Design and static testing of wing structure of a composite four-seater electric aircraft
Source abstract
Abstract
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)
Source: crossref · Quality: baseline
Research context
OpenAlex topics: Advanced Battery Technologies Research · Aeroelasticity and Vibration Control · Vehicle Noise and Vibration Control
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
Affiliations
Design department, Liaoning General Aviation Academy , Shenyang 110136 , China
Liaoning Key Laboratory of General Aviation, Shenyang Aerospace University , Shenyang , 110136 China
Liaoning Rui-xiang General Aircraft Manufacturing Co., LTD , Shenyang 110136 , China
References (19)
Show source-provided references
1. HUANG Jun, YANG Fengtian. Development and challenges of electric aircraft with new energies. Acta Aeronautica et Astronautica Sinica. 2015; 37(1):57-68.
2. LIN Z M. Making aviation green. Advance in Manufacturing. 2013; 1:42-49.10.1007/s40436-013-0008-3 ↗
3. HYDER A K. A century of aerospace electrical power technology. Journal of propulsion and power. 2003; 19(6):1155-1179.10.2514/2.6949 ↗
4. STEINER H, VRATNY PC, GOLOGANC, et al. Optimum number of engines for transport aircraft employing electrically powered distributed propulsion. CEAS Aeronautical Journal. 2015; 5(2):157-170.10.1007/s13272-013-0096-6 ↗
5. SALANM A, EUNUS Z I. Recent green aviation technologies an overview. Journal of Modern Science and Technology. 2013; 1(1):61-75.
6. TOMAZIZ T, PLEVNIK V, VEBLE G, et al. Pipistrel Taurus G4: On creation and evolution of the winning aero-plane of NASA green flight challenge 2011.Journal of Mechanical Engineering. 2011; 57(12):869-878.10.5545/sv-jme.2011.212 ↗
7. BRUCE P G,FREUNBERGER S A,HARDWICK J J, et al. LiO2 and LIS batteries with high energy storage. Nature Materials. 2012; 11(1):19-29.10.1038/nmat3191 ↗
8. SRILATHA A R. Design of a 4-seat general aviation electric aircraft. San Jose: San Jose State University; 2012.
9. Tang Jianmao. Review of studies of carbon fiber resin matrix composites. SPACECRAFT ENVIRONMENT ENGINEERING. 2010; 27(3): 269-280.
10. Zhang Xianhua, Gao Yanqiu, et al. Development and applications of carbon nanotubes and continuous carbon fiber reinforced composites. Aeronautical Manufacturing Technology. 2014; 459(15):71-73.
11. BAO Jianwen, JIANG Shicai, ZHANG Daijun. Current status and trends of aeronautical resin matrix composites reinforced by carbon fiber. Science & Technology Review. 2018; 36(19): 52-63.
12. Kang Yang, Liguo Zhang, Shude Ji, Yumei Yue, Wang Ji. Static testing and analysis of composite wing of a two-seater aircraft powered by Li-ion battery electric propulsion. Advanced Composites Letters. 2016; 25(6):127-131.10.1177/096369351602500601 ↗
13. ASTM F2245-11, Standard Specification for Design and Performance of a Light Sport Airplane.
14. DU Chunzhi, FU Boyu, QIU Zhihao. Design and finite element analysis of composite wing for a low speed aircraft. JOURNAL OF MACHINE DESIGN. 2019; 36(S2):55-58.
15. Wang Tong, Wu Zhen. Finite element analysis for simulate composite wing of X model aircraft. Journal of Shenyang Aerospace University. 2011; 28(05):48-51.
16. SMITH, Howard W. Static test of an ultralight airplane. Journal of Aircraft. 1988; 25(1):37-40.10.2514/3.45538 ↗
17. Zhang W, Yao L J, Tong X Y. Structural Design and Testing of Small Ultralight Solar-Powered Unmanned Aerial Vehicle. Advanced Materials Research. 2011; 317-319:227-230.10.4028/www.scientific.net/AMR.317-319.227 ↗
18. Simsiriwong J. Structural testing of an ultralight UAV composite wing and fuselage. Dissertations & Theses Grad-works; 2009.
19. CAAC. Part 23 of China civil aviation regulations: airworthiness requirements for normal, practical, special effects and commuting aircraft: CCAR 23-R3. Beijing: CAAC.