Perseus Hybrid Rocket - A Student Lead Hybrid Rocketry Team

The Perseus hybrid rocketry team is developing a hybrid rocket system to reach a minimum altitude of 8,000 feet and a flight duration of at least one minute while capturing crucial telemetry data. The rocket combines nitrous oxide oxidizer with HTPB-based solid fuel, ensuring a safer and more controllable propulsion system. The design process focused on optimizing engine efficiency, fuel burn rate, structural integrity, and aerodynamics, using CFD simulations and testing to refine performance. The team has explored various configurations and materials to balance weight, strength, and cost, ultimately selecting a modular rocket design for its scalability. The next steps include prototyping the rocket and conducting static fire tests to validate thrust and burn rates. Integrating all components into the flight vehicle will enable testing of the rocket's stability and performance, providing real-world data on the hybrid propulsion system. The team continues refining the design based on ground and flight test results. These insights will inform future test flights and improvements, moving closer to creating a reliable, reusable hybrid rocket for educational, research, and commercial use. Ultimately, is to become the first successful undergraduate hybrid rocket team. The project demonstrates the potential of hybrid propulsion systems in small-scale rocketry and offers valuable hands-on experience for undergraduate students in aerospace engineering.