By using a moving injector

the combustion chamber pressure of pulse rocket engine is much higher than feed system supply pressure.In order to analyze the characteristics of bipropellant-fueled pulse rocket engine

a mathematics model was presented.The zero-dimensional models were used for combustion chamber and extrusion rooms

and the one-dimensional

quasi-steady model was used for nozzle flow.Using N2O4 and MMH as propellant

the equation sets were calculated with fourth-degree Runge-Kutta method.According to calculated results

the maximal pressure and average pressure of combustion chamber are much higher than supply pressure

on account of the nonequivalent mass flow rate in combustion chamber.The performance difference between pulse rocket engine and conventional constant-pressure liquid rocket engine(LRE) was compared.Results show that

under the same supply pressure

the same mean thrust and area ratio

the vacuum specific impulse of pulse rocket engine has increased by 7.5%

but the throat area is only 10.2% of LRE.