جستجوی مقالات مرتبط با کلیدواژه « aluminum 6061-t6 » در نشریات گروه « مکانیک »

Nowadays, Aluminum alloys are chosen for various industrial applications due to their special properties and high corrosion resistance. By optimizing the surface properties of Aluminum alloys, the performance and reliability of using these materials can be effectively improved. Therefore, investigating the surface mechanical treatment has been the focus of researchers and various mechanical methods have been used to improve the surface characteristics of Aluminum alloys. Among these methods, ultrasonic hammer peening is a cold work process in which many impacts are applied to the surface of the sample in a short period with high frequency. In this research, the effect of ultrasonic hammer peening on the wear properties of Aluminum alloy Al6061-T6 has been investigated. To carry out the process of ultrasonic hammering, three parameters of vibration amplitude, rotational speed of the work piece, and feed rate of the tool were selected and their effect on the wear resistance was investigated. The obtained results showed that the ultrasonic hammer peening increased the surface hardness by about 141.4%. With the increase of the vibration amplitude and the feed rate, the wear resistance increased and the increase of the rotational speed decreased the wear resistance. The highest wear resistance has been obtained in the vibration amplitude of 11 µm, rotational speed of 500 rpm, and feed rate of 0.8 mm/rev. As a result, the wear resistance has increased by about 46% compared to the raw material in these conditions.

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. In order to have safe situation, the CBR value be 15 and greater has been recommended. 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.