Spraying device for surface treatment of aircraft parts

Abstract

The invention discloses a spraying device for aircraft part surface treatment, and particularly relates to the technical field of aircraft part surface treatment.The spraying device comprises a device bottom frame, a transposition mechanism is arranged in the middle of the device bottom frame, an aircraft part body is arranged at the top end of the transposition mechanism, and a supporting frame is fixedly installed on one side of the top end of the device bottom frame; the device comprises a device bottom frame, a supporting frame is fixedly installed at the top end of the device bottom frame, a spraying mechanism is fixedly installed at the end of the supporting frame, and a feeding mechanism is fixedly installed on the side, away from the supporting frame, of the top end of the device bottom frame. And synchronous outer wall and inner wall rotary type comprehensive spraying operation is conducted on the aircraft part body, meanwhile, synchronous air body drying is conducted on the outer wall and the inner wall of the aircraft part body, attachment of spraying paint on the outer wall and the inner wall of the aircraft part body is accelerated, and therefore the spraying quality and efficiency of the aircraft part body are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft component surface treatment, and specifically to a spraying device for aircraft component surface treatment. Background Technique

[0002] With the continuous development of modern aviation technology, aircraft equipment surface treatment technology has also been widely applied. Aircraft equipment surface treatment technology refers to a technology that changes the surface performance and morphological structure of aircraft equipment by performing physical, chemical, or mechanical treatment on the surface of aircraft equipment. Its purpose is to improve the service life, corrosion resistance, fatigue resistance of aircraft materials, and reduce aerodynamic drag, thereby ensuring flight safety. When traditional aircraft components are processed and produced, a spraying device is required to perform spraying operations on aircraft components. Compared with the spraying of tubular aircraft components, for the spraying of tubular aircraft components, it is mostly manual spraying with a spraying gun held by hand on the clamped tubular aircraft components. During spraying, first, the outer wall of the tubular aircraft component is sprayed, and then the inner wall of the tubular aircraft component is sprayed. The outer wall spraying is relatively easy, but for the inner wall spraying, it is more troublesome and prone to missed spraying, thus affecting the overall processing quality and efficiency of aircraft components. For this reason, we propose a spraying device for aircraft component surface treatment to solve the above problems. Summary of the Invention

[0003] The purpose of the present invention is to provide a spraying device for aircraft component surface treatment to solve the problems raised in the above background technique.

[0004] To achieve the above purpose, the present invention provides the following technical solution: A spraying device for aircraft component surface treatment, including a device bottom frame. A rotating mechanism is provided in the middle of the device bottom frame. An aircraft component body is provided at the top of the rotating mechanism. A support frame is fixedly installed on one side of the top of the device bottom frame. A spraying mechanism is fixedly installed at the end of the support frame. A feeding mechanism is fixedly installed on the side of the top of the device bottom frame away from the support frame. A discharging mechanism is fixedly installed on the side of the top of the device bottom frame away from the support frame.

[0005] Preferably, the transposition mechanism includes a first bearing, which is fixedly clamped in the middle of the bottom frame of the device. A transposition shaft column is fixedly clamped in the middle of the first bearing. A transposition chassis is fixedly installed at the top end of the transposition shaft column. A lifting cylinder is fixedly installed at the top end of the transposition chassis. A transposition top plate is fixedly installed at the driving end of the lifting cylinder. Three object placing racks distributed in an annular array are integrally formed on the outer side of the transposition top plate. Second bearings are fixedly clamped at one ends of the object placing racks far away from the transposition top plate. A support bottom pipe is fixedly installed in the middle of the second bearing. An object placing seat is fixedly installed at the top end of the support bottom pipe. An object placing groove is formed at the top end of the object placing seat. The aircraft part body is movably clamped in the object placing groove.

[0006] Preferably, the bottom of the transposition shaft column extends into the bottom frame of the device. A driven worm gear is fixedly sleeved at the bottom of the transposition shaft column. A driving worm is meshed and connected to the outer side of the driven worm gear. A driving motor is fixedly installed on the lower inner wall of the device bottom frame near the driving worm. The driving end of the driving motor and one end of the driving worm are coaxially fixedly installed.

[0007] Preferably, the bottom of the support bottom pipe extends to the bottom end of the object placing rack. Crown gears are fixedly sleeved at the bottoms of the support bottom pipes. Rotating frames are fixedly installed in the middle of the bottom ends of the object placing racks. Auxiliary shafts are rotatably installed at the bottoms of the rotating frames. First gears are fixedly installed at the opposite ends of the plurality of auxiliary shafts. The first gears are meshed and connected to the bottoms of the corresponding crown gears. Second gears are installed at the opposite ends of the plurality of auxiliary shafts. The side ends of the second gears are meshed and connected to auxiliary racks. The bottom ends of the auxiliary racks are fixedly installed at the top end of the transposition chassis. The auxiliary racks are slidably clamped at the side ends of the corresponding object placing racks.

[0008] Preferably, the spraying mechanism includes a spraying outer ring frame and a spraying inner cylinder, which are coaxially arranged. The spraying outer ring frame is vertically corresponding to the position of one of the object placing seats. A plurality of outer nozzles distributed in an annular array are fixedly installed on the inner side of the spraying outer ring frame. A plurality of inner nozzles distributed in an annular array are fixedly installed on the outer side of the spraying inner cylinder. A guide material longitudinal pipe is integrally formed in the middle of the top end of the spraying inner cylinder. A first connector is fixedly installed at the top end of the guide material longitudinal pipe. A guide material branch pipe is integrally formed on the outer side of the spraying outer ring frame. A guide material ring pipe is arranged on the outer sides of the plurality of guide material branch pipes. A connecting pipe corresponding to the guide material branch pipe is integrally formed on the inner side of the guide material ring pipe. The end of the connecting pipe is fixedly installed with the corresponding guide material branch pipe. A second connector is fixedly clamped on the outer side of the guide material ring pipe.

[0009] Preferably, a diversion outer frame is fixedly installed at the top end of the spraying outer ring frame. An outer exhaust cavity is formed at the bottom of the diversion outer frame, an outer air inlet cavity is formed at the top of the diversion outer frame, an outer exhaust ring groove is formed at the inner bottom of the diversion outer frame, the outer exhaust ring groove communicates with the outer exhaust cavity, an outer air inlet ring groove is formed at the inner top of the diversion outer frame, the outer air inlet ring groove communicates with the outer air inlet cavity, a first guide pipe and a second guide pipe are fixedly clamped at the top end of the diversion outer frame, the bottom of the first guide pipe extends to the top of the outer exhaust cavity, and the bottom of the second guide pipe extends to the top of the outer air inlet cavity.

[0010] Preferably, a diversion inner frame is fixedly installed at the top end of the spraying inner cylinder. The diversion inner frame is of an annular structure. The longitudinal material guiding pipe movably penetrates through the middle of the diversion inner frame, and the top of the longitudinal material guiding pipe extends out of the top end of the diversion inner frame. An inner exhaust cavity is formed at the bottom of the diversion inner frame, an inner air inlet cavity is formed at the top of the diversion inner frame, an inner exhaust ring groove is formed at the outer bottom of the diversion inner frame, the inner exhaust ring groove communicates with the inner exhaust cavity, an inner air inlet ring groove is formed at the outer top of the diversion inner frame, the inner air inlet ring groove communicates with the inner air inlet cavity, a third guide pipe and a fourth guide pipe are fixedly clamped at the top end of the diversion inner frame, the bottom of the third guide pipe extends to the top of the inner exhaust cavity, and the bottom of the fourth guide pipe extends to the top of the inner air inlet cavity.

[0011] Preferably, two symmetrically distributed U-shaped frames are fixedly installed at the top ends of the diversion outer frame and the diversion inner frame, and the U-shaped frames are fixedly installed at the ends of the support frame.

[0012] Preferably, the feeding mechanism includes a linear electric rail which is fixedly installed on one side of the top end of the device bottom frame away from the support frame. The driving end of the linear electric rail is fixedly installed with an electric lifting rod, the driving end of the electric lifting rod is fixedly installed with a support base, the top end of the support base is fixedly installed with a rotary cylinder, the driving end of the rotary cylinder is fixedly installed with a rotary frame, the end of the rotary frame is fixedly installed with a positioning outer frame, two symmetrically distributed positioning clamping rods are slidably clamped on one side of the positioning outer frame away from the rotary frame, a bidirectional telescopic rod is fixedly installed in the positioning outer frame, the driving end of the bidirectional telescopic rod is fixedly installed with the corresponding positioning clamping rod, and the positions of the two positioning clamping rods in the feeding mechanism are vertically corresponding to those of one of the object placing seat holders.

[0013] Preferably, the structure of the discharging mechanism is the same as that of the feeding mechanism. The discharging mechanism is fixedly installed on one side of the top end of the device bottom frame away from the support frame through the linear electric rail, and the positions of the two positioning clamping rods in the discharging mechanism are vertically corresponding to those of one of the object placing seat holders.

[0014] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. By setting up a transposition mechanism and a spraying mechanism, automatic transposition operations are carried out on multiple aircraft component bodies, and synchronous rotary comprehensive spraying operations are performed on the outer and inner walls of the aircraft component bodies. At the same time, synchronous air drying is carried out on the outer and inner walls of the aircraft component bodies to accelerate the adhesion of the spray coating on the outer and inner walls of the aircraft component bodies, thereby improving the spraying quality and efficiency of the aircraft component bodies.

[0015] 2. By setting up a feeding mechanism and a discharging mechanism, automatic feeding operations and automatic discharging operations of multiple aircraft component bodies can be carried out, improving the spraying efficiency of the aircraft component bodies. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0017] Figure 1 It is a schematic structural diagram of the present invention. Figure 2 It is a schematic structural connection diagram of the device bottom frame and the transposition mechanism in the present invention. Figure 3 It is a partial schematic structural connection diagram of the transposition mechanism in the present invention. Figure 4 It is a schematic structural connection diagram of the spraying mechanism in the present invention. Figure 5 For the present invention Figure 4 It is an enlarged view of part A in the present invention. Figure 6 For the present invention Figure 4 It is an enlarged view of part B in the present invention. Figure 7 For the present invention Figure 4 It is an enlarged view of part C in the present invention. Figure 8 It is a schematic structural connection diagram of the feeding mechanism in the present invention.

[0018] In the figure: 1. Device bottom frame; 2. Transposition mechanism; 3. Airplane component body; 4. Support frame; 5. Spraying mechanism; 6. Feeding mechanism; 7. Discharging mechanism; 8. Driving motor; 21. First bearing; 22. Transposition shaft column; 23. Transposition chassis; 24. Lifting cylinder; 25. Transposition top plate; 26. Storage rack; 261. Second bearing; 27. Support bottom pipe; 28. Storage card seat; 281. Storage groove; 29. Driven worm gear; 291. Driving worm; 210. Crown gear; 211. First gear; 212. Auxiliary shaft; 213. Rotating frame; 214. Second gear; 215. Auxiliary rack; 51. Spraying outer ring frame; 511. Material guiding branch pipe; 512. Material guiding ring pipe; 513. Connecting pipe; 514. Second connection head; 52. Spraying inner cylinder; 501. Outer spray head; 502. Inner spray head; 53. Material guiding longitudinal pipe; 531. First connection head; 54. Flow guiding outer frame; 541. Outer exhaust cavity; 542. Outer intake cavity; 543. Outer exhaust ring groove; 544. Outer intake ring groove; 545. First air duct; 546. Second air duct; 55. Flow guiding inner frame; 552. Inner exhaust cavity; 553. Inner intake cavity; 554. Inner exhaust ring groove; 555. Inner intake ring groove; 556. Third air duct; 557. Fourth air duct; 56. U-shaped frame; 61. Linear electric rail; 62. Electric lifting rod; 63. Support base; 64. Rotary cylinder; 65. Rotary frame; 66. Positioning outer frame; 67. Positioning clamping rod; 68. Bidirectional telescopic rod. Detailed implementation manners

[0019] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0020] Embodiment: As Figures 1-8 shown, the present invention provides a spraying device for surface treatment of airplane components, including a device bottom frame 1. A transposition mechanism 2 is provided in the middle of the device bottom frame 1. An airplane component body 3 is provided at the top end of the transposition mechanism 2. A support frame 4 is fixedly installed on one side of the top end of the device bottom frame 1. A spraying mechanism 5 is fixedly installed at the end of the support frame 4. A feeding mechanism 6 is fixedly installed on one side of the top end of the device bottom frame 1 away from the support frame 4. A discharging mechanism 7 is fixedly installed on one side of the top end of the device bottom frame 1 away from the support frame 4.

[0021] The transposition mechanism 2 includes a first bearing 21 which is fixedly clamped in the middle of the device bottom frame 1. A transposition shaft column 22 is fixedly clamped in the middle of the first bearing 21. The transposition shaft column 22 is convenient for rotating in the middle of the device bottom frame 1. A transposition chassis 23 is fixedly installed at the top end of the transposition shaft column 22. A lifting cylinder 24 is fixedly installed at the top end of the transposition chassis 23. A transposition top plate 25 is fixedly installed at the driving end of the lifting cylinder 24. Three storage racks 26 distributed in a circular array are integrally formed on the outer side of the transposition top plate 25. Second bearings 261 are fixedly clamped at one ends of the storage racks 26 far away from the transposition top plate 25. A support bottom pipe 27 is fixedly installed in the middle of the second bearings 261. A storage card seat 28 is fixedly installed at the top end of the support bottom pipe 27. The rotation of the transposition shaft column 22 drives the transposition chassis 23, the lifting cylinder 24, the transposition top plate 25, the three storage racks 26, the support bottom pipe 27, and the storage card seat 28 to rotate, so as to perform position conversion on the three storage card seats 28, which is convenient for subsequent feeding, transposition, spraying, and blanking of multiple aircraft component bodies 3 in sequence, and improves the spraying efficiency of the aircraft component bodies 3. A storage groove 281 is formed at the top end of the storage card seat 28. The aircraft component body 3 is movably clamped in the storage groove 281 for clamping, placing, and positioning of the aircraft component body 3.

[0022] The bottom of the transposition shaft column 22 extends into the device bottom frame 1. A driven worm gear 29 is fixedly sleeved at the bottom of the transposition shaft column 22. A driving worm 291 is meshed and connected to the outer side of the driven worm gear 29. A driving motor 8 is fixedly installed on the lower wall inside the device bottom frame 1 close to the driving worm 291. The driving end of the driving motor 8 and one end of the driving worm 291 are coaxially fixedly installed. By controlling the start of the driving motor 8 to drive the driving worm 291 to drive the driven worm gear 29 to rotate, the transposition shaft column 22 is driven to rotate in the middle of the device bottom frame 1.

[0023] The bottom of the supporting bottom pipe 27 extends to the bottom end of the storage rack 26. Crown gears 210 are fixedly sleeved on the bottoms of the supporting bottom pipes 27. Rotating frames 213 are fixedly installed in the middle of the bottom ends of the storage racks 26. Auxiliary shafts 212 are rotatably installed at the bottoms of the rotating frames 213. First gears 211 are fixedly installed at the opposite ends of the plurality of auxiliary shafts 212. The bottoms of the first gears 211 are meshed and connected with the corresponding crown gears 210. A plurality of second gears 214 are installed at the opposite ends of the plurality of auxiliary shafts 212. Auxiliary racks 215 are meshed and connected to the side ends of the second gears 214. The bottoms of the auxiliary racks 215 are fixedly installed at the top ends of the indexing chassis 23. The auxiliary racks 215 are slidably clamped at the side ends of the corresponding storage racks 26. Among them, by controlling the lifting cylinder 24 to drive the indexing top plate 25, the three storage racks 26, the supporting bottom pipe 27, the storage seat 28 and the aircraft component body 3 to rise. During the rising process, since the auxiliary rack 215 and the second gear 214 are meshed and connected, when the second gear 214 rises, the auxiliary rack 215 drives the second gear 214 to rotate synchronously, thereby driving the auxiliary shaft 212 and the first gear 211 to rotate, and further driving the crown gear 210, the supporting bottom pipe 27 and the storage seat 28 to rotate synchronously, so that the aircraft component body 3 rotates while rising, which is convenient for subsequent rotary full spraying operation on the aircraft component body 3, thereby improving the spraying quality of the aircraft component body 3.

[0024] The spraying mechanism 5 includes a spraying outer ring frame 51 and a spraying inner cylinder 52. The spraying outer ring frame 51 and the spraying inner cylinder 52 are coaxially arranged. The position of the spraying outer ring frame 51 is vertically corresponding to that of one of the object placing clamping seats 28. A plurality of outer nozzles 501 distributed in an annular array are fixedly installed on the inner side of the spraying outer ring frame 51. A plurality of inner nozzles 502 distributed in an annular array are fixedly installed on the outer side of the spraying inner cylinder 52. A guide material vertical pipe 53 is integrally formed in the middle of the top end of the spraying inner cylinder 52. A first connection head 531 is fixedly installed at the top end of the guide material vertical pipe 53. A guide material branch pipe 511 is integrally formed on the outer side of the spraying outer ring frame 51. A guide material ring pipe 512 is arranged on the outer side of a plurality of the guide material branch pipes 511. A connection pipe 513 corresponding to the guide material branch pipe 511 is integrally formed on the inner side of the guide material ring pipe 512. The end of the connection pipe 513 is fixedly installed with the corresponding guide material branch pipe 511. A second connection head 514 is fixedly clamped on the outer side of the guide material ring pipe 512. During use, the ends of the first connection head 531 and the second connection head 514 are connected to the material conveying end of the spraying solvent output pump mechanism. The spraying solvent output pump mechanism is controlled to be turned on. The spraying solvent is introduced into the spraying inner cylinder 52 through the first connection head 531 and the guide material vertical pipe 53 and is evenly sprayed out through a plurality of inner nozzles 502. The spraying solvent is evenly introduced into the spraying outer ring frame 51 through the second connection head 514, the guide material ring pipe 512, a plurality of connection pipes 513, and the guide material branch pipes 511 and is evenly sprayed out through a plurality of outer nozzles 501.

[0025] A flow guiding outer frame 54 is fixedly installed at the top end of the spraying outer ring frame 51. An outer exhaust cavity 541 is formed at the bottom of the flow guiding outer frame 54. An outer air inlet cavity 542 is formed at the top of the flow guiding outer frame 54. An outer exhaust ring groove 543 is formed at the inner bottom of the flow guiding outer frame 54. The outer exhaust ring groove 543 communicates with the outer exhaust cavity 541. An outer air inlet ring groove 544 is formed at the inner top of the flow guiding outer frame 54. The outer air inlet ring groove 544 communicates with the outer air inlet cavity 542. A first air guide pipe 545 and a second air guide pipe 546 are fixedly clamped at the top end of the flow guiding outer frame 54. The bottom of the first air guide pipe 545 extends to the top of the outer exhaust cavity 541. The bottom of the second air guide pipe 546 extends to the top of the outer air inlet cavity 542. During use, the first air guide pipe 545 and the second air guide pipe 546 are respectively connected to the output end and the output end of the air guiding pump mechanism. The air guiding pump mechanism is controlled to be turned on. The air flow is introduced into the outer exhaust cavity 541 through the first air guide pipe 545 and is discharged into the flow guiding outer frame 54 through the outer exhaust ring groove 543, and then is introduced into the outer air inlet cavity 542 through the outer air inlet ring groove 544 and is cyclically sucked into the air guiding pump mechanism through the second air guide pipe 546 to realize the air flow circulation inside the flow guiding outer frame 54.

[0026] A flow guide inner frame 55 is fixedly installed at the top end of the spraying inner cylinder 52. The flow guide inner frame 55 is of an annular structure. The longitudinal material guide pipe 53 movably penetrates through the middle of the flow guide inner frame 55. The top of the longitudinal material guide pipe 53 extends out of the top end of the flow guide inner frame 55. An inner exhaust cavity 552 is formed at the bottom of the flow guide inner frame 55. An inner air inlet cavity 553 is formed at the top of the flow guide inner frame 55. An inner exhaust ring groove 554 is formed at the outer bottom of the flow guide inner frame 55. The inner exhaust ring groove 554 communicates with the inner exhaust cavity 552. An inner air inlet ring groove 555 is formed at the outer top of the flow guide inner frame 55. The inner air inlet ring groove 555 communicates with the inner air inlet cavity 553. A third air guide pipe 556 and a fourth air guide pipe 557 are fixedly clamped at the top end of the flow guide inner frame 55. The bottom of the third air guide pipe 556 extends to the top of the inner exhaust cavity 552. The bottom of the fourth air guide pipe 557 extends to the top of the inner air inlet cavity 553. During use, the third air guide pipe 556 and the fourth air guide pipe 557 are respectively connected to the output ends of the air guide pump mechanism. The air guide pump mechanism is controlled to be turned on. Airflow is introduced into the inner exhaust cavity 552 through the third air guide pipe 556 and discharged to the outside of the flow guide inner frame 55 through the inner exhaust ring groove 554, and then is introduced into the inner air inlet cavity 553 through the inner air inlet ring groove 555 and is cyclically sucked into the air guide pump mechanism through the fourth air guide pipe 557 to realize the circulation of the airflow outside the flow guide inner frame 55.

[0027] Two symmetrically distributed U-shaped frames 56 are fixedly installed at the top ends of the flow guide outer frame 54 and the flow guide inner frame 55. The U-shaped frames 56 are fixedly installed at the ends of the support frame 4 to fix the spraying mechanism 5.

[0028] The feeding mechanism 6 includes a linear electric rail 61. The linear electric rail 61 is fixedly installed on one side of the top end of the device bottom frame 1 away from the support frame 4. The driving end of the linear electric rail 61 is fixedly installed with an electric lifting rod 62. The driving end of the electric lifting rod 62 is fixedly installed with a support base 63. A rotary cylinder 64 is fixedly installed at the top end of the support base 63. The driving end of the rotary cylinder 64 is fixedly installed with a rotary frame 65. A positioning outer frame 66 is fixedly installed at the end of the rotary frame 65. Two symmetrically distributed positioning clamping rods 67 are slidably clamped on one side of the positioning outer frame 66 away from the rotary frame 65. A bidirectional telescopic rod 68 is fixedly installed in the positioning outer frame 66. The driving end of the bidirectional telescopic rod 68 is fixedly installed with the corresponding positioning clamping rod 67. By controlling the bidirectional telescopic rod 68 to drive the two positioning clamping rods 67 to move towards each other, the aircraft component body 3 between the two positioning clamping rods 67 is clamped. On the contrary, by controlling the bidirectional telescopic rod 68 to drive the two positioning clamping rods 67 to move away from each other, the aircraft component body 3 loses the clamping. The positions of the two positioning clamping rods 67 in the feeding mechanism 6 are vertically corresponding to one of the storage seat holders 28.

[0029] The structure of the material discharging mechanism 7 is the same as that of the feeding mechanism 6. The material discharging mechanism 7 is fixedly installed at the top of the device bottom frame 1 on the side far from the support frame 4 through a linear electric rail 61. The positions of the two positioning clamping rods 67 and one of the object placing seats 28 in the material discharging mechanism 7 are vertically corresponding.

[0030] Working principle: During use, connect the ends of the first connector 531 and the second connector 514 to the material conveying end of the spraying solvent output pump mechanism. Connect the first air duct 545 and the second air duct 546 to the output ends of the air guiding pump mechanism respectively. Connect the third air duct 556 and the fourth air duct 557 to the output ends of the air guiding pump mechanism respectively. Automatically load the aircraft component body 3 to be sprayed at the position of the feeding mechanism 6 in sequence. Control the rotary cylinder 64 to drive the two positioning clamping rods 67 to rotate, place the aircraft component body 3 to be sprayed between the two positioning clamping rods 67. Control the bidirectional telescopic rod 68 to drive the two positioning clamping rods 67 to move towards each other to clamp the aircraft component body 3 between the two positioning clamping rods 67. Control the rotary cylinder 64 to drive the aircraft component body 3 to rotate again, and turn on the electric lifting rod 62 to drive the aircraft component body 3 to move upward. At the same time, turn on the linear electric rail 61 to drive the aircraft component body 3 to move horizontally, move the aircraft component body 3 to the top of one of the object placing seats 28, lower the aircraft component body 3, and the aircraft component body 3 is movably clamped in the object placing groove 281 to realize the clamping placement and positioning of the aircraft component body 3, and achieve the sequential automatic loading of multiple aircraft component bodies 3. Subsequently, control the drive motor 8 to drive the drive worm 291 to drive the driven worm wheel 29 to rotate, thereby driving the indexing shaft column 22 to rotate in the middle of the device bottom frame 1, driving the indexing chassis 23, the lifting cylinder 24, the indexing top plate 25, the three object placing frames 26, the support bottom pipe 27, and the object placing seats 28 to rotate, so as to perform position conversion on the three object placing seats 28 and rotate the aircraft component body 3 to be sprayed below the spraying mechanism 5. Subsequently, control the lifting cylinder 24 to drive the indexing top plate 25, the three object placing frames 26, the support bottom pipe 27, the object placing seats 28, and the aircraft component body 3 to rise. During the rising process, since the auxiliary rack 215 is meshed and connected with the second gear 214, the second gear 214 rises, and the auxiliary rack 215 drives the second gear 214 to rotate synchronously, thereby driving the auxiliary shaft 212 and the first gear 211 to rotate, and further driving the crown gear 210, the support bottom pipe 27, and the object placing seats 28 to rotate synchronously, so as to drive the aircraft component body 3 to rotate while rising. The aircraft component body 3 gradually passes through the inner side of the spraying outer ring frame 51 and the outer side of the spraying inner cylinder 52. At the same time, the spraying solvent output pump mechanism is controlled to be turned on. The spraying solvent is introduced into the spraying inner cylinder 52 through the first connector 531 and the material guiding longitudinal pipe 53, and is evenly sprayed out through a plurality of inner nozzles 502 to perform a rotary full-surface spraying operation on the outer wall of the aircraft component body 3. At the same time, the spraying solvent is evenly introduced into the spraying outer ring frame 51 through the second connector 514, the material guiding ring pipe 512, a plurality of connecting pipes 513, and the material guiding branch pipe 511, and is evenly sprayed out through a plurality of outer nozzles 501 to simultaneously perform a rotary full-surface spraying operation on the inner wall of the aircraft component body 3; During the spraying operation, the air guiding pump mechanism is controlled to be turned on. The air flow is introduced into the outer exhaust cavity 541 through the first air guiding pipe 545 and is discharged into the diversion outer frame 54 through the outer exhaust ring groove 543. Then, it is introduced into the outer intake cavity 542 through the outer intake ring groove 544 and is cyclically sucked into the air guiding pump mechanism through the second air guiding pipe 546 to conduct the air flow inside the diversion outer frame 54, perform synchronous air drying on the outer wall of the aircraft component body 3, and accelerate the adhesion of the sprayed coating on the outer wall of the aircraft component body 3; At the same time, the air flow is introduced into the inner exhaust cavity 552 through the third air guiding pipe 556 and is discharged to the outside of the diversion inner frame 55 through the inner exhaust ring groove 554. Then, it is introduced into the inner intake cavity 553 through the inner intake ring groove 555 and is cyclically sucked into the air guiding pump mechanism through the fourth air guiding pipe 557 to conduct the air flow outside the diversion inner frame 55, perform synchronous air drying on the inner wall of the aircraft component body 3, and accelerate the adhesion of the sprayed coating on the inner wall of the aircraft component body 3; After the spraying is completed, the sprayed aircraft component body 3 is lowered and reset, and the sprayed aircraft component body 3 is rotated to the unloading mechanism 7. According to the usage steps of the feeding mechanism 6, the sprayed aircraft component body 3 is unloaded to perform automatic unloading of the aircraft component body 3; In sequence, automatic feeding operation, automatic rotation operation, automatic rotary full-surface spraying operation, and automatic unloading operation of multiple aircraft component bodies 3 are realized, improving the spraying quality and efficiency of the aircraft component body 3.

[0031] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirits of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A spraying device for surface treatment of aircraft parts, including a device bottom frame (1), characterized in that: In the middle of the bottom frame (1) of the device, a transposition mechanism (2) is provided. At the top of the transposition mechanism (2), an aircraft component body (3) is provided. On one side of the top of the bottom frame (1) of the device, a support frame (4) is fixedly installed. At the end of the support frame (4), a spraying mechanism (5) is fixedly installed. On the side of the top of the bottom frame (1) of the device away from the support frame (4), a feeding mechanism (6) is fixedly installed. On the side of the top of the bottom frame (1) of the device away from the support frame (4), a discharging mechanism (7) is fixedly installed.

2. A spraying device for surface treatment of aircraft parts according to claim 1, characterized in that: The transposition mechanism (2) includes a first bearing (21). The first bearing (21) is fixedly clamped in the middle of the bottom frame (1) of the device. In the middle of the first bearing (21), a transposition shaft column (22) is fixedly clamped. At the top of the transposition shaft column (22), a transposition chassis (23) is fixedly installed. At the top of the transposition chassis (23), a lifting cylinder (24) is fixedly installed. At the driving end of the lifting cylinder (24), a transposition top plate (25) is fixedly installed. On the outer side of the transposition top plate (25), three storage racks (26) distributed in an annular array are integrally formed. At the end of each storage rack (26) away from the transposition top plate (25), a second bearing (261) is fixedly clamped. In the middle of the second bearing (261), a support bottom tube (27) is fixedly installed. At the top of the support bottom tube (27), a storage card seat (28) is fixedly installed. On the top of the storage card seat (28), a storage groove (281) is opened. The aircraft component body (3) is movably clamped in the storage groove (281).

3. The spraying device for surface treatment of aircraft parts according to claim 2, wherein: The bottom of the transposition shaft column (22) extends into the bottom frame (1) of the device. At the bottom of the transposition shaft column (22), a driven worm gear (29) is fixedly sleeved. On the outer side of the driven worm gear (29), a driving worm (291) is meshed. On one side of the inner lower wall of the bottom frame (1) close to the driving worm (291), a driving motor (8) is fixedly installed. The driving end of the driving motor (8) and one end of the driving worm (291) are coaxially fixedly installed.

4. A spraying device for surface treatment of aircraft parts according to claim 2, characterized in that: The bottom of the support bottom tube (27) extends to the bottom end of the storage rack (26). At the bottom of the support bottom tube (27), a crown gear (210) is fixedly sleeved. In the middle of the bottom end of each storage rack (26), a rotating frame (213) is fixedly installed. At the bottom of the rotating frame (213), an auxiliary shaft (212) is rotatably installed. At the opposite ends of the plurality of auxiliary shafts (212), a first gear (211) is fixedly installed. The first gear (211) is meshed with the bottom of the corresponding crown gear (210). At the relative ends of the plurality of auxiliary shafts (212), a plurality of second gears (214) are installed. The side ends of the second gears (214) are meshed with auxiliary racks (215). The bottom ends of the auxiliary racks (215) are fixedly installed on the top of the transposition chassis (23). The auxiliary racks (215) are slidably clamped on the side ends of the corresponding storage racks (26).

5. The spraying device for surface treatment of aircraft parts according to claim 2, wherein: The spraying mechanism (5) includes a spraying outer ring frame (51) and a spraying inner cylinder (52). The spraying outer ring frame (51) and the spraying inner cylinder (52) are coaxially arranged. The position of the spraying outer ring frame (51) is vertically corresponding to that of one of the object placing seat holders (28). A plurality of outer nozzles (501) distributed in an annular array are fixedly installed on the inner side of the spraying outer ring frame (51). A plurality of inner nozzles (502) distributed in an annular array are fixedly installed on the outer side of the spraying inner cylinder (52). A material guiding vertical pipe (53) is integrally formed in the middle of the top end of the spraying inner cylinder (52). A first connector (531) is fixedly installed at the top end of the material guiding vertical pipe (53). A material guiding branch pipe (511) is integrally formed on the outer side of the spraying outer ring frame (51). A material guiding ring pipe (512) is arranged on the outer sides of the plurality of material guiding branch pipes (511). A connecting pipe (513) corresponding to the material guiding branch pipe (511) is integrally formed on the inner side of the material guiding ring pipe (512). The end of the connecting pipe (513) is fixedly installed with the corresponding material guiding branch pipe (511). A second connector (514) is fixedly clamped on the outer side of the material guiding ring pipe (512).

6. The spraying device for surface treatment of aircraft parts according to claim 5, characterized in that: A flow guiding outer frame (54) is fixedly installed at the top end of the spraying outer ring frame (51). An outer exhaust cavity (541) is formed at the bottom of the flow guiding outer frame (54). An outer intake cavity (542) is formed at the top of the flow guiding outer frame (54). An outer exhaust ring groove (543) is formed at the inner bottom of the flow guiding outer frame (54). The outer exhaust ring groove (543) communicates with the outer exhaust cavity (541). An outer intake ring groove (544) is formed at the inner top of the flow guiding outer frame (54). The outer intake ring groove (544) communicates with the outer intake cavity (542). A first air duct (545) and a second air duct (546) are fixedly clamped at the top end of the flow guiding outer frame (54). The bottom of the first air duct (545) extends to the top of the outer exhaust cavity (541). The bottom of the second air duct (546) extends to the top of the outer intake cavity (542).

7. A spraying device for surface treatment of aircraft parts according to claim 6, characterized in that: A flow guiding inner frame (55) is fixedly installed at the top end of the spraying inner cylinder (52). The flow guiding inner frame (55) is arranged in an annular structure. The longitudinal material guiding pipe (53) movably penetrates through the middle of the flow guiding inner frame (55). The top of the longitudinal material guiding pipe (53) extends out of the top end of the flow guiding inner frame (55). An inner exhaust cavity (552) is formed at the bottom of the flow guiding inner frame (55). An inner air inlet cavity (553) is formed at the top of the flow guiding inner frame (55). An inner exhaust ring groove (554) is formed at the outer bottom of the flow guiding inner frame (55). The inner exhaust ring groove (554) communicates with the inner exhaust cavity (552). An inner air inlet ring groove (555) is formed at the outer top of the flow guiding inner frame (55). The inner air inlet ring groove (555) communicates with the inner air inlet cavity (553). A third air guiding pipe (556) and a fourth air guiding pipe (557) are fixedly clamped at the top end of the flow guiding inner frame (55). The bottom of the third air guiding pipe (556) extends to the top of the inner exhaust cavity (552). The bottom of the fourth air guiding pipe (557) extends to the top of the inner air inlet cavity (553).

8. A spraying device for surface treatment of aircraft parts according to claim 7, characterized in that: Two symmetrically distributed U-shaped frames (56) are fixedly installed at the top ends of the flow guiding outer frame (54) and the flow guiding inner frame (55). The U-shaped frames (56) are fixedly installed at the ends of the support frame (4).

9. The spraying device for surface treatment of aircraft parts according to claim 2, characterized in that: The feeding mechanism (6) includes a linear electric rail (61). The linear electric rail (61) is fixedly installed on one side of the top end of the device bottom frame (1) away from the support frame (4). A driving end of the linear electric rail (61) is fixedly installed with an electric lifting rod (62). A driving end of the electric lifting rod (62) is fixedly installed with a support base (63). A rotating cylinder (64) is fixedly installed at the top end of the support base (63). A driving end of the rotating cylinder (64) is fixedly installed with a rotating frame (65). A positioning outer frame (66) is fixedly installed at the end of the rotating frame (65). Two symmetrically distributed positioning clamping rods (67) are slidably clamped on one side of the positioning outer frame (66) away from the rotating frame (65). A bidirectional telescopic rod (68) is fixedly installed in the positioning outer frame (66). A driving end of the bidirectional telescopic rod (68) is fixedly installed with the corresponding positioning clamping rod (67). The positions of the two positioning clamping rods (67) in the feeding mechanism (6) are vertically corresponding to one of the object placing seat holders (28).

10. A spraying device for surface treatment of aircraft parts according to claim 9, characterized in that: The structure of the discharging mechanism (7) is the same as that of the feeding mechanism (6). The discharging mechanism (7) is fixedly installed on one side of the top end of the device bottom frame (1) away from the support frame (4) through the linear electric rail (61). The positions of the two positioning clamping rods (67) in the discharging mechanism (7) are vertically corresponding to one of the object placing seat holders (28).

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