Low-altitude rocket design with payload transport up to 1700 meters and stability margin calculation

Rocketsystems are used in both civilian and military applications and require advanced engineering knowledge. In particular, rockets in the low-altitude category have gained significance due to the cost-effective solutions they offer for training, testing, and R&D activities. In this context, the development of systems that provide safe and stable flight while carrying mission payloads is of critical importance in engineering.In this thesis study, a low-altitude rocket capable of reaching up to 1700 meters and suitable for experimental use has been designed. During the design process, aerodynamic and structural analyses were carried out by considering key parameters such as body structure, fin configuration, center of gravity (CG), center of pressure (CP), and overall flight stability. Additionally, the stability margin, which directly affects flight safety, was optimized.Simulations performed using the OpenRocket software validated the performance and safety of the system. As a result of aerodynamic analyses, the stability margin was maintained within the range of 1.8 to 2.3 calibers to ensure safe flight conditions. The most suitable combination of design parameters was determined through an optimization process based on genetic algorithms. In structural analyses, carbon fiber and lightweight alloy materials were preferred, and the system was validated with a safety factor exceeding 6.0.To enhance landing safety, auxiliary components such as a parachute system were also integrated, making the system suitable for experimental applications. As a result, the proposed design increases payload-carrying capacity while improving flight safety and control precision. This study contributes to the development of economical and efficient rocket systems, particularly for educational, research, and light payload transport applications