Effects of adherend thickness and taper on adhesive bond strength measured by portable pull-off tests
Source abstract
Abstract
Abstract Portable pull-off test using the Pneumatic Adhesion Tensile Testing Instrument (PATTI) has been employed to quantify the residual strength of bonded patch repairs on retired aircraft, with a view towards establishing a reliability-based airworthiness certification methodology for bonded repairs of primary structures. The pull-off strength obtained using this field-testing method may be affected by two major factors: the structure's cross-sectional thickness and tapering near repair edges. This paper aims to investigate and quantify the effects of these two parameters on the pull-off strength, through a combination of experimental testing and computational modelling. By subjecting scarf joints of varying angles to tensile loading, film adhesive FM300 was found to obey the modified Drucker–Prager/cap plasticity criterion. With these data as inputs to a finite element model and a failure criterion that defines final fracture as when the maximum strain at a characteristic distance reaches the adhesive's failure strain, strength predictions of PATTI tests were carried out, with results being compared to experimental data. The results show that the modified Drucker–Prager/cap plasticity model gives better prediction than the von Mises yield criterion, with the characteristic distance being determined by an inverse method using test results pertinent to tensile butt joints.
Source: openaire · Quality: candidate unverified · Source record ↗
Research context
OpenAlex topics: Mechanical Behavior of Composites · Fatigue and fracture mechanics · Probabilistic and Robust Engineering Design
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
References (19)
Show source-provided references
1. Residual strength of composite laminates containing scarfed and straight-sided holes10.1016/j.compositesa.2011.08.020 ↗
2. A proposed approach for certification of bonded composite repairs to flight-critical airframe structure
3. Baker A. Structural health monitoring of a bonded composite patch repair on a fatigue-cracked F-111C wing. Defence Science and Technology Organisation. Fishermans Bend, Victoria; 2008.
4. A proposed approach for certification of bonded composite repairs to flight-critical airframe structure10.1007/s10443-010-9161-z ↗
5. Plastic yielding of a film adhesive under multiaxial stresses10.1016/S0143-7496(99)00033-0 ↗
6. Callus PJ, Chang P, Dellios D, Nicholson KJ, Rider A, Stoyanovski I, et al. F-111 Adhesive Bonded Repair Assessment Program (FABRAP)—Phase I Testing, Preliminary Results, Defence Science and Technology Organisation, Fishermans Bend, Victoria; 2011.
7. Effect of off-normal loading on the bond strength measurement of bonded repairs
8. Void minimization in adhesive joints10.1016/0143-7496(89)90107-3 ↗
9. ASTM, Annual Book of ASTM Standards, ASTM D1002 Standard Test Method for Apparent Shear Strength of Single-Lap-Joint Adhesively Bonded Metal Specimens by Tension Loading (Metal-to-Metal), ASTM, 2005.
10. Stress analysis of axisymmetric Butt joints loaded in torsion and tension10.1243/03093247V131001 ↗
11. Elastic analysis of adhesive Butt joints10.1080/00218467608075059 ↗
12. Stress analysis and testing of parallel and tapered adhesive butt joints10.1163/156856193X00772 ↗
13. Inc. A.A.S.M., Aluminum 7075-T6; 7075-T651, 2001.
14. On the use of laminated beams for the determination of pure and mixed-mode fracture properties of structural adhesives10.1080/00218468908030880 ↗
15. Fracture of interface cracks under combined loading10.1016/S0013-7944(96)00111-7 ↗
16. FM300 high-shear strength modified epoxy film adhesive. In: Materials C.E. (editor.), Havre de Grace.
17. Lee · 1995 · 511
18. Compact solutions for the corner singularity in bonded lap joints10.1016/S0143-7496(99)00032-9 ↗
19. Cytec, FM300-2 modified epoxy resin film, Cytec Engineered Materials, Havre de Grace, MD, 1998.