An aircraft assembly having a pylon and a nacelle comprising a cowl fitted with a tensioning system and a centering system

Abstract

The invention relates to an assembly of a pylon and a nacelle of an aircraft, in which the nacelle has a structural part, a windshield (220), two centering systems (302) and two tensioning systems (304). Each tensioning system (304) comprises a first fitting (306) attached to the structural part and having an engagement wall (310) through which a bore (312) passes, a second fitting (308) attached to the windshield (220), a threaded rod (314) articulated on the second fitting (308) and passing through the bore (312), a spring member (318) fitted on the threaded rod (314) against the engagement wall (310) on the opposite face of the second fitting (308), and a stop device (320) blocking the spring member (318). Each centering system (302) comprises a first fitting (330) attached to the structural part and having a hole (334), and a second fitting (332) attached to the windshield (220) and carrying a shaft (336) housed in the hole (334). By virtue of this arrangement, the bulk of the attachment devices is reduced.

Description

Technical Field

[0001] The present invention relates to a component for an aircraft, wherein the component has a pylon and a nacelle, the nacelle itself including a windshield equipped with a tensioning system and a centering system, and to an aircraft including such a component. Background Technology

[0002] Aircraft typically consist of a fuselage with wings attached to either side. Each wing supports at least one mounting pylon, which in turn supports the engine and nacelle that form the turbine. The nacelle forms the aerodynamic surface surrounding the engine. The mounting pylon is attached between the wing structure and the nacelle.

[0003] Figure 2 A perspective view of a propulsion system 200 is shown, which includes an engine 202 and a nacelle 204. The engine 202 is represented here by its nozzle. The nacelle 204 has an air intake 206 and is attached to the wing via a pylon 208.

[0004] The nacelle 204 has a structural section attached to the pylon 208 and carrying multiple fairings, including: an intake fairing 210 surrounding the air intake 206; side fairings 212 on both sides of the nacelle 204, specifically fan fairings and thrust reverser fairings; and an upper fairing 214 providing a fairing around the joint between the structural section of the pylon 208 and the nacelle 204.

[0005] The nacelle 204 also has a windshield 220, which is an aerodynamic fairing that aerodynamically connects the intake fairing 210, the side fairings 212 and the upper fairing 214.

[0006] In the case of existing technology, the windshield 220 is attached by a relatively large and complex attachment device.

[0007] Therefore, there is a need to find an implementation that limits the size of the attachment device and makes installation and adjustment easier. Summary of the Invention

[0008] The object of the present invention is to provide a component for an aircraft, wherein the component has a pylon and a nacelle, the nacelle including a windshield equipped with a simple and easy-to-implement tensioning system and a centering system.

[0009] To this end, a component for aircraft has been proposed, the component having a pylon and a generally cylindrical nacelle designed to surround the aircraft engine.

[0010] The nacelle has a central plane and includes:

[0011] - Structural part, which is attached to the bracket at the joint between the bracket and the structural part;

[0012] - Air intake fairing, which surrounds the air intake of the nacelle;

[0013] - Side fairings, which are positioned on both sides of the center plane of the nacelle;

[0014] - Upper fairing, which provides a rectifier around the joint;

[0015] - Windshield, comprising an arc-shaped fairing that aerodynamically connects the intake fairing, side fairings, and upper fairing; and

[0016] - Attachment device, which includes two centering systems and two tensioning systems, wherein the two tensioning systems are located on both sides of the nacelle's center plane and between the two centering systems;

[0017] Each tensioning system includes:

[0018] - The first tensioning system component, which is attached to the structural part;

[0019] - The second tensioning system component is attached to the windshield;

[0020] - A threaded rod, the first end of which is hingedly mounted on the second tensioning system fitting;

[0021] - Spring components; and

[0022] - Stopping device;

[0023] The first tensioning system fitting has a mating wall through which the orifice passes, and the mating wall has a face oriented toward the second tensioning system fitting and an opposite face;

[0024] The threaded rod passes through the orifice, the spring component is mounted on the threaded rod and positioned opposite to the second tensioning system fitting by means of the engaging wall, and the stop device prevents the spring component from moving.

[0025] Each centering system includes:

[0026] - The first centering system component, which is attached to the structural part; and

[0027] - Second centering system component, which is attached to the windshield;

[0028] One of the fittings has a hole, and another fitting carries a shaft that is accommodated in the hole.

[0029] This arrangement reduces the size of the attachment device.

[0030] Advantageously, the hinge of the threaded rod is achieved by a ball joint system mounted on the second tensioning system fitting.

[0031] Advantageously, the spring components are stacked disc washers (Bell washers).

[0032] Advantageously, the stop device includes two nuts screwed onto the second end of the threaded rod.

[0033] Advantageously, the shaft is in the form of a threaded rod, and the centering system includes a nut screwed onto the threaded rod, thereby clamping either the first centering system component or the second centering system component in the middle.

[0034] The present invention also proposes an aircraft having components according to one of the aforementioned variations. Attached Figure Description

[0035] The above and other features of the invention will become more apparent from the following description of exemplary embodiments, which is given in conjunction with the accompanying drawings, in which:

[0036] Figure 1 This is a side view of an aircraft according to the present invention;

[0037] Figure 2 It is a 3D view of the nacelle; and

[0038] Figure 3 This is a three-dimensional front view of the windshield according to the present invention;

[0039] Figure 4 This is a front view of the tensioning system according to the present invention;

[0040] Figure 5 It is along Figure 4 A cross-sectional view of line V-V in the diagram;

[0041] Figure 6 This is a front sectional view of the centering system according to the present invention; and

[0042] Figure 7 yes Figure 6 A magnified view of detail VII. Detailed Implementation

[0043] In the following description, the position-related terms refer to those installed in forward motion, i.e., as... Figure 1 The nacelle shown is on the aircraft.

[0044] Figure 1An aircraft 100 is shown, comprising a fuselage 102, with wings 104 attached to both sides of the fuselage 102. A mounting pylon 208 is attached below each wing 104 to which a propulsion system 200 is mounted. The propulsion system 200 includes a generally cylindrical nacelle and an engine surrounded by the nacelle. Thus, the assembly according to the invention has a pylon 208 and a nacelle.

[0045] In the following description, generally, the X-axis is the longitudinal axis of the nacelle, which is positive in the forward direction of the aircraft 100 and is also parallel to the longitudinal axis of the aircraft 100; the Y-axis is the transverse axis of the nacelle, which is horizontal when the aircraft 100 is on the ground; the Z-axis is the vertical axis or vertical height of the aircraft 100 when it is on the ground. The three directions X, Y, and Z are orthogonal to each other, forming an orthogonal reference frame. The nacelle therefore has a longitudinal intermediate plane XZ, which is vertical and parallel to the longitudinal axis X, and divides the nacelle into two parts, namely the left part and the right part.

[0046] Figure 2 A perspective view of a propulsion system 200 is shown, which is similar to existing propulsion systems except for the device used to attach the windshield 220.

[0047] Therefore, the propulsion system includes a motor 202 and a nacelle 204, the structural part of which is attached to the pylon 208 at the joint between the pylon 208 and the structural part. Figure 2 In an exemplary embodiment, the nacelle 204 includes a plurality of fairings (or rectifiers) attached to its structure for generating aerodynamic surfaces.

[0048] Therefore, the nacelle 204 includes an intake fairing 210 around its air intake 206, and the nacelle 204 also includes side fairings 212 on both sides of the midplane XZ of the nacelle 204, and an upper fairing 214 above the nacelle 204, which provides a rectifier around the joint between the hangar 208 and the structure.

[0049] The nacelle 204 has an aerodynamic windshield 220, which includes an arc-shaped fairing that aerodynamically connects the intake fairing 210, the side fairings 212, and the upper fairing 214. The fairing is arc-shaped to match the shape of the nacelle 204.

[0050] The windshield 220 is attached by an attachment device, which includes a centering system and a tensioning system, ensuring that the windshield 220 is positioned and stably pushed.

[0051] Figure 3 The windshield 220 is shown, wherein the attachment device includes two centering systems 302 and two tensioning systems 304.

[0052] like Figure 3 As shown, the two tensioning systems 304 are located on both sides of the central plane of the nacelle 204 and between the two centering systems 302.

[0053] This arrangement provides the possibility of keeping the windshield 220 in place on the Z-axis to prevent it from tearing while moving the windshield 220 about the horizontal axis Y.

[0054] Figure 4 and 5 The tensioning system 304 is shown. Figure 6 and 7 The centering system 302 is shown.

[0055] Tensioning system 304 includes a first tensioning system fitting 306 attached to a structural portion of nacelle 204 and a second tensioning system fitting 308 attached to windshield 220. The structural portion of nacelle 204 is represented here by wall 50, which may be a wall extending directly from the structural portion or a wall extending from another fairing further attached to the structural portion.

[0056] The first tensioning system fitting 306 has a mating wall 310 through which an orifice 312 passes. The mating wall 310 has a face oriented toward the second tensioning system fitting 308 and an opposite face.

[0057] The tensioning system 304 also includes a threaded rod 314, the first end of which is hingedly mounted on the second tensioning system fitting 308. The hinge of the threaded rod 314 is achieved by a ball joint system 316, which is mounted on the second tensioning system fitting 308, and the first end of the threaded rod 314 is fixed to the ball joint system 316. The arrangement with the ball joint system 316 allows for greater flexibility.

[0058] The tensioning system 304 also includes a spring component 318 mounted on the threaded rod 314 and a stop device 320 for holding the spring component 318 in place on the threaded rod 314.

[0059] Once the tensioning system 304 is installed, the threaded rod 314 passes through the orifice 312, the spring component 318 is mounted on the threaded rod 314 and positioned on the side opposite to the engagement wall 310 and the second tensioning system accessory 308, and the stop device 320 prevents the spring component 318 from moving.

[0060] As from Figure 5 As can be seen more clearly, the spring component 318 is tensioned by being clamped between the engagement wall 310 and the stop device 320.

[0061] The spring component 318 can be, for example, a compression spring, or, as in this case, a stack of disc washers.

[0062] exist Figures 3 to 5 In the embodiment of the invention shown, the stop device 320 includes two nuts screwed onto the second end of the threaded rod 314, but it may also include any other components that hold the spring component 318 in place.

[0063] The greater the tension in the spring component 318, the greater the restoring force applied to the windshield 220. Therefore, the tensioning system 304 can counteract the suction force acting on the windshield 220. The tension of the spring component 318 can be modified by changing the spring component 318 or by modifying the clamping of the nut of the stop device 320.

[0064] The centering system 302 includes a first centering system accessory 330 attached to a structural part of the nacelle 204 and a second centering system accessory 332 attached to the windshield 220.

[0065] One of the fittings, in this case, is the first centering system fitting 330, having a hole 334, while the other fitting, in this case, is the second centering system fitting 332, carrying a shaft 336, which is received in the hole 334. When the shaft 336 is introduced into the hole 334, the axis of the hole 334 is parallel to the axis of the shaft 336, and these axes are generally parallel to the direction along which the windshield 220 is installed.

[0066] Each shaft 336 is introduced into the corresponding hole 334 so that the windshield 220 can be positioned. Rotation about the X-axis of the windshield 220 relative to the air inlet is limited by two shafts 336 mounted on both sides of the windshield 220.

[0067] While installing each centering system 302, the installation of the tensioning system 304 includes: introducing a threaded rod 314 into the orifice 312, positioning the spring member 318 along the threaded rod 314 by stably pressing the spring member 318 against the opposite side of the engagement wall 310 and the second tensioning system accessory 308, and then installing a stop device 320 at the second end of the threaded rod 314.

[0068] Therefore, the attachment device is relatively compact because the centering system 302 and the tensioning system 304 are partially mounted on the windshield 220, and installation and adjustment become easier considering that all systems are concentrated around the windshield 220.

[0069] In the embodiment of the invention presented herein, positioning of the spring component 318 along the threaded rod 314 includes mounting a disc washer through the second end of the threaded rod 314.

[0070] In the embodiment of the invention presented herein, the installation of the stop device 320 includes tightening two nuts.

[0071] Figure 7 The gap “J” between the diameter of the hole 334 and the diameter of the shaft 336 is shown. The size of this gap “J” allows the position of the windshield 220 to be controlled.

[0072] In the embodiments of the invention presented herein, the hole 334 and the shaft 336 are circular so as to have the same clearance "J" in all directions, especially in the X and Y directions, but the shape of the hole 334 and / or the shaft 336 may also be adjusted in order to accommodate different clearances "J" depending on the direction.

[0073] To enhance the holding force of the windshield 220, the shaft 336 can be in the form of a threaded rod, and the centering system 302 includes a nut screwed onto the threaded rod, which clamps the first centering system accessory 330 or the second centering system accessory 332 in the middle.

Claims

1. A component for an aircraft (100), the component having a pylon (208) and a generally cylindrical nacelle (204) intended to surround an engine (202) of the aircraft (100), wherein, The nacelle (204) has a mid-plane (XZ) and includes: - A structural part, which is attached to the bracket (208) at the joint between the bracket (208) and the structural part. - Air intake fairing (210), the air intake fairing surrounding the air intake (206) of the nacelle (204); - Side fairings (212), which are disposed on both sides of the central plane of the nacelle (204); - Upper fairing (214), which provides a rectifier around the joint; - A windshield (220) comprising an arc-shaped fairing aerodynamically connecting the intake fairing (210), the side fairings (212), and the upper fairing (214); and - an attachment device comprising two centering systems (302) and two tensioning systems (304), wherein the two tensioning systems (304) are disposed on both sides of the intermediate plane of the nacelle (204) and between the two centering systems (302); Each tensioning system (304) includes: - The first tensioning system accessory (306) is attached to the structure; - A second tensioning system accessory (308) is attached to the windshield (220); - A threaded rod (314), the first end of which is hingedly mounted on the second tensioning system accessory (308); - Spring component (318); and - Stop device (320); The first tensioning system fitting (306) has a mating wall (310) through which the orifice (312) passes, the mating wall having a face oriented toward the second tensioning system fitting (308) and an opposite face; The threaded rod (314) passes through the orifice (312), the spring component (318) is mounted on the threaded rod (314) and positioned opposite to the second tensioning system accessory (308) by the engagement wall (310), and the stop device (320) prevents the spring component (318) from moving. Each centering system (302) includes: - First centering system component (330), which is attached to the aforementioned structural part; and - Second centering system accessory (332), which is attached to the windshield (220); In this system, one of the first centering system component and the second centering system component has a hole (334), and the other of the first centering system component and the second centering system component carries a shaft (336) accommodated in the hole (334).

2. The component according to claim 1, characterized in that, The hinge of the threaded rod (314) is achieved by a ball joint system (316) mounted on the second tensioning system accessory (308).

3. The component according to claim 1, characterized in that, The spring component (318) is a stack of disc washers.

4. The component according to claim 1, characterized in that, The stop device (320) includes two nuts screwed onto the second end of the threaded rod (314).

5. The component according to claim 1, characterized in that, The shaft (336) is in the form of a threaded rod, and the centering system (302) includes a nut screwed onto the threaded rod, thereby clamping the first centering system accessory (330) or the second centering system accessory (332) of the centering system (302) in the middle.

6. An aircraft (100) having the components according to claim 1.

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