Assessment and optimization of a hybrid rocket motor as the final stage of small satellite launch vehicle

Abstract

In the realm of space exploration, launch vehicles or carrier rockets transport payloads from Earth to space for tasks such as commercial or military satellite deployment, meteorological observations, and experimental studies. These vehicles range from single-stage to reusable systems, classified by launch platforms on land, sea, or air, and categorized by payload size for targeted orbits. Hybrid rocket motors, combining solid propellants with liquid or gaseous oxidizers, provide flexibility and efficiency in propulsion. This thesis develops a six-degrees-of-freedom model for simulating small satellite launch vehicle orbits, including the replacement of the final stage of the Minotaur-I launch vehicle with a hybrid rocket motor. Multi-objective optimization addresses complex design parameters and mission objectives, utilizing hybrid propulsion for cost-effectiveness and environmental benefits. Additionally, response surface analysis evaluates key parameters influencing vehicle performance and trajectory optimization.