Numerical simulation of the operation process of a hybrid rocket motor

Propellant performance, solid fuel regression rate and characteristic of combustion and flow in a classic hybrid motor were analyzed theoretically. Computation of fuel regression rate and combustion flow in a hybrid motor were studied. Characteristic of combustion and flow in a classic hybrid motor was obtained from analysis of computational solution. LOX/HTPB was taken as propellant in computation. Influential factor of fuel regression rate, vacuum special impulse and vacuum thrust at various oxidizer mass flow rates were obtained. Two chemistry models were adopted and the better chemistry model was chosen at the last, which will be useful for the hybrid rocket motor design.