CN217074830U - Overturning equipment convenient to move and used for undercarriage of airplane component - Google Patents
Overturning equipment convenient to move and used for undercarriage of airplane component Download PDFInfo
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- CN217074830U CN217074830U CN202221057289.7U CN202221057289U CN217074830U CN 217074830 U CN217074830 U CN 217074830U CN 202221057289 U CN202221057289 U CN 202221057289U CN 217074830 U CN217074830 U CN 217074830U
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- fixedly connected
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- undercarriage
- overturning
- air bag
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Abstract
The utility model discloses an aircraft part tipping arrangement for undercarriage convenient to remove belongs to aviation aircraft parts processing technology field, the on-line screen storage device comprises a base, one side of base is provided with the removal subassembly, the top both sides of base all are provided with the portal frame. The utility model discloses in, drive first pivot through first motor, initiative bevel gear, driven cone pulley and lead screw rotate, it removes to make the thread bush drive sliding plate and portal frame are automatic, the shift position to sliding plate and portal frame is injectd, and then artificial adjust time has been reduced, it rotates to drive the second pivot through the second motor, overturn aircraft part, carry the inside gas of first gasbag to the inside of second gasbag through the cam, it carries the lubricating oil of the inside storage of oil bag to sponge piece department to drive the stripper plate, lubricate lead screw and thread bush, prevent that the lead screw from exposing for a long time and producing the corrosion phenomenon in the air, cause the influence to its performance.
Description
Technical Field
The utility model belongs to the technical field of the processing of aviation aircraft part, especially, relate to an aircraft part is tipping arrangement for undercarriage convenient to remove.
Background
With the development of modern aviation industry, large-scale integral structural parts widely applied to modern airplanes need to be turned over and then subjected to subsequent processing of airplane parts in order to improve the airplane production efficiency and the airplane automatic production level and further meet the requirement for multi-angle processing of airplane parts when the airplane parts are mechanically processed.
The existing overturning equipment for undercarriage aircraft parts is poor in stability and safety performance when in use, inconvenient equipment is automatically moved and needs to be manually operated, so that the position between the overturning equipment and the aircraft parts is inaccurate, the working efficiency is low, the automatic lubrication is inconvenient to equipment elements after the overturning equipment is used for a long time, the elements are directly exposed in the air for a long time, the rusting phenomenon is easily generated, the service life and the service performance of the elements are influenced, and certain improvement is needed.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a: the overturning equipment for the undercarriage of the airplane component is convenient to move and solves the problems that the existing overturning equipment for the undercarriage of the airplane component is poor in stability and safety performance when in use, inconvenient equipment is inconvenient to automatically move and needs to be manually operated, the position between the overturning equipment and the airplane component is inaccurate, the working efficiency is low, the automatic lubrication is inconvenient to equipment elements after the overturning equipment is used for a long time, the elements are directly exposed in the air for a long time, the rusting phenomenon is easily generated, and the service life and the service performance of the elements are influenced.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a turning device convenient to move and used for undercarriage of an airplane component comprises a base, wherein a moving assembly is arranged on one side of the base, portal frames are arranged on two sides of the top of the base, an air cylinder is fixedly connected to the top of each portal frame, a limiting sliding block is fixedly connected to the top of each air cylinder after the top of each air cylinder penetrates through a first through hole formed in each portal frame, a turning box is arranged on one side of each limiting sliding block, a second motor is fixedly connected to one side of the inside of each turning box, a second rotating shaft is fixedly connected to an output shaft of each second motor, and a lubricating assembly is arranged inside each turning box;
the movable assembly comprises a fixed box, a first motor is fixedly connected to one side of the inside of the fixed box, a first rotating shaft is fixedly connected to an output shaft of the first motor, two driving bevel gears are fixedly clamped on the first rotating shaft and located on two sides of the first rotating shaft, the two driving bevel gears are connected with driven bevel wheels in a meshed mode, lead screws are fixedly clamped inside the two driven bevel wheels, one ends of the two lead screws, deviating from the two driven bevel wheels, of the two lead screws penetrate through threaded sleeves behind grooves formed in the base, the two lead screws are arranged on two sides of the base respectively, supporting blocks are fixedly connected to the tops of the threaded sleeves, and sliding plates are fixedly connected to the tops of the supporting blocks.
As a further description of the above technical solution:
the lubricating assembly comprises a cam, the cam is fixedly clamped on the second rotating shaft, transverse plates are arranged on two sides of the cam, one side of each transverse plate, which deviates from the cam, is fixedly connected with a guide rod, and a shell is arranged at the other end of each guide rod.
As a further description of the above technical solution:
the inside sliding connection of casing has the flat board, dull and stereotyped one side and guide arm fixed connection, dull and stereotyped opposite side fixedly connected with first gasbag, one side fixed connection that first gasbag deviates from the flat board is on the inside wall of casing.
As a further description of the above technical solution:
one side of the first air bag is communicated with a connecting pipe, one end of the connecting pipe, which deviates from the first air bag, sequentially penetrates through a second through hole formed in the shell and the turnover box and then is communicated with a second air bag, the second air bag is arranged in an inner cavity formed in the supporting block, a pressure valve is arranged on the connecting pipe, the other side of the first air bag is provided with an air inlet pipe, and a switch valve is arranged on the air inlet pipe.
As a further description of the above technical solution:
the bottom fixedly connected with stripper plate of second gasbag, the below of stripper plate is provided with the oil bag, the one end intercommunication of oil bag has into oil pipe, the other end intercommunication of oil bag has out oil pipe, it all is provided with the check valve on oil pipe and the oil pipe to go out, one side that goes out oil pipe is provided with the choke valve, the other end that goes out oil pipe has the sponge piece through coupling and second connecting pipe intercommunication, the sponge piece is provided with two, the sponge piece sets up respectively in the both sides of thread bush, just the thread bush contacts with the lead screw, is provided with the check valve on the second connecting pipe.
As a further description of the above technical solution:
the top of the sliding plate is fixedly connected with the bottom of the portal frame, two idler wheels are symmetrically arranged at the bottom of the sliding plate, a first I-shaped sliding rail is slidably connected to the bottom of each idler wheel, and the bottom of each first I-shaped sliding rail is fixedly connected to the top of the base.
As a further description of the above technical solution:
the limiting sliding block is arranged in an I shape, the four corners of the limiting sliding block are fixedly connected with sliding blocks, one side of the sliding block, which deviates from the limiting sliding block, is connected with a second sliding rail in a sliding mode, and one side of the second sliding rail, which deviates from the sliding block, is fixedly connected to the portal frame.
To sum up, owing to adopted above-mentioned technical scheme, the beneficial effects of the utility model are that:
1. the utility model discloses in, drive first pivot through first motor and rotate, utilize first pivot, initiative bevel gear, the linkage effect between driven cone pulley and the lead screw, make the lead screw rotate, and then make the thread bush drive sliding plate and portal frame remove automatically, the shift position of sliding plate and portal frame is injectd through first motor, and then prevent that the manual work from operating the time to it the position inaccuracy of outside fixing device and grabbing device and aircraft part, artificial regulation time has been increased, and then the work efficiency of equipment has been reduced, the stability of equipment when removing has been guaranteed through gyro wheel and first I shape slide rail, and when gyro wheel and first I shape slide rail were got and overturn aircraft part clamp at equipment, carry out the outrigger to the portal frame, and then the stability of equipment has been improved.
2. The utility model discloses in, it rotates to drive the second pivot through the second motor, overturn aircraft parts, when overturning aircraft parts, the second pivot drives the cam and rotates, make the diaphragm drive the flat board and extrude first gasbag, carry the inside of first gasbag inside gas to the second gasbag, along with the inside gaseous increase of second gasbag, drive the stripper plate and extrude the oil bag, carry the lubricating oil of the inside storage of oil bag to sponge piece department through an oil pipe, lubricate lead screw and thread bush through the sponge piece, prevent that the lead screw from exposing for a long time and producing the corrosion phenomenon in the air, cause the influence to its performance.
Drawings
Fig. 1 is a schematic view of an overall three-dimensional structure of a turning device for undercarriage of an airplane component, which is convenient to move according to the present invention;
fig. 2 is a schematic structural diagram of a moving assembly in a turning device for undercarriage of an aircraft component, which is convenient to move according to the present invention;
fig. 3 is a schematic structural diagram of a supporting block in a turning device for undercarriage of an aircraft component, which is convenient to move according to the present invention;
fig. 4 is the utility model provides an aircraft part undercarriage is with lubricating component's in tipping arrangement schematic structure view convenient to remove.
Illustration of the drawings:
1. a base; 2. a moving assembly; 201. a fixed box; 202. a first motor; 203. a first rotating shaft; 204. a drive bevel gear; 205. a driven conical wheel; 206. a screw rod; 207. a threaded sleeve; 208. a support block; 209. a sliding plate; 210. a roller; 3. a second rotating shaft; 4. a gantry; 5. a cylinder; 6. a limiting sliding block; 7. a second motor; 8. turning over the box; 9. a lubrication assembly; 901. a cam; 902. a transverse plate; 903. a guide bar; 904. a flat plate; 905. a housing; 906. a first air bag; 907. a connecting pipe; 908. a second air bag; 909. a pressing plate; 910. an oil pocket; 911. an oil outlet pipe; 912. a sponge block.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.
Referring to fig. 1-4, the present invention provides a technical solution: a turning device convenient for moving an airplane component to put on a shelf comprises a base 1, wherein a moving assembly 2 is arranged on one side of the base 1, portal frames 4 are arranged on two sides of the top of the base 1, an air cylinder 5 is fixedly connected to the top of each portal frame 4, a limiting sliding block 6 is fixedly connected to the top of each air cylinder 5 after passing through a first through hole formed in each portal frame 4, a turning box 8 is arranged on one side of each limiting sliding block 6, a second motor 7 is fixedly connected to one side inside of each turning box 8, a second rotating shaft 3 is fixedly connected to an output shaft of each second motor 7, and a lubricating assembly 9 is arranged inside each turning box 8;
the movable assembly 2 comprises a fixed box 201, a first motor 202 fixedly connected to one side of the inside of the fixed box 201, a first rotating shaft 203 fixedly connected to an output shaft of the first motor 202, two driving bevel gears 204 are fixedly clamped on the first rotating shaft 203, the two driving bevel gears 204 are located on two sides of the first rotating shaft 203, the two driving bevel gears 204 are all meshed with driven bevel wheels 205, lead screws 206 are fixedly clamped inside the two driven bevel wheels 205, one ends of the two lead screws 206 deviating from the two driven bevel wheels 205 penetrate through grooves formed in the base 1 and then are connected with thread sleeves 207 in a threaded mode, the two lead screws 206 are arranged on two sides of the base 1 respectively, supporting blocks 208 fixedly connected to the tops of the thread sleeves 207, and sliding plates 209 are fixedly connected to the tops of the supporting blocks 208.
The implementation mode is specifically as follows: the external fixing device and the grabbing device are fixedly clamped on the second rotating shaft 3, when the aircraft component needs to be turned over, the first motor 202 is controlled through the external control device, the first motor 202 drives the first rotating shaft 203 to rotate, the first rotating shaft 203 is utilized, the driving bevel gear 204 and the linkage effect between the driven bevel wheel 205 and the lead screw 206 are utilized, the lead screw 206 is rotated, the rotating force is converted into linear movement through the thread sleeve 207, the sliding plate 209 and the portal frame 4 are driven to automatically move, the moving positions of the sliding plate 209 and the portal frame 4 are limited through the first motor 202, and therefore the situation that the external fixing device, the grabbing device and the aircraft component are inaccurate when the external fixing device and the portal frame are manually operated is prevented from being caused, manual adjusting time is prolonged, and further the working efficiency of equipment is influenced.
The lubricating component 9 comprises a cam 901, the cam 901 is fixedly clamped on the second rotating shaft 3, both sides of the cam 901 are provided with transverse plates 902, one side of the transverse plate 902, which is far away from the cam 901, is fixedly connected with a guide rod 903, the other end of the guide rod 903 is provided with a shell 905, the interior of the shell 905 is connected with a flat plate 904 in a sliding manner, one side of the flat plate 904 is fixedly connected with the guide rod 903, the other side of the flat plate 904 is fixedly connected with a first air bag 906, one side of the first air bag 906, which is far away from the flat plate 904, is fixedly connected on the inner side wall of the shell 905, one side of the first air bag 906 is communicated with a connecting pipe 907, one end of the connecting pipe 907, which is far away from the first air bag 906, sequentially penetrates through a second through hole formed in the shell 905 and the turnover box 8 and is communicated with a second air bag 908, the second air bag 908 is arranged in an inner cavity formed in the supporting block 208, a pressure valve is arranged on the connecting pipe, the other side of the first air bag 906 is provided with an air inlet pipe, and a switch valve is arranged on the air inlet pipe 907, the bottom fixedly connected with stripper plate 909 of second gasbag 908, the below of stripper plate 909 is provided with oil bag 910, the one end intercommunication of oil bag 910 has into oil pipe, the other end intercommunication of oil bag 910 has an oil pipe 911, all be provided with the check valve on oil pipe 911 and the oil pipe, one side of oil pipe 911 is provided with the choke valve, the other end of oil pipe 911 has sponge piece 912 through coupling and second connecting pipe intercommunication, sponge piece 912 is provided with two, sponge piece 912 sets up respectively in the both sides of thread bush 207, and thread bush 207 contacts with lead screw 206, be provided with the check valve on the second connecting pipe.
The implementation mode is specifically as follows: when overturning aircraft parts, the second rotating shaft 3 drives the cam 901 to rotate, the transverse plate 902 is moved, the transverse plate 902 is utilized, the linkage effect between the guide rod 903 and the transverse plate 904 is utilized, the first air bag 906 is extruded by the flat plate 904, the gas in the first air bag 906 is conveyed to the inside of the second air bag 908, along with the increase of the gas in the second air bag 908, the extrusion plate 909 is driven to extrude the oil bag 910, the lubricating oil stored in the oil bag 910 is conveyed to the sponge block 912 through the oil outlet pipe 911, the screw rod 206 and the thread sleeve 207 are lubricated through the sponge block 912, the phenomenon that the screw rod 206 is rusted in the air after being exposed for a long time is prevented, and the influence on the service performance of the screw rod is caused.
The top of sliding plate 209 and the bottom fixed connection of portal frame 4, sliding plate 209 bottom symmetry is provided with two gyro wheels 210, the bottom sliding connection of gyro wheel 210 has first I shape slide rail, the bottom fixed connection of first I shape slide rail is at the top of base 1, spacing sliding block 6 sets up to the I shape, the equal fixedly connected with slider in four corners of spacing sliding block 6, one side sliding connection that the slider deviates from spacing sliding block 6 has the second slide rail, one side fixed connection that the second slide rail deviates from the slider is on portal frame 4.
The implementation mode is specifically as follows: the roller 210 and the first i-shaped slide rail ensure the stability of the equipment during movement, and the roller 210 and the first i-shaped slide rail stably support the portal frame 4 when the external fixing device and the grabbing device clamp and overturn the aircraft component, thereby preventing the aircraft component from overturning, the center of gravity of the device is deviated, which affects the stability of the device, when the device is moved to a proper place, the air cylinder 5 drives the turnover box 8 to move downwards, the external control device controls the external fixing device and the gripping device to clamp and fix, at this time, the second motor 7 drives the second rotating shaft 3 to rotate, further overturning the aircraft component, providing stability for the overturning box 8 up and down through the limit sliding block 6, the sliding block and the second sliding rail, the acting force during the overturning is dispersed, and further the influence on the service performance and the service life of the equipment is prevented.
The working principle is as follows: when the device is used, the external fixing device and the gripping device are fixedly clamped on the second rotating shaft 3, when an airplane component needs to be turned, the first motor 202 is controlled by the external control device, the first motor 202 drives the first rotating shaft 203 to rotate, the screw rod 206 is rotated by utilizing the linkage effect among the first rotating shaft 203, the driving bevel gear 204, the driven bevel wheel 205 and the screw rod 206, the rotating force is converted into linear movement by the thread sleeve 207 to drive the sliding plate 209 and the portal frame 4 to automatically move, the moving positions of the sliding plate 209 and the portal frame 4 are limited by the first motor 202, the manual adjusting time is further reduced, the roller 210 and the first I-shaped slide rail ensure the stability of the device during moving, and when the airplane component is clamped and turned by the external fixing device and the gripping device through the roller 210 and the first I-shaped slide rail, the gantry 4 is stably supported, so that the condition that the center of gravity of the aircraft part deviates when the aircraft part is overturned to influence the stability of equipment is prevented, the overturning box 8 is driven to move downwards by the air cylinder 5, the external control device controls the external fixing device and the grabbing device to clamp and fix, and the second rotating shaft 3 is driven to rotate by the second motor 7 to overturn the aircraft part;
when overturning the aircraft component, second pivot 3 drives cam 901 and rotates, make diaphragm 902 remove, utilize diaphragm 902, the linkage effect between guide arm 903 and the diaphragm 904, make dull and stereotyped 904 extrude first gasbag 906, carry the inside gas of first gasbag 906 to the inside of second gasbag 908, along with the increase of the inside gas of second gasbag 908, drive extrusion board 909 extrudees oil bag 910, carry the inside lubricating oil of storing of oil bag 910 to sponge piece 912 department through play oil pipe 911, lubricate lead screw 206 and thread bush 207 through sponge piece 912, high durability and convenient use.
The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.
Claims (6)
1. The overturning equipment convenient for moving the undercarriage of the aircraft component comprises a base (1) and is characterized in that a moving assembly (2) is arranged on one side of the base (1), portal frames (4) are arranged on two sides of the top of the base (1), an air cylinder (5) is fixedly connected to the top of each portal frame (4), a limiting sliding block (6) is fixedly connected to the top of each air cylinder (5) after the top of each air cylinder passes through a first through hole formed in each portal frame (4), an overturning box (8) is arranged on one side of each limiting sliding block (6), a second motor (7) is fixedly connected to one side of the inside of each overturning box (8), a second rotating shaft (3) is fixedly connected to an output shaft of each second motor (7), and a lubricating assembly (9) is arranged inside each overturning box (8);
the moving assembly (2) comprises a fixed box (201), a first motor (202) is fixedly connected to one side inside the fixed box (201), an output shaft of the first motor (202) is fixedly connected with a first rotating shaft (203), two driving bevel gears (204) are fixedly clamped on the first rotating shaft (203), the two driving bevel gears (204) are located on two sides of the first rotating shaft (203), the two driving bevel gears (204) are respectively connected with a driven bevel wheel (205) in a meshed manner, lead screws (206) are fixedly clamped inside the two driven bevel wheels (205), one ends of the two lead screws (206) departing from the two driven bevel wheels (205) penetrate through grooves formed in the base (1) and then are connected with threaded sleeves (207) in a threaded manner, the two lead screws (206) are respectively arranged on two sides of the base (1), and supporting blocks (208) are fixedly connected to the tops of the threaded sleeves (207), the top of the supporting block (208) is fixedly connected with a sliding plate (209).
2. The aircraft component undercarriage overturning device convenient to move according to claim 1, wherein the lubricating assembly (9) comprises a cam (901), the cam (901) is fixedly clamped on the second rotating shaft (3), transverse plates (902) are arranged on two sides of the cam (901), a guide rod (903) is fixedly connected to one side, away from the cam (901), of each transverse plate (902), and a shell (905) is arranged at the other end of each guide rod (903).
3. The aircraft component undercarriage overturning device convenient to move according to claim 2, wherein a flat plate (904) is slidably connected to the inside of the housing (905), one side of the flat plate (904) is fixedly connected with the guide rod (903), the other side of the flat plate (904) is fixedly connected with a first air bag (906), and one side of the first air bag (906) departing from the flat plate (904) is fixedly connected to the inner side wall of the housing (905).
4. The aircraft component undercarriage turning device convenient to move according to claim 3, wherein one side of the first air bag (906) is communicated with a connecting pipe (907), one end of the connecting pipe (907) departing from the first air bag (906) sequentially penetrates through a second through hole formed in the shell (905) and the turning box (8) and is communicated with a second air bag (908), and the second air bag (908) is arranged in an inner cavity formed in the supporting block (208).
5. The overturning device convenient for moving of the undercarriage of an aircraft component as claimed in claim 4, wherein a squeeze plate (909) is fixedly connected to the bottom of the second air bag (908), an oil bag (910) is arranged below the squeeze plate (909), one end of the oil bag (910) is communicated with an oil inlet pipe, the other end of the oil bag (910) is communicated with an oil outlet pipe (911), the other end of the oil outlet pipe (911) is communicated with two sponge blocks (912) through a pipe joint and a second connecting pipe, the two sponge blocks (912) are arranged, the sponge blocks (912) are respectively arranged on two sides of the threaded sleeve (207), and the threaded sleeve (207) is in contact with the screw rod (206).
6. The overturning device for conveniently moving the undercarriage of an aircraft component according to claim 1, wherein the top of the sliding plate (209) is fixedly connected with the bottom of the gantry (4), two rollers (210) are symmetrically arranged at the bottom of the sliding plate (209), the bottom of each roller (210) is slidably connected with a first i-shaped sliding rail, and the bottom of each first i-shaped sliding rail is fixedly connected with the top of the base (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221057289.7U CN217074830U (en) | 2022-05-05 | 2022-05-05 | Overturning equipment convenient to move and used for undercarriage of airplane component |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221057289.7U CN217074830U (en) | 2022-05-05 | 2022-05-05 | Overturning equipment convenient to move and used for undercarriage of airplane component |
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| Publication Number | Publication Date |
|---|---|
| CN217074830U true CN217074830U (en) | 2022-07-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202221057289.7U Active CN217074830U (en) | 2022-05-05 | 2022-05-05 | Overturning equipment convenient to move and used for undercarriage of airplane component |
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| CN (1) | CN217074830U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115319202A (en) * | 2022-09-14 | 2022-11-11 | 安泰爱科科技有限公司 | Neodymium iron boron tombarthite permanent magnet does not have boiling material processing with keeping anchor clamps and cutting equipment |
-
2022
- 2022-05-05 CN CN202221057289.7U patent/CN217074830U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115319202A (en) * | 2022-09-14 | 2022-11-11 | 安泰爱科科技有限公司 | Neodymium iron boron tombarthite permanent magnet does not have boiling material processing with keeping anchor clamps and cutting equipment |
| CN115319202B (en) * | 2022-09-14 | 2023-12-19 | 安泰爱科科技有限公司 | Neodymium iron boron rare earth permanent magnet does not have material processing of boiling and uses holding fixture and cutting equipment |
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