Simulation Study on Impact Damage of Aircraft Panel Structure under Stress


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Based on ANSYS/LS-DYNA code, the finite-element models were created to simulate the response of the aircraft panel structure impacted by high velocity projectile. The models proved to be effective through the comparison between the results of simulation and relative experiments. Then the impact process was simulated respectively considering the states of various types of stress in the panel. Through analyzing the simulation results, the influence of various stress states in the panel on impact response and damage mechanism was summed up. The conclusions indicated that the stress and particularly compression stress in aircraft panel structure can facilitate much more deformation and damage when the panel suffers high velocity impact.



Key Engineering Materials (Volumes 324-325)

Edited by:

M.H. Aliabadi, Qingfen Li, Li Li and F.-G. Buchholz




M. Y. Hou et al., "Simulation Study on Impact Damage of Aircraft Panel Structure under Stress ", Key Engineering Materials, Vols. 324-325, pp. 391-394, 2006

Online since:

November 2006




[1] Jim Young. Predator Wing Ballistic Test. Aircraft Survivability. July (2004), pp.38-40.

[2] Zahid Iqbal Baig. Effects of Ballistic Impact Damage on Thin and Thick Composites. Iowa State University, Ames, Iowa, (1997), pp.33-104.

[3] Emile Greenhalgh, Andrew Clarke, et al. Investigation of Impact Damage in a CFRP Wing box Under Load. Structure Dynamics, and Materials Conference and Exhibit, April (2000), pp.1-11.


[4] Livermore Software Technology Cooperation. LS-DYNA Theoretical Manual. (1998), pp.1-10.

[5] Ping Zhou. Study of Battle-Damage Prediction Mode of Aircraft Structure Material LY-12CZ with Projectile. Journal of Air Force Engineering University. Vol. 5, No. 1, Feb (2004), pp.27-30.