With particular applications in low-energy projectile systems, educational rocketry, and prototype-level aerospace engineering, this paper investigates the feasibility of spring-based propulsion systems as a mechanical substitute for traditional chemical propulsion.  The study models and analyses the transformation of potential energy held in a spring into kinetic energy imparted to a payload using Hooke's Law and conservation of energy principles, which are based on classical mechanics.  A specially designed launcher prototype with movable springs and adjustable compression lengths was used for a number of tests, allowing for a methodical assessment of thrust production, projectile velocity, and launch trajectory To forecast system performance across a variety of design parameters, such as spring stiffness, launch angle, and projectile mass, analytical models and numerical simulations were utilized.  These hypotheses were confirmed by experimental evidence gathered using motion tracking and high-speed videography.  The findings confirmed the prediction accuracy of the underlying physical model by showing a good correlation between theoretical and actual results.  Additionally, mechanical dampening, air resistance, and friction-related efficiency losses were measured and examined. Despite its inherent limitations due to its low energy density and scaling issues, spring propulsion has strong benefits like operational safety, low environmental impact, and reusability.  Because of these characteristics, it is especially appealing for scholarly and experimental applications that need for repeatable, regulated launch conditions.  The incorporation of hybrid mechanical-pneumatic systems and energy recovery mechanisms are among the design optimization suggestions made in the paper's conclusion.  By showcasing the promise of spring-based systems in particular use cases where accuracy, ease of use, and sustainability are valued, this study adds to the larger conversation on Additionally, mechanical dampening, air resistance, and friction-related efficiency losses were measured and examined. Despite its inherent limitations due to its low energy density and scaling issues, spring propulsion has strong benefits like operational safety, low environmental impact, and reusability. Because of these characteristics, it is especially appealing for scholarly and experimental applications that need for repeatable, regulated launch conditions. The incorporation of hybrid mechanical-pneumatic systems and energy recovery mechanisms are among the design optimization suggestions made in the paper's conclusion. By showcasing the promise of spring- based systems in particular use cases where accuracy, ease of use, and sustainability are valued, this study adds to the larger conversation on alternative propulsion technologies. Keywords: Spring propulsion, Rocketry, Mechanical propulsion systems, Kinetic energy conversion, Small satellite launch, 1) Energy Efficiency and Launch Velocity: Under optimal laboratory circumstances, the prototype spring propulsion system showed a consistent launch velocity of 2.8–3.1 m/s for a 500g payload. According to estimates, the spring's mechanical energy conversion efficiency was roughly 68%. This indicates that although a significant amount of the energy stored is converted into motion, some of it is wasted due to deformation and friction. 2) Repeatability and Reliability: The technology demonstrated good dependability with an exit velocity variance of less than 5% over 20 consecutive trials. During the trial period, no notable spring fatigue or mechanical problems were noticed. 3) Mass Optimization: According to Chen et al. (2020) and Smith & Johnson (2022), who highlighted the inverse relationship between payload mass and initial thrust in spring systems, lighter payloads (200–300g) produced higher velocities (up to 4.2 m/s) as shown in fig 3. 4) Vacuum Chamber Test Results: Fig 3. (Heidt et al., 2017) Launch velocity increased by around 12.5% when tested in low-pressure settings that mimic near-space environments because there was no atmospheric drag. This supports theoretical models indicating that spring propulsion operates more effectively in vacuum given in table VIII (NASA, 2021). Furthermore, a scalable, secure, and mechanically reliable ejection mechanism like spring propulsion could reduce entrance barriers and system complexity considering the growing commercial interest in tiny satellite constellations (McKinsey, 2023). 4) Limitations Notwithstanding its advantages, the existing technology does not have the thrust-to-weight ratio required for escape velocity launches or bigger payloads. Furthermore, scalability is restricted by mechanical limits after a specific payload mass. Although it was outside the purview of this study, long-term fatigue testing spanning thousands of cycles is essential for applications in the future. The study effectively shown that spring-based systems may provide dependable and repeatable propulsion for light payloads, especially in low-gravity or vacuum settings, through theoretical modeling and actual testing. With a steady mechanical energy conversion efficiency of roughly 68%, the experimental prototype launched a 500g payload at a range of 2.8–3.1 m/s. Additionally, tests conducted in low-pressure settings verified that the launch velocity rose by about 12.5%, highlighting the system's improved performance in vacuum. According to Park and Kim (2020), composite spring materials outperformed traditional steel in lowering mechanical fatigue and internal damping losses, confirming its potential for use in aerospace in the future. The system's benefits in terms of safety, scalability for small payloads, and low operational complexity were also emphasized in the study. It does, however, recognize certain significant drawbacks, such as inadequate thrust for orbital launches and restricted scalability because of mechanical limits.