基于AMESim/Simulink的补燃循环火箭发动机与调节阀特性仿真
Simulation of characteristics of staged combustion cycle rocket engine and control valve based on AMESim/Simulink
李辉 1郭迎清 1徐柯杰 1闫星辉1
作者信息
- 1. 西北工业大学动力与能源学院,西安 710129
- 折叠
摘要
在AMESim软件环境下重新建立了某型补燃循环液体火箭发动机的调节阀部件动态模型,在Simulink软件环境下建立了机电作动系统的动态模型,将两者与修改后的火箭发动机模型进行变推力过程联合仿真,并在仿真中注入输送管路压力扰动.仿真结果表明:机电作动系统与调节阀模型能够反映发动机变推力过程中各部件内部的参数变化;联合仿真保持了原发动机模型的稳态精度,各主要参数误差均在1‰量级;调节阀的活塞自反馈机构能够抑制输送管路中低频压力波动对发动机推力的影响.
Abstract
The model of a control valve of a staged combustion liquid rocket engine was rebuilt in AMESim software environment.And the model of electromechanical actuation system was built in Simulink.Co-Simulation on process of variable thrust,including control valve,actuation system and modified engine model,was conducted.Then perturbance of pressure was introduced during simulation.The results showed that the model of electromechanical actuation system and control valve can reflect the internal parameter changes of each component in the process of variable thrust.The co-simulation maintained the steady-state accuracy of the original engine model,the errors of the main parameters were within the order of 1％o.The self-feedback structure of piston of control valve can restrain the influence of low frequency pressure fluctuation in the conveying pipeline on the thrust of the engine.
关键词
液体火箭发动机/调节阀/电动执行机构/AMESim软件/Simulink软件/联合仿真Key words
liquidrocket engine/controlvalve/electric actuator/AMESim software/Simulink software/co-simulation引用本文复制引用
基金项目
国家自然科学基金(62203362)
国家科技重大专项(J2019-V-0003)
出版年
2024
NETL
NSTL
万方数据