Assembly of wing longitudinal member and engine pylon horizontally aligned with respect to each other
By designing a component including a longitudinal member of the wing and an engine hanger, using structures such as screw-nut system and shear pins, the problem of insufficient space in the engine hanger is solved, and the component height is reduced and the engine performance is improved.
Patent Information
- Application Number
- CN202411197708.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2023-08-31
- Filing Date
- 2024-08-29
- Publication Date
- 2025-02-28
AI Technical Summary
In existing aircraft, the positioning of the engine mount under the wings limits the possibility of the engine increasing in size, resulting in insufficient space to improve engine performance.
An assembly is designed in which the longitudinal members of the wing are connected to the engine hanger through contact walls penetrating through a plurality of first holes, providing horizontally oriented fixation using a screw-nut system, reducing assembly height, and optimizing the structure through shear pins and intermediate walls.
The reduction in component height is achieved, ensuring that the connection between the engine mount and the wing is closer, which can effectively transmit the forces generated by the engine and improve the performance of the engine.
Smart Images
Figure CN119527557A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to an assembly of a longitudinal member of an aircraft wing and an engine pylon, which are horizontally aligned with each other and fixed by a horizontal screw-nut system. The invention also relates to an aircraft comprising such an assembly. Background Art
[0002] An aircraft generally comprises at least one engine, in particular a jet engine. The aircraft comprises an engine pylon under each wing, and for each engine, the engine pylon is fixed to the wing structure, and the engine is suspended under the engine pylon.
[0003] The engine pylon is usually arranged under the wing and fixed to the wing by various fixing devices.
[0004] To increase efficiency, engines have become increasingly larger, but the positioning of the engine pylons under the wings limits the possibility of increasing size, since the engines must maintain a minimum distance relative to the ground.
[0005] Therefore, it is desirable to find a new arrangement so that the space in the connection area between the engine pylon and the wing can be increased to facilitate lifting the engine. Summary of the invention
[0006] The subject of the invention is to propose an assembly of a longitudinal member of an aircraft wing and an engine pylon, which allows the height of the assembly to be reduced. To this end, an assembly for an aircraft comprising a wing is proposed, the assembly comprising:
[0007] - A longitudinal member of a wing, wherein the longitudinal member has a contact wall pierced by a plurality of first holes, each first hole passing through the contact wall and parallel to a longitudinal direction perpendicular to the contact wall.
[0008] an engine pylon arranged at the end of the longitudinal member in the longitudinal direction and having an upper longitudinal member substantially perpendicular to the contact wall and pierced, for each first hole, by a second hole parallel to the longitudinal direction and aligned with the first hole; and
[0009] - a nut and a screw for each pair of aligned first and second holes, wherein the screw is screwed into the nut through the first and second holes in sequence, thereby clamping the upper longitudinal member and the contact wall.
[0010] Such an assembly allows to reduce the height of the assembly and the horizontal orientation of the screw-nut system ensures that it works only under tension.
[0011] Advantageously, the engine pylon comprises side walls on either side of the upper longitudinal member, and the assembly comprises two shear pins, one of which is inserted into a first aperture in the contact wall and a second aperture in the side wall, and the other of which is inserted into the first aperture in the contact wall and a second aperture in the other side wall.
[0012] Advantageously, the shear pins are mounted to be fastened in corresponding apertures and the screws are mounted with play in corresponding holes.
[0013] Advantageously, the assembly comprises an intermediate wall arranged between the contact wall and the upper longitudinal member and, for each screw, the intermediate wall is traversed by an intermediate hole through which the screw passes and, when a shear pin is present, by an intermediate aperture through which the shear pin passes.
[0014] Advantageously, the upper longitudinal member is pierced by at least one third hole perpendicular to the longitudinal direction in which the second hole opens, and the nut is a cylindrical nut received in the third hole.
[0015] The invention also proposes an aircraft comprising a wing and an assembly according to one of the aforementioned variants. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] The above and other features of the present invention will become more apparent upon reading the following description of exemplary embodiments given with reference to the accompanying drawings, in which:
[0017] Figure 1 is a side view of an aircraft according to the present invention;
[0018] Figure 2 is a perspective view of an assembly according to a first embodiment of the present invention;
[0019] Figure 3 is a perspective view of an assembly according to a second embodiment of the present invention;
[0020] Figure 4 yes Figure 3 A cross-sectional view of the component along plane IV; and
[0021] Figure 5 It is a front view of a wing longitudinal member of an assembly according to the invention without an engine pylon. DETAILED DESCRIPTION
[0022] In the following description, position-related terms are considered relative to the aircraft in the forward position, i.e. Figure 1 As shown, arrow F indicates the forward direction.
[0023] Figure 1An aircraft 100 is shown having a fuselage 102 , wings 108 arranged on either side of the fuselage, and engines 105 , in particular turbojet engines, which are fastened below the fuselage by means of engine pylons 104 which in turn are fastened to the wings 108 .
[0024] In the following description and for the sake of convention, X refers to the longitudinal direction of the engine pylon 104, which is in the forward direction of the aircraft 100 and is oriented approximately parallel to the longitudinal axis of the aircraft 100, Y refers to the lateral direction of the engine pylon 104, which is horizontal when the aircraft 100 is on the ground, and Z refers to the vertical direction or vertical height when the aircraft 100 is on the ground, and these three directions X, Y and Z are at right angles to each other.
[0025] exist Figure 1 In the embodiment of the invention shown in FIG. 1 , the aircraft 100 includes an engine 105 under each wing 108 of the aircraft 100 , but it is also possible to have multiple engines under each wing 108 .
[0026] The wing 108 comprises in particular a longitudinal member 106 extending parallel to the longitudinal direction X. The longitudinal member 106 of the wing 108 has a contact wall 106a extending in a plane substantially perpendicular to the longitudinal direction X.
[0027] Figure 2 A first embodiment of an assembly 250 is shown located between the longitudinal member 106 of the wing 108 and the engine pylon 204. Figure 3 and Figure 4 A second embodiment of an assembly 350 between the longitudinal member 106 of the wing 108 and the engine pylon 304 is shown. The difference between the first and second embodiments is the shape of the upper longitudinal member 204a, 304a of the engine pylon 204, 304 and its fixing to the longitudinal member 106 of the wing 108.
[0028] The engine pylon 204, 304 is in the form of a box, which in this example includes an upper longitudinal member 204a, 304a, a lower longitudinal member 204b, 304b and two side walls 204c-d, 304c-d. The walls and the longitudinal members are fixed to each other to form a box, the vertical cross section of which is generally trapezoidal. Each longitudinal member 204a-b, 304a-b and each side wall 204c-d, 304c-d extends in a plane generally parallel to the longitudinal direction X, that is, generally perpendicular to the contact wall 106a. The engine pylon 204, 304 is generally symmetrical with respect to the vertical middle plane XZ.
[0029] The side walls 204c-d, 304c-d are arranged on both sides of the upper longitudinal members 204a, 304a.
[0030] The contact wall 106a is penetrated by a plurality of first holes 401, wherein each hole passes through the contact wall 106a and is parallel to the longitudinal direction X, ie perpendicular to the contact wall 106a.
[0031] The engine pylons 204 , 304 are arranged at the ends of the longitudinal members 106 of the wing 108 in the longitudinal direction X, ie extend from each other in the longitudinal direction X. Thus, the engine pylons 204 , 304 extend the longitudinal members 106 of the wing 108 in the longitudinal direction X.
[0032] For each first hole 401 , the upper longitudinal member 204 a , 304 a is pierced by a second hole 402 , also parallel to the longitudinal direction X and aligned with the first hole 401 in the assembled position.
[0033] In the first embodiment of the present invention, the second hole is created in an angle piece 210 of the upper longitudinal member 204a, wherein the angle piece 210 is parallel to the contact wall 106a.
[0034] In the second embodiment of the invention, the second hole 402 is produced from the third hole 308 produced in the upper longitudinal member 304 a perpendicularly to the longitudinal direction X. Thus, the second hole 402 opens into the third hole 308 .
[0035] The third hole 308 opens in the upper surface area of the upper longitudinal member 304a and is preferably a blind hole.
[0036] In the same way, the side walls 204 c - d , 304 c - d comprise an angle piece 212 , 312 parallel to the contact wall 106 a and also traversed by a second hole aligned with a first hole parallel to the longitudinal direction X of the contact wall 106 a .
[0037] The fixing of the engine pylon 204, 304 to the longitudinal member 106 of the wing 108 is provided by a screw-nut system. Thus, the assembly 250, 350 comprises a nut 206, 406 and a screw 208 for each pair of aligned first holes 401 and second holes 402. The screw 208 is screwed into the nut 206, 406 successively through the first hole 401 of the contact wall 106a and the second hole 402 of the upper longitudinal member 204a, 304a, thereby clamping the upper longitudinal member 204a, 304a and the contact wall 106a between the head of the screw 208 and the nut 206, 406. With this arrangement, the height of the assembly is reduced due to the alignment of the longitudinal member 106 of the wing 108 and the engine pylon 204, 304 and their orientation parallel to the longitudinal direction X, and each screw-nut system works only in tension, withstanding axial forces in the longitudinal direction X, such as thrust. The connection between the engine pylons 204, 304 and the longitudinal member 106 of the wing 108 is thus implemented in a single interface plane, namely the plane of the contact wall 106a, where the screw-nut system is arranged, so as to transmit the forces generated by the engine 105 to the wing 108 while ensuring that this joint does not separate.
[0038] exist Figure 2 and Figure 3 In the embodiment of the invention shown, the assembly 250, 350 also includes shear pins 214, 314, which are symmetrically arranged on both sides of the vertical median plane XZ, and thus on both sides of the upper longitudinal member 204a, 304a. Thus, one shear pin 214, 314 is located on the port side and the other is located on the starboard side. Each shear pin 214, 314 is also parallel to the longitudinal direction X.
[0039] Figure 5 The longitudinal member 106 of the wing 108 is shown, and more specifically the contact wall 106a. In this embodiment, there are eleven screw-nut systems, of which three are in the region of the upper longitudinal member 204a, 304a and four are on each side wall 204c-d, 304c-d. Each shear pin 214, 314 is inserted into a first aperture 502a-b of the contact wall 106a, i.e. the first aperture 502a on the port side and the first aperture 502b on the starboard side, and a second aperture in the side wall 204c-d, 304c-d, here considered is the corner piece 212, 312 of the side wall 204c-d, 304c-d of the engine pylon 204, 304. The first aperture 502a-b and the second aperture associated with each other are aligned in the assembled position. The first aperture 502a-b and the second aperture are arranged on both sides of the vertical middle plane XZ.
[0040] Thus, one shear pin 214, 314 is inserted into the first aperture 502a of the contact wall 106a and the second aperture of the side walls 204c-d, 304c-d, and the other shear pin 214, 314 is inserted into the first aperture 502b of the contact wall 106a and the second aperture of the other side wall 204d-c, 304d-c.
[0041] The shear pins 214, 314 withstand shear forces and engine torque and are mounted to be tightened in corresponding apertures, while the screws 208 are mounted with clearance in corresponding holes, including the intermediate aperture and the intermediate hole 410 described below.
[0042] By such an arrangement, in the event of a screw-nut system breaking, the other screw-nut systems compensate for this and ensure the transmission of the axial force, and in the event of a shear pin 214, 314 breaking, the longitudinal member 106 of the wing 108 and the engine pylon 204, 304 can pivot around the other shear pin 314, 214, and the rotation is stopped by the screw-nut system, thereby transmitting the axial force as well as the shear force and the engine torque.
[0043] exist Figure 2 and Figure 3 In the illustrated embodiment of the invention, the assembly 250, 350 further comprises an intermediate wall 110 disposed between the contact wall 106a and the upper longitudinal member 204a, 304a.
[0044] For each screw 208 , the intermediate wall 110 is traversed by an intermediate hole 410 through which the screw 208 passes.
[0045] When the shear pins 214, 314 are present, for each of them, the intermediate wall 110 is penetrated by the intermediate aperture through which the shear pins 214 and 314 pass. Figure 3 and Figure 4 In the illustrated embodiment of the present invention, the nut 406 is a barrel nut that is received in the third hole 308 to prevent the nut from rotating when the screw 208 is tightened.
[0046] With this special arrangement, since there is no need to provide space for the angle piece 210 , the thickness of the upper longitudinal member 304 a is increased, thereby optimizing the inertia of the engine mount 304 so that a greater force can be transmitted to the engine mount 304 .
Claims
1. An assembly (250, 350) for an aircraft (100), the aircraft comprising a wing (108), the assembly (250, 350) comprising: - a longitudinal member (106) of a wing (108), wherein the longitudinal member (106) has a contact wall (106a) pierced by a plurality of first holes (401), each first hole (401) passing through the contact wall (106a) and parallel to a longitudinal direction (X) perpendicular to the contact wall (106a); an engine pylon (104, 204, 304) arranged at the end of the longitudinal member (106) in the longitudinal direction (X) and having an upper longitudinal member (204a, 304a) which is generally perpendicular to the contact wall (106a) and is pierced, for each first hole (401), by a second hole (402) parallel to the longitudinal direction (X) and aligned with the first hole (401); and - a nut (206, 406) and a screw (208) for each pair of aligned first holes (401) and second holes (402), wherein the screw (208) is screwed into the nut (206, 406) via the first hole (401) and the second hole (402) in sequence, thereby clamping the upper longitudinal member (204a, 304a) and the contact wall (106a).
2. The assembly (250, 350) according to claim 1, characterized in that The engine pylon (204, 304) comprises side walls (204c-d, 304c-d) on both sides of the upper longitudinal member (204a, 304a), and wherein the assembly (250, 350) comprises two shear pins (214, 314), one of which is inserted into a first hole (502a-b) of the contact wall (106a) and a second hole of the side wall (204c-d, 304c-d), and the other shear pin is inserted into the first hole (502a-b) of the contact wall (106a) and the second hole of the other side wall (204d-c, 304d-c).
3. The assembly (250, 350) according to claim 2, characterized in that The shear pins (214, 314) are mounted to be fastened in the corresponding apertures, and the screws (208) are mounted with clearance in the corresponding holes.
4. The assembly (250, 350) according to claim 1, characterized in that The assembly comprises an intermediate wall (110) arranged between the contact wall (106a) and the upper longitudinal member (204a, 304a), wherein, for each screw (208), the intermediate wall (110) is penetrated by an intermediate hole (410) through which the screw (208) passes, and wherein, when a shear pin (214, 314) is present, for each shear pin (214, 314), the intermediate wall (110) is penetrated by an intermediate aperture through which the shear pin (214, 314) passes.
5. The assembly (250, 350) according to claim 1, characterized in that The upper longitudinal member (304a) is penetrated by at least one third hole (308), the third hole (308) being perpendicular to the longitudinal direction (X) towards which the second hole (402) opens, and wherein the nut (406) is a cylindrical nut received in the third hole (308).
6. An aircraft (100) comprising a wing (108) and an assembly (250, 350) according to claim 1.