碳纤维织物材料鸟撞动力学分析参数试样级试验与仿真研究
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摘要
根据复合材料鸟撞适航取证要求,制定了积木式复合材料鸟撞符合性验证方法。完成了一种典型碳纤维织物试样级试验,对试验数据研究发现碳纤维织物在45°方向吸能约是0°方向的2倍,可供复材结构抗冲击吸能铺层设计使用。以试样级试验数据为基础通过编程处理得到基于Pam-crash软件鸟撞动力学参数,随后完成了拉压剪三种受载方式的仿真计算,计算结果表明分析和试验结果基本一致。因此,基于试样级试验数据处理得到的参数可用于更高级别的鸟撞动力学仿真模拟,供飞机设计使用。
The building-block compliance verification method of composite structure on bird strike is established according to the requirements of airworthiness. A serial of coupon tests were conducted on carbon composite material,the conclusion is found that two times energy is absorbed by carbon composite in ± 45° direction compared with0° direction,which can be used the composite ply design in energy absorption. The simulation parameters based on Pam-crash software were derived by compiling program with the test original data. A reasonable result is achieved by comparing the simulation with test about tension,compression and shear type. The derived parameters can be used in high level simulation of composite structure for aircraft design.
The building-block compliance verification method of composite structure on bird strike is established according to the requirements of airworthiness. A serial of coupon tests were conducted on carbon composite material,the conclusion is found that two times energy is absorbed by carbon composite in ± 45° direction compared with0° direction,which can be used the composite ply design in energy absorption. The simulation parameters based on Pam-crash software were derived by compiling program with the test original data. A reasonable result is achieved by comparing the simulation with test about tension,compression and shear type. The derived parameters can be used in high level simulation of composite structure for aircraft design.
引文
1杨乃宾,章怡宁.复合材料飞机结构设计[M].北京:航空工业出版社,2002Yang Naibin, Zhang Yining. Composite aircraft structure design[M]. Beijing:Aviation Industry Press,2002
2 U. S. Department of Transportation Federal Aviation Administration.Composite aircraft structure:AC 20-107B[S]. Washington,D. C.:AIR-100,2009
3 Mc Carthy M A,Xiao J R,Petrinic N,et al. Modelling of bird strike on an aircraft wing leading edge made from fibre metal laminates-Part1 :Material modelling[J]. Applied Composite Materials,2004,11(5):295-315
4 Mc Carthy M A,Xiao J R,Mc Carthy C T,et al. Modelling of bird strike on an aircraft wing leading edge made from fibre metal laminates-Part 2:Moddelling of impact with SPH bird model[J]. Applied Composite Materials,2004,11(5):317-340
5 Liu J,Li Y L,Gao X S,et al. Dynamic response of bird strike on aluminum foam-based sandwich panels[J]. International Journal of Crashworthiness,2015,20(4):325-336
6 Reglero J A,Rodriguez-Perez M A,Solorzano E,et al. Aluminum foam as a filler for leading edges:Improvements in the mechanical behavior under bird strike impact tests[J]. Material and Design,2011,32(2):907-910
7 Johnson A F,Holzapfel M. Modelling soft body impact on composite structures[J]. Composite Structures,2001,61(1):103-113
8 Georgiadis S,Gunnion A J,Thomson R S,et al. Bird-strike simulation for certification of the Boeing 787 composite moveable trailing edge[J]. Composite Structures,2008,86(1-3):258-268
9 Smojver I,Ivancevic D. Numerical simulation of bird strike damage prediction in airplane flap structure[J]. Composite Structures,2010,92(9):2016-2026
10 Engineering Systems International. PAM-CRASHTMVPS 2014 solver reference manual[M]. Paris:Engineering Systems International,2014
2 U. S. Department of Transportation Federal Aviation Administration.Composite aircraft structure:AC 20-107B[S]. Washington,D. C.:AIR-100,2009
3 Mc Carthy M A,Xiao J R,Petrinic N,et al. Modelling of bird strike on an aircraft wing leading edge made from fibre metal laminates-Part1 :Material modelling[J]. Applied Composite Materials,2004,11(5):295-315
4 Mc Carthy M A,Xiao J R,Mc Carthy C T,et al. Modelling of bird strike on an aircraft wing leading edge made from fibre metal laminates-Part 2:Moddelling of impact with SPH bird model[J]. Applied Composite Materials,2004,11(5):317-340
5 Liu J,Li Y L,Gao X S,et al. Dynamic response of bird strike on aluminum foam-based sandwich panels[J]. International Journal of Crashworthiness,2015,20(4):325-336
6 Reglero J A,Rodriguez-Perez M A,Solorzano E,et al. Aluminum foam as a filler for leading edges:Improvements in the mechanical behavior under bird strike impact tests[J]. Material and Design,2011,32(2):907-910
7 Johnson A F,Holzapfel M. Modelling soft body impact on composite structures[J]. Composite Structures,2001,61(1):103-113
8 Georgiadis S,Gunnion A J,Thomson R S,et al. Bird-strike simulation for certification of the Boeing 787 composite moveable trailing edge[J]. Composite Structures,2008,86(1-3):258-268
9 Smojver I,Ivancevic D. Numerical simulation of bird strike damage prediction in airplane flap structure[J]. Composite Structures,2010,92(9):2016-2026
10 Engineering Systems International. PAM-CRASHTMVPS 2014 solver reference manual[M]. Paris:Engineering Systems International,2014