Study on the characteristics of bipropellant-fueled pulse rocket engine with high combustion chamber pressure

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.