Universal folding mechanism for wings

Abstract

The application discloses a general folding mechanism for a wing and belongs to the technical field of aerospace equipment, which comprises a main wing section, a folding wing section and a folding assembly, the main wing section is fixedly connected with a fuselage, the folding assembly is connected with the main wing section and the folding wing section and can move the folding wing section, the folding assembly comprises a sectional hinge component, a skin support component and a driving assembly, the sectional hinge component is located between the main wing section and the folding wing section, the skin support component is connected with the main wing section and the folding wing section and is hingedly connected with the sectional hinge component, and the driving assembly connects the sectional hinge component with the main wing section and the folding wing section through the driving assembly; the sectional hinge component is arranged, in the process of overturning the folding wing section, can synchronously rotate with the folding wing section, the bending stress of the upper skin with large curvature in the 180-degree folding process is greatly reduced, and the local deformation and damage of the skin are effectively avoided.

Description

Technical Field

[0001] This invention relates to the field of aerospace equipment technology, and in particular to a universal wing folding mechanism. Background Technology

[0002] During takeoff and landing, the lifting surface of a compound-wing UAV is significantly affected by crosswinds and gusts, and the wing skin continuously bears uneven aerodynamic loads. As a core component of compound-wing UAVs, the wing folding mechanism can greatly improve the reliability of low-altitude wind-resistant takeoff and landing. Furthermore, by folding the outer wing section, it reduces the overall storage volume of the aircraft, facilitating ground transportation and warehousing deployment. Existing wing folding mechanisms are mostly designed for flat or low-curvature upper skins. When the curvature of the wing upper skin is large, the skin is prone to stretching, wrinkling, or compression deformation during folding due to uneven stress. In addition, the skin is prone to interference with the main wing structure, resulting in a limited folding angle and making it difficult to achieve a complete 180° fold, further deteriorating the stability of takeoff and landing operations under complex wind conditions.

[0003] Some improvement solutions attempt to alleviate deformation by adding an elastic compensation layer to the skin, but the compensation effect is limited, and the elastic layer is prone to aging and failure after long-term use. Another solution adjusts the folding axis position, but to adapt to the large curvature skin, an arc-shaped joint is required, which is difficult to manufacture and still suffers from problems such as folding jamming and skin damage. Therefore, there is an urgent need for a mechanism that can adapt to the large curvature upper skin and achieve 180° damage-free folding, reducing the complexity of the manufacturing and assembly process and improving the reliability and versatility of the folding mechanism. Summary of the Invention

[0004] The purpose of this invention is to provide a universal wing folding mechanism that enables stable 180° folding of the wing while preventing deformation or damage to the upper skin.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: a universal wing folding mechanism, comprising a main wing section, a folding wing section, and a folding assembly. The main wing section is fixedly connected to the fuselage. The folding assembly is connected to the main wing section and the folding wing section, enabling the folding wing section to move. The folding assembly includes a segmented hinge component, a skin support component, and a drive assembly. The segmented hinge component is located between the main wing section and the folding wing section. The skin support component is connected to the main wing section and the folding wing section, and is also hinged to the segmented hinge component. The drive assembly connects the segmented hinge component to the main wing section and the folding wing section. Through the operation of the drive assembly, the segmented hinge component and the folding wing section can be simultaneously rotated and moved, causing the folding wing section to fold or unfold.

[0006] Furthermore, the skin support component includes a fixed support arm and a movable support arm. One side of the fixed support arm is fixedly connected to the main wing section, and the other side is hinged to the segmented hinge component. One side of the movable support arm is fixedly connected to the folding wing section, and the other side is hinged to the segmented hinge, so that both the movable support arm and the segmented hinge component can rotate around the hinge point.

[0007] Furthermore, the segmented hinge component includes a triangular hinge and a folding spindle, with the bottom corner of the triangular hinge hinged to the drive assembly; the folding spindle simultaneously connects the fixed support arm, the triangular hinge, and the movable support arm.

[0008] Furthermore, there are several triangular hinges, and these triangular hinges are arranged along the chord length of the wing.

[0009] Furthermore, the fixed support arm is provided with two sets of hinges, and the movable support arm is provided with two protrusions, which can be hinged with the hinges to form a connection between the fixed support arm and the movable support arm.

[0010] Furthermore, the drive assembly includes two push-pull components, one of which connects the main wing section to the segmented hinge component, and the other of which connects the folding wing section to the segmented hinge component. The two push-pull components can operate simultaneously.

[0011] Furthermore, the push-pull component includes an electric actuator and a fixed base. The output end of the electric actuator is hinged to a segmented hinge component, which can rotate during the extension or retraction of the electric actuator. The fixed base is used to position the electric actuator.

[0012] Furthermore, a support structure is provided between the main wing section and the folding wing section, through which the skin support component is connected to the main wing section and the folding wing section.

[0013] Furthermore, the support structure includes two fixed support groups, which are symmetrically arranged. One fixed support group fixes the main wing section to the skin support component, and the other fixed support group fixes the folding wing section to the skin support component.

[0014] Furthermore, the fixed support assembly includes two sets of corner plates spaced apart along the chord of the wing.

[0015] Compared with the prior art, the beneficial effects of the present invention are: by setting up segmented hinge components, the segmented hinge components can rotate synchronously with the folding wing segment during the flipping process, which greatly reduces the bending stress of the large curvature upper skin during the 180° folding process and effectively avoids local deformation and damage of the skin. Attached Figure Description

[0016] Figure 1This is a schematic diagram of the folded state of the present invention; Figure 2 This is a schematic diagram of the unfolded state of the present invention; Figure 3 This is a schematic diagram of the skin support component in this invention; Figure 4 This is a schematic diagram of the segmented hinge component in this invention; Figure 5 This is a schematic diagram of the driving component in this invention.

[0017] Among them, 1-main wing section, 11-first fixed support group, 2-folding wing section, 21-second fixed support group, 3-segmented hinge component, 31-folding main shaft, 32-triangular hinge, 4-skin support component, 41-fixed support arm, 42-movable support arm, 51-first electric actuator, 52-first fixed seat, 53-second electric actuator, 54-second fixed seat. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0020] like Figures 1 to 5As shown, the present invention provides a universal wing folding mechanism, which, in terms of its overall structure, mainly includes a main wing section 1, a folding wing section 2, and a folding assembly. The main wing section 1 serves as the fixed foundation of the entire folding mechanism, with one end fixedly connected to the fuselage structure via a bolt assembly. This bolted connection ensures the stability and reliability of the connection between the main wing section 1 and the fuselage, effectively transmitting various loads generated during flight. The folding wing section 2 is located on the side of the main wing section 1 furthest from the fuselage and is the part that needs to be folded. The main wing section 1 is connected to the folding wing section 2 via the folding assembly, allowing the folding wing section 2 to rotate within a 180° range, thus enabling the folding wing section 2 to be in a folded or unfolded state.

[0021] In this example, the folding assembly includes a skin support component 4, a segmented hinge component 3, and a drive assembly. The skin support component 4 serves as an intermediate bridge connecting the main wing section 1 and the folding wing section 2. The segmented hinge component 3 serves as the core hub for achieving relative rotation. The drive assembly provides the power source for the entire folding or unfolding action. The specific structural forms of each of the above components, their assembly and connection relationships, and the overall operation process of the machine will be described in detail below.

[0022] In this example, support structures are also provided at the close ends of the main wing section 1 and the folding wing section 2, and are connected to the skin support component 4 through these support structures. Specifically, the support structures include a first fixed support group 11 and a second fixed support group 21. The first fixed support group 11 is located at the end of the main wing section 1 facing the folding wing section 2, and includes two sets of corner pieces spaced apart along the chord direction of the wing. These two sets of corner pieces are fixedly connected to the internal load-bearing structure of the main wing section 1 by fasteners, forming a stable mounting base. Correspondingly, the second fixed support group 21 is located at the end of the folding wing section 2 facing the main wing section 1, and also includes corner piece structures spaced apart and corresponding in position and quantity to the first fixed support group 11. These corner pieces are also fixed to the internal main load-bearing component of the folding wing section 2. The two sets of corner piece structures together constitute the mounting interface of the skin support component 4, providing a solid foundation for the reliable connection of the fixed support arm 41 and the movable support arm 42.

[0023] Based on the aforementioned end support structure, the skin support component 4 is fixedly connected between the first fixed support group 11 and the second fixed support group 21. Specifically, the skin support component 4 consists of two parts: a fixed support arm 41 and a movable support arm 42. The fixed support arm 41 is fixedly connected to the first fixed support group 11 at the end of the main wing segment 1 via bolts or rivets, forming a fixed, immovable unit with the main wing segment 1. The movable support arm 42 is fixedly connected to the second fixed support group 21 at the end of the folding wing segment 2, thus forming another movable unit with the folding wing segment 2. The fixed support arm 41 and the movable support arm 42 are hinged together via a segmented hinge component 3, allowing the two units to rotate relative to each other around the same axis of rotation. It is worth noting that this embodiment uses conventional corner pieces as fixed support groups, which completely avoids the practice of using arc-shaped joints in the prior art. This not only significantly reduces the processing difficulty and manufacturing cost of each component, but also makes the assembly process more convenient and efficient. More importantly, it avoids the arc-shaped support head from directly contacting the inner surface of the skin, which is conducive to the uniform transmission and stable support of the skin surface load and reduces the risk of local stress concentration.

[0024] The fixed support arm 41 and the movable support arm 42 mentioned above are both long strip plates. A hinge lug is provided on the side of one of the long strip plates, and a protrusion is provided on the side of the other long strip plate. After the protrusion is hinged to the hinge lug, the fixed support arm 41 and the movable support arm 42 can be hinged together. When the fixed support arm 41 and the movable support arm 42 are hinged, they are also connected to the segmented hinge component 3. Next, the specific structure of the segmented hinge component 3 and its assembly relationship will be explained in detail.

[0025] The segmented hinge component 3 includes a folding main shaft 31 and triangular hinges 32. There are several triangular hinges 32, which are arranged in segments along the chord length of the wing. The segmented arrangement can effectively increase the torsional stiffness of the folding wing segment 2 and improve the stability of the folding process. The folding spindle 31 simultaneously passes through several segmented triangular hinges 32, and the fixed support arm 41 and the movable support arm 42 are also simultaneously passed through this folding spindle 31. That is, the fixed support arm 41, the movable support arm 42 and several triangular hinges 32 are connected through the folding spindle 31, so that the movable support arm 42 and the triangular hinges 32 can rotate around the folding spindle 31. The two bottom corners of the triangular hinges 32 are hinged to the drive component. When the drive component starts to work, it can make the triangular hinges 32 and the movable support arm 42 rotate.

[0026] In this example, from an assembly perspective, the folding spindle 31 passes through coaxial mounting holes on the fixed support arm 41, the movable support arm 42, and each of the triangular hinges 32 along the chord direction, enabling precise coaxial assembly of the three components via the same folding spindle 31. Furthermore, the segmented hinge components 3 are precisely positioned within the space defined by the two sets of hinge lugs on the fixed support arm 41. Under this assembly relationship, the movable support arm 42 and all the triangular hinges 32 can rotate freely relative to the fixed support arm 41 around the folding spindle 31, while the fixed support arm 41 remains stationary, thus achieving the folding or unfolding action of the folding wing segment 2 relative to the main wing segment 1. Specifically, there are multiple triangular hinges 32, and these triangular hinges 32 are arranged in a segmented, spaced manner along the wing chord direction, ensuring synchronous rotation of all triangular hinges 32 during folding or unfolding. This multi-segment coaxial hinge structure effectively disperses the bending stress generated by the large curvature upper skin during the large-angle folding of the folding wing segment 2 along the chord direction, significantly reducing the stress level per unit area and thus greatly avoiding the risk of local deformation, wrinkling, or compression damage to the skin. Simultaneously, the segmented arrangement of multiple triangular hinges 32 significantly enhances the torsional stiffness of the folding wing segment 2 in both folded and unfolded states, making the entire folding process smoother and more reliable, and effectively suppressing any possible torsional swaying of the folding wing segment 2.

[0027] Based on a thorough understanding of the hinge structure, the following section will provide a detailed description of the specific components of the drive assembly, the installation positions of each part, and the power transmission path.

[0028] The drive assembly, serving as the power source for the active rotation of the folding wing section 2, mainly comprises a first electric actuator 51, a first fixed base 52, a second electric actuator 53, and a second fixed base 54. In terms of installation layout, the first fixed base 52 is fixedly mounted to the main load-bearing rib web inside the main wing section 1 using fasteners, and the second fixed base 54 is also fixedly mounted to the main load-bearing rib web inside the folding wing section 2 using fasteners. Both fixed bases possess sufficient structural strength to withstand the reaction force generated by the electric actuators during operation. The tail hinged end of the first electric actuator 51 is hinged to the first fixed base 52 via a pin, and the tail hinged end of the second electric actuator 53 is similarly hinged to the second fixed base 54 via a pin. This hinged connection allows the electric actuators to adaptively adjust their attitude according to changes in the rotation angle during operation. The output ends of the first electric actuator 51 and the second electric actuator 53 are respectively hinged to the hinge holes at the two base corners of the triangular hinge 32 via pins, thereby converting the linear motion of the electric actuators into the rotational motion of the triangular hinge 32 around the folding main axis 31. From a spatial layout perspective, the first electric actuator 51 and the second electric actuator 53 are symmetrically arranged along the spanwise direction of the wing and achieve strictly synchronized extension and retraction under the unified command of the control system. This symmetrical arrangement and synchronized control design ensures balanced force on both sides of the folding wing section 2, preventing off-center loading or torsional torque. This guarantees the smoothness of movement and the accuracy of the final position during the 180° folding and unfolding processes, greatly improving the operational reliability and service life of the entire folding mechanism.

[0029] In this example, the first fixed base 52 and the first electric push rod 51 can be combined to form a first push-pull component, and the second fixed base 54 and the second electric push rod 53 can be combined to form a second push-pull component. That is, the drive assembly is composed of the first push-pull component and the second push-pull component.

[0030] Based on the structural scheme described in detail above, the complete working process of the universal wing folding mechanism provided by this invention in actual use is as follows: When the wings are in the deployed state, such as Figure 2 As shown, both the first electric actuator 51 and the second electric actuator 53 are in the fully retracted initial position. At this time, the fixed support arm 41 and the movable support arm 42 in the skin support component 4 maintain a relatively fixed angle. The movable support arm 42 provides stable lower support for the folding wing section 2. The entire wing presents a complete aerodynamic shape and can perform flight missions normally.

[0031] When a folding operation is required, the control system simultaneously sends extension commands to the first electric actuator 51 and the second electric actuator 53. The extended ends of the two electric actuators advance synchronously, applying a rotational driving force to the triangular hinge 32 through their output ends connecting to the hinge hole at the bottom of the hinge. Since the triangular hinge 32 is sleeved on the folding main shaft 31 and is connected to the movable support arm 42 through the same main shaft, the driving torque, after being transmitted through the triangular hinge 32, drives the movable support arm 42 and the folding wing segment 2 fixedly connected to it to rotate upward around the folding main shaft 31. Throughout the rotation process, the movable support arm 42 always rotates synchronously with the folding wing segment 2, while the fixed support arm 41 remains stationary, and the angle between the two gradually changes.

[0032] When the folding wing segment 2 rotates close to 180°, that is, when the folding wing segment 2 is fully flipped and fits against the side of the main wing segment 1, the control system issues a stop command. The first electric actuator 51 and the second electric actuator 53 stop extending and lock at the current extension length. At this time, the folding wing segment 2 is stably held in the folded position, completing the entire folding process, as shown in Figure 1. It should be emphasized that during the entire rotation process, because the segmented hinge component 3 adopts a multi-segment coaxial hinge structure, the bending deformation of the large-curvature upper skin at various points on the folding path is evenly distributed to multiple hinge segments, avoiding stress concentration and excessive deformation at a single hinge point, effectively ensuring the integrity and surface quality of the skin structure.

[0033] The unfolding process follows the reverse of the folding process. When it is necessary to return from the folded state to the unfolded state, the control system drives the first electric actuator 51 and the second electric actuator 53 to retract synchronously. Their output ends pull back the bottom of the triangular hinge 32, causing the folding wing segment 2 to rotate in the opposite direction around the segmented hinge component 3 until the folding wing segment 2 returns to the unfolded position coplanar with the main wing segment 1. At this time, the electric actuators return to the fully retracted state, and the skin support component 4 provides stable support again, completing the unfolding action.

[0034] In summary, this invention, through the coordinated design of the segmented hinge component 3 and the skin support component 4, combined with symmetrically arranged and strictly synchronized drive components, successfully solves the long-standing technical problems of skin deformation, compression damage, and interference with the main structure that easily occur during ultra-large angle folding of the upper skin with large curvature. This achieves stable and smooth folding and unfolding operations of the wing within a 180° range. Furthermore, the mechanism of this invention has excellent adaptability to upper skins with different curvature ranges, making it suitable for a wide range of applications, especially for carrier-based aircraft, compound-wing UAVs, and other aviation equipment with stringent requirements for folding performance, reliability, and space utilization. All components can be manufactured using conventional processing techniques, and the assembly process is simple and quick, demonstrating outstanding engineering practical value and promising prospects for widespread application.

[0035] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

Claims

1. A universal wing folding mechanism, characterized in that, include: The main wing section (1) and the folding wing section (2) are provided, wherein the main wing section (1) can be fixedly connected to the fuselage; The folding assembly, connected to the main wing section (1) and the folding wing section (2), enables the folding wing section (2) to move; The folding assembly includes: The segmented hinge component (3) is located between the main wing section (1) and the folding wing section (2); The skin support component (4) is connected to the main wing section (1) and the folding wing section (2), and is also hinged to the segmented hinge component (3); The drive assembly (5) is used to connect the segmented hinge component (3) to the main wing segment (1) and the folding wing segment (2), and through the operation of the drive assembly (5), the segmented hinge component (3) and the folding wing segment (2) can be flipped at the same time, so that the folding wing segment (2) can be folded or unfolded.

2. The universal wing folding mechanism according to claim 1, characterized in that, The skin support component (4) includes: The fixed support arm (41) is fixedly connected to the main wing section (1) on one side and hinged to the segmented hinge component (3) on the other side; The movable support arm (42) is fixedly connected to the folding wing section (2) on one side and hinged to the segmented hinge component (3) on the other side; This allows both the movable support arm (42) and the segmented hinge component (3) to rotate.

3. The universal wing folding mechanism according to claim 2, characterized in that, The segmented hinge component (3) includes: The triangular hinge (32) is hinged to the drive assembly (5) at its bottom corner; Fold the main shaft (31) while passing through the fixed support arm (41), the triangular hinge (32) and the movable support arm (42).

4. The universal wing folding mechanism according to claim 3, characterized in that, The triangular hinges (32) are a plurality of each other and the plurality of triangular hinges (32) are arranged along the chord direction of the wing.

5. The universal wing folding mechanism according to claim 2, characterized in that, The fixed support arm (41) is provided with two sets of hinges, and the movable support arm (42) is provided with two protrusions. The fixed support arm (41) and the movable support arm (42) can be connected by the cooperation of the protrusions and the hinges.

6. The universal wing folding mechanism according to claim 1, characterized in that, The drive assembly (5) includes two push-pull components. One push-pull component connects the main wing segment (1) to the segmented hinge component (3), and the other push-pull component connects the folding wing segment (2) to the segmented hinge component (3). The two push-pull components can work simultaneously.

7. The universal wing folding mechanism according to claim 6, characterized in that, The push-pull component includes: The electric actuator has its output end hinged to the segmented hinge component (3). When the electric actuator extends or retracts, it can make the segmented hinge component (3) rotate. The mounting bracket is used to position the electric actuator.

8. The universal wing folding mechanism according to claim 1, characterized in that, A support structure is provided between the main wing section (1) and the folding wing section (2), and the skin support component (4) is connected to the main wing section (1) and the folding wing section (2) through the support structure.

9. The universal wing folding mechanism according to claim 8, characterized in that, The support structure includes two fixed support groups, which are symmetrically arranged. One fixed support group fixes the main wing section (1) to the skin support component (4), and the other fixed support group fixes the folding wing section (2) to the skin support component (4).

10. The universal wing folding mechanism according to claim 9, characterized in that, The fixed support assembly includes two sets of corner plates spaced apart along the chord of the wing.

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