CN108100934A - A kind of aircraft bracket - Google Patents
A kind of aircraft bracket Download PDFInfo
- Publication number
- CN108100934A CN108100934A CN201711352861.6A CN201711352861A CN108100934A CN 108100934 A CN108100934 A CN 108100934A CN 201711352861 A CN201711352861 A CN 201711352861A CN 108100934 A CN108100934 A CN 108100934A
- Authority
- CN
- China
- Prior art keywords
- driving
- supporting plate
- jack
- frames
- bevel gear
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000003756 stirring Methods 0.000 claims description 3
- 238000013016 damping Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 3
- 238000001727 in vivo Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66F—HOISTING, LIFTING, HAULING OR PUSHING, NOT OTHERWISE PROVIDED FOR, e.g. DEVICES WHICH APPLY A LIFTING OR PUSHING FORCE DIRECTLY TO THE SURFACE OF A LOAD
- B66F7/00—Lifting frames, e.g. for lifting vehicles; Platform lifts
- B66F7/10—Lifting frames, e.g. for lifting vehicles; Platform lifts with platforms supported directly by jacks
- B66F7/12—Lifting frames, e.g. for lifting vehicles; Platform lifts with platforms supported directly by jacks by mechanical jacks
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66F—HOISTING, LIFTING, HAULING OR PUSHING, NOT OTHERWISE PROVIDED FOR, e.g. DEVICES WHICH APPLY A LIFTING OR PUSHING FORCE DIRECTLY TO THE SURFACE OF A LOAD
- B66F7/00—Lifting frames, e.g. for lifting vehicles; Platform lifts
- B66F7/28—Constructional details, e.g. end stops, pivoting supporting members, sliding runners adjustable to load dimensions
Landscapes
- Life Sciences & Earth Sciences (AREA)
- Engineering & Computer Science (AREA)
- Geology (AREA)
- Mechanical Engineering (AREA)
- Structural Engineering (AREA)
- Toys (AREA)
Abstract
The present invention relates to a kind of aircraft brackets, it includes A-frame, the stull being arranged between two A-frames, the jacking apparatus being arranged on two A-frames and the supporting plate being arranged on jacking apparatus, the supporting plate top surface shape is adapted with the bottom shape of aircraft, felt is equipped on supporting plate, the jacking apparatus includes the left jack and the right jack that are separately positioned on two A-frames；The present invention simultaneously acts on supporting plate by two jack, and supporting plate is lifted, is lifted airframe using mop, it is reliable and stable, safety coefficient can be improved, while has felt on supporting plate, on the one hand it on the other hand can prevent supporting plate from generating scuffing to fuselage surface with damping.
Description
Technical field
The present invention relates to a kind of aircraft brackets.
Background technology
During aircraft is dismounted with repair, it is required for holding up on the fuselage of aircraft, and currently used method is
Fuselage is jacked up using jack, and when the jack-up height of jack is higher, safe operation coefficient can substantially reduce, so as to
The personal safety of entail dangers to operating personnel.
The content of the invention
The technical problems to be solved by the invention are to provide a kind of aircraft bracket that can stablize and hold up fuselage.
The technical solution adopted in the present invention is：A kind of aircraft bracket including A-frame, is arranged on two triangle branch
Stull, the jacking apparatus being arranged on two A-frames and the supporting plate being arranged on jacking apparatus between frame, institute
It states supporting plate top surface shape to be adapted with the bottom shape of aircraft, felt is equipped on supporting plate.
The jacking apparatus includes the left jack and the right jack that are separately positioned on two A-frames.
The left jack is identical with right jack structure and is oppositely arranged on two A-frames, left very heavy
Driving device is provided between top and right jack.
The left jack include cylinder, be arranged on the in vivo outer sleeve of cylinder be connected through a screw thread with outer sleeve upper end it is interior
Sleeve and the bevel gear for being arranged on outer sleeve lower end are provided with annular snap-gauge, in the cylinder in the lateral wall of the outer sleeve
It is provided with the annular slot being adapted with the annular snap version in vivo；It is provided in the lateral wall of the inner sleeve axially disposed
Card slot, be provided with the bayonet lock being adapted with the card slot in the cylinder, the bevel gear is sequentially connected with driving device.
The driving device includes what driving box, the driving shaft being rotatably arranged in driving box and driving shaft were sequentially connected
Driven shaft and the driving bevel gear for being arranged on driven shaft both ends, the driving bevel gear is meshed with bevel gear, described driven
Axis is rotatably arranged on driving box, and swing handle is connected on driving shaft.
Two adjacent driving gears are provided on the driving shaft, there are two sliding teeth in driven shaft interval setting
Wheel is provided with to stir the shift fork of shifting slide gear movement on driving box.
The positive effect of the present invention is：The present invention simultaneously acts on supporting plate by two jack, and supporting plate is lifted,
Airframe is lifted using mop, it is reliable and stable, safety coefficient can be improved, while have felt on supporting plate, on the one hand may be used
With damping, it on the other hand can prevent supporting plate from generating scuffing to fuselage surface.The present invention is driven simultaneously by one group of driving device
Two jack effects, two jack rise or fall simultaneously, and synchronism is very good.It is simple in structure using screw jack,
Self-locking can be achieved, effectively prevent from falling after rise when propping up weight.
Description of the drawings
Fig. 1 is schematic structural view of the invention；
Fig. 2 is the left jack structure schematic diagram of the present invention；
Fig. 3 is inner sleeve structure schematic diagram of the present invention；
Fig. 4 is driving device structure schematic diagram of the present invention.
Specific embodiment
As shown in Figure 1, the present invention includes A-frame 1, the stull 11 being arranged between two A-frames 1, sets
Jacking apparatus on two A-frames 1 and the supporting plate 4 being arranged on jacking apparatus, 4 top surface shape of supporting plate
It is adapted with the bottom shape of aircraft, felt is equipped on supporting plate 4.The jacking apparatus includes being separately positioned on described in two
Left jack 3 and right jack 6 on A-frame 1.
As shown in Figure 2-4, the left jack 3 is identical with right 6 structure of jack and is oppositely arranged on two described three
In angle support 1, driving device is provided between left jack 3 and right jack 6.The left jack 3 include cylinder 301,
The inner sleeve 302 and be arranged on outer that the outer sleeve 304 being arranged in cylinder 301 is connected through a screw thread with 304 upper end of outer sleeve
The bevel gear 306 of 304 lower end of sleeve is provided with annular snap-gauge 305, in the cylinder 301 in the lateral wall of the outer sleeve 304
Inside it is provided with the annular slot being adapted with the annular snap version 305；It is provided with vertically in the lateral wall of the inner sleeve 302
The card slot 307 of setting is provided with the bayonet lock 303 being adapted with the card slot 307, the bevel gear 306 in the cylinder 301
It is sequentially connected with driving device.Outer sleeve 304 is erected at by annular snap version 305 in cylinder 301, under the action of driving device
It rotation, inner sleeve 302 can be spirally connected in cylinder 301 with outer sleeve 304 by screw thread, and inner sleeve 302 is in card slot 307 and card
Under the action of pin 303, inner sleeve 302 can only be carried out vertically mobile and cannot rotated, then when outer sleeve 304 rotates
When, inner sleeve 302 can only upper and lower translation, realize and weight moved up and down.Two-half structure may be employed in cylinder 301,
Inner sleeve 302 and outer sleeve 301 are fastened inside it.Simple using the jack structure of this structure, design is reasonable, and ties up
It repaiies conveniently.
The driving device includes driving box 14, the driving shaft 7 being rotatably arranged in driving box 14, is driven with driving shaft 7
The driven shaft 10 of connection and the driving bevel gear 11 for being arranged on 10 both ends of driven shaft, the driving bevel gear 11 and bevel gear
306 are meshed, and the driven shaft is rotatably arranged on driving box 14, and swing handle 13 is connected on driving shaft 7.In the master
Two adjacent driving gears 8 are provided on moving axis 7, are arranged at intervals in driven shaft 10 there are two shifting slide gear 9, in driving box 14
On be provided with to stir the shift fork of the movement of shifting slide gear 9.By setting shifting slide gear 9, can adjust driving shaft and driven shaft it
Between rotating ratio, realize that different jack is regulated the speed, when supporting plate 4 apart from airframe farther out when may be employed faster from
Moving axis velocity of rotation makes supporting plate 4 quickly close to fuselage.And when supporting plate 4 is nearer apart from fuselage, slower velocity of rotation is changed to,
Make supporting plate 4 slowly close, it can be with damage of the reduction supporting plate 4 of maximum possible for fuselage.
The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although with reference to the foregoing embodiments
The present invention is described in detail, it will be understood by those of ordinary skill in the art that：It still can be to previous embodiment
Recorded technical solution modifies or carries out equivalent substitution to which part technical characteristic；And these are changed or replace
It changes, the essence of appropriate technical solution is not made to depart from the spirit and scope of technical solution of the embodiment of the present invention.
Claims (4)
1. a kind of aircraft bracket, it is characterised in that it includes A-frame（1）, be arranged on two A-frames（1）Between horizontal stroke
Support（11）, be arranged on two A-frames（1）On jacking apparatus and the supporting plate that is arranged on jacking apparatus（4）, institute
State supporting plate（4）Top surface shape is adapted with the bottom shape of aircraft, in supporting plate（4）On be equipped with felt；
The jacking apparatus includes being separately positioned on two A-frames（1）On left jack（3）With right jack
（6）.
A kind of 2. aircraft bracket according to claim 1, it is characterised in that the left jack（3）With right jack（6）
Structure is identical and is oppositely arranged on two A-frames（1）On, in left jack（3）With right jack（6）Between set
There is driving device；
The left jack（3）Including cylinder（301）, be arranged on cylinder（301）Interior outer sleeve（304）With outer sleeve（304）
The inner sleeve that upper end is connected through a screw thread（302）And it is arranged on outer sleeve（304）The bevel gear of lower end（306）, described outer
Sleeve（304）Lateral wall be provided with annular snap-gauge（305）, in the cylinder（301）It is inside provided with and the annular snap version
（305）The annular slot being adapted；In the inner sleeve（302）Lateral wall be provided with axially disposed card slot（307）,
The cylinder（301）It is inside provided with and the card slot（307）The bayonet lock being adapted（303）, the bevel gear（306）It is filled with driving
Put drive connection.
3. a kind of aircraft bracket according to claim 2, it is characterised in that the driving device includes driving box（14）, turn
It is dynamic to be arranged on driving box（14）Interior driving shaft（7）With driving shaft（7）The driven shaft of drive connection（10）And it is arranged on driven
Axis（10）The driving bevel gear at both ends（11）, the driving bevel gear（11）With bevel gear（306）It is meshed, the driven shaft turns
It is dynamic to be arranged on driving box（14）On, in driving shaft（7）On be connected with swing handle（13）.
4. a kind of aircraft bracket according to claim 3, it is characterised in that in the driving shaft（7）On be provided with it is adjacent
Two driving gears（8）, in driven shaft（10）Shifting slide gear there are two being arranged at intervals（9）, in driving box（14）Upper setting is useful
In stirring shifting slide gear（9）Mobile shift fork.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711352861.6A CN108100934A (en) | 2017-12-15 | 2017-12-15 | A kind of aircraft bracket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711352861.6A CN108100934A (en) | 2017-12-15 | 2017-12-15 | A kind of aircraft bracket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108100934A true CN108100934A (en) | 2018-06-01 |
Family
ID=62217353
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711352861.6A Pending CN108100934A (en) | 2017-12-15 | 2017-12-15 | A kind of aircraft bracket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108100934A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101100271A (en) * | 2007-07-26 | 2008-01-09 | 谢翠斌 | Automobile maintenance lifting platform |
| CN203319626U (en) * | 2013-05-14 | 2013-12-04 | 中国长江三峡集团公司 | Novel mechanical jacking ensuring device |
| CN105174130A (en) * | 2015-08-18 | 2015-12-23 | 广西大学 | Gear lifting mechanism |
| CN206265337U (en) * | 2016-12-12 | 2017-06-20 | 贵州航天特种车有限责任公司 | A kind of collapsible aircraft bracket of synchronization lifting |
| CN207861788U (en) * | 2017-12-15 | 2018-09-14 | 石家庄飞机工业有限责任公司 | A kind of aircraft bracket |
-
2017
- 2017-12-15 CN CN201711352861.6A patent/CN108100934A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101100271A (en) * | 2007-07-26 | 2008-01-09 | 谢翠斌 | Automobile maintenance lifting platform |
| CN203319626U (en) * | 2013-05-14 | 2013-12-04 | 中国长江三峡集团公司 | Novel mechanical jacking ensuring device |
| CN105174130A (en) * | 2015-08-18 | 2015-12-23 | 广西大学 | Gear lifting mechanism |
| CN206265337U (en) * | 2016-12-12 | 2017-06-20 | 贵州航天特种车有限责任公司 | A kind of collapsible aircraft bracket of synchronization lifting |
| CN207861788U (en) * | 2017-12-15 | 2018-09-14 | 石家庄飞机工业有限责任公司 | A kind of aircraft bracket |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180601 |