基于耗氧惰化技术的飞机燃油箱热模型

刘冠男; 王立群; 王悦; 许扬; 王洋洋; 冯诗愚; 范菊莉

doi:10.13700/j.bh.1001-5965.2022.0097

基于耗氧惰化技术的飞机燃油箱热模型

doi: 10.13700/j.bh.1001-5965.2022.0097

1.
南京航空航天大学航空学院，南京 210016
2.
中国航空工业集团有限公司沈阳飞机设计研究所，沈阳 110035
3.
航空工业四川泛华航空仪表电器有限公司，成都 610599
4.
中国航空工业集团有限公司南京机电液压工程研究中心，南京 211106

基金项目: 国家自然科学基金委员会-中国民用航空局民航联合研究基金(U1933121)

详细信息

通讯作者:
E-mail：fjl@nuaa.edu.cn

中图分类号: V228；TQ021.4
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- 被引次数: 0
出版历程
- 收稿日期: 2022-03-01
- 录用日期: 2022-08-21
- 网络出版日期: 2022-09-05
- 整期出版日期: 2023-12-31

Thermal model of aircraft fuel tank based on oxygen consumption inerting technology

1.
College of Aero-space Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
Shenyang Aircraft Design and Research Institute，Aviation Industry Corporation of China Limited，Shenyang 110035，China
3.
AVIC Sichuan Fanhua Aviation Instrument Electric Appliance Co.，Ltd.，Chengdu 610599，China
4.
Nanjing Engineering Institute of Aircraft Systems，Aviation Industry Corporation of China Limited，Nanjing 211106，China

Funds: National Natural Science Foundation of China-Civil Aviation Administration of China Joint Research Fund (U1933121)

More Information

Corresponding author: E-mail：fjl@nuaa.edu.cn

摘要

摘要:
温度是燃油箱耗氧惰化系统适航符合性验证过程中重要指标。基于MATLAB Simulink软件，建立了飞机燃油箱耗氧型惰化系统油箱部件的传质传热模型，并验证其可靠性。在此基础上，分析了惰化系统抽气流量和出口温度对飞机燃油箱气相空间节点温度和燃油节点温度的影响。结果表明：所建立的飞机燃油箱传质传热模型具有较高的可靠性；随着惰化系统抽气流量的增加和惰化系统出口温度的升高，气相空间节点温度随之升高但对燃油节点温度影响不明显。
- 飞机燃油箱 /
- 耗氧惰化 /
- 热模型 /
- 传热传质 /
- 适航
Abstract:
The temperature serves as a crucial indicator in the airworthiness compliance verification process of the fuel tank inerting system. Using MATLAB Simulink software, a mass and heat transfer model was established and validated for analyzing the behavior of gas phase space nodes and fuel nodes' temperatures within an aircraft's fuel tank inerting system under varying conditions such as different gas extraction flow rates or outlet temperatures. The results demonstrate that this developed model exhibits high reliability when applied to analyze thermal characteristics inside an aircraft's fuel tank during its operation with different operating parameters.
- aircraft fuel tank /
- oxygen-consuming inerting /
- thermal model /
- heat and mass transfer /
- airworthiness

HTML全文

图 1 耗氧型惰化系统流程示意图

Figure 1. Flow diagram of oxygen-consuming inerting system

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图 2 机翼燃油箱基元模块示意图

Figure 2. Schematic diagram of wing fuel tank primitive module

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图 3 耗氧惰化飞机燃油箱热模型研究流程

Figure 3. Flow chart of thermal model of aircraft fuel tank for oxygen-consuming inerting

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图 4 某飞机隔舱简化示意图

Figure 4. Simplified schematic diagram of an aircraft partition

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图 5 某飞机飞行包线及马赫数

Figure 5. Flight envelope and mach number of an aircraft

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图 6 基于Simulink软件的燃油箱传质传热模型图

注：$T_f $为燃油温度；$T_g $为气体温度；$T_r $为壁面恢复温度。

Figure 6. Model diagram of mass and heat transfer of fuel tank based on Simulink software

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图 7 机翼燃油箱各节点温度随时间变化

Figure 7. Temperature of each node of wing fuel tank varies with time

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图 8 中央燃油箱各节点温度随时间变化

Figure 8. Temperature of each node of central fuel tank varies with time

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图 9 气相空间节点温度随耗氧型惰化系统抽气流量的变化

Figure 9. Variation of gas phase space node temperature with exhaust flow rate of oxygen-consuming inerting system

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图 10 燃油节点温度随耗氧型惰化系统抽气流量的变化

Figure 10. Variation of fuel node temperature with exhaust flow rate of oxygen-consuming inerting system

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图 11 气相空间节点温度随耗氧型惰化系统出口温度的变化

Figure 11. Variation of gas phase space node temperature with outlet temperature of oxygen-consuming inerting system

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图 12 燃油节点温度随耗氧型惰化系统出口温度的变化

Figure 12. Variation of fuel node temperature with outlet temperature of oxygen-consuming inerting system

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