A wing 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 provides lift force for the flight of the body (2), at least one fitting (4) that is located inside the body (2) and allows the wing (3) to be mounted on the body (2), and more than one wing surface (5) that are located on the wing (3), almost completely surrounding the wing (3) and being the outer surface of the wing (3).

Description

[0001] A WING STRUCTURE

[0002] The present invention relates to mechanisms that enable the wings brought to different aerodynamic forms in aircraft to be mounted on the aircraft.

[0003] In aircraft, the wing lower shell is designed as a single fixed surface due to the structural load requirement and the manufacturing method. A part of the wing surface provides an aerodynamic effect and the aerodynamic surface is followed by structures called wing-body fairing towards the root side of the wing. However, wing body fairing is only used to create an aerodynamic surface between the wing and the body or to provide aerodynamic improvement on the surfaces. This situation leads to extra weight. A wing design is required that will generate both lifting force without the extra weight that would be created if extra equipment were used, but at the same time will not create additional drag force in the root area where the wing is attached to the fuselage.

[0004] In the United States patent document numbered US20080205763A1 in the state of the art, mechanisms that enable the body and wings in aircraft to be connected to each other are mentioned. The document describes the connection parts that are adjusted according to the wing inclination when the aircraft wing is brought to different angles of attack, allowing the fittings to take a similar angle.

[0005] The United States patent document numbered US20220097820A1 in the state of the art mentions a design that allows the body and wings in aircraft to be connected to each other. The document mentions that an additional angled connection part is added in order to compensate for the angle between the aircraft wing and the aircraft body.

[0006] The aim of the present invention is to provide an aerodynamic surface between the wing and the body that is not exposed to additional drag force by not using wing-body fairing.

[0007] Another aim of this invention is to ensure that the surface of the wing along its length and the wing root region surface are one-piece.

[0008] Another aim of this invention is to provide a wide-range connection / mounting (fitting) design by connecting the wing to the body with a wide angle, increasing the moment arm and reducing the coupling effect loads. The wing structure defined in the first claim and the claims dependent on this claim, which is realised in to achieve the aim of the invention, comprises an aerodynamic body on the aircraft. The wing is mounted on the body and provides the creation of the necessary lift force for the flight of the body and the carrying of structural / aerodynamic loads. There is a fitting inside the body and allows the wing to be mounted to the body from inside the body. There is a wing surface that surrounds the wing centre spar and forms the lower and upper aerodynamic surfaces of the wing.

[0009] Said wing structure comprises an axis that is at least partially parallel to the direction in which the wing extends from the body and extends to the wingtip and makes a pitching motion around the body and is the spanwise direction axis. There is a main region, which is the region where the wing surface extends from the point determined by the manufacturer to the wingtip and is at least partially parallel to the axis. There is a root region, which is the region where the wing surface extends from the point where the main region starts to the body and extends at least partially into the body. The region of the root region extending into the body is mounted to the fitting and structural loads are carried from the surface of the root region mounted to the fitting. The area of the root region outside the body provides aerodynamic continuity and performs the wing-body connection function. The root region and main region are manufactured as a single piece and are preferably made of composite material.

[0010] In one embodiment of the invention, the wing structure comprises a hollow-shaped slot that is located on the body and extends from the body to the fitting. There are more than one hollow-shaped holes on the fitting. Each hole is aligned with the slot it is opposite to and is made opposite to each other in a way that they are at least partially concentric. Each pin is passed through the mutually aligned hole and slot by means of more than one pin, allowing the fitting to be mounted to the body. The hole is located on the fitting in the direction where the wing surface extends towards the fitting.

[0011] In one embodiment of the invention, the wing structure comprises a protrusion extending from the fitting so that it remains inside the body. The surface of the root region inside the body enters the protrusion in the form of a lug, and the protrusion allows the root region to be mounted to the fitting. By positioning the area of the root region inside the body in the protrusion in the form of a lug, the connector is mounted inside the protrusion and root region by the manufacturer. In this way, the wing is fixed to the body. The groove that is opened in the root region for the wing to be mounted on the body is form compatible with connector and protrusion.

[0012] In one embodiment of the invention, the wing structure comprises a first surface, which is the lower aerodynamic surface of the wing. The wing structure comprises a second surface, which is the upper aerodynamic surface of the wing. The first surface and the second surface are located on the wing in a way that they are opposite to each other according to the wing centre spar. The root region and the main region are located on the first surface and the second surface. The root region is mounted to the body via a fitting.

[0013] In one embodiment of the invention, the wing structure comprises a bracket that is located on the fitting in a way that it will be partially in an “L” shape. One surface of the “L” shaped bracket is mounted to the wing centre spar by means of fixers and the fitting is fixed to the wing centre spar. Another surface of the “L” shaped bracket is located on the fitting and allows the loads transmitted from the wing to the body to be distributed.

[0014] In one embodiment of the invention, the wing structure comprises a first fitting forming the upper surface of the fitting and a second fitting forming the lower surface of the fitting. The first fitting and the second fitting are spaced apart and do not contact each other. The bracket is placed in the space between the first fitting and the second fitting. The load transfer between the first fitting and the second fitting is carried out via the bracket. The bracket is mounted to the first fitting and the second fitting by means of stabilizers (fixers) and forms a rigid structure together with the first fitting and the second fitting.

[0015] In one embodiment of the invention, the wing structure comprises a flange surface, which is the surface of the bracket that contacts the wing, provides the bracket to be in the form of an “L”, and ensures that the bracket locates in a right angle with the fitting and is fixed to the wing. The flange surface is mounted to the wing centre spar by means of a fixer and ensures that the fitting is fixed to the wing centre spar in a rigid structure. The structural loads formed during the aircraft flight on the wing centre spar are transferred to the bracket, fitting and body via the flange surface.

[0016] In one embodiment of the invention, the wing structure comprises a plurality of first fittings and a plurality of second fittings located one after the other. A strut is located between the first fitting and the second fitting located one after the other. The strut contacts the first fitting and the second fitting. The region of the root region extending into the body is fixed to the first fitting and the second fitting by means of the connector by passing through the strut in the form of a lug. The strut allows more than one first fitting and the second fitting to be fixed to each other and the wing surface to be fixed to the fitting.

[0017] In one embodiment of the invention, the wing structure comprises a connector that is passed through the protrusion and strut by the user so that it is almost perpendicular to the surface of the root region extending into the body and allows the wing surface to be mounted to the fitting.

[0018] In one embodiment of the invention, the wing structure comprises a root region manufactured as a single piece with the main region. The angle transition between the main region and the root region is a kink type geometry. The angle change between the main region and the root region is determined by the manufacturer in a way that will not create drag force at least partially between the root region and the body and will ensure the carrying of aerodynamic loads. The root region both ensures the carrying of aerodynamic loads and serves as a wing-body connection that ensures the creation of a continuous surface between itself and the body. The main region and the root region are preferably produced from composite material.

[0019] In one embodiment of the invention, the wing structure comprises a bracket that is located at least partially on the first fitting and the second fitting, so as to fit into the space between the first fitting and the second fitting. The surface of the bracket corresponding to the area between the holes that are located on the first fitting and the second fitting is concave and form compatible with the first fitting and the second fitting. There is no load transfer from the area between the holes that are located on the first fitting and the second fitting. For this reason, the area between the holes of the bracket and the areas between the holes of the first fitting and the second fitting are emptied and concave, thus allowing weight gain.

[0020] In one embodiment, the wing structure comprises multiple fixers that allow the bracket to be mounted to the first fitting, the second fitting, and the wing centre spar. The bracket is positioned between the two fixers on the first fitting and the second fitting, and the recess provides the areas of the bracket that are subject to stress below the threshold value specified by the manufacturer for carrying structural or aerodynamic loads to be indented, radiused, and peaked.

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

[0022] Figure 1 is a perspective view of the wing and the body.

[0023] Figure 2 is a side view of the body and slot.

[0024] Figure 3 is a perspective view of the wing structure.

[0025] Figure 4 is a perspective view of the wing, fitting and body.

[0026] Figure 5 is a front view of the strut, first surface and second surface.

[0027] The parts in the figures are numbered one by one and the equivalents of these numbers are given below.

[0028] 1 . Wing structure

[0029] 2. Body

[0030] 3. Wing

[0031] 4. Fitting

[0032] 410. First fitting

[0033] 420. Second fitting

[0034] 401. Hole

[0035] 402. Pin

[0036] 403. Connector

[0037] 404. Bracket

[0038] 4040. Flange surface

[0039] 405. Strut

[0040] 406. Recess

[0041] 5. Wing surface

[0042] 501. First surface

[0043] 502. Second surface

[0044] 5001 . Main region

[0045] 5002. Root region

[0046] 6. Slot

[0047] 7. Protrusion (H) Axis

[0048] (F) Fixer

[0049] The wing 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 provides the lift force for the flight of the body (2), at least one fitting (4) that is located inside the body (2) and allows the wing

[0050] (3) to be mounted on the body (2), and more than one wing surface (5) that are located on the wing (3), almost completely surrounding the wing (3) and being the outer surface of the wing (3) (Figure - 1 , Figure - 3).

[0051] The wing structure (1 ) which is the subject of the invention comprises an axis (H) that is parallel to the direction in which the wing (3) extends along its length, a main region (5001 ) which forms the wing surface (5) and is parallel to the axis (H), a root region (5002) which extends into the body (2) in a direction different from the direction in which the main region (5001 ) extends relative to the axis (H) and is mounted on the fitting

[0052] (4), thus enables the structural loads to be carried from the surface to which it is connected with the fitting (4), enables the aerodynamic continuity of the wing surface

[0053] (5), creates a bend in the wing (3) profile relative to the main region (5001 ) and is produced as a single piece with the main region (5001 ) (Figure - 3).

[0054] The body (2) which is an aircraft has a wing (3) that is detachably attached to the body (2), provides lift for the flight of the body (2) and allows the aerodynamic loads to be carried. A fitting (4) is located inside the body (2) and allows the wing (3) to be mounted on the body (2). There is a wing surface (5) that forms the lower and upper aerodynamic surfaces of the wing (3) and allows the aerodynamic loads formed on the wing (3) to be carried.

[0055] There is an axis (H) that forms the direction from the point determined by the manufacturer of the wing (3) to the tip of the wing (3). There is a main region (5001 ) that forms the region from the point determined by the manufacturer of the wing (3) to the tip of the wing (3) and is almost completely parallel to the axis (H). There is a root region (5002) extending towards the body (2) in a kink type angle with the direction in which the main region (5001 ) extends towards the wing (3) tip, and has a different direction with the axis (H), forming the region of the wing surface (5) close to the body (2) The surface of the root region (5002) extending into the body (2) is mounted on the fitting (4) and allows the wing (3) to be fixed at least partially over the wing surface (5). The root region (5002) has an angle value that will allow aerodynamic continuity to be created on the side of the wing (3) close to the body (2) and this angle value is determined by the manufacturer. The main region (5001 ) and the root region (5002) together create a bend in the wing (3) profile. In this way, without the need for a wingbody connection, the drag force formation in the root region (5002) is at least partially prevented, the drag force value can be reduced and the aerodynamic loads are carried.

[0056] In one embodiment of the invention, the wing structure (1 ) comprises more than one slot (6) that are located on the body (2), more than one hole (401 ) that are located on the fitting (4), more than one pin (402) that are removably attached to the hole (401 ) and the slot (6) and allow the fitting (4) to be fixed to the body (2), and a hole (401 ) that allows sufficient lift force to be created for the wing (3) by being located on the fitting (4) in the direction where the wing surface (5) extends towards the fitting (4). The hole (401 ) and the slot (6) are reciprocated by the manufacturer, and the pin (402) is passed through them to ensure that the wing (3) is fixed to the body (2) by means of the fitting (4) (Figure - 2).

[0057] In one embodiment of the invention, the wing structure (1 ) comprises at least one protrusion (7) that is located on the fitting (4), extends outward from the fitting (4), is at least partially parallel to the root region (5002) and allows the root region (5002) to be mounted on the fitting (4), and at least one connector (403) that is removably attached to the protrusion (7) and enables the second region (5002) to be mounted on the fitting (4), enabling the wing (3) to be fixed to the body (2). The connector (403) is attached to the protrusion (7) in the form of a lug and passed through the root region (5002). The connector (403) is mounted almost completely perpendicular to the surface of the root region (5002) inside the body (2). In this way, the transfer of structural and aerodynamic loads between different axes is ensured (Figure - 4).

[0058] In one embodiment of the invention, the wing structure (1 ) comprises a first surface (501 ) that is the wing surface (5) and forms the lower surface of the wing (3) according to the direction in which the wing (3) extends from the body (2) along its length, a second surface (502) that is the wing surface (5) and forms the upper surface of the wing (3) according to the direction in which the wing (3) extends from the body (2) along its length and is mirror symmetrical to the first surface (501 ) with respect to the wing (3), and a fitting (4) which allows the root region (5002) that is located on the first surface (501 ) and / or the second surface (502) to be connected to the body (2) in a way that forms the wing (3) profile determined by the manufacturer, enabling the structural loads formed on the wing (3) to be carried. The root region (5002) is located on the first surface (501 ) and the second surface (502), is at least partially located inside the body (2) and is mounted on the fitting (4). In this way, the drag force on the surface of the root region (5002) close to the wing (3) is partially prevented and the wing (3) is allowed to be carried from the surface of the root region (5002) inside the body (2).

[0059] In one embodiment of the invention, the wing structure (1 ) comprises at least one bracket (404) that is located on the fitting (4) in a way that will contact the wing (3) and allows the fittings (4) to be connected to each other by means of more than one fixer (F) and allows the distribution of the structural load formed on the fitting (4). The bracket (404) allows the transfer of structural and aerodynamic loads from the centre spar of the wing (3) and the wing surface (5) to the fitting (4) and body (2).

[0060] In one embodiment of the invention, the wing structure (1 ) comprises a plurality of first fittings (410) that form the upper surface of the fitting (4), a plurality of second fittings (420) that are located opposite the first fitting (410), spaced apart from the first fitting (410) and form the lower surface of the fitting (4), and a bracket (404) that is mounted to the first fitting (410) and the second fitting (420) by means of a fixer (F) in a way that closes the gap between the first fitting (410) and the second fitting (420), enabling structural and aerodynamic load transfer between the first fitting (410) and the second fitting (420). By having a hollow structure in the exposed areas of the bracket (404), which are determined by the manufacturer and whose structural and aerodynamic load carrying capacity is not stressed below a predetermined threshold value, both aerodynamic and structural loads are carried, and weight is saved.

[0061] In one embodiment of the invention, the wing structure (1 ) comprises at least one flange surface (4040) that is the surface of the bracket (404) that contacts the wing (3), and provides the bracket (404) to be in the form of an “L”, and a flange surface (4040) that enables the bracket (404) and the fitting (4) to be mounted to the wing (3) via the fixer (F), enabling the structural loads formed on the wing (3) to be transferred to the first fitting (410) and the second fitting (420). The flange surface (4040) is mounted to the centre spar of the wing (3) via the fixer (F) and enables the load transfer between the first fitting (410) and the second fitting (420) and the centre spar of the wing (3). In one embodiment of the invention, the wing structure (1 ) comprises a plurality of first fittings (410) and second fittings (420) that are positioned on the bracket (404) so as to be opposite each other, and at least one strut (405) that enables the wing (3) to be fixed to the first fitting (410) and the second fitting (420) by means of the connector (403) positioned on it, enabling the loads formed on the wing (3) to be carried over the wing surface (5). The strut (405) is located between the first fittings (410) and the second fittings (420) of the fittings (4) placed one after the other and ensures the fixing of the first fittings (410) to each other and the second fittings (420) to each other and the load transfer between them (Figure - 5).

[0062] In one embodiment of the invention, the wing structure (1 ) comprises a connector (403) that is mounted almost perpendicular to the surface of the root region (5002) extending into the body (2), thus allowing the necessary lift force to be created for the wing (3). In this way, the structural and aerodynamic loads transferred from the wing (3) centre spar and wing surface (5) to the fitting (4) and bracket (404) are allowed to be transferred to different axes and the wing (3) is allowed to remain rigid. Mounting the connector (403) perpendicularly to the root region (5002) improves the aerodynamic form of the wing (3) while providing the wing (3) strength required for the lift force and enables the load transfer to the body (2) on the wing (3) (Figure - 3).

[0063] In one embodiment of the invention, the wing structure (1 ) comprises a root region (5002) that is produced as a single piece with the main region (5001 ), extends outwards by providing a transition from the main region (5001 ) with a kink type geometry, thus providing aerodynamic continuity for the wing (3) and allowing weight gain. The angle transition between the main region (5001 ) and the root region (5002) is a kink geometric type angular transition.

[0064] In one embodiment of the invention, the wing structure (1 ) comprises a bracket (404) that is positioned on the first fitting (410) and the second fitting (420) and between the opposite holes (401 ), has a concave form is compatible with the fitting (4), provides effective load transfer between the first fitting (410) and the second fitting (420) and enables weight gain. The bracket (404) and the fitting (4) are in a concave form compatible with each other from the first fitting (410) to the second fitting (420) according to the placement of the holes (401 ) on the fitting (4). In one embodiment of the invention, the wing structure (1 ) comprises the fixer (F) that allows the bracket (404) to be mounted on the first fitting (410), the second fitting (420) and / or the wing (3), and at least one recess (406) that allows the creation of a topshaped surface between at least two consecutively positioned fixers (F) and thus provides weight gain. The recess (406) is located on the bracket (404), the first fitting (410) and the second fitting (420) in the regions not expected to carry loads by the manufacturer and / or in the regions where the load-carrying potential is below the threshold value determined by the manufacturer.

Claims

CLAIMS1. A wing 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 provides lift force for the flight of the body (2), at least one fitting (4) that is located inside the body (2) and allows the wing (3) to be mounted on the body (2), and more than one wing surface (5) that are located on the wing (3), almost completely surrounding the wing (3) and being the outer surface of the wing (3), characterised by an axis (H) that is parallel to the direction in which the wing (3) extends along its length, a main region (5001 ) which forms the wing surface (5) and is parallel to the axis (H), a root region (5002) which extends into the body (2) in a direction different from the direction in which the main region (5001 ) extends relative to the axis (H) and is mounted on the fitting (4), thus enables the structural loads to be carried from the surface to which it is connected with the fitting (4), enables the aerodynamic continuity of the wing surface (5), creates a bend in the wing (3) profile relative to the main region (5001 ) and is produced as a single piece with the main region (5001 ).

2. A wing structure (1 ) according to Claim 1 , characterised by more than one slot (6) that are located on the body (2), more than one hole (401 ) that are located on the fitting (4), more than one pin (402) that are removably attached to the hole (401 ) and the slot (6) and allow the fitting (4) to be fixed to the body (2), and a hole (401 ) that allows sufficient lift force to be created for the wing (3) by being located on the fitting (4) in the direction where the wing surface (5) extends towards the fitting (4).

3. A wing structure (1 ) according to Claim 1 or Claim 2, characterised by at least one protrusion (7) that is located on the fitting (4), extends outward from the fitting (4), is at least partially parallel to the root region (5002) and allows the root region (5002) to be mounted on the fitting (4), and at least one connector (403) that is removably attached to the protrusion (7) and enables the second region (5002) to be mounted on the fitting (4), enabling the wing (3) to be fixed to the body (2).

4. A wing structure (1 ) according to any of the previous claims, characterised by a first surface (501 ) that is the wing surface (5) and forms the lower surface of the wing (3) according to the direction in which the wing (3) extends from the body (2) along its length, a second surface (502) that is the wing surface (5) and forms the upper surface of the wing (3) according to the direction in which the wing (3) extends from the body (2) along its length and is mirror symmetrical to the first surface (501 ) with respect to the wing (3), and a fitting (4) which allows the root region (5002) that is located on the first surface (501 ) and / or the second surface (502) to be connected to the body (2) in a way that forms the wing (3) profile determined by the manufacturer, enabling the structural loads on the wing (3) to be carried.

5. A wing structure (1 ) according to any of the previous claims, characterised by at least one bracket (404) that is located on the fitting (4) in a way that will contact the wing (3) and allows the fittings (4) to be connected to each other by means of more than one fixer (F) and allows the distribution of the structural load formed on the fitting (4).

6. A wing structure (1 ) according to Claim 5, characterised by a plurality of first fittings (410) that form the upper surface of the fitting (4), a plurality of second fittings (420) that are located opposite the first fitting (410), spaced apart from the first fitting (410) and form the lower surface of the fitting (4), and a bracket (404) that is mounted to the first fitting (410) and the second fitting (420) by means of a fixer (F) in a way that closes the gap between the first fitting (410) and the second fitting (420), enabling structural and aerodynamic load transfer between the first fitting (410) and the second fitting (420).

7. A wing structure (1 ) according to Claim 5 or Claim 6, characterised by at least one flange surface (4040) that is the surface of the bracket (404) that contacts the wing (3), and provides the bracket (404) to be in the form of an “L”, and a flange surface (4040) that enables the bracket (404) and the fitting (4) to be mounted to the wing (3) via the fixer (F), enabling the structural loads formed on the wing (3) to be transferred to the first fitting (410) and the second fitting (420).

8. A wing structure (1 ) according to Claim 6 or Claim 7, characterised by a plurality of first fittings (410) and second fittings (420) that are positioned on the bracket (404) so as to be opposite each other, and at least one strut (405) that enables the wing (3) to be fixed to the first fitting (410) and the second fitting (420) by means of the connector (403) positioned on it, enabling the loads formed on the wing (3) to be carried over the wing surface (5).

9. A wing structure (1 ) according to Claims 3 to 8, characterised by the connector(403) that is mounted perpendicular to the surface of the root region (5002) extending into the body (2), and enables the creation of the necessary lift force for the wing (3).

10. A wing structure (1 ) according to any of the previous claims, characterised by a root region (5002) that is produced as a single piece with the main region (5001 ), extends outwards by providing a transition from the main region (5001 ) with a kink type geometry, thus providing aerodynamic continuity for the wing (3) and allowing weight gain.

11. A wing structure (1 ) according to Claims 6 to 10, characterised by a bracket(404) that is positioned on the first fitting (410) and the second fitting (420) and between the opposite holes (401 ), has a concave form is compatible with the fitting (4), provides effective load transfer between the first fitting (410) and the second fitting (420) and enables weight gain.

12. A wing structure (1 ) according to Claims 6 to 1 1 , characterised by the fixer (F) that allows the bracket (404) to be mounted on the first fitting (410), the second fitting (420) and / or the wing (3), and at least one recess (406) that allows the creation of a top-shaped surface between at least two consecutively positioned fixers (F) and thus provides weight gain.

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