A helicopter

Abstract

The present invention relates to a body (2) that is exposed to the air flow, at least one wing (3) that is located on the body (2) extending outwards from the body (2), provides lifting force to the body (2) and allows ammunition and similar payloads to be placed on it, at least one fastener (B) that connects the wing (3) to the body (2), at least one rod (4) one end of which is connected to the body (2) and the other end to the wing (3), providing load transfer to the wing (3), a root region (301) that is located on the wing (3) and extends from the body (2) in a dihedral angle, an end region (302) that is located on the wing (3) and extends from the root region (301) in a anhedral angle with the body (2), a bend region (303) in an inclined form that is located on the wing (3) between the root region (301) and the end region (302), and connects the root region (301) and the end region (302).

Description

[0001] A HELICOPTER

[0002] The present invention relates to a helicopter that has a wing-body connection in a gull wing form, thus has high aerodynamic performance.

[0003] In aircraft, the wing is usually connected directly to the body from its vertical axis with a four-point tension bolt. Due to the structure of the wing, it is possible to connect the wing directly to the body. However, this is not possible in a helicopter in which an eagle wing consisting of three inclined regions is used. 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 angled wing cannot be connected on the y-axis, that is, perpendicular to the body, it must be connected on the x-axis, that is, on the axis along the body. For this reason, mounting angled wings, which are called gull wings, which would be located aerodynamically within the wing surface, is required.

[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 US20110089292A1 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. By a helicopter developed with the present invention, an increase in the forward flight speed capability of the helicopter is provided.

[0006] Another aim of this invention is to ensure that the payloads that are located on the gull wing are carried effectively.

[0007] Another aim of this invention is to ensure that the pressure distribution of the air going to the aircraft engine is adjusted at an optimum level and that it exhibits better fuel performance.

[0008] Another aim of this invention is to provide the ability of the helicopter to operate with higher weight and / or payload in the hover flight condition at altitudes with high air density.

[0009] The helicopter 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 that meets the air flow. There is at least one wing extending out from the body, providing the necessary lifting force to the body, and having the function of carrying payloads on it. The wing is connected to the body with a fastener. One end of the rod is connected to the wing and the other end is connected to the body and keeps the wing fixed. There is a root region on the wing that extends at a dihedral angle with the body. There is an end region on the wing that extends at an anhedral angle with the body. There is a curved bend region between the root region and the end region on the wing.

[0010] Said helicopter comprises a rod, one end of which is located in the body and the other end in the bend region. By means of the rod, the deformations caused by torsional or bending forces on the wing are reduced and the aerodynamic force acting on the wing is distributed.

[0011] In one embodiment of the invention, the helicopter comprises at least one wing bracket that is located between the rod and the wing in a way that it will connect the rod to the wing.

[0012] In one embodiment of the invention, the helicopter comprises at least one wing bracket that is compatible with the radius form of the bend region.

[0013] In one embodiment of the invention, the helicopter comprises a wing with a root region, an end region and a bend region that are in different geometries, where the cross-sectional region of each of the root region, end region and bend region is independent and / or different from the others.

[0014] In one embodiment of the invention, the helicopter comprises a rod that is connected in a way that the bend region extends from the tip point to the body in the same direction so as to ensure the continuity of the direction in which the end region extends with the tip point located on the bend region.

[0015] In one embodiment of the invention, the helicopter comprises two side-by-side rods and wing brackets on the bend region, in the region where the wing is affected by higher forces, close to the centre of gravity of the wing, thus ensuring that the wing is less affected by the torsional force.

[0016] In one embodiment of the invention, the helicopter has a surface on the body, on the face where the wing is connected via the fastener. There is a roof on the body, positioned perpendicular to the surface and touching the surface. There is a body bracket that is located between the rod and the body, partly on the surface and partly on the roof, at the corner where the surface and the roof intersect, connects the rod to the body, and is almost L-shaped.

[0017] In one embodiment of the invention, the helicopter comprises a rod with a flexible structure that will dampen the vibration on the wing that vibrates due to the loads acting on it during flight.

[0018] In one embodiment of the invention, the helicopter comprises a rod that can be opened and closed telescopically and the length of which is adjusted according to the shape of the wing and the position of the bend region during production.

[0019] In one embodiment of the invention, the helicopter comprises at least one turnbuckle positioned on the rod so that it will be close to the wing bracket and / or the body bracket. The user can adjust the tension of the turnbuckle. In this way, the rod allows the adjustment of the distance between the end region and the bend region with the body.

[0020] In one embodiment of the invention, the helicopter comprises at least one root bracket that is located on the body and allows the wing to be connected to the body from the root region. There is at least one protrusion that is located on the root region, where the root region is located opposite the root bracket, and the shape of which is compatible with the root bracket in a way that it will surround the root bracket, thus ensuring that the load on the wing is carried. There is a fastener that is mounted on the root region, between two protrusions, and distributes the load transferred by the wing over the protrusions in a way that prevents the root region from bending.

[0021] In one embodiment of the invention, the helicopter comprises a shell that is located on the wing with an aerodynamic geometry, surrounds the root region, end region and bend region, improving air flow.

[0022] The helicopter realised to achieve the aim of the present invention is shown in the attached figures, and of these figures;

[0023] Figure 1 shows the front view of the helicopter.

[0024] Figure 2 shows the schematic view of the wing.

[0025] Figure 3 shows the front view of the body, wing, rod, wing bracket, body bracket, fastener, surface and roof.

[0026] Figure 4 shows the perspective view of rod, wing bracket, body bracket, fastener, turnbuckle and shell.

[0027] Figure 4 shows the perspective view of wing, root bracket, protrusion and surface.

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

[0029] 1 . Helicopter

[0030] 2. Body

[0031] 3. Wing

[0032] 301 . Root region

[0033] 302. End region

[0034] 303. Bend region 5. Wing bracket

[0035] 6. Body bracket

[0036] 7. Turnbuckle

[0037] 8. Root bracket

[0038] (B) Fastener

[0039] (C) Protrusion

[0040] (K) Shell

[0041] (T) Roof

[0042] (Y) Surface

[0043] The helicopter (1 ) comprises a body (2) that is exposed to the air flow, at least one wing (3) that is located on the body (2) extending outwards from the body (2), provides lifting force to the body (2) and allows ammunition and similar payloads to be placed on it, at least one fastener (B) that connects the wing (3) to the body (2), at least one rod (4) one end of which is connected to the body (2) and the other end to the wing (3), providing load transfer to the wing (3), a root region (301 ) that is located on the wing (3) and extends from the body (2) in a dihedral angle, an end region (302) that is located on the wing (3) and extends from the root region (301) in a anhedral angle with the body (2), a bend region (303) in an inclined form that is located on the wing (3) between the root region (301 ) and the end region (302), and connects the root region (301 ) and the end region (302).

[0044] The helicopter (1 ) which is the subject of the invention comprises a rod (4) one end of which is connected to the body (2) and the other end to the bend region (303) and thus reduces the deformation caused by the bending moment on the wing (3) and distributes the force acting on the wing (3).

[0045] There is a body (2) exposed to air flow on the helicopter (1 ). The wing (3) that is located on the body (2) provides lifting force to the body. The wing (3) also carries payloads such as ammunition. For this reason, it is exposed to various loads. The wing (3) is connected to the body with a fastener (B). Apart from the fastener (B), a rod (4) is located with one end on the body (2) and the other end on the wing (3) in order to strengthen the connection of the wing (3) to the body (2). There is a root region (301 ) that is located on the wing (3) in the part that makes a dihedral angle with the body (2). There is an end region (302) on the wing (3) extending in an anhedral angle between the root region (301 ) and the body (2). There is a bend region (303) in a curved form connecting the end region (302) and the root region (301 ). In this way, a curved and / or bend form is obtained in the wing (3) to form a seagull wing and its placement on the body (2) is ensured. (Figure-1 , Figure-2)

[0046] One end of the rod (4) is located on the body (2) and the other end on the root region (301 ). In this way, the rod (4) distributes the stresses caused by the bending moment acting on the wing (3) and reduces the deformation. (Figure-3)

[0047] In one embodiment of the invention, the helicopter (1 ) comprises at least one wing bracket (5) that is located between the rod (4) and the wing (3) and enables the rod (4) to be connected to the wing (3). By means of the wing bracket (5), the rod (4) is connected to the wing (3) and the wing (3) is carried firmly on the body (2).

[0048] In one embodiment of the invention, the helicopter (1 ) comprises at least one wing bracket (5) which has almost completely radius-shape of the bend region (303) onto which it is connected. In this way, the rod (4) is carried on the body (2) by holding the wing (3) from the bend region (303).

[0049] In one embodiment of the invention, the helicopter (1 ) comprises a wing (3) the root region (301), end region (302) and bend region (303) of which are each independent from each other and / or have a different cross-sectional region geometry. By means of the different cross-sectional region and cross-sectional geometry of the root region (301 ), end region (302) and bend region (303), more efficient fuel consumption and better suspension performance are provided in the helicopter (1 ).

[0050] In one embodiment of the invention, the helicopter (1) comprises a rod (4) that is connected in a way that extends from the tip of the bend region (303) to the body (2) in the same direction, so as to ensure the continuity of the direction in which the end region (302) and the tip of the bend region (303) extend on the body (2). The direction in which the end region (302) extends on the body (2) is provided by the rod (4). The angle at which the rod (4) is positioned on the body (2) is such that the continuity of the end region (302) is ensured. In this way, carrying of the payload by the wing (3) is structurally supported during the flight of the helicopter (1 ). In one embodiment of the invention, the helicopter (1 ) comprises rods (4) and wing brackets (5) that are positioned almost completely centring the centre of gravity of the wing (3) on the bend region (303), in the local region where the wing (3) experiences relatively high forces, thus preventing the bending of the wing (3) at least partially. Rods (4) and wing brackets (5) are located side by side on the body (2) and the wing (3). The part where the wing brackets (5) are positioned on the wing is where high forces act on the wing (3) and is positioned close to the centre of gravity of the wing (3). Thus, the wing (3) is structurally supported to carry the payload and the imbalances that occur during flight are prevented.

[0051] In an embodiment of the invention, the helicopter (1 ) comprises a surface (Y) that is located on the body (2) where the wing (3) is connected by means of the fastener (B), at least one roof (T) that is located on the body (2) and is in contact with the surface (Y) in a way that extends perpendicularly to the surface (Y), a body bracket (6) that is located between the rod (4) and the body (2) and enables the rod (4) to be connected to the body (2), and a body bracket (6) that is located at the intersection point of the surface (Y) and the roof (T), one part of which is on the surface (Y) and the other part is on the roof (T), and is almost L-shaped. The body (2) consists of surface (Y) and roof (T). The wing (3) is connected to the body (2) from the root region (301 ) via the fastener (B) from the surface (Y). The wing (3) is connected to the body (2) from the bend region (303) via the rod (4). The rod (3) is connected to the body (2) via the body bracket (6). The body bracket (6) is located in the region where the surface (Y) and the roof (T) intersect. The body bracket (6) has an L shape to fit the corner form of the surface (Y) and the roof (T). In this way, the wing (3) is strongly connected to the body (2) via the rod (4).

[0052] In one embodiment of the invention, the helicopter (1 ) comprises a flexible rod (4) that dampens the vibration coming to the wing (3) that is exposed to vibration during the flight of the helicopter (1). In this way, the vibration is damped by the rod (4) and the flight performance of the helicopter (1 ) is prevented from being affected by the vibration.

[0053] In one embodiment of the invention, the helicopter (1 ) comprises a rod (4) that can be opened and closed telescopically, the length of which is pre-adjusted by the manufacturer according to the shape of the wing (3) and the position of the bend region (303). In this way, the rod (4) in one size can be adapted to different helicopters (1).

[0054] In one embodiment of the invention, the helicopter (1 ) comprises at least one turnbuckle (7) that is located on the rod (4), close to the wing bracket (5) and / or the body bracket (6), and the rod (4) that is triggered by the user adjusting the tension of the turnbuckle (7), thus adjusting the distance of the end region (302) and the bend region (303) to the body (2). In this way, the rod (4) in one size can be adapted to different helicopters (1 ). (Figure-4)

[0055] In an embodiment of the invention, the helicopter (1 ) comprises at least one root bracket (8) that is located on the body (2) and enables the wing (3) to be mounted from the root region (301) to the body (2); at least one protrusion (C) that is located on the root region (301 ) which is positioned opposite to the root bracket (8) and is form-compatible with the root bracket (8) in a way that it almost completely surrounds the root bracket (8) and thus carries the load on the wing (3); and a fastener (B) that is mounted on the root region (301 ) in a way that it remains between the two protrusions (C) and allows the load transferred from the wing (3) to be distributed on the protrusions (C) in a way that provides resistance against the bending of the root region (301 ). In this way, the wing (3) is connected to the body (2) from the root region (301 ). (Figure-5)

[0056] In one embodiment of the invention, the helicopter (1 ) comprises a shell (K) that is located on the wing (3) with an aerodynamic structure that almost completely surrounds the root region (301 ), end region (302) and bend region (303) and directs the air flow. In this way, the aerodynamic performance of the wing (3) is increased.

Claims

CLAIMS1. A helicopter (1 ) comprising a body (2) that is exposed to the air flow, at least one wing (3) that is located on the body (2) that is extending outwards from the body(2), provides lifting force to the body (2) and allows ammunition and similar payloads to be placed on it, at least one fastener (B) that fixesthe wing (3) to the body (2), at least one rod (4) one end of which is fixed to the body (2) and the other end to the wing (3), providing load transfer to the wing (3), a root region (301 ) that is located on the wing (3) and extends from the body (2) in a dihedral angle, an end region (302) that is located on the wing (3) and extends from the root region (301 ) in a anhedral angle with the body (2), a bend region (303) in an inclined form that is located on the wing (3) between the root region (301 ) and the end region (302), and fixes the root region (301 ) and the end region (302) characterised by a rod (4) one end of which is fixed to the body (2) and the other end to the bend region (303) and thus reduces the deformation caused by the bending moment on the wing (3) and distributes the force acting on the wing (3).

2. A helicopter (1 ) according to Claim 1 , characterised by at least one wing bracket (5) that is located between the rod (4) and the wing (3) and enables the rod (4) to be fixed to the wing (3).

3. A helicopter (1 ) according to Claim 1 or Claim 2, characterised by the wing bracket (5) which has an almost completely radius form in the bend area (303) to which it is connected.

4. A helicopter (1 ) according to any of the previous claims, characterised by a wing(3) the root region (301 ), end region (302) and bend region (303) of which are each independent from each other and / or have a different cross-sectional region geometry.

5. A helicopter (1) according to any of the previous claims, characterised by a rod(4) that is connected in a way that extends from the tip of the bend region (303) to the body (2) in the same direction, so as to ensure the continuity of the direction in which the end region (302) and the tip of the bend region (303) extend on the body (2).

6. A helicopter (1) according to Claims 2 to 5, characterised by rods (4) and wing brackets (5) that are positioned almost completely centring the centre of gravity of the wing (3) on the bend region (303), in the local region where the wing (3) experiences relatively high forces, thus preventing the bending of the wing (3) at least partially.

7. A helicopter (1 ) according to any of the previous claims, characterised by a surface (Y) that is located on the body (2) where the wing (3) is connected by means of the fastener (B), at least one roof (T) that is located on the body (2) and is in contact with the surface (Y) in a way that extends perpendicularly to the surface (Y), a body bracket (6) that is located between the rod (4) and the body (2) and enables the rod (4) to be connected to the body (2), and a body bracket (6) that is located at the intersection point of the surface (Y) and the roof (T), one part of which is on the surface (Y) and the other part is on the roof (T), and is almost L-shaped.

8. A helicopter (1 ) according to any of the previous claims, characterised by a flexible rod (4) that dampens the vibration coming to the wing (3) that is exposed to vibration during the flight of the helicopter (1 ).

9. A helicopter (1) according to any of the previous claims, characterised by a rod (4) that can be opened and closed telescopically, the length of which is preadjusted by the manufacturer according to the shape of the wing (3) and the position of the bend region (303).

10. A helicopter (1 ) according to Claims 7 to 9, characterised by at least one turnbuckle (7) that is located on the rod (4), close to the wing bracket (5) and / or the body bracket (6), and the rod (4) that is triggered by the user adjusting the tension of the turnbuckle (7), thus adjusting the distance of the end region (302) and the bend region (303) to the body (2).

11. A helicopter (1 ) according to any of the previous claims, characterised by at least one root bracket (8) that is located on the body (2) and enables the wing (3) to be mounted from the root region (301 ) to the body (2); at least one protrusion (C)that is located on the root region (301 ) which is positioned opposite to the root bracket (8) and is form-compatible with the root bracket (8) in a way that it almost completely surrounds the root bracket (8) and thus carries the load on the wing (3); and a fastener (B) that is mounted on the root region (301 ) in a way that it remains between the two protrusions (C) and allows the load transferred from the wing (3) to be distributed on the protrusions (C) in a way that provides resistance against the bending of the root region (301 ).

12. A helicopter (1 ) according to any of the previous claims, characterised by a shell (K) that is located on the wing (3) with an aerodynamic structure that almost completely surrounds the root region (301 ), end region (302) and bend region (303) and directs the air flow.

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