Restartable Hybrid Rocket Motor using Nitrous Oxide
- Paper number
IAC-06-C4.2.02
- Author
Dr. Vadim Zakirov, Tsinghua University, China
- Coauthor
Mr. Wan Ke, Tsinghua University, China
- Coauthor
Dr. Haiyun Zhang, Tsinghua University, China
- Coauthor
Dr. Luming Li, Tsinghua University, China
- Year
2006
- Abstract
Restartable, N2O-fed hybrid rocket motors may further promote N2O propulsion technology applications since they allow multiple space vehicle maneuvers. In the restartable, N2O-fed hybrid rocket motor the catalyst pack is used as an igniter. In such a thruster N2O injected inside catalyst pack is first decomposed to nitrogen and oxygen, and then, hot, oxygen-rich exhaust is injected into combustion chamber igniting a solid fuel upon contact. Combustion products leave the chamber through the nozzle producing thrust. Hydroxyl-terminated poly-butadiene (HTPB), plexiglas (PMMA) and paraffin (wax) solid fuels have been repeatedly ignited during lab-scale hybrid rocket motor test firings. During the hybrid rocket motor test firings chamber pressure, catalyst pack pressure and temperature, N2O mass flow rate, and thrust data were acquired, ignition time delays were measured. Chamber pressure oscillations were observed and characterized. Based on the experimental data, relationships between oxidizer mass flux and oxidize-to-fuel ratio have been derived as well as combustion efficiencies have been obtained for the propellant combinations. Application of nitrous oxide decomposition catalyst for multiple ignition of hybrid rocket motor has demonstrated promising results. However, further research is required to optimize ignition process and system performance.
- Abstract document
- Manuscript document
IAC-06-C4.2.02.pdf (🔒 authorized access only).
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