Simulation on working process of 10 N attitude-control thruster combustion chamber at lower-pressure condition

A simulation model for the working process of rocket engine combustion chamber was described. Simulation was implemented by using this model for a 10 N thruster working at different lower supply pressures. Comparisons were made to find some characteristics of chamber pressure and thrust of the thruster when it worked in long-pulse and short-pulse modes at regular and lower supply pressures. According to the theoretical thrust obtained by simulation and the experimental thrust in long-pulse mode, it can be concluded that the thrust efficiencies are 94%, 91% and 90%, respectively, while supply pressures equal to 1.48, 1.0, 0.6 MPa, separately. Meanwhile, simulation results of short-pulse mode cases show that, when the supply pressure decreases to 0.4 MPa, the thruster cannot be ignited in short-pulse mode.