| In this paper,various schemes of the engine pylon for attachment to the wing made of polymer composite materials are considered.Although composite materials have been used for a long time,there is still a number of issues relating,in particular,to the certification of aircraft made of this type of materials.The relevance of this topic lies in its contribution to modern aircraft industry.The aircraft is a complex system,all its components must meet the requirements of reliability,and much attention is paid to fail safety.An emergency landing of the aircraft was chosen as a load case to evaluate the reliability,since it is necessary to ensure the safety of passengers even under extreme conditions.Nevertheless,conducting full-scale tests of the aircraft during an emergency landing is an extremely expensive task.Therefore,the paper presents a numerical simulation of the same conditions using the Finite Element Method.The calculations were made according to eight cases,which are based on two main schemes of pylon attachment to the wing structure.In the first scheme,the attachment of the pylon to the wing spar is made using two coaxial mounts,while in the second scheme,these mounts are misaligned.During the simulating,different variants of the steel detachable element,which allows the engine with a pylon to safely separate from the wing in a collision with the surface,were considered.In addition,the impact of an emergency landing on a wing with different carbon fiber ply stacking was taken into account.Based on the results of calculations,conclusions were made on the optimality of the proposed schemes. |
