Dynamic analysis and optimization of a bionic flapping-wing aircraft

• Autorzy: Jin X. , Zhou X. , Tian P. , Zhang L. , Nie Z.
• Języki publikacji: EN

Abstrakty

EN

This research has been conducted for the purpose of developing bionic flapping-wing aircraft. In this paper, wings are regarded as flexible, and the response issues of wings under certain excitation functions are investigated. The research is based on preliminary studies about bionic flapping wings and aims to provide data references to aid the selection of electrical actuators and the design of driving mechanisms for bionic flapping-wing aircraft at a later stage. The dynamic analysis shows that the response functions adapt well to the flapping movements of the wings. However, there are mutational situations in the wing structure transformation which are bad for structural stability, and cause there to be too little lift force. Under such circumstances, the minimum norm of low-order vibration mode difference values is used as the optimization principle to conduct the structural optimization. The optimization results and the wing flutter test both show that the optimized wings can better avoid structural mutations and their response functions can also better meet the design requirements.

Słowa kluczowe

EN

bionic flapping-wing aircraft; flexible wing; structural mutation; structural optimization; flutter test

• Wydawca: Instytut Podstawowych Problemów Techniki PAN
• Czasopismo: Engineering Transactions
• Rocznik: 2016
• Tom: Vol. 64, iss. 2
• Strony: 181--196
• Opis fizyczny: Bibliogr. 16 poz., rys., tab., wykr.

Twórcy

autor

Jin X.

• Shanghai University of Engineering Science Mechanical Design Department Mechanical Engineering College P.O. Box: 201620, Shanghai, China

autor

Zhou X.

• Shanghai University of Engineering Science Mechanical Design Department Mechanical Engineering College P.O. Box: 201620, Shanghai, China

autor

Tian P.

• Shanghai University of Engineering Science Mechanical Design Department Mechanical Engineering College P.O. Box: 201620, Shanghai, China

autor

Zhang L.

• Shanghai University of Engineering Science Mechanical Design Department Mechanical Engineering College P.O. Box: 201620, Shanghai, China

autor

Nie Z.

• University of Missouri Department of Mechanical and Aerospace Engineering Columbia, MO 65211 USA

Bibliografia

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• 4. Tien Van Truong, Jihoon Kim, Min Jun Kim, et al., Flow structures around a flappingwing considering ground effect, Experiments in Fluids, 54(7): 1575–1594, 2013.
• 5. Geng-feng Z., Shun-feng M., Ji-gang S., et al., High precision test method for dynamic imaging of space camera [in Chinese], 2nd IEEE International Conference on Advanced Computer Control, 1: 111–116, 2010.
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• 7. Wenyuan C., Weiping Z., Flapping wing micro aircraft [in Chinese], Shanghai, Shanghai Jiaotong University Press, 2010.
• 8. Yahui Z., Jiahao L., Basics of structural dynamics [in Chinese], Dalian University of Technology Press, Dalian, 2007.
• 9. Qing W., Bin X., Jiaqi H., Optimized design of structural dynamic boundary condition based on topology optimization [in Chinese], Mechanical Science and Technology, 31(11): 1845–1850, 2012.
• 10. Xucheng W., Finite element method [in Chinese], Tsinghua University Press, Beijing, 2003.
• 11. Decan Z., Several key problems of flapping-wing MAV [in Chinese], Shanghai Jiaotong University, Shanghai, 2007.
• 12. Ivanyi A., Ivanyi P., Ivanyi M.M., Ivanyi M., Hysteresis in structural dynamics, Physica B: Condensed Matter, 407(9): 1412–1414, 2012.
• 13. Lalibert´e J.F., Kraemer K.L., Dawson J.W., Miyata D., Design and manufacturing of biologically inspired micro aerial vehicle wings using rapid prototyping, International Journal of Micro Air Vehicles, 5(1): 15–38, 2013.
• 14. Yuefei G., Optimization design of boundaries and engineering implementation methods of structural dynamics [in Chinese], Northwestern Polytechnical University, Xi ’an, 2005.
• 15. Bo-lan J., Yun-ju Y., Xu B., Topology optimal design of structural dynamic boundary condition based on ICM criterion method [in Chinese], Journal of Vibration Engineering, 26(1): 55–59, 2013.
• 16. Xie C., Wu Z., Yang C., Aeroelastic analysis of flexible large aspect ratio wing [in Chinese], Journal of Beijin University of Aeronautics and Astronautics, 29(12): 1087– 1090, 2003.

Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę.