This paper discusses the stress analysis of adhesively bonded joints and therefore, by analogy, bonded repairs. Attention is focused on the effects of the rate dependence of structural adhesives and it is shown that the use of rate independent solutions to obtain the adhesive shear stresses and shear strains, cannot be said to be generally conservative.
Hart-SmithL. J., Adhesively bonded double lap joints, NASA Langley Research Center Report NASA CR-112235, January (1973).
3.
BakerA. A. and JonesR., Bonded Repair of Aircraft Structures, Martinus Nijhoff, The Netherlands, (1988).
4.
BartholomeusR. A., PaulJ. J. and RobertsJ. D., Application of bonded composite Repair technology to Civilian Aircraft- 747 Demonstrator Program, Proceedings International Conference on Aircraft Damage Assessment and Repair, ed. by JonesR. and MillerN. J., Published by The Institution of Engineers, Australia ISBN (BOOK) 85825 537 5, July (1991).
5.
JonesR., BridgfordN., MolentL. and WallaceG., Bonded repair of multisite damage, pp 199–213, Structural Integrity of Aging Airplanes, edited by AtluriS. N., SampathS. G. and TongP., Springer Verlag, Berlin/Hieldelberg, (1991).
6.
JonesR., Recent developments in advanced repair technology, Proc. Int. Conf. on Aircraft Damage Assessment and Repair, Melbourne, August 1991, Published by Institution of Engineers Australia, ISBN (BOOK) 85825 5375, July (1991).
7.
JonesR., ChiuW.K. and PaulJ., “Designing for damage tolerant composite joints”, J. Composite Structures, 25 (1993) 201–207.
8.
ChiuW.K., ReesD., ChalkleyP. and JonesR., Designing for damage tolerant repairs, Journal of Composite Structures, 28, 1 (1994) 19–38.
9.
HellerM., WilliamsJ.F., DunnS. and JonesR., Thermo-mechanical analysis of composite specimens, J. Composite Structures11, (1988) 309–324.
10.
MolentL., CallinanR.J. and JonesR., Structural aspects of the design of an all boron epoxy reinforcement for the Fl 1 lC Wing Pivot Fitting: Final Report, ARL, Aircraft Structures Report 436, September (1992).
11.
ChiuW.K., and JonesR., A numerical study of adhesively bonded joints, International Journal of Adhesion and Adhesives, 12, 4 (1992) 219–225.
12.
RamaswamyV. G., A constitutive model for the inelastic multi-axial cyclic response of the nickel based super alloy, Rene 80, NASA CR 3998, July (1986).
13.
SweeneyJ. and WardI.M., A unified model of stress relaxation and creep applied to oriented polyethylene, J. Materials Science, 25 (1990) 697–705.
14.
WatanabeO. and AtluriS.N., Internal time, general internal variable, and multi-yield-surface theories of plasticity and creep: A unification of concepts, Int. J. of Plasticity, 2, (1986) 37–57.
15.
CernockyE. P., Comparison of the unloading and reversed loading behaviour of three visco-plastic constitutive theories, J. Materials Science, 17, 4 (1982) 255–266.
16.
PaulJ., BridgfordN. and StoufferD.C., Progress report on the implementation of a constitutive model into the PAFEC finite element package, ARL Aircraft Structures Technical Memorandum 529, June (1990).
17.
BakerA. A., CallinanR. J., DavisM. J. and JonesR. and WilliamsJ.G., Repair of Mirage HI aircraft using BFRP crack patching technology, Theoretical and Applied Fracture Mechanics, 2, 1 (1984) 1–16.
18.
AtluriS. N. and KathiresanM, Stress analysis of typical flaws in aerospace structural components using 3-D hybrid displacement finite element method, 19the AIAA/ASME Structures, Structural Dynamics and Materials Conference, (1978) 340–350.
19.
RoseL.R.F., A cracked plate repaired by bonded reinforcements, Int. J. Fracture, 18 (1982) 135–144.
20.
JonesR. and CallinanR. J., A design study in crack patching, Aeronautical Research Laboratory Structures Report 376, Defence Science and Technology Organisation, Melbourne, (1979).
21.
HeD.T., WilliamsJ.F. and JonesR., ‘A Summary Program of the Ramaswamy-Stouffer-Bodner Constitutive Model for a One-Dimensional Case’, Internal Report, No. SM/1/92, Department of Mechanical and Manufacturing Engineering, University of Melbourne, (1992).
