Title:

Deployable Hybrid Rockets for High Altitude Data Collection

This project presents the design and development of a deployable hybrid rocket system for high-altitude data collection (DHR-HADC), with a focus on propulsion performance, structural integration, and active thrust vector control. The system utilizes a hybrid propulsion architecture combining hydroxyl-terminated polybutadiene (HTPB) fuel with nitrous oxide (N2O) oxidizer to balance performance, safety, and manufacturability. A central objective is the implementation of a gimbal-based thrust vector control system driven by linear actuators and guided by inertial measurement units (IMUs), enabling real-time orientation correction during flight. The mechanical design emphasizes modularity through a load-bearing internal frame that transfers thrust while allowing plug-and-play payload integration. Finite element analysis was conducted to evaluate material performance under expected loading conditions, guiding the selection of aluminum and steel components. The control architecture incorporates a microcontroller-based system capable of sensor fusion, actuator feedback, and fault detection. Computational modeling was used to estimate regression rates, burn duration, and thrust characteristics. This work is conducted in informal collaboration with NASA Wallops Flight Facility, supporting future sounding rocket applications and high-altitude research initiatives.

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