Experimental Hybrid Propulsion Research
Hybrid rocket engines use a combination of solid and liquid propellants, typically with a solid fuel grain and liquid oxidizer. This design offers advantages in safety, throttleability, and restart capability compared to traditional solid or liquid systems.
SOAR's hybrid rocket project explored the fundamentals of hybrid propulsion technology, providing hands-on experience with alternative rocket propulsion methods.
Design and cast solid fuel grains with optimal geometry
Create efficient liquid oxidizer injection systems
Conduct controlled burn tests to measure performance
Develop comprehensive safety protocols for hybrid testing
Fuel: Hydroxyl-terminated polybutadiene (HTPB) or paraffin-based solid fuel
Oxidizer: Nitrous oxide (N₂O) or gaseous oxygen
Custom combustion chamber with replaceable fuel grains
Pressure-fed oxidizer delivery system for controlled flow rates
Vertical test stand with load cell for thrust measurement
Data acquisition system monitoring pressure, temperature, and thrust
Multiple successful static fire tests
Developed fuel grain casting procedures
Collected thrust and pressure data
Zero incidents during testing phase
The team faced several technical challenges throughout the project:
The hybrid rocket project provided team members with unique exposure to alternative propulsion technologies and hands-on experience with:
Propellant formulation and combustion chemistry
Oxidizer flow and injection systems
Heat transfer and combustion efficiency
Sensor integration and data analysis
While the hybrid rocket project has concluded, the knowledge and experience gained continue to influence current propulsion research efforts. The safety protocols, testing procedures, and technical documentation produced during this project serve as valuable resources for future propulsion teams.