A surrogate model method for aircraft cabin thermal analysis based on equivalent heat sink

IF 6.1 2区 工程技术 Q2 ENERGY & FUELS
Chuang Sun , Yinan Wang , Qian Luo , Xuejun Yang , Xue Chen , Xinlin Xia
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引用次数: 0

Abstract

Thermal analysis of an aircraft cabin is challenging to simulate accurately because of the complexity of the involved heat transfer processes. The natural convection heat transfer coefficient, a critical parameter for thermal analysis, is difficult to determine reliably through direct numerical simulation or experimental measurement, largely because of the presence of numerous instruments and unknown operational conditions. To overcome these challenges, a surrogate model with physical significance was proposed, in which the instruments are represented as equivalent heat sinks. The parameters required for the surrogate model were determined by analyzing the heat transfer processes within the cabin. Using a set of real temperature field data, genetic algorithms were employed to identify the relevant surrogate model parameters, including the natural convection heat transfer coefficient, heat transfer surface area, volume, and heat generation power.
To validate the proposed surrogate model, the temperature field predicted by the surrogate model was compared with experimental results from the real aircraft cabin. It was found that the surrogate model can accurately predict the temperature data of the real aircraft cabin, and the more data utilized in the parameter identification process, the more accurate the temperature prediction. Additionally, as long as the cabin structure remains unchanged, the surrogate model is applicable across different scenarios, significantly improving the efficiency of thermal analysis. Finally, temperature predictions under various boundary conditions were performed and compared with directly simulated temperature fields. The maximum error of the convective heat transfer coefficient obtained through parameter identification was approximately 6 %, while the maximum error of the temperature field predicted by the surrogate model was 2.2 K.
基于等效散热器的飞机座舱热分析替代模型方法
由于涉及的传热过程的复杂性,飞机客舱热分析的精确模拟具有挑战性。自然对流换热系数是热分析的关键参数,但由于仪器众多,操作条件未知,很难通过直接数值模拟或实验测量可靠地确定。为了克服这些挑战,提出了一个具有物理意义的替代模型,其中仪器被表示为等效散热器。通过分析机舱内的传热过程,确定了替代模型所需的参数。利用一组实际温度场数据,采用遗传算法确定相应的替代模型参数,包括自然对流换热系数、换热表面积、体积和产热功率。为了验证所提出的替代模型,将替代模型预测的温度场与真实飞机机舱的实验结果进行了比较。结果表明,该替代模型能够准确预测真实飞机客舱的温度数据,且参数识别过程中使用的数据越多,预测的温度越准确。此外,在客舱结构不变的情况下,替代模型适用于不同的场景,显著提高了热分析的效率。最后,进行了不同边界条件下的温度预测,并与直接模拟的温度场进行了比较。通过参数辨识得到的对流换热系数最大误差约为6%,而代理模型预测的温度场最大误差为2.2 K。
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来源期刊
Applied Thermal Engineering
Applied Thermal Engineering 工程技术-工程:机械
CiteScore
11.30
自引率
15.60%
发文量
1474
审稿时长
57 days
期刊介绍: Applied Thermal Engineering disseminates novel research related to the design, development and demonstration of components, devices, equipment, technologies and systems involving thermal processes for the production, storage, utilization and conservation of energy, with a focus on engineering application. The journal publishes high-quality and high-impact Original Research Articles, Review Articles, Short Communications and Letters to the Editor on cutting-edge innovations in research, and recent advances or issues of interest to the thermal engineering community.
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