Dynamic Response Analysis for the Solar-Powered Aircraft Composite Wing Panel with Viscoelastic Damping Layer

Abstract:

In design of solar powered aircraft wing panel, vibration properties of wing panel should be considered, especially for the peak value of dynamic response. In this research, a viscoelastic damping layer is built for vibration isolation, wing panel finite element models of stiffened and no-stiffened structures base on fiber-reinforced laminates with damping layer in the middle are built. Natural frequency and displacement response are analyzed with different thickness of damping layer and structures. Result shows natural frequencies decrease as thickness increased, and that of laminates are lower than stiffened structure. The maximum displacement response value decreased when thickness increased and that of laminates is higher than structured with stiffer. The presented work is helpful for type selection and designing of solar powered aircraft wing panel.

• Periodical: Applied Mechanics and Materials (Volumes 105-107)
• Pages: 491-494
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.105-107.491
• Online since: September 2011
• Authors: Tie Jun Liu, Yong Zhang, Gang Li, Feng Hui Wang
• Keywords: Composite, Dynamic Response, HALE, Natural Frequency, Viscoelastic Damping Layer

References

[1] M. Cowley: Wings in the Sun: the Evolution of Solar Challenger, Flight International, (1981) No.13, p.1865.

[2] E. Cestino: Design of solar high altitude long endurance aircraft for multi payload & operations, Aerospace Science and Technology, Vol.10, (2006) No.6, p.541.

DOI: 10.1016/j.ast.2006.06.001

[3] E. Rizzo, A. Frediani: A model for Solar Powered Aircraft Preliminary Design, The Aeronautical Journal, (2008), No.2, p.57.

DOI: 10.1017/s0001924000002001

[4] C. Wilson, J. Nutbean and I. Bond: Aerodynamic and Structural Design of A Solar-powered Micro Unmanned Air Vehicle, Journal of Aerospace Engineering, Vol. 214 (2000) No. 2, p.97.

DOI: 10.1243/0954410001531845

[5] S. Adhikari, 2000. Damping Models for Structural Vibration (PH.D., Cambridge University, UK, 2000), p.5.

[6] H. Hu, S. Belouettar and M. Potier-Ferry: Review and assessment of various theories for modeling sandwich composites, Composite Structures, (2008) No.84, p.282.

DOI: 10.1016/j.compstruct.2007.08.007

[7] M. WANG, H. Chen, R. Bai and Y. Cai: Dynamic Characteristics of Composite Reinforced Laminates Attached with Frequency-dependant Damping Layers, Engineering Mechanics, Vol. 23 (2006) No.6, p.174. (In Chinese)