Abstract
Hybrid rockets that use glycidyl azide polymer (GAP) as a solid fuel were studied. The linear burning rate spectrum of GAP was broadened when it was diluted it with polyethylene glycol (PEG). Self-combustible mixtures were used for the gas hybrid rocket motor; non-self-combustible mixtures were used for the traditional hybrid motor. Both were tested as functions of various experimental parameters, and the results of the traditional hybrid rocket are summarized in this paper. In particular, the fuel regression rates of GAP50PEG50 and GAP60PEG40 fuels were investigated, and the results indicate that the fuel regression rate of the fuel with high GAP content showed pressure dependability. Simultaneous measurements of the surface regression rate, which has attracted great interest, were conducted using ultrasonics in a special chamber, the results for the instantaneous surface regression rate during combustion were obtained. The obtained results are presented, and on the basis of experimental observations, a flame model of the traditional hybrid motor is discussed.
