Purpose <p>This work presents the numerical framework of a variable stiffness composite laminate (VSCL) shell panel structure to investigate the nonlinear dynamic responses.</p> Methods <p>The numerical framework is developed using higher-order displacement kinematics, which satisfy through-thickness strain continuity and eliminate the need for a shear correction factor. Geometrical nonlinearity has been incorporated using the Green–Lagrange’s strains as it considers the total nonlinearity without omitting any of the nonlinear terms. The variable stiffness effect is achieved by continuously varying the fiber angle along a predefined curvilinear fiber path function. The governing equation for dynamic deflection responses is derived using Hamilton's principle. Further, Newmark's time integration method is used to evaluate the time-dependent deflection responses.</p> Results <p>The numerical model developed is tested for the nonlinear response consistency and accuracy via convergence and comparison tests, respectively. The model's capabilities have been explored and demonstrated through numerical case studies, investigating the effects of geometrical parameters, boundary conditions, material properties, fiber angles, and the number of fiber layers on the time-dependent deflection response of VSCL shell panel under a uniformly distributed load (UDL).</p> Conclusions <p>The results reveal that increasing the aspect ratio and modular ratio reduces the central dynamic deflection. In continuation, imposing stricter boundary constraints decreases transient deflection, indicating increased plate stiffness. Additionally, for a fixed fiber angle at the plate's center, the dynamic central deflection exhibits a downtrend as the fiber angle increases near the edges. Finally, the study presents a detailed discussion and concludes with remarks based on the numerical findings.</p>