Assembly for an aircraft including a wing element and a suspension pylon

Abstract

The invention relates to an assembly for an aircraft comprising a wing element (2) and a suspension pylon (4) for an engine (10) under the wing element, the suspension pylon (4) comprising a rigid structure (6) forming a box provided with an aft closing element (28), and the wing element (2) having a forward spar (34) extending substantially parallel to a leading edge (30) of the wing element. According to the invention, the rigid structure is assembled on the wing element such that the aft closing element bears in contact with the forward spar (34).

Description

TECHNICAL DOMAIN[0001]This invention relates in general to an assembly for an aircraft comprising a wing element and an engine suspension pylon under said wing element.[0002]Such an assembly may be used for any type of aircraft, for example aircraft with turbo-engines suspended from the wing, such as turbojets or turboprops.STATE OF PRIOR ART[0003]On existing aircraft, turbo-engines are suspended below the wing by complex mounting devices, also called EMS (Engine Mounting Structure), or suspension pylon. For turbojets, the mounting devices usually used comprise a rigid box structure, in other words formed by the assembly of upper and lower spars connected to each other through a plurality of transverse ribs.[0004]In a known manner, these pylons are designed particularly to transmit static and dynamic forces generated by the turbo-engines such as the weight, thrust or the different dynamic forces, to the wing.[0005]In this respect, forces are usually transmitted between suspension py...

AI Technical Summary

Benefits of technology

[0014]Consequently, the assembly according to the invention enables larger dimensions of suspension pylons, so that they can be better adapted to the high forces that they are designed to resist.

[0015]Furthermore, note that this solution no longer uses conventional attachments like those described in the state of prior art, considering that in the preferable required, the entire rigid structure forming a box is located in front of the forward spar of the wing element. Fastening means for fixing the rigid structure onto the wing element can then be entirely laid out at the closing element that is normally vertical, and are no longer partially added on the upper spar of the box as was the case previously with the spigot type intermediate attachment. Thus, the presence of these fastening means does not increase the size in the vertical direction, so that the dimensions of the suspension pylon and / or the ground clearance can be further increased.

Problems solved by technology

On recent aircraft turbo-engines, the large dilution ratio required results in an extremely large overall dimension, because increasing the dilution ratio inevitably increases the engine diameter, and also more particularly increases the diameter of its fan case.

Thus, with a ground clearance that is naturally fixed so as to remain acceptable from a safety point of view, the space remaining between the wing and the turbo-engine to hold the suspension pylon and the different attachments is becoming increasingly restricted, while paradoxically the forces to be resisted are becoming increasingly high.

This development of turbo-engines has the unfortunate consequence of reducing the vertical dimensions of the suspension pylon, particularly to maintain sufficient space to put the clamping fitting of the intermediate attachment into place, for which large dimensions are necessary in order to resist the turbo-engine thrust forces, in other words forces along the longitudinal direction of the turbo-engine, and forces along the transverse direction of the turbo-engine.

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