基于AMESim/Simulink的补燃循环火箭发动机与调节阀特性仿真

李辉; 郭迎清; 徐柯杰; 闫星辉

doi:10.13224/j.cnki.jasp.20210401

基于AMESim/Simulink的补燃循环火箭发动机与调节阀特性仿真

doi: 10.13224/j.cnki.jasp.20210401

西北工业大学动力与能源学院，西安 710129

基金项目: 国家自然科学基金（62203362）；国家科技重大专项（J2019-Ⅴ-0003）

详细信息

作者简介:
李辉（1982-），男，工程师，博士生，主要从事火箭推进系统建模与仿真研究

通讯作者:
闫星辉（1991-），男，副教授，博士，主要从事飞行/推进控制系统研究。E-mail：yanxh@nwpu.edu.cn

中图分类号: V431
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出版历程
- 收稿日期: 2021-07-29
- 网络出版日期: 2023-10-18

Simulation of characteristics of staged combustion cycle rocket engine and control valve based on AMESim/Simulink

School of Power and Energy，Northwestern Polytechnical University，Xi’an 710129，China

摘要

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。
- 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
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‰. 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.
- liquid rocket engine /
- control valve /
- electric actuator /
- AMESim software /
- Simulink software /
- co-simulation

HTML

图 1 某型液氧/液氢补燃循环发动机系统示意图

Figure 1. Diagram of the LOX/LH staged combustion cycle engine system

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图 2 调节阀与电动执行机构系统框图

Figure 2. System diagram of control valve and electric actuator

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图 3 预燃室调节阀结构简图

1 调节阀入口；2 周向过流窗口；3 齿轮套筒；4 齿轮轴；5 调节阀出口；6 活塞；7 可调节流嘴；8 弹簧；9 阀体。

Figure 3. Structure of control valve of precombustion chamber

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图 4 推力室调节阀结构简图

1 阀入口；2 周向矩形节流窗；3 齿轮套筒；4 齿轮轴；5 阀出口； 6 阀内腔。

Figure 4. Structure of control valve of main combustion chamber

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图 5 发动机系统分层模型结构

Figure 5. Hierarchical structure of model of engine system

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图 6 机电作动系统结构原理图

Figure 6. Principle diagram of electromechanical actuator system

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图 7 机电作动系统Simulink模型框图

Figure 7. Diagram of model of electromechanical actuator system in Simulink

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图 8 POV阀AMESim模型

1 入口压力端；2 流体属性；3 入口至出口泄漏；4 活塞前端容腔；5 活塞前后端泄漏；6 活塞弹簧内腔；7 内腔至出口泄漏；8 活塞质量块；9 流体参数输入；10 出口压力端；11 第二级节流副；12 阀内容积；13 可调节流嘴；14 第一级节流副；15 开度指令。

Figure 8. Model of POV valve in AMESim

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图 9 MOV阀AMESim模型

1 入口压力端；2 流体属性；3 流体参数输入；4 出口压力端；5 节流机构；6 开度指令。

Figure 9. Model of MOV valve in AMESim

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图 10 联合仿真模型各分系统之间的数据交换

Figure 10. Data exchanging between sub-systems of co-simulation model

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图 11 火箭发动机联合仿真模型

Figure 11. Co-simulation model of rocket engine

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图 12 变推力仿真过程中的开度指令及响应

Figure 12. Opening instruction and response in the process of variable thrust simulation

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图 13 变推力仿真过程中部分关键参数

Figure 13. Some key parameters in the process of variable thrust simulation

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图 14 联合仿真中的POV阀活塞位移量

Figure 14. Displacement of piston of POV valve in co-simulation

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图 15 推力室压力变化对管路压力扰动的频率特性

Figure 15. Frequency characteristics of thrust chamber pressure change caused by pipeline pressure disturbance

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表 1 联合仿真与原发动机模型各参数对比

Table 1. Comparison of parameters between co-simulation and original engine model

参数	原发动机模型	联合仿真模型	绝对误差	相对误差/%
预燃室氧流量/ （kg/s）	48.70	48.76	0.06	0.12
推力室氧流量/ （ kg/s）	390.8	391.1	0.3	0.07
预燃室氢流量/ （kg/s）	59.10	59.14	0.04	0.06
推力室混合比	6.041	6.042	0.001	0.016

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