Design and static testing of wing structure of a composite four-seater electric aircraft

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 tr...

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Bibliographic Details
Published in:Science and engineering of composite materials 2020-01, Vol.27 (1), p.258-263
Main Authors: Yang, Kang, Guo, Yi-lin, Li, Dong-hui, Ma, Gang, Geng, Hao, Li, Qun-fang, Xue, Ji-jia
Format: Article
Language:English
Subjects:
Aircraft
Aircraft reliability
Aviation
CCAR 23-R3
Civil aviation
Composite materials
Composite wing
Composite wings
Finite element analysis
Finite element method
Fly by wire control
Four-seater electric aircraft
Numerical analysis
Regulations
Special effects
Static testing
Static tests
Strain distribution
Structural design
Weight reduction
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Summary: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)
ISSN:0792-1233
2191-0359
DOI:10.1515/secm-2020-0023