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unique098

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Hi, I am looking for some guidance on a problem I am trying to solve on laminate analysis.

This is a flat laminate (9 plies with a thickness of 0.125mm) of unidirectional carbon fibre reinforced plastic with a stacking sequence of:

0/60/0/-60/90/-60/0/60/0.

Ply properties are as follows:

E1 = 134 GPa, E2 = 10.3 GPa, G12 = 5.1 GPa and v12 = 0.326

stress1UT = 2090 MPa, stress2UT = 97 MPa, stress1UC = -1600 MPa, stress2UC = -356 MPa and

T1UT = 114 MPa

How do I calculate Nx, the load per unit width in the 0 angle direction at which each set of plies will fail. I do not have any stress or strain values so I am unable to put this into the Tsai-Hill formulae. Is there any way I can calculate the stress and strain values? So far I have calculates the Q, Qbar and A B and D matrices. I do not know how to go further from this.

In addition to this, I need to find ultimate strength allowing for those plies which fail early.

I am not looking for plain answers, I would prefer some guidance on how to go about solving this. Any help is appreciated.

This is a flat laminate (9 plies with a thickness of 0.125mm) of unidirectional carbon fibre reinforced plastic with a stacking sequence of:

0/60/0/-60/90/-60/0/60/0.

Ply properties are as follows:

E1 = 134 GPa, E2 = 10.3 GPa, G12 = 5.1 GPa and v12 = 0.326

stress1UT = 2090 MPa, stress2UT = 97 MPa, stress1UC = -1600 MPa, stress2UC = -356 MPa and

T1UT = 114 MPa

How do I calculate Nx, the load per unit width in the 0 angle direction at which each set of plies will fail. I do not have any stress or strain values so I am unable to put this into the Tsai-Hill formulae. Is there any way I can calculate the stress and strain values? So far I have calculates the Q, Qbar and A B and D matrices. I do not know how to go further from this.

In addition to this, I need to find ultimate strength allowing for those plies which fail early.

I am not looking for plain answers, I would prefer some guidance on how to go about solving this. Any help is appreciated.