【作者】 郝雨； 唐国安； 张美艳；

【Author】 Hao Yu;Tang Guoan;Zhang Meiyan;Institute of Engineering Physics,China Academy of Engineering Physics;Fudan University;

【机构】 中国工程物理研究院总体工程研究所； 复旦大学；

【摘要】 液体火箭在飞行过程中,推进-结构系统之间可能发生动力学耦合,严重的可能导致飞行失败。补燃循环发动机是一种重要的液体火箭推进装置,它的建模对液体火箭推进-结构耦合振动分析具有重要意义。本文以某液氧-煤油补燃循环发动机为研究对象,提出了时滞问题的近似处理方法,建立了发动机的时域动力学模型,将补燃循环发动机的控制方程表征为二阶线性微分方程的形式。通过一个算例,分析了补燃循环发动机的传递特性,验证了时域模型的正确性和精度,为液体火箭推进-结构耦合振动分析和发动机设计打下了基础。更多还原

【Abstract】 In the flight process of a large liquid-propuls ion launch vehicle,dynamical interaction between the structure and propulsion systems may occur,which may cause failure of flight mission.Staged combustion cycle engine is a kind of propulsion device for liquid rockets.The mathematical modeling of this kind of engine has essential signif icance for the analysis of structure-propulsion coupled vibration of a liquid-propuls ion launch vehicle.In this paper,aiming at a certain LOX-kerosene staged combustion cycle engine,an approximate treatment for time delay is proposed.A Time-domain dynamic model of this engine is established; furthermore,the governing equation of staged combustion cycle engine is represented in the form of second order linear ODE’s.Transfer characteristics of the engine are analyzed through an example to verify the validity and accuracy of the time-domain model.This paper has laid a good foundation for liquid rocket POGO analysis and engine design.更多还原