Wing structure of an aircraft, adapter module for use in a wing structure, aircraft wing, use of an adapter module in a wing structure, and aircraft having an aircraft wing

Abstract

The invention provides a wing structure of an aircraft, an adapter module for use in a wing structure, an aircraft wing, a use of an adapter module in a wing structure and an aircraft having an aircraft wing. The wing structure comprises a fixed wing portion and a wing tip portion foldable about a hinge axis relative to the fixed wing portion by means of at least one tip actuation unit having at least one gear-type rotary actuator, wherein an adapter module is provided to be fixed to a fixed wing portion structure element, wherein the adapter module has a base plate fixed to the fixed wing portion and an engagement structure comprising at least one flange for attaching the gear-type rotary actuator and receiving a hinge bar of the fixed wing portion, wherein the at least one flange protrudes from the base plate towards the wing tip portion and has a through hole.

Description

Technical Field

[0001] The present invention relates to an aircraft wing structure, an adapter module for use in the wing structure, an aircraft wing, and an aircraft having such a wing. Background Technology

[0002] Although the invention can be used in many applications, the invention and its potential problems will be explained in more detail in conjunction with aircraft aspects. However, the described apparatus and methods can also be used in vehicles in all sectors of the transportation industry, such as for road vehicles, rail vehicles, or for ships or other installation environments.

[0003] There is a growing trend toward larger passenger aircraft with higher performance efficiency (e.g., reduced fuel combustion), which necessitates a considerable wingspan. However, the maximum aircraft wingspan is actually limited by airport operating rules, which govern the various spacing requirements for maneuvering around the airport (e.g., the wingspan and / or ground spacing required for gate entry and safe taxiway use).

[0004] To address this problem, an aircraft with a folding wing is known. The folding wing typically comprises an inner region and an outer region, the outer region being movable relative to the inner region between a) a flight configuration used during flight and b) a ground configuration used during ground-based operations. In the ground configuration, the outer region moves (typically rotates) relative to the inner region, resulting in a reduced wingspan. Therefore, the aircraft can still comply with airport operating rules but benefits from a larger flight span. Some systems use separate actuators to achieve latching, locking, and tip actuation functions, i.e., for folding the wingtip. In some of these systems, a single motor is used for tip actuation, while two motors are used for latching and locking. These systems require more space and are challenging to install within the limited space available in the aircraft wing. Summary of the Invention

[0005] In this context, the object of the present invention is to find a wing structure for an aircraft wing that allows for more efficient use of available space and exhibits reduced complexity during assembly.

[0006] This objective is achieved by an aircraft wing structure having the features of the first aspect of the invention, an adapter module for use in the wing structure having the features of the other aspect of the invention, an aircraft wing having the features of the other aspect of the invention, and an aircraft having the features of the other aspect of the invention.

[0007] According to a first aspect of the invention, an aircraft wing structure is provided, comprising a fixed wing portion and a wingtip, the wingtip being foldable relative to the fixed wing portion about a hinge axis by means of at least one wingtip actuation unit having at least one geared rotary actuator, wherein an adapter module is configured to be fixed to a structural element of the wing portion, the adapter module having a base plate fixed to the wing portion structure and a joining structure including at least one flange for attaching the geared rotary actuator and receiving a hinge rod of the fixed wing portion, wherein the flange projects from the base plate toward the wingtip and has a through hole. The inventive concept is to provide an aircraft wing structure having an integrated actuation system for a foldable wingtip. The invention solves the problem of safely and efficiently integrating a wingtip actuation unit having at least one geared rotary actuator into a fixed wing portion that ensures precise hinged connection of a foldable wing or wing portion, such as the wingtip, and overcomes limitations in terms of space, installation complexity, and precise alignment of actuating components. Advantageously, the present invention overcomes space constraints and meets the requirements imposed by an aircraft wing with foldable wingtips by employing an adapter module. The adapter module simplifies installation, enhances structural integrity, and ensures accurate transmission of actuation force to the wingtips. The adapter module is designed to be rigidly mounted on the fixed wing section and provides a connection for the geared rotary actuator and related components. The adapter module serves as an intermediate structural element facilitating precise positioning, safe load distribution, and optimal mechanical connection between the wingtips and the wing structure. This structure supports dual load paths, ensuring redundancy and fail-safe operation in the event of partial mechanical failure. The adapter module provides precise mounting positions for one or more geared rotary actuators, reducing alignment and assembly complexity. Fasteners and through-holes are positioned to allow easy access even when the wingtips are already installed. The adapter module also ensures a robust connection between the wingtips and the aircraft structure, thereby minimizing localized stress concentrations. The flange configuration, particularly one with two parallel flanges and aligned through-holes within the flanges, provides a stable mounting engagement while maintaining the integrity of the load path at the attachment point. This structure also allows the actuation drive shaft to automatically engage when the gear-driven rotary actuator is installed, reducing manual adjustments. The dual load path configuration ensures that a mechanical failure at one attachment point will not lead to a complete actuation failure. Therefore, this structure helps prevent uncontrolled wingtip movement, ensuring safety during operation and mitigating the risk of failure. As an advantage, the adapter module integrates into existing wing structures without requiring significant modifications. The alignment of the adapter with respect to the longitudinal axis of the wing allows for optimal encapsulation of the actuation components. For mounting in an aircraft wing, the unit of the invention is preferably aligned with the defining hinge line of the wing and arranged in a plane having the hinge line within the fixed wing section.The units of the present invention can also be arranged at an angle relative to the hinge line, perpendicular to or substantially perpendicular to the longitudinal axis of the wing, or parallel to or substantially parallel to the fuselage, depending on the configuration and structural design of the aircraft wing.

[0008] Another aspect of the invention relates to an adapter module for use in the wing structure of the invention, the adapter module comprising a base plate and a joining structure including at least one flange projecting from the base plate and having a through hole. The inventive concept is to provide a mechanically stable, precisely aligned, and installation-friendly joining member for securing a tip actuating component to a wing assembly. This joining member advantageously overcomes the problems of requiring alignment processes during assembly, increased structural stress, and structural complexity by providing a rigid and accurately positioned mounting structure that ensures optimal force transfer while minimizing mechanical stress and facilitating direct installation. By combining a base plate with a joining structure having flanges, particularly two parallel flanges with through holes arranged in a positional alignment, a standardized attachment solution is provided, enabling efficient and reproducible installation of the actuation system. The base plate provides a robust connection for securing the wing portion, thereby reducing mechanical deformation and stress concentration. The flanges provide predetermined mounting positions, ensuring consistent alignment of the mounted components. The through hole allows easy insertion of a shaft, enabling quick and repeatable installation without the need for post-installation adjustments. The integrated joint structure ensures uniform load transfer between the actuation system and the wing structure, thereby reducing wear and increasing component life. The adapter module offers the advantages of efficient space utilization and minimizing the weight of additional structures while maintaining high mechanical integrity.

[0009] Another aspect of the invention relates to an aircraft wing having a wing structure according to the invention. The concept of the invention is to allow for a larger wingspan in flight by combining actuation and latching / locking into a single system, while the wingtip section can be folded down on the ground to comply with airport regulations. The use of the wing structure according to the invention results in improved use of available space and reduced complexity in the assembly process.

[0010] Another aspect of the invention relates to an aircraft having an aircraft wing according to the invention. The wing comprises a fixed main section and a hinged wingtip section controlled by an actuation system and a latching and locking system. This allows the wingtip to fully deploy in flight to improve aerodynamic efficiency and fold on the ground to meet structural requirements and space constraints.

[0011] Advantageous embodiments and further improvements are apparent from further aspects of the invention and from the description portion with reference to the accompanying drawings.

[0012] According to the embodiment of the wing structure, gear-type rotary actuators, connected by connecting elements extending through through-holes, are arranged on opposite sides of the flange. The connecting element is preferably constructed as one of a through-shaft, a connecting tube, and a rod bearing assembly. Preferably, the connecting element is selected based on structural and functional requirements. Providing a through-shaft has the advantage of establishing a rigid mechanical link, thereby ensuring direct torque transmission between the actuators. The connecting tube provides reduced weight and mechanical flexibility, while the rod bearing assembly enables controlled force reorientation for optimizing actuation dynamics. The opposite placement of the gear-type rotary actuators results in a uniform force distribution, thereby reducing stress concentration within the adapter module and the wing structure. The through-hole in the flange allows for accurate positioning of the connecting element, thereby minimizing mechanical backlash and ensuring synchronous actuation. The selection of the appropriate connecting element allows for customization based on actuator configuration and specifications, load conditions, actuation speed, and available installation space. The predetermined alignment of the connecting element within the through-hole advantageously facilitates installation and maintenance without requiring additional structural modifications.

[0013] According to an embodiment of the invention, the articulated rod is received in a receiving space defined by a flange. This has the advantage of allowing controlled and precise alignment of the articulated rod during installation within the actuation system, thereby facilitating pivoting movement of the articulated rod relative to the fixed wing portion. The receiving space formed by the flange, or by two parallel flanges, or between two parallel flanges, provides a defined and stable mounting position for the articulated rod, thereby ensuring reliable mechanical connection within the actuation system.

[0014] According to another embodiment of the invention, at least one gearbox—specifically configured as one of a bevel gearbox, a hypoid gearbox, and a worm gearbox—is configured to be coupled to a geared rotary actuator, wherein the at least one gearbox includes a drive shaft extending toward the fixed wing section structure, and wherein the gearbox is coupled to a shaft protruding at the free end of the geared rotary actuator. Coupling the gearbox to the geared rotary actuator ensures efficient conversion of the actuator's motion to the controlled rotational motion of the wingtip. Choosing different gearbox configurations (bevel gearbox, hypoid gearbox, or worm gearbox) allows for adaptation to different load conditions and space constraints, thereby optimizing mechanical efficiency. The drive shaft extending toward the fixed wing section facilitates a compact and aligned connection, thereby reducing mechanical strain and ensuring stable operation. The direct connection between the gearbox and the protruding shaft of the actuator minimizes backlash in the transmission system, thereby ensuring precise actuation of the wingtip mechanism. The wing structure according to the invention has the advantage of allowing automatic establishment of the drive shaft connection when the geared rotary actuator is installed. The connection required for the geared rotary actuator to the drive unit, such as a hydraulic or electric motor, can advantageously be established by a gearbox. To establish the connection and reduce assembly effort, a stabilizing bearing is mounted inside the hinged rib of the fixed wing section structure. The stabilizing bearing includes a concave input shaft mounted behind an opening in the hinged rib. The gearbox is mounted at the input end of the geared rotary actuator and includes a shaft protruding from the free end of the geared rotary actuator, thus including a shaft pointing in the direction of the stabilizing bearing when the geared rotary actuator is installed. The shaft is attached to the gearbox of the geared rotary actuator to allow rotational movement, but the shaft is rigidly connected to prevent axial movement. The rotational movement is restricted to deflection, which is necessary to allow compensation for typical build-up and deflection tolerances for this application, and which is necessary to allow installation without damaging the equipment. The inner shaft end includes a convex spline that fits into the concave spline of the stabilizing bearing and serves as a moving spline. When the gear-type rotary actuator is mounted to the articulated rib, a shaft connection is established, which allows for positioning and attachment of the gear-type rotary actuator with minimal effort. It is now necessary to avoid simultaneously positioning the adapter plate and the shaft connection.

[0015] According to another embodiment of the invention, the gear-type rotary actuator is connected to the flange by screwing, riveting, or bolting. This fastening configuration provides a rigid and durable attachment, thereby offering structural stability and reliable force transmission between the actuator and the wing structure, ensuring that the actuator remains firmly secured under operating loads.

[0016] In another embodiment of the adapter module according to the invention, the base plate includes a device for engaging with the fixed wing portion. The engagement device provides a robust mechanical connection, thereby ensuring a precise and stable connection between the adapter module and the wing structure. The engagement device facilitates accurate positioning, controlled load distribution, and efficient force transfer, while allowing for reduced assembly workload. By ensuring an effective mechanical connection, the engagement device achieves uniform load distribution on the wing structure, thereby minimizing stress concentration and enhancing durability.

[0017] According to another embodiment of the invention, the device for engagement is configured as a pin protruding from the side of the base plate opposite to the engagement structure, wherein the pin can be received in a corresponding pin mount provided in the fixed wing section. The engagement of the pin provides a predetermined positioning engagement, thereby facilitating repeatable and accurate installation while allowing controlled load transfer and structural reinforcement. This configuration ensures that the adapter module remains firmly positioned within the wing structure under operating loads and stresses. The predetermined pin mount allows for quick and reliable installation within the limited space available in the aircraft wing structure. The form-fit engagement of the pin in the mount also provides high drag against operating vibrations and mechanical shocks.

[0018] According to another embodiment of the invention, the base plate includes a threaded hole with a threaded insert or a cylindrical nut for receiving a screw or tension bolt disposed in a fixed wing portion for engaging with the base plate, thereby securing the base plate to the fixed wing portion. The use of threaded fastening elements provides a high-strength connection, ensuring the adapter module remains firmly fixed under operating loads and dynamic forces, thus reducing mechanical deflection and undesirable movement. Furthermore, the combination of the threaded insert or cylindrical nut allows for optimized load transfer and simplifies maintenance procedures.

[0019] According to another embodiment of the invention, a threaded stud is disposed at the base plate and can be inserted into the fixed wing portion for engagement with threaded mating elements, particularly threaded nuts, thereby securing the base plate to the fixed wing portion. This alternative or complementary configuration ensures mechanically fixed and load-bearing attachment, thereby allowing for precise positioning and reliable fixation of the adapter module within the wing structure.

[0020] According to another embodiment of the invention, the adapter module includes longitudinal partitions dividing a first module half and a second module half connected to the first module half, wherein the module halves are connected to each other by one of gluing, welding, or bolting. This configuration enhances mechanical reliability and structural resilience by ensuring that each module half remains firmly attached while maintaining the required structural integrity and load distribution characteristics. The connection method between the module halves is selected based on mechanical strength, operating load, and crack propagation resistance to prevent failure modes such as complete separation due to material fatigue or cracking. In particular, the dual-plate configuration allows for fail-safe design, ensuring that in the event of structural damage to one module half, the other module half remains intact, thereby maintaining the mechanical connection of the actuation system. The dual-plate configuration mitigates the risk of failure, ensuring that cracks do not propagate across the entire adapter module, thereby maintaining the attachment of the actuation system in the event of partial damage. The mechanical connection between the module halves creates dual load paths, ensuring that the actuation function remains operational even if one module half is damaged, thereby preventing uncontrolled failure conditions. Connection options—glued, welded, or bolted—allow for adaptation to diverse mechanical and manufacturing requirements, ensuring compatibility with weight limitations, structural loads, and maintenance needs. By distributing mechanical loads across the two interconnected module halves, stress concentration is minimized, reducing the likelihood of fatigue-induced cracking and enhancing the long-term durability of the adapter module. Attached Figure Description

[0021] The invention will be described in more detail with reference to the exemplary embodiments depicted in the accompanying drawings.

[0022] Figure 1 A perspective view depicting a wing structure according to an embodiment of the present invention is provided;

[0023] Figure 2 A perspective view of an adapter module according to an embodiment of the present invention is depicted;

[0024] Figure 3 A perspective view of an adapter module installed in a wing structure according to an embodiment of the present invention is depicted; and

[0025] Figure 4 A perspective view of an adapter module according to another embodiment of the present invention is depicted. Detailed Implementation

[0026] The accompanying drawings are included to provide a further understanding of the invention, and these drawings are incorporated in and constitute a part of this application. The drawings illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention. Other embodiments of the invention and many anticipated advantages of the invention will be readily understood as they become clearer with reference to the detailed description. Elements in the drawings are not necessarily to scale relative to each other. In the drawings, unless otherwise stated, similar reference numerals denote similar or functionally similar parts.

[0027] Although specific embodiments are illustrated and described herein, those skilled in the art will understand that various alternative and / or equivalent implementations may be used in place of the specific embodiments shown and described without departing from the scope of the invention. Generally, this application is intended to cover any modifications or variations of the particular embodiments discussed herein.

[0028] In the figures, unless otherwise specified, the same elements, features and parts having the same function and effect are each given the same reference numerals.

[0029] Figure 1 A perspective view of a wing structure 1 according to an embodiment of the present invention is depicted. The illustration focuses on the attachment configuration of the tip actuation unit 2 between the fixed wing portion 10 and the foldable wing or foldable wing portion, such as, for example, the tip 11 of the foldable wing.

[0030] exist Figure 1 The illustration shows an embodiment with a foldable wingtip 11, but the invention is not limited thereto. The wing structure 1 includes a fixed wing portion 10 and a foldable wingtip 11, which is pivotally movable relative to the fixed wing portion 10 about a hinge axis 12. To achieve controlled movement of the foldable wingtip 11, a wingtip actuation unit 2 is provided, which includes two gear-type rotary actuators 3a, 3b that generate the required torque for actuation. An adapter module 20 is fixed to the fixed wing portion 10, which extends perpendicular to the longitudinal axis L of the wing. The adapter module 20 includes a base plate 21 rigidly attached to the fixed wing portion 10 to provide a robust and stable connection. Extending from the base plate 21 is a joining structure 22 including a parallel flange 23 projecting from the base plate 21 toward the foldable wingtip 11. The flange 23 is configured to serve as a mounting point for gear-type rotary actuators 3a and 3b and to define a receiving space 24 for the hinge rod 25 of the foldable wingtip 11.

[0031] One of the geared rotary actuators, 3a, is coupled to a gearbox 30, which is connected to an actuation shaft (not shown) extending through a through-hole 26 in the flange 23. The gearbox 30 allows torque to be transmitted from the driver to the geared rotary actuators 3a, 3b to control the rotational movement of the hinge rod 25 and the foldable wingtip 11. The hinge rod 25 is positioned within and pivotally supported in a receiving space 24 between the flanges 23. The rod 25 interacts with the foldable wingtip 11 to transmit actuation force, thereby ensuring synchronized and precise movement about the hinge shaft 12. The through-hole 26 in the flange 23 (see...) Figure 2 Alignment is used to accommodate the actuation shaft, thereby ensuring accurate alignment and effective force transmission.

[0032] Figure 2 A perspective view of an adapter module 20 according to an embodiment of the present invention is depicted. The adapter module 20 is configured for attachment to a fixed wing portion 10 and includes a base plate 21 and a coupling structure 22 extending from the base plate 21. The base plate 21 is provided with coupling devices to facilitate precise alignment and secure fixation of the adapter module 20 to the fixed wing portion 10. In this embodiment, the coupling device is configured as a pin 27 protruding from a surface of the base plate 21 opposite to the coupling structure 22. The pin 27 is designed to be received in a corresponding pin mounting member 42 provided in the fixed wing portion 10 (see [link to documentation]). Figure 3 The base plate 21 also includes fastening holes 28 arranged to receive screws or bolts for securing the adapter module 20 to the fixed wing section 10. A through-hole 26 is provided in the engagement structure 22, which aligns with the hinge shaft 12 of the wingtip actuation system in its mounting position within the wing structure 1. The engagement structure 22 includes parallel aligned flanges 23. The through-hole 26 serves as a mounting point for the actuation shaft or structural connection element. The combination of pin-based engagement and fastening holes 28 ensures precise alignment, stable attachment, and controlled load distribution between the adapter module 20 and the fixed wing section 10, as the predetermined positioning of the pin 27 facilitates quick and repeatable assembly while minimizing the risk of misalignment. The combination of pin engagement and additional fasteners provides a mechanically reinforced and vibration-resistant connection.

[0033] Figure 3A perspective view of an adapter module 20 installed in a wing structure 10 according to an embodiment of the present invention is depicted. The adapter module 20 is mounted to a rib 40 of a fixed wing portion 10, thereby providing a rigid and precisely aligned attachment engagement for the actuating components of the foldable wingtip system. The rib 40, as a structural element of the fixed wing portion 10, is aligned perpendicular to the longitudinal axis L of the aircraft wing. The base plate 21 of the adapter module 20 is secured to the rib 40 by attachment devices 41, such as bolts or tension screws, thereby ensuring a mechanically stable connection. For precise alignment and additional load distribution, pins 27 protrude from the base plate 21 and are received in corresponding pin mounts 42 provided in the rib 40 of the fixed wing portion 10. This predetermined engagement mechanism facilitates the positioning of the adapter module 20, thereby preventing misalignment during installation. The adapter module 20 is designed as a split configuration, including a first module half 43 and a second module half 44, which are connected together along a dividing line 45. The connection between module halves 43 and 44 can be achieved by gluing, welding, or bolting, thereby ensuring structural integrity and load-bearing capacity. The engagement structure 22 of the adapter module 20 accommodates a hinge rod 25, which is positioned within a receiving space 24 defined by a parallel flange 23. The hinge rod 25 is pivotally supported on a connecting element 46, which extends through a through-hole 26 in the flange 23. The connecting element 46 is configured to provide a rotational connection between the gear-type rotary actuators 3a and 3b and the hinge rod 25. For this purpose, the connecting element 46 is provided with a concave spline 47 designed to engage with a convex spline (not shown) on the shaft of the gear-type rotary actuators 3a and 3b, or vice versa, the connecting element 46 is provided with a convex spline 47 and the concave spline 47 is designed to engage with a concave spline (not shown) on the shaft of the gear-type rotary actuators 3a and 3b, thereby ensuring effective torque transmission.

[0034] Figure 4 A perspective view of an adapter module 20 according to another embodiment of the invention is depicted. The adapter module 20 is configured for attachment to a fixed wing portion 10 and includes a base plate 21 and a engagement structure 22 extending from the base plate 21. In this embodiment, the adapter module 20 is secured to the fixed wing portion 10 using threaded studs 50, which are either machined directly into the base plate 21 or configured as separate fastening elements. The threaded studs 50 extend from the base plate 21 and are designed to pass through corresponding mounting holes in the fixed wing portion 10, where the threaded studs 50 utilize attachment devices 41, such as... Figure 3The nut shown is used for securing the adapter module 20. This configuration achieves a reliable and load-bearing connection between the adapter module 20 and the fixed wing section 10, while ensuring efficient assembly and maintenance procedures. To prevent accidental loosening of the attachment device 41, additional locking features can be applied. These additional locking features may include a wire locking mechanism, a locking plate, or a self-locking thread, thereby ensuring that the fastening elements remain firmly engaged under operating conditions including vibration and dynamic loads. The adapter module 20 also includes a pin 27, which is secured by a corresponding pin mount 42 in the fixed wing section 10 (see [link to pin mount]). Figure 3 The engagement provides precise alignment. This ensures that the adapter module 20 is correctly positioned before the attachment device 41 is finally tightened, thus reducing the risk of misalignment.

[0035] In the foregoing detailed description, various features have been combined in one or more examples for the purpose of simplifying this disclosure. It should be understood that the foregoing description is intended to be illustrative and not restrictive. The foregoing description is intended to cover all alternatives, modifications, and equivalents. Many other examples will be readily understood by those skilled in the art after reviewing the foregoing application. Various embodiments were chosen and described to best illustrate the principles of the invention and its practical application, thereby enabling those skilled in the art to best utilize the invention and its various embodiments with various modifications suitable for the specific intended use.

[0036] List of reference numerals

[0037] 1. Wing Structure

[0038] 2 tip actuation units

[0039] 3a, 3b Gear-type rotary actuators

[0040] 10 Fixed Wing Section

[0041] 11 Wingtip

[0042] 12 hinge shafts

[0043] 20 adapter modules

[0044] 21 base plate

[0045] 22-joint structure

[0046] 23 flanges

[0047] 24 Acceptance Space

[0048] 25 strokes

[0049] 26 through holes

[0050] 27 pins

[0051] 28 holes

[0052] 30 gearbox

[0053] 40 ribs

[0054] 41 Attachment Devices

[0055] 42 pin mounting parts

[0056] 43 First Module Half

[0057] 44 Second Module Half

[0058] 45-degree dividing line

[0059] 46 connecting elements

[0060] 47 concave splines

[0061] 50 threaded studs

[0062] L longitudinal axis

Claims

1. A wing structure (1) for an aircraft, the wing structure (1) comprising a fixed wing portion (10) and a wingtip (11), the wingtip (11) being foldable about a hinge axis (12) relative to the fixed wing portion (10) by means of at least one wingtip actuation unit (2) having at least one geared rotary actuator (3a, 3b), wherein, The adapter module (20) is configured as a structural element fixed to the fixed wing portion (10), wherein the adapter module (20) has a base plate (21) fixed to the fixed wing portion (10) and a coupling structure (22), the coupling structure (22) including at least one flange (23) for attaching the gear-type rotary actuator (3a, 3b) and receiving the hinge rod (25) of the fixed wing portion (10), wherein at least one of the flanges (23) protrudes from the base plate (21) toward the wing tip (11) and has a through hole (26).

2. The wing structure (1) according to claim 1, wherein, At least one of the gear-type rotary actuators (3a, 3b), connected by a connecting element (46) extending through the through hole (26), is arranged on the opposite side of the flange (23).

3. The wing structure (1) according to claim 2, wherein, The connecting element (46) is constructed as one of a through shaft, a connecting tube, and a rod bearing assembly.

4. The wing structure (1) according to any one of claims 1 to 3, wherein, The hinge rod (25) is received in the receiving space (24) defined by the flange (23).

5. The wing structure (1) according to any one of claims 1 to 4, wherein, At least one gearbox (30) is configured to be coupled to at least one of the geared rotary actuators (3a, 3b), wherein at least one gearbox (30) is specifically configured as one of a bevel gearbox, a hypoid gearbox and a worm gearbox, wherein at least one gearbox (30) includes a drive shaft extending toward the fixed wing portion (10), and wherein the gearbox (30) is coupled to a shaft protruding at the free end of the geared rotary actuator (3a, 3b).

6. The wing structure (1) according to any one of claims 1 to 5, wherein, At least one of the gearboxes (30) is configured to be coupled to the fixed wing portion (10), and the at least one gearbox (30) is specifically constructed as one of a bevel gearbox, a hypoid gearbox and a worm gearbox, wherein the at least one gearbox (30) includes a drive shaft mounted on the inside of the fixed wing portion (10) and extending toward at least one of the geared rotary actuators (3a, 3b), and wherein the gearbox (30) is coupled to a shaft protruding at the free end of the geared rotary actuator (3a, 3b).

7. The wing structure (1) according to claim 6, wherein, To establish a connection with the gearbox (30), a stabilizing bearing is provided on the inner side of the fixed wing section (10) structure and the stabilizing bearing is mounted on the hinge rib of the fixed wing section (10) structure, wherein the stabilizing bearing preferably includes a concave input shaft, which is specifically mounted behind an opening in the hinge rib, wherein the gearbox (30) is mounted on the input end of the gear rotary actuator (3a, 3b), the gearbox (30) including a shaft protruding at the free end of the gear rotary actuator (3a, 3b), thereby including a shaft pointing in the direction of the stabilizing bearing when the gear rotary actuator (3a, 3b) is mounted.

8. The wing structure (1) according to any one of claims 1 to 7, wherein, The gear-type rotary actuators (3a, 3b) are connected to the flange (23) by screwing, riveting or bolting.

9. An adapter module (20) for use in a wing structure (1) according to any one of claims 1 to 8, the adapter module (20) comprising a base plate (21) and a joining structure (22), the joining structure (22) comprising at least one flange (23), wherein, At least one of the flanges (23) protrudes from the base plate (21) and has a through hole (26).

10. The adapter module (20) according to claim 9, wherein, The base plate (21) includes a device for engaging with the fixed wing portion (10).

11. The adapter module (20) according to claim 10, wherein, The device for engagement is constructed as a pin (27) protruding from the side of the base plate opposite to the engagement structure (22), wherein the pin (27) can be received in a corresponding pin mount (42) provided in the fixed wing portion (10).

12. The adapter module (20) according to any one of claims 9 to 11, wherein, The base plate (21) includes a threaded hole (28), a hole with a threaded insertion portion, or a cylindrical nut for receiving a screw or tension bolt disposed in the fixed wing portion (10) for engaging with the base plate (21) to secure the base plate (21) to the fixed wing portion (10).

13. The adapter module (20) according to any one of claims 9 to 12, wherein, A threaded stud (50) is provided at the base plate (21) and the threaded stud (50) can be inserted into the fixed wing portion (21) for engagement with a threaded mating element, in particular a threaded nut, thereby for fixing the base plate (21) to the fixed wing portion (10).

14. The adapter module (20) according to any one of claims 9 to 13, wherein, The adapter module (20) includes a longitudinal partition dividing a first module half (43) and a second module half (44) connected to the first module half (43), wherein the module half (43, 44) are connected to each other by one of gluing, welding and bolting.

15. An aircraft wing having a wing structure (1) according to any one of claims 1 to 8.

16. Use of the adapter module (20) according to any one of claims 9 to 14 in the wing structure (1) according to any one of claims 1 to 8.

17. An aircraft having an aircraft wing as claimed in claim 16.

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