Main Landing Gear Conceptual Design and Analysis for M.A.L.E U.C.A.V

Abstract

Among the major components for any Unmanned Combat Aerial Vehicle (UCAV) landing gear is of significant importance, as it performs the function of supporting weight, shock-absorbing structure, taxiing, and providing stable ground support during the nonoperational period, Takeoff and at the most critical phase of Landing. This study presents the Conceptual Design, Preliminary Structure Design, Sizing and Stress Analysis, Finite Element Analysis for Medium Altitude Long Endurance Unmanned Combat Aerial Vehicle (MALE UCAV) adhering to the C-23 Certificate Specification. The MALE UCAV design was carried out by different groups and this study is a part of that program. The conceptual design was carried out by fulfilling the preset constraints of Main Landing Gear weight, its height, and location. Tri-cycle layout configuration was selected and geometric parameters such as Wheel track and Wheel base and other parameters were worked out. A detailed study of all the possible loading conditions was conducted and the most critical and maximum loads were selected for sizing and stress analysis. Two candidate materials were selected and based on the Normal stress and Shear stress criteria, simultaneously sizing and stress analysis was carried out leading to the desirable design of the Main Landing Gear strut. Finite Element Analysis was performed on the designed Landing Gear for three models and the design fulfilling our requirements was selected.