CN216512343U - Whole wing lifts by crane fixing device - Google Patents
Whole wing lifts by crane fixing device Download PDFInfo
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- CN216512343U CN216512343U CN202122511388.XU CN202122511388U CN216512343U CN 216512343 U CN216512343 U CN 216512343U CN 202122511388 U CN202122511388 U CN 202122511388U CN 216512343 U CN216512343 U CN 216512343U
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- fixing device
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- engine
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Abstract
The utility model discloses a hoisting and fixing device for an integral wing. The wing flap suspension system comprises a front lifting beam (2) used for lifting the position of an engine connecting fork lug (8) of an engine hanger (7) on a wing (6), and a rear lifting beam (4) used for lifting the position of a flap suspension arm intersection point (9) on the wing (6); two ends of the front lifting beam (2) are connected with the engine hanger switching components (1) through slings (5), and the two engine hanger switching components (1) are respectively and correspondingly connected with an engine connecting fork lug (8); the two ends of the rear lifting beam (4) are connected with the flap suspension support arm switching components (3) through slings (5), and the two flap suspension support arm switching components (3) are correspondingly connected with a flap suspension support arm intersection point (9) respectively. The utility model has the characteristics of simple design, relatively light weight and low requirement on a crane.
Description
Technical Field
The utility model relates to the technical field of aircraft wing lifting, in particular to an integral wing lifting and fixing device.
Background
At present, the wings of the airplane are hoisted in the process of manufacturing the airplane at home and abroad. In the large turboprop currently researched or produced in batches, the wings of the large turboprop are generally divided into five sections, namely a central wing, a left middle outer wing, a left outer wing, a right middle outer wing and a right outer wing, or three sections, namely the central wing, the right outer wing and the left outer wing, and only a single section is required to be lifted according to the assembly sequence without lifting the whole wings; in the process of lifting the integral wing of a large-scale turbojet airplane in a grinding or batch production process, lifting points are generally designed on the front and rear beams of the wing, or an integral lifting appliance is designed to wrap the wing for lifting, and the lifting appliance is high in design complexity, heavy in weight and high in requirement on a crane.
SUMMERY OF THE UTILITY MODEL
The purpose of the utility model is: a hoisting and fixing device for the integral wing is provided. The utility model has the characteristics of simple design, relatively light weight and low requirement on a crane.
The technical scheme of the utility model is as follows: a hoisting and fixing device for an integral wing comprises a front hoisting beam used for hoisting the position of an engine connecting fork lug of an engine hanger on the wing, and a rear hoisting beam used for hoisting the position of a flap suspension support arm intersection point on the wing; two ends of the front lifting beam are connected with the engine hanger switching assemblies through slings, and the two engine hanger switching assemblies are respectively and correspondingly connected with an engine connecting fork lug; the two ends of the rear lifting beam are connected with the flap suspension support arm switching components through slings, and the two flap suspension support arm switching components are respectively and correspondingly connected with a flap suspension support arm intersection point.
In the integral wing lifting and fixing device, the engine hanger switching assembly comprises the supporting shaft, the middle section of the supporting shaft is provided with the lifting hook, and the two ends of the supporting shaft are respectively extended with the step shaft with the diameter smaller than that of the middle section of the supporting shaft.
In the above-mentioned integrated wing lifting fixing device, the shoulder bushes are sleeved on the two step shafts, and the two shoulder bushes are fixed on the step shafts through fastening bolts.
In the above-mentioned integrated wing hoisting fixing device, the shoulders of the two shoulder bushes are arranged oppositely.
In the integrated wing lifting and fixing device, the flap suspension support arm switching assembly comprises a U-shaped piece, through holes are formed in the open end of the U-shaped piece and connected through supporting bolts, and the end parts of the supporting bolts are connected with fastening nuts after penetrating through the through holes.
In the above-mentioned integrated wing lifting and fixing device, the closed end of the U-shaped member is a straight beam structure, and an included angle θ between the straight beam and the axis of the supporting bolt is 3.28 °.
In the integrated wing lifting and fixing device, the through hole is internally provided with a support bushing, and the two support bushings are penetrated by the support bolt.
The utility model has the advantages that: the utility model can complete the lifting of the integral wing of the large-scale turboprop by taking the intersection point of the engine connecting fork lug and the flap hanging support arm of the engine hanging rack of the airplane wing as the lifting point of the integral wing, has simple operation, can ensure that the wing is in a horizontal posture in the lifting process, has simple design, relatively lighter weight and low requirement on a crane.
Drawings
FIG. 1 is a state diagram of the use of the present invention;
FIG. 2 is a schematic structural view of the present invention;
FIG. 3 is a schematic illustration of the engine pylon adapter assembly;
FIG. 4 is a schematic view of a flap suspension arm adapter assembly.
Reference numerals: 1-engine pylon adapter assembly, 2-front lifting beam, 3-flap suspension arm adapter assembly, 4-rear lifting beam, 5-sling, 6-wing, 7-engine pylon, 8-engine connecting fork ear, 9-flap suspension arm intersection point, 10-support shaft, 11-lifting hook, 12-shoulder bush, 13-fastening bolt, 14-U-shaped piece, 15-support bolt, 16-fastening nut and 17-support bush.
Detailed Description
The utility model is further illustrated by the following figures and examples, which are not to be construed as limiting the utility model.
Example 1. A lifting and fixing device for an integral wing is formed as shown in figures 1-4 and comprises a front lifting beam 2 used for lifting an engine connecting fork ear 8 of an engine hanger 7 on a wing 6 and a rear lifting beam 4 used for lifting a flap hanging arm intersection point 9 on the wing 6; two ends of the front lifting beam 2 are connected with the engine hanger switching assemblies 1 through slings 5, and the two engine hanger switching assemblies 1 are correspondingly connected with an engine connecting fork lug 8 respectively; the two ends of the rear lifting beam 4 are connected with the flap suspension support arm switching components 3 through slings 5, and the two flap suspension support arm switching components 3 are respectively and correspondingly connected with a flap suspension support arm intersection point 9.
The engine pylon adapter assembly 1 comprises a support shaft 10, a lifting hook 11 is arranged at the middle section of the support shaft 10, and step shafts with diameters smaller than that of the middle section of the support shaft 10 are respectively extended from the two ends of the support shaft 10.
And the two step shafts are sleeved with shoulder bushes 12, and the two shoulder bushes 12 are fixed on the step shafts through fastening bolts 13.
The shoulders of the two shoulder bushes 12 are arranged opposite each other.
The flap suspension arm adapter assembly 3 comprises a U-shaped part 14, through holes are formed in the open ends of the U-shaped part 14, the two through holes are connected through a support bolt 15, and the end of the support bolt 15 is connected with a fastening nut 16 after penetrating through the through holes.
The closed end of the U-shaped member 14 is a straight beam structure, and the included angle θ between the straight beam and the axis of the supporting bolt 15 is 3.28 °.
The through hole is also provided with a support bush 17, and the two support bushes 17 are penetrated by the support bolt 15.
Example 2. A lifting and fixing device for an integral wing is shown in figures 1-4 and comprises an engine hanger adapter assembly 1, a front lifting beam 2, a flap suspension support arm adapter assembly 3, a rear lifting beam 4 and a sling 5; the engine pylon adapter assembly 1 is mounted on an aircraft engine pylon 7; the flap suspension support arm adapter component 3 is arranged on the flap suspension support arm intersection point 9; two ends of the front lifting beam 2 are connected with the engine hanger adapter assembly 1 through slings 5, and the middle part of the front lifting beam is connected with a crane hook; and two ends of the rear lifting beam 4 are connected with the flap suspension support arm switching assembly 3 through slings 5, and the middle part of the rear lifting beam is connected with a crane hook.
Further, the engine pylon adapter assembly consists of a support shaft, a bolt and a bushing; the bolt penetrates through the bushing and an engine connecting fork lug on the engine hanger to be connected with the supporting shaft; the supporting shaft is provided with a lifting hook for connecting a sling; the support shaft can support the engine to connect the fork lug in the hoisting process, and the change of the distance between the two lug plates of the fork lug is prevented.
Further, the flap suspension arm adapter assembly 3 is composed of a U-shaped member, a bolt, a nut and a bushing, wherein the U-shaped member is connected to the intersection point of the flap suspension arm by the bolt, the bushing and the nut.
Example 3. A lifting and fixing device for an integral wing comprises an engine pylon adapter assembly 1, a front lifting beam 2, a flap suspension support arm adapter assembly 3, a rear lifting beam 4 and a sling 5, which are shown in figures 1-4. The engine pylon adapter assembly 1 comprises a support shaft, a bolt, a nut and a bush, and the flap suspension support arm adapter assembly 3 comprises a U-shaped piece, a bolt, a nut and a bush.
Before the embodiment of the utility model is used for lifting wings, a support shaft in an engine pylon adapter assembly 1 is placed between two lug plates of an engine connecting fork lug on an engine pylon 7, two shoulder bushes 12 are respectively arranged in lug holes of the two lug plates, and the shoulder bushes 12 are fixed on corresponding step shafts by using fastening bolts 13, namely, the operation of connecting the engine pylon adapter assembly 1 to the engine pylon 7 is completed; a bolt in the flap suspension support arm adapter assembly 3 passes through the bush, the U-shaped piece and the intersection point of the flap suspension support arm and is screwed by a nut, and the operation of connecting the flap suspension support arm adapter assembly 3 to the intersection point of the flap suspension support arm is completed; two ends of a front lifting beam 2 are connected with an engine hanger adapter assembly 1 through slings 5, and the middle part of the front lifting beam is connected with a crane hook; two ends of a rear lifting beam 4 are connected with a flap suspension support arm switching component 3 through slings 5, and the middle part of the rear lifting beam is connected with a crane hook; and after checking that all the connections are reliable, hoisting the integral wing by using a crane.
Therefore, the integral wing hoisting and fixing device can complete hoisting of the integral wing of the large turboprop, is simple to operate, and can ensure that the wing is in a horizontal posture in the hoisting process.
While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the utility model.
Claims (7)
1. The integral wing hoisting and fixing device is characterized by comprising a front hoisting beam (2) used for hoisting an engine connecting fork lug (8) of an engine hanger (7) on a wing (6), and a rear hoisting beam (4) used for hoisting a flap suspension support arm intersection point (9) on the wing (6); two ends of the front lifting beam (2) are connected with the engine hanger switching assemblies (1) through slings (5), and the two engine hanger switching assemblies (1) are respectively and correspondingly connected with an engine connecting fork lug (8); the two ends of the rear lifting beam (4) are connected with the flap suspension support arm switching components (3) through slings (5), and the two flap suspension support arm switching components (3) are correspondingly connected with a flap suspension support arm intersection point (9) respectively.
2. The integrated wing lifting fixing device of claim 1, wherein: engine pylon switching subassembly (1) is equipped with lifting hook (11) including back shaft (10) in back shaft (10) middle section, and back shaft (10) both ends all stretch out the step axle that has the diameter to be less than back shaft (10) middle section.
3. The integrated wing lifting fixing device of claim 2, wherein: and the two step shafts are sleeved with shoulder bushes (12), and the two shoulder bushes (12) are fixed on the step shafts through fastening bolts (13).
4. The integrated wing lifting fixing device of claim 3, wherein: the shoulders of the two shoulder bushes (12) are arranged oppositely.
5. The integrated wing lifting fixing device of claim 1, wherein: the flap suspension support arm switching assembly (3) comprises a U-shaped piece (14), through holes are formed in the open end of the U-shaped piece (14), the two through holes are connected through a support bolt (15), and the end portion of the support bolt (15) is connected with a fastening nut (16) after penetrating through the through holes.
6. The integrated wing lifting fixing device of claim 5, wherein: the closed end of the U-shaped part (14) is of a straight beam structure, and the included angle theta between the straight beam and the axis of the supporting bolt (15) is 3.28 degrees.
7. The integrated wing lifting fixing device of claim 5, wherein: the through hole is also internally provided with a support bushing (17), and the two support bushings (17) are penetrated by the support bolt (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122511388.XU CN216512343U (en) | 2021-10-18 | 2021-10-18 | Whole wing lifts by crane fixing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122511388.XU CN216512343U (en) | 2021-10-18 | 2021-10-18 | Whole wing lifts by crane fixing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216512343U true CN216512343U (en) | 2022-05-13 |
Family
ID=81522274
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122511388.XU Active CN216512343U (en) | 2021-10-18 | 2021-10-18 | Whole wing lifts by crane fixing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216512343U (en) |
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2021
- 2021-10-18 CN CN202122511388.XU patent/CN216512343U/en active Active
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