Recent advancements in space technology have sparked significant interest in small satellite constellations, primarily due to their reduced costs, quicker development cycles, and improved capabilities. Although the costs associated with launching these satellites remain high, innovative strategies are emerging that offer alternatives to conventional deployment methods for positioning constellations in their designated orbits. These deployment strategies can be broadly categorized into two types: direct and indirect. This paper explores an indirect deployment method that utilizes Earth's oblateness perturbation alongside the satellite's propulsion subsystem to position satellites across multiple orbital planes. The method has been rigorously simulated and analyzed in the context of two operational satellite constellations, each serving distinct purposes—remote sensing and global internet provision. Furthermore, a comprehensive launch and deployment strategy has been developed and applied to a regional satellite navigation system, consisting of 130 satellites designed to serve Iran. This approach emphasizes the influence of Earth's shape on satellite orbits to optimize deployment efficiency. The analysis focuses on key parameters such as the time required for deployment and the necessary change in velocity (ΔV). The study demonstrates how leveraging the natural nodal precession caused by Earth's oblateness can significantly enhance the deployment process, reducing fuel consumption and operational costs. This approach presents a promising alternative for future satellite constellation deployments, offering both economic and technical advantages.