某小推力发动机试验系统自动器故障仿真研究

于锐渤; 石奇玉; 张黎辉; 段娜

doi:10.13224/j.cnki.jasp.20220564

某小推力发动机试验系统自动器故障仿真研究

doi: 10.13224/j.cnki.jasp.20220564

于锐渤^1,,
石奇玉²,
张黎辉^1,*, ,,
段娜²

1.
北京航空航天大学宇航学院，北京 102206
2.
中国航天科技集团有限公司北京航天试验技术研究所，北京 100048

详细信息

作者简介:
于锐渤（1999-），男，硕士生，主要从事液体火箭发动机系统仿真研究

通讯作者:
张黎辉（1966-），女，副教授，博士，主要从事液体火箭发动机系统设计、仿真和优化研究。E-mail：zhanglihui@buaa.edu.cn

中图分类号: V434⁺.23
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- 文章访问数: 27
- HTML浏览量: 25
- PDF量: 6
- 被引次数: 0
出版历程
- 收稿日期: 2022-08-02
- 网络出版日期: 2023-11-20

Simulation of automatic actuator fault in a low-thrust rocket engine test system

YU Ruibo^1
,,
SHI Qiyu²,
ZHANG Lihui^{1,*
, ,},
DUAN Na²

1.
School of Astronautics，Beihang University，Beijing 102206，China
2.
Beijing Institute of Astronautics Testing Technology，China Aerospace Science and Technology Corporation，Beijing 100048，China

摘要

摘要:
针对某小推力发动机试验系统中自动器故障的情况，建立了包括气动液阀、减压器、燃烧室、贮箱等组件模型，在Amesim平台上搭建试验系统仿真模型。通过仿真结果与试验数据的对比，验证了组件模型及仿真系统对试验系统实际工作情况的模拟效果，系统稳定工作阶段各主要参数的误差不超过2.8%。在系统正常工况基础上，对气动阀控制腔泄漏和减压器内漏两种故障下系统工况进行仿真计算，得到了故障工况下系统各参数的预测结果：减压器内漏故障发生30 s后，燃烧室压力可偏移正常工况14.3%，混合比偏移37.3%；气动阀泄漏面积达到24 mm²时，推进剂阀门将完全关闭。仿真结果对试验系统故障工况做出预测，并为故障分析、识别等积累了数据。
- 试验系统 /
- 自动器 /
- Amesim /
- 气动阀泄漏 /
- 减压器内漏 /
- 故障仿真
Abstract:
Taking the fault conditions of automatic actuator failure in a low-thrust liquid rocket engine test system as the research object, the models of the pneumatic liquid valve, the pressure regulator, the combustion chamber and the propellant tank were conducted. And the simulation system was built on Amesim platform. Through comparison between calculated data and test data, the reliability of new models was verified respectively. Furthermore, the simulation effect on the normal working condition of the whole test system was demonstrated, showing that the steady state error of main parameters was less than 2.8%. Based on the normal working condition, the prediction results of fault conditions under failure of the pneumatic liquid valve control cavity leakage and the pressure regulator internal leakage were calculated. The results showed that the chamber pressure can deviate from the normal conditions by 14.3% and the mixing ratio by 37.3% after the failure of pressure regulator internal leakage for 30 s. And when the leakage area of the pneumatic valve reached 24 mm², the propellant valve was completely closed. The prediction results can be accumulated for further work on fault detection, fault analysis and intelligent control of the test system.
- test system /
- automatic actuator /
- Amesim /
- pneumatic valve leakage /
- pressure regulator internal leakage /
- fault simulation

HTML

图 1 减压器原理图

Figure 1. Schematic diagram of the pressure regulator

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图 2 减压器仿真模型图

Figure 2. Simulation model diagram of the pressure regulator

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图 3 减压器模型对比图

Figure 3. Comparison of the pressure regulator models

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图 4 气动液阀原理图

Figure 4. Schematic diagram of the pneumatic liquid valve

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图 5 气动液阀仿真模型图

Figure 5. Simulation model diagram of the pneumatic liquid valve

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图 6 气动液阀起动过程仿真结果

Figure 6. Simulation results of the pneumatic liquid valve startup process

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图 7 燃烧室压力曲线

Figure 7. Curve of chamber pressure

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图 8 贮箱模型对比算例仿真结果

Figure 8. Simulation results of the tank model validation examples

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图 9 液发试验系统仿真模型

Figure 9. Simulation model of the low-thrust rocket engine test system

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图 10 正常工况仿真结果与试验数据对比

Figure 10. Comparison of simulation and test results of the normal condition

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图 11 减压器内漏故障工况仿真结果

Figure 11. Simulation results of the pressure regulator fault condition

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图 12 气动阀故障工况Ⅰ仿真结果

Figure 12. Simulation results of the pneumatic liquid valve fault condition Ⅰ

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图 13 不同泄漏面积下气动阀故障工况Ⅱ的比较

Figure 13. Comparison of the pneumatic liquid valve fault condition Ⅱ with different leakage areas

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图 14 气动液阀故障工况Ⅱ系统仿真结果

Figure 14. Simulation results of the pneumatic liquid valve fault condition Ⅱ

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表 1 正常工况仿真结果与试验数据对比

Table 1. Comparison of simulation and test results of the normal condition

参数	仿真结果	试验数据	误差/%
燃烧室压力/MPa	0.805	0.807	0.2
燃料质量流量/（g/s）	366.6	364.2	0.6
氧化剂质量流量/（g/s）	606.3	623.9	2.8
燃料贮箱压力/MPa	1.638	1.656	1.1
氧化剂贮箱压力/MPa	1.659	1.686	1.6

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