3327 Experimental Research on Wax/N_2O Hybrid Rocket Engine

Abstract

Burning characteristics of a few kinds of hybrid rocket propellant grains were investigated using two different sized rocket engines, both of which employed nitrous oxide N_2O as oxidizer. Regression rates of PMMA, HTPB and wax were measured and compared one another by a series of tests of a 20N class micro-hybrid engine. From these experiments, regression rate of wax fuel is larger than 2 times compared with other conventional fuel grains. A 300N class engine was mainly used to measure the combustion characteristics of liquid N_2O/wax combination.