固体火箭发动机喉衬用轴编C/C复合材料的细观热结构特性分析
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摘要
为研究固体火箭发动机喉衬用轴编C/C复合材料的细观热结构特性,以组分材料之间界面分析为基础,完成热结构参数的实验测定与基于代表性体积单元的等效热物理参数的预测,得出轴编C/C复合材料的等效热膨胀系数与等效热导率系数。分析表明:基于代表性体积单元程序温度周期性边界条件的应用,可以较精确预测复合材料等效热膨胀系数和等效热传导率;得出了组分材料界面相对等效热结构参数的影响,组分材料界面相采用一定厚度的单元模拟更加接近实验数据;讨论了等效热膨胀系数和等效热导率随编织参数的变化规律。
In order to study thermo-structural characteristics of the four-directional carbon/carbon(C/C)composites on mesoscopic of throat in solid rocket motor,based on the component of interface,the experimental thermophysical properties and prediction of the effective thermophysical properties on the representative volume element were completed. The effective thermal expansion coefficient and the effective thermal conductivity of the 4D C/C composites are obtained. The analysis results show that a procedure for the periodic boundary condition of temperature is realized based on the representative volume element,which can accurately predict the effective thermal expansion coefficient and the effective thermal conductivity of the 4D C/C composites. The influence of the component of interface on the effective thermophysical properties is obtained. The interface is established with a certain thickness more in line with the experimental measurement results. The influence of braiding parameters on the effective thermal expansion coefficient and the effective thermal conductivity are discussed.
In order to study thermo-structural characteristics of the four-directional carbon/carbon(C/C)composites on mesoscopic of throat in solid rocket motor,based on the component of interface,the experimental thermophysical properties and prediction of the effective thermophysical properties on the representative volume element were completed. The effective thermal expansion coefficient and the effective thermal conductivity of the 4D C/C composites are obtained. The analysis results show that a procedure for the periodic boundary condition of temperature is realized based on the representative volume element,which can accurately predict the effective thermal expansion coefficient and the effective thermal conductivity of the 4D C/C composites. The influence of the component of interface on the effective thermophysical properties is obtained. The interface is established with a certain thickness more in line with the experimental measurement results. The influence of braiding parameters on the effective thermal expansion coefficient and the effective thermal conductivity are discussed.
引文
[1]Wajed Zaman,Li Ke-zhi,Li Wei,et al.Flexural Strength and Thermal Expansion of 4D-inplain Carbon/Carbon Composites after Flexural Fatigue Loading[J].New Carbon Materials,2014,29(3):169-175.
[2]陈汝训.固体火箭发动机设计与研究[M].北京:宇航出版社,1991.
[3]汪海滨,李鑫.轴编C/C复合材料喉衬的多尺度烧蚀分析方法[J].固体火箭技术,2017,40(3):295-301.
[4]吴小军,刘博,韩明,等.软硬混编预制体增强沥青基4D-inplain-C/C材料的弯曲行为[J].炭素技术,2014,33(5):34-38.
[5]封伟强.组分材料就位性能分析及其对C/C材料剪切性能的影响[D].哈尔滨:哈尔滨工业大学,2017.
[6]张波,贺平照,肖春,等.径棒法编织C/C复合材料高温拉伸性能研究[J].材料导报,2017,31(5):351-354.
[7]王培吉,范素华.纤维复合材料的热膨胀系数[J].复合材料学报,2002,19(3):124-126
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[10]赵建国,李克智,李贺军,等.炭/炭复合材料热膨胀性能的研究[J].材料热处理学报,2006,27(6):1-4.
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[12]方国才,韩杰才,梁军,等.轴编C/C复合材料组分材料有效性能[J].固体火箭技术,2012,35(5):644-649.
[13]Suresh Kumar,Juhi Kushwaha,Samar Mondal,et al.Fabrication and Ablation Testing of 4D-Inplain C/C Composite at 10MW/m2Heat Flux under a Plasma Arc Heater[J].Materials Science&Engineering,2013,566:102-111.
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[15]Shameel Farhan,Li Ke-zhi,Guo L,et al.Effect of Density and Fibre Orientation on the Ablation Behaviour of Carbon-Carbon Composites[J].New Carbon Materials,2010,25(3):161-167.
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[17]Soydan Ozcan,Jale Tezcan,Peter Filip.Microstructure and Elastic Properties of Individual Components of C/CComposites[J].Carbon,2009,47:3403-3414.
[18]Zhang Wei-hong,Wang Feng-wen,Dai Gao-ming,et al.Topology Optimal Design of Material Microstructures Using Strain Energy-Based Method[J].Chinese Journal of Aeronautics,2007,20(4):320-326.
[19]张芳芳.编织复合材料力学性能及热物理性能预报研究[D].秦皇岛:燕山大学,2014.
[20]李书良,顾靖伟,李国才,等.编织参数对轴编C/C复合材料热膨胀系数的影响[J].固体火箭技术,2012,35(5):670-674.
[21]Li Hong-zhou.Prediction of Effective Thermal Conductivities of Woven Fabric Composites Using Unit Cells at Multiple Length Scales[J].Materials Research Society,2011,26(3):384-394.
[22]钟正祥.陶瓷粘接用硅树脂基胶粘剂的制备及耐高温性能研究[D].哈尔滨:哈尔滨工业大学,2017.
[23]XIA Zi-hui,ZHANG Yun-fa,Fernand Ellyin.A Unified Periodical Boundary Conditions for Representative Volume Elements of Composites and Applications[J].Solid and Structures,2003,40:1907-1921
[24]时圣波.高硅氧/酚醛复合材料的烧蚀机理及热-力学性能研究[D].哈尔滨:哈尔滨工业大学,2013.
[25]Bacon R,倪燕.碳-碳复合材料中基体碳的性能[J].新型炭材料,1990,19(1):39-41.
[26]Rao M V.Effect of Architecture on Mechanical Properties of Carbon/Carbon Composites[J].Composite Structure,2008,83(2):131-142.
[2]陈汝训.固体火箭发动机设计与研究[M].北京:宇航出版社,1991.
[3]汪海滨,李鑫.轴编C/C复合材料喉衬的多尺度烧蚀分析方法[J].固体火箭技术,2017,40(3):295-301.
[4]吴小军,刘博,韩明,等.软硬混编预制体增强沥青基4D-inplain-C/C材料的弯曲行为[J].炭素技术,2014,33(5):34-38.
[5]封伟强.组分材料就位性能分析及其对C/C材料剪切性能的影响[D].哈尔滨:哈尔滨工业大学,2017.
[6]张波,贺平照,肖春,等.径棒法编织C/C复合材料高温拉伸性能研究[J].材料导报,2017,31(5):351-354.
[7]王培吉,范素华.纤维复合材料的热膨胀系数[J].复合材料学报,2002,19(3):124-126
[8]LIU Zheng-guo,ZHANG Hai-guo,LU Zi-xing,et al.Investigation on the Thermal Conductivity of 3-Dimensional and 4-Directional Braided Composites[J].Chinese Journal of Aeronautice,2007,20:327-331.
[9]高亚奇,邹武,程文,等.高密度轴棒法C/C复合材料的热膨胀性能[J].固体火箭技术,2010,33(3):333-335.
[10]赵建国,李克智,李贺军,等.炭/炭复合材料热膨胀性能的研究[J].材料热处理学报,2006,27(6):1-4.
[11]刘亚琴,裘华,郑美雯,等.激光脉冲法测试C/C复合材料比热容的影响因素[J].高科技纤维与应用,2014,39(4):24-26.
[12]方国才,韩杰才,梁军,等.轴编C/C复合材料组分材料有效性能[J].固体火箭技术,2012,35(5):644-649.
[13]Suresh Kumar,Juhi Kushwaha,Samar Mondal,et al.Fabrication and Ablation Testing of 4D-Inplain C/C Composite at 10MW/m2Heat Flux under a Plasma Arc Heater[J].Materials Science&Engineering,2013,566:102-111.
[14]Shameel Farhan,Wang Ru-min,Li Ke-zhi.Directional Thermophysical,Ablative and Compressive Behavior of 3D Carbon/Carbon Composites[J].Ceramics International,2015,41:9763-9769.
[15]Shameel Farhan,Li Ke-zhi,Guo L,et al.Effect of Density and Fibre Orientation on the Ablation Behaviour of Carbon-Carbon Composites[J].New Carbon Materials,2010,25(3):161-167.
[16]Wajed Zaman,Li Kezhi,Sumeera Ikram,et al.Morphology,Thermal Response and Anti-Ablation Performance of 3D-Four Directional Pitch Based Carbon/Carbon Composites[J].Corrosion Science,2012,61:134-142.
[17]Soydan Ozcan,Jale Tezcan,Peter Filip.Microstructure and Elastic Properties of Individual Components of C/CComposites[J].Carbon,2009,47:3403-3414.
[18]Zhang Wei-hong,Wang Feng-wen,Dai Gao-ming,et al.Topology Optimal Design of Material Microstructures Using Strain Energy-Based Method[J].Chinese Journal of Aeronautics,2007,20(4):320-326.
[19]张芳芳.编织复合材料力学性能及热物理性能预报研究[D].秦皇岛:燕山大学,2014.
[20]李书良,顾靖伟,李国才,等.编织参数对轴编C/C复合材料热膨胀系数的影响[J].固体火箭技术,2012,35(5):670-674.
[21]Li Hong-zhou.Prediction of Effective Thermal Conductivities of Woven Fabric Composites Using Unit Cells at Multiple Length Scales[J].Materials Research Society,2011,26(3):384-394.
[22]钟正祥.陶瓷粘接用硅树脂基胶粘剂的制备及耐高温性能研究[D].哈尔滨:哈尔滨工业大学,2017.
[23]XIA Zi-hui,ZHANG Yun-fa,Fernand Ellyin.A Unified Periodical Boundary Conditions for Representative Volume Elements of Composites and Applications[J].Solid and Structures,2003,40:1907-1921
[24]时圣波.高硅氧/酚醛复合材料的烧蚀机理及热-力学性能研究[D].哈尔滨:哈尔滨工业大学,2013.
[25]Bacon R,倪燕.碳-碳复合材料中基体碳的性能[J].新型炭材料,1990,19(1):39-41.
[26]Rao M V.Effect of Architecture on Mechanical Properties of Carbon/Carbon Composites[J].Composite Structure,2008,83(2):131-142.