Prediction of Energy Absorption Capability of Curved Panel Structure; For Wing Leading Edge Study

Abstract:

This paper works on the curvature effect of wing leading edge structure subjected to impact loading. At first stage, rigid spherical projectile and semi-elliptical panel were used. The impact testing has been carried out by varying the radius of curvature and the thickness of the panel. The experimental results show the trend of specific energy absorption capability of structure in function of the radius and thickness of panel. From experimental observation, it shows that the failure of structure subjected to impact loading can be distinguished in two types of failure; the projectile went through the structure and large displacement of curved panel. The two failure criteria are used later on to determine the energy absorption capability using Finite Element Analysis method. A FEA model is proposed to simulate the behavior of curved composite structure and validated by the experimental results in order, as final goal, to propose the simulation as a tool of designing the leading edge of wing with an optimum radius curvature and thickness of wing leading edge panel to absorb a specific magnitude of impact energy.

• Periodical: Applied Mechanics and Materials (Volume 225)
• Pages: 178-182
• DOI: https://doi.org/10.4028/www.scientific.net/AMM.225.178
• Online since: November 2012
• Authors: Nurihan Omar, Nur Aisyah Md Khalid, Nor Fadilah Shamsudin, Yulfian Aminanda
• Keywords: Energy Absorption, FEA Simulation, Impact Loading, Wing Leading Edge

References

[1] Guan Yupu et al, Foreign Object damage to fan rotor blades of aero engine part II : Numerical simulation of bird impact, Chinese Journal of Aeronautics 21 ( 2008 ) pp.328-334.

DOI: 10.1016/s1000-9361(08)60043-6

[2] A. Airoldi, B. Cacchione, Modelling of impact forces and pressures in lagrangien bird strike analyses, International Journal of Impact Engineering. 32, ( 2006)p.1651 – 1677.

DOI: 10.1016/j.ijimpeng.2005.04.011

[3] Li Yulong et al, Study of similarity law for Bird impact on structure, Chinese Journal of Aeronautics. 21(2008) 512 – 517.

DOI: 10.1016/s1000-9361(08)60168-5

[4] Richardson, John, W. Serious birdstrike-related accidents to military aircraft Of ten countries: preliminary analysis of circumstances. Bird Strike Committee Europe BSCE 22/WP22(1994).

[5] Goldsmith, W. Impact: the theory and physical behaviour of colliding solids. (2001).

[6] J.P. Hou, C. Ruiz. Soft body impact on laminated composite materials. (2007), p.505–515

[7] J. Lo´pez-Puente , R. Zaera, C. Navarro,Experimental and numerical analysis of normal and obliqueballistic impacts on thin carbon/epoxy woven laminates. 39 (2008) , p.374–387.

DOI: 10.1016/j.compositesa.2007.10.004

[8] S. Takedaa, S. Minakuchi, Y. Okabe, N. Takeda, Delamination monitoring of laminated composites subjected to low-velocity impact using small diameter FBG sensors.36 (2005) 903– 908.

DOI: 10.1016/j.compositesa.2004.12.005