CN211167473U - Aircraft rudder transportation upset installation car - Google Patents
Aircraft rudder transportation upset installation car Download PDFInfo
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- CN211167473U CN211167473U CN201921798022.1U CN201921798022U CN211167473U CN 211167473 U CN211167473 U CN 211167473U CN 201921798022 U CN201921798022 U CN 201921798022U CN 211167473 U CN211167473 U CN 211167473U
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Abstract
The utility model discloses an aircraft rudder transportation overturning installation vehicle, which comprises a transportation frame, wherein the top of the transportation frame is provided with an overturning plate, and the two ends of the bottom of the overturning plate are respectively connected with the top of the transportation frame through a lifting adjusting device; the top of the turning plate is provided with a placing frame; the left side and the right side of the placement frame are symmetrically provided with placement grooves, and the front side and the rear side of the placement frame are symmetrically provided with supporting devices; the utility model discloses have firm aircraft rudder, the nimble aircraft rudder that overturns, prevent the landing of aircraft rudder, greatly alleviate the beneficial effect of artifical burden.
Description
Technical Field
The utility model belongs to the technical field of aircraft spare part conveyer, concretely relates to aircraft rudder transportation upset installation car.
Background
The airplane rudder is an important component for controlling the flight direction of an airplane, the airplane rudder is assembled by a delivery part in a part workshop at a production site, the grader rudder is generally horizontally placed on a transport vehicle which is designed independently, the airplane rudder is transported to a specified place which is combined with the vertical tail of the airplane through the transport vehicle, then the airplane rudder is manually matched with the vertical tail of the airplane through physical force, the heavy airplane rudder is unloaded from the transport vehicle, the airplane rudder is manually raised to the height of 1 meter to be combined and installed with the vertical tail of the airplane, the combining direction of the airplane rudder and the vertical tail is judged through manual visual observation in the installation process, and the combined and installed operation can be completed through repeated trial overturning. The whole involution process lasts for more than 10 minutes, so the requirement on the physical strength of an operator at the bottom of the rudder of the airplane is high. Meanwhile, the bottom of the aircraft rudder is of a prismatic structure, the shoulder of an operator is easy to cause shoulder injury under long-time friction bearing, and the risk that the aircraft rudder is easy to slip off exists in the installation process, so that the product quality is damaged and the economic loss is serious. Therefore, it is necessary to develop a set of transportation tools for airplane rudder transportation and turning adjustment to replace manual transportation.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aircraft rudder transportation upset installation car realizes convenient transportation aircraft rudder to nimble convenient rotation angle's of adjusting aircraft rudder function when installing the aircraft rudder.
The utility model discloses a following technical scheme realizes:
the aircraft rudder transporting and overturning installation vehicle comprises a transporting frame, wherein a turning plate is arranged at the top of the transporting frame, and two ends of the bottom of the turning plate are respectively connected with the top of the transporting frame through a lifting adjusting device; the top of the turning plate is provided with a placing frame; the left side and the right side of the placement frame are symmetrically provided with placement grooves, and the front side and the rear side of the placement frame are symmetrically provided with supporting and fixing devices.
The working principle is as follows:
the four corners department of the bottom of transportation frame is provided with the gyro wheel for remove the part that the transportation is located the transportation frame, the top of transportation frame is provided with turns over the board, and turns over and be connected through lift adjusting device between both sides around the board bottom and the front and back both sides at transportation frame top respectively, lift adjusting device can drive and turn over the board and go up and down and the upset of certain angle, turns over the board angle and the direction that the board goes on overturning and pass through lift adjusting device regulation control. When the aircraft rudder transports to the installation station, carry out the altitude mixture control of aircraft rudder through the lift of lift adjusting device, simultaneously through the lift adjusting device's of both sides around adjusting lift order and difference in height, the upset that the board carries out certain angle is turned over in the drive, and then the aircraft rudder that the board top was turned over in the drive carries out the upset of certain angle, the junction that makes the aircraft rudder and the aircraft vertical tail's junction aligns, avoided artifical manual regulation aircraft rudder inclination, it is more convenient laborsaving.
The top of turning over the board is provided with the arrangement frame, settles adjacent left and right sides symmetry and is provided with the standing groove, and the interior profile of standing groove corresponds the outline setting of aircraft rudder, through putting into the standing groove with the aircraft rudder, can realize the support and the fixed to the aircraft rudder. Meanwhile, in order to avoid the airplane rudder from sliding in the placing groove, the front side and the rear side of the placing frame are symmetrically provided with the supporting and fixing devices, the positions of the supporting and fixing devices correspond to the positions of the fixing and fixing parts on the airplane rudder, the supporting and fixing devices are connected with the fixing and fixing parts on the airplane rudder, the airplane rudder is completely fixed, and the airplane rudder is effectively prevented from shaking or sliding in the transportation process.
In order to better realize the utility model discloses, furtherly, prop up solid device and include the support column and insert the ear, the support column symmetry sets up the upper portion in the front and back both sides of rack, insert the lower part that the ear symmetry set up both sides around the rack.
The support columns are symmetrically arranged at the upper parts of the front side and the rear side of the placement frame, the length of each support column is slightly smaller than the distance from the outer surface of the aircraft rudder to the side surface of the top of the placement frame, one end of each support column is connected with the side surface of the upper part of the placement frame, the other end of each support column extends towards the aircraft rudder and is in contact with the outer surface of the upper part of the aircraft rudder, and the support columns symmetrically arranged at the front side and the rear side support and fix the upper part of the aircraft rudder to realize the fixation of the upper part of the; the inserting lugs are symmetrically arranged at the lower parts of the front side and the rear side of the placing frame, the length of the inserting lugs is equal to the distance from the central line of the intersection point hole of the support arm of the aircraft rudder to the side surface of the bottom of the placing frame, and the inserting lugs are connected with the intersection point hole of the support arm through bolts to fix the lower part of the aircraft rudder.
In order to better realize the utility model, furthermore, upper side laths are respectively arranged between the left side and the right side of the top of the placing frame, and lower side laths are respectively arranged between the left side and the right side of the bottom of the placing frame; the installation side of going up the side slat is provided with the support column, be provided with on the installation side of lower side slat and insert the ear.
The upper edge lath, the lower edge lath and the placing frame form a frame structure, the support of the aircraft rudder is more stable, the installation side of the upper edge lath is used for installing the support column, and the installation side of the lower edge lath is used for installing the insert lug.
In order to better realize the utility model discloses, furtherly, it is linear on the installation side of slat to be provided with two sets of support columns, it is linear on the installation side of lower slat to be provided with two sets of ears of inserting.
The two groups of support columns positioned on the installation sides of the upper edge strip plates linearly support the outer surface of the upper part of the aircraft rudder, and the point support is more stable compared with the point support by arranging a single support column; in a similar way, two sets of inserting lugs on the installation side of the same lower edge strip plate linearly support the lower part of the aircraft rudder, and the lower part is more stable than point support by arranging a single inserting lug.
In order to better realize the utility model discloses, furtherly, the support column includes spliced pole and backup pad, the one end of spliced pole is connected with the installation side of last slat, and the other end of spliced pole is connected with one side of backup pad.
The spliced pole is used for connecting the side of last slat installation side and backup pad, and the backup pad corresponds the inclination setting of the surface of aircraft rudder, guarantees promptly that the backup pad is close to the terminal surface of aircraft rudder and the inclination of the surface of aircraft rudder is unanimous, and then guarantees that the backup pad can closely laminate with the surface contact of aircraft rudder as far as possible, prevents that the aircraft rudder from taking place to rock in the transportation.
For better realization the utility model discloses, further, the top of transportation frame is the rectangular array and is provided with four lift adjustment device.
The top of transportation frame is rectangular array and is provided with four lift adjustment device, sets up two lift adjustment device settings with one side in transportation frame top and turning over the board bottom promptly, makes to turn over the board and goes up and down to become linear lift by punctiform lift with the lift of one side, makes the upset regulation of turning over the board more stable.
In order to better realize the utility model discloses, furtherly, lifting adjusting device is hydraulic pressure lift post.
For better realization the utility model discloses, further, the standing groove is the V-arrangement groove.
Compared with the prior art, the utility model, following advantage and beneficial effect have:
(1) the utility model discloses a set up the lift adjusting device respectively between the front and back both sides at the transport frame top and the front and back both sides of turning over the board bottom to realize adjusting the difference in height of turning over the board both sides through the lift of lift adjusting device, and then realize driving and turn over the board and carry out the upset of certain angle, finally realize driving and turn over the fixed aircraft rudder of board and carry out the upset of certain angle; the utility model has the advantages of flexible turning of the airplane rudder and great reduction of the manual burden;
(2) the utility model realizes the supporting and positioning of the airplane rudder by arranging the placing frame at the top of the turning plate and symmetrically arranging the placing grooves at the left side and the right side of the placing frame, wherein the placing grooves are arranged corresponding to the outline of the airplane rudder; the utility model has the beneficial effect of stable support of the airplane rudder;
(3) the utility model arranges the upper side plate between the left and right sides of the top of the placing groove, the lower side plate between the left and right sides of the bottom of the placing groove, the support column is arranged on the installation side of the upper side plate, the inserting lug is arranged on the installation side of the lower side plate, and the top and the bottom of the airplane rudder are respectively fixed through the support column and the inserting lug; the utility model discloses have firm fixed aircraft rudder, prevent the beneficial effect of aircraft rudder landing.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic view of the installation of the lift adjustment assembly;
FIG. 3 is a schematic view of the installation of the side strip and the support member.
Wherein: 01-placing rack; 02-placing a groove; 21-upper side lath; 22-lower side lath; 31-a support column; 32-inserting ears; 3-a supporting and fixing device; 4-turning over the board; 5-a transportation frame; 6-a lifting adjusting device; 311-connecting column; 312-support plate.
Detailed Description
Example 1:
the aircraft rudder transportation overturning installation vehicle comprises a transportation frame 5, wherein a turning plate 4 is arranged at the top of the transportation frame 5, and two ends of the bottom of the turning plate 4 are respectively connected with the top of the transportation frame 5 through a lifting adjusting device 6, as shown in fig. 1 and 2; the top of the turning plate 4 is provided with a placing frame 01; the left side and the right side of the placing frame 01 are symmetrically provided with placing grooves 02, and the front side and the rear side of the placing frame 01 are symmetrically provided with supporting devices 3.
The four corners of the bottom of the transport frame 5 are provided with rollers, and the transport frame 5 is used for rapidly transporting the parts carried above the transport frame. The top of the transportation frame 5 is provided with a turning plate 4, a lifting adjusting device 6 is respectively arranged between the two ends of the bottom of the turning plate 4 and the top of the transportation frame 5, and the lifting and overturning of the turning plate 4 are adjusted through the lifting control of the lifting adjusting devices 6 at the two ends.
When the lifting adjusting devices 6 at the two ends lift synchronously, the two sides of the turning plate 4 are driven to lift synchronously, and at the moment, the turning plate 4 only lifts in the vertical direction. When the lifting adjusting devices 6 at the two ends are lifted at different parts, the two ends of the turning plate 4 are driven to lift asynchronously, the two sides of the turning plate 4 are subjected to height difference, and then the turning plate 4 is driven to turn over at a certain angle. The overturning angle of the turning plate 4 is controlled by adjusting the lifting height difference of the lifting adjusting devices 6 at the two ends, and the larger the lifting height difference between the lifting adjusting devices 6 at the two ends is, the larger the height difference at the two sides of the turning plate 4 is, and the larger the overturning angle of the turning plate 4 is; conversely, the smaller the lifting height difference between the lifting adjusting devices 6 at the two ends is, the smaller the height difference between the two sides of the turning plate 4 is, and the smaller the turning angle of the turning plate 4 is.
The turning angle of the turning plate 4 is controlled by adjusting the lifting sequence of the lifting adjusting devices 6 at the two sides, if the lifting adjusting device 6 at one side of the turning plate 4 is raised and the lifting adjusting device 6 at the other side is lowered, the turning plate 4 turns towards the lowering side.
The top of turning over board 4 is provided with arrangement frame 01, the symmetry is provided with standing groove 02 on arrangement frame 01's the left and right sides, the interior profile of standing groove 02 corresponds the outline setting of aircraft rudder, directly put into arrangement frame 01's the standing groove 02 of the left and right sides with the aircraft rudder, the interior profile of standing groove 02 and the outline laminating of aircraft rudder this moment, the realization is to the support of aircraft rudder, simultaneously in order to avoid the internal surface fish tail aircraft rudder of standing groove 02, consequently, be provided with flexible material layers such as felt on arrangement groove 02's the internal surface. Meanwhile, the front side and the rear side of the placing frame 01 are symmetrically provided with the supporting and fixing devices 3, and the supporting and fixing devices 3 are supported or connected with the connecting parts on the aircraft rudder to completely fix the aircraft rudder.
Example 2:
the embodiment is further optimized on the basis of embodiment 1, as shown in fig. 1, the supporting device 3 includes supporting columns 31 and inserting lugs 32, the supporting columns 31 are symmetrically disposed on the upper portions of the front and rear sides of the placement frame 01, and the inserting lugs 32 are symmetrically disposed on the lower portions of the front and rear sides of the placement frame 01.
The supporting columns 31 are arranged at the upper parts of the front side and the rear side of the placing frame 01, the length of each supporting column 31 is slightly smaller than the distance from the outer surface of the aircraft rudder to the side surface of the upper part of the placing frame 01, and the end, close to the aircraft rudder, of each supporting column 31 is in contact with the outer surface of the aircraft rudder and used for assisting in supporting and fixing the upper part of the aircraft rudder; the inserting lugs 32 are arranged at the lower parts of the front side and the rear side of the mounting frame 01, the length of the inserting lugs 32 is equal to the distance from the center line of the intersection point hole of the aircraft rudder support arm to the side surface of the lower part of the mounting frame 01, and the inserting lugs 32 are connected with the intersection point hole of the support arm through bolts to fix the lower part of the aircraft rudder.
Other parts of this embodiment are the same as embodiment 1, and thus are not described again.
Example 3:
the present embodiment is further optimized on the basis of the above embodiment 1 or 2, as shown in fig. 3, upper laths 21 are respectively disposed between the left and right sides of the top of the placement frame 01, and lower laths 22 are respectively disposed between the left and right sides of the bottom of the placement frame 01; a support column 31 is provided on the mounting side of the upper slat 21, and an insert lug 32 is provided on the mounting side of the lower slat 22.
The installation side of the upper side lath 21 refers to the side of the upper side lath 21 close to the rudder of the airplane; the mounting side of the rocker panel 22 refers to the side of the rocker panel 22 that is adjacent to the rudder of the aircraft.
An upper baffle plate 21 is respectively arranged between the left side and the right side of the top of the placing frame 01, two ends of the upper baffle plate 21 are respectively in threaded connection with the side surface of the top of the placing frame 01 through screws, and a supporting column 31 is arranged on the mounting side of the upper baffle plate 21.
The upper baffle plate 21, the lower baffle plate 22 and the mounting frame 01 form a frame supporting structure, and the support for the rudder of the airplane is more stable.
The rest of this embodiment is the same as embodiment 1 or 2, and therefore, the description thereof is omitted.
Example 4:
this embodiment is further optimized on the basis of any of the above embodiments 1 to 3, wherein two sets of support posts 31 are linearly arranged on the mounting side of the upper slat 21, and two sets of insert lugs 32 are linearly arranged on the mounting side of the lower slat 22.
Be linear two support columns 31 that set up on the installation side of slat 21 on the left, be linear two support columns 31 that set up on the installation side of slat 21 on the right side, two support columns 31 on the installation side of slat 21 on the same root carry out linear support to the surface of aircraft rudder, compare and support more firmly in the single point.
Similarly, be two insert ears 32 that are linear setting on the side that left lower side slat 22 is close to standing groove 02, be two insert ears 32 that are linear setting on the installation side of lower side slat 22 on the right side, two insert ears 32 on the installation side of same lower side slat 22 carry out linear support to the bottom of aircraft rudder, compare in single-point support more firm.
The number of the supporting columns 31 and the inserting lugs 32 is not limited to two, and the number and the arrangement positions of the supporting columns 31 and the inserting lugs 32 can be correspondingly arranged according to the lengths and the connecting parts of the airplane rudders with different specifications.
Other parts of this embodiment are the same as any of embodiments 1 to 3, and thus are not described again.
Example 5:
this embodiment is further optimized on the basis of any one of the above embodiments 1 to 4, as shown in fig. 3, the supporting column 31 includes a connecting column 311 and a supporting plate 312, one end of the connecting column 311 is connected to the mounting side of the upper side lath 21, and the other end of the connecting column 311 is connected to one side of the supporting plate 312.
The spliced pole 311 is used for connecting the side of the installation side of last slat 21 and backup pad 312, and backup pad 312 corresponds the inclination setting of the surface of aircraft rudder, guarantees promptly that backup pad 312 is close to the terminal surface of aircraft rudder and the inclination of the surface of aircraft rudder is unanimous, and then guarantees that backup pad 312 can closely laminate with the surface contact of aircraft rudder as far as possible, prevents that the aircraft rudder from taking place to rock in the transportation.
Meanwhile, in order to prevent the end surface of the support plate 312 from scratching the outer surface of the aircraft rudder, a flexible material layer such as felt is provided on the end surface of the support plate 312 close to the aircraft rudder.
Other parts of this embodiment are the same as any of embodiments 1 to 4, and thus are not described again.
Example 6:
this embodiment is further optimized on the basis of any one of the above embodiments 1 to 5, and as shown in fig. 2, four lifting adjusting devices 6 are arranged on the top of the transportation frame 5 in a rectangular array.
Two lifting adjusting devices 6 are linearly arranged between the front end of the bottom of the turnover plate 4 and the top of the transportation frame 5, and two lifting adjusting devices 6 are linearly arranged between the rear end of the bottom of the turnover plate 4 and the top of the transportation frame 5.
Compare in only carrying out the one end that turns over board 4 through a lift adjusting device 6 and carry out single-point lift adjustment, it is more stable to carry out synchronous linear lift adjustment to the one end that turns over board 4 between two sets of lift adjusting device 6 of same end.
The number of the lifting adjusting devices 6 arranged between the top of the transport frame 5 and the same end of the bottom of the turning plate 4 is not limited to two groups, and the lifting adjusting devices can be correspondingly arranged according to the actually loaded component weight.
Other parts of this embodiment are the same as any of embodiments 1 to 5, and thus are not described again.
Example 7:
this embodiment is further optimized on the basis of any one of the embodiments 1 to 6, and the lifting adjusting device 6 is a hydraulic lifting column.
The reason why the ascent and descent adjusting device 6 is provided as the hydraulic ascent and descent adjusting device 6 is heavy in weight of the aircraft rudder, and the hydraulic ascent and descent column has a large bearing capacity and can stably bear and turn over the aircraft rudder.
Other parts of this embodiment are the same as any of embodiments 1 to 6, and thus are not described again.
Example 8:
this embodiment is further optimized on the basis of any one of the above embodiments 1 to 7, and the placement grooves 02 are V-shaped grooves.
Other parts of this embodiment are the same as any of embodiments 1 to 7, and thus are not described again.
The above is only the preferred embodiment of the present invention, not to the limitation of the present invention in any form, all the technical matters of the present invention all fall into the protection scope of the present invention to any simple modification and equivalent change of the above embodiments.
Claims (8)
1. The aircraft rudder transport overturning installation vehicle comprises a transport frame (5), and is characterized in that a turning plate (4) is arranged at the top of the transport frame (5), and two ends of the bottom of the turning plate (4) are respectively connected with the top of the transport frame (5) through a lifting adjusting device (6); the top of the turning plate (4) is provided with a placing frame (01); the left side and the right side of the placement frame (01) are symmetrically provided with placement grooves (02), and the front side and the rear side of the placement frame (01) are symmetrically provided with supporting devices (3).
2. An aircraft rudder transporting and overturning installation vehicle as claimed in claim 1, wherein the supporting device (3) comprises supporting columns (31) and inserting lugs (32), the supporting columns (31) are symmetrically arranged at the upper parts of the front side and the rear side of the mounting frame (01), and the inserting lugs (32) are symmetrically arranged at the lower parts of the front side and the rear side of the mounting frame (01).
3. The aircraft rudder transporting and overturning installation vehicle as claimed in claim 2, wherein upper side slats (21) are respectively arranged between the left side and the right side of the top of the placement frame (01), and lower side slats (22) are respectively arranged between the left side and the right side of the bottom of the placement frame (01); the installation side of going up side lath (21) is provided with support column (31), be provided with on the installation side of lower side lath (22) and insert ear (32).
4. An aircraft rudder transportation and overturning installation vehicle according to claim 3, characterized in that two sets of support columns (31) are linearly arranged on the installation side of the upper side strip plate (21) and two sets of insertion lugs (32) are arranged on the installation side of the lower side strip plate (22).
5. An aircraft rudder transportation and overturning installation vehicle according to claim 4, characterized in that the supporting column (31) comprises a connecting column (311) and a supporting plate (312), one end of the connecting column (311) is connected with the installation side of the upper side lath (21), and the other end of the connecting column (311) is connected with one side of the supporting plate (312).
6. An aircraft rudder transportation and overturning installation vehicle according to any one of claims 1 to 5, characterised in that the top of the transportation frame (5) is provided with four ascent and descent control devices (6) in a rectangular array.
7. An aircraft rudder transportation and overturning installation vehicle according to claim 6, characterised in that said lifting and lowering adjustment means (6) are hydraulic lifting columns.
8. An aircraft rudder transportation and overturning installation vehicle according to claim 1, characterised in that said placement groove (02) is a V-shaped groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921798022.1U CN211167473U (en) | 2019-10-24 | 2019-10-24 | Aircraft rudder transportation upset installation car |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921798022.1U CN211167473U (en) | 2019-10-24 | 2019-10-24 | Aircraft rudder transportation upset installation car |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211167473U true CN211167473U (en) | 2020-08-04 |
Family
ID=71807911
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921798022.1U Active CN211167473U (en) | 2019-10-24 | 2019-10-24 | Aircraft rudder transportation upset installation car |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211167473U (en) |
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2019
- 2019-10-24 CN CN201921798022.1U patent/CN211167473U/en active Active
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