ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Analysis Model and Experimental Study of Bending Behavior of Composite Honeycomb Sandwich Structures with One-side Bonded Repair
Received date: 2012-11-14
Revised date: 2013-03-29
Online published: 2013-04-25
Supported by
National Basic Research Program of China(11072205)
Composite honeycomb sandwich structures are widely used in aircraft control surfaces and various fairing parts as a lightweight structural design, and their bending properties can be integrated to characterize their mechanical properties. In view of this, experimental study and numerical analysis are performed on one-side bonded composite honeycomb sandwich specimens. First, a three-point bending test is carried on damaged composite honeycomb sandwich panels with one-side bonded repair. The failure loads and strength recovery values of the structures are obtained, and the failure mechanism of the two failure modes of core crush and patch debond are analyzed. A trapezoidal constitutive relationship and failure criterion based on the quadratic stress criterion and energy release rate criterion are introduced with Hill failure criterion, Hashin fabric failure criterion and the cohesive element technique, by means of which a three-dimensional finite element analysis model of the repaired structures is established. The bending strength and failure mechanism of one-side bonded honeycomb sandwich structures are predicted and detected with the model. The numerical results show that the patch debond mode can be well simulated with the introduction of the trapezoidal constitutive relationship in the adhesive, and a good agreement is found between the numerical results and the test data, which demonstrated the validity of the proposed model. Then the effect of patch diameter and thickness on the repair is analyzed, which revealed that with the increase of patch diameter and thickness, the loading capacity of the repaired specimens first increased and then decreased.
LI Jianfeng , YAN Ying , LIAO Baohua , MA Jian , ZHANG Taotao , LIU Bo . Analysis Model and Experimental Study of Bending Behavior of Composite Honeycomb Sandwich Structures with One-side Bonded Repair[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013 , 34(8) : 1884 -1891 . DOI: 10.7527/S1000-6893.2013.0213
[1] Du S Y. Advanced composite materials and aerospace engineering. Acta Materiae Compositae Sinica, 2007, 24(1): 1-12. (in Chinese) 杜善义. 先进复合材料与航空航天. 复合材料学报, 2007, 24(1): 1-12.
[2] Chen S J. Composite structures repair guide. Beijing: Aviation Industry Press, 2001: 37-185. (in Chinese) 陈绍杰. 复合材料结构修理指南. 北京: 航空工业出版社, 2001, 37-185.
[3] Chinese Aeronautical Establishment. Composite structures design manual. Beijing: Aviation Industry Press, 2001: 550-569. (in Chinese) 中国航空研究院. 复合材料结构设计手册.北京: 航空工业出版社, 2001: 550-569.
[4] Wang H, Chen X H, Guo X L, et al. Strength investigation of composite honeycomb structures after repair. Acta Aeronautica et Astronautica Sinica, 2001, 22(3): 270-273. (in Chinese) 汪海, 陈秀华, 郭杏林,等. 复合材料蜂窝夹芯结构修理后强度研究. 航空学报, 2001, 22(3): 270-273.
[5] Randolph A O, Clifford M F. A comparative study of finite element models for the bonded repair of composite structures. Journal of Reinforced Plastics and Composites, 2002, 21(4): 311-332.
[6] Henry C H L, Felix B, Olivier D, et al. Strain-based health assessment of bonded composite repairs. Composite Structures, 2006, 76(3): 234-242.
[7] Wang C H, Gunnion A. Design methodology for scarf repairs to composite structures. DSTO-RR-0317, 2006.
[8] Kumar S B, Sridhar I, Sivashanker S, et al. Tensile failure of adhesively bonded CFRP composite scarf joints. Materials Science and Engineering:B, 2006, 132(1-2): 113-120.
[9] Liu X, Wang G P. Progressive failure analysis of bonded composite repairs. Composite Structures, 2007, 81(3): 331-340.
[10] Manabendra D, Erkan O, Erdogan M, et al. Residual strength of sandwich panels with hail damage. Composite Structures, 2009, 88(3): 403-412.
[11] Liao B H. Analysis model and experimental study of repaired aerocraft composite structure. Beijing: School of Aeronautic Science and Engineering,Beihang University, 2010. (in Chinese) 廖宝华. 飞行器复合材料结构修补分析模型与试验研究. 北京: 北京航空航天大学航空科学与工程学院, 2010.
[12] Campilho R D S G, Moura M F S F, Domingues J J M S. Numerical prediction on the tensile residual strength of repaired CFRP under different geometric changes. International Journal of Adhesion & Adhesives, 2009, 29(2):195-205.
[13] Andersson T, Stigh U. The stress-elongation relation for an adhesive layer loaded in peel using equilibrium of energetic forces. International Journal of Solids and Structures, 2004, 41(2): 413-434.
[14] Campilho R D S G, Moura M F S F, Ramantani D A, et al. Tensile behaviour of three-dimensional carbon-epoxy adhesively bonded single- and double-strap repairs. International Journal of Adhesion & Adhesives, 2009, 29(6): 678-686.
[15] MSC Software Corporation. Marc 2011 user documentation volume A: theory and user information. 2011.
[16] Zinoviev P A, Grigoriev S V, Labedeva O V, et al. The strength of multilayered composites under a plane-stress state. Composites Science and Technology, 1998, 58(7): 1209-1223.
[17] Botgetti T A, Hoppel C P R, Harik V M, et al. Predicting the nonlinear response and progressive failure of composite laminates. Composites Science and Technology, 2004, 64(3-4): 329-342.
[18] Puck A, Schümann H. Failure analysis of FRP laminates by means of physically based phenomenological models. Composites Science and Technology, 1998, 58(7): 1045- 1067.
[19] Liu K S, Tsai S W. A progressive quadratic failure criterion for a laminate. Composites Science and Technology, 1998, 58(7): 1023-1032.
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