Experimental investigation for hydrogen/oxygen engine using gas dynamic resonance ignition technique

Gas dynamic resonance ignition technique was used in design of hydrogen/oxygen small thrust rocket engine. By means of analysis of special impulse and combustion gas temperature in different mixture rate, system parameters of hydrogen/oxygen small thrust rocket engine were determined. Ignition tests of gas dynamic resonance igniter, hot firing tests of hydrogen/oxygen small thrust rocket engine and impulse ignition tests were carried out in different thrust operation conditions. It can be confirmed from the hot firing tests that hydrogen/oxygen small thrust rocket engine can realized multi-restart and stable performance. This may verify the reliability and feasibility of the hydrogen/oxygen small thrust rocket engine.