Composite Materials

· A two-ply non-symmetric laminate is shown together with the response to the same uniaxial stress of the individual laminae and the laminate.
· The individual laminae will have a larger strain when the stress is applied normal to the fiber direction than when it is applied in the parallel direction:
ε₁ = σ / E₁ , ε₂ = σ / E₂ .
· When they are bonded to form the laminate, the laminate strain lies between that for the parallel and normal directions: ε₁ < ε < ε₂ .

From: Hull, "Introduction to Composite Materials," Cambridge (1992)