This paper presents a novel approach for the optimal design of the orbital transfer trajectory of a satellite with proposed continuous-thrust. In this study, the thrust direction angle is approximated using a truncated Fourier series, with the Fourier coefficients selected via a genetic algorithm. The goal of this optimization is to ensure the satellite reaches the desired position in the final orbit while achieving tangential conditions at the entry and exit points, thereby minimizing fuel consumption. The advantage of the proposed method is its ability to account for orbital perturbations, such as the Earth's oblateness effect, without significantly increasing computational complexity. Additionally, the proposed model does not require a predefined number of orbital revolutions, offering high flexibility in mission design. Numerical results and simulations demonstrate that this method provides accurate and efficient transfers between different orbits. Furthermore, performance analysis of this method under varying parameters, such as thrust force and initial orbital conditions, shows its robustness and adaptability. Overall, this paper provides an efficient framework for designing continuous thrust maneuvers in space missions, leading to reduced fuel consumption, shorter operation times, and optimized mission costs. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .