CN103754387A - Method and device for lifting and assembling part in airplane cabin - Google Patents
Method and device for lifting and assembling part in airplane cabin Download PDFInfo
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- CN103754387A CN103754387A CN201410047885.0A CN201410047885A CN103754387A CN 103754387 A CN103754387 A CN 103754387A CN 201410047885 A CN201410047885 A CN 201410047885A CN 103754387 A CN103754387 A CN 103754387A
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Abstract
The invention provides a method and device for lifting and assembling a part in an airplane cabin. The method and device for lifting and assembling the part in the airplane cabin comprises a fixing assembly, a lifting assembly and a cable catapulting machine, wherein a fixed pulley is fixed to one side of the fixing assembly, a movable pulley is arranged on the lifting assembly, the cable catapulting machine is fixed to the floor in the airplane cabin through a base, and the end of a lifting cable of the cable catapulting machine surrounds the fixed pulley on the fixing assembly and then surrounds the movable pulley on the lifting assembly to be fixed to a rigid clamping base.
Description
Technical field
The application relates to the wayside equipment technology of aircraft manufacturing frock, specifically a kind of method and bont that promotes assembly unit in aircraft cabin.
Background technology
Airplane in transportation category inside is equipped with the products such as electric hoist conventionally, and this product is general to be installed on above airframe top support beam from focusing on 150kg left and right, can move along support beam, for the lifting of goods, very convenient.But in aircraft manufacturing process, at aircraft cabin inner top, how the product that this deadweight is larger being installed is but a large problem.Be subject to the impact of aircaft configuration, wayside equipment (as working stand, liftable installation car) cannot enter interior of aircraft work conventionally, and narrow space between aircraft top support beam and wallboard, and hanging can not be used for herein.For this situation, need to develop a kind of method and device that can the small space in aircraft cabin can load and unload fast, promote assembly unit and be very important.
Summary of the invention
The application's object is to provide a kind of method and bont that promotes assembly unit in aircraft cabin.This bont fast handling, convenient operation, be beneficial to Product Assembly, and can be safe and reliable product is risen to assigned address.For reaching above object, the application takes following technical scheme to be achieved:
A kind of method and device that promotes assembly unit in aircraft cabin, it is characterized in that comprising a fixation kit, a lifting subassembly and a bomb rammer, the body of described fixation kit is a rigidity deck, the middle part of this rigidity deck is fixed on the support beam of aircraft cabin inner top, a side at rigidity deck is fixed with fixed pulley, separately there is a balance cable wire that the opposite side of rigidity deck is connected with the floor in aircraft cabin, the body of lifting subassembly is the attaching parts of a rigidity, the middle part of this attaching parts is fixed with a movable pulley, the both sides of attaching parts are provided with adapter shaft, bomb rammer is fixed on the floor in aircraft cabin by pedestal, the fixed pulley on fixation kit is walked around in the cable wire termination of bomb rammer, after walking around again the movable pulley on lifting subassembly, be fixed on rigidity deck, assembly unit is fixed on the adapter shaft of attaching parts both sides, by rotating the handle of bomb rammer, assembly unit can be promoted to the support beam place that approaches aircraft cabin inner top.
The advantage of foregoing invention scheme is: 1) the body deck of fixation kit is fixed on fixed pulley on the support beam in aircraft cabin, after being convenient to parts and having assembled, deck is removed in aircraft cabin together with fixed pulley; 2) movable pulley is fixed on the middle part of lifting subassembly body, makes parts in lifting process, keep balance and stable; 3) balance cable wire is connected fixation kit with aircraft cabin ground, guarantees the relatively stable of in lifting piece process fixation kit, avoids fixation kit and nacelle top to interfere; 4) bomb rammer, for promoting engine installation, is connected with aircraft floor by pedestal, utilizes himself to be with to lift cable wire each component string is unified into an entirety.5), while using, shake bomb rammer, can be promoted to installation site by product, completes docking.6) the application has broken through the restriction in space, and what energy was safe and reliable rises to assigned address by product, and novel structure, processing is simple, lightweight, volume is little, facilitates again workman to operate, high-effective and labour-saving, be beneficial to Product Assembly, the most important thing is to have shortened assembly period, solved an assembling difficult problem.With respect to other frocks such as liftable installation cars, this frock cost reduces greatly simultaneously.The design concept of this frock is also for the installation of (the unreachable region of working stand) product in similar small space provides new approaches.
Below in conjunction with embodiment accompanying drawing, this application is described in further detail:
Accompanying drawing explanation
Fig. 1 is the signal of bont use state
Fig. 2 is bont structural representation
Number description: 1 deck, 2 fixed pulleys, 3 lift cable wire, 4 bomb rammers, 5 handles, 6 pedestals, 7 connectors, 8 movable pulleys, 9 balance cable wires, 10 support beams, 11 fuselages, 12 floors, 13 assembly units.
The specific embodiment
Referring to accompanying drawing, narrow space between airframe 11 top support beam 10 and wallboard, installation site is liftoff, and plate distance is large, operating personal is unreachable, working stand and hanging can not be used, therefore the present invention utilizes the structure design foundation of movable pulley principle as this application, designs a kind of method for improving and device, makes product rise to installation site from floor.
The application's the method that promotes assembly unit in aircraft cabin, comprise a fixation kit, a lifting subassembly and a bomb rammer, the body of described fixation kit is a rigidity deck 1, the middle part of rigidity deck is provided with groove, can be suspended on the support beam 10 of aircraft cabin inner top, bottom is provided with connecting bore, be bolted, prevent that deck 1 from departing from from support beam 10, one side of deck 1 is fixed with fixed pulley 2, the opposite side of deck 1 is by bearing pin stable equilibrium cable wire 9, and the other end of balance cable wire 9 is fixed on the floor 12 in aircraft cabin; The body of lifting subassembly is the attaching parts 7 of a rigidity, and movable pulley 8 is fixed on the fork ear of connector 7 by center shaft, and the two ends of connector 7 are provided with adapter shaft, for the fixing assembly unit 13 that needs lifting; Bomb rammer 4 is engine installation, by pedestal 6, be fixed on floor 12, the termination that lifts cable wire 3 of bomb rammer is walked around fixed pulley on fixation kit, is fixed on rigidity deck after walking around the movable pulley on lifting subassembly, assembly unit 13 is fixed on the adapter shaft of attaching parts both sides, by rotating the handle 5 of bomb rammer, lifting subassembly can be promoted to the support beam place that approaches aircraft cabin inner top together with assembly unit 13.
During use, first the body rigidity deck 1 of fixation kit is suspended on the support beam 10 at top, secondly the assembly unit 13 needs being promoted is fixed on the both sides adapter shaft of the body attaching parts that lifts assembly, shake bomb rammer handle 5, at the uniform velocity promote assembly unit 13 to installation site, complete docking.Available rope auxiliary traction in lifting process, prevents from.
Claims (2)
1. one kind promotes the method for assembly unit in aircraft cabin, it is characterized in that comprising a fixation kit, a lifting subassembly and a bomb rammer, the body of described fixation kit is a rigidity deck, the middle part of this rigidity deck is fixed on the guide rail beam of aircraft cabin inner top, a side at rigidity deck is fixed with fixed pulley, separately there is a balance cable wire that the opposite side of rigidity deck is connected with the floor in aircraft cabin, the body of lifting subassembly is the attaching parts of a rigidity, the middle part of this attaching parts is fixed with a movable pulley, the both sides of attaching parts are provided with adapter shaft, bomb rammer is fixed on the floor in aircraft cabin by pedestal, the fixed pulley on fixation kit is walked around in the cable wire termination of bomb rammer, after walking around again the movable pulley on lifting subassembly, be fixed on rigidity deck, assembly unit is fixed on the adapter shaft of attaching parts both sides, by rotating the handle of bomb rammer, assembly unit can be promoted to the guide rail beam place that approaches aircraft cabin inner top.
2. one kind promotes the device of assembly unit in aircraft cabin, contain fixation kit, lifting subassembly and bomb rammer, the body that it is characterized in that described fixation kit is a rigidity deck, the middle part of this deck can be fixed on the support beam of aircraft cabin inner top, a side at deck is fixed with fixed pulley, at the opposite side of deck, be fixed with a balance cable wire, the other end of balance cable wire is fixed on the floor in aircraft cabin, the body of lifting subassembly is the attaching parts of a rigidity, there is a movable pulley by center shaft, to be fixed on the middle part fork ear of connector, the two ends of connector are respectively equipped with adapter shaft, bomb rammer is fixed on the floor in aircraft cabin by pedestal, bomb rammer lifts the termination of cable wire and walks around the fixed pulley on fixation kit, after walking around again the movable pulley on lifting subassembly, be fixed on rigidity deck.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410047885.0A CN103754387A (en) | 2014-02-11 | 2014-02-11 | Method and device for lifting and assembling part in airplane cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410047885.0A CN103754387A (en) | 2014-02-11 | 2014-02-11 | Method and device for lifting and assembling part in airplane cabin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103754387A true CN103754387A (en) | 2014-04-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410047885.0A Pending CN103754387A (en) | 2014-02-11 | 2014-02-11 | Method and device for lifting and assembling part in airplane cabin |
Country Status (1)
| Country | Link |
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| CN (1) | CN103754387A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108820244A (en) * | 2018-06-26 | 2018-11-16 | 刘先平 | A kind of aircraft tail propeller assembling Intelligent treatment equipment |
| CN111993981A (en) * | 2020-08-31 | 2020-11-27 | 重庆领直航科技有限公司 | Unmanned aerial vehicle loading and unloading device and shelter |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4858855A (en) * | 1987-06-04 | 1989-08-22 | Aerospatiale Societe Nationale Industrielle | Autonomous onboard loading device for a cargo-aircraft |
| RU2076831C1 (en) * | 1990-04-23 | 1997-04-10 | Акционерное общество открытого типа "Нижегородский авиастроительный завод "Сокол" | Device for transportation, hoisting and suspending of cargo on flying vehicles |
| US7270297B2 (en) * | 2004-01-30 | 2007-09-18 | The Boeing Company | Hoist for aircraft cabin construction |
| CN201040693Y (en) * | 2007-05-08 | 2008-03-26 | 焦世瑜 | Domestic weight hoister |
| CN103350971A (en) * | 2013-07-04 | 2013-10-16 | 中铁二十一局集团第三工程有限公司 | Device for assembling and disassembling construction jumbo in tunnel |
| CN203255870U (en) * | 2013-04-12 | 2013-10-30 | 河南华北起重吊钩有限公司 | Double-hook group device |
| CN203753420U (en) * | 2014-02-11 | 2014-08-06 | 中航飞机股份有限公司西安飞机分公司 | Device for lifting assembling parts in aircraft cabin |
-
2014
- 2014-02-11 CN CN201410047885.0A patent/CN103754387A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4858855A (en) * | 1987-06-04 | 1989-08-22 | Aerospatiale Societe Nationale Industrielle | Autonomous onboard loading device for a cargo-aircraft |
| RU2076831C1 (en) * | 1990-04-23 | 1997-04-10 | Акционерное общество открытого типа "Нижегородский авиастроительный завод "Сокол" | Device for transportation, hoisting and suspending of cargo on flying vehicles |
| US7270297B2 (en) * | 2004-01-30 | 2007-09-18 | The Boeing Company | Hoist for aircraft cabin construction |
| CN201040693Y (en) * | 2007-05-08 | 2008-03-26 | 焦世瑜 | Domestic weight hoister |
| CN203255870U (en) * | 2013-04-12 | 2013-10-30 | 河南华北起重吊钩有限公司 | Double-hook group device |
| CN103350971A (en) * | 2013-07-04 | 2013-10-16 | 中铁二十一局集团第三工程有限公司 | Device for assembling and disassembling construction jumbo in tunnel |
| CN203753420U (en) * | 2014-02-11 | 2014-08-06 | 中航飞机股份有限公司西安飞机分公司 | Device for lifting assembling parts in aircraft cabin |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108820244A (en) * | 2018-06-26 | 2018-11-16 | 刘先平 | A kind of aircraft tail propeller assembling Intelligent treatment equipment |
| CN108820244B (en) * | 2018-06-26 | 2021-08-06 | 汉中万利航空装备制造有限公司 | Intelligent processing equipment is used in equipment of aircraft fin screw |
| CN111993981A (en) * | 2020-08-31 | 2020-11-27 | 重庆领直航科技有限公司 | Unmanned aerial vehicle loading and unloading device and shelter |
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| PB01 | Publication | ||
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140430 |