关键词: 肼, 动态响应, 供油, 数值模拟, 推力, 单组元火箭发动机

Abstract: Monocomponent rocket engines are important elements for attitude adjustment and orbit control of spacecraft. Aim-ing at the dynamic response of hydrazine-based monopropellant rocket engine to the change form of inlet flow, sim-ulation models of propellant flow, decomposition and heat transfer in the thrust chamber of the engine were estab-lished, and the numerical simulation and calculation analysis of three different fuel supply modes (steady-state fuel supply, linear fuel supply and pulse fuel supply) were carried out by using these models. The result is that the tem-perature at each point of the engine will vary in response to the inlet flow due to the difference in position. Pressure, velocity and thrust are correspondingly rapid in the inlet flow change, and the overall trend of the three changes is synchronized with the change trend of the inlet flow. In steady-state oil supply, speed and thrust spikes are 8.6% and 4.7% higher than the stable value of the starting stage, respectively, in the pulse oil supply, the speed and thrust spikes are 6.2% and 3.0% higher than the stable value of the start-up stage, respectively, in the first pulse phase, the speed and thrust spikes are 6.2% and 3.0% higher than the stable value of the start-up phase, and in the second pulse phase, the speed and thrust spikes are 9.3% and 5.2% higher than the stable value of the start-up phase, re-spectively.

Key words: Hydrazine, Dynamic response, Fuel supply, Numerical simulation, Thrust, Monocomponent Rocket Engine