Abstract Because of its light weight, high strength, designable, composite materials are more and more widely used in the field of aerospace, especially in the field of general aviation. In this paper, the structural design and analysis of the composite wing (include wing beam, rib, skin, leading edge and trailing edge) of a four-seater electric aircraft were carried out. The finite element numerical analysis model of the composite wing was established, and the deformation and strain distribution of the composite wing under the limited load required by airworthiness regulations were calculated. Finally, the static test of the whole composite wing was carried out to verify the accuracy of the finite element results. The finite element analysis and testing results showed that the structural design of the composite wing of the electric aircraft meets the structural strength requirements specified in the airworthiness standard (part 23 of China civil aviation regulations: air-worthiness requirements for normal, practical, special effects and commuting aircraft: CCAR 23-R3)

中文翻译：

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复合材料四人座电动飞机机翼结构设计与静态试验

摘要 复合材料由于具有重量轻、强度高、可设计性强等优点，在航空航天领域，特别是通用航空领域得到越来越广泛的应用。本文对一架四座电动飞机的复合材料机翼（包括翼梁、翼肋、蒙皮、前缘和后缘）进行了结构设计和分析。建立了复合材料机翼有限元数值分析模型，计算了复合材料机翼在适航法规要求的有限载荷下的变形和应变分布。最后，对整个复合材料机翼进行静力试验，验证有限元结果的准确性。