About Odyssey
Project Odyssey was a 500 lbf hybrid rocket engine utilizing HTPB and nitrous oxide as propellants. The engine was fired twice with the second test resulting in the loss of the engine due to thermal failures. Odyssey was ERPL’s first engine test in over a decade and acted as a knowledge gathering project that resulted in the development of a propellant feed system, custom data collection, and a multitude of operations planning documents.
The engine is retired and on display in the College of Engineering.
Odyssey Testing
Test Fire 01 – principium
Test Fire 02 – fini
Engine Specs
- Thrust – 500 lbf
- Chamber Pressure – 500 psia
- Oxidizer Flow Rate – 1 kg/s
- Injection Type – Swirl
Project Contact
Cameron Sexsmith – [email protected]
Alex Clay – [email protected]