抄録
Burning tests of a swirling-oxidizer-type hybrid rocket engine with the PMMA/O_2 propellant, which were conducted at large O_2 mass fluxes and high chamber pressures, showed that rapid ignition and stable combustion occurred and overall fuel regression rate with swirl increased up to 2.7 times of that without swirl. A full-scale engine achieved a maximum thrust of 692 [N] and specific impulse of 263 [s]. Using this engine, a small hybrid rocket that was 1.8 [m] in length and 15.4 [kg] in mass was designed and fabricated. It was launched from Taiki-cho, Hokkaido, Japan, and reached an altitude of about 600 [m]. The successful launch demonstrated the advantages of this hybrid rocket engine with a swirling oxidizer flow and a maturity level of the propulsion.
