V-型皱褶芯材一体化热防护结构等效热传导系数预测
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摘要
皱褶芯材夹层结构经过合理的设计,可作为一体化热防护结构应用于航空航天领域。以V-型皱褶芯材一体化热防护结构作为研究对象,给出了针对V-型皱褶芯材等效热传导系数的修正混合定律,从而建立了结构沿厚度方向的一维等效传热模型。同时,对详细的三维模型进行稳态传热分析,得到了由拉丁超立方抽样方法生成的各个样本点的等效热传导系数,并与采用修正混合定律计算得到的结果进行了对比。最后,在典型再入环境下进行瞬态传热分析,对比了三维模型和一维模型各部分的温度变化。经过修正的混合定律能够较精确地描述等效热传导系数;基于该等效热传导系数的一维模型可有效地预测沿结构厚度方向各点的温度响应。
Folded core sandwich structures can be suitably designed to work as an integrated thermal protection system(ITPS) in aerospace industry. A V-pattern folded core-based ITPS is considered. Effective thermal conductivity through the core thickness is obtained using a modified rule of mixtures, based on which a one-dimensional(1-D) equivalent thermal model is established. In the meantime, steady state analyses of a detailed three-dimensional(3-D) model are conducted to obtain the effective thermal conductivities for samples generated using Latin Hypercube Sampling method, which are then compared with those from the modified rule of mixtures. Afterwards, comparisons are conducted between the 3-D and 1-D thermal models for transient heat transfer analyses under typical re-entry environment. The results show that the modified rule of mixture is fairly accurate compared with the numerical simulation results, and the 1-D thermal model is able to predict the temperature variation with time through the ITPS thickness satisfactorily.
Folded core sandwich structures can be suitably designed to work as an integrated thermal protection system(ITPS) in aerospace industry. A V-pattern folded core-based ITPS is considered. Effective thermal conductivity through the core thickness is obtained using a modified rule of mixtures, based on which a one-dimensional(1-D) equivalent thermal model is established. In the meantime, steady state analyses of a detailed three-dimensional(3-D) model are conducted to obtain the effective thermal conductivities for samples generated using Latin Hypercube Sampling method, which are then compared with those from the modified rule of mixtures. Afterwards, comparisons are conducted between the 3-D and 1-D thermal models for transient heat transfer analyses under typical re-entry environment. The results show that the modified rule of mixture is fairly accurate compared with the numerical simulation results, and the 1-D thermal model is able to predict the temperature variation with time through the ITPS thickness satisfactorily.
引文
[1]Glass D E.Ceramic matrix composite(CMC)thermal protection systems(TPS)and hot structures for hypersonic vehicles[C].Dayton,Ohio:15th AIAA International Space Planes and Hypersonic Systems and Technologies Conferences,2008.
[2]孟松鹤,等.一体化热防护技术现状和发展趋势[J].宇航学报,2013,34(10):1295-1302.Meng Songhe,et al.State-of-arts and trend of integrated thermal protection systems[J].Journal of Astronautics,2013,34(10):1295-1302.
[3]解维华,等.新型一体化热防护系统热力分析与试验研究[J].航空学报,2013,34(09):2169-2176.Xie Weihua,et al.Thermal-mechanical analysis and test study of a new integrated thermal protection system[J].Aeronautica et Astronautica Sinica,2013,34(09):2169-2176.
[4]Bapanapalli S K,et al.Analysis and design of corrugated-core sandwich panels for thermal protection systems of space vehicles[C].Newport,Rhode Island:47th AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics and Materials Conference,2006.
[5]Fischer S.Aluminium foldcores for sandwich structure application:mechanical properties and FE-simulation[J].Thin-Walled Structures,2015(90):31-41.
[6]蔡克乾,靳明山,姜开宇.新型折叠夹芯结构材料研究进展[J].材料导报,2015,29(04):129-133.Cai Keqian,Jin Mingshan,Jiang Kaiyu.Review of progress in materials for sandwich structure with folded Core[J].Materials Review,2015,29(04):129-133.
[7]王志瑾,张辉,徐庆华.铝合金皱褶芯材夹层板当量导热系数[J].南京航空航天大学学报,2008,40(04):507-512.Wang Zhijin,Zhang Hui,Xu Qinghua.Equivalent thermal conductivity coefficient for sandwich plates with folded core[J].Journal of Nanjing University of Aeronautics and Astronautics,2008,40(04):507-512.
[8]周华志,王志瑾.M-型皱褶芯材夹层板吸能性能研究[J].航空学报,2016,37(2):579-587.Zhou Huazhi,Wang Zhijin.Analysis of energy absorption capability of M-type folded core sandwich structure[J].Acta Aeronautica et Astronautica Sinica,2016,37(2):579-587.
[9]Johnson A F.Novel hybrid structural core sandwich materials for aircraft applications[C].Porto,Portugal:11th Euro-Japanese Symposium on Composite Materials,2008.
[10]Heimbs S.Foldcore sandwich structures and their impact behaviour:an overview[M].Netherlands:Springer,2013:491-544.
[11]Martin Jr C J,Max L B.Parametric weight comparison of advanced metallic,ceramic tile,and ceramic blanket thermal protection systems[R].NASA Technical Memorandum,2000,NASA TM-2000-210289.
[12]王志瑾,徐庆华.M-型皱褶芯材弹性常数的细观力学模型[J].南京航空航天大学学报,2004,36(04):449-453.Wang Zhijin,Xu Qinghua.Meso-mechanical model of elastic constants of M-type folded core[J].Journal of Nanjing University of Aeronautics and Astronautics,2004,36(04):449-453.
[13]王志瑾,Khaliulin V,Skripkin E.皱褶结构芯格构型的几何设计方法[J].南京航空航天大学学报,2002,34(1):6-11.Wang Zhijin,Khaliulin V,Skripkin E.Geometry design method of folded structure[J].Journal of Nanjing University of Aeronautics and Astronautics,2002,34(1):6-11.
[14]Xie G,Wang Q,Sunden B,et al.Thermomechanical optimization of lightweight thermal protection system under aerodynamic heating[J].Applied Thermal Engineering,2013,59(1-2):425-434.
[15]Williams S D,Curry D M.Thermal protection materials:thermophysical property data[J].NASA Reference Publication 1289.1992,N93-1876.
[2]孟松鹤,等.一体化热防护技术现状和发展趋势[J].宇航学报,2013,34(10):1295-1302.Meng Songhe,et al.State-of-arts and trend of integrated thermal protection systems[J].Journal of Astronautics,2013,34(10):1295-1302.
[3]解维华,等.新型一体化热防护系统热力分析与试验研究[J].航空学报,2013,34(09):2169-2176.Xie Weihua,et al.Thermal-mechanical analysis and test study of a new integrated thermal protection system[J].Aeronautica et Astronautica Sinica,2013,34(09):2169-2176.
[4]Bapanapalli S K,et al.Analysis and design of corrugated-core sandwich panels for thermal protection systems of space vehicles[C].Newport,Rhode Island:47th AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics and Materials Conference,2006.
[5]Fischer S.Aluminium foldcores for sandwich structure application:mechanical properties and FE-simulation[J].Thin-Walled Structures,2015(90):31-41.
[6]蔡克乾,靳明山,姜开宇.新型折叠夹芯结构材料研究进展[J].材料导报,2015,29(04):129-133.Cai Keqian,Jin Mingshan,Jiang Kaiyu.Review of progress in materials for sandwich structure with folded Core[J].Materials Review,2015,29(04):129-133.
[7]王志瑾,张辉,徐庆华.铝合金皱褶芯材夹层板当量导热系数[J].南京航空航天大学学报,2008,40(04):507-512.Wang Zhijin,Zhang Hui,Xu Qinghua.Equivalent thermal conductivity coefficient for sandwich plates with folded core[J].Journal of Nanjing University of Aeronautics and Astronautics,2008,40(04):507-512.
[8]周华志,王志瑾.M-型皱褶芯材夹层板吸能性能研究[J].航空学报,2016,37(2):579-587.Zhou Huazhi,Wang Zhijin.Analysis of energy absorption capability of M-type folded core sandwich structure[J].Acta Aeronautica et Astronautica Sinica,2016,37(2):579-587.
[9]Johnson A F.Novel hybrid structural core sandwich materials for aircraft applications[C].Porto,Portugal:11th Euro-Japanese Symposium on Composite Materials,2008.
[10]Heimbs S.Foldcore sandwich structures and their impact behaviour:an overview[M].Netherlands:Springer,2013:491-544.
[11]Martin Jr C J,Max L B.Parametric weight comparison of advanced metallic,ceramic tile,and ceramic blanket thermal protection systems[R].NASA Technical Memorandum,2000,NASA TM-2000-210289.
[12]王志瑾,徐庆华.M-型皱褶芯材弹性常数的细观力学模型[J].南京航空航天大学学报,2004,36(04):449-453.Wang Zhijin,Xu Qinghua.Meso-mechanical model of elastic constants of M-type folded core[J].Journal of Nanjing University of Aeronautics and Astronautics,2004,36(04):449-453.
[13]王志瑾,Khaliulin V,Skripkin E.皱褶结构芯格构型的几何设计方法[J].南京航空航天大学学报,2002,34(1):6-11.Wang Zhijin,Khaliulin V,Skripkin E.Geometry design method of folded structure[J].Journal of Nanjing University of Aeronautics and Astronautics,2002,34(1):6-11.
[14]Xie G,Wang Q,Sunden B,et al.Thermomechanical optimization of lightweight thermal protection system under aerodynamic heating[J].Applied Thermal Engineering,2013,59(1-2):425-434.
[15]Williams S D,Curry D M.Thermal protection materials:thermophysical property data[J].NASA Reference Publication 1289.1992,N93-1876.