Wing assembly turnover device

Abstract

The invention relates to the technical field of aircraft manufacturing, and one embodiment of the invention provides a wing assembly turnover device which comprises a first turnover frame, the first turnover frame is provided with a plurality of limiting parts, a limiting space is formed among the limiting parts, a second turnover frame is arranged in a lifting and translation mode relative to the first turnover frame, and the first turnover frame is provided with a plurality of limiting parts. The second turnover frame moves into or out of the limiting space after moving relative to the first turnover frame, the third turnover frame is movably arranged relative to the second turnover frame, the adjusting frames are arranged in a lifting and swinging mode relative to the third turnover frame, and the multiple adjusting frames are used for bearing aircraft wings. By means of the technical scheme, the technical problem that in the prior art, a wing transfer device is poor in flexibility 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 field of aircraft manufacturing, wings are key components of aircraft, and their assembly and turnover processes require extremely high performance and precision of equipment. However, traditional wing assembly and turnover devices have many obvious shortcomings and are difficult to meet the efficient and precise production needs of the modern aircraft manufacturing industry.

[0003] The early wing turnover devices had relatively simple functions, and most of them only supported the movement of the wing in a single direction, and could not achieve precise adjustment at multiple angles and multiple degrees of freedom. In the actual assembly process, multiple different types of equipment are often required to cooperate with each other to complete the adjustment of the wing attitude, which not only increases the investment cost of the equipment, but also makes the assembly process cumbersome and complicated. For example, when the wing is placed on the side of the aircraft fuselage for installation, since the equipment cannot achieve fine attitude fine-tuning, it is necessary to repeatedly switch the equipment and manually calibrate, resulting in low assembly efficiency, which seriously affects the production progress of the aircraft. During the transportation of the wing, manual calibration and positioning are mainly relied on. This method not only consumes a lot of manpower and time, but also due to the influence of human factors, it is easy to produce cumulative errors, causing the wing to shift during the transportation process, affecting the subsequent assembly accuracy. Once the wing is offset, it needs to be readjusted, which not only increases the production cost, but also may cause certain damage to the structure of the wing. 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: A first turnover rack, wherein the first turnover rack has a limiting portion, wherein the limiting portions are a plurality of limiting portions, and a limiting space is formed between the plurality of limiting portions; A second turnover frame, the second turnover frame is arranged to be lifted and translated relative to the first turnover frame, and after the second turnover frame moves relative to the first turnover frame, it moves into or out of the limited space; A third turnover frame, the third turnover frame is movably arranged relative to the second turnover frame, and the moving direction forms an angle with the moving direction of the second turnover frame relative to the first turnover frame; The adjusting frame is lifted and swung relative to the third turnover frame. There are several adjusting frames for supporting the wings of the aircraft.

[0006] 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: a first transfer wheel, the first transfer wheel being swingably arranged on the second turnover frame, and the first transfer wheel entering the guide groove after swinging; A lifting frame, the lifting frame is lifted and arranged on the second turnover frame; A second transfer wheel is rotatably arranged at the bottom of the lifting frame.

[0007] For example, at least one embodiment of the present disclosure provides a wing assembly turnover device, wherein there are a plurality of first transfer wheels arranged in at least two rows, the lifting frame is arranged between two adjacent rows of the first transfer wheels, and one end of the guide groove has a guide opening, and the guide opening is used to guide the first transfer wheel to enter the guide groove.

[0008] For example, in at least one embodiment of the present disclosure, a wing assembly turnover device is provided, wherein the second turnover frame includes: A support frame, the support frame is lifted and translated relative to the first turnover frame, and the lifting frame is lifted and translated on the support frame; Shock absorber, the shock absorber is arranged on the support frame, and the shock absorber is arranged in a plurality of rows; A support bracket is arranged on the shock absorber, and the third rotating frame is movably arranged relative to the support bracket.

[0009] For example, at least one embodiment of the present disclosure provides a wing assembly turnover device, further comprising: 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; A second linear driving member, wherein the second linear driving member is arranged on the third rotating frame, and the notch of the adjustment frame is arranged to be slidably matched with the output end of the second linear driving member.

[0010] 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 a notch of one of the adjustment holes.

[0011] For example, at least one embodiment of the present disclosure provides a wing assembly turnover device, wherein the second turnover frame has a cable through hole, and the cable through holes are arranged in a plurality of rows, and further comprises: Limiting plate; Connectors, there are several of the connectors, and the several connectors are respectively used to connect the upper and lower ends of the limiting plate with the limiting portion and the second turnover frame; A fixing cable, the fixing cable passing through the cable hole, for fixing the aircraft wing; A fixed hinge, the fixed hinge is rotatably arranged on the second turnover frame, the end of the fixing cable is arranged on the fixed hinge, and the fixed hinge is used for tightening and fixing the fixing cable; A locking member, wherein the locking member is arranged 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.

[0012] 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 limit clamping parts, and the locking member includes: 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; A rotating lock, the rotating lock is rotatably arranged in the installation cavity, the rotating lock passes through the fixed shell, the rotating lock has a clamping cavity, the clamping cavity is used to accommodate one of the limit clamping parts, the rotating lock has a ratchet part, and the ratchet part is located in the installation cavity; A pawl is swingably arranged on the fixed shell and extends into the installation cavity, and the pawl is used to engage with or cancel the engagement with the ratchet part.

[0013] 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 comprises: A plug-in unit is penetrated and slidably arranged on the connecting lock portion, and after sliding, the plug-in unit abuts against or cancels the abutment with the connecting member.

[0014] For example, at least one embodiment of the present disclosure provides a wing assembly turnover device, wherein the plug-in has a clamping portion, and 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.

[0015] The beneficial effects of the embodiments of the present disclosure are: 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 realized. Compared with the prior art transfer device 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 prior art transfer device, the aircraft wing can be assembled on the adjustment frame and transferred after assembly. A single device can complete complex posture adjustments, reduce the number of equipment switching times, and improve assembly efficiency.

[0016] The limiting part of the first turnover frame forms a limiting space, and the second turnover frame is mechanically linked to move in / out of the limiting space to achieve 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 scheme can reduce the manual calibration time, reduce the cumulative error, and avoid the risk of wing deviation.

[0017] The transfer devices of the prior art have separate functional modules, occupy a large space and have poor coordination. The present application realizes space compression of the equipment in a non-working state through the nested mobile design of the first turnover rack, the second turnover rack, and the third turnover rack, as well as the folding storage capacity of the adjustment rack. The occupied space is reduced, which is suitable for small workshop environments and improves site utilization.

[0018] The existing support frame is rigidly fixed and cannot adapt to the change of the wing's center of gravity, which can easily lead to imbalance. The application has multiple adjustment frames that independently control the lifting and swinging, and can adjust the supporting force in real time through system control according to the distribution of the wing's center of gravity. Combined with the physical constraints of the limited space, it prevents accidental displacement, improves the stability of wing transportation, and reduces the risk of collision or falling. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present disclosure, the following briefly introduces the drawings required for use in the description of the embodiments of the present disclosure. Obviously, the drawings described below are only some exemplary embodiments of the present disclosure. For those of ordinary skill in the art, other drawings can be obtained based on the contents of the exemplary embodiments of the present disclosure and these drawings without creative work.

[0020] Figure 1 It is a structural schematic diagram of an embodiment of the present disclosure; Figure 2 for Figure 1 A is a schematic diagram of the partially enlarged structure of the middle part; Figure 3 for Figure 1 A schematic diagram of the partially enlarged structure of B in the middle; Figure 4 for Figure 1 A schematic diagram of the partially enlarged structure of C in the middle; Figure 5 for Figure 1 A schematic diagram of the partially enlarged structure of D in the middle; Figure 6 for Figure 1 The local enlarged structural diagram of E in the middle; Figure 7 It is a schematic diagram of the structure of the locking member and related parts in the present disclosure; Figure 8 for Figure 7 A schematic diagram of the internal structure of the structure from one perspective; Fig. 9 for Figure 7 Another view of the structure: a schematic diagram of the internal structure; Fig.10 for Figure 7 Schematic diagram of the partially enlarged structure of F in the middle.

[0021] In the figure: first rotating frame 1, limiting part 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 The present disclosure is further described in detail below in conjunction with 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.

[0022] In order to simplify the drawings, only the parts related to the disclosure are schematically shown in each figure, and they do not represent the actual structure of the product. In addition, in order to simplify the drawings and facilitate understanding, in some figures, only one of the parts with the same structure or function is schematically shown, or only one of them is marked. In this article, "one" not only means "only one", but also means "more than one", and "several" includes "two" and "more than two".

[0023] In this document, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this disclosure can be understood according to specific circumstances.

[0024] In the present disclosure, unless otherwise expressly specified and limited, a first feature being “above” or “below” a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being “above”, “above”, and “above” a second feature includes that the first feature is 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 that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0025] In the description of this embodiment, terms such as "up", "down", "left", and "right" and other orientations or positional relationships are based on the orientations or positional relationships shown in the accompanying drawings and are only for the convenience of description and simplification of operation, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present disclosure.

[0026] 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.

[0027] like Figure 1 to Figure 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, there are a plurality of limiting portions 101, and a limiting space 102 is formed between the plurality of limiting portions 101, the second turnover frame 2 is lifted and lowered relative to the first turnover frame 1 and is arranged to be translated, 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 arranged to be moved relative to the second turnover frame 2, and the moving direction is arranged to form an angle with the translation direction of the second turnover frame 2, the adjustment frame 4 is lifted and lowered relative to the third turnover frame 3 and is arranged to be swung, there are a plurality of adjustment frames 4, and is used to support the wing of the aircraft.

[0028] For example, Figure 1As shown, the present application realizes 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 prior art transfer device 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 prior art, the aircraft wing can be assembled on the adjustment frame 4, and the transfer can be realized after assembly. A single device can complete complex posture adjustment, reduce the number of equipment switching times, and improve assembly efficiency.

[0029] The limiting portion 101 of the first turnover frame 1 forms a limiting space 102, and the mechanical linkage of the second turnover frame 2 moving in / out of the limiting space 102 is combined 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 fix the second transfer frame 2 through the limiting portion 101, which can reduce the manual calibration time, reduce the cumulative error and avoid the risk of wing deviation. 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 with the translation direction of the second turnover frame 2 provides convenience for the installation of the wing after the transfer is completed.

[0030] The transfer devices of the prior art have separate functional modules, occupy a large space and have poor coordination. The present application realizes space compression of the equipment in a non-working state through the nested mobile design of the first turnover frame 1, the second turnover frame 2, and the third turnover frame 3, and the folding storage capability of the adjustment frame 4. The occupied space is reduced, which is suitable for small workshop environments and improves site utilization.

[0031] The existing support frame is rigidly fixed and cannot adapt to the change of the wing's center of gravity, which easily leads to imbalance. The present application has multiple adjustment frames 4 that independently control the lifting and swinging, and can adjust the supporting force in real time through system control according to the distribution of the wing's center of gravity. Combined with the physical constraints of the limited space 102, it prevents accidental displacement, improves the stability of wing transportation, and reduces the risk of collision or falling.

[0032] In some examples, the first revolving frame 1 has a guide groove 103 and also includes a first transfer wheel 5, which is swingably set on the second revolving frame 2. The first transfer wheel 5 enters the guide groove 103 after swinging. 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.

[0033] For example, Figure 1 to Figure 6As shown, the guide groove 103 of the first revolving frame 1 cooperates with the first transfer wheel 5, and the first transfer wheel 5 swings and then embeds into the guide groove 103, forming a mechanical path locking. Compared with the defect that the revolving frame movement in the prior art relies on manual operation or simple slide rails and is easy to deviate from the preset path, the accuracy of operation is improved and the stability during the transfer process is ensured. The second transfer wheel 7 provides multi-directional rotation capability at the bottom of the lifting frame 6 to adapt to uneven ground or steering requirements.

[0034] The lifting mechanism of the prior art adopts a single-point drive, which is prone to tilt or shake when the load is uneven. The lifting frame 6 is integrated into the second circulating frame 2, and is synchronously driven by multiple groups of hydraulic / electric units to achieve dynamic balance during the lifting process. The first transfer wheel 5 and the guide groove 103 are engaged to provide additional support during lifting to avoid lateral shaking. The transfer wheel of the prior art has a single function, and it takes a long time to switch between the moving and positioning modes. 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 circulating frame 2 moves to the first circulating frame 1, the first transfer wheel 5 on the second circulating frame 2 is not at the same height as the guide groove 103, and the lifting frame 3 can drive the second transfer frame 2 to rise, raise the height of the first transfer wheel 3, and achieve the purpose of the second transfer frame 2 moving smoothly to the first transfer frame.

[0035] The mechanical linkage between the guide groove 103 and the first transfer wheel 5 reduces the positioning error, meeting the high-precision requirements of aviation manufacturing. At the same time, the deviation of the moving path is reduced, and the assembly efficiency is improved. The multi-point drive of the lifting frame 6 and the physical limit of the guide groove 103 eliminate the risk of shaking under heavy loads; the double transfer wheel design prevents accidental displacement of the equipment and effectively reduces the accident rate. At the same time, it can cope with complex ground conditions and reduce the need for modification of the workshop floor; quickly switch the mobile mode to adapt to multi-scenario operations.

[0036] In some examples, there are multiple 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 to enter the guide groove 103.

[0037] For example, Figure 5 As shown, a trumpet-shaped guide opening 104 is provided at one end of the guide groove 103, and the first transfer wheel 5 is guided to automatically slide into the guide groove 103 through the gradually expanding opening; the inclination angle design of the guide opening 104 satisfies the automatic correction of the initial position deviation. The alignment time of the transfer wheel 5 entering the guide groove 103 is greatly reduced, and the collision probability is reduced, thereby protecting the structural integrity of the transfer wheel 5 and the guide groove 103 and avoiding affecting the wing.

[0038] In the prior art, the transfer wheels and the lifting mechanism are arranged separately, and the equipment has a large horizontal dimension and is difficult to fit into a narrow space. In the present application, the parallel arrangement of the two rows of first transfer wheels 5 and the central lifting frame 6 form a symmetrical structure, which optimizes the horizontal space occupation; the guide port 104 and the vertical lifting path of the lifting frame 6 do not overlap, ensuring that the movement and lifting actions are independently controllable.

[0039] 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, a lifting frame 6 is raised and lowered on the support frame 201, a shock absorber 202 is set on the support frame 201, and several shock absorbers 202 are arranged in an array, a 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.

[0040] For example, Figure 1~Figure 3 As shown, the support frame 201 of the second turnover frame 2 can be lifted and moved relative to the first turnover frame 1. This design greatly enhances the flexibility of the device. In actual operation, by flexibly adjusting the position of the support frame 201, it can quickly adapt to the transportation needs of wings at different heights and positions, reducing the waiting time and adjustment times during the transportation process, and improving the overall work efficiency.

[0041] The lifting frame 6 is arranged on the support frame 201, which further optimizes the lifting function of the second rotating frame 2. The multiple hydraulic / electric units of the lifting frame 6 are synchronously driven, and combined with the stable structure of the support frame 201, the second rotating frame 2 can maintain a high degree of dynamic balance during the lifting process. Compared with the tilting and shaking problems that are prone to occur in the lifting mechanism in the prior art, this design effectively avoids these problems, ensures the stability of the wing during the lifting process, and reduces the risk of wing damage caused by unstable lifting.

[0042] A plurality of shock absorbers 202 are arranged on the support frame 201. The shock absorbers 202 are steel wire shock absorbers, which provide excellent shock absorption performance for the device. During the wing transportation process, whether it is the unevenness of the ground or the vibration generated when the equipment is moved, the shock absorbers 202 can effectively absorb and buffer these vibration energies. This greatly reduces the vibration impact on the wing placed on the support frame 203, further ensuring the safe transportation of the wing and avoiding damage to the wing structure or rotation of parts caused by vibration.

[0043] The support bracket 203 is arranged on the shock absorber 202, providing a stable support platform for the third turnover frame 3. The third turnover frame 3 is arranged to be movable relative to the support bracket 203, so that during the transportation process, the position of the third turnover frame 3 can be flexibly adjusted according to actual needs, so as to better cooperate with the adjustment frame 4 to adjust the attitude of the wing. This multi-level, multi-degree-of-freedom mobile design enables the entire device to complete complex wing transportation and assembly operations in a small space, thereby improving the applicability and work efficiency of the device.

[0044] In the prior art, the shock absorption effect of the device is not good, and it is easy to cause damage to the wings during transportation. The present application effectively solves this problem by setting the shock absorber 202. At the same time, the coordination between the various turnover frames in the prior art is poor, making it difficult to achieve efficient transportation and assembly operations. 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, greatly improving the overall performance and work efficiency of the device.

[0045] In some examples, a first linear drive member 8 is further included, the first linear drive member 8 is arranged on the second rotating frame 2, the third rotating 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 rotating frame 3, and the adjustment frame 4 is slidingly matched with the output end slot of the second linear drive member 9.

[0046] For example, Figure 1 , Figure 3 As 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 enhancing the device's ability to transport and assemble wings with complex postures.

[0047] The second linear drive 9 is arranged on the third turnover frame 3, and the notch of the adjustment frame 4 is slidably fitted at its output end. This design gives the adjustment frame 4 a more flexible adjustment capability. The second linear drive 9 can accurately control the swing angle and position of the adjustment frame 4. Compared with the previous adjustment that only relied on the electric push rod, more refined operations can now be achieved. During the wing assembly process, through the control of the adjustment frame 4 by the second linear drive 9, the attitude of the wing can be adjusted quickly and accurately according to the actual installation requirements of the wing, which greatly improves the accuracy and efficiency of the wing assembly.

[0048] Compared with the prior art, the present application achieves more precise and flexible control of the turnover frame and the adjustment frame through the provision of the first linear drive member 8 and the second linear drive member 9. The prior art often lacks such precise drive control, resulting in inaccurate position and attitude adjustment during wing transportation and assembly, requiring a lot 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 adjustment, providing a strong guarantee for efficient and safe assembly of the wing.

[0049] 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, and the output end of the second linear drive member 9 is slidably matched with a notch of one of the adjustment holes 401 .

[0050] For example, Figure 4 As shown, the plurality of adjustment holes 401 arranged on the adjustment frame 4 greatly enrich the connection modes between the adjustment frame 4 and the second linear drive member 9. Since the output end of the second linear drive member 9 is slidably matched with the notch of one of the adjustment holes 401, the adjustment frame 4 has more options for angle adjustment. In actual operation, the staff can flexibly select adjustment holes at different positions to slide with the notch of the second linear drive member 9 according to the specific size, shape and required assembly posture of the wing.

[0051] For example, when facing different types of wings, by replacing the adjustment holes that slide with the notches, the initial angle of the adjustment frame 4 can be quickly changed, thereby more accurately adapting to the attitude adjustment requirements of the wing. Compared with the design of fixed connection points, this flexible connection method significantly improves the versatility and adaptability of the adjustment frame 4. Before assembly, the working state of the adjustment frame 4 can be quickly adjusted by simply switching the adjustment holes, which greatly saves the time spent on adjusting the equipment and further improves the efficiency of wing assembly.

[0052] At the same time, the design of the adjustment hole 401 also enhances the control of the adjustment accuracy. The adjustment holes in different positions correspond to different adjustment angle ranges, and the staff can select the most suitable adjustment hole for connection according to the actual assembly accuracy requirements. This enables the adjustment frame 4 to more accurately control the angle change when fine-tuning the wing attitude, and effectively avoids the assembly error caused by insufficient adjustment accuracy. Compared with the prior art, the present application not only improves the flexibility and versatility of the adjustment frame 4 through the setting of the adjustment hole 401, but also further improves the accuracy and efficiency of the wing assembly, providing a more reliable guarantee for the efficient and high-quality assembly of the wing.

[0053] In some examples, the second revolving frame 2 has a cable through hole 204, and the cable through holes 204 are arranged in a plurality of rows. It also includes a limit plate 10, and a plurality of connecting members 11. The plurality of connecting members 11 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 wing of the aircraft. 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.

[0054] For example, Figure 1 As shown, the plurality of cable through holes 204 arranged on the second turnover frame 2 provide more fixing point options for fixing the aircraft wing. In actual operation, the staff can flexibly decide which cable through holes 204 the fixing cable 12 passes through according to the size and shape of the wing, thereby achieving a more stable and more fitting fixation of the wing. Compared with the fixed cable through hole layout, this flexible setting can adapt to wings of different models and sizes, improving the versatility of the turnover device.

[0055] The limiting plate 10 is connected to the limiting part 101 and the second turnover frame 2 through the connecting piece 11. This structure enhances the stability of the entire device. The limiting plate 10 can prevent the second turnover frame 2 from shifting during the movement process, ensuring the position accuracy of the wing during the transportation process. At the same time, the use of the connecting piece 11 makes the installation and removal of the limiting plate 10 more convenient, and is convenient for adjustment and replacement in different operating scenarios.

[0056] The fixing cable 12 passes through the cable hole 204 and is tightened and fixed by the fixing hinge 13, which greatly improves the convenience and reliability of fixing the wing. The fixing hinge 13 is rotatably arranged on the second turnover frame 2, and the staff can easily rotate the fixing hinge 13 to tighten or loosen the fixing cable 12 and adjust the fixing force according to the actual situation of the wing. Before the wing is transported, the fixing cable 12 can be quickly tightened to ensure that the wing will not shake or fall off during the transportation process; and when the wing needs to be removed, the fixing cable 12 can be conveniently loosened.

[0057] The locking member 14 is disposed 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, 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 connecting member 11 can prevent the fixed hinge 13 from accidentally rotating, and prevent 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.

[0058] 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 a 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. The rotating lock 1403 has a ratchet portion 1405, and the ratchet portion 1405 is located in the installation cavity 1402. 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.

[0059] For example, Figure 7~Figure 9 As shown, in the actual wing assembly turnover operation, the limit clamping parts 1301 at both ends of the fixed hinge 13 cooperate with the locking member 14. When performing the wing fixing task, the operator only needs to gently rotate the rotating lock 1403. With its precise mechanical design, the clamping cavity 1404 can quickly and accurately align the limit clamping part 1301 and accommodate it. The whole process is completed in one go, achieving rapid preliminary positioning. This operation greatly improves work efficiency on a time-sensitive production line.

[0060] The ratchet part 1405 on the rotating lock 1403 is more tightly engaged with the ratchet 1406. During the transportation of the wings of large transport aircraft, the transport vehicle may pass through bumpy roads, and the device may be subjected to large vibrations and impacts. However, thanks to the tight engagement between the ratchet part 1405 and the ratchet 1406, the fixed hinge 13 always remains stable, and the fixed cable 12 will not be loose at all, ensuring that the wing can be safely transported even under complex road conditions.

[0061] 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 and quickly release the limit clamping part 1301 from the clamping cavity 1404. In the scenario where the wing needs to be quickly transferred to the next process after assembly, 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.

[0062] 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, the plug-in 1409 passes through and is slidably set on the connecting lock portion 1407, and after sliding, the plug-in 1409 abuts against or cancels the abutment with the connecting member 11.

[0063] For example, Figure 7~Figure 9 As shown, in the actual wing assembly turnover operation, the limit clamps 1301 at both ends of the fixed hinge 13 cooperate with the locking member 14. The fixing groove 1408 of the connecting lock 1407 can accurately accommodate one end of the connecting member 11, realizing the tight positioning of the fixed shell 1401 and the connecting member 11. This high-precision positioning and matching ensures that there will be no relative displacement between the fixed shell 1401 and the connecting member 11 during the wing transportation process, laying a solid foundation for the subsequent locking operation of the plug-in 1409.

[0064] After the fixed hinge 13 is initially fixed by rotating the lock 1403 and the limit clamp 1301, the operator only needs to gently push the plug-in 1409 to make it penetrate and slide on the connecting lock 1407 until it abuts against the connecting member 11. After the plug-in 1409 abuts against the connecting member 11, the friction force generated can further lock the connecting member 11 to prevent it from loosening due to vibration or external force during the wing transportation process. During transportation, the wing may be subjected to various complex external forces such as road bumps and wind impacts. The close cooperation between the plug-in 1409 and the connecting member 11 greatly enhances the stability of the fixation.

[0065] In the face of harsh working environments, such as outdoor assembly sites with strong winds, or frequent bumps and vibrations during transportation, the close contact between the plug 1409 and the connector 11, and the cooperation between the ratchet 1405 and the pawl 1406 complement each other, doubly guaranteeing the stability of the fixed hinge 13, ensuring that the fixed cable 12 always firmly fixes the wing. The ratchet and pawl mechanism prevents the rotating lock 1403 from rotating in the opposite direction, and the plug 1409 prevents the connector 11 from loosening. The two cooperate with each other to form an all-round, multi-level fixed guarantee system.

[0066] When it is necessary to release the fixed hinge 13, the plug-in 1409 is slid in the reverse direction to cancel the contact with the connecting member 11, and then the ratchet 1406 is swung to cancel the engagement between the ratchet 1406 and the ratchet wheel 1405, and the rotating lock 1403 can be easily rotated to release the limit clamping part 1301 from the clamping cavity 1404. This multiple unlocking design not only ensures the safety of the fixation, but also takes into account the convenience of operation. In the scenario where the wing needs to be quickly transported to the next process after assembly, the entire unlocking process is efficient and smooth, which can save a lot of time for the entire production process.

[0067] In some examples, 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 .

[0068] For example, Figure 7 , Fig.10 As shown, from the perspective of stability, when the plug-in 1409 slides to abut against the connector 11 to achieve the reinforcement lock of the connector 11, the clamping part 1410 is synchronously abutted against the pawl 1406. This ingenious design is like adding double insurance to the entire fixing system. The original clamping of the pawl 1406 and the ratchet part 1405 can prevent the rotating lock 1403 from rotating in the opposite direction, and the restriction of the swing of the pawl 1406 by the clamping part 1410 further strengthens this locking mechanism. During the wing transportation process, facing various complex and challenging working conditions, such as the strong vibration caused by the rugged road surface and the inertial force caused by the size and weight of the wings of large aircraft, the clamping part 1410 can effectively prevent the pawl 1406 from being separated from the ratchet part 1405 due to accidental impact, ensuring that the fixed hinge 13 always maintains a stable locking state, so that the fixing cable 12 can continue to firmly fix the wing, greatly reducing the safety risks such as displacement and collision of the wing due to loose fixation during transportation.

[0069] 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, only the plug-in 1409 needs to be slid in the reverse direction to achieve two key actions at the same time: the plug-in 1409 cancels the abutment with the connecting member 11, thereby releasing the lock on the connecting member 11; the clamping portion 1410 cancels the abutment with the pawl 1406, thereby releasing the restriction on the swing of the pawl 1406. Thereafter, by simply swinging the pawl 1406 to cancel the clamping connection 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 requirements in the wing assembly process, greatly shorten the turnover time, and improve overall production efficiency.

[0070] Compared with the traditional fixing method, this innovative fixing structure design shows unique advantages. The traditional method is often difficult to cope with the fixing challenges under complex working conditions, and is prone to problems such as loosening and displacement. However, this device achieves a perfect combination of stability and operational convenience through the synergy between the clamping part 1410 of the plug-in 1409 and other components.

[0071] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present disclosure rather than to limit it. 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, which 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 revolving frame (1), the first revolving frame (1) having a limiting portion (101), the limiting portion (101) being a plurality of the limiting portions (101), and a limiting space (102) being formed between the plurality of the limiting portions (101); a second revolving frame (2), the second revolving frame (2) being arranged to be lifted and translated relative to the first revolving frame (1), and after the second revolving frame (2) moves relative to the first revolving frame (1), it moves into or out of the limited space (102); a third revolving frame (3), the third revolving frame (3) being arranged to move relative to the second revolving frame (2), and the moving direction being arranged to form an angle with the moving direction of the second revolving frame (2) relative to the first revolving frame (3); An adjusting frame (4), wherein the adjusting frame (4) is lifted and lowered and swung relative to the third turnover frame (3), and there are a plurality of the adjusting frames (4) for supporting an aircraft wing.

2. A 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 revolving frame (2), the first transfer wheel (5) entering the guide groove (103) after swinging; A lifting frame (6), the lifting frame (6) being 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. A 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, and 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), and the guide opening (104) is used to guide the first transfer wheel (5) to enter the guide groove (103).

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

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

6. A 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 arranged to be slidably 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 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 respectively used to connect the upper and lower ends of the limiting plate (10) with the limiting portion (101) and the second turnover frame (2); A fixing cable, the fixing cable passing through the cable hole (204) and used for fixing the aircraft wing; A fixed hinge (13), the fixed hinge (13) being rotatably mounted on the second rotating 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.

8. A wing assembly turnover device according to claim 7, characterized in that: Both ends of the fixed hinge (13) are provided with a limit clamping portion (1301), and the locking member (14) comprises: A fixed shell (1401), the fixed shell (1401) being arranged on the fixed hinge (13) and located on one side of the limiting plate (10), the fixed shell (1401) having a mounting cavity (1402); a rotating lock (1403), the rotating lock (1403) being rotatably disposed in the installation cavity (1402), the rotating lock (1403) penetrating the fixed shell (1401), the rotating lock (1403) having a clamping cavity (1404), the clamping cavity (1404) being used to accommodate one of the position-limiting clamping portions (1301), the rotating lock (1403) having a ratchet portion (1405), the ratchet portion (1405) being located in the installation cavity (1402); A ratchet pawl (1406), the ratchet pawl (1406) is swingably disposed on the fixed shell (1401) and extends into the installation cavity (1402), and the ratchet pawl (1406) is used to engage with or cancel the engagement with the ratchet wheel portion (1405).

9. A wing assembly turnover device according to claim 8, characterized in that: 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 comprises: A plug-in unit (1409), the plug-in unit (1409) penetrates and is slidably disposed on the connecting lock portion (1407), and the plug-in unit (1409) abuts against or cancels the abutment with the connecting member (11) after sliding.

10. A wing assembly turnover device according to claim 9, characterized in that: 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).

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