A wing connection structure

Abstract

The present invention relates to a body (2) that is located on the aircraft, at least one wing (3) that is located on the body (2) and extends outwards from the body (2), providing lifting force to the body (2) and allowing the placement of payload on it, a root region (31) that is located on the wing (3) and extends from the body (2) in a dihedral angle, and at least one root bracket (4) that is located on the body (2) and enables the wing (3) to be mounted on the body (2).

Description

[0001] A WING CONNECTION STRUCTURE

[0002] The present invention relates to a wing connection structure that enables the connection of the inclined wing structure to the aircraft.

[0003] In aircraft, the wing is directly connected to the body in the y-axis with a four-point tension bolt. In helicopter-like aircraft, it is possible to connect the wing directly to the body due to the structure of the wing. However, this is not possible in an aircraft using an inclined wing structure. Since the wing is positioned at an angle to the body, it is not possible to mount it at a right angle to the body. Since the connection of the angled wing cannot be made perpendicularly to the body surface, which can be defined as the y-axis, it must be connected on the x-axis, the axis along the body. For this reason, it was necessary to mount the angled wings in a way that they would be located aerodynamically within the wing surface.

[0004] In the American patent document numbered US10106240B2 in the state of the art, an aircraft, a body, and a wing assembly is mentioned. The wing assembly is connected with body-wing connections fixed to the body. During the flight of the aircraft, the aerodynamic forces on the wing assembly create axial, lateral and vertical loads at the body-wing connections, primarily at the aircraft. Additional body loads at the body-wing connections are produced by the pressure inside the body and the body deformation caused by frame bending.

[0005] In the American patent document numbered US201 10089292A1 in the state of the art, a method of joining a wing to an aircraft body by forming a series of fixed lug joints between a body side and a wing side of a wing box structure is mentioned. In said patent document, the joint formation process comprises providing single row protrusions on one side of the joint to be formed and providing corresponding double row protrusions on the other side of the joint to be formed. The space between the opposing protrusions of the double row varies along the row. The wing side and the body side of the wing box structure are brought together in such a way that the protrusions of the single row are placed in the respective spaces between the opposing protrusions of the double row and the protrusions are fixed to form a series of fixed protrusion joints.

[0006] With the wing connection structure developed with the present invention, it is aimed to mount the angled wings to the body using a protruding fork structure.

[0007] Another aim of the present invention is to connect the angled wings with a connection structure in a way that does not affect an aerodynamic structure that allows for flexing movement.

[0008] Another aim of the present invention is to ensure that the angled wing structure is mounted to the body from two different points with at least two fasteners at each point.

[0009] Another aim of the present invention is to provide a secure connection structure against the breakage of one of the fasteners.

[0010] Another aim of the present invention is to ensure that the angled wing structures that cannot be connected perpendicularly to the body are connected in a way that they will be located within the aerodynamic structure.

[0011] The wing connection structure defined in the first claim and the claims dependent on this claim, which is realised to achieve the aim of the invention, comprises a body, at least one wing that is mounted to the body and allows the equipment to be carried, a root region extending from the body in an angled manner, and at least one root bracket that is positioned on the surface of the body facing the wing, and enables the wing to be connected to the body. The wing connection structure which is the subject of the invention comprises at least one protrusion that is located on the root region, is positioned such that the root region faces the root bracket, has a form that almost completely covers the root bracket, thereby carries the load on the wing, and that allows the stress on the wing to be distributed by transferring the load on the wing to the protrusions in a way that provides resistance against the bending of the root region, and a support part that is positioned by the manufacturer between the two protrusions and extends over the root region to act as a bridge.

[0012] In one embodiment of the invention, the wing connection structure comprises a first structural part and a second structural part, which are located on the root region that allows the loads on the wing to be transferred to the body, extending towards the body, and two protrusions that are located on the first structural part and the second structural part parallel to each other and one of which enable the first structural part and the other the second structural part to be placed on the body by means of the root bracket.

[0013] In one embodiment of the invention, the wing connection structure comprises a support part that is located between two opposite protrusions, extending from one protrusion to the other in the form of a bridge, ensuring that the protrusions are positioned horizontally parallel to each other against bending that the load may create, thus transmitting the force resulting from the bending resistance created by the load on it, partly to the root brackets and partly to the wing.

[0014] In one embodiment of the invention, the wing connection structure comprises a support part that is located away from the body so as to be positioned outwards from the body, extending between the first structural part and the second structural part, and provides a rigid structure against each other by distributing the load between the first structural part and the second structural part against the bending caused by the load on the wing.

[0015] In one embodiment of the invention, the wing connection structure comprises at least one bracket hole that is located on the root bracket, and enables the wing to be removably connected to the body, at least one connection hole that is located on the protrusion, and at least one fastener that enables the root bracket and the protrusion to be connected to the body in the axis direction from the tail to the nose region of the aircraft with the help of the bracket hole and the connection hole.

[0016] In one embodiment of the invention, the wing connection structure comprises an end region that is located on the wing and extends from the root region to an anhedral angle with the body, a bend region in the form of an inverted V that is located between the root region and the end region on the wing, connecting the root region and the end region to each other.

[0017] In one embodiment of the invention, it comprises a shell that is located on the wing, almost completely covers the wing and has an aerodynamic structure in the direction of the air flow.

[0018] In one embodiment of the invention, the wing connection structure comprises at least one rod, one end of which is mounted to the body and the other end to the bend region, thus maintaining its rigidity against bending that may occur with the lift of the wing and transferring the force acting on the wing to the body.

[0019] In one embodiment of the invention, the wing connection structure comprises at least one wing bracket that is located in the area where the wing is affected by higher forces, allows the rod to be mounted on the bending area on the wing, and positioned side- by-side as two near the wing's centre of gravity, thus transferring the torsional force of the wing to the body with the help of the rods, and a body bracket that is almost L- shaped and is located, between the rod and the body, at the corner where the surface and the rood intersect, with one part located on the surface where the wing is connected to the root bracket, and the other part located on the roof, which is positioned perpendicular to the surface where the root bracket is located.

[0020] In one embodiment of the invention, the wing connection structure comprises a root bracket that is positioned in alignment with the body bracket at a certain distance to it. In one embodiment of the invention, the wing connection structure comprises at least one beam that has a rib structure, is located at the position where the wing bracket of the bend region is mounted, positioned within the bend region to provide resistance to bending due to the load on the wing, preserves the structural shape of the bend region, reinforcing the inverted V-shaped structure of the bend region, and extends from one surface of the bend region to the other as a rib-structured fan.

[0021] The wing connection structure realised to achieve the aim of this invention is shown in the attached figures, and of these figures;

[0022] Figure 1 shows the front view of the helicopter.

[0023] Figure 2 shows the top schematic view of the wing.

[0024] Figure 3 shows the front view of the wing connection structure.

[0025] Figure 4 shows the perspective view of the wing connection structure.

[0026] Figure 5 shows the perspective view of the support part.

[0027] Figure 6 shows the perspective view of the root bracket, protrusion, fastener hole and bracket hole.

[0028] The parts in the figures are numbered one by one and the equivalents of these numbers are given below.

[0029] 1 . A Wing Connection Structure

[0030] 2. Body

[0031] 3. Wing

[0032] 31 . Root region

[0033] 31 1 . First structural part

[0034] 312. Second structural part

[0035] 32. End region

[0036] 33. Bend region

[0037] 320. Support part 4. Root bracket

[0038] 5. Protrusion

[0039] 6. Bracket hole

[0040] 7. Connection hole

[0041] 8. Fastener

[0042] 9. Shell

[0043] 10. Rod

[0044] 1 1 .Wing bracket

[0045] 12. Body bracket

[0046] 13. Beam

[0047] The wing connection structure (1 ) comprises a body (2) that is located on the aircraft, at least one wing (3) that is located on the body (2) and extends outwards from the body (2), providing lifting force to the body (2) and allowing the placement of payload on it, a root region (31 ) that is located on the wing (3) and extends from the body (2) in a dihedral angle, and at least one root bracket (4) that is located on the body (2) and enables the wing (3) to be mounted on the body (2).

[0048] The wing connection structure (1 ) which is the subject of the invention comprises at least one protrusion (5) that is located on the root region (31 ) which is positioned opposite to the root bracket (4), is form-compatible with the root bracket (4) in a way that it almost completely surrounds the root bracket (4), and carries the load on the wing (3) and a support part (320) mounted on the root region (31 ) in a way that it remains between the two protrusions (5), and allows the load transferred from the wing (3) to be distributed on the protrusions (5) in a way that provides resistance against the bending of the root region (31 ).

[0049] There is at least one wing (3) on the body (2) of the aircraft, which provides the necessary lift for the flight of the aircraft and enables the carrying of useful loads such as ammunition. The wing (3) comprises a root region (31 ) in a dihedral angle upwards from the body (2). There is at least one root bracket (4) that is positioned on the surface of the body (2) facing the wing (3) where the wing (3) is connected to the body (2). The root region (31 ) is fixed to the body (2) in a way that it can move freely on the y-axis parallel to the length of the body (2) by means of the root bracket (4). The root bracket (4) is placed on the body (2) in a T-shaped manner so that the tail of the root bracket (4) extends to the root region (31 ). In this way, the connection of the wing (3) structure is provided by connecting the angled wing (3) to the body (2) in parallel instead of connecting it perpendicularly. (Figure- 1 and Figure- 5)

[0050] For the wing (3) to be mounted on the body (2), the root region (31 ) comprises at least one protrusion (5) that is positioned opposite the root bracket (4) in a way that it will surround the root bracket (4) and transfers the load on the wing (3) from the root region (31 ) to the body (2). The protrusion (5) has a U-shaped structure to surround the root bracket (4) which is in the form of a T. The protrusion (5) and the root bracket (4) provide the wing (3) to be mounted on the body (2) in a form similar to a lug-clevis structure. In this way, the load on the wing (3) is transferred from the root bracket (4) to the body (2) by means of the protrusion (5) that is located on the root region (31 ). It comprises a support part (320) that is positioned to form a bridge between two protrusions (5) so as to be resistant to the bending moment of the root region (31 ). In this way, the force on the wing (3) is distributed equally to the support part (320) and the root brackets (4). (Figure - 5)

[0051] In an embodiment of the invention, the wing connection structure (1 ) comprises a first structural part (31 1 ) and a second structural part (312) that are located on the root region (31 ) that allows the loads on the wing (3) to be transferred to the body (2), and two protrusions (5) that are located on the first structural part (311 ) and the second structural part (312), one of which enables the first structural part (311 ) and the other of which enables the second structural part (312) to be mounted to the body (2) by means of the root bracket (4) so that the second structural part (312) is opposite to the first structural part (31 1 ). The root region (31 ) comprises the first structural part (311 ) and the second structural part (312) that extend towards the body (2) and are parallel to each other. There are protrusions (5) that are positioned in the part where the first structural part (31 1 ) and the second structural part (312) extend towards the body (2), allowing the first structural part (311 ) and the second structural part (312) to be fixed onto the body (2). In this way, the wing (3), which is connected to the body (2) from two different points, provides resistance against bending by providing resistance against air flow. (Figure- 3 and Figure- 5)

[0052] In one embodiment of the invention, the wing connection structure (1 ) comprises a support part (320) that is located between the protrusions (5) in a way that is in alignment with the protrusions (5), extending from one protrusion (5) to the other protrusion (5), thus transferring the bending resistance partly to the root brackets (4) and partly to the wing (3). The support part (320) extends in the bridge structure between the protrusions (5), ensuring that the loads arising from the carrying force are transferred almost equally on the protrusions (5). (Figure - 5)

[0053] In one embodiment of the invention, the wing connection structure (1 ) comprises a support part (320) that is located between the first structural part (31 1 ) and the second structural part (312) in a way that there is a distance between the body (2) and allows the wing (3) to flex due to the payload. The support part (320) is located at the end where the first structural part (31 1 ) and the second structural part (312) extend to the body (2). The support part (320) is mounted on the root bracket (4) of the wing (2) on the axis where the wing (3) is mounted on the body (2) and extends along the length of the aircraft and is positioned at a certain distance from the body (2) in a way that allows the wing (3) angle to change with the free rotation movement. The support part (320) ensures that the protrusions (5) are positioned at the end of the first structural part (31 1 ) and the second structural part (312) and that the protrusions (5) are located in the same plane. In this way, the wing (3) is connected to the body (2) parallel to the ground by mounting the protrusions (5) to the body (2). (Figure- 3 and Figure- 5)

[0054] In one embodiment of the invention, the wing connection structure (1 ) comprises at least one bracket hole (6) that is located on the root bracket (4) and enables the wing (3) to be mounted detachably to the body (2), at least one connection hole (7) that is located on the projection (5), and at least one fastener (8) that enables the root bracket (4) and the projection (5) to be connected mutually by means of the bracket hole (6) and the connection hole (7). The wing (3) is mounted to the body (2) via the fasteners (8) by means of at least two bracket holes (6) on each root bracket (4) and at least two connection holes (7) located on each protrusion (5) opposite each bracket hole (6). In this way, in case one of the fasteners (8) that is located on the protrusion (5) accidentally breaks, the load on the wing (3) is transferred to the root bracket (4) to which it is connected via the other fastener (8) positioned on the same root bracket (4), thus distributing the amount of load distributed to the other root bracket (4) equally and thus ensuring a safe connection. (Figure- 5 and Figure- 6)

[0055] In one embodiment of the invention, the wing connection structure (1 ) comprises an end region (32) that is located on the wing (3) and extends from the root region (31 ) to make an anhedral angle with the body (2), and a bend region (33) that is located between the root region (31 ) and the end region (32) on the wing (3), connecting the root region (31 ) and the end region (32) to each other. The end region (32) that allows the wing (3) having the root region (31 ) extending in a dihedral angle to extend in an anhedral angle with respect to the body (2) is connected to the root region (31 ) by means of the bend region (33) having an inverted V structure. By means of the bend form wing (3), more weight suspension capability is provided. (Figure- 1 and Figure- 2)

[0056] In one embodiment of the invention, it comprises at least one shell (9) that is located on the wing (3) and has an aerodynamic structure that almost completely surrounds the wing (3) and directs the air flow. The shell (9) covers the protrusion (5) that are located on the root region (31 ) and the root bracket (4) that is located on the body (2) in a way that it will almost completely surround them so that they will not be affected by the air flow, thus creating an aerodynamic surface. The shell (9) extends from the wing (3) to the body (2) in a way that covers the root bracket (4). In this way, the root bracket (4) and the protrusion (5) are provided with an aerodynamic surface against air resistance. (Figure- 1 and Figure- 3) In one embodiment of the invention, the wing connection structure (1 ) comprises at least one rod (10), one end of which is connected to the body (2) and the other end to the bend region (33), reducing the deformation caused by the bending moment in the wing (3) and distributing the force acting on the wing (3). In this way, the load on the wing (3) is carried by connecting it to the body (2) from a different point than the root bracket (4). (Figure- 2 and Figure- 3)

[0057] In one embodiment of the invention, the wing connection structure (1 ) comprises at least one wing bracket (1 1 ) that is located between the rod (10) and the wing (3), and provides the connection of the rod (10) to the wing (3), and a body bracket (12) that is located on the body (2), and provides the connection of the rod (10) to the body (2). In this way, the load on the wing (3) is transferred from a different point than the body bracket (12) and the root bracket (4) to the body (2), providing resistance to bending of the wing (3). (Figure - 4)

[0058] In one embodiment of the invention, the wing connection structure (1 ) comprises a root bracket (4) that is positioned oppositely with a distance between it and the body bracket (12). The root bracket (4) is located below the body bracket (12) in a way that it is on the same vertical direction as the body bracket (12). The body bracket (12) is positioned partially in the roof area of the aircraft. In this way, the wing (3) is fixed on the body (2) from different points and the load distribution transferred to the body (2) is provided. (Figure - 4)

[0059] In one embodiment of the invention, the wing connection structure (1 ) comprises at least one beam (13) that has a fan structure and is positioned within the bend region (33) to carry the load on the wing (3) and is located at the location where the bend region (33) is connected to the wing bracket (1 1 ). As a result of the load transferred by the wing bracket (1 1 ) via the rod (10), the bend region (33) is prevented from structurally deteriorating against torsion by means of the beams (13) having a rib structure within the bend region (33). (Figure - 5)

Claims

CLAIMS1. A wing connection structure (1 ) comprising a body (2) that is located on the aircraft, at least one wing (3) that is located on the body (2) and extends outwards from the body (2), providing lifting force to the body (2) and allowing the placement of payload on it, a root region (31 ) that is located on the wing (3) and extends from the body (2) in a dihedral angle, and at least one root bracket (4) that is located on the body (2) and enables the wing (3) to be mounted on the body (2), characterised by at least one protrusion (5) that is located on the root region (31 ) which is positioned opposite to the root bracket (4), is formcompatible with the root bracket (4) in a way that it almost completely surrounds the root bracket (4), and carries the load on the wing (3), and a support part (320) mounted on the root region (31 ) in a way that it remains between the two protrusions (5), and allows the load transferred from the wing (3) to be distributed on the protrusions (5) in a way that provides resistance against the bending of the root region (31 ).

2. A wing connection structure (1 ) according to Claim 1 , characterised by a first structural part (31 1 ) and a second structural part (312) that are located on the root region (31 ) that allows the loads on the wing (3) to be transferred to the body (2), and two protrusions (5) that are located on the first structural part(31 1 ) and the second structural part (312), one of which enables the first structural part (31 1 ) and the other of which enables the second structural part(312) to be mounted to the body (2) by means of the root bracket (4) so that the second structural part (312) is opposite to the first structural part (31 1 ).

3. A wing connection structure (1 ) according to Claim 1 or Claim 2, characterised by a support part (320) that is located between the protrusions (5) in a way that is in alignment with the protrusions (5), extending from one protrusion (5) to the other protrusion (5), thus transferring the bending resistance partly to the root brackets (4) and partly to the wing (3).

4. A wing connection structure (1 ) according to Claim 2 or Claim 3, characterised by a support part (320) that is located between the first structural part (31 1 ) andthe second structural part (312) in a way that there is a distance between the body (2) and allows the wing (3) to flex due to the payload.

5. A wing connection structure (1 ) according to any of the previous claims, characterised by at least one bracket hole (6) that is located on the root bracket (4) and enables the wing (3) to be mounted detachably to the body (2), at least one connection hole (7) that is located on the projection (5), and at least one fastener (8) that enables the root bracket (4) and the projection (5) to be connected mutually by means of the bracket hole (6) and the connection hole (7).

6. A wing connection structure (1 ) according to any of the previous claims, characterised by an end region (32) that is located on the wing (3) and extends from the root region (31 ) to make an anhedral angle with the body (2), and a bend region (33) that is located between the root region (31 ) and the end region (32) on the wing (3), connecting the root region (31 ) and the end region (32) to each other.

7. A wing connection structure (1 ) according to any of the previous claims, characterised by at least one shell (9) that is located on the wing (3) and has an aerodynamic structure that almost completely surrounds the wing (3) and directs the air flow.

8. A wing connection structure (1 ) according to Claim 6 or Claim 7, characterised by at least one rod (10), one end of which is connected to the body (2) and the other end to the bend region (33), reducing the deformation caused by the bending moment in the wing (3) and distributing the force acting on the wing (3).

9. A wing connection structure (1 ) according to Claim 8, characterised by at least one wing bracket (1 1 ) that is located between the rod (10) and the wing (3), and provides the connection of the rod (10) to the wing (3), and a body bracket (12) that is located on the body (2), and provides the connection of the rod (10) to the body (2).

0. A wing connection structure (1 ) according to Claim 9, characterised by a root bracket (4) that is positioned oppositely with a distance between it and the body bracket (12). 1.A wing connection structure (1 ) according to Claim 9 or Claim 10, characterised by at least one beam (13) that has a fan structure and is positioned within the bend region (33) to carry the load on the wing (3) and is located at the location where the bend region (33) is connected to the wing bracket (11 ).

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