The main aim of this paper is the study of the strength of AM-2 matting plate made of Al6061-T6 under impact loads due to aircraft landing. In this study, the damping effects of the aircraft tire have been modeled by means of Mooney-Rivlin hyperelastic criterion. Effective parameters such as the landing vertical velocity at 1. 5, 2, 2. 5, and 3 m/s; the landing horizontal velocity at 42, 45, 50, 55, and 60 m/s; the CBR value of subgrade at 5, 10, 15, 20 and 25; and the thickness of subgrade at 160, 200, 300, and 500 mm, have been studied. The results showed that the stresses in matting plate increases with increasing both horizontal and vertical components of landing velocity, but decreases by increasing the CBR value. On the other hand, considering the subgrade thickness greater than 300mm has no significant effect on stresses. The results obtained from modeling in software has been compared with that obtained experimentally and good agreement was found. Also, comparison of the results with those obtained without modeling the damping effects showed that the stresses be 15% greater in conditions without modeling damping of the tire.