Dear Ahmad,

In some of the following works, you can find a solution to your question:

Conference Paper Investigation on repairs of aircraft composite structures ma...

Article On the static strength of aluminium and carbon fibre aircraf...

Poster Comparison of the performance of aircraft repair patches con...

Article Comparison of fatigue crack growth of riveted and bonded air...

In some of these investigations, we did numerical models of composite laminates and joints with composite substrates and doublers, joined by adhesive bonding, and we needed information like the information you need, so you could see there how we solved these type of issues.

Siddharth Pitta is at present day finishing his PhD and another article is under review, where we have more information that would be interesting to you but that we might be able to share but through a message.

Best regards,

Jose

https://www.sciencedirect.com/search?qs=identify%20Carbon%20fiber%20reinforced%20plastic&show=25&sortBy=relevance&origin=home&zone=qSearch

Article Influence of Curing on the Mechanical Performance of FRP Laminates

you can check this article

For simple equations, you may want to find that old paper from NASA:

CHAMIS; Simplified Composite Micromechanics Equations for Strength, Fracture Toughness, Impact Resistance and Environmental Effects (1984)

An easy assumption is that through thickness (TT) properties are close to transverse properties of UD material. As most theoretical values are approximate at best, this may be sufficient. It is always better to characterize the material if possible, but it is quite a job for composites.

Be aware that ASTM D3518 is not considered very reliable for strength, although it is ok for stiffness. You may want to look for the Iosipescu test method (ASTM D5379 and D7078) for transverse and TT shear modulus. I think the more recent D7078 is preferred for complex laminates, but the first may be better for TT properties.

Best regards,

Thank you very much for the suggestions and shared idea. I really appreciate it.

Dear Ahmad,

If you are also interested in the quantification of uncertainty in the material properties of CFRP, you can check the attached paper and the references therein (see in particular Table 1 for material property identification).

Experimental definition of the module of interlayered shift of the layred

carbon fibre reinforced plastic

P.V. MIKHEEV, A. N. MURANOV, S. A. GUSEV

Bauman Moscow State Technical University, Moscow, Russia

Possibility of measurement of interlaminar shift module GXZ of layered CFRP at a three-point bending was showed. Using of modern experimental equipment allowed us to measure deformation of a CFRP specimen in a place of contact with loading tools of the test device and to use the known formulas for the calculation of interlaminar shift deformation at bending.

On the basis of use of a difference between the elasticity module E determined at stretching and the effective module of elasticity of a composite at a bending value of GXZ was defined for CFRP wich produced by method of vacuum infusion of resin.

Another possibility is to use a combination of Digital Image Correlation with the Virtual Fields Method. You can read more about it in the book of prof. Fabrice Pierron:

Book The Virtual Fields Method