Abstract
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, because of their advantageous characteristics such as safety, easy handling, and low costs. The performance of hybrid rocket motors of three classes of thrust - 10tonf, 1tonf, and 200kgf- is estimated. The feasibility of reusable winged launch systems based on the three motors is preliminarily analyzed for suborbital micro-gravity experiments. The results tell that a system with a 10tonf-class motor by a coolant bleed cycle with polystyrene and LOx fed by an LE-5B turbopump will be capable of exposing a payload of 360kg to a micro-gravity environment for three minutes. It is also predicted that a system with a 1tonf-class motor will be moderately capable and that with a 200kgf-class motor will not be feasible for micro gravity missions mainly because the weight of its helium pressurization system for feeding LOx will reduce the mass fraction.
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