CN113770677A - Working platform for internal assembly of large airplane body - Google Patents
Working platform for internal assembly of large airplane body Download PDFInfo
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- CN113770677A CN113770677A CN202111103454.8A CN202111103454A CN113770677A CN 113770677 A CN113770677 A CN 113770677A CN 202111103454 A CN202111103454 A CN 202111103454A CN 113770677 A CN113770677 A CN 113770677A
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- course
- airplane
- assembly
- guide rails
- working platform
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25H—WORKSHOP EQUIPMENT, e.g. FOR MARKING-OUT WORK; STORAGE MEANS FOR WORKSHOPS
- B25H1/00—Work benches; Portable stands or supports for positioning portable tools or work to be operated on thereby
- B25H1/02—Work benches; Portable stands or supports for positioning portable tools or work to be operated on thereby of table type
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a working platform for internal assembly of a large-scale airplane body, which comprises two groups of process joint components, two groups of steel pipe components, a group of honeycomb plate components and a group of series light rail components, wherein the process joint components are symmetrically fixed on side frames at two sides of the airplane body through process hole shafts on frames of the airplane body, the steel pipe components are symmetrically erected on the process joint, the honeycomb plate components are sequentially laid on the steel pipe components along the course of the airplane to form the working platform, and the series light rail components are arranged at the bottom of the honeycomb plate components to realize bottom hoisting of the working platform. The landing-leg-free working platform is realized by the aid of the fabrication holes in the frame of the airplane, the hoisting function inside the airplane body is realized by the aid of the course and the unfolding-direction light guide rail at the bottom of the platform, repeated work of repeatedly building the large airplane working platform is solved, the problem of difficult hoisting inside the large airplane barrel section is solved, and the quality and the efficiency of airplane assembly are guaranteed.
Description
Technical Field
The invention relates to the technical field of assembly of large airplane fuselages in the aviation manufacturing industry, in particular to a working platform for internal assembly of the large airplane fuselages.
Background
Aircraft technical equipment always occupies a great position in the aviation manufacturing industry, and the technical level of the aircraft technical equipment directly influences the quality and progress of aircraft assembly. The working platform is one of important devices in the process of assembling the airplane, and an operator finishes the assembling work of each part and assembly of the airplane on the working platform. With the vigorous development of the aircraft manufacturing industry, aviation enterprises must put forward higher updating requirements on process equipment under the double competition of industry and market, and the seeking of a rapid and efficient working platform is imperative.
The overall length of a large aircraft fuselage is about 20m, and the diameter is about 5.5 m. Before the airplane floor is not installed, the operation of the upper part of the airplane cylinder section is completed by adopting a method of building a working platform and supporting legs on a bottom lattice frame in the airplane body. When the airplane floor is assembled on the bottom frame, the working platform needs to be dismantled, and after the floor is assembled, the working platform is rebuilt on the airplane floor again to enable the upper part and the lower part of the airplane cylinder section to work simultaneously. Because the fuselage is longer, and the technology platform need cover whole fuselage length, and required platform plate and landing leg are in large quantity, and weight is heavier, and the ordinary crane in the factory building can't be used in the fuselage inside, and whole build, dismouting and floor transportation process can only rely on the manpower transport, and work load is big, and repeatability work is more, and work efficiency is extremely low.
In view of the above, there is a need to design a process working platform which is light in weight, convenient for manual movement, fast in assembly and capable of realizing internal hoisting of a machine body.
Disclosure of Invention
The application aims to provide a working platform for assembling and using a large airplane fuselage inside.
The technical scheme adopted by the invention for solving the technical problems is as follows: the utility model provides a work platform for large-scale aircraft fuselage internal assembly uses, contain two sets of technology joint subassemblies, two sets of steel pipe assembly, a set of honeycomb panel subassembly, a set of light rail subassembly of establishing ties, two sets of technology joint subassemblies are connected and the symmetry is fixed on the side frame of fuselage both sides through the fabrication hole cooperation with aircraft fuselage frame, two sets of steel pipe assembly symmetric frames are on technology joint, honeycomb panel subassembly is laid on the steel pipe subassembly in proper order along aircraft course, form work platform, the light rail unit mount of establishing ties is in honeycomb panel subassembly bottom, realize work platform's bottom hoist and mount.
The process joint assembly comprises a process joint, a quick assembling and disassembling pipe clamp and a pipe clamp mounting seat, wherein the side surface of the process joint is in an inverted Y shape, the upper end of the process joint is in an insert lug structure and is connected with a process hole in an airplane side frame through a screw rod, the lower end of the process joint is abutted against the airplane side frame, a platform mounting pipe clamp mounting seat is arranged on one side of the process joint, and the quick assembling and disassembling pipe clamp is mounted on the pipe clamp mounting seat.
The honeycomb panel assembly comprises a plurality of same light honeycomb panels, edges for reinforcement are arranged on the periphery of the light honeycomb panels, two hooks for lapping with the steel tube assembly are arranged at two ends in the length direction respectively, and a threaded sleeve for connecting with the series light rail is arranged at the bottom of the light honeycomb panel assembly.
The serial light rail assembly comprises a plurality of course guide rails, a plurality of course trolleys, a plurality of unfolding guide rails and a plurality of unfolding chain blocks, wherein the course guide rails are divided into two groups and are symmetrically arranged below the honeycomb panel along the central axis of the machine body, the course trolleys are arranged below the course guide rails and can slide along the course, the unfolding guide rails are connected with the course guide rails in series through the course trolleys, and the chain blocks are arranged on the unfolding guide rails and can slide along the unfolding guide rails, so that the hoisting in each direction in the machine body is realized.
Has the advantages that: according to the working platform for the internal assembly of the large-scale airplane body, the landing-leg-free working platform is realized by utilizing the fabrication holes on the frame of the airplane, the hoisting function in the body is realized by utilizing the course and the unfolding direction of the bottom of the platform, the repeated work of repeatedly building the large-scale airplane working platform is solved, the difficult problem of hoisting the interior of the large-scale airplane cylinder section is solved, and the quality and the efficiency of the airplane assembly are ensured. The working platform is simple in structure, simple and convenient to mount and dismount, original workload is greatly reduced, and quality safety of products is guaranteed. The method can be directly popularized to the technical field of installation and lifting of airplane floors of different sizes and types in the aviation manufacturing industry.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a schematic view of a working platform for the internal assembly of an aircraft fuselage
FIG. 2 schematic view of a process connection assembly
FIG. 3 is a schematic view of the lap joint of the lightweight honeycomb panel and the steel pipe assembly
FIG. 4 schematic view of a series light rail assembly
The reference numbers in the figures illustrate: 1, a process connection assembly; 2, a steel pipe component; 3 a honeycomb panel assembly; 4 light rail components are connected in series; 5, a process joint; 6, quickly disassembling and assembling the pipe clamp; 7, pipe clamp mounting seats; 8 light honeycomb board; 9, hanging hooks; 10 course guide rail; 11, a course trolley; 12 a spanwise rail; 13 extending to the chain block.
Detailed Description
Referring to the attached drawings, the invention provides a working platform for assembling the interior of a large airplane body.
Seen from figure 1, a work platform for large aircraft fuselage internal assembly, contain two sets of technology joint subassemblies 1, two sets of steel pipe subassembly 2, a set of honeycomb panel subassembly 3, a set of light rail subassembly 4 of establishing ties, two sets of technology joint subassemblies 1 are installed on the fabrication hole of aircraft both sides frame along fuselage axis symmetry, two sets of steel pipe subassembly 2 symmetric frames are on technology joint subassembly 1, honeycomb panel subassembly 3 is laid in proper order on steel pipe subassembly 2 along aircraft course, form two layers of work platform, light rail subassembly 4 of establishing ties is installed in the honeycomb panel bottom, realize the bottom hoist and mount of work platform.
As shown in figure 2, the process joint assembly 1 comprises a process joint 5, a quick assembly disassembly pipe clamp 6 and a pipe clamp mounting seat 7, wherein the side surface of the process joint 5 is in an inverted Y shape, the upper end of the process joint is in an insert lug structure and is connected with a process hole in an airplane side frame through a screw rod, the lower end of the process joint is abutted against the airplane side frame, a platform mounting pipe clamp mounting seat 7 is arranged on one side of the process joint 5, and the quick assembly disassembly pipe clamp 6 is mounted on the pipe clamp mounting seat 7.
As seen from figure 3, the honeycomb plate component 3 comprises a plurality of same light honeycomb plates 8, the peripheries of the light honeycomb plates 8 are provided with edges for reinforcement, two ends in the length direction are respectively provided with two hooks 9 for lapping with the steel pipe component 2, and the bottom of each light honeycomb plate component is provided with a threaded sleeve for connecting with a series light rail.
As shown in fig. 4, the tandem light rail assembly 4 includes a plurality of heading guide rails 10, a plurality of heading trolleys 11, a plurality of span-wise guide rails 12, and a plurality of span-wise chain blocks 13, the heading guide rails 10 are divided into two groups and symmetrically arranged below the honeycomb panel assembly 3 along the central axis of the machine body, the heading trolleys 11 are installed below the heading guide rails 10 and can slide along the heading, the span-wise guide rails 12 are in tandem connection with the heading guide rails 10 through the heading trolleys 11, and the chain blocks 13 are installed on the span-wise guide rails 12 and can slide along the span-wise guide rails 12, so as to realize hoisting in each direction inside the machine body.
According to the working platform for the internal assembly of the large-scale airplane body, the landing-leg-free working platform is realized by utilizing the fabrication holes on the frame of the airplane, the hoisting function in the body is realized by utilizing the course and the unfolding direction of the bottom of the platform, the repeated work of repeatedly building the large-scale airplane working platform is solved, the difficult problem of hoisting the interior of the large-scale airplane cylinder section is solved, and the quality and the efficiency of the airplane assembly are ensured. The working platform is simple in structure, simple and convenient to mount and dismount, original workload is greatly reduced, and quality safety of products is guaranteed. The method can be directly popularized to the technical field of installation and lifting of airplane floors of different sizes and types in the aviation manufacturing industry.
Claims (4)
1. The utility model provides a work platform that large-scale aircraft fuselage internal assembly used, its characterized in that contains two sets of technology joint subassemblies, two sets of steel pipe assembly, a set of honeycomb panel subassembly, a set of light rail subassembly of establishing ties, two sets of technology joint subassemblies are connected and the symmetry is fixed on the side frame of fuselage both sides through the fabrication hole cooperation with aircraft fuselage frame, two sets of steel pipe assembly symmetric frames are on technology joint, honeycomb panel subassembly is laid on the steel pipe subassembly in proper order along aircraft course, form work platform, the light rail subassembly of establishing ties is installed in honeycomb panel subassembly bottom, realize work platform's bottom hoist and mount.
2. The work platform for the internal assembly of the large aircraft fuselage according to claim 1, wherein the process joint assembly comprises a process joint, a quick-release pipe clamp and a pipe clamp mounting seat, the side surface of the process joint is in an inverted Y shape, the upper end of the process joint is in an insertion lug structure and is connected with a process hole in the aircraft side frame through a screw, the lower end of the process joint abuts against the aircraft side frame, the platform mounting pipe clamp mounting seat is arranged on one side of the inverted Y shape, and the quick-release pipe clamp is mounted on the pipe clamp mounting seat.
3. The working platform for the internal assembly of the large aircraft fuselage according to claim 1, wherein the honeycomb panel assembly comprises a plurality of identical light honeycomb panels, the light honeycomb panels are provided with edges for reinforcement at the periphery, two hooks for lapping with the steel tube assembly are respectively arranged at two ends in the length direction, and threaded sleeves for connecting with the series light rails are arranged at the bottom.
4. The working platform for the internal assembly of the large aircraft body as claimed in claim 1, wherein the series light rail assembly comprises a plurality of course guide rails, a plurality of course trolleys, a plurality of span guide rails and a plurality of span chain blocks, the course guide rails are divided into two groups and symmetrically arranged below the honeycomb panel along the central axis of the large aircraft body, the course trolleys are arranged below the course guide rails and can slide along the course, the span guide rails are connected in series with the course guide rails through the course trolleys, and the chain blocks are arranged on the span guide rails and can slide along the span guide rails, so that the hoisting in each direction of the internal of the large aircraft body is realized.
Priority Applications (1)
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CN202111103454.8A CN113770677B (en) | 2021-09-18 | 2021-09-18 | Working platform for internal assembly of large airplane body |
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CN202111103454.8A CN113770677B (en) | 2021-09-18 | 2021-09-18 | Working platform for internal assembly of large airplane body |
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CN113770677A true CN113770677A (en) | 2021-12-10 |
CN113770677B CN113770677B (en) | 2022-09-20 |
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Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5560102A (en) * | 1992-10-13 | 1996-10-01 | The Boeing Company | Panel and fuselage assembly |
CN101891010A (en) * | 2009-05-18 | 2010-11-24 | 张楚 | Mobile operation platform device for ship |
CN102849218A (en) * | 2012-09-04 | 2013-01-02 | 西安飞机工业(集团)有限责任公司 | Mounting beam for auxiliary power unit of aircraft |
CN103921954A (en) * | 2014-04-25 | 2014-07-16 | 浙江大学 | Digitizing correction method for aircraft panel assembling deformation based on triaxial numerical control locator |
CN205257816U (en) * | 2016-01-06 | 2016-05-25 | 包头市金陵风电科技有限公司 | Be used for lifting machine in wind generating set cabin |
US20170211284A1 (en) * | 2016-01-26 | 2017-07-27 | The Boeing Company | Scaffolding apparatus and related methods |
CN108238281A (en) * | 2017-10-17 | 2018-07-03 | 西安飞机工业(集团)有限责任公司 | A kind of aircraft hold moves assembly work platform |
CN208882129U (en) * | 2018-08-30 | 2019-05-21 | 哈尔滨飞机工业集团有限责任公司 | A kind of aircraft maintenance platform of fast demountable |
US20200002025A1 (en) * | 2018-06-27 | 2020-01-02 | Airbus Operations Gmbh | Assembly System For An Automated Internal Assembly Of An Aircraft Fuselage |
-
2021
- 2021-09-18 CN CN202111103454.8A patent/CN113770677B/en active Active
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5560102A (en) * | 1992-10-13 | 1996-10-01 | The Boeing Company | Panel and fuselage assembly |
CN101891010A (en) * | 2009-05-18 | 2010-11-24 | 张楚 | Mobile operation platform device for ship |
CN102849218A (en) * | 2012-09-04 | 2013-01-02 | 西安飞机工业(集团)有限责任公司 | Mounting beam for auxiliary power unit of aircraft |
CN103921954A (en) * | 2014-04-25 | 2014-07-16 | 浙江大学 | Digitizing correction method for aircraft panel assembling deformation based on triaxial numerical control locator |
CN205257816U (en) * | 2016-01-06 | 2016-05-25 | 包头市金陵风电科技有限公司 | Be used for lifting machine in wind generating set cabin |
US20170211284A1 (en) * | 2016-01-26 | 2017-07-27 | The Boeing Company | Scaffolding apparatus and related methods |
CN108238281A (en) * | 2017-10-17 | 2018-07-03 | 西安飞机工业(集团)有限责任公司 | A kind of aircraft hold moves assembly work platform |
US20200002025A1 (en) * | 2018-06-27 | 2020-01-02 | Airbus Operations Gmbh | Assembly System For An Automated Internal Assembly Of An Aircraft Fuselage |
CN208882129U (en) * | 2018-08-30 | 2019-05-21 | 哈尔滨飞机工业集团有限责任公司 | A kind of aircraft maintenance platform of fast demountable |
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