CN212024654U - Lifting device for aircraft engine maintenance - Google Patents
Lifting device for aircraft engine maintenance Download PDFInfo
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- CN212024654U CN212024654U CN201922488975.4U CN201922488975U CN212024654U CN 212024654 U CN212024654 U CN 212024654U CN 201922488975 U CN201922488975 U CN 201922488975U CN 212024654 U CN212024654 U CN 212024654U
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- shaped plate
- shaped
- fixed
- aircraft engine
- plate
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Abstract
The utility model discloses an aircraft engine maintenance is with lifting device, including the U-shaped plate, sliding sleeve is equipped with two movable blocks on the U-shaped plate, one side fixed mounting that two movable blocks are close to each other has the fixed case that same bottom set up for the opening, the top fixed mounting of fixed case has the U-shaped block, the top fixed mounting of U-shaped block has first screw rod, the top of first screw rod extends to the top of U-shaped plate, the top of U-shaped block is equipped with fixed pipe, the top of fixed pipe extends to the top of U-shaped plate, the U-shaped plate rotates the cover and establishes on fixed pipe, fixed pipe thread bush is established on first screw rod, fixed cover is equipped with the first gear that is located U-shaped plate top on the fixed pipe, the top thread fixing of U-shaped plate. The utility model discloses simple structure, convenient operation is convenient for carry out the centre gripping according to actual automation to aircraft engine fixed, and is convenient for lift aircraft engine, and the inspection maintenance of being convenient for satisfies the use needs, is favorable to the use.
Description
Technical Field
The utility model relates to a lifting means technical field especially relates to an aircraft engine maintenance is with lifting device.
Background
The aircraft engine is the heart of an aircraft, when the spare part of the aircraft engine is damaged or breaks down, the engine needs to be checked and maintained, when the aircraft engine is checked and maintained, the engine of the aircraft needs to be lifted through the lifting device, the aircraft engine is convenient to be checked in all directions, and therefore the maintenance is convenient.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving the defects existing in the prior art and providing a lifting device for maintaining an aircraft engine.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a lifting device for maintaining an aircraft engine comprises a U-shaped plate, wherein two moving blocks are slidably sleeved on the U-shaped plate, one side, close to each other, of each moving block is fixedly provided with a fixed box, the bottom of each fixed box is provided with an opening, a U-shaped block is fixedly arranged at the top of each fixed box, a first screw is fixedly arranged at the top of each U-shaped block, the top end of each first screw extends to the upper side of the U-shaped plate, a fixed pipe is arranged above each U-shaped block, the top end of each fixed pipe extends to the upper side of the U-shaped plate, the U-shaped plate is rotatably sleeved on the fixed pipe, the fixed pipe is in threaded sleeved mode on the first screw, a first gear positioned above the U-shaped plate is fixedly sleeved on the fixed pipe, a first driving motor is fixedly arranged on the top of the U-shaped plate in a threaded mode, a second gear is fixedly arranged at, the fixing box is characterized in that the same U-shaped rod is slidably mounted between the inner walls of two sides of the fixing box, a T-shaped plate is fixedly mounted at the top of the fixing plate, a same second screw rod is rotatably mounted between the top of the T-shaped plate and the inner wall of the top of the fixing box, the U-shaped rod is in threaded sleeve connection with the second screw rod, a second driving motor is fixedly in threaded sleeve connection with the top of the fixing box, the end part of an output shaft of the second driving motor extends into the fixing box and is fixedly connected with the top end of the second screw rod, two L-shaped plates are arranged in the fixing box and are symmetrically arranged, a same transverse plate is fixedly mounted on the inner wall of one side, close to each other, of the two L-shaped plates, the T-shaped plate is slidably arranged on the two transverse plates, obliquely arranged connecting rods are hinged to the inner walls of, two first rectangular holes have been seted up at the top of fixed plate, fixed mounting has same backup pad between the both sides inner wall of first rectangular hole, the bottom of L shaped plate runs through corresponding first rectangular hole and extends to the below of fixed plate, the equal fixed mounting in one side that two L shaped plates are close to each other has arc splint, L shaped plate sliding sleeve establishes in the backup pad that corresponds, equal fixed mounting has a plurality of springs on the both sides inner wall of T shaped plate, the one end that the T shaped plate was kept away from to the spring is close to one side inner wall fixed connection of T shaped plate with the L shaped plate that corresponds.
Preferably, the top of the moving block is provided with a second rectangular hole, and the side wall of the second rectangular hole is in sliding connection with the outer side of the U-shaped plate.
Preferably, a circular hole is formed in the inner wall of the top of the U-shaped plate, a bearing is fixedly sleeved in the circular hole, and an inner ring of the bearing is fixedly sleeved on the outer side of the fixed pipe.
Preferably, the inner side of the fixed pipe is provided with an internal thread, the outer side of the first screw is provided with an external thread, and the internal thread is meshed with the external thread.
Preferably, a threaded hole is formed in the inner wall of the top of the U-shaped rod and is in threaded connection with the second screw rod.
Preferably, the inner walls of the two sides of the fixed box are provided with sliding grooves, the two sides of the U-shaped rod are fixedly provided with sliding blocks, and the sliding blocks are connected with the corresponding sliding grooves in a sliding mode.
Preferably, rectangular channels are formed in the two sides of the T-shaped plate, and the side walls of the rectangular channels are connected with the outer sides of the corresponding transverse plates in a sliding mode.
Compared with the prior art, the beneficial effects of the utility model are that:
by matching the U-shaped plate, the moving block, the fixed box, the U-shaped block, the first screw, the fixed tube, the first gear, the first driving motor, the second gear, the fixed plate, the U-shaped rod, the T-shaped plate, the second screw, the second driving motor, the L-shaped plate, the transverse plate, the connecting rod, the supporting plate, the arc-shaped clamping plates and the spring, the aircraft engine is placed between the two arc-shaped clamping plates, the second driving motor is reversely started to drive the second screw to rotate, the second screw rotates to drive the U-shaped rod to move upwards and extrude the two connecting rods, the connecting rods drive the corresponding L-shaped plate to move towards the direction close to the T-shaped plate and compress the spring, the L-shaped plate drives the corresponding arc-shaped clamping plates to move, the two arc-shaped clamping plates move towards the direction close to each other and clamp and fix the aircraft engine, when the aircraft engine needs to be lifted for inspection and maintenance, the second gear rotates to drive the first gear to rotate, the first gear rotates to drive the fixed pipe to rotate, the fixed pipe rotates to drive the first screw to move upwards, the first screw drives the fixed box to move upwards through the U-shaped block, and the fixed box drives the aircraft engine to move upwards, so that the aircraft engine is lifted conveniently and is convenient to check and maintain.
The utility model discloses simple structure, convenient operation is convenient for carry out the centre gripping according to actual automation to aircraft engine fixed, and is convenient for lift aircraft engine, and the inspection maintenance of being convenient for satisfies the use needs, is favorable to the use.
Drawings
Fig. 1 is a schematic structural view of a lifting device for maintaining an aircraft engine according to the present invention;
fig. 2 is a sectional view schematically showing the structure of the joint between the stationary box and the stationary plate of fig. 1.
In the figure: the device comprises a U-shaped plate 1, a moving block 2, a fixed box 3, a U-shaped block 4, a first screw rod 5, a fixed pipe 6, a first gear 7, a first driving motor 8, a second gear 9, a fixed plate 10, a U-shaped rod 11, a T-shaped plate 12, a second screw rod 13, a second driving motor 14, a L-shaped plate 15, a transverse plate 16, a connecting rod 17, a supporting plate 18, an arc-shaped clamping plate 19 and a spring 20.
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.
Referring to the attached drawings 1 and 2 in the specification, the lifting device for maintaining the aircraft engine comprises a U-shaped plate 1, wherein two moving blocks 2 are slidably sleeved on the U-shaped plate 1, one side, close to each other, of each moving block 2 is fixedly provided with a same fixed box 3 with an opening at the bottom, the top of each fixed box 3 is fixedly provided with a U-shaped block 4, the top of each U-shaped block 4 is fixedly provided with a first screw 5, the top end of each first screw 5 extends to the upper side of the U-shaped plate 1, a fixed pipe 6 is arranged above each U-shaped block 4, the top end of each fixed pipe 6 extends to the upper side of the U-shaped plate 1, the U-shaped plate 1 is rotatably sleeved on the fixed pipe 6, the fixed pipe 6 is sleeved on the first screws 5 in a threaded manner, a first gear 7 positioned above the U-shaped plate 1 is fixedly sleeved on the fixed pipe 6, a first driving motor 8 is fixedly arranged on the top of the U-shaped plate, the first gear 7 is engaged with the second gear 9, the bottom of the fixed box 3 is fixedly provided with a fixed plate 10, the two side inner walls of the fixed box 3 are slidably provided with a same U-shaped rod 11, the top of the fixed plate 10 is fixedly provided with a T-shaped plate 12, a same second screw 13 is rotatably arranged between the top of the T-shaped plate 12 and the top inner wall of the fixed box 3, the U-shaped rod 11 is in threaded sleeve connection with the second screw 13, the top of the fixed box 3 is in threaded fixed connection with a second driving motor 14, the end part of the output shaft of the second driving motor 14 extends into the fixed box 3 and is fixedly connected with the top end of the second screw 13, the fixed box 3 is internally provided with two L-shaped plates 15, the two L-shaped plates 15 are symmetrically arranged, the inner wall of one side of the two L-shaped plates 15 close to each other is fixedly provided with a same transverse plate 16, the T-shaped plate 12 is in, the two connecting rods 17 are symmetrically arranged, one end of each connecting rod 17 close to each other is hinged with the top of one side of each L-shaped plate 15 away from each other, two first rectangular holes are formed in the top of the fixed plate 10, the same supporting plate 18 is fixedly installed between the inner walls of the two sides of each first rectangular hole, the bottom of each L-shaped plate 15 penetrates through the corresponding first rectangular hole and extends to the lower part of the fixed plate 10, the arc-shaped clamping plate 19 is fixedly installed on one side of each L-shaped plate 15 close to each other, the L-shaped plates 15 are slidably sleeved on the corresponding supporting plates 18, a plurality of springs 20 are fixedly installed on the inner walls of the two sides of the T-shaped plate 12, one end of each spring 20 far away from the T-shaped plate 12 is fixedly connected with the inner wall of one side of the corresponding L-shaped plate 15 close to the T-shaped plate 12, the aircraft engine is convenient to clamp, the inspection and maintenance are convenient, the use requirement is met, and the use is facilitated.
In the utility model, the top of the moving block 2 is provided with a second rectangular hole, the side wall of the second rectangular hole is connected with the outside of the U-shaped plate 1 in a sliding way, the inner wall of the top of the U-shaped plate 1 is provided with a circular hole, the circular hole is internally and fixedly sleeved with a bearing, the inner ring of the bearing is fixedly sleeved with the outside of the fixed tube 6, the inside of the fixed tube 6 is provided with an internal thread, the outside of the first screw 5 is provided with an external thread, the internal thread is meshed with the external thread, the inner wall of the top of the U-shaped rod 11 is provided with a threaded hole, the threaded hole is in threaded connection with the second screw 13, the inner walls of the two sides of the fixed box 3 are both provided with chutes, the two sides of the U-shaped rod 11 are both fixedly provided with sliders, the sliders are in sliding connection with the corresponding chutes, the two sides of, be convenient for carry out the centre gripping according to actual automation to aircraft engine fixed, and be convenient for lift aircraft engine, be convenient for the inspection and maintenance, satisfy the operation needs, be favorable to using.
The working principle is as follows: when the aircraft engine fixing device is used, the aircraft engine is placed between the two arc-shaped clamping plates 19, when the aircraft engine needs to be fixed, the second driving motor 14 is started reversely, the second driving motor 14 works to drive the second screw 13 to rotate, under the action of a threaded hole formed in the U-shaped rod 11, the second screw 13 rotates to drive the U-shaped rod 11 to move upwards, the U-shaped rod 11 drives the sliding block to slide in the corresponding sliding groove, the U-shaped rod 11 extrudes the two connecting rods 17 in the upward moving process, under the action of the extrusion force, the connecting rods 17 move and rotate, the connecting rods 17 drive the corresponding L-shaped plates 15 to move towards the direction close to the T-shaped plates 12, the L-shaped plates 15 drive the corresponding transverse plates 16 to slide in the rectangular grooves, the L-shaped plates 15 compress the corresponding springs 20 in the moving process, the L-shaped plates 15 slide on the corresponding supporting plates 18, and the L-shaped plates 15 drive the corresponding, the two arc-shaped clamping plates 19 move towards the direction close to each other and clamp and fix the aircraft engine, and at the moment, under the action of self-thread locking damping force between the second screw 13 and the U-shaped rod 11, the self-thread locking force of a common thread piece is equivalent to self-thread locking force of a common thread piece, so that the two arc-shaped clamping plates 19 are fixed, and the aircraft engine is fixed between the two arc-shaped clamping plates 19;
when the aircraft engine needs to be lifted for inspection and maintenance, the first driving motor 8 is started in the forward direction, the first driving motor 8 works to drive the second gear 9 to rotate, under the meshing effect of the first gear 7 and the second gear 9, the second gear 9 rotates to drive the first gear 7 to rotate, the first gear 7 rotates to drive the fixed pipe 6 to rotate, under the threaded connection effect of the fixed pipe 6 and the first screw 5, the fixed pipe 6 rotates to drive the first screw 5 to move upwards, the first screw 5 drives the U-shaped block 4 to move upwards, the U-shaped block 4 drives the fixed box 3 to move upwards, the fixed box 3 drives the aircraft engine to move upwards, the aircraft engine is convenient to lift, and the inspection and maintenance are convenient.
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 (7)
1. The lifting device for maintaining the aircraft engine comprises a U-shaped plate (1) and is characterized in that two moving blocks (2) are slidably sleeved on the U-shaped plate (1), one side, close to each other, of each moving block (2) is fixedly provided with a fixed box (3) with the same bottom arranged as an opening, the top of each fixed box (3) is fixedly provided with a U-shaped block (4), the top of each U-shaped block (4) is fixedly provided with a first screw (5), the top end of each first screw (5) extends to the upper side of the U-shaped plate (1), a fixed pipe (6) is arranged above the U-shaped block (4), the top end of each fixed pipe (6) extends to the upper side of the U-shaped plate (1), the U-shaped plate (1) is rotatably sleeved on the fixed pipe (6), the fixed pipe (6) is sleeved on the first screw (5) in a threaded manner, a first gear (7) positioned above the U-shaped plate (1, the top thread of the U-shaped plate (1) is fixed with a first driving motor (8), the end part of an output shaft of the first driving motor (8) is fixedly provided with a second gear (9), a first gear (7) is meshed with the second gear (9), the bottom of the fixed box (3) is fixedly provided with a fixed plate (10), a same U-shaped rod (11) is slidably arranged between the inner walls of the two sides of the fixed box (3), the top of the fixed plate (10) is fixedly provided with a T-shaped plate (12), a same second screw rod (13) is rotatably arranged between the top of the T-shaped plate (12) and the inner wall of the top of the fixed box (3), the U-shaped rod (11) is sleeved on the second screw rod (13) in a threaded manner, the top thread of the fixed box (3) is fixed with a second driving motor (14), the end part of the output shaft of the second driving motor (14) extends into the fixed box (3) and is fixedly connected, two L-shaped plates (15) are arranged in the fixed box (3), the two L-shaped plates (15) are symmetrically arranged, the inner wall of one side, close to each other, of the two L-shaped plates (15) is fixedly provided with a same transverse plate (16), the T-shaped plate (12) is sleeved on the two transverse plates (16) in a sliding manner, the inner walls of two sides of the U-shaped rod (11) are hinged with connecting rods (17) which are obliquely arranged, the two connecting rods (17) are symmetrically arranged, one ends, close to each other, of the two connecting rods (17) are hinged with the top of one side, far away from each other, of the two L-shaped plates (15), two first rectangular holes are formed in the top of the fixed plate (10), the same supporting plate (18) is fixedly arranged between the inner walls of two sides of each first rectangular hole, the bottom of each L-shaped plate (15) penetrates through the corresponding first rectangular hole and extends to the lower, l shaped plate (15) slip cover establish on corresponding backup pad (18), all fixed mounting has a plurality of springs (20) on the both sides inner wall of T shaped plate (12), and the one end that T shaped plate (12) were kept away from in spring (20) is close to one side inner wall fixed connection of T shaped plate (12) with L shaped plate (15) that corresponds.
2. The lifting device for maintaining the aircraft engine as claimed in claim 1, wherein a second rectangular hole is formed at the top of the moving block (2), and the side wall of the second rectangular hole is slidably connected with the outer side of the U-shaped plate (1).
3. The lifting device for maintaining the aircraft engine as claimed in claim 1, wherein a circular hole is formed in the inner wall of the top of the U-shaped plate (1), a bearing is fixedly sleeved in the circular hole, and an inner ring of the bearing is fixedly sleeved with the outer side of the fixed pipe (6).
4. The lifting device for aircraft engine maintenance according to claim 1, characterized in that the inner side of the fixed pipe (6) is provided with an internal thread, the outer side of the first screw (5) is provided with an external thread, and the internal thread is engaged with the external thread.
5. The lifting device for aircraft engine maintenance according to claim 1, characterized in that a threaded hole is provided on the top inner wall of the U-shaped rod (11), and the threaded hole is in threaded connection with the second screw (13).
6. The lifting device for maintaining the aircraft engine as claimed in claim 1, wherein sliding grooves are formed in the inner walls of the two sides of the fixed box (3), sliding blocks are fixedly mounted on the two sides of the U-shaped rod (11), and the sliding blocks are slidably connected with the corresponding sliding grooves.
7. The lifting device for maintaining the aircraft engine as claimed in claim 1, wherein rectangular grooves are formed in both sides of the T-shaped plate (12), and the side walls of the rectangular grooves are slidably connected with the outer sides of the corresponding transverse plates (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922488975.4U CN212024654U (en) | 2019-12-30 | 2019-12-30 | Lifting device for aircraft engine maintenance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922488975.4U CN212024654U (en) | 2019-12-30 | 2019-12-30 | Lifting device for aircraft engine maintenance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212024654U true CN212024654U (en) | 2020-11-27 |
Family
ID=73483369
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922488975.4U Active CN212024654U (en) | 2019-12-30 | 2019-12-30 | Lifting device for aircraft engine maintenance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212024654U (en) |
-
2019
- 2019-12-30 CN CN201922488975.4U patent/CN212024654U/en active Active
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