肼基单组元火箭发动机的动态响应  

Dynamic response of hydrazine⁃based monocomponent rocket engine

作　　者：蒋耀东 徐全勇[2] 马玉林[1] 程瑶 JIANG Yaodong;XU Quanyong;MA Yulin;CHENG yao(School of Mechanics and Engineering,Liaoning Technical University,Fuxin 123000,China;Aircraft Engine Research Institute,Tsinghua University,Beijing 100084,China;School of Innovation and Practice,Liaoning Technical University,Fuxin 123000,China)

机构地区：[1]辽宁工程技术大学力学与工程学院,阜新123000 [2]清华大学航空发动机研究院,北京100084 [3]辽宁工程技术大学创新实践学院,阜新123000

出　　处：《航空学报》2023年第21期341-353,共13页Acta Aeronautica et Astronautica Sinica

基　　金：国家科技重大专项(J2019-V-0001-0092,J2019-V-0013-0108)。

摘　　要：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3种不同推进剂供给方式(稳态式供给、线性式供给和脉冲式供给)的数值模拟与计算分析。计算结果表明: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响应非常迅速,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给和脉冲式供给中都存在高于起动阶段稳定值的尖峰,在稳态式供给中,速度和推力尖峰分别高出起动阶段稳定值的8.6%和4.7%,在脉冲式供给中,第1次脉冲阶段,速度和推力尖峰分别高出起动阶段稳定值的6.2%和3.0%,第2次脉冲阶段,速度和推力尖峰分别高出起动阶段稳定值的9.3%和5.2%。Monocomponent rocket engines are important elements for attitude adjustment and orbit control of space-craft.According to the dynamic response of hydrazine-based monocomponent rocket engine to the change form of in⁃let flow,a simulation model of propellant flow,decomposition and heat transfer in the thrust chamber of the engine is established,and the numerical simulation and calculation analysis of three different propellant supply modes(steady-state supply,linear supply and pulse supply)of the engine are carried out by using these models.The result is that the temperature at each point of the engine will vary in response to the inlet flow due to the difference in position.The response of pressure,velocity and thrust to changes in inlet flow rate is very rapid,and the overall trend of the three remains synchronized with the trend of inlet flow rate changes.There are spikes in velocity and thrust that are higher than the stable values during the start-up phase in both steady-state and pulse supply,in the steady-state supply,the velocity and thrust spikes are 8.6%and 4.7%higher than the stable value of the start-up phase,respectively,in the pulsed supply,the velocity and thrust spikes are 6.2%and 3.0%higher than the stable value of the start-up phase,respectively,in the first pulse phase,the velocity and thrust spikes are 6.2%and 3.0%higher than the stable value of the start-up phase,respectively,and the second pulse phase,the velocity and thrust spikes are 9.3%and 5.2%higher than the stable value of the start-up phase,respectively.

关 键 词：肼 动态响应 推进剂供给 推力 单组元火箭发动机 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]