复合材料层合板下陷区结构设计
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摘要
复合材料层合板下陷是飞机结构中应用广泛的典型结构细节。以下陷长深比、相同方向下陷区间距、两个不同方向下陷区间距为下陷区设计变量,建立参数化有限元模型;通过下陷应力应变分布、初始失效和最终承载能力分析,确定各设计变量对下陷区结构力学性能的影响,并进行参数化设计。分析结果表明:下陷区结构最先发生损伤的部位为下陷区转折处;合理的下陷参数设计变量取值为长深比B/A≥20、主受力方向上两个下陷区间距A/H≥12、不同方向上两个下陷区间距C/A_(min)≥1.5。
Composite laminates with joggles as typical design details are widely used in aircraft structures.The length to depth ratio,the same direction joggle spacing and two different direction joggle spacing are used as design verifications to establish the parametric finite element model. Through stress and strain distribution,previous failure and final loading capacity analysis,the effect of design variables on joggle structures mechanical property is determined and the parametric design is carried out. The results indicate that the structure damage initiates at the transition of joggle;the reasonable design parameters for the joggle are B/A ≥ 20 for length to depth ratio,A/H≥12 for spacing between two joggles in the same direction and C/A_(min)≥ 1.5 for spacing between two joggles in different directions.
Composite laminates with joggles as typical design details are widely used in aircraft structures.The length to depth ratio,the same direction joggle spacing and two different direction joggle spacing are used as design verifications to establish the parametric finite element model. Through stress and strain distribution,previous failure and final loading capacity analysis,the effect of design variables on joggle structures mechanical property is determined and the parametric design is carried out. The results indicate that the structure damage initiates at the transition of joggle;the reasonable design parameters for the joggle are B/A ≥ 20 for length to depth ratio,A/H≥12 for spacing between two joggles in the same direction and C/A_(min)≥ 1.5 for spacing between two joggles in different directions.
引文
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[10] ZHENG R,LIN J,WANG P C,et al. Effect of adhesive characteristics on static strength of adhesive-bonded aluminum alloys[J]. International Journal of Adhesion&Adhesives,2015,57:85-94.
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[12] ELICES M,GUINEA G V,GóMEZ J,et al. The cohesive zone model:Advantages, limitations and challenges[J]. Engineering Fracture Mechanics,2002,69(2):137-163.
[13] CORNEC A,SCHEIDER I,SCHWALBE K H. On the practical application of the cohesive model[J].Engineering Fracture Mechanics,2003,70(14):1963-1987.
[14] YANG Q, COX B. Cohesive models for damage evolution in laminated composites[J]. International Journal of Fracture,2005,133(2):107-137.
[15] CHEN E,LEUNG C K Y. Displacement discontinui-ty method for cohesive crack propagation[J].Engineering Fracture Mechanics,2019,190:319-330.
[2]牛春匀.实用飞机结构应力分析及尺寸设计[M].北京:航空工业出版社,2008.NIU Chunyun. Airframe structural design[M]. Bei-jing:Aviation Industry Press,2008.
[3] BIGWOOD D A, CROCOMBE A D. Nonlinear adhesive bonded joint design analyses[J]. Int J Adhes Adhes 1990,10:31-41.
[4] TAIB A A, BOUKHILI R. Bonded joints with composite adherends. Part I:Effect of specimen configuration, adhesive thickness, spew fillet and adherend stiffness on fracture[J]. International Journal of Adhesion&Adhesives,2006,26:226-236.
[5] HASHIN Z. Fatigue failure criteria for unidirectional fiber composites[J]. Journal of Applied Mechanics,1981,47(4):329-334.
[6] ENGELSTAD S P, EDDY J N, NIGHT N F.Postbuckling response and failure prediction of graphite-epoxy plates loaded in compression[J]. AIAA Journal,2012,30(8):2106-2113.
[7] DUGDALE D S. Yieding of steels containing slits[J].Mech Phys Solids,1960,8:100-104.
[8] BARENBLATT G. The mathematical theory of equilibrium cracks in brittles fracture[J]. Advances in Applied Mechanics,1962,7:55-129.
[9] BLACKMAN B R K,HADAVINIA H,KINLOCH A J,et al. The use of a cohesive zone model to study the fracture of fibre composites and adhesively-bonded joints[J]. International Journal of Fracture,2003,119(1):25-46.
[10] ZHENG R,LIN J,WANG P C,et al. Effect of adhesive characteristics on static strength of adhesive-bonded aluminum alloys[J]. International Journal of Adhesion&Adhesives,2015,57:85-94.
[11] WISNOM M R. Modelling discrete failures in composites with interface elements[J]. Composites Part A:Applied Science&Manufacturing,2010,41(7):795-805.
[12] ELICES M,GUINEA G V,GóMEZ J,et al. The cohesive zone model:Advantages, limitations and challenges[J]. Engineering Fracture Mechanics,2002,69(2):137-163.
[13] CORNEC A,SCHEIDER I,SCHWALBE K H. On the practical application of the cohesive model[J].Engineering Fracture Mechanics,2003,70(14):1963-1987.
[14] YANG Q, COX B. Cohesive models for damage evolution in laminated composites[J]. International Journal of Fracture,2005,133(2):107-137.
[15] CHEN E,LEUNG C K Y. Displacement discontinui-ty method for cohesive crack propagation[J].Engineering Fracture Mechanics,2019,190:319-330.