Stress concentration factor in composite structure 1

[VMomo]

Hello,

I'd like to know if anyone has any documentation for stress concentration factors (Kt) in composite structure. More specifically I am looking for concentration factors in the radii of composite structural members.

Is there an industry standard or is the information company specific?

Any help would be greatly appreciated.

 

[Jimneeson]

Most of my composite work, which involves deducing Kt's, is based on in-house practices.

Perhaps this can be of help.

Developing the Reduced stiffness matrix for your laminate, you can apply this in a calc for whitney point stress methods, to arrive at a kt. This is more useful for holes, or damage greater than BVID damage.

 

[SWComposites]

Are you looking for Kt's for a curved laminate (out-of-plane radii) or for an in-plane radii, such as a hole or cutout? Please be more specific regarding your actual geometry.

 

[WKTaylor]

VMomo...

Try this...

Go to:

http://www.directtextbook.com/advanced-search.php

In advanced search "keywords" block, type in:

composites stress concentration

The search should return many book title "hits" of interest to You.

Regards, Wil Taylor

 

[WKTaylor]

Vmomo..

Go to following website for books on this subject...

http://www.directtextbook.com/advanced-search.php

In the "keywords" block enter:

composite stress concentration...

Have fun searching...

Regards, Wil Taylor

 

[aircraftengr]

There's this 'black metal' method which you use a program to make the entire laminate have isolinear properties. Then all you have to do is analyse it using finite element method as if it was a metal with uniform characteristics.

 

[cguay]

The Kt for a hole in a composite laminate is

Kt = 1 + { 2*[(Ex/Ey)0.5-nuxy] + Ex/Gxy }^0.5

 

[cguay]

sorry for the typo

Kt = 1 + { 2*[ (Ex/Ey)^0.5-nuxy] + Ex/Gxy}^0.5