Proceedings of the Korean Society of Propulsion Engineers Conference (한국추진공학회:학술대회논문집)
- 2008.03a
- /
- Pages.849-854
- /
- 2008
- /
- 1975-342X(pISSN)
Development of a 1500N-thrust Swirling-Oxidizer-Flow-Type Hybrid Rocket Engine
- Sakurazawa, Toshiaki (Tokyo Metropolitan University) ;
- Kitagawa, Koki (Tokyo Metropolitan Institute of Technology) ;
- Hira, Ryuji (Tokyo Metropolitan University) ;
- Matsuo, Yuji (Tokyo Metropolitan Institute of Technology) ;
- Sakurai, Takashi (Tokyo Metropolitan University) ;
- Yuasa, Saburo (Tokyo Metropolitan University)
- Published : 2008.03.30
Abstract
We have been developing a 1500N-thrust Swirling-Oxidizer-Flow-Type hybrid rocket engine. In order to put the engine into practical use, we conducted long duration burning experiments up to 25s to examine the influence of configuration change of fuel grain on the engine performance and designed an LOX vaporization nozzle to supply GOX for the 1500N-thrust engine. The experiment with a small hybrid rocket engine showed that combustion was stable and the engine performance was approximately constant during combustion. There was no essential problem to with increasing combustion time. The LOX vaporization nozzle designed had 30 rectangular channels with a depth of 0.5mm. During passing through the nozzle, the LOX increased in temperature and vaporized sufficiently.