Active combustion control in a hybrid rocket engine: performance gain from a case study and practical application needs

Carmine Carmicino（カルミネ　カルミチーノ）
ISAS/JAXA 宇宙飛翔工学研究系

Hybrid rocket engines are chemical propulsion systems which, in the most common configuration, employ a liquid oxidizer and a solid fuel. Yet essentially preserving performance comparable to the most complicated liquid rocket engines, their typical arrangement involves a series of benefits that can lead to extensive employment as game changing technology in the current space industry. Because of the separation of propellants, throttling can be easily achieved to meet the thrust profile required by the specific mission by controlling the oxidizer mass flow rate; but, to maintain the operation at the optimum mixture ratio (maximum specific impulse), apart from the main oxidizer flow rate, an additional oxidizer stream must be controlled as, for instance, in the configuration of an A-SOFT hybrid rocket. The latter is analyzed from a performance gain perspective compared to a classical hybrid rocket concept, and the requirements of the fuel regression rate measurement sensors needed for a practical implementation are presented.

Place: New Bldg. A 2F Conf. room A (1257) / 新A棟２階会議室A (1257号室)