Satellites working in Very Low Earth Orbit (VLEO) experience substantial atmospheric drag, constraining operational lifespan through increased fuel consumption and orbital decay. This study investigates the impact of drag on the dynamics of VLEO satellites, employing the CelestLab toolbox in Scilab. The framework employs the STELA to generate spacecraft models with customizable geometric parameters and solar panel orientations. The method incorporates momentum exchange calculations between thermospheric molecules and spacecraft surfaces, evaluating cross-sectional area variations throughout orbital periods. Rotating solar arrays can be mechanically complex as compared to fixed configurations, but optimal orientation is suggested in this study, which enhances energy harvest significantly. Temporal analysis showed that orbital decay due to drag causes the semi-major axis to decrease slowly at higher initial altitudes and then accelerate as perigee drops into denser atmospheric layers. Solar flux sensitivity analysis indicates that increased solar activity correlates with enhanced propulsion capability, thereby reducing the rate of orbital degradation. Iterative simulations helped identifying optimal spacecraft configuration depending upon mass of the satellite. Results provide practical design guidelines for minimizing drag-induced perturbations in VLEO missions while maximizing operational efficiency.