CN206155820U - Aircraft vertical fin removes transfers appearance butting device - Google Patents
Aircraft vertical fin removes transfers appearance butting device Download PDFInfo
- Publication number
- CN206155820U CN206155820U CN201621231544.XU CN201621231544U CN206155820U CN 206155820 U CN206155820 U CN 206155820U CN 201621231544 U CN201621231544 U CN 201621231544U CN 206155820 U CN206155820 U CN 206155820U
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- CN
- China
- Prior art keywords
- vertical fin
- aircraft vertical
- locomotive
- bracing frame
- supporting construction
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- 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.)
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Abstract
The utility model provides an aircraft vertical fin removes transfers appearance butting device, includes locomotive, elevating system, bearing structure, adjustment butt -joint structural and clamping structure, adjustment butt -joint structural includes four locators, elevating system sets up between four locators, bearing structure sets up at the elevating system top, bearing structure includes the support frame, the lateral part of support frame is equipped with the extension that corresponds with locator quantity, the bottom of extension is equipped with the bulb, bulb and the ball slot combination of setting at the lifter top, the top of support frame is equipped with the rotor plate mounting bracket that is vertical setting, the bottom and the support frame of rotor plate mounting bracket pass through the guide rail, slider sliding connection, be equipped with the rotatory rotor plate through motor drive on the rotor plate mounting bracket, it is rotatory that clamping structure passes through the rotor plate drive, clamping structure is including the centre gripping frame that is trapezoidal setting, the upper base of centre gripping frame is equipped with two grip blocks that are used for centre gripping aircraft vertical fin respectively with going to the bottom.
Description
Technical field
The utility model belongs to aircraft mounting technology field, especially has with a kind of aircraft vertical fin movement posture adjustment the service of connection devices
Close.
Background technology
Aircraft assembling is again an extremely important ring in aircraft manufacturing link, the precision and efficiency of its assembling, in very great Cheng
Final mass, manufacturing cost and the cycle of aircraft are determined on degree.But at present most domestic adopts manual assembly, efficiency is non-
It is often low.The particularly existing installation to aircraft vertical fin is docked, extremely difficult.For the problem, applicant research and development
A kind of applicable aircraft vertical fin assembling automatically adjusts the service of connection devices.
Utility model content
For the problem that above-mentioned background technology is present, the utility model aims to provide a kind of aircraft vertical fin movement posture adjustment docking
Equipment.
For this purpose, the utility model is employed the following technical solutions：A kind of aircraft vertical fin moves posture adjustment the service of connection devices, its feature
Be, including locomotive, be installed at the top of locomotive elevating mechanism, the supporting construction for supporting aircraft vertical fin, for adjusting
The adjustment docking structure of described supporting construction angle and the clamp structure for gripping aircraft vertical fin；Described adjustment is right
Binding structure includes setting up separately the locator in four corners at the top of the locomotive, and described locator includes elevating lever, up and down
The Y-axis slipping mechanism and X-axis slipping mechanism of closed assembly, X-axis slipping mechanism and Y-axis slipping mechanism pass through respectively respective motor
Sliding, elevating lever is driven to drive lifting, described X-axis by the lift drive mechanism being arranged on the slide unit of Y-axis slipping mechanism
In the top horizontal sliding of described locomotive, and X-axis slipping mechanism drives the shift length of whole locator to slipping mechanism
Not less than the half of locomotive lateral length；Described elevating mechanism is arranged in the gap formed between four locater, institute
The supporting construction stated is arranged on the top of described elevating mechanism, and supporting construction includes bracing frame, and bracing frame is horizontal by many
Bar and longitudinal rod intersect fixed-type, and the sidepiece of bracing frame is provided with extension corresponding with described locator quantity, prolongs
The bottom of extending portion is provided with bulb, and bulb and the ball groove being arranged at the top of elevating lever coordinate, and is provided with the top of described bracing frame and is in
The rotation board mounting stand being vertically arranged, the bottom for rotating board mounting stand is slidably connected with bracing frame by guide rail, slide block, swivel plate
Installing rack is provided with the swivel plate rotated by Motor drive, and described clamp structure is driven by swivel plate and rotated, clamping knot
Structure includes the clamping framework of trapezoidal setting, clamps the upper bottom of framework and is respectively equipped with two for clamping aircraft vertical fin with going to the bottom
Grip block.
Used as the supplement to above-mentioned technical proposal and perfect, the utility model also includes following technical characteristic.
Described elevating mechanism includes the lifter plate for supporting the supporting construction for placing described and drives lifter plate lifting
Scissors fork mechanism, scissors pitch mechanism by hydraulic means drive.
Described locomotive is to be driven by servomotor, and its roller is Mecanum wheel.
Described grip block realizes the clamping to aircraft vertical fin by air cylinder driven, so that grip block clamping is firm, tool
Have locking, anti-lost function is made because clamping not strongly by and loss that vertical fin drops is reduced to zero.
Following beneficial effect can be reached using the utility model：The utility model can realize three directions by locator
Accurate movement and positioning, one group of composition of four locater digitizes attitude-adjusting unit, realizes pose adjustment and the docking of vertical fin.
Solve the problems, such as the wasting time and energy of manual assembly, overhang greatly it is difficult install, realize the automation of assembling, saved and be assembled into
This, improves the efficiency of aircraft manufacturing.
Description of the drawings
Fig. 1 is original operating state structural representation of the present utility model.
Fig. 2 is working state structure schematic diagram of the present utility model.
Specific embodiment
Specific embodiment of the present utility model is described in detail below in conjunction with the accompanying drawings.
As shown in Fig. 1～Fig. 2, elevating mechanism 2, use that the utility model includes locomotive 1, is installed on the top of locomotive 1
In supporting the supporting construction 3 of aircraft vertical fin 6, the adjustment docking structure for adjusting the angle of supporting construction 3 and for gripping
The clamp structure 4 of aircraft vertical fin 6；Adjustment docking structure includes setting up the locator in four corners at the top of the locomotive 1 separately
5, locator 5 includes elevating lever 13, the Y-axis slipping mechanism of upper and lower closed assembly and X-axis slipping mechanism, X-axis slipping mechanism and Y-axis sliding
Mechanism drives sliding by respective motor respectively, and elevating lever 13 is by the liter that is arranged on the slide unit of Y-axis slipping mechanism
Drop drive mechanism drives lifting, X-axis slipping mechanism locomotive 1 top horizontal sliding, and X-axis slipping mechanism drive it is whole
Half of the shift length of locator 5 not less than the lateral length of locomotive 1；Elevating mechanism 2 is arranged on shape between four locater 5
Into gap in, supporting construction 3 is arranged on the top of elevating mechanism 2, and supporting construction 3 includes bracing frame 7, and bracing frame 7 is by more
Root transverse bar and longitudinal rod intersect fixed-type, and the sidepiece of bracing frame 7 is provided with extension corresponding with the quantity of locator 5
10, the bottom of extension 10 is provided with bulb 11, and bulb 11 coordinates with the ball groove for being arranged on the top of elevating lever 13, the top of bracing frame 7
Portion is provided with the rotation board mounting stand 8 being vertically arranged, and the bottom and bracing frame 7 for rotating board mounting stand 8 is slided by guide rail, slide block
Connection, is rotated board mounting stand 8 and is provided with the swivel plate 9 rotated by Motor drive, and clamp structure 4 drives rotation by swivel plate 9
Turn, clamp structure 4 includes the clamping framework of trapezoidal setting, clamp the upper bottom of framework and be respectively equipped with two for clamping with going to the bottom
The grip block 12 of aircraft vertical fin 6, grip block 12 realizes the clamping to aircraft vertical fin by air cylinder driven, so that grip block clamping
It is firm, with locking, anti-lost function, make because clamping not strongly by and loss that vertical fin drops is reduced to zero.
Further, elevating mechanism 2 is included for supporting the lifter plate for placing supporting construction 3 and driving lifter plate lifting
Scissors pitches mechanism, and scissors is pitched mechanism and driven by hydraulic means.Locomotive 1 is to be driven by servomotor, and its roller is wheat
Ke Namu takes turns.
As shown in figure 1, situation during this to be equipment be at ordinary times off position, supporting construction and clamp structure are by rising
Descending mechanism support drops to certain altitude, and four locater moves to centre position to avoid supporting construction.When needing work
When making, elevating mechanism shores supporting construction with clamp structure to certain altitude, and four locater is found respectively bulb position accurately, makes ball
Head returns to origin-location completely into ball groove, elevating mechanism.Vertical fin grabs clamping from vertical fin unwheeling by boosting manipulator
In structure, clamp body steps up.Equipment is moved to installation site, and by laser tracker bigness scale amount is carried out, and judges vertical fin and machine
The rough position relation of body, adjustment docking structure carries out coarse adjustment appearance.When vertical fin enters accurate posture adjustment position, found range by light-metering
The measurement of instrument group judges the precise positional relationship of vertical fin and fuselage, carries out accurate adjustment appearance, after attitude is mixed up, carries out the related work such as docking
Make.Work is completed, and clamp structure unclamps, and equipment removes installation site, and each unit returns to state shown in Fig. 1, and equipment is returned to be parked
Place, waits next task, so circulation.The utility model saves parking space, when not working, using hoistable platform support
Bracket simultaneously declines, and reduces equipment whole height, in being conveniently parked in special double-deck material platform.The utility model has certainly
Dynamic track function, path learning ability, can be by fixed course action；With any direction translation and no-radius turning function, make
Mobile avoidance is more convenient.
General principle of the present utility model and principal character and advantage of the present utility model has been shown and described above.One's own profession
The technical staff of industry it should be appreciated that the utility model is not restricted to the described embodiments, described in above-described embodiment and specification
Simply illustrate principle of the present utility model, on the premise of without departing from the utility model spirit and scope, the utility model is also
Various changes and modifications are had, these changes and improvements are both fallen within the range of claimed the utility model.The utility model
Claimed scope is by appending claims and its equivalent thereof.
Claims (4)
1. a kind of aircraft vertical fin moves posture adjustment the service of connection devices, it is characterised in that：Including locomotive（1）, be installed on locomotive（1）Top
The elevating mechanism in portion（2）, for supporting aircraft vertical fin（6）Supporting construction（3）, for adjusting described supporting construction（3）Angle
The adjustment docking structure of degree and for gripping aircraft vertical fin（6）Clamp structure（4）；Described adjustment docking structure includes
Set up separately in the locomotive（1）The locator in four corners at top（5）, described locator（5）Including elevating lever（13）, on
The Y-axis slipping mechanism and X-axis slipping mechanism of lower closed assembly, X-axis slipping mechanism and Y-axis slipping mechanism drive electricity by respective respectively
Machine drives sliding, elevating lever（13）Lifting is driven by the lift drive mechanism being arranged on the slide unit of Y-axis slipping mechanism, it is described
X-axis slipping mechanism in described locomotive（1）Top horizontal sliding, and X-axis slipping mechanism drives whole locator（5）
Shift length be not less than locomotive（1）The half of lateral length；Described elevating mechanism（2）It is arranged on four locater（5）
Between formed gap in, described supporting construction（3）It is arranged on described elevating mechanism（2）Top, supporting construction（3）Bag
Include bracing frame（7）, bracing frame（7）Intersected fixed-type, bracing frame by many transverse bars and longitudinal rod（7）Sidepiece set
Have and described locator（5）The corresponding extension of quantity（10）, extension（10）Bottom be provided with bulb（11）, bulb（11）
Be arranged on elevating lever（13）The ball groove at top coordinates, described bracing frame（7）Top be provided with the swivel plate that is vertically arranged
Installing rack（8）, rotate board mounting stand（8）Bottom and bracing frame（7）It is slidably connected by guide rail, slide block, rotates board mounting stand
（8）It is provided with the swivel plate rotated by Motor drive（9）, described clamp structure（4）By swivel plate（9）Drive rotation,
Clamp structure（4）Including the clamping framework of trapezoidal setting, clamp the upper bottom of framework and be respectively equipped with two for clamping with going to the bottom
Aircraft vertical fin（6）Grip block（12）.
2. a kind of aircraft vertical fin according to claim 1 moves posture adjustment the service of connection devices, it is characterised in that：Described lift
Structure（2）Described supporting construction is placed including for supporting（3）Lifter plate and drive lifter plate lifting scissors fork mechanism, cut
Knife and fork mechanism is driven by hydraulic means.
3. a kind of aircraft vertical fin according to claim 2 moves posture adjustment the service of connection devices, it is characterised in that：Described locomotive
（1）Driven by servomotor, and its roller is Mecanum wheel.
4. a kind of aircraft vertical fin according to claim 3 moves posture adjustment the service of connection devices, it is characterised in that：Described grip block
（12）Clamping to aircraft vertical fin is realized by air cylinder driven.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621231544.XU CN206155820U (en) | 2016-11-16 | 2016-11-16 | Aircraft vertical fin removes transfers appearance butting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621231544.XU CN206155820U (en) | 2016-11-16 | 2016-11-16 | Aircraft vertical fin removes transfers appearance butting device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206155820U true CN206155820U (en) | 2017-05-10 |
Family
ID=58660320
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621231544.XU Expired - Fee Related CN206155820U (en) | 2016-11-16 | 2016-11-16 | Aircraft vertical fin removes transfers appearance butting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206155820U (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107963237A (en) * | 2017-12-04 | 2018-04-27 | 晨龙飞机（荆门）有限公司 | A kind of aircraft wing maintenance and lifting auxiliary device |
| CN108071910A (en) * | 2017-12-08 | 2018-05-25 | 中国人民解放军火箭军工程设计研究院 | A kind of pose adjusting apparatus |
| CN108637724A (en) * | 2018-04-25 | 2018-10-12 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft class titanium alloy component processing tool platform hold-down mechanism |
| CN108639375A (en) * | 2018-06-26 | 2018-10-12 | 中电科芜湖钻石飞机制造有限公司 | The assembly method of airframe and wing centre section assembly |
| CN108791947A (en) * | 2018-05-28 | 2018-11-13 | 成都飞机工业（集团）有限责任公司 | A kind of anti-tailspin mounting device and localization method |
| CN110092010A (en) * | 2018-01-31 | 2019-08-06 | 株式会社斯巴鲁 | Manufacture auxiliary device |
| CN112340054A (en) * | 2020-09-18 | 2021-02-09 | 成都飞机工业（集团）有限责任公司 | Multi-axis main follow-up attitude adjusting method and attitude adjusting device for large part of airplane |
| CN112824228A (en) * | 2019-11-20 | 2021-05-21 | 中国商用飞机有限责任公司 | Variable-constraint airplane component posture adjusting, butting and positioning method |
| CN113910153A (en) * | 2021-10-29 | 2022-01-11 | 中航通飞华南飞机工业有限公司 | Supporting and fixing platform for assisting vertical fin disassembly and assembly |
-
2016
- 2016-11-16 CN CN201621231544.XU patent/CN206155820U/en not_active Expired - Fee Related
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107963237A (en) * | 2017-12-04 | 2018-04-27 | 晨龙飞机（荆门）有限公司 | A kind of aircraft wing maintenance and lifting auxiliary device |
| CN108071910A (en) * | 2017-12-08 | 2018-05-25 | 中国人民解放军火箭军工程设计研究院 | A kind of pose adjusting apparatus |
| CN108071910B (en) * | 2017-12-08 | 2019-10-11 | 中国人民解放军火箭军工程设计研究院 | A kind of pose adjustment device |
| CN110092010A (en) * | 2018-01-31 | 2019-08-06 | 株式会社斯巴鲁 | Manufacture auxiliary device |
| CN108637724B (en) * | 2018-04-25 | 2020-06-30 | 西安飞机工业（集团）有限责任公司 | Pressing mechanism of machining tool table for airplane-type titanium alloy parts |
| CN108637724A (en) * | 2018-04-25 | 2018-10-12 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft class titanium alloy component processing tool platform hold-down mechanism |
| CN108791947A (en) * | 2018-05-28 | 2018-11-13 | 成都飞机工业（集团）有限责任公司 | A kind of anti-tailspin mounting device and localization method |
| CN108639375A (en) * | 2018-06-26 | 2018-10-12 | 中电科芜湖钻石飞机制造有限公司 | The assembly method of airframe and wing centre section assembly |
| CN108639375B (en) * | 2018-06-26 | 2021-08-31 | 中电科芜湖钻石飞机制造有限公司 | Method for assembling airplane fuselage and middle wing assembly |
| CN112824228A (en) * | 2019-11-20 | 2021-05-21 | 中国商用飞机有限责任公司 | Variable-constraint airplane component posture adjusting, butting and positioning method |
| CN112824228B (en) * | 2019-11-20 | 2024-03-12 | 中国商用飞机有限责任公司 | Variable constraint type airplane component gesture-adjusting butt-joint positioning method |
| CN112340054A (en) * | 2020-09-18 | 2021-02-09 | 成都飞机工业（集团）有限责任公司 | Multi-axis main follow-up attitude adjusting method and attitude adjusting device for large part of airplane |
| CN112340054B (en) * | 2020-09-18 | 2022-05-06 | 成都飞机工业（集团）有限责任公司 | Multi-axis main follow-up attitude adjusting method and attitude adjusting device for large part of airplane |
| CN113910153A (en) * | 2021-10-29 | 2022-01-11 | 中航通飞华南飞机工业有限公司 | Supporting and fixing platform for assisting vertical fin disassembly and assembly |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170510 Termination date: 20211116 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |