火箭推进2025，Vol.51Issue(2)：30-40,11.DOI:10.3969/j.issn.1672-9374.2025.02.004
某大推力氢氧火箭发动机起动特性分析
Analysis on the starting characteristics of a high thrust hydrogen-oxygen rocket engine
于锐渤 1张黎辉 1段娜 2石奇玉2
作者信息
- 1. 北京航空航天大学 宇航学院,北京 102206
- 2. 北京航天试验技术研究所,北京 100048
- 折叠
摘要
Abstract
Based on the generalized simulation software Amesim,the engine simulation system was built by using the two-phase flow pipeline,thrust chamber,turbopump and other component models provided by the software,and the transient characteristics of engine ignition and engine transition from primary to main stage were simulated and analyzed.The simulation results show that the generalized simulation model provided by the software can describe the starting characteristics of the engine more accurately,and the error between the calculated engine performance curve and the test measurement data does not exceed 10%,which meets the basic requirements of the simulation task.By setting different gunpowder starter operating times and operating pressures and comparing the effects of different starting conditions on the engine starting characteristics,it is found that the working environment of the combustion chamber in the transition section is more severe when the starter operating pressure is low,the higher the starter operating pressure is,the higher the peak temperature the turbine needs to withstand.In order to ensure smooth engine start,the simulation method can be used to optimize the design of the starting scheme.关键词
氢氧火箭发动机/起动特性/起动方案/仿真分析Key words
hydrogen-oxygen rocket engine/startup characteristics/startup solutions/simulation analy-sis引用本文复制引用
于锐渤,张黎辉,段娜,石奇玉..某大推力氢氧火箭发动机起动特性分析[J].火箭推进,2025,51(2):30-40,11.
