass Transfer, 2014, 73:103-109.
[13] BAILLIS D, COQUARD R, MOURA L M. Heat transfer in cellulose-based aerogels:Analytical modelling and measurements[J]. Energy, 2015, 84:732-744.
[14] 杨景兴, 何凤梅, 于帆, 等. SiO₂气凝胶热参数测试及评价[J]. 宇航材料工艺, 2013(2):92-94. YANG J X, HE F M, YU F, et al. Measurement and estimate of thermophysical parameters of SiO₂ aerogel[J]. Aerospace Materials and Technology, 2013(2):92-94(in Chinese).
[15] 周祥发, 冯坚, 肖汉宁, 等. 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 X F, FENG J, XIAO H N, et al. Performance and heat transfer simulation of silica aerogel composites[J]. Journal of National University of Defense of Technology, 2009, 31(2):36-40(in Chinese).
[16] 李翔, 傅波. 高超声速飞行器复杂结构热试验技术[J]. 航空学报, 2016, 37(S1):S73-S79. LI X, FU B. Thermal test technique of complex structure of hypersonic aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(S1):S73-S79(in Chinese).
[17] SWANSON A D, COGHLAN S C, PRATT D M, et al. Hypersonic vehicle thermal structure test challenges:AIAA-2007-1670[R]. Reston, VA:AIAA, 2007.
[18] 谭光辉, 李秋彦, 邓俊. 热环境下结构固有振动特性试验及分析[J]. 航空学报, 2016, 37(S1):S32-S37. TAN G H, LI Q Y, DENG J. Test and analysis of natural modal characteristics of a wing model with thermal effect[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(S1):S32-S37(in Chinese).
[19] SPIVEY N D. High-temperature modal survey of a hot-structure control surface:NASA/TM-2011-215965[R]. Washington, D.C.:NASA, 2011.
[20] 吴大方, 商兰, 高镇同, 等. 1700℃高温、有氧及时变环境下隔热性能试验[J]. 宇航学报, 2015, 36(9):1083-1092. WU D F, SHANG L, GAO Z T, et al. Experimental research on thermal-insulation performance under high-temperature/oxidation and time-varying environment up to 1700℃[J]. Journal of Astronautics, 2015, 36(9):1083-1092(in Chinese).
[21] 吴大方, 潘兵, 高镇同, 等. 超高温、大热流、非线性气动热环境试验模拟及测试技术研究[J]. 实验力学, 2012, 27(3):255-271. WU D F, PAN B, GAO Z T, et al. On the experimental simulation of ultra-high temperature, high heat flux and nolinear aerodynamic heating environment and thermo-machanical testing technique[J]. Journal of Experimental Mechanics, 2012, 27(3):255-271(in Chinese).
[22] 吴大方, 王岳武, 商兰, 等. 1200℃高温环境下板结构热模态试验研究与数值模拟[J]. 航空学报, 2016, 37(6):1861-1875. WU D F, WANG Y W, SHANG L, et al. Test research and numerical simulation on thermal modal of plate structure in 1200℃ high-temperature environments[J]. Acta Aeronautica et Astronantica Sinica, 2016, 37(6):1861-1875(in Chinese).
[23] 吴文军, 胡子君, 李俊宁, 等. Al₂O₃掺杂对SiO₂纳米透波/隔热材料性能的影响[J]. 宇航材料工艺, 2014(1):97-100. WU W J, HU Z J, LI J N, et al. Effect on the properties of SiO₂ nanoporous transparent-wave/heat-insulation materials doped with Al₂O₃[J]. Aerospace Materials and Technology, 2014(1):97-100(in Chinese).
[24] 杨世铭, 陶文铨. 传热学[M]. 北京:高等教育出版社, 2006:33-296. YANG S M, TAO W Q. Heat transfer[M]. Beijing:Higher Education Press, 2006:33-296(in Chinese).

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