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Failure modelling of Self piercing rivet

Failure modelling of Self piercing rivet

Failure modelling of Self piercing rivet

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.

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

o Trust - But Verify!
o We believe to be true what we prefer to be true. [Unknown]
o For those who believe, no proof is required; for those who cannot believe, no proof is possible. [variation,Stuart Chase]
o Unfortunately, in science what You 'believe' is irrelevant. ["Orion", Homebuiltairplanes.com forum]

RE: Failure modelling of Self piercing rivet

I agree with Wil, the Bollhoff rivets have not been used in any air structures that I am aware of. You might want to check out some of the SAE papers that have been written about them for automotive use, there may some useful info in them.

RE: Failure modelling of Self piercing rivet

I admit I had to look it up with Google to know what you meant.
I found the company website. And some test results:

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.

No one believes the theory except the one who developed it. Everyone believes the experiment except the one who ran it.

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