Abstract：The premixed C2H4/N2O propulsion system has significant potential for attitude and orbit control thrusters since the propellant is not toxic and the systems are efficient and simple. However, methods are needed to prevent flashback. This study used a numerical model to analyze ignition in a thruster chamber with a single injector unit with a premixed C2H4/N2O propellant. The model included the plenum chamber, injection panel, combustion chamber and nozzle. The numerical model included a detailed chemical reaction mechanism for the ignition in the combustor and plenum chamber by coupling the reacting flow in the entire model and the heat transfer in the injection panel. The model predicts the spatio-temporal evolution of the unsteady ignition process in the thruster chamber and the steady characteristics are consistent with the results of chemical equilibrium calculations. Reducing the hole to the panel area ratio significantly increased the soak-back heat from the combustion chamber to the plenum chamber through the injection panel which eventually led to ignition of the premixed C2H4/N2O propellant in the plenum chamber. This is a new flashback mode induced by structural heat transfer through the injection panel. This process has a critical hole to panel area ratio for this propellant with a conventional chamber head. Thus, a new constraint criterion is given for the injection panel design of a premixed C2H4/N2O propulsion system.
王伟龙, 张会强. 预混C2H4/N2O推力室喷注面板热反侵着火现象数值模拟[J]. 清华大学学报（自然科学版）, 2020, 60(3): 206-211.
WANG Weilong, ZHANG Huiqiang. Numerical simulations of ignition by soak-back heat through the injection panel in a premixed C2H4/N2O thruster. Journal of Tsinghua University(Science and Technology), 2020, 60(3): 206-211.
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2020, Vol. 60 
