液体酸素中でのPMMA の燃焼反応を利用したハイブリッドロケットエンジン用液体酸素気化装置の成立可能性について

摘要

Feasibility of LOX-vaporization equipment using combustion of PMMA in LOX for swirling-oxidizer-flow-type hybridrocket engines was examined from the viewpoint of thermal energy and structure, and a burning experiment of PMMA inLOX was conducted. The burning amount of PMMA to vaporize the LOX propellant for the hybrid rocket engine witha 1500 N-thrust was estimated to be at most 3 % of the fuel propellant of the rocket. The trade-off considerationsuggested that the vaporization equipment using combustion had an advantage of compact and simple structurecomparing with the LOX-vaporization nozzle. PMMA could burn steadily and safely in LOX and vaporize a largeamount of LOX.