Laminated composite shell structures fulfill a central role in real-world engineering, such as aircraft fuselages, iconic buildings, car body panels, orthopedic implants, pressure vessels, and satellite exteriors accompanying the significance of beam and plate structures. A comprehensive examination of the mechanical behavior of laminated composite structures under diverse loads is imperative during the design phase, facilitating the identification of potential stress concentration regions and ensuring the realization of a structurally sound framework. Recently, Kutlu [1] and Kutlu et al. [2] employed the mixed finite element method to perform the Refined Zigzag Theory-based static analysis of laminated composite beams and plates, respectively. In this paper, the mixed finite element formulation is developed to explore the linear static response of both thin and moderately thick laminated composite cylindrical shells. By employing the Refined Zigzag Theory (RZT), the necessity for the shear correction factor in First-order shear deformation theory is eliminated. Utilizing the Hellinger-Reissner principle, the stationary condition of the functional for the system is represented. Finite element discretization employs four-noded quadrilateral two-dimensional elements and the bilinear shape functions are utilized due to C0 continuity requirements of the formulation. Upon solving the mixed finite element equations, displacements, and stress resultants are directly obtained at the nodes. To affirm the efficacy of the presented solution method, analyses of comparison and convergence are conducted across diverse lamination schemes and under various boundary conditions.