DEVELOPMENT OF TEST FACILITIES FOR 5 KN-THRUST HYBRID ROCKET ENGINES AND A SWIRLING-OXIDIZER-FLOW-TYPE HYBRID ROCKET ENGINE FOR TECHNOLOGY DEMONSTRATION

摘要

At the Hybrid Rocket research Working Group, performing demonstrations of current technologies is pursued. The target thrust was set as 5kN and a hybrid rocket test engine program (HTE-5-1) was initiated. To demonstrate the hybrid rocket engine technology, a hybrid rocket test facility was designed at the Akiruno facility, which belongs to the Japan Aerospace Exploration Agency. A low-flow rate gaseous oxygen (GOX)feed system that includes a purge system, test stand, measurement system, and control system was manufactured. The operability and functionality, such as the GOX mass flow range and natural frequency of the test stand, were examined. It was confirmed that combustion tests under a condition of up to 0.5 kg/s GOX mass flow rate could be conducted. A 5-kN-thrust swirling-oxidizer-flow-type hybrid rocket engine using a GOX/polypropylene propellant was designed and manufactured as a demonstrator. Two combustion tests were performed with the demonstration engine under conditions below the design point. Reliable ignition and stable combustion for long durations were achieved, and accurate experimental data were obtained. This demonstrated the effectiveness of the combustion test and validated the suitability of our engine design method. It was confirmed that the combustion test could be performed safely and properly using the new test facility and demonstrator.