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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

于锐渤, 石奇玉, 张黎辉, 等. 某小推力发动机试验系统自动器故障仿真研究[J]. 航空动力学报, 2024, 39(8):20220564 doi: 10.13224/j.cnki.jasp.20220564
引用本文: 于锐渤, 石奇玉, 张黎辉, 等. 某小推力发动机试验系统自动器故障仿真研究[J]. 航空动力学报, 2024, 39(8):20220564 doi: 10.13224/j.cnki.jasp.20220564
YU Ruibo, SHI Qiyu, ZHANG Lihui, et al. Simulation of automatic actuator fault in a low-thrust rocket engine test system[J]. Journal of Aerospace Power, 2024, 39(8):20220564 doi: 10.13224/j.cnki.jasp.20220564
Citation: YU Ruibo, SHI Qiyu, ZHANG Lihui, et al. Simulation of automatic actuator fault in a low-thrust rocket engine test system[J]. Journal of Aerospace Power, 2024, 39(8):20220564 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
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

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

  • 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。

     

  • 图 1  减压器原理图

    Figure 1.  Schematic diagram of the pressure regulator

    图 2  减压器仿真模型图

    Figure 2.  Simulation model diagram of the pressure regulator

    图 3  减压器模型对比图

    Figure 3.  Comparison of the pressure regulator models

    图 4  气动液阀原理图

    Figure 4.  Schematic diagram of the pneumatic liquid valve

    图 5  气动液阀仿真模型图

    Figure 5.  Simulation model diagram of the pneumatic liquid valve

    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

    图 7  燃烧室压力曲线

    Figure 7.  Curve of chamber pressure

    图 8  贮箱模型对比算例仿真结果

    Figure 8.  Simulation results of the tank model validation examples

    图 9  液发试验系统仿真模型

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

    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

    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

    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

    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

    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

    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/MPa0.8050.8070.2
    燃料质量流量/(g/s)366.6364.20.6
    氧化剂质量流量/(g/s)606.3623.92.8
    燃料贮箱压力/MPa1.6381.6561.1
    氧化剂贮箱压力/MPa1.6591.6861.6
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  • 收稿日期:  2022-08-02
  • 网络出版日期:  2023-11-20

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