Failure modelling of Self piercing rivet
Failure modelling of Self piercing rivet
(OP)
I want to model a shear failure of the Lap shear joint which is connected by a self piercing rivet (Top sheet is Steel and Bottom sheet is aluminium joined with high strength steel Böllhoff standard Self piercing rivet). Basically its a crash simulation in Quasi-static loading. So what would be the parameters in have to specify and the what type of a failure model and criteria should be given to model in abaqus 2018 version.
Thanks in advance for reply.
Thanks in advance for reply.
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RE: Failure modelling of Self piercing rivet
The assembly method You described... "high strength steel Böllhoff standard Self piercing rivet"... sounds highly non-standard and would NEVER be used in any aircraft for any structural applications... hence no need for a structural or DADTA analysis.
The 'closest' assembly procedure that sounds vaguely-similar, that I've specified, is 'metal stitching'... and is only used to join very-thin/soft aluminum sheets together for non structural light-weight parts.
There is an 'Engineering Computer Programs Area' forum... might find help there... https://www.eng-tips.com/threadcategory.cfm?lev2=2...
Regards, Wil Taylor
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RE: Failure modelling of Self piercing rivet
RE: Failure modelling of Self piercing rivet
I found the company website. And some test results:
https://www.sciencedirect.com/science/article/pii/...
https://www.sciencedirect.com/science/article/pii/...
Not very inspiring. I can't picture a way to disassemble this joint for repair.
The strength is about 1/2 to 1/4 the strength of a bucked rivet of the same size, and the joint deforms permanently at a tiny fraction of the failure load. So it would only take a small joint load before the parts are permanently warped and won't return to their original shape.
Normal solid buck-driven rivets are very stiff (nearly matching the base materials) and have a linear stress-strain curve up to roughly 75% of their ultimate strength. In aerospace we rely on these facts because we build many structures that are loaded to a fairly high % of their ultimate strength every flight. They must be counted on to withstand peak service loads without permanent deformation.
I don't think these rivets make the cut for aerospace. As the others said, you may find applications in other industries.
FYI, in one of the papers linked above, the quasi-static loading condition you are asking about is modeled using SIMlab.
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