Mode I Crack Propagation Experimental Analysis of Adhesive Bonded Joints Comprising Glass Fibre Composite Material under Impact and Constant Amplitude Fatigue Loading

被引:6
作者
Bautista Villamil, Alirio Andres [1 ]
Casas-Rodriguez, Juan Pablo [1 ]
Porras Holguin, Alicia [2 ]
Silva Barrera, Maribel [3 ]
机构
[1] Univ Ios Andes, Dept Mech Engn, Struct Integr Res Grp, Bogota 111711, Colombia
[2] Univ Ios Andes, Dept Chem & Food Engn, Grp Diseno Productos & Procesos GDPP, Bogota 111711, Colombia
[3] CIPAER Grp, Escuela Postgrad Fuerza Aerea Colombiana EPFAC, Bogota 110111, Dc, Colombia
关键词
adhesive-bonded joints; crack propagation; composite materials; double cantilever beam; impact fatigue; constant amplitude fatigue; SINGLE LAP JOINTS; EPOXY ADHESIVE; THICKNESS; FRACTURE; DELAMINATION; STRENGTH; BEHAVIOR; STANDARD; GROWTH;
D O I
10.3390/ma14164380
中图分类号
O64 [物理化学(理论化学)、化学物理学];
学科分类号
070304 ; 081704 ;
摘要
The T-90 Calima is a low-wing monoplane aircraft. Its structure is mainly composed of different components of composite materials, which are mainly bonded by using adhesive joints of different thicknesses. The T-90 Calima is a trainer aircraft; thus, adverse operating conditions such as hard landings, which cause impact loads, may affect the structural integrity of aircrafts. As a result, in this study, the mode I crack propagation rate of a typical adhesive joint of the aircraft is estimated under impact and constant amplitude fatigue loading. To this end, effects of adhesive thickness on the mechanical performance of the joint under quasistatic loading conditions, impact and constant amplitude fatigue in double cantilever beam (DCB) specimens are experimentally investigated. Cyclic impact is induced using a drop-weight impact testing machine to obtain the crack propagation rate (da/dN) as a function of the maximum strain energy release rate (G(Imax)) diagram; likewise, this diagram is also obtained under constant amplitude fatigue, and both diagrams are compared to determine the effect of each type of loading on the structural integrity of the joint. Results reveal that the crack propagation rate under impact fatigue is three orders of magnitude greater than that under constant amplitude fatigue.
引用
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页数:17
相关论文
共 40 条
[1]  
Abdel Wahab M.M., 2012, ISRN MAT SCI, V2012, P1, DOI DOI 10.5402/2012/746308
[2]   Durability study of adhesive joints used in high-speed crafts manufactured with composite materials subjected to impact fatigue [J].
Alvarado Carvajal, David Ricardo ;
Mejia Correa, Ricardo Alfonso ;
Pablo Casas-Rodriguez, Juan .
ENGINEERING FRACTURE MECHANICS, 2020, 225
[3]  
Arzoumanidis A, 2018, CHALLENGES MECH TIME, V2
[4]   Fatigue Crack Growth in Adhesively Bonded Joints with Intermittent Impacts [J].
Ashcroft, I. A. ;
Casas-Rodriguez, J. P. ;
Silberschmidt, V. V. .
ADVANCES IN FRACTURE AND DAMAGE MECHANICS IX, 2011, 452-453 :5-8
[5]   Mode I fracture of epoxy bonded composite joints - 2. Fatigue loading [J].
Ashcroft, IA ;
Shaw, SJ .
INTERNATIONAL JOURNAL OF ADHESION AND ADHESIVES, 2002, 22 (02) :151-167
[6]   Mixed-mode crack growth in bonded composite joints under standard and impact-fatigue loading [J].
Ashcroft, Ian A. ;
Casas-Rodriguez, Juan Pablo ;
Silberschmidt, Vadim V. .
JOURNAL OF MATERIALS SCIENCE, 2008, 43 (20) :6704-6713
[7]  
Ashcroft IA, 2011, SHOCK VIB, V18, P157, DOI [10.3233/SAV-2010-0607, 10.1155/2011/301761]
[8]  
ASTM International, 2007, D55280107 ASTM INT
[9]  
ASTM International, 2005, D5573992005 ASTM INT
[10]   The Effect of Adhesive Thickness on the Mechanical Behavior of a Structural Polyurethane Adhesive [J].
Banea, M. D. ;
Da Silva, L. F. M. ;
Campilho, R. D. S. G. .
JOURNAL OF ADHESION, 2015, 91 (05) :331-346