Abstract Scope |
Carbon fiber-epoxy laminate composites’ high strength, relatively low weight, and mechanical properties retention at high temperatures are advantageous for high performance applications – e.g., military and commercial aerospace structures. A composite’s strength is attributed to its transverse properties, interlaminar shear strength, and fracture toughness; however, a critical factor controlling strength under dynamic loading is the material’s tendency to delaminate. Bending, compression, and tensile loading can lead to interlaminar damage, i.e., delaminations, or the splitting apart of two fiber-rich laminate layers – reducing the composite’s bending stiffness. Delaminations are one of the most common failure modes in a laminate structure. Therefore, it is important to explore what initiates this phenomenon: structure, matrix cracking, interlaminar shear, temperature change, and interfacial adhesion between fiber and matrix. Further, the impact on the material’s mechanical properties and what toughening mechanisms can be employed to reduce this failure mode and create a stronger material. |