抄録
Experimental investigations are carried out about the combustion of new form of hybrid rocket propellants, in which oxidizer gas flows gap space in a fibrous fuel bed, under normal and micro gravity conditions. The new form of propellant has a potential to improve combustion efficiency and thrust level of hybrid rocket motors. Regression rates of fibrous strand fuels are measured with lower oxygen gas flow rates of near the combustion limit. Main results are in the followings: Gravity effects decrease with decreasing the oxygen gas flow rate until the effect almost diminishes near the combustion limit. In a certain range of oxygen gas flow rates near the combustion limit, the equivalence ratio keeps a constant value. The range of oxygen gas flow rates, in which equivalence ratio is constant, does not depend on the ambient pressure.
