Numerical calculation on behavior of fuel regression in hybrid rocket motor
Hybrid rocket motor has many advantages for space propulsion applications.The mechanism and behavior of the fuel regression in the motor are complicated due to different phase states of the oxidizer and the fuel.The hybrid rocket motor code(HRM) for the unsteady simulation of motor operation has been programmed.This code can calculate physical and chemical processes from the oxidizer injector to the nozzle during motor operation.The mass and energy coupling between gas and solid phases as well as a dynamic fuel surface regression technique with a two-step calculation method is applied to simulate the fuel regression.The calculated motor thrust and fuel regression are compared to the experimental data for the code validation.The fuel regression rate equation and the relation between fuel regression rate and chamber diameter have been derived.The reasons for scale effect in hybrid rocket motor have been determined and analyzed.