CN113102679A - Flexible positioning frame for positioning aircraft wall plate - Google Patents
Flexible positioning frame for positioning aircraft wall plate Download PDFInfo
- Publication number
- CN113102679A CN113102679A CN202110344296.9A CN202110344296A CN113102679A CN 113102679 A CN113102679 A CN 113102679A CN 202110344296 A CN202110344296 A CN 202110344296A CN 113102679 A CN113102679 A CN 113102679A
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- frame
- positioning
- movable base
- aircraft
- flexible positioning
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J15/00—Riveting
- B21J15/38—Accessories for use in connection with riveting, e.g. pliers for upsetting; Hand tools for riveting
- B21J15/44—Rivet hole positioners
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J15/00—Riveting
- B21J15/38—Accessories for use in connection with riveting, e.g. pliers for upsetting; Hand tools for riveting
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
- Automatic Assembly (AREA)
Abstract
The invention discloses a flexible positioning frame for an aircraft panel, wherein the aircraft panel comprises a stringer and a skin fixed on the stringer, the flexible positioning frame comprises a frame main body, a plurality of inner profiled sheets which are arranged in parallel and used for fixing the aircraft panel are arranged in the frame main body, and two ends of the inner profiled sheet positioned between the two outer inner profiled sheets are respectively arranged on the frame main body through movable base components. The invention is convenient for the installation and the disassembly of the aircraft wallboard, and can improve the rigidity of the aircraft wallboard in a processing area and the processing rigidity of the positioning frame.
Description
Technical Field
The invention relates to the technical field of aircraft manufacturing, in particular to a flexible positioning frame for positioning an aircraft wallboard.
Background
In the manufacturing process of modern airplanes, the requirements on the efficiency and the precision of structural assembling and connecting are higher and higher, so that automatic hole-making connecting equipment represented by an automatic hole-making system and an automatic drilling and riveting system is widely applied to the airplane assembling process. The automatic hole making and riveting technology has the characteristics of good drilling/riveting quality, high production efficiency, good labor condition, easy operation control and the like, so the development of the aviation manufacturing riveting technology in China is greatly promoted.
No matter the automatic hole making system based on an industrial robot or a large numerical control machine tool or the automatic drilling and riveting system consisting of an automatic drilling and riveting machine and a numerical control bracket, a positioning tool for positioning and clamping an aircraft product assembly is required. The traditional structural form of this kind of frock has two kinds: one is that a universal bracket is provided with a connecting angle seat for connecting an appearance clamping plate, and a set of different positioning clamping plates are replaced for different product objects; the other type is a form of sleeving a small frame by a large frame, namely, a special small frame for positioning is designed for each different product, and a fixing and clamping device of the small frame is arranged on the large universal surrounding frame. Both of these structural forms have practical applications, but also expose some problems: for the replacement of the clamping plates, different positioning clamping plates are needed for different products, the clamping plates are large in number, the clamping plates need to be carefully identified during replacement, the workload of replacement of the clamping plates is large, and mistakes are easy to make; to "big frame cover small frame" formula, different product objects have dedicated location frock, difficult the mistake of during the use, but because a brill rivets the work of riveting that bores of system need undertake a plurality of models, numerous wallboard products for the quantity of enclosing the frame for a short time is huge, and then leads to enclosing the frame for a short time and deposit and need very big area, need enclose the frame hoist and mount to enclosing the frame greatly for a short time in addition when using, because it is relatively poor to enclose the frame rigidity for a short time, location installation difficulty, the installation cycle is long.
In addition, modern aircraft assembly lines are often arranged in a multi-station assembly mode, and parts to be machined, such as aircraft wall panels, need to be transferred between stations. Traditional transportation mode is like hoist and mount, track movement etc. inefficiency, lack flexibility, positioning speed is slow, collide with station facility easily, can not adapt to current aircraft assembly demand, consequently can design a location frame that can bear, fix a position the wallboard frock, only needs each station department design unified mounting structure of processing line, just can make this location frame install on each station fast, accurate and reliably, and loading and unloading are simple and convenient rapid moreover.
The patent specification with the publication number of CN106514343A discloses a positioning tool for automatic hole-making riveting of an aircraft panel, which comprises a frame, a connecting plate, a positioning clamping plate, a positioning connecting seat, a shape positioning piece and a skin pressing piece, wherein the frame is of a rectangular frame structure, and the end of the frame is provided with the connecting plate which is connected with a supporting framework of an automatic hole-making riveting system; the upper surfaces of two longitudinal beams of the frame are provided with two parallel guide rails, the outer sides of the guide rails are provided with positioning plates, the positioning plates are provided with positioning holes corresponding to different wall plate products and mark product information, and the bottoms of the positioning connecting seats are provided with sliding blocks capable of sliding on the guide rails; the positioning connecting seat is provided with a connecting hole for fixing the positioning connecting seat on the frame, and the positioning connecting seat and the positioning plate are fixed through a positioning bolt; the location cardboard spanes between two longerons, the location cardboard both ends are connected with the last corresponding location connecting seat of two guide rails, the longitudinal position of location cardboard is confirmed according to the position of locating hole on the locating plate, install a plurality of appearance setting elements on every location cardboard, be equipped with one on every appearance setting element and follow the location axle that the appearance normal direction carries out the adjustment of stretching out and drawing back, adjust the location axle on a plurality of appearance setting elements simultaneously, make its location axle end form the wallboard product shape of corresponding position department, the product laminating is at the location axle head of appearance setting element, install the covering at location cardboard both ends and compress tightly the piece and compress tightly the product, accomplish the product location. The locating clamping plate is fixed in the scheme, and the rigidity of a processing area can not be guaranteed when the aircraft panel is processed.
Disclosure of Invention
The invention aims to provide a flexible positioning frame for positioning an aircraft panel, which is convenient for the installation and the disassembly of the aircraft panel and can improve the rigidity of the aircraft panel in a processing area and the processing rigidity of the positioning frame.
The flexible positioning frame comprises a frame body, a plurality of inner type plates which are arranged in parallel and used for fixing the aircraft wallboard are arranged in the frame body, and two ends of the inner type plate between the two outer inner type plates are respectively installed on the frame body through movable base assemblies.
According to the scheme, the movable inner template is arranged, the inner template in the part can move within a certain range on the horizontal plane, the riveting processing coverage range is enlarged, and meanwhile, the rigidity of the aircraft wallboard in the processing area is improved by adjusting the distance between the adjacent inner templates. Meanwhile, on the positioning frame capable of being repeatedly installed on the aircraft wall plate, tedious work of hoisting the wall plate, repositioning the wall plate and the like is omitted, and riveting working time is greatly saved.
Preferably, the inner mould plate is provided with a groove for clamping a stringer of the aircraft wall plate, and the inner mould plate is provided with fasteners for clamping the stringer corresponding to the positions of the grooves.
Preferably, the movable base assembly includes a movable base, a first cylinder driving the movable base to move in a length direction of the frame body, and a second cylinder driving the movable base to move in a width direction of the frame body.
The movable base is driven by the two cylinders to move along the length direction and the width direction of the frame main body, and the control is stable and reliable.
Further preferably, the movable base assembly further comprises a limiting mechanism for limiting the movable base;
the limiting mechanism comprises a third cylinder for limiting the length direction of the frame body of the movable base and a fourth cylinder for limiting the width direction of the frame body of the movable base.
Through setting up stop gear, when the interior template of hopeing not removes, fix a position and lock movable base.
Preferably, the outer walls of the two sides of the frame main body are also provided with guide adapting devices for positioning the frame main body;
the direction adaptation device is including setting up slide rail on the frame bulk phase wall, with slide rail complex slider, setting up the cavity post on the slider and carrying out spacing elasticity to the slider and draw the piece.
The hollow column of the guide adapting device can be quickly embedded into the positioning guide block on the machine corresponding to the station during installation and can also quickly slide out during disassembly. After the installation is successful, the air cylinder on the station machine can complete the fastening of the frame body. Specifically, the movable end of the cylinder extends into the hollow column to form a plug pin structure.
The guide adapting device can ensure that the positioning guide block on the corresponding station machine adapts to the width of the frame body within a certain elastic range by means of the elastic pulling piece, and reduces the assembly stress between the frame body and the positioning guide block on the corresponding station machine.
Further preferably, the outer walls of the two sides of the frame main body and the positions at the four corners are respectively provided with a guiding adaptive device. Four guiding adaptation devices are arranged at four corners, so that the stability and the processing rigidity of the frame main body are further improved.
Preferably, the inner mould plate is provided with an adsorption device for adsorbing a skin of the aircraft panel.
Preferably, the bottom of the frame body is provided with a positioning block for preliminary positioning of the frame body.
The invention has the beneficial effects that:
(1) the aircraft wallboard is on the locating frame of repeatedly mountable, has saved loaded down with trivial details work such as hoist and mount wallboard, repositioning wallboard, has saved riveting operating time greatly.
(2) A part of inner template is connected with the frame body by the movable base, and the part of inner template can move in a certain range on the horizontal plane, so that the riveting processing coverage range is enlarged, and the rigidity of the part in the processing area can be increased by adjusting the distance between adjacent inner templates.
(3) All install direction adaptation device on four angles of frame main part, the well hollow column on this direction adaptation device can be when the installation imbed fast and correspond the position guide block of going into on the station machine, also can roll off fast when dismantling, can accomplish the fastening of frame main part by the cylinder on the station machine after the installation is successful, has optimized the dismantlement process well, has also increaseed positioning frame's processing rigidity.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is an enlarged view of portion A of FIG. 1;
FIG. 3 is a schematic structural view of a guide adaptation device;
FIG. 4 is a schematic structural view of the positioning guide block;
FIG. 5 is a schematic structural diagram of a V-shaped positioning block.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1-5, a flexible positioning frame for an aircraft panel, the aircraft panel includes a stringer and a skin fixed on the stringer, the flexible positioning frame includes a frame body 1, a plurality of inner mold plates 2 arranged in parallel and used for fixing the aircraft panel are arranged in the frame body 1, and both ends of the inner mold plate 2 located between the two outer inner mold plates 2 are respectively installed on the frame body 1 through a movable base assembly 3.
In the embodiment, four parallel inner shaping plates 2 are arranged in a frame main body 1, two ends of two outer inner shaping plates 2 are arranged on a fixed base 4 arranged on the frame main body 1, namely the two outer inner shaping plates 2 are immovable, and the two inner shaping plates 2 are used for fixing two end parts of an aircraft wall plate; two ends of the two inner shaping plates 2 at the inner side are arranged on the frame main body 1 through the movable base component 3; the inner mould plate 2 is provided with grooves 21 for the stringer of the aircraft wall to be clamped into, and the inner mould plate 2 is provided with fasteners for clamping the stringer corresponding to the positions of the grooves 21, and the fasteners belong to the prior art, so the structure of the fasteners is not described in detail here.
The movable base assembly 3 includes a movable base 31, a first cylinder 32 that drives the movable base 31 to move in the length direction of the frame body 1, and a second cylinder 33 that drives the movable base 31 to move in the width direction of the frame body 1; specifically, a first guide rail 34 is mounted on the frame body 1 along the length direction of the frame body 1, a first slide seat 35 is arranged on the first guide rail 34, and the first air cylinder 32 can drive the first slide seat 35 to slide on the first guide rail 34; a second guide rail 36 along the width direction of the frame body is arranged on the first slide seat 35, a second slide seat 37 is arranged on the second guide rail 36, the second air cylinder 33 drives the second slide seat 37 to slide on the second guide rail 36, the movable base 31 is correspondingly fixed on the second slide seat 37, and the end parts of the two inner shaping plates 2 at the inner side are fixed on the corresponding movable base 31 to realize the movement in the direction of X, Y.
In order to prevent the two inner templates on the inner sides from moving when the inner templates are static, the movable base component 3 also comprises a limiting mechanism for locking the movable base 31; the limiting mechanism comprises a third air cylinder 38 for limiting the movable base 31 in the length direction of the frame body 1 and a fourth air cylinder 39 for limiting the movable base 31 in the width direction of the frame body 1; specifically, the third cylinder 38 is installed on the first slide seat 35, the fourth cylinder 39 is installed on the second slide seat 37, a first limiting hole which forms a bolt structure by matching with the movable end of the third cylinder 38 is formed in the corresponding frame main body 1, and a second limiting hole which forms a bolt structure by matching with the movable end of the fourth cylinder 39 is formed in the first slide seat 35.
The outer walls of the two sides of the frame body 1 are also provided with a guiding adaptive device 5 for positioning the frame body 1; the guiding adaptation device 5 comprises a sliding rail 51 arranged on the side wall of the frame body, a sliding block 52 matched with the sliding rail 51, a hollow column 53 arranged on the sliding block 52 and an elastic pulling piece 54 for limiting the sliding block 52.
During specific positioning, the hollow column 53 of the guide adapting device 5 can be quickly embedded into the positioning guide block 6 on the corresponding station machine and can also quickly slide out during disassembly. After the positioning and installation are successful, the fastening of the frame body 1 can be completed by an air cylinder on a station machine. Specifically, the movable end of the cylinder extends into the hollow post 53 to form a plug structure.
The elastic pulling member 54 is specifically two springs, one end of each of the two springs is fixed to the upper end and the lower end of the sliding block 52, the other end of each of the two springs is fixed to the outer wall of the frame body 1 through a connecting member 55, and the sliding block 52 can move within a small range from top to bottom under the pulling force of the upper spring and the lower spring, so that the positioning guide block 6 on the corresponding station machine can be ensured to adapt to the width of the frame body 1 within a certain elastic range.
In some optional embodiments, one guiding adaptive device 5 is respectively arranged at the outer walls of two sides of the frame body 1 and at four corners, and four guiding adaptive devices 5 are arranged at four corners, so that the stability and the processing rigidity of the frame body 1 are further improved.
In some alternative embodiments, the inner mould plate 2 is provided with a suction device 7 for sucking the skin of the aircraft panel, and the suction device 7 may be a vacuum chuck.
In some optional embodiments, the bottom of the frame body 1 is provided with a positioning block 8 for preliminary positioning of the frame body 1; specifically, the positioning block 8 is semi-cylindrical, the two ends of the bottom of the frame body 1 are respectively provided with a longitudinal positioning block 8, and the center of the bottom of the frame body 1 is provided with a transverse positioning block 8; when the frame body 1 is preliminarily positioned, the three semi-cylindrical positioning blocks 8 are placed into the grooves of the V-shaped positioning blocks 9 on the corresponding station machine.
The specific working process of the invention is as follows:
1) positioning installation of positioning frame
Three semi-cylindrical positioning blocks 8 at the bottom of the frame body 1 are aligned to grooves of V-shaped positioning blocks 9 in the station machine, after primary positioning is completed, a hollow column 53 of the guide adapting device 5 can be embedded into a positioning guide block 6 in the corresponding station machine to complete positioning, and a cylinder in the corresponding station machine enables a movable end to stretch into the hollow column 53 and tightly press the frame body 1. When the device is disassembled, the air cylinder is canceled for pressing, and the guide adapting device 5 slides out of the positioning guide block 6 of the station machine along the opposite direction.
2) Installation and processing of aircraft wall panels
The aircraft panel, with the stringers already attached to the skin, is fitted to the inner profile 2. The stringer is mounted in the groove 21 of the inner plate 2, clamped by the fastener, and sucked by the adsorption device 7. In the processing process, the positions of the inner shaping plates 2 are adjusted by controlling the first air cylinder 32 and the second air cylinder 33, so that the corresponding areas can have higher rigidity when all areas of the aircraft wall plate are processed.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that various changes in the embodiments and/or modifications of the invention can be made, and equivalents and modifications of some features of the invention can be made without departing from the spirit and scope of the invention.
Claims (8)
1. A flexible positioning frame for positioning an aircraft panel, the aircraft panel including stringers and a skin secured to the stringers, the flexible positioning frame comprising a frame body, characterized in that: a plurality of inner templates which are arranged in parallel and used for fixing the aircraft wall panel are arranged in the frame main body, and two ends of the inner template which is positioned between the two outer inner templates are respectively arranged on the frame main body through movable base components.
2. The flexible positioning frame of claim 1, wherein: the inner shaping plate is provided with grooves for clamping stringers of the aircraft wall plate, and fasteners for clamping the stringers are arranged on the inner shaping plate corresponding to the positions of the grooves.
3. The flexible positioning frame of claim 1, wherein: the movable base assembly comprises a movable base, a first air cylinder and a second air cylinder, wherein the first air cylinder drives the movable base to move along the length direction of the frame body, and the second air cylinder drives the movable base to move along the width direction of the frame body.
4. The flexible positioning frame of claim 3, wherein: the movable base component also comprises a limiting mechanism for limiting the movable base;
the limiting mechanism comprises a third cylinder for limiting the length direction of the frame body of the movable base and a fourth cylinder for limiting the width direction of the frame body of the movable base.
5. The flexible positioning frame of claim 1, wherein: the outer walls of the two sides of the frame main body are also provided with a guiding adaptive device for positioning the frame main body;
the direction adaptation device is including setting up slide rail on the frame bulk phase wall, with slide rail complex slider, setting up the cavity post on the slider and carrying out spacing elasticity to the slider and draw the piece.
6. The flexible positioning frame of claim 5, wherein: and the outer walls of two sides of the frame main body and the positions at four corners are respectively provided with a guiding adaptation device.
7. The flexible positioning frame of claim 1, wherein: and an adsorption device for adsorbing a skin of the aircraft wallboard is arranged on the inner shaping plate.
8. The flexible positioning frame of claim 1, wherein: the bottom of the frame body is provided with a positioning block for preliminarily positioning the frame body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110344296.9A CN113102679B (en) | 2021-03-30 | 2021-03-30 | Flexible positioning frame for positioning aircraft wall plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110344296.9A CN113102679B (en) | 2021-03-30 | 2021-03-30 | Flexible positioning frame for positioning aircraft wall plate |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113102679A true CN113102679A (en) | 2021-07-13 |
| CN113102679B CN113102679B (en) | 2022-09-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110344296.9A Active CN113102679B (en) | 2021-03-30 | 2021-03-30 | Flexible positioning frame for positioning aircraft wall plate |
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| Country | Link |
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| CN (1) | CN113102679B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115540791A (en) * | 2022-12-01 | 2022-12-30 | 成都市鸿侠科技有限责任公司 | Aircraft skin appearance precision detection device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103921116A (en) * | 2014-04-24 | 2014-07-16 | 浙江大学 | Flexible assembly system for aircraft panel |
| CN204035998U (en) * | 2014-06-27 | 2014-12-24 | 中航飞机股份有限公司西安飞机分公司 | Airframe wallboard flexible assembly platform |
| CN106514343A (en) * | 2016-12-14 | 2017-03-22 | 中航飞机股份有限公司西安飞机分公司 | Positioning tool and method for automatic drilling and riveting of aircraft panels |
| CN109920354A (en) * | 2017-12-12 | 2019-06-21 | 江苏荣大文化创意有限公司 | A kind of advertisement suspended structure of bus platform |
| CN110216235A (en) * | 2019-06-03 | 2019-09-10 | 西安飞机工业（集团）有限责任公司 | A kind of flexible fuselage wallboard assembly tooling and assembly method based on measured data |
-
2021
- 2021-03-30 CN CN202110344296.9A patent/CN113102679B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103921116A (en) * | 2014-04-24 | 2014-07-16 | 浙江大学 | Flexible assembly system for aircraft panel |
| CN204035998U (en) * | 2014-06-27 | 2014-12-24 | 中航飞机股份有限公司西安飞机分公司 | Airframe wallboard flexible assembly platform |
| CN106514343A (en) * | 2016-12-14 | 2017-03-22 | 中航飞机股份有限公司西安飞机分公司 | Positioning tool and method for automatic drilling and riveting of aircraft panels |
| CN109920354A (en) * | 2017-12-12 | 2019-06-21 | 江苏荣大文化创意有限公司 | A kind of advertisement suspended structure of bus platform |
| CN110216235A (en) * | 2019-06-03 | 2019-09-10 | 西安飞机工业（集团）有限责任公司 | A kind of flexible fuselage wallboard assembly tooling and assembly method based on measured data |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115540791A (en) * | 2022-12-01 | 2022-12-30 | 成都市鸿侠科技有限责任公司 | Aircraft skin appearance precision detection device |
| CN115540791B (en) * | 2022-12-01 | 2023-03-14 | 成都市鸿侠科技有限责任公司 | Aircraft skin appearance precision detection device |
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| CN113102679B (en) | 2022-09-06 |
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