A Study on Combustion Efficiency Improvement of Low Melting Temperature Thermoplastics as a Hybrid Rocket Fuel

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This paper introduces the development of laboratory scale hybrid rocket using low melting point thermoplastics (LT) as a hybrid rocket fuel. The LT developed by Katazen Corporation have the higher regression rate comparing with Hydroxyl-Terminated-PolyButadiene (HTPB) and excellent mechanical properties, which makes them as promising candidates for hybrid rocket fuel. Therefore, the small hybrid rocket motor of the LT was prepared for the rocket launch program of the space-education using N2O as oxidizer. The motor length is variable and combustion efficiency was evaluated at several L/Ds. From the result was confirmed that characteristic exhaust velocity (C*) was increased significantly with increasing of the characteristic length (L*). From these results were suggested that the unburned fuel droplets did not contribute to combustion as a fuel. However, large L* will become large motor and will cause low fuel volume density in the chamber. In this study, C* function was investigated by static firing test using several types of baffle plate and several shape of aft combustion chamber as to small L* and confirmed large increasing of C* under the small L*. The details are presented and discussed in this paper.
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