Device for joining first element of aircraft to second element of aircraft, and aircraft

Abstract

The invention relates to a device for joining a first element of an aircraft to a second element of the aircraft and the aircraft. The invention relates to a device (1) comprising a first connecting portion intended to be integral with said first element and a second connecting portion (3) intended to be integral with said second element, the device (1) comprising an elliptical ring (10), the device (1) comprising a connecting pin (9) arranged in the elliptical ring (10) to be locked in the elliptical ring (10) in a first direction (Z) and free in a second direction (X), the device (1) comprises at least one sheet (14, 15) made of an elastomeric material into which the connecting shaft is inserted in order to reduce the movement of the connecting shaft (9) in the second direction (X).

Description

Technical Field

[0001] This invention relates to a coupling device for aircraft. Background Technology

[0002] During flight, especially during cruise, aircraft are subjected to external temperatures of up to -50°C, while the internal temperature remains typically between 20°C and 24°C. This large temperature difference subjectes the aircraft structure to high stress, such as thermal compression in the longitudinal direction, which significantly leads to forced deformation of the cockpit floor relative to the fuselage and can potentially damage the cockpit floor.

[0003] The purpose of this invention is to at least partially overcome this drawback. Summary of the Invention

[0004] To this end, an apparatus is proposed for engaging a first element of an aircraft to a second element of an aircraft. The apparatus includes a first connecting portion intended to be fastened to the first element and a second connecting portion intended to be fastened to the second element. The first connecting portion includes an elliptical ring. The apparatus includes a connecting pin arranged in the elliptical ring to be fixed in the ring along a first direction and free along a second direction. The apparatus includes at least one pad made of an elastomeric material, into which the connecting pin is inserted to reduce displacement of the connecting pin along the second direction.

[0005] The anisotropic behavior of the device claimed in this invention, which is fixed in a first direction and capable of slow translational movement in a second direction, prevents significant loads in the connecting device 1 caused by deformation of the floor plate in the second direction when the aircraft is in flight. Furthermore, in the first vertical direction, loads from the cockpit floor plate can be rigidly transferred from the longitudinal beams to the transverse beams through mechanical contact between the metal parts, particularly between the connecting pins and the elliptical rings.

[0006] According to another perspective, the second direction is orthogonal to the first direction.

[0007] On the other hand, the diameter of the connecting pin is the same as the width of the elliptical ring.

[0008] According to another aspect, the device includes at least two cylindrical rings stacked along a connecting pin, each of the cylindrical rings being inserted into the at least one elastomeric pad.

[0009] According to another aspect, the device includes three stacked cylindrical rings.

[0010] According to another aspect, the device includes at least one first elastomeric pad and at least one second elastomeric pad arranged on both sides of an elliptical ring, with a connecting pin inserted into each elastomeric pad.

[0011] According to another perspective, the elastomer has a stiffness of less than or equal to 3000 N / mm.

[0012] On the other hand, the connecting pin is made of steel.

[0013] On the other hand, the elliptical ring is made of cupronickel.

[0014] The present invention also relates to an aircraft comprising the connecting device described above.

[0015] According to another aspect, the first element is a transverse component of the fuselage, such as a transverse component of the cockpit floor, and the second element is a longitudinal fuselage beam.

[0016] The present invention also relates to an apparatus for engaging a first element of an aircraft to a second element of an aircraft, the apparatus comprising a first connecting portion intended to fasten to the first element and a second connecting portion intended to fasten to the second element, the apparatus comprising an elliptical housing, the apparatus comprising a connecting pin disposed in an elliptical ring, the apparatus comprising a device for fixing the pin along a first direction, the device being shaped such that the pin is rigidly supported against the elliptical housing along the first direction, the apparatus further comprising a device for fixing the pin along a second direction orthogonal to the first direction, the device being shaped such that the pin is flexibly supported within the elliptical housing. Attached Figure Description

[0017] Other features, details, and advantages will become clear by reading the following detailed description and by studying the accompanying drawings, in which: Figure 1

[0018] Figure 1 This is a schematic side view of a joining device for joining a first panel of an aircraft to a second panel of an aircraft according to an embodiment of the present invention. Figure 2

[0019] Figure 2 yes Figure 1 A schematic diagram of the cross-section of the connecting device in direction AA. Detailed Implementation

[0020] The examples and associated conditions detailed herein are primarily intended to help the reader understand the principles of the invention, and not to limit the scope of the invention to these specific examples and conditions. It will be understood that those skilled in the art will envision various arrangements, although not explicitly described or represented herein, that embody the principles of the invention and are included within its spirit and scope.

[0021] Furthermore, for ease of understanding, the following description illustrates a relatively simplified implementation of the invention. As those skilled in the art will understand, other implementations of the invention may be more complex.

[0022] In some cases, examples of modifications to the invention may also be presented. This is done merely to aid understanding and, likewise, not to limit the scope of the invention or to impose any restrictions on it. These modifications are not exhaustive, and those skilled in the art can make other modifications while still remaining within the scope of the invention.

[0023] Furthermore, all statements below relating to the principles, aspects, and implementations of the invention, as well as specific examples thereof, are intended to cover both structural and functional equivalents of the invention, whether they are currently known or to be developed in the future.

[0024] In the figure, orthogonal reference frames (X, Y, Z) have been illustrated to simplify the understanding of the description of the invention. Direction Z corresponds to the vertical direction (yaw axis), direction X corresponds to the longitudinal direction of the aircraft (roll axis), and direction Y corresponds to the lateral direction (pitch axis).

[0025] As shown in the figure, the subject of the present invention is an apparatus for joining an element of an aircraft to a second element of the aircraft, the apparatus being labeled 1 in the figure.

[0026] In the illustrated embodiment, and in a non-limiting manner, the first element is, for example, a transverse member of the cockpit floor of an aircraft, and the second element is a longitudinal beam.

[0027] The connecting device 1 includes a first part 2 intended to be fastened to a transverse member and a second part 3 intended to be fastened to a longitudinal beam.

[0028] In the illustrated embodiment, and in a non-limiting manner, the first element 2 is a connecting fitting, and the second element 3 is a fork-shaped member.

[0029] As shown in the figure, the assembly 2 is fastened to the transverse component 4 of the aircraft by a set of corner brackets 5, for example by screwing or riveting.

[0030] As shown in the figure, the fork-shaped member 3 includes a main branch 6, which is divided into two branches 7 and 8 in the direction X. These two branches 7 and 8 are called the upper branch and the lower branch, respectively. The upper branch and the lower branch are spaced apart from each other in order to define the internal volume V of the fork-shaped member 3.

[0031] The connecting device 1 includes a connecting pin 9 extending longitudinally in the Y direction. The connecting pin 9 is preferably made of 45NCD16 steel.

[0032] As shown in the figure, the fitting 1 includes a housing with an elliptical ring 10, into which a connecting pin 9 is inserted. Preferably, the elliptical ring 10 is made of cupronickel to reduce the coefficient of friction between the connecting pin 9 and the elliptical ring 10, thereby minimizing the impact of wear between the connecting pin 9 and the elliptical ring 10.

[0033] The dimensions of the connecting pin 9 and the elliptical ring 10 are such that pin 9 is supported against the elliptical ring 10 along the Y direction, while pin 9 is free along the X direction, as shown below. Figure 1 and Figure 2 As clearly shown in the image. Figure 1 As shown, the diameter D of pin 9 matches the width L of ring 10, which helps to fix the pin along the Y and Z directions. Figure 1 and Figure 2 As shown, the diameter D of pin 9 is strictly smaller than the length L of ring 10, which makes pin 9 free in the direction X.

[0034] The connecting device 1 includes a rigid fixing device 11 for securing the connecting pin 9 against the elliptical ring 10 in the Z direction. The rigid fixing device 11 includes, for example, a nut 12 positioned against the elliptical ring 10.

[0035] like Figure 1 and Figure 2 As shown, the connecting pin 9 is arranged in at least one plane (X, Y) at a certain distance from the elliptical ring 10.

[0036] The coupling device 1 further includes a flexible fixing device 13 for securing the connecting pin 9 in the X direction. The flexible fixing device 13 includes at least one pad made of an elastomeric material, which is fastened to the coupling fitting 2. The elastomeric material advantageously has low stiffness, preferably less than or equal to 3000 N / mm. Each pad restricts displacement of the connecting pin 9 in the X direction.

[0037] In the illustrated embodiment, the connecting device 1 includes two elastomeric pads 14 and 15 arranged within the internal volume V of the fork-shaped member 3. Pad 14 is arranged abutting against the connecting fitting 2, the upper branch 7, and the elliptical ring 10. Pad 15 is arranged abutting against the connecting fitting 2, the lower branch 8, and the elliptical ring 10.

[0038] The connecting device 1 also includes at least one cylindrical ring for clamping the connecting pin 9. In the illustrated embodiment, the connecting device 1 includes three cylindrical rings stacked in the Y direction, referred to as the upper ring 16, the center ring 17, and the lower ring 18, respectively. Each of the cylindrical rings 16 to 18 is preferably made of 45NCD16 steel. Stacking the cylindrical rings 16 to 18 in the Y direction allows the pin 9 to be clamped without prestressing the fork 3. The mechanical contact between each cylindrical ring and the connecting pin 9 is part of the rigid fixing device 11.

[0039] Especially Figure 2 As shown, the upper cylindrical ring 16 is supported against the elastomeric pad 14, while the lower cylindrical ring 18 is supported against the elastomeric pad 15. The connecting pin 9 is supported against the pads 14 and 15 to ensure flexible support of the pin 9 in the X direction.

[0040] like Figure 2 As shown, the connecting pin 9 passes through the upper branch 6 and lower branch 7 of the fork-shaped member 3, the elliptical ring 10, and the elastomer pads 14 and 15 along the Y direction.

[0041] Therefore, the rigid fastening device 11—including the rigid contact between the pin and the metal parts (branches 6 and 7 of the fork 3, cylindrical rings 16 to 18, and elliptical ring 10) and the fastening by a nut or washer—ensures zero degree of freedom in the Z direction. The flexible fastening device 13, including each elastomeric pad 14 and 15, ensures a non-zero degree of freedom in the X direction. In other words, the device 1 enables the formation of a connection between aircraft components that allows displacement in one direction (direction X in the figure) through the use of elastomeric materials, while preventing displacement in one or more other perpendicular directions (directions Y and Z in the figure) through rigid mechanical contact. The device 1—which includes both elastomeric pads and rigid contact between the metal parts (connecting pin and fork, connecting pin and elliptical ring)—ensures the anisotropic behavior of the device 1. In the longitudinal direction (X), the elastomer pads 14 and 15 allow for smooth displacement due to the low stiffness of the elastomer (less than 3000 N / mm), ensuring that deformation of the floor plate does not generate significant loads in the coupling device 1 when the aircraft is in flight. In the vertical direction (Z), the load from the cockpit floor plate is rigidly transferred from the longitudinal beam to the transverse beam through the mechanical contact between the metal parts, particularly the connecting pin 9, the cylindrical ring 13, and the elliptical ring 10.

[0042] In addition, the fitting 2 is held on the transverse member 4 by the corner bracket 5 so as to redirect the force applied to the cockpit floor back to the hybrid elastomer-metal joint.

[0043] Those skilled in the art can modify and improve the above-described implementations of the present invention. In particular, the described embodiments and variations can be combined, provided that these embodiments and variations are not incompatible. The above description is illustrative by way of example and not restrictive. Therefore, the scope of the present invention is defined only by the scope of the appended claims.

Claims

1. An apparatus for engaging a first element of an aircraft to a second element of an aircraft, the apparatus comprising a first connecting portion (2) intended to be fastened to the first element and a second connecting portion (3) intended to be fastened to the second element, the apparatus (1) comprising an elliptical ring (10), the apparatus (1) comprising a connecting pin (9) arranged in the elliptical ring (10) to be fixed in the elliptical ring (10) along a first direction (Z) and free along a second direction (X), the apparatus (1) comprising at least one pad (14, 15) made of an elastomeric material, the connecting pin being inserted into the at least one pad (14, 15) to reduce displacement of the connecting pin (9) along the second direction (X).

2. The apparatus according to the preceding claim, wherein, The diameter (D) of the connecting pin (9) is the same as the width (L) of the elliptical ring (10).

3. The device according to any one of the preceding claims, the device comprising at least two cylindrical rings (16, 17, 18) stacked along the connecting pin (9), each of the cylindrical rings (16, 17, 18) being inserted into the at least one elastomeric pad (14, 15).

4. The apparatus according to the preceding claim, the apparatus comprising three stacked cylindrical rings (16, 17, 18).

5. The apparatus according to any one of the preceding claims, the apparatus comprising at least one first elastomeric pad (14) and at least one second elastomeric pad (15) disposed on both sides of the elliptical ring (10), the connecting pin (9) being inserted into each of the elastomeric pads (14, 15).

6. The apparatus according to any one of the preceding claims, wherein, The elastomer has a stiffness of less than or equal to 3000 N / mm.

7. The apparatus according to any one of the preceding claims, wherein, The connecting pin (9) is made of steel.

8. The apparatus according to any one of the preceding claims, wherein, The elliptical ring (10) is made of cupronickel.

9. An aircraft comprising a coupling device according to any one of the preceding claims.

10. The aircraft according to the preceding claim, wherein, The first element is a transverse component of the fuselage, such as a transverse component of the cockpit floor, and the second element is a longitudinal fuselage beam.

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