Journal
MATERIALS
Volume 14, Issue 16, Pages -Publisher
MDPI
DOI: 10.3390/ma14164380
Keywords
adhesive-bonded joints; crack propagation; composite materials; double cantilever beam; impact fatigue; constant amplitude fatigue
Categories
Funding
- MINCIENCIAS [995-2017]
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This study experimentally investigated the effects of different adhesive thicknesses on the adhesive joint under impact and constant amplitude fatigue loading, revealing that the crack propagation rate under impact fatigue is three orders of magnitude greater than that under constant amplitude fatigue.
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.
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