再使用型有翼ハイブリットロケットシステムの基本設計と飛行性能予測

概要

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Hybrid rocket motors, propelled by a combination of a solid fuel and a liquid oxidizer,are best suited to development of small launch systems in university laboratories,becauee af their advantageous characteristics such as Bafety, easy handling. and lawcosts. The performance of hybrid rocket motors of three classes of thrust - 10tonf,1tonf, and 200kgf - is estimated. The feasibility of reusable winged launch systemsbased on the three motors is prelirninarily analyzed for suborbital micro-gravityexperiments. The results tell that a sysbem with a 10tonf-class motor by a coolant bleedcycle with polystyrene and LOx fed by an LE-5B turbopump will be capabre of exposinga payload of 360kg to a micro-gravity environment for three minutes. It is alsopredictied that a system with a 1tonf-class motor will be moderately capable and thatwith a 200kgf-class motor will not be feasible for micro gravity missions mainly becausethe weight of its helium pressurization system for feeding LOx will reduce the massfraction.
室蘭工業大学の論文
2001-11-30