CN217456386U - Supporting device for eliminating lateral force during aircraft maintenance - Google Patents
Supporting device for eliminating lateral force during aircraft maintenance Download PDFInfo
- Publication number
- CN217456386U CN217456386U CN202221975569.6U CN202221975569U CN217456386U CN 217456386 U CN217456386 U CN 217456386U CN 202221975569 U CN202221975569 U CN 202221975569U CN 217456386 U CN217456386 U CN 217456386U
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- movable unit
- aircraft maintenance
- adapter
- aircraft
- support device
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- 238000012423 maintenance Methods 0.000 title claims abstract description 25
- 238000001179 sorption measurement Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000000007 visual effect Effects 0.000 description 2
- 238000012548 In-process support Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
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Abstract
The utility model relates to a supporting device for eliminating lateral force in aircraft maintenance, which is provided with a movable unit, a fixed unit and a lifting screw rod; the movable unit and the fixed unit are both mounted at the top of the lifting screw rod, and the lower end of the movable unit can freely slide in the fixed unit. The utility model discloses a head movable unit slides and eliminates the yawing force because of jacking angle incline, jacking positional deviation arouse to after aircraft jacking operation, pin movable unit position through the electro-magnet, movable unit is not hard up when preventing the aircraft maintenance.
Description
Technical Field
The utility model relates to an aircraft maintenance technical field, in particular to lateral force's strutting arrangement is eliminated in aircraft maintenance.
Background
The maintenance work of the aircraft mainly includes the repair, assembly and debugging of the structure and accessories of the aircraft body, and the maintenance work of the aircraft is usually completed on a maintenance platform. When the aircraft is maintained, generally use supporting equipment to jack the aircraft, common supporting equipment is the jack, jack head spherical structure pushes up into the aircraft and reserves ball socket structure in, and the equipment station removes in jacking process, lift lead screw is to the straightness that hangs down on ground, the counterpoint of bulb and ball socket is accomplished by artifical visual, receive visual precision to influence, the station deviation can appear big, hang down straightness poor, the inaccurate condition of counterpointing, produce oblique top, askew top, need adjust the supporting equipment position many times repeatedly in order to reduce the yawing force, this kind of counterpoint is inefficient, the precision is poor, there is equipment slope risk.
SUMMERY OF THE UTILITY MODEL
The utility model aims at overcoming the defect that current support equipment has the yawing force at the jacking in-process, providing one kind can be in the certain limit effectively eliminate because of the supporting arrangement of the yawing force is eliminated in the aircraft maintenance of the yawing force that jacking angle incline, jacking positional deviation arouse.
Realize the utility model discloses the technical scheme of purpose is: a supporting device for eliminating lateral force in aircraft maintenance is provided with a movable unit, a fixed unit and a lifting screw rod; the movable unit and the fixed unit are both mounted at the top of the lifting screw rod, and the lower end of the movable unit can freely slide in the fixed unit.
In the technical scheme, an electromagnet is arranged inside the fixing unit; the electromagnet is arranged corresponding to the lower end face of the movable unit.
In the technical scheme, the movable unit comprises a supporting ball head and a switching seat; the upper portion of support bulb is spherical, and cooperatees with aircraft ball socket, and the lower part links to each other with the adapter.
According to the technical scheme, the fixing unit comprises a limiting cover and an adapter flange; the limiting cover is installed at the top of the adapter flange.
According to the technical scheme, an annular ring is arranged on the outer ring of the lower part of the adapter; the limiting cover is provided with a through hole in a shape like a Chinese character 'tu'; the small inner diameter of the upper part of the through hole is smaller than the outer diameter of the annular ring, and the large inner diameter of the lower part of the through hole is larger than the outer diameter of the annular ring.
According to the technical scheme, the upper end face of the electromagnet is lower than the adapter flange.
According to the technical scheme, the lower end face of the annular ring of the adapter is in contact with the upper end face of the adapter flange, and the lower end face of the adapter is connected with the electromagnet in an adsorption mode.
After the technical scheme is adopted, the utility model discloses a main aim at provides an aircraft maintenance eliminates measurement power device, when solving aircraft maintenance in-process support equipment jacking aircraft, slide through head movable unit and eliminate because of jacking angle incline, the yawing force that jacking positional deviation arouses, and after aircraft jacking operation, pin movable unit position through the electro-magnet, movable unit is not hard up when preventing aircraft maintenance, reduce jacking regulation time, improve aircraft maintenance efficiency, personnel can't arrive or the operational difficulty when avoiding the jacking distance too high.
Drawings
In order that the present invention may be more readily and clearly understood, the following detailed description of the present invention is provided in connection with the accompanying drawings, in which:
FIG. 1 is a schematic sectional view of the present invention;
fig. 2 is an exploded view of the present invention.
The reference numbers in the drawings are as follows: the device comprises a support ball head 1, an adapter 2, a limiting cover 3, an adapter flange 4, an electromagnet 5 and a lifting screw rod 6.
Detailed Description
See fig. 1 and fig. 2, the utility model discloses have support bulb 1, adapter 2, spacing lid 3, adapter flange 4, electro-magnet 5, lift lead screw 6, support bulb 1 top spherical surface and aircraft support ball socket cooperation, the lower part is connected with adapter 2, support bulb 1 connects into whole with adapter 2 and forms movable unit, spacing lid 3 is installed at adapter flange 4 top, this spacing lid 3 limits the sliding range of movable unit in the horizontal plane, electro-magnet 5 is installed inside adapter flange 4, adapter flange 4 top installation spacing lid 3, internally mounted electro-magnet 5 forms fixed unit, movable unit and fixed unit are installed at lift lead screw 6 top, movable unit can freely slide in fixed unit inside in order to eliminate the jacking lateral force; lifting up and down along with a lifting screw rod 6 of the supporting equipment; when supporting device jacking support bulb 1 is in to the aircraft ball socket, because supporting device angle skew, jacking position deviation leads to exerting the yawing force to the supporting device top, the movable unit takes place to slide this moment, through the displacement self-adaptation aircraft ball socket in the horizontal plane, eliminate the yawing force, spacing lid 3 restriction movable unit is in the slip range of horizontal plane, prevent the movable unit roll-off, after the jacking operation, pin movable unit position to the electro-magnet circular telegram, movable unit is not hard up when preventing the aircraft maintenance.
The utility model discloses a theory of operation does: when the jacking of supporting equipment when aircraft maintenance, the movable unit can be by passive displacement self-adaptation aircraft ball socket, effectively eliminate in certain extent because of jacking angle skew, the yawing force that jacking positional deviation arouses, can the switching on of remote control electro-magnet 5 after the jacking process, the outage is in order to pin, loosen the movable unit position, reduces jacking adjust time, improves aircraft maintenance efficiency, and personnel can't arrive or the operational difficulty when avoiding the jacking distance too high.
The above-mentioned embodiments further describe the objects, technical solutions and advantages of the present invention in detail, it should be understood that the above-mentioned embodiments are only specific embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. The utility model provides an aircraft maintenance eliminates strutting arrangement of lateral force which characterized in that: comprises a movable unit, a fixed unit and a lifting screw rod (6); the movable unit and the fixed unit are both arranged at the top of the lifting screw rod (6), and the lower end of the movable unit can freely slide in the fixed unit.
2. A support device for eliminating lateral force in aircraft maintenance according to claim 1, wherein: an electromagnet (5) is arranged inside the fixed unit; the electromagnet (5) is arranged corresponding to the lower end face of the movable unit.
3. A support device for eliminating lateral force in aircraft maintenance according to claim 2, wherein: the movable unit comprises a supporting ball head (1) and a switching seat (2); the upper part of the supporting ball head (1) is spherical and matched with an aircraft ball socket, and the lower part of the supporting ball head is connected with the adapter (2).
4. A support device for eliminating side force in aircraft maintenance according to claim 3, wherein: the fixing unit comprises a limiting cover (3) and an adapter flange (4); the limiting cover (3) is arranged on the top of the adapter flange (4).
5. An aircraft maintenance support device for eliminating lateral forces according to claim 4, wherein: an annular ring is arranged on the outer ring of the lower part of the adapter (2); the limiting cover (3) is provided with a through hole in a shape of a Chinese character 'tu'; the small inner diameter of the upper part of the through hole is smaller than the outer diameter of the annular ring, and the large inner diameter of the lower part of the through hole is larger than the outer diameter of the annular ring.
6. A support device for eliminating side force in aircraft maintenance according to claim 4 or 5, wherein: the upper end face of the electromagnet (5) is lower than the adapter flange (4).
7. An aircraft maintenance lateral force cancellation support device as claimed in claim 6, wherein: the lower end face of the annular ring of the adapter (2) is in contact with the upper end face of the adapter flange (4), and the lower end face of the adapter (2) is connected with the electromagnet (5) in an adsorption mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221975569.6U CN217456386U (en) | 2022-07-29 | 2022-07-29 | Supporting device for eliminating lateral force during aircraft maintenance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221975569.6U CN217456386U (en) | 2022-07-29 | 2022-07-29 | Supporting device for eliminating lateral force during aircraft maintenance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217456386U true CN217456386U (en) | 2022-09-20 |
Family
ID=83249767
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221975569.6U Active CN217456386U (en) | 2022-07-29 | 2022-07-29 | Supporting device for eliminating lateral force during aircraft maintenance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217456386U (en) |
-
2022
- 2022-07-29 CN CN202221975569.6U patent/CN217456386U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: Room 303-19, No. 333 Huanhu West 1st Road, Nanhui New Town, Pudong New Area, Shanghai, 200120 Patentee after: Shanghai Shangfei Aircraft Equipment Manufacturing Co.,Ltd. Address before: Room 303-19, No. 333 Huanhu West 1st Road, Nanhui New Town, Pudong New Area, Shanghai, 200120 Patentee before: SHANGHAI SHANGFEI AIRCRAFT EQUIPMENT MANUFACTURING Co.,Ltd. |
|
| CP03 | Change of name, title or address |