Large aircraft skin automatic spraying and curing device and control method thereof

Abstract

The invention relates to the technical field of aircraft surface spraying, and discloses an automatic spraying and curing device for large aircraft skin and a control method thereof, comprising a spraying unit, wherein the spraying unit comprises a conveying module, a return module and a feeding module, wherein the conveying module comprises a conveying belt, wherein a middle-layer substrate is arranged inside the conveying belt, wherein a slide groove is provided on the middle-layer substrate, wherein a synchronization mechanism is arranged at the slide groove on the middle-layer substrate, and wherein the return module comprises a clamping mechanism and a clamping mechanism; a curing unit, wherein the curing unit comprises a collecting trough, wherein a curing lamp is installed on the collecting trough, and wherein the curing unit is used for curing the aircraft skin after spraying; the invention transports the aircraft skin by arranging a conveying belt, and during the transporting process, drives a nozzle to follow the movement of the aircraft skin by a mounting block and other structures, and sprays, and there is no need to arrange a nozzle on the entire conveying path of the aircraft skin, thereby reducing the waste of paint.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft surface spraying, and in particular relates to an automatic spraying and curing device for large aircraft skin and a control method thereof. Background Art

[0002] The spraying method of aircraft skin mostly adopts fluid spraying method. Before the aircraft is assembled, large flat aircraft skin can be processed centrally, which can improve the spraying efficiency. The common fluid spraying method can adopt fluid spraying line, which can process multiple aircraft skins at the same time, but it will cause a lot of paint waste during spraying. The use of intelligent spraying equipment to spray aircraft skin can effectively reduce the waste of paint, but it will cause a significant reduction in work efficiency.

[0003] A Chinese patent application with authorization announcement number CN218251003U discloses a clamp for spray processing of panels, which can adjust the extension or shortening of the hydraulic rod according to the length of the panel, thereby adjusting the distance between the upper and lower clamping mechanisms to adapt to panels of different lengths; through the cooperation of the internal and external threads of the threaded rod and the clamping plate, panels of different thicknesses can be clamped, so this device is suitable for clamping panels of various sizes. At the same time, a plurality of irregularly raised rubber fastening plates are provided on the surface to further improve the stability of the clamping.

[0004] However, this technical solution still has at least the following defects: this solution not only cannot solve the problem of paint waste, but also requires each plate to be loaded and unloaded separately during spraying, which is not suitable for spraying multiple plates, and the efficiency is greatly reduced. In view of this, the present invention is proposed. Summary of the invention

[0005] In order to solve the above technical problems, the present invention provides an automatic spraying and curing device for large aircraft skin and a control method thereof. The aircraft skin is transported by arranging a conveyor belt, and during the transportation process, the nozzle is driven by the installation block and other structures to follow the movement of the aircraft skin and spray. There is no need to set the nozzle on the entire conveying path of the aircraft skin, thereby reducing the waste of paint. Compared with the intelligent and precisely controlled spraying equipment, it also has higher mechanical stability and reduces the technical cost. By arranging a curing lamp to perform light curing on the aircraft skin, the curing process can be completed quickly, and the cured aircraft skin naturally slides down under the action of gravity without manual operation. By arranging structures such as a lever, the aircraft skin is sampled and falls on the conveyor belt. It only needs to operate the unloading rack to place the aircraft skin on one end of the conveyor belt before the installation block is reset. The operation is simple.

[0006] The technical solution adopted by the present invention to solve its technical problem is:

[0007] Large aircraft skin automatic spraying and curing device, including:

[0008] The spraying unit includes a conveying module, a return module and a feeding module. The conveying module includes a conveying belt, a middle-layer substrate is arranged inside the conveying belt, a slide groove is provided on the middle-layer substrate, and a synchronization mechanism is arranged at the slide groove on the middle-layer substrate. The return module includes a clamping mechanism and a card connection mechanism. The return module drives the conveying belt to drive the spraying unit to move in the opposite direction through the card connection mechanism and the clamping mechanism. The feeding module is used for feeding the aircraft skin; the spraying unit is used for spraying paint on the aircraft skin;

[0009] The curing unit comprises a collecting tank on which a curing lamp is installed. The curing unit is used for curing the sprayed aircraft skin.

[0010] As a preferred embodiment of the present invention, a sliding mechanism is arranged inside the middle-layer substrate, and the sliding mechanism includes a mounting block, and the mounting block is slidably mounted inside the middle-layer substrate. A pushing component is installed inside the mounting block, and the pushing component is used to control the synchronization mechanism. Side panels are fixedly mounted at both ends of the mounting block, and a nozzle is fixedly mounted on the top of the side panel.

[0011] As a preferred embodiment of the present invention, the synchronization mechanism includes an open groove, which is provided on a conveyor belt, and a cylinder is fixedly installed on one end of the conveyor belt at the open groove. The synchronization mechanism also includes a baffle, which is rotatably connected to the top of the mounting block, and the baffle is adapted to the cylinder. An elastic reset component is provided at one end of the baffle, and a locking control component is provided at the other end.

[0012] As a preferred embodiment of the present invention, the elastic reset assembly includes a first telescopic rod and a first spring, the first spring is movably sleeved on the outside of the first telescopic rod, the first telescopic rod is rotatably connected between the baffle and the mounting block, the lock control assembly includes a seesaw, a baffle is fixedly installed at the bottom of the seesaw, one end of the seesaw is fixedly connected to the baffle, and a lock plate is provided at one end of the seesaw.

[0013] As a preferred embodiment of the present invention, the pushing assembly includes a connecting frame, which is slidably connected inside the mounting block, and one end of the connecting frame extends to the outside of the mounting block, one end of the locking plate is fixedly connected to one end of the connecting frame, a groove is provided inside the mounting block, a reset spring plate is provided inside the groove, and the reset spring plate is connected to the connecting frame.

[0014] As a preferred embodiment of the present invention, the clamping mechanism includes a clamping plate, the clamping plate is rotatably connected to the side plate, a protrusion is installed on one side of the bottom of the clamping plate, and tooth grooves are provided on both sides of the conveyor belt, and the protrusions are adapted to the tooth grooves, a second telescopic rod is rotatably connected to one side of the clamping plate, one end of the second telescopic rod is rotatably connected to one side of the side plate, and a second spring is movably sleeved on the outer side of the second telescopic rod;

[0015] The clamping mechanism comprises a top plate and a pressure plate, one end of the top plate is fixedly connected to the clamping plate, and the pressure plate is fixedly connected to the connecting frame;

[0016] A mounting seat is installed at one end of the conveyor belt, a material unloading rack is installed on the mounting seat, a guide ring is installed on one side of the mounting seat, the guide ring is adapted to the clamping plate, and one end of the middle substrate is fixedly connected to the mounting seat.

[0017] As a preferred embodiment of the present invention, the loading module includes a toggle mechanism and a locking mechanism;

[0018] The toggle mechanism comprises a first fixed block, the first fixed block is fixedly mounted on one side of the side plate, second fixed blocks are fixedly mounted on both ends of the first fixed block, a toggle rod is rotatably mounted on one side of the first fixed block, a push rod is fixedly mounted on one end of the toggle rod, a push block is mounted on one side of the mounting seat, the push block is aligned with the push rod, a torsion spring is mounted at the connection between the toggle rod and the first fixed block, a first connecting rod is fixedly mounted on the rotating shaft of the toggle rod, and a second connecting rod is mounted on one end of the first connecting rod;

[0019] The locking mechanism includes a locking plate, a rubber band is installed between the locking plate and the bottom of the first fixed block, one end of the locking plate is rotatably connected to the side plate, one end of the locking plate is fixedly installed with a protrusion, the protrusion is adapted to the second connecting rod, the other end of the locking plate is fixedly installed with a guide rod, a mounting frame is fixedly installed on one side of the mounting seat, a pressure rod is fixedly installed on one end of the mounting frame, and the pressure rod is adapted to the guide rod.

[0020] As a preferred embodiment of the present invention, the curing unit also includes an adaptive adjustment module, the adaptive adjustment module includes a third support seat, a power device is installed on one side of the third support seat, the third support seat is connected to the conveying belt, a connecting plate is rotatably connected to the third support seat, a second roller is rotatably connected to the connecting plate, the second roller is located at the bottom of the conveying belt, a third telescopic rod is rotatably installed at both ends of the second roller, the third telescopic rod is rotatably connected to the third support seat, a third spring is movably connected to the third telescopic rod, the adaptive adjustment module also includes a lifting frame, a third roller is installed on the lifting frame, and the third roller is located at the top of the conveying belt.

[0021] As a preferred embodiment of the present invention, a limiting rod is installed on the lifting frame, a support plate is fixedly installed on one side of the collecting tank, one end of the support plate is rotatably connected to a second support seat, a limiting groove is provided on the support plate, and the limiting rod is movably connected to the limiting groove;

[0022] A first roller is also arranged inside the conveyor belt, and first support seats are installed at both ends of the first roller. The other end of the middle substrate is fixedly connected to the first support seat.

[0023] The present invention also discloses a control method for the large aircraft skin automatic spraying and curing device, and the control method for the large aircraft skin automatic spraying and curing device comprises the following steps:

[0024] S1. When the conveyor belt drives the aircraft skin to move, the cylinder presses against the baffle, thereby driving the mounting block to slide in the middle substrate. The mounting block drives the side plate and the nozzle to move, and the moving aircraft skin is sprayed;

[0025] S2. When the mounting block moves to one end of the middle substrate, the connecting frame abuts against the middle substrate and moves relatively, driving the lock plate to move and separate it from the rocker plate, the cylinder and the baffle plate are staggered, the baffle plate is pressed down to drive the rocker plate and the block to tilt up, and the block abuts against the lock plate;

[0026] S3, the connection frame moves and drives the pressure plate to move at the same time, the pressure plate and the top plate are staggered, the second spring pushes the clamping plate close to the conveyor belt, the protrusion at the bottom of the clamping plate enters the tooth groove at the bottom of the conveyor belt, and the installation block is driven to reset under the movement of the conveyor belt;

[0027] S4. When the mounting block is reset, the clamping plate is aligned with the guide ring and reset under its action, disengaging from the conveyor belt, so that the mounting block remains in place.

[0028] As a preferred embodiment of the present invention, the control method of the large aircraft skin automatic spraying and curing device further includes the following steps:

[0029] S5, when the mounting block is reset, the loading module is driven to move. When the reset is completed, the push block on one side of the mounting seat presses against the lever to make it rotate and press against the aircraft skin. The lever rotates through the first connecting rod to drive the second connecting rod to move. The second connecting rod is staggered with the protrusion. The rubber band pulls the protrusion downward to press against the second connecting rod, so that the lever keeps the direction unchanged.

[0030] S6, when the opening slot moves to the spraying unit again, the first spring pushes the baffle to reset, the conveyor belt drives the spraying unit to move again, the baffle resets to make the block and the lock plate staggered, the reset spring plate drives the connecting frame to reset, the lock plate buckles the rocker, and at the same time, the clamping plate is kept separated from the conveyor belt under the action of the guide ring, and the connecting frame resets to drive the pressure plate to lock the clamping plate;

[0031] S7. When the conveyor belt drives the spray unit to move again, the lever pushes the aircraft skin to detach from the unloading rack and fall onto the conveyor belt. When the aircraft skin falls completely, the pressure rod presses against the guide rod to make the guide rod tilt up, and the lever is reset under the action of the torsion spring.

[0032] As a preferred embodiment of the present invention, the control method of the large aircraft skin automatic spraying and curing device further includes the following steps:

[0033] S8. When the painted aircraft skin moves to the first roller, the lifting frame drives the third roller down, causing the conveyor belt to deform. The second roller moves down to adapt to the deformation. The third roller descends and drives the limit rod to rotate the support plate. The collecting trough is aligned with the conveyor belt. The aircraft skin enters the collecting trough and is cured under the action of the curing lamp. When the open slot moves to the spraying unit again, the lifting frame is reset, the collecting trough is tilted, and the cured aircraft skin slides off.

[0034] Compared with the prior art, the present invention has the following beneficial effects:

[0035] The present invention transports the aircraft skin by arranging a conveyor belt, and during the transportation process, the nozzle is driven by the installation block and other structures to follow the movement of the aircraft skin and spray. There is no need to arrange the nozzle on the entire transportation path of the aircraft skin, thereby reducing the waste of paint. Compared with the intelligent precision-controlled spraying equipment, it also has higher mechanical stability and reduces the technical cost.

[0036] The present invention can quickly complete the curing process by arranging a curing lamp to perform light curing on the aircraft skin, and the cured aircraft skin slides down naturally under the action of gravity without manual operation;

[0037] The invention samples the aircraft skin by arranging structures such as a lever and the like, so that the sample falls on a conveyor belt. The unloading rack only needs to be operated to place the aircraft skin on one end of the conveyor belt before the mounting block is reset, and the operation is simple. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 This is a schematic diagram of the overall structure of the large aircraft skin automatic spraying and curing device of the present invention;

[0039] Figure 2 It is a schematic diagram of the structure of the spray unit of the present invention;

[0040] Figure 3 It is a schematic diagram of the structure of the opening groove of the present invention;

[0041] Figure 4 It is a structural schematic diagram of the middle substrate of the present invention;

[0042] Figure 5 This is a schematic diagram of the structure of the baffle of the present invention;

[0043] Figure 6 This is a structural schematic diagram of the locking plate of the present invention;

[0044] Figure 7 This is a schematic diagram of the structure of the connecting frame of the present invention;

[0045] Figure 8 It is a structural schematic diagram of the pressing plate of the present invention;

[0046] Fig. 9 It is a schematic diagram of the protrusion structure of the present invention;

[0047] Fig.10 This is a structural schematic diagram of the first fixing block of the present invention;

[0048] Fig.11 It is a structural schematic diagram of the locking plate of the present invention;

[0049] Fig.12 It is a schematic diagram of the position relationship between the guide rod and the pressure rod of the present invention;

[0050] Fig.13 is a schematic diagram of the second connecting rod structure of the present invention;

[0051] Fig.14 It is a schematic diagram of the structure of the collecting tank of the present invention;

[0052] Fig.15 This is a schematic structural diagram of the third roller of the present invention;

[0053] Fig.16 It is a schematic diagram of the position relationship between the shifting rod and the pushing block of the present invention;

[0054] Fig.17 This is a schematic diagram of the state of the collecting trough of the present invention collecting aircraft skin.

[0055] Reference numerals:

[0056] 100, conveyor belt; 101, open slot; 102, cylinder; 103, middle base plate; 104, slide slot; 105, mounting block; 106, baffle plate; 107, rocker plate; 108, baffle; 109, first telescopic rod; 110, first spring; 111, connecting frame; 112, locking plate; 113, groove; 114, reset spring plate;

[0057] 200, nozzle; 201, side plate; 202, clamping plate; 203, second telescopic rod; 204, second spring; 205, top plate; 206, pressing plate; 207, protrusion; 208, tooth groove; 209, guide ring;

[0058] 300, first fixed block; 301, second fixed block; 302, lever; 303, push rod; 304, torsion spring; 305, first connecting rod; 306, second connecting rod; 307, locking plate; 308, bump; 309, rubber band; 310, guide rod; 311, mounting seat; 312, mounting frame; 313, pressure rod; 314, unloading frame; 315, push block;

[0059] 400, first support seat; 401, first roller; 402, second support seat; 403, support plate; 404, collecting tank; 405, curing lamp; 406, limiting slot; 407, lifting frame; 408, limiting rod; 409, second roller; 410, third roller; 411, third support seat; 412, third telescopic rod; 413, third spring; 414, connecting plate; 415, power device. DETAILED DESCRIPTION

[0060] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. The following embodiments are used to illustrate the present invention.

[0061] Example 1

[0062] like Figures 1 to 17 As shown, the large aircraft skin automatic spraying and curing device includes:

[0063] The spraying unit includes a conveying module, a return module and a feeding module. The conveying module includes a conveying belt 100. A middle substrate 103 is arranged inside the conveying belt 100. A slide groove 104 is provided on the middle substrate 103. A synchronization mechanism is arranged at the slide groove 104 of the middle substrate 103. The return module includes a clamping mechanism and a card connection mechanism. The return module drives the conveying belt 100 to drive the spraying unit to move in the opposite direction through the card connection mechanism and the clamping mechanism. The feeding module is used for feeding the aircraft skin;

[0064] The curing unit includes a collecting tank 404 on which a curing lamp 405 is installed. The curing unit is used to cure the sprayed aircraft skin.

[0065] like Figure 5 , Figure 6 , Figure 8As shown, in a specific embodiment, a sliding mechanism is provided inside the middle substrate 103, and the sliding mechanism includes a mounting block 105, which is slidably mounted inside the middle substrate 103, and a pushing component is installed inside the mounting block 105, and the pushing component is used to control the synchronization mechanism, and side panels 201 are fixedly mounted at both ends of the mounting block 105, and a nozzle 200 is fixedly mounted on the top of the side panel 201. In this setting, the side panel 201 drives the nozzle 200 to move so that the nozzle 200 sprays the aircraft skin, which can effectively cover the aircraft skin with paint while avoiding waste caused by fixed nozzles.

[0066] like Figure 3-Figure 6 As shown, further, the synchronization mechanism includes an open slot 101, the open slot 101 is opened on the conveyor belt 100, and the conveyor belt 100 is fixedly installed with a cylinder 102 at one end of the open slot 101. The synchronization mechanism also includes a baffle 106, which is rotatably connected to the top of the mounting block 105, and the baffle 106 is adapted to the cylinder 102. An elastic reset component is provided at one end of the baffle 106, and a locking control component is provided at the other end. In this setting, the conveyor belt 100 is composed of a multi-layer composite structure, which can enhance the toughness of the conveyor belt 100 and thus enhance its structural strength. At the same time, the cylinder 102 is made of metal material, which can drive the baffle 106 to move, and can also reduce the friction between the cylinder 102 and the baffle 106 when the baffle 106 is disengaged.

[0067] like Figure 5 , Figure 6 , Figure 8 As shown, further, the elastic reset assembly includes a first telescopic rod 109 and a first spring 110, the first spring 110 is movably sleeved on the outside of the first telescopic rod 109, the first telescopic rod 109 is rotatably connected between the baffle 106 and the mounting block 105, and the lock control assembly includes a seesaw 107, a stopper 108 is fixedly installed at the bottom of the seesaw 107, one end of the seesaw 107 is fixedly connected to the baffle 106, and a lock plate 112 is arranged at one end of the seesaw 107. In this setting, one end of the stopper 108 is arc-shaped, and when the lock plate 112 is separated from the seesaw 107, the arc-shaped end of the stopper 108 makes it keep the function of rotating when it abuts against the lock plate 112, and the lock plate 112 will not move.

[0068] like Figure 6-Figure 8 As shown, further, the pushing assembly includes a connecting frame 111, the connecting frame 111 is slidably connected inside the mounting block 105, and one end of the connecting frame 111 extends to the outside of the mounting block 105, one end of the locking plate 112 is fixedly connected to one end of the connecting frame 111, a groove 113 is provided inside the mounting block 105, a reset spring plate 114 is provided inside the groove 113, and the reset spring plate 114 is connected to the connecting frame 111. In this setting, the reset spring plate 114 is used to provide elastic force for the connection frame 111 to reset.

[0069] Example 2

[0070] like Figure 1 , Figure 2 , Figure 8 , Fig. 9 As shown, in a specific embodiment, the clamping mechanism includes a clamping plate 202, which is rotatably connected to the side plate 201, a protrusion 207 is installed on one side of the bottom of the clamping plate 202, and tooth grooves 208 are provided on both sides of the conveyor belt 100, and the protrusion 207 is adapted to the tooth grooves 208, and a second telescopic rod 203 is rotatably connected to one side of the clamping plate 202, one end of the second telescopic rod 203 is rotatably connected to one side of the side plate 201, and a second spring 204 is movably sleeved on the outer side of the second telescopic rod 203; in this configuration, the protrusion 207 is driven to move by the tooth grooves 208 during the movement of the conveyor belt 100, thereby moving the clamping plate 202;

[0071] The clamping mechanism includes a top plate 205 and a pressure plate 206. One end of the top plate 205 is fixedly connected to the clamping plate 202. The pressure plate 206 is fixedly connected to the connecting frame 111. The clamping mechanism controls the locking of the clamping plate 202 through the top plate 205 and the pressure plate 206.

[0072] A mounting seat 311 is mounted on one end of the conveyor belt 100, a material unloading rack 314 is mounted on the mounting seat 311, a guide ring 209 is mounted on one side of the mounting seat 311, the guide ring 209 is matched with the clamping plate 202, and one end of the middle substrate 103 is fixedly connected to the mounting seat 311. In this configuration, the clamping plate 202 is rotated and reset by the guide ring 209.

[0073] like Fig.10 , Fig.11 , Fig.12 , Fig.13 , Fig.16 As shown, further, the feeding module includes a toggle mechanism and a locking mechanism;

[0074] The toggle mechanism includes a first fixed block 300, which is fixedly mounted on one side of the side plate 201, and second fixed blocks 301 are fixedly mounted on both ends of the first fixed block 300. A toggle rod 302 is rotatably mounted on one side of the first fixed block 300, and a push rod 303 is fixedly mounted on one end of the toggle rod 302. A push block 315 is mounted on one side of the mounting seat 311, and the push block 315 is aligned with the push rod 303. A torsion spring 304 is mounted at the connection between the toggle rod 302 and the first fixed block 300, and a first connecting rod 305 is fixedly mounted on the rotating shaft of the toggle rod 302, and a second connecting rod 306 is mounted on one end of the first connecting rod 305.

[0075] The locking mechanism includes a locking plate 307, a rubber band 309 is installed between the locking plate 307 and the bottom of the first fixed block 300, one end of the locking plate 307 is rotatably connected to the side plate 201, one end of the locking plate 307 is fixedly installed with a protrusion 308, and the protrusion 308 is adapted to the second connecting rod 306, and the other end of the locking plate 307 is fixedly installed with a guide rod 310, and a mounting bracket 312 is fixedly installed on one side of the mounting seat 311, and a pressure rod 313 is fixedly installed on one end of the mounting bracket 312, and the pressure rod 313 is adapted to the guide rod 310. In this setting, the mounting block 105 drives the loading module to move during the reset process, and at this time, the protrusion 308 is located at the top of the second connecting rod 306 (refer to Fig.10 ), when the mounting block 105 is reset, the push block 315 on one side of the mounting seat 311 presses against the lever 302, so that the lever 302 rotates and presses against the aircraft skin. At the same time, during the rotation of the lever 302, the second connecting rod 306 is driven to move through the first connecting rod 305, and the second connecting rod 306 is staggered with the protrusion 308. At this time, the rubber band 309 pulls the protrusion 308 downward and presses against the second connecting rod 306, so that the lever 302 keeps the direction unchanged. When the conveyor belt 100 drives the spraying unit to move again, the lever 302 pushes the aircraft skin to separate from the unloading rack 314 and fall on the conveyor belt 100. When the aircraft skin completely falls on the conveyor belt 100, the pressure rod 313 on the mounting rack 312 presses against the guide rod 310, so that the guide rod 310 is tilted. At this time, the lever 302 is reset under the action of the torsion spring 304.

[0076] Example 3

[0077] like Fig.14 , Fig.15 , Fig.17As shown, in a specific embodiment, the curing unit further includes an adaptive adjustment module, which includes a third support seat 411, a power device 415 is installed on one side of the third support seat 411, and the power device 415 adopts a permanent magnet assisted synchronous reluctance motor, which has the characteristics of low speed and high torque. The third support seat 411 is connected to the conveyor belt 100, and a connecting plate 414 is rotatably connected to the third support seat 411, and a second roller 409 is rotatably connected to the connecting plate 414. The second roller 409 is located at the bottom of the conveyor belt 100, and the second roller 409 is rotatably installed at both ends of the second roller 409. 12. The third telescopic rod 412 is rotatably connected to the third support seat 411, and the third telescopic rod 412 is movably connected to the third spring 413. The adaptive adjustment module also includes a lifting frame 407, and the lifting frame 407 is equipped with a third roller 410, and the third roller 410 is located on the top of the conveyor belt 100; a limiting rod 408 is installed on the lifting frame 407, and a support plate 403 is fixedly installed on one side of the collecting tank 404. One end of the support plate 403 is rotatably connected to the second support seat 402, and a limiting groove 406 is provided on the support plate 403, and the limiting rod 408 is movably connected to the limiting groove 406;

[0078] A first roller 401 is further provided inside the conveyor belt 100 . First support seats 400 are installed at both ends of the first roller 401 . The other end of the middle substrate 103 is fixedly connected to the first support seat 400 . In this arrangement, when the painted aircraft skin moves to the first roller 401 along with the conveyor belt 100, the lifting frame 407 drives the third roller 410 to descend. During the downward pressure of the third roller 410, the conveyor belt 100 is deformed accordingly. At the same time, the second roller 409 moves downward to adapt to the deformation of the conveyor belt 100. During the descent of the third roller 410, the support plate 403 is driven to rotate through the limit rod 408. During the rotation of the support plate 403, the collecting trough 404 is driven to move. At this time, the collecting trough 404 is aligned with the conveyor belt 100, so that the aircraft skin enters the collecting trough 404 and is quickly cured under the action of the curing lamp 405. When the opening slot 101 moves to the spraying unit and the aircraft skin is transported again, the lifting frame 407 is reset and the collecting trough 404 is tilted. At this time, the cured aircraft skin slides out.

[0079] The implementation principle of the large aircraft skin automatic spraying and curing device of this embodiment is as follows: during transportation, the conveyor belt 100 drives the aircraft skin to move, and at the same time drives the cylinder 102 at the opening groove 101 to move, and the cylinder 102 abuts against the baffle 106, thereby driving the mounting block 105 to slide in the middle substrate 103, and at this time the mounting block 105 drives the side plate 201 to move, and drives the nozzle 200 to follow the movement, so that the aircraft skin is sprayed by the nozzle 200 during the movement;

[0080] When the mounting block 105 moves to one end of the middle substrate 103, the connecting frame 111 on the mounting block 105 abuts against the middle substrate 103, thereby moving relative to the mounting block 105 and driving the locking plate 112 to move during the movement. At this time, the locking plate 112 is separated from the rocker 107. The conveyor belt 100 continues to move so that the cylinder 102 and the baffle 106 are staggered. The baffle 106 is pressed downward under the action of the conveyor belt 100, and drives the rocker 107 and the block 108 to tilt up. At this time, the block 108 abuts against the locking plate 112.

[0081] When the connecting frame 111 moves relatively, the pressing plate 206 is driven to move, and the pressing plate 206 is staggered with the top plate 205. At this time, the second spring 204 pushes the clamping plate 202 to approach the conveyor belt 100, and the protrusion 207 at the bottom of the clamping plate 202 enters the tooth grooves 208 on both sides of the bottom of the conveyor belt 100, and drives the installation block 105 to reset during the movement of the conveyor belt 100;

[0082] When the mounting block 105 is reset, the clamping plate 202 is aligned with the guide ring 209 and reset under the action of the guide ring 209. At this time, the clamping plate 202 is separated from the conveyor belt 100, so that the mounting block 105 remains in place;

[0083] The mounting block 105 drives the loading module to move during the resetting process. At this time, the protrusion 308 is located at the top of the second connecting rod 306 (refer to Fig.10 ), when the mounting block 105 is reset, the push block 315 on one side of the mounting seat 311 abuts against the lever 302, so that the lever 302 rotates and abuts against the aircraft skin. At the same time, during the rotation of the lever 302, the second connecting rod 306 is driven to move by the first connecting rod 305, and the second connecting rod 306 is staggered from the protrusion 308. At this time, the rubber band 309 pulls the protrusion 308 downward and abuts against the second connecting rod 306, so that the lever 302 keeps the direction unchanged;

[0084] When the opening slot 101 moves to the spraying unit again, the first spring 110 pushes the baffle 106 to reset, so that the conveyor belt 100 drives the spraying unit to move again, and at the same time, the baffle 106 resets so that the block 108 and the lock plate 112 are staggered. At this time, the reset spring plate 114 drives the connecting frame 111 to reset, so that the lock plate 112 buckles the rocker plate 107. At the same time, because the clamping plate 202 is kept separated from the conveyor belt 100 under the action of the guide ring 209, when the connecting frame 111 resets, it can directly drive the pressing plate 206 to move above the top plate 205 and lock the clamping plate 202;

[0085] When the conveyor belt 100 drives the spray unit to move again, the lever 302 pushes the aircraft skin to separate from the unloading rack 314 and fall onto the conveyor belt 100. When the aircraft skin completely falls onto the conveyor belt 100, the pressure rod 313 on the mounting rack 312 presses against the guide rod 310, so that the guide rod 310 tilts up. At this time, the lever 302 is reset under the action of the torsion spring 304.

[0086] When the painted aircraft skin moves to the first roller 401 along with the conveyor belt 100, the lifting frame 407 drives the third roller 410 to descend. During the downward pressure of the third roller 410, the conveyor belt 100 is deformed accordingly. At the same time, the second roller 409 moves downward to adapt to the deformation of the conveyor belt 100. During the descent of the third roller 410, the support plate 403 is driven to rotate through the limit rod 408. During the rotation of the support plate 403, the collecting tank 404 is driven to move. At this time, the collecting tank 404 is aligned with the conveyor belt 100, so that the aircraft skin enters the collecting tank 404 and is quickly cured under the action of the curing lamp 405. When the opening slot 101 moves to the spraying unit and the aircraft skin is transported again, the lifting frame 407 is reset and the collecting tank 404 is tilted. At this time, the cured aircraft skin slides out and the subsequent process can be carried out.

[0087] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit it. Although the present invention 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 invention may be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the present invention, which should all be included in the scope of the claims of the present invention.

Claims

1. Automatic spraying and curing device for large aircraft skin, characterized in that: include: A spraying unit, the spraying unit comprising a conveying module, a folding module and a feeding module, the conveying module comprising a conveying belt (100), a middle-layer substrate (103) being arranged inside the conveying belt (100), a slide groove (104) being provided on the middle-layer substrate (103), a synchronization mechanism being arranged on the middle-layer substrate (103) at the slide groove (104), the folding module comprising a clamping mechanism and a snap-fit ​​mechanism, the folding module causing the conveying belt (100) to drive the spraying unit to move in the opposite direction through the snap-fit ​​mechanism and the clamping mechanism, the feeding module being used for feeding the aircraft skin, and the spraying unit being used for spraying paint on the aircraft skin; A curing unit, the curing unit comprising a collecting tank (404), a curing lamp (405) being installed on the collecting tank (404), and the curing unit being used for curing the sprayed aircraft skin; A sliding mechanism is provided inside the middle substrate (103), the sliding mechanism comprising a mounting block (105), the mounting block (105) being slidably mounted inside the middle substrate (103), a pushing component being mounted inside the mounting block (105), the pushing component being used to control the synchronization mechanism, side plates (201) being fixedly mounted at both ends of the mounting block (105), and a nozzle (200) being fixedly mounted on the top of the side plate (201); The synchronization mechanism comprises an open groove (101), wherein the open groove (101) is formed on a conveying belt (100), and a cylinder (102) is fixedly mounted on one end of the conveying belt (100) located at the open groove (101). The synchronization mechanism also comprises a baffle (106), wherein the baffle (106) is rotatably connected to the top of the mounting block (105), and the baffle (106) is adapted to the cylinder (102) so that the conveying belt (100) is pressed against the baffle (106) by the cylinder (102) during movement, and the baffle (106) is pressed downward under the action of the conveying belt (100) after the cylinder (102) and the baffle (106) are offset, and an elastic reset component is arranged at one end of the baffle (106), and a locking control component is arranged at the other end; The elastic reset assembly comprises a first telescopic rod (109) and a first spring (110), the first spring (110) being movably sleeved on the outside of the first telescopic rod (109), the first telescopic rod (109) being rotatably connected between the baffle (106) and the mounting block (105), the locking control assembly comprising a seesaw (107), a baffle (108) being fixedly mounted on the bottom of the seesaw (107), one end of the seesaw (107) being fixedly connected to the baffle (106), and a locking plate (112) being provided at one end of the seesaw (107); The pushing assembly comprises a connecting frame (111), the connecting frame (111) is slidably connected inside the mounting block (105), and one end of the connecting frame (111) extends to the outside of the mounting block (105), one end of the locking plate (112) is fixedly connected to one end of the connecting frame (111), a groove (113) is provided inside the mounting block (105), a reset spring plate (114) is provided inside the groove (113), and the reset spring plate (114) is connected to the connecting frame (111); The clamping mechanism comprises a clamping plate (202), the clamping plate (202) being rotatably connected to the side plate (201), a protrusion (207) being installed on one side of the bottom of the clamping plate (202), tooth grooves (208) being provided on both sides of the conveying belt (100), and the protrusion (207) being adapted to the tooth grooves (208) so that the protrusion (207) enters the tooth grooves (208) and drives the mounting block (105) to reset during the movement of the conveying belt (100), a second telescopic rod (203) being rotatably connected to one side of the clamping plate (202), one end of the second telescopic rod (203) being rotatably connected to one side of the side plate (201), and a second spring (204) being movably sleeved on the outer side of the second telescopic rod (203); The clamping mechanism comprises a top plate (205) and a pressure plate (206); one end of the top plate (205) is fixedly connected to the clamping plate (202); and the pressure plate (206) is fixedly connected to the connecting frame (111); A mounting seat (311) is installed at one end of the conveyor belt (100), a material unloading rack (314) is installed on the mounting seat (311), a guide ring (209) is installed on one side of the mounting seat (311), the guide ring (209) is adapted to the clamping plate (202), so that the clamping plate (202) remains detached from the conveyor belt (100) under the action of the guide ring (209), and one end of the middle substrate (103) is fixedly connected to the mounting seat (311); The feeding module includes a toggle mechanism and a locking mechanism; The toggle mechanism comprises a first fixed block (300), the first fixed block (300) is fixedly mounted on one side of the side plate (201), second fixed blocks (301) are fixedly mounted on both ends of the first fixed block (300), a toggle rod (302) is rotatably mounted on one side of the first fixed block (300), a push rod (303) is fixedly mounted on one end of the toggle rod (302), a push block (315) is mounted on one side of the mounting seat (311), the push block (315) is aligned with the push rod (303), a torsion spring (304) is mounted at the connection between the toggle rod (302) and the first fixed block (300), a first connecting rod (305) is fixedly mounted on the rotation axis of the toggle rod (302), and a second connecting rod (306) is mounted on one end of the first connecting rod (305); The locking mechanism comprises a locking plate (307), a rubber band (309) is installed between the locking plate (307) and the bottom of the first fixing block (300), one end of the locking plate (307) is rotatably connected to the side plate (201), and a protrusion (308) is fixedly installed on one end of the locking plate (307), the protrusion (308) is adapted to the second connecting rod (306), and the second connecting rod (306) and the protrusion (308) are staggered so that the rubber band (309) pulls the protrusion (308) down The locking plate (307) is provided to move the guide rod (302) and to abut against the second connecting rod (306) so that the direction of the lever (302) remains unchanged; a guide rod (310) is fixedly mounted on the other end of the locking plate (307); a mounting frame (312) is fixedly mounted on one side of the mounting seat (311); a pressure rod (313) is fixedly mounted on one end of the mounting frame (312); the pressure rod (313) is matched with the guide rod (310) so that the pressure rod (313) abuts against the guide rod (310), thereby causing the guide rod (310) to tilt up.

2. The large aircraft skin automatic spraying and curing device according to claim 1 is characterized in that: The curing unit further comprises an adaptive adjustment module, the adaptive adjustment module comprising a third support seat (411), a power device (415) being installed on one side of the third support seat (411), the third support seat (411) being connected to the conveyor belt (100), a connecting plate (414) being rotatably connected to the third support seat (411), a second roller (409) being rotatably connected to the connecting plate (414), the second roller (409) being located at the bottom of the conveyor belt (100), third telescopic rods (412) being rotatably installed at both ends of the second roller (409), the third telescopic rod (412) being rotatably connected to the third support seat (411), a third spring (413) being movably connected to the third telescopic rod (412), and the adaptive adjustment module further comprises a lifting frame (407), a third roller (410) being installed on the lifting frame (407), the third roller (410) being located at the top of the conveyor belt (100).

3. The large aircraft skin automatic spraying and curing device according to claim 2 is characterized in that: A limiting rod (408) is installed on the lifting frame (407); a support plate (403) is fixedly installed on one side of the collecting tank (404); one end of the support plate (403) is rotatably connected to a second support seat (402); a limiting groove (406) is provided on the support plate (403); and the limiting rod (408) is movably connected to the limiting groove (406); A first roller (401) is also provided inside the conveyor belt (100), and first support seats (400) are installed at both ends of the first roller (401), and the other end of the middle substrate (103) is fixedly connected to the first support seat (400).

4. A control method for an automatic spraying and curing device for large aircraft skin, applied to the automatic spraying and curing device for large aircraft skin according to any one of claims 1 to 3, characterized in that: The steps include: S1, when the conveyor belt (100) drives the aircraft skin to move, the cylinder (102) presses against the baffle (106), thereby driving the mounting block (105) to slide in the middle substrate (103), and the mounting block (105) drives the side plate (201) and the spray head (200) to move, so as to spray the moving aircraft skin; S2, when the mounting block (105) moves to one end of the middle substrate (103), the connecting frame (111) abuts against the middle substrate (103) and moves relatively thereto, driving the locking plate (112) to move so as to be separated from the seesaw (107), the cylinder (102) and the baffle (106) are staggered, the baffle (106) is pressed downward to drive the seesaw (107) and the baffle (108) to tilt up, and the baffle (108) abuts against the locking plate (112); S3, the connecting frame (111) moves and drives the pressing plate (206) to move at the same time, the pressing plate (206) is staggered with the top plate (205), the second spring (204) pushes the clamping plate (202) close to the conveying belt (100), the protrusion (207) at the bottom of the clamping plate (202) enters the tooth groove (208) at the bottom of the conveying belt (100), and drives the mounting block (105) to reset under the movement of the conveying belt (100); S4. When the mounting block (105) is reset, the clamping plate (202) is aligned with the guide ring (209) and reset under the action of the guide ring, and is separated from the conveyor belt (100), so that the mounting block (105) remains in place.

5. The control method of the large aircraft skin automatic spraying and curing device according to claim 4 is characterized in that: The following steps are also included: S5, when the mounting block (105) is reset, it drives the loading module to move. When the reset is completed, the push block (315) on one side of the mounting seat (311) presses against the lever (302) to rotate it and press against the aircraft skin. The lever (302) rotates to drive the second connecting rod (306) to move through the first connecting rod (305). The second connecting rod (306) is staggered with the protrusion (308). The rubber band (309) pulls the protrusion (308) downward to press against the second connecting rod (306), so that the lever (302) keeps the direction unchanged; S6. When the opening slot (101) moves to the spraying unit again, the first spring (110) pushes the baffle (106) to reset, the conveyor belt (100) drives the spraying unit to move again, the baffle (106) resets to make the block (108) and the lock plate (112) staggered, the reset spring plate (114) drives the connecting frame (111) to reset, the lock plate (112) buckles the rocker (107), and at the same time, the clamping plate (202) is kept separated from the conveyor belt (100) under the action of the guide ring (209), and the connecting frame (111) resets to drive the pressure plate (206) to lock the clamping plate (202); S7. When the conveyor belt (100) drives the spray unit to move again, the lever (302) pushes the aircraft skin to detach from the unloading rack (314) and fall onto the conveyor belt (100). When the aircraft skin falls completely, the pressure rod (313) presses against the guide rod (310) to make the guide rod (310) tilt up, and the lever (302) is reset under the action of the torsion spring (304).

6. The control method of the large aircraft skin automatic spraying and curing device according to claim 5 is characterized in that: The following steps are also included: S8. When the sprayed aircraft skin moves to the first roller (401), the lifting frame (407) drives the third roller (410) to descend, causing the conveyor belt (100) to deform, and the second roller (409) moves downward to adapt to the deformation. The third roller (410) descends and drives the limit rod (408) to rotate the support plate (403), so that the collecting trough (404) is aligned with the conveyor belt (100), and the aircraft skin enters the collecting trough (404) and is cured under the action of the curing lamp (405). When the open slot (101) moves to the spraying unit again, the lifting frame (407) is reset, the collecting trough (404) is tilted, and the cured aircraft skin slides off.

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