Composite constructions have acquired universal recognition in the automobile, aerospace, marine, and sustainable energy industries. Composites provide many advantages over metal, such as a high strength and stiffness-to-weight ratio, low cost, thermal insulation, and durability. One of the most common failure types in adhesively bonded composite structures is delamination through the interface of two lamina or between skin and core in sandwich panel. A new discrete cohesive zone model (DCZM) is proposed to model crack initiation and its subsequent propagation in thin laminated composite adhesive bonded beams. Unlike in existing continuum cohesive zone models (CCZM), the proposed model treats the interface as a spring element and the adherent as a beam element. The constitutive relation of the adhesive is modeled using a bi-linear traction separation law. Using the initial assumptions, the problem can be reduced from a 2D to 1D framework relaxing the requirements of maintaining the aspect ratio in the finite element mesh. Three standard fracture tests, a double cantilever beam (DCB), an end notch flexure (ENF) beam, and a mixed-mode beam (MMB), were simulated to illustrate the advantages of the proposed methodology. In the three simulations (mode-I, mode-II, and mixed-mode), it has been observed that the model is independent of element size and the load step size increment. The results have been validated with reported (benchmark) numerical, analytical, and experimental findings [1]. The proposed methodology can reduce the unknown degrees of freedom by more than 25% from the corresponding mesh employed with existing methods [1]. The model is further extended to model the interface of adhesively bonded sandwich panels. The results obtained from the proposed model agree with the experiments reported in the literature. REFERENCES [1 ]Xie, D., & Waas, A. M. (2006). Discrete cohesive zone model for mixed-mode fracture using finite element analysis. Engineering fracture mechanics, 73(13), 1783-1796.