Experimental Investigation on the New 100N Bipropellant Space Rocket Engine

Abstract

This paper developed experimental research on the new 100N bipropellant space rocket engine. The bi-centrifugal swirl injector with high degree of technological maturity, high reliability and properties is used on this engine. The cold flow test, steady-state hot firing, pulse-mode firing, long life hot firing and deflection firing test are carried out. The results show that, the flow and spray characteristics of injector keep stable; during the steady-state hot firing, the structure of engine is intact; the impulse is good and the heat back temperature can up to 220.2 °C; during the different pulse-mode firing, the engine response time (t90) is lower than 38 ms; after the 45000 s long life firing, the structure temperate is not high which can fit the demand of long life; the heat back temperature of weld can up to 232.0 °C.