A wing assembly turn-around device

Abstract

The present disclosure relates to the technical field of aircraft manufacturing, and one embodiment of the present disclosure provides a wing assembly turnover device, which comprises a first turnover frame, the first turnover frame is provided with a plurality of limiting parts, the plurality of limiting parts form a limiting space, a second turnover frame is arranged to be lifted and translated relative to the first turnover frame, the second turnover frame moves into or out of the limiting space after moving relative to the first turnover frame, a third turnover frame is arranged to move relative to the second turnover frame, and an adjusting frame is arranged to be lifted and swung relative to the third turnover frame, the adjusting frame is provided with a plurality of adjusting frames for supporting an aircraft wing. Through the above technical scheme, the technical problem of poor flexibility of the wing transfer device in the prior art is solved.

Description

Technical Field

[0001] Embodiments of the present disclosure relate to the technical field of aircraft manufacturing, and in particular, to a wing assembly turnover device. Background Art

[0002] In the aircraft manufacturing industry, wings are critical components, and their assembly and turnover processes require extremely high performance and precision from the equipment. However, traditional wing assembly and turnover equipment has many significant shortcomings, making it difficult to meet the efficient and precise production needs of the modern aircraft manufacturing industry.

[0003] Early wing rotation devices had relatively limited functionality, mostly supporting only single-direction wing movement and failing to achieve precise adjustment across multiple angles and degrees of freedom. During the actual assembly process, multiple different types of equipment often required coordination to adjust the wing's attitude, increasing equipment costs and making the assembly process cumbersome and complex. For example, when placing the wing on the side of the aircraft fuselage for installation, the inability of the equipment to achieve precise attitude adjustments necessitated repeated equipment switching and manual calibration, resulting in low assembly efficiency and severely impacting aircraft production schedules. During the wing's transportation, manual calibration and positioning were primarily performed. This method was not only labor-intensive and time-consuming, but also prone to cumulative errors due to human error, causing the wing to shift during transportation, compromising subsequent assembly accuracy. Any shifting of the wing required readjustment, which not only increased production costs but also potentially damaged the wing structure. Summary of the Invention

[0004] In order to overcome the above-mentioned defects, an embodiment of the present disclosure provides a wing assembly turnover device, which solves the technical problem of poor flexibility of the wing transfer device in the prior art.

[0005] According to one aspect, at least one embodiment of the present disclosure provides a wing assembly turnover device, comprising:

[0006] a first turnover rack, wherein the first turnover rack has a plurality of limiting portions, and a limiting space is formed between the plurality of limiting portions;

[0007] a second turnover frame, the second turnover frame being arranged to rise and fall and to move horizontally relative to the first turnover frame, and the second turnover frame being moved relative to the first turnover frame to move into or out of the limited space;

[0008] a third turnover frame, the third turnover frame being arranged to move relative to the second turnover frame, and the moving direction thereof being arranged to form an angle with the moving direction of the second turnover frame relative to the first turnover frame;

[0009] An adjusting frame is arranged to be lifted and swung relative to the third turnover frame. There are several adjusting frames for supporting the wings of an aircraft.

[0010] For example, at least one embodiment of the present disclosure provides a wing assembly turnover device, wherein the first turnover frame has a guide groove and further includes:

[0011] a first transfer wheel, the first transfer wheel being swingably disposed on the second turnover frame, and the first transfer wheel entering the guide groove after swinging;

[0012] A lifting frame, the lifting frame is lifted and arranged on the second turnover frame;

[0013] A second transfer wheel is rotatably arranged at the bottom of the lifting frame.

[0014] For example, at least one embodiment of the present disclosure provides a wing assembly turnover device, wherein there are multiple first transfer wheels, which are arranged in at least two rows, and the lifting frame is arranged between two adjacent rows of the first transfer wheels. One end of the guide groove has a guide opening, and the guide opening is used to guide the first transfer wheel into the guide groove.

[0015] For example, in at least one embodiment of the present disclosure, a wing assembly turnover device is provided, wherein the second turnover frame includes:

[0016] A support frame, the support frame is arranged to be lifted and translated relative to the first turnover frame, and the lifting frame is lifted and translated on the support frame;

[0017] Shock absorber, the shock absorber is arranged on the support frame, and the shock absorber is arranged in a plurality of rows;

[0018] A supporting bracket is provided on the shock absorber, and the third turnover frame is movably provided relative to the supporting bracket.

[0019] For example, at least one embodiment of the present disclosure provides a wing assembly turnover device, further comprising:

[0020] a first linear driving member, wherein the first linear driving member is arranged on the second rotating frame, and the third rotating frame is arranged on an output end of the first linear driving member;

[0021] The second linear driving member is arranged on the third turnover frame, and the adjustment frame notch is slidingly matched with the output end of the second linear driving member.

[0022] For example, at least one embodiment of the present disclosure provides a wing assembly turnover device, wherein the adjustment frame has a plurality of adjustment holes, the plurality of adjustment holes are arranged in an array, and the output end of the second linear drive member is slidingly matched with one of the adjustment hole slots.

[0023] For example, at least one embodiment of the present disclosure provides a wing assembly turnover device, wherein the second turnover frame has cable through holes, and the cable through holes are arranged in a plurality of rows, and further comprises:

[0024] Limiting plate;

[0025] Connecting pieces, there are a plurality of connecting pieces, and the plurality of connecting pieces are used to connect the upper and lower ends of the limiting plate with the limiting portion and the second turnover frame respectively;

[0026] a fixing cable, the fixing cable passing through the cable through-hole and being used to fix the aircraft wing;

[0027] a fixed hinge, the fixed hinge being rotatably mounted on the second turnover frame, the end of the fixing cable being mounted on the fixed hinge, and the fixed hinge being used for tightening and fixing the fixing cable;

[0028] A locking member is provided on the fixed hinge and abuts against one end of the connecting member, and is used for locking the fixed hinge and one of the connecting members to prevent the fixed hinge from rotating.

[0029] For example, in at least one embodiment of the present disclosure, a wing assembly turnover device is provided, wherein both ends of the fixed hinge have a limit clamping portion, and the locking member includes:

[0030] A fixed shell, the fixed shell is arranged on the fixed hinge and is located on one side of the limiting plate, and the fixed shell has a mounting cavity;

[0031] a rotating lock member, the rotating lock member being rotatably disposed in the mounting cavity, the rotating lock member penetrating the fixed shell, the rotating lock member having a clamping cavity, the clamping cavity being used to accommodate one of the position-limiting clamping portions, the rotating lock member having a ratchet portion, the ratchet portion being located in the mounting cavity;

[0032] A pawl is swingably arranged on the fixed shell and extends into the installation cavity. The pawl is used to engage with or cancel the engagement with the ratchet part.

[0033] For example, at least one embodiment of the present disclosure provides a wing assembly turnover device, wherein the fixing shell has a connecting lock portion, the connecting lock portion has a fixing groove, one end of the connecting member is located in the fixing groove, and further includes:

[0034] The plug-in unit is penetrated and slidably arranged on the connecting lock portion, and the plug-in unit abuts or cancels the abutment with the connecting piece after sliding.

[0035] For example, at least one embodiment of the present disclosure provides a wing assembly turnover device, wherein the plug-in has a clamping portion. After the plug-in slides, the clamping portion abuts against or cancels the abutment with the pawl, and the clamping portion is used to limit the swing of the pawl.

[0036] The beneficial effects of the embodiments of the present disclosure are:

[0037] In the present disclosure, through the coordinated design of the second turnover frame, the third turnover frame and the adjustment frame, the multi-degree-of-freedom precise adjustment of the wing in horizontal movement, vertical lifting and lowering, and multi-angle swinging is achieved. Compared with the existing technology that only supports single-direction movement or fixed-angle support and requires multiple devices to cooperate to adjust the wing posture, after the transfer is completed, the aircraft wing can be directly placed on the side of the aircraft fuselage, and the wing can be installed by fine-tuning the posture. Compared with the transfer device of the existing technology, the aircraft wing can be assembled on the adjustment frame and transferred after assembly. A single device can complete complex posture adjustments, reducing the number of equipment switching times and improving assembly efficiency.

[0038] The first revolving frame's limiting structure forms a limited space, and combined with the mechanical linkage of the second revolving frame moving in and out of the limited space, this modular positioning of the wing transfer path is achieved. Compared to the existing technology, which has a simple limiting structure and relies on manual calibration, which is prone to cumulative errors, this application solution can reduce manual calibration time, reduce cumulative errors, and avoid the risk of wing deviation.

[0039] The existing transfer devices have separate functional modules, occupying a large space and lacking coordination. This application utilizes the nested, movable design of the first, second, and third turnover racks, along with the foldable storage capability of the adjustment rack, to achieve space compression when the equipment is not in operation. This reduces the space required, making it suitable for use in confined workshops and improving site utilization.

[0040] Existing support brackets are rigidly fixed and cannot adapt to changes in the wing's center of gravity, which can easily lead to imbalance. This application uses multiple adjustment brackets to independently control lifting and swinging. The system can adjust the support force in real time based on the wing's center of gravity distribution. Combined with the physical constraints of the confined space, this prevents accidental displacement, improves wing transport stability, and reduces the risk of collision or falling. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] To more clearly illustrate the technical solutions in the embodiments of the present disclosure, the following briefly describes the drawings required for use in describing the embodiments of the present disclosure. Obviously, the drawings described below are merely some exemplary embodiments of the present disclosure. Those skilled in the art can, without inventive effort, derive other drawings based on the content of the exemplary embodiments of the present disclosure and these drawings.

[0042] Figure 1 This is a schematic structural diagram of an embodiment of the present disclosure;

[0043] Figure 2 for Figure 1 A schematic diagram of the partially enlarged structure of the middle part;

[0044] Figure 3 for Figure 1 A schematic diagram of the partially enlarged structure of B in the middle;

[0045] Figure 4 for Figure 1 Schematic diagram of the partially enlarged structure of C in the middle;

[0046] Figure 5 for Figure 1 A schematic diagram of the partially enlarged structure of D in the middle;

[0047] Figure 6 for Figure 1 Schematic diagram of the partially enlarged structure of E in the middle;

[0048] Figure 7 It is a schematic structural diagram of the locking member and related parts in the present disclosure;

[0049] Figure 8 for Figure 7 A schematic diagram of the internal structure of the structure from one perspective;

[0050] Figure 9 for Figure 7 Another perspective of the structure: a schematic diagram of the internal structure;

[0051] Figure 10 for Figure 7 Schematic diagram of the locally enlarged structure of F in the middle.

[0052] Figure: First rotating frame 1, limiting portion 101, limiting space 102, guide groove 103, guide opening 104, second rotating frame 2, support frame 201, shock absorber 202, support frame 203, cable hole 204, third rotating frame 3, adjustment frame 4, adjustment hole 401, first transfer wheel 5, lifting frame 6, second transfer wheel 7, first linear drive member 8 , second linear drive member-9, limiting plate-10, connecting member-11, fixed hinge-13, limiting clamping part-1301, locking member-14, fixed shell-1401, mounting cavity-1402, rotating locking member-1403, clamping cavity-1404, ratchet part-1405, pawl-1406, connecting lock part-1407, fixing groove-1408, plug-in-1409, clamping part-1410. DETAILED DESCRIPTION

[0053] The present disclosure will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present disclosure, rather than to limit the present disclosure.

[0054] To simplify the drawings, only the parts relevant to the disclosure are schematically shown in each figure; they do not represent the actual structure of the product. Furthermore, to simplify the drawings and facilitate understanding, in some figures, only one of the components with the same structure or function is schematically shown or labeled. In this document, "one" not only means "only one" but also "more than one," and "several" includes "two" and "more than two."

[0055] It should be noted that, unless otherwise specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they can refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediary; and internal communication between two components. Those skilled in the art will understand the specific meanings of these terms in this disclosure based on the specific circumstances.

[0056] In the present disclosure, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature includes the first feature being directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0057] In the description of this embodiment, the terms "up", "down", "left", "right", etc., and the orientation or position relationship are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present disclosure.

[0058] In addition, in the description of the present application, the terms "first", "second", etc. are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0059] like Figures 1 to 10 As shown, it shows a wing assembly turnover device in an embodiment of the present disclosure, including a first turnover frame 1, the first turnover frame 1 has a limiting portion 101, and there are several limiting portions 101, and a limiting space 102 is formed between the several limiting portions 101. The second turnover frame 2 is lifted and lowered and translated relative to the first turnover frame 1. After the second turnover frame 2 moves relative to the first turnover frame 1, it moves into or out of the limiting space 102. The third turnover frame 3 is moved relative to the second turnover frame 2, and the moving direction is set at an angle to the translation direction of the second turnover frame 2. The adjustment frame 4 is lifted and lowered and swung relative to the third turnover frame 3. There are several adjustment frames 4 for supporting the aircraft wing.

[0060] For example, Figure 1 As shown, the present application realizes the multi-degree-of-freedom precise adjustment of the wing in horizontal movement, vertical lifting, and multi-angle swinging through the coordinated design of the second turnover frame 2, the third turnover frame 3 and the adjustment frame 4. Compared with the existing technology that only supports single-direction movement or fixed-angle support and requires multiple devices to cooperate to adjust the wing posture, the aircraft wing can be placed directly on the side of the aircraft fuselage after the transportation is completed, and the wing can be installed by fine-tuning the posture. Compared with the transportation device of the existing technology, the aircraft wing can be assembled on the adjustment frame 4 and transported after assembly. A single device can complete complex posture adjustment, reducing the number of equipment switching times and improving assembly efficiency.

[0061] The limiting portion 101 of the first turnover frame 1 forms a limiting space 102, which is combined with the mechanical linkage of the second turnover frame 2 moving in / out of the limiting space 102 to realize the modular positioning of the wing transfer path. Compared with the prior art, the limiting structure is simple, relies on manual calibration, and is prone to cumulative errors. The present application can achieve the fixation of the second transfer frame 2 by the limiting portion 101, which can reduce the manual calibration time, reduce the cumulative error and avoid the risk of wing offset. The third turnover frame 3 is arranged to be movable relative to the second turnover frame 2, and the way in which the moving direction is arranged at an angle to the translation direction of the second turnover frame 2 provides convenience for the installation of the wing after the transfer is completed.

[0062] Existing transfer devices have separate functional modules, occupying large spaces and lacking coordination. This application utilizes the nested, movable design of the first, second, and third revolving frames 1, 2, and 3, along with the foldable storage capability of the adjustment frame 4, to achieve space reduction when the device is not in operation. This reduces space usage, making it suitable for use in confined workshops and improving space utilization.

[0063] Existing support brackets are rigidly fixed and cannot adapt to changes in the wing's center of gravity, which can easily lead to imbalance. The present invention uses multiple adjustment brackets 4 to independently control lifting and swinging. This system can adjust the support force in real time based on the wing's center of gravity distribution. Combined with the physical constraints of the limited space 102, this prevents accidental displacement, improves the stability of the wing during transportation, and reduces the risk of collision or falling.

[0064] In some examples, the first revolving frame 1 has a guide groove 103 and also includes a first transfer wheel 5. The first transfer wheel 5 is swingably set on the second revolving frame 2. After swinging, the first transfer wheel 5 enters the guide groove 103. The lifting frame 6 is lifted and set on the second revolving frame 2, and the second transfer wheel 7 is rotatably set at the bottom of the lifting frame 6.

[0065] For example, Figures 1 to 6 As shown, the guide groove 103 of the first revolving frame 1 cooperates with the first transfer wheel 5. The first transfer wheel 5 swings and then engages the guide groove 103, forming a mechanical path lock. Compared to existing revolving frames that rely on manual operation or simple slides and are prone to deviation from the preset path, this system improves operational accuracy and ensures smooth transfer. The second transfer wheel 7 at the bottom of the lifting frame 6 provides multi-directional rotation capability to adapt to uneven ground or steering requirements.

[0066] The lifting mechanism of the prior art adopts a single-point drive, which is prone to tilting or shaking when the load is uneven. The lifting frame 6 is integrated into the second revolving frame 2 and is synchronously driven by multiple groups of hydraulic / electric units to achieve dynamic balance in the lifting process. The first transfer wheel 5 and the guide groove 103 are interlocked to provide additional support during lifting and lowering to avoid lateral shaking. The transfer wheels of the prior art have a single function, and it takes a long time to switch between movement and positioning mode. The swing design of the first transfer wheel 5 can quickly switch between the guide mode and the free movement mode; the rotation support device of the second transfer wheel 7 does not require additional tools when performing a simple mobile location change. When the second revolving frame 2 moves onto the first revolving frame 1, if the first transfer wheel 5 on the second revolving frame 2 is not at the same height as the guide groove 103, the lifting frame 3 can drive the second transfer frame 2 to rise, raising the height of the first transfer wheel 3, so as to achieve the purpose of smoothly moving the second transfer frame 2 to the first transfer frame.

[0067] The mechanical linkage between the guide slot 103 and the first transfer wheel 5 minimizes positioning errors, meeting the high-precision requirements of aviation manufacturing. This also reduces movement path deviation, improving assembly efficiency. The multi-point drive system of the lifting frame 6 and the physical limiter of the guide slot 103 eliminate the risk of vibration under heavy loads. The dual transfer wheel design prevents accidental equipment displacement, effectively reducing the accident rate. It can also cope with complex ground conditions, reducing the need for workshop floor modifications. Quickly switching between movement modes adapts to various operational scenarios.

[0068] In some examples, there are several first transfer wheels 5 arranged in at least two rows, and the lifting frame 6 is arranged between two adjacent rows of first transfer wheels 5. One end of the guide groove 103 has a guide opening 104, and the guide opening 104 is used to guide the first transfer wheel 5 into the guide groove 103.

[0069] For example, Figure 5 As shown, a trumpet-shaped guide opening 104 is provided at one end of the guide slot 103. This gradually widens the opening, guiding the first transfer wheel 5 to automatically slide into the guide slot 103. The angle of the guide opening 104 is designed to automatically correct for initial position deviations. This significantly reduces the time required to align the transfer wheel 5 within the guide slot 103, lowering the probability of collision and protecting the structural integrity of the transfer wheel 5 and the guide slot 103 while preventing impact on the wings.

[0070] In existing technologies, the transfer wheels and lifting mechanism are arranged separately, resulting in large lateral dimensions and difficulty fitting into confined spaces. In this application, the parallel arrangement of two rows of first transfer wheels 5 forms a symmetrical structure with a central lifting frame 6, optimizing lateral space usage. The guide opening 104 and the vertical lifting path of the lifting frame 6 do not overlap, ensuring independent and controllable movement and lifting.

[0071] In some examples, the second revolving frame 2 includes a support frame 201, which is raised and lowered and translated relative to the first revolving frame 1, the lifting frame 6 is raised and lowered on the support frame 201, the shock absorber 202 is set on the support frame 201, and the shock absorber 202 is arranged in a plurality of rows, the supporting frame 203 is set on the shock absorber 202, and the third revolving frame 3 is movably set relative to the supporting frame 203.

[0072] For example, Figures 1 to 3 As shown, the support frame 201 of the second revolving frame 2 can be raised, lowered, and moved relative to the first revolving frame 1, greatly enhancing the flexibility of the device. In practice, by flexibly adjusting the position of the support frame 201, it can quickly adapt to the needs of transporting wings at different heights and positions, reducing waiting time and the number of adjustments during the transfer process, thereby improving overall work efficiency.

[0073] Lifting frame 6, mounted on support frame 201, further optimizes the lifting function of second revolving frame 2. The synchronous actuation of multiple hydraulic / electric units within lifting frame 6, combined with the stable structure of support frame 201, enables second revolving frame 2 to maintain a high degree of dynamic balance during the lifting process. Compared to existing lifting mechanisms prone to tilting and shaking, this design effectively avoids these issues, ensuring stable wing movement during lifting and reducing the risk of wing damage caused by unstable lifting.

[0074] Several shock absorbers 202 are arranged on the support frame 201. These are wire rope shock absorbers, providing excellent shock absorption. During wing transport, whether it's ground unevenness or vibrations generated by the equipment's movement, these shock absorbers 202 effectively absorb and buffer these vibrations. This significantly minimizes the impact of vibration on the wing resting on the support frame 203, further ensuring safe transport and preventing structural damage or component rotation caused by vibration.

[0075] Support bracket 203, mounted on shock absorber 202, provides a stable support platform for third revolving frame 3. The third revolving frame 3 is movable relative to support bracket 203, enabling flexible adjustment of its position during transport, thereby coordinating with adjustment frame 4 to adjust the wing's posture. This multi-level, multi-degree-of-freedom design enables the entire device to complete complex wing transport and assembly operations within a confined space, improving its applicability and operational efficiency.

[0076] In the prior art, the device's shock absorption effect is poor, which can easily damage the wings during transport. The present application effectively solves this problem through the provision of shock absorbers 202. At the same time, the coordination between the various turnover frames in the prior art is poor, making efficient transport and assembly operations difficult. The present application achieves close coordination between the various turnover frames through the optimized design of the various components of the second turnover frame 2, significantly improving the overall performance and operating efficiency of the device.

[0077] In some examples, a first linear drive member 8 is further included, the first linear drive member 8 is arranged on the second revolving frame 2, the third revolving frame 3 is arranged on the output end of the first linear drive member 8, the second linear drive member 9 is arranged on the third revolving frame 3, and the adjustment frame 4 is slidingly matched with the output end slot of the second linear drive member 9.

[0078] For example, Figure 1 、 Figure 3As shown, the first linear drive 8 is arranged on the second revolving frame 2, and the third revolving frame 3 is located at its output end. This makes the movement of the third revolving frame 3 more precise and controllable, and the first linear drive 8 can drive the third revolving frame 3 to move in a specific direction according to preset programs and instructions. Since its driving direction is set at an obtuse angle to the straight direction of the guide groove 103, this unique layout provides more possibilities for the movement path of the third revolving frame 3. In actual operation, when the position of the wing needs to be adjusted, the third revolving frame 3 can be moved at an oblique angle under the action of the first linear drive 8, and cooperate with other revolving frames and adjustment frames to achieve multi-dimensional adjustment of the wing position, further improving the device's ability to transport and assemble wings with complex postures.

[0079] The second linear drive 9 is mounted on the third rotating frame 3, with the notch in the adjustment frame 4 slidingly fitted into its output end. This design allows for greater flexibility in the adjustment of the adjustment frame 4. The second linear drive 9 precisely controls the swing angle and position of the adjustment frame 4, enabling more refined operation than previously possible adjustments solely through electric push rods. During wing assembly, the second linear drive 9 controls the adjustment frame 4, enabling quick and accurate adjustment of the wing's posture based on actual installation requirements, significantly improving the precision and efficiency of wing assembly.

[0080] Compared to the prior art, the present application achieves more precise and flexible control of the turnover frame and adjustment frame through the provision of the first linear drive member 8 and the second linear drive member 9. The prior art often lacks this precise drive control, resulting in imprecise position and attitude adjustments during wing transportation and assembly, requiring a significant amount of time and manpower for repeated adjustments. The design of the present application not only improves work efficiency but also reduces the risk of wing damage caused by improper adjustments, providing a strong guarantee for efficient and safe wing assembly.

[0081] In some examples, the adjustment frame 4 has a plurality of adjustment holes 401 , and the plurality of adjustment holes 401 are arranged in an array. The output end of the second linear drive member 9 is slidingly matched with a notch of one of the adjustment holes 401 .

[0082] For example, Figure 4 As shown, the multiple adjustment holes 401 arranged in a row on the adjustment frame 4 greatly enrich the connection options between the adjustment frame 4 and the second linear actuator 9. Since the output end of the second linear actuator 9 slides into a notch in one of the adjustment holes 401, this provides more options for angle adjustment of the adjustment frame 4. In actual operation, personnel can flexibly select different adjustment holes in different locations to slide into the notch in the second linear actuator 9 based on the specific size and shape of the wing and the desired assembly posture.

[0083] For example, when working with different wing models, the initial angle of the adjustment bracket 4 can be quickly changed by replacing the adjustment holes that slide into the notches, thereby more precisely adapting to the wing's required attitude. This flexible connection method significantly improves the versatility and adaptability of the adjustment bracket 4 compared to designs with fixed connection points. Before assembly, the operating state of the adjustment bracket 4 can be quickly adjusted by simply switching the adjustment holes, significantly reducing the time spent adjusting the equipment and further improving the efficiency of wing assembly.

[0084] At the same time, the design of adjustment hole 401 also enhances control over adjustment accuracy. Adjustment holes in different positions correspond to different adjustment angle ranges. Workers can select the most appropriate adjustment hole for connection based on the actual assembly accuracy requirements. This allows the adjustment frame 4 to more accurately control angle changes when fine-tuning the wing attitude, effectively avoiding assembly errors caused by insufficient adjustment accuracy. Compared with the prior art, the provision of adjustment hole 401 in this application not only enhances the flexibility and versatility of the adjustment frame 4, but also further improves the accuracy and efficiency of wing assembly, providing a more reliable guarantee for efficient and high-quality wing assembly.

[0085] In some examples, the second revolving frame 2 has a cable through-hole 204, which is arranged in a plurality of rows, and further includes a limit plate 10 and a plurality of connecting members 11, which are respectively used to connect the upper and lower ends of the limit plate 10 with the limit portion 101 and the second revolving frame 2. The fixing cable passes through the cable through-hole 204 and is used to fix the aircraft wing. The fixed hinge 13 is rotatably arranged on the second revolving frame 2, and the end of the fixing cable is arranged on the fixed hinge 13. The fixed hinge 13 is used to tighten and fix the fixing cable. The locking member 14 is arranged on the fixed hinge 13 and abuts against one end of the connecting member 11, and is used to lock the fixed hinge 13 with a connecting member 11 to prevent the fixed hinge 13 from rotating.

[0086] For example, Figure 1 As shown, the multiple cable holes 204 arranged in an array on the second turnover frame 2 provide more options for securing the aircraft wing. In practice, personnel can flexibly determine which cable holes 204 to pass the fixing cable 12 through based on the size and shape of the wing, thereby achieving a more stable and snug fit. Compared to a fixed cable hole layout, this flexible arrangement can accommodate wings of varying models and sizes, enhancing the versatility of the turnover device.

[0087] The limiting plate 10 is connected to the limiting portion 101 and the second revolving frame 2 via a connector 11. This structure enhances the stability of the entire device. The limiting plate 10 prevents the second revolving frame 2 from shifting during movement, ensuring the precise positioning of the wing during transport. Furthermore, the use of the connector 11 facilitates both installation and removal of the limiting plate 10, facilitating adjustment and replacement in different operational scenarios.

[0088] The securing cable 12 passes through the cable hole 204 and is tightened and secured by the securing hinge 13, greatly improving the convenience and reliability of wing securing. The securing hinge 13 is rotatably mounted on the second revolving frame 2, allowing operators to easily rotate the hinge 13 to tighten or loosen the securing cable 12, adjusting the securing force according to the actual situation of the wing. Before transporting the wing, the securing cable 12 can be quickly tightened to prevent the wing from shaking or falling off during transportation; and the securing cable 12 can be easily loosened when the wing needs to be removed.

[0089] The locking member 14 is provided on the fixed hinge 13 and abuts against one end of the connector 11, and is used to lock the fixed hinge 13 to one connector 11, further enhancing the stability of the fixation. When the fixed hinge 13 tightens the fixing cable 12, the cooperation between the locking member 14 and the connector 11 can prevent the fixed hinge 13 from accidentally rotating and the fixing cable 12 from loosening, thereby ensuring the safety of the wing during the entire transportation and assembly process. Compared with the prior art, the present application has significantly improved the flexibility, stability, and safety of wing fixation through the synergistic effect of these newly added components, providing more powerful support for the efficient and safe transportation and assembly of the wing.

[0090] In some examples, both ends of the fixed hinge 13 have a limit clamping portion 1301, and the locking member 14 includes a fixed shell 1401, which is set on the fixed hinge 13 and located on one side of the limit plate 10. The fixed shell 1401 has an installation cavity 1402, and the rotating lock 1403 is rotatably set in the installation cavity 1402. The rotating lock 1403 passes through the fixed shell 1401, and the rotating lock 1403 has a clamping cavity 1404. The clamping cavity 1404 is used to accommodate a limit clamping portion 1301, and the rotating lock 1403 has a ratchet portion 1405. The ratchet portion 1405 is located in the installation cavity 1402, and the pawl 1406 is swingably set on the fixed shell 1401 and extends into the installation cavity 1402. The pawl 1406 is used to engage with or cancel the engagement with the ratchet portion 1405.

[0091] For example, Figures 7 to 9As shown, during actual wing assembly operations, the position-limiting clamps 1301 at each end of the fixed hinge 13 cooperate with the locking member 14. To secure the wing, the operator simply turns the rotating locking member 1403. Thanks to its precise mechanical design, the locking cavity 1404 quickly and accurately aligns with the position-limiting clamp 1301 and accommodates it. The entire process is seamless, achieving rapid initial positioning. This operation significantly improves work efficiency on time-sensitive production lines.

[0092] The ratchet portion 1405 on the rotating lock 1403 forms a tighter engagement with the pawl 1406. During the transport of large transport aircraft wings, the transport vehicle may traverse bumpy roads, subjecting the device to significant vibration and impact. However, thanks to the tight engagement between the ratchet portion 1405 and the pawl 1406, the fixed hinge 13 remains stable, and the fixing cable 12 does not loosen at all, ensuring safe transport of the wing even in complex road conditions.

[0093] When it is necessary to loosen the fixed hinge 13, the operator only needs to gently swing the pawl 1406 to easily cancel the engagement between the pawl 1406 and the ratchet part 1405. At this time, the rotating lock 1403 can rotate freely, quickly releasing the limit clamping part 1301 from the clamping cavity 1404. In the scenario where the wing assembly is completed and needs to be quickly transferred to the next process, this convenient unlocking method can save a lot of time for the entire production process. Compared with traditional fixing methods, such as simple bolt tightening or snap fixation, the structural design of this device has achieved all-round transcendence in safety, stability and ease of operation. It not only provides reliable protection for the wing assembly turnover device in the wing fixing link, but also greatly improves the efficiency and quality of the entire wing production and assembly process in actual production applications.

[0094] In some examples, the fixed shell 1401 has a connecting lock portion 1407, the connecting lock portion 1407 has a fixing groove 1408, one end of the connecting member 11 is located in the fixing groove 1408, and also includes a plug-in 1409, which passes through and is slidably set on the connecting lock portion 1407. After sliding, the plug-in 1409 abuts against or cancels the abutment with the connecting member 11.

[0095] For example, Figures 7 to 9 As shown, during actual wing assembly and turnover, the stopper portions 1301 at both ends of the fixed hinge 13 cooperate with the locking member 14. The fixing groove 1408 of the connecting lock 1407 precisely accommodates one end of the connector 11, ensuring a tight positioning of the fixed housing 1401 and the connector 11. This high-precision positioning ensures that relative displacement between the fixed housing 1401 and the connector 11 does not occur during wing transportation, laying a solid foundation for the subsequent locking operation of the plug-in 1409.

[0096] After the fixed hinge 13 is initially secured by rotating the locking element 1403 and the stopper 1301, the operator simply pushes the insert 1409, causing it to penetrate and slide onto the connecting lock 1407 until it contacts the connector 11. The friction generated by the contact between the insert 1409 and the connector 11 further secures the connector 11, preventing it from loosening due to vibration or external forces during transport. During transportation, the wing may be subjected to various complex external forces such as road bumps and wind impact. The tight fit between the insert 1409 and the connector 11 greatly enhances the stability of the fixation.

[0097] In harsh operating environments, such as windy outdoor assembly sites or the frequent jolting and vibrations of transportation, the tight contact between insert 1409 and connector 11, and the coordinated action between ratchet 1405 and pawl 1406, provide a dual guarantee for the stability of fixed hinge 13 and ensure that fixed cable 12 remains firmly fixed to the wing. The ratchet and pawl mechanism prevents reverse rotation of rotating lock 1403, while insert 1409 prevents loosening of connector 11. The two work together to form a comprehensive, multi-layered securement system.

[0098] To release the fixed hinge 13, insert 1409 is slid in the opposite direction to release it from contact with connector 11. Then, pawl 1406 is swung to release its engagement with ratchet 1405. This allows for easy rotation of rotary lock 1403, releasing limiter 1301 from clamping cavity 1404. This multi-unlocking design ensures both secure fixation and ease of operation. This efficient and smooth unlocking process saves significant time in production processes, especially when wing assembly requires rapid transfer to the next step.

[0099] In some examples, the plug-in 1409 has a latching portion 1410 . After the plug-in 1409 slides, the latching portion 1410 abuts against or cancels the abutment with the pawl 1406 . The latching portion 1410 is used to limit the swinging of the pawl 1406 .

[0100] For example, Figure 7 、 Figure 10As shown, from a stability perspective, when the plug 1409 slides into contact with the connector 11, achieving a reinforced lock on the connector 11, the latch 1410 simultaneously engages the pawl 1406. This ingenious design acts as a double insurance policy for the entire fixing system. The original engagement between the pawl 1406 and the ratchet 1405 prevents the rotating lock 1403 from rotating in the opposite direction, and the restriction of the pawl 1406's swing by the latch 1410 further strengthens this locking mechanism. During the wing transport process, facing various complex and challenging working conditions, such as strong vibrations caused by rough roads and the inertial forces caused by the size and weight of large aircraft wings, the latch 1410 effectively prevents the pawl 1406 from disengaging from the ratchet 1405 due to accidental impacts, ensuring that the fixed hinge 13 always maintains a stable locked state, thereby allowing the fixing cable 12 to continuously and firmly secure the wing, greatly reducing the safety risks of displacement and collision caused by loose fixation during wing transport.

[0101] From the perspective of operational convenience, this design does not bring additional complexity to the unlocking operation. When it is necessary to loosen the fixed hinge 13, it is only necessary to slide the plug-in 1409 in the opposite direction to achieve two key actions at the same time: the plug-in 1409 cancels the contact with the connecting member 11, thereby releasing the lock on the connecting member 11; the clamping portion 1410 cancels the contact with the pawl 1406, thereby releasing the restriction on the swing of the pawl 1406. After that, by simply swinging the pawl 1406 to cancel the engagement with the ratchet portion 1405, the rotating lock 1403 can be easily rotated to complete the release of the limiting clamping portion 1301 from the clamping cavity 1404. The entire unlocking process is coherent and efficient. In actual production scenarios, it can quickly respond to the turnover needs in the wing assembly process, significantly shorten the turnover time, and improve overall production efficiency.

[0102] This innovative fixing structure design offers unique advantages over traditional fixing methods. Traditional methods often struggle to meet the challenges of fixing in complex working conditions, prone to loosening and displacement. However, this device, through the synergistic effect of the locking portion 1410 of the plug-in 1409 and other components, achieves a perfect combination of stability and operational convenience.

[0103] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present disclosure and are not limiting. Although the present disclosure has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solutions of the present disclosure may be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the present disclosure, and all of these should be included in the scope of the claims of the present disclosure.

Claims

1. A wing assembly turnover device, characterized in that: include: A first turnover rack (1), wherein the first turnover rack (1) has a limiting portion (101), wherein the limiting portions (101) are multiple, and a limiting space (102) is formed between the multiple limiting portions (101); a second turnover frame (2), the second turnover frame (2) being arranged to be lifted and translated relative to the first turnover frame (1), and the second turnover frame (2) being moved relative to the first turnover frame (1) to move into or out of the limited space (102); a third turnover frame (3), the third turnover frame (3) being arranged to move relative to the second turnover frame (2), and the moving direction and the moving direction of the second turnover frame (2) relative to the first turnover frame (1) forming an angle; An adjusting frame (4), wherein the adjusting frame (4) is lifted and lowered relative to the third turnover frame (3) and is swingably arranged, and the adjusting frame (4) is in a plurality and is used to support an aircraft wing; The second turnover frame (2) has a cable through hole (204), wherein the cable through holes (204) are arranged in a plurality of rows, and further comprises: Limiting plate (10); Connecting members (11), there are a plurality of connecting members (11), and the plurality of connecting members (11) are used to connect the upper and lower ends of the limiting plate (10) with the limiting portion (101) and the second turnover frame (2) respectively; A fixing cable, the fixing cable passing through the cable hole (204) for fixing the aircraft wing; A fixed hinge (13), the fixed hinge (13) being rotatably mounted on the second turnover frame (2), the end of the fixing cable being mounted on the fixed hinge (13), and the fixed hinge (13) being used for tightening and fixing the fixing cable; a locking member (14), the locking member (14) being arranged on the fixed hinge (13) and abutting against one end of the connecting member (11), and being used for locking the fixed hinge (13) and one of the connecting members (11) to prevent the fixed hinge (13) from rotating; Both ends of the fixed hinge (13) have a limit clamping portion (1301), and the locking member (14) includes: A fixed shell (1401), the fixed shell (1401) is arranged on the fixed hinge (13) and is located on one side of the limiting plate (10), and the fixed shell (1401) has a mounting cavity (1402); A rotating lock (1403), the rotating lock (1403) having a ratchet portion (1405), the ratchet portion (1405) being located within the mounting cavity (1402); A pawl (1406), the pawl (1406) is swingably disposed on the fixed shell (1401) and extends into the mounting cavity (1402), the pawl (1406) being used to engage with or cancel the engagement with the ratchet portion (1405); The fixing shell (1401) has a connecting lock portion (1407), the connecting lock portion (1407) has a fixing groove (1408), one end of the connecting member (11) is located in the fixing groove (1408), and further includes: A plug-in unit (1409), the plug-in unit (1409) is passed through and slidably disposed on the connecting lock portion (1407), and the plug-in unit (1409) abuts or cancels the abutment with the connecting member (11) after sliding; The plug-in (1409) has a clamping portion (1410). After the plug-in (1409) slides, the clamping portion (1410) abuts against or cancels the abutment with the pawl (1406). The clamping portion (1410) is used to limit the swing of the pawl (1406).

2. The wing assembly turnover device according to claim 1, characterized in that: The first turnover frame (1) has a guide groove (103) and further comprises: a first transfer wheel (5), the first transfer wheel (5) being swingably disposed on the second circulatory frame (2), and the first transfer wheel (5) entering the guide groove (103) after swinging; A lifting frame (6), the lifting frame (6) is lifted and arranged on the second turnover frame (2); A second transfer wheel (7), the second transfer wheel (7) is rotatably arranged at the bottom of the lifting frame (6).

3. The wing assembly turnover device according to claim 2, characterized in that: There are a plurality of first transfer wheels (5) arranged in at least two rows. The lifting frame (6) is arranged between two adjacent rows of the first transfer wheels (5). One end of the guide groove (103) has a guide opening (104). The guide opening (104) is used to guide the first transfer wheel (5) into the guide groove (103).

4. The wing assembly turnover device according to claim 2, characterized in that: The second turnover rack (2) comprises: A support frame (201), the support frame (201) is arranged to be lifted and translated relative to the first turnover frame (1), and the lifting frame (6) is arranged to be lifted and translated on the support frame (201); A shock absorber (202), the shock absorber (202) being arranged on the support frame (201), and the shock absorber (202) being arranged in a plurality; A support bracket (203), wherein the support bracket (203) is arranged on the shock absorber (202), and the third turnover frame (3) is movably arranged relative to the support bracket (203).

5. The wing assembly turnover device according to claim 3, characterized in that: Also includes: a first linear drive (8), wherein the first linear drive (8) is arranged on the second rotating frame (2), and the third rotating frame (3) is arranged on the output end of the first linear drive (8); A second linear drive member (9), wherein the second linear drive member (9) is arranged on the third turnover frame (3), and the adjustment frame (4) is arranged to be slidably matched with the output end notch of the second linear drive member (9).

6. The wing assembly turnover device according to claim 5, characterized in that: The adjustment frame (4) has a plurality of adjustment holes (401), the plurality of adjustment holes (401) are arranged in an array, and the output end of the second linear drive member (9) is slidingly matched with a notch of one of the adjustment holes (401).

7. The wing assembly turnover device according to claim 1, characterized in that: The rotating lock member (1403) is rotatably arranged in the installation cavity (1402), and the rotating lock member (1403) passes through the fixed shell (1401). The rotating lock member (1403) has a clamping cavity (1404), and the clamping cavity (1404) is used to accommodate one of the limit clamping parts (1301).

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