复合材料飞机电气结构网络系统电气特性分析
收稿日期: 2024-12-19
修回日期: 2025-01-03
录用日期: 2025-02-19
网络出版日期: 2025-02-25
基金资助
天津市航空装备安全性与适航技术创新中心开放基金(JCZX-2023-KF-06)
Electrical characteristics analysis of composite aircraft electrical structure network system
Received date: 2024-12-19
Revised date: 2025-01-03
Accepted date: 2025-02-19
Online published: 2025-02-25
Supported by
Open Fund of Tianjin Aviation Equipment Safety and Airworthiness Technology Innovation Center(JCZX-2023-KF-06)
复合材料的高电阻率会影响飞机原有的导电路径，为保障飞机电气系统的正常运行，需要构建复合材料飞机电气结构网络系统模型来探究其电气特性。首先，针对电磁场下电气结构网络电气特性的计算问题，采用有限元法与稳定双共轭梯度法共同构建了电气结构网络系统模型，计算空间消耗量比部分元等效电路（Partial Element Equivalent Circuit，PEEC）法节省了63.92%。其次，通过对多类型激励源/多区域接入点组合的探究，分析了区域阻抗特性、电势分布图谱、电流密度矢量等多维度电学结果及性能影响。通过构建与测量实物模型，对实测结果与仿真结果进行了差异化分析，并验证了实测结果符合适航规章HB 6129。最后，基于实际工况角度与适航规章，对系统模型进行了接触因素系统误差分析、精细化理想模型分析和部件应力因素分析。所获结果及分析对复合材料飞机/电动飞机的电气结构网络的构建具有重要意义。
杨占刚 , 魏宇昊 , 杨娟 . 复合材料飞机电气结构网络系统电气特性分析[J]. 航空学报, 2025 , 46(16) : 331685 -331685 . DOI: 10.7527/S1000-6893.2025.31685
The high resistivity of composite materials affects the original conductive path of the aircraft. To ensure the normal operation of the aircraft electrical system， it is necessary to construct a composite aircraft electrical structure network system model to explore its electrical characteristics. Firstly， to address the calculation of the electrical characteristics of the electrical structure network under electromagnetic field， the finite element method and the stable double conjugate gradient method are adopted to jointly construct the electrical structure network system model， achieving a computational consumption reduction of 63.92% compared to Partial Element Equivalent Circuit （PEEC） method. Secondly， by exploring the combination of multi-type excitation sources/multi-area access points， the multi-dimensional electrical results and performance impacts， such as area impedance characteristics， potential distribution profiles， and current density vectors， are analyzed. By constructing and measuring the physical model， the difference between the measured and simulated results is analyzed， and the compliance with the airworthiness regulation HB 6129 is verified. Finally， based on the actual working condition perspective and airworthiness regulation， contact factor system error analysis， refined ideal model analysis and component stress factor analysis of the system model are conducted. The obtained results and analyses are of great significance for the construction of electrical structure network of composite/electric aircraft.
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