单组元火箭发动机是航天器姿态调整和轨道控制的重要元件。针对肼基单组元火箭发动机对入口流量变化形式的动态响应，建立发动机推力室内推进剂的流动、分解和传热仿真模型，并利用这些模型对发动机进行了三种不同供油方式(稳态式供油、线性式供油和脉冲式供油)的数值模拟与计算分析。计算结果得出:发动机各点的温度会因位置差异而对入口流量的响应变化存在不同。压强、速度和推力对入口流量变化的相应非常迅速，三者在总体上的变化趋势与入口流量的变化趋势保持同步。速度和推力在稳态式供油和脉冲式供油中都存在高于启动阶段稳定值的尖峰，在稳态式供油中，速度和推力尖峰分别高出启动阶段稳定值的8.6%和4.7%，在脉冲式供油中，第一次脉冲阶段，速度和推力尖峰分别高出启动阶段稳定值的6.2%和3.0%，第二次脉冲阶段，速度和推力尖峰分别高出启动阶段稳定值的9.3%和5.2%。

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.