CN112373713B - Large aircraft leading edge assembly hanging tool - Google Patents
Large aircraft leading edge assembly hanging tool Download PDFInfo
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- CN112373713B CN112373713B CN202011097150.0A CN202011097150A CN112373713B CN 112373713 B CN112373713 B CN 112373713B CN 202011097150 A CN202011097150 A CN 202011097150A CN 112373713 B CN112373713 B CN 112373713B
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- edge assembly
- leading edge
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- positioning
- airplane
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- 238000003825 pressing Methods 0.000 claims description 22
- 238000000034 method Methods 0.000 claims description 8
- 230000008569 process Effects 0.000 claims description 8
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 230000009466 transformation Effects 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 7
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 230000009471 action Effects 0.000 description 3
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000005056 compaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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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)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Load-Engaging Elements For Cranes (AREA)
Abstract
The invention discloses a large aircraft leading edge assembly hanging tool, which comprises a main truss and is arranged on the main truss: the device comprises a positioning device for fixing the front edge assembly of the airplane, a supporting device for supporting the front edge assembly of the airplane, a lifting ring for connecting an external pulling device, a universal wheel for hanging the tool to move and a ground supporting device for supporting and fixing. The invention is beneficial to improving the hoisting efficiency of the airplane front edge assembly, reducing the hoisting cost of the airplane front edge assembly, is easy to install and maintain and has higher application value in the field of airplane assembly and manufacturing.
Description
Technical Field
The invention belongs to the field of airplane digital assembly, and particularly relates to a large airplane front edge assembly hanging tool.
Background
In the aircraft assembly, the hanging tool of the aircraft assembly is essential technological equipment in the aircraft manufacturing process. The flexible hanging tool is a reconfigurable modularized and automatic hanging tool system, and aims to avoid designing and manufacturing traditional hanging tools special for hanging and assembling various airplane components, such as airplane wing hanging tools in patent applications with publication numbers of CN110921485A and CN 107253668A.
In recent years, the flexibility degree of the hanging tool for the aircraft front edge component adopted in China is improved, but the practical requirement of rapid assembly of the aircraft cannot be met. For example, traditional aircraft leading edge subassembly is hung frock is difficult to satisfy and all can carry out hoist and mount support and fixed needs to aircraft left and right leading edge subassembly, also is difficult to realize the requirement that can all carry out accurate location to aircraft left and right leading edge subassembly. The traditional aircraft hanging tool and the aircraft hanging tool with lower flexibility degree become important obstacles for improving the aircraft assembly efficiency and reducing the aircraft assembly manufacturing cost.
Meanwhile, the traditional hanging tool for the aircraft front edge assembly is low in functional integration level, and cannot provide some or all functions of the aircraft front edge assembly, such as being movable on the ground, being fixable on the ground and being capable of measuring the hanging angle, so that the hanging tool has an effect of preventing neglect in the hanging process of the aircraft front edge assembly, reduces the hanging assembly efficiency of the aircraft front edge assembly to a certain extent, and has negative effects on the aircraft assembly production period and the aircraft assembly manufacturing cost.
Disclosure of Invention
Aiming at the problems, the invention designs the large aircraft front edge assembly hanging tool which has the capabilities of respectively carrying out hoisting positioning and hoisting support on the left and right front edge assemblies of the large aircraft, and has high flexibility; meanwhile, the functions of hanging the tool for the aircraft front edge assembly, moving the ground, supporting and fixing the ground, measuring the inclination angle of the aircraft front edge assembly in the hoisting process and the like are integrated. The invention is beneficial to improving the hoisting efficiency of the airplane front edge assembly, reducing the hoisting cost of the airplane front edge assembly, is easy to install and maintain and has higher application value in the field of airplane assembly and manufacturing.
The utility model provides a frock is hung to large aircraft leading edge subassembly, includes the main part truss, installs on the main part truss: the device comprises a positioning device for fixing the front edge assembly of the airplane, a supporting device for supporting the front edge assembly of the airplane, a lifting ring for connecting an external pulling device, a universal wheel for hanging the tool to move and a ground supporting device for supporting and fixing.
Several alternatives are provided below, but not as an additional limitation to the above general solution, but merely as a further addition or preference, each alternative being combinable individually for the above general solution or among several alternatives without technical or logical contradictions.
Optionally, the main truss is a beam truss made of steel.
Optionally, the positioning devices are positioning structures symmetrically arranged on the main truss in an array; the positioning device is arranged in the V-shaped groove of the main truss through the locking pin;
the positioning device comprises a T-shaped beam, two ends of the T-shaped beam extend into the V-shaped groove, a vertical pressing block and a vertical positioning block which are in a matched action are mounted on the T-shaped beam, a horizontal transverse positioning block and a horizontal transverse pressing block which are in a matched action, and a horizontal longitudinal positioning block and a horizontal longitudinal pressing block which are in a matched action.
Optionally, the front edge assembly of the aircraft can be vertically fixed by rotating a knob on the vertical pressing block, and the vertical positioning block provides a vertical positioning reference for the front edge assembly of the aircraft; the front edge component of the airplane can be horizontally and transversely fixed by rotating a knob on a horizontal transverse pressing block, and a horizontal transverse positioning block provides a horizontal transverse positioning reference for the front edge component of the airplane; the front edge assembly of the airplane is horizontally and longitudinally fixed by rotating a knob on the horizontal longitudinal pressing block, and the horizontal longitudinal positioning block provides a horizontal longitudinal positioning reference for the front edge assembly of the airplane.
Optionally, the T-shaped beam and the V-shaped groove are connected by a locking pin. Corresponding T-shaped beams can be respectively installed for the two conditions of hanging the left front edge assembly and the right front edge assembly of the airplane, so that the hoisting and positioning of the front edge assembly of the airplane under the two conditions are realized, and the quick connection is realized through the locking pin.
Optionally, the supporting devices are supporting structures symmetrically arranged on the main truss in an array; the supporting device comprises a supporting plate and auxiliary supporting feet for supporting the front edge assembly of the airplane;
the supporting device further comprises a middle rotating shaft, and the supporting plates rotate around the middle rotating shaft to carry out structural symmetry transformation and are respectively used for supporting the left front edge assembly and the right front edge assembly of the airplane.
Optionally, the lifting ring is fixed on the positioning device through a bolt connection, and is connected to the external pulling-up device through a sling.
Optionally, the universal wheel performs horizontal free motion, and is used for realizing ground movement of the aircraft front edge assembly hanging tool.
Optionally, the ground support device is provided with a retractable support foot.
Optionally, an angle measuring instrument is installed on the main truss and used for displaying the inclination angle of the aircraft leading edge assembly in the hoisting process of the aircraft leading edge assembly.
The advantages of the invention include:
(1) different positioning devices are arranged on the main truss, so that the left and right front edge assemblies of the large airplane can be hoisted and positioned, and the flexibility degree is high;
(2) different positioning devices are arranged in the V-shaped groove of the main truss through the locking pin, so that quick connection can be realized;
(3) the middle rotating shaft of the supporting device is rotated, so that the supporting device can be symmetrically transformed, and the left and right front edge assemblies of the large airplane can be hoisted and supported;
(4) the universal wheels can enable the large aircraft front edge assembly hanging tool to horizontally move on the ground;
(5) the supporting legs of the ground supporting device can be extended by rotating the knob of the lifting mechanism in the ground supporting device, so that the universal wheels are separated from the ground while the universal wheels are contacted with the ground, and the suspension tool of the large aircraft front edge assembly can be supported and fixed on the ground;
(6) the angle measuring instrument can display the self inclination angle of the aircraft leading edge component in the hanging process;
(7) easy to install and maintain.
Drawings
FIG. 1 is a block diagram of a large aircraft leading edge assembly hanger fixture;
FIG. 2 is a structural diagram of a positioning device in a hanging tool for a left front edge assembly of a large aircraft;
FIG. 3 is a structural diagram of a supporting device in a large aircraft leading edge component hanging tool.
In the figure, 1-main truss; 2-a positioning device; 3-a support device; 4-a hoisting ring; 5-universal wheels; 6-ground support means; 7-an angle measuring instrument; 2-1-vertical compaction block; 2-2-vertical positioning blocks; 2-3-horizontal transverse positioning blocks; 2-4-horizontal transverse compaction block; 2-5-horizontal longitudinal positioning blocks; 2-6-horizontal longitudinal pressing blocks; 2-7-T beam; 2-8-V type groove; 2-9 locking pins; 3-1-auxiliary supporting legs; 3-2-a support plate; 3-3-middle rotating shaft.
Detailed Description
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, however, the present invention may be practiced in other ways than those specifically described herein, and thus the present invention is not limited to the specific embodiments disclosed below. The terms "upper", "lower", "left" and "right" as used herein are set forth with reference to the accompanying drawings, and it is understood that the presence of the terms does not limit the scope of the present invention.
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative and intended to explain the present invention and should not be construed as limiting the present invention.
In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
As shown in fig. 1, a large aircraft leading edge assembly hanging tool mainly comprises a main truss 1, a positioning device 2, a supporting device 3, a hanging ring 4, a universal wheel 5, a ground supporting device 6 and an angle measuring instrument 7.
The main truss 1 is a beam truss made of high-quality steel material of 24m 1.2m 1.3 m. The positioning device 2 can be quickly installed on the V-shaped grooves 2-8 of the main body truss 1 through the locking pins 2-9. The supporting device 3, the universal wheel 5, the ground supporting device 6 and the angle measuring instrument 7 are fixed on the main truss 1 through threaded connection. The hanging ring 4 is fixed on the positioning device 2 through bolt connection.
As shown in fig. 2, the positioning device 2 mainly comprises a vertical pressing block 2-1, a vertical positioning block 2-2, a horizontal transverse pressing block 2-3, a horizontal transverse pressing block 2-4, a horizontal longitudinal positioning block 2-5, a horizontal longitudinal pressing block 2-6, a T-shaped beam 2-7, a V-shaped groove 2-8, a locking pin 2-9 and the like. The vertical pressing blocks 2-1, the vertical positioning blocks 2-2, the horizontal transverse positioning blocks 2-3, the horizontal transverse pressing blocks 2-4, the horizontal longitudinal positioning blocks 2-5, the horizontal longitudinal pressing blocks 2-6, the T-shaped beams 2-7 and the V-shaped grooves 2-8 are all fixed on the main truss 1 through threaded connection. The vertical compression block 2-1 can vertically fix the airplane leading edge assembly, and the vertical positioning block 2-2 provides a vertical positioning reference for the airplane leading edge assembly; the horizontal transverse pressing blocks 2-4 can horizontally and transversely fix the aircraft leading edge assembly, and the horizontal transverse positioning blocks 2-3 provide a horizontal transverse positioning reference for the aircraft leading edge assembly; the horizontal longitudinal pressing blocks 2-6 can horizontally and longitudinally fix the aircraft leading edge assembly, and the horizontal longitudinal positioning blocks 2-5 provide a horizontal longitudinal positioning reference for the aircraft leading edge assembly. For two conditions of hanging the left front edge assembly and the right front edge assembly of the airplane, corresponding hoisting and positioning can be realized by installing the corresponding positioning devices 2, and quick installation can be realized by the locking pins 2-9.
As shown in FIG. 3, the supporting device 3 is mainly composed of an auxiliary supporting foot 3-1, a middle rotating shaft 3-2, a supporting plate 3-3 and the like. The supporting plate 3-3 can support the aircraft leading edge assembly in the hoisting process, and the auxiliary supporting leg 3-1 can provide auxiliary support for the aircraft leading edge assembly in the hoisting process. For the two conditions of hanging the left front edge assembly and the right front edge assembly of the airplane, the middle rotating shaft 3-2 can be rotated to respectively support the front edge assembly of the airplane under the two conditions.
As shown in fig. 1, the hoist ring 4 may be connected to an external pulling device by a hoist rope.
As shown in figure 1, the universal wheels 5 can move horizontally and freely, so that the hanging tool of the large aircraft leading edge assembly can move on the ground conveniently.
As shown in fig. 1, the ground supporting device 6 can extend the supporting legs through the lifting mechanism, and then contact the ground while separating the universal wheels from the ground, so as to support and fix the hanging tool of the large aircraft front edge assembly on the ground.
As shown in FIG. 1, the angle measuring device 7 can display the inclination angle of the leading edge component of the large aircraft during the hanging process of the leading edge component.
The above description is only exemplary of the preferred embodiments of the present invention, and is not intended to limit the present invention, and any modifications, equivalents, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. The utility model provides a frock is hung to large aircraft leading edge subassembly which characterized in that includes main part truss (1), installs on main part truss (1):
a positioning device (2) for fixing the leading edge component of the airplane,
a support device (3) for supporting the leading edge assembly of the aircraft,
a lifting ring (4) used for connecting an external pulling device,
a universal wheel (5) for hanging the tool to move,
ground support means (6) for supporting and securing;
the positioning devices (2) are positioning structures which are symmetrically arrayed on the main truss (1); the positioning device (2) is arranged in a V-shaped groove (2-8) of the main truss (1) through a locking pin (2-9); the positioning device (2) comprises a T-shaped beam (2-7) with two ends extending into a V-shaped groove (2-8), wherein a vertical pressing block (2-1) and a vertical positioning block (2-2) which are matched with each other are arranged on the T-shaped beam (2-7), a horizontal transverse positioning block (2-3) and a horizontal transverse pressing block (2-4) which are matched with each other, and a horizontal longitudinal positioning block (2-5) and a horizontal longitudinal pressing block (2-6) which are matched with each other;
rotating a knob on the vertical pressing block (2-1) to vertically fix the aircraft leading edge assembly, and providing a vertical positioning reference for the aircraft leading edge assembly by the vertical positioning block (2-2); the front edge assembly of the airplane is horizontally and transversely fixed by rotating a knob on a horizontal transverse pressing block (2-4), and a horizontal transverse positioning block (2-3) provides a horizontal transverse positioning reference for the front edge assembly of the airplane; the aircraft leading edge assembly is horizontally and longitudinally fixed by rotating a knob on the horizontal longitudinal pressing block (2-6), and the horizontal longitudinal positioning block (2-5) provides a horizontal longitudinal positioning reference for the aircraft leading edge assembly.
2. The large aircraft leading edge assembly hanging tool according to claim 1, characterized in that: the main truss (1) is a beam truss made of steel.
3. The large aircraft leading edge assembly hanging tool according to claim 1, characterized in that: the T-shaped beams (2-7) are connected with the V-shaped grooves (2-8) through locking pins (2-9).
4. The large aircraft leading edge assembly hanging tool according to claim 1, characterized in that: the supporting devices (3) are supporting structures which are symmetrically arrayed on the main truss (1); the supporting device (3) comprises a supporting plate (3-3) for supporting the front edge component of the airplane and an auxiliary supporting foot (3-1);
the supporting device (3) further comprises a middle rotating shaft (3-2), and the supporting plate (3-3) rotates around the middle rotating shaft (3-2) to carry out structural symmetry transformation and is respectively used for supporting the left front edge assembly and the right front edge assembly of the airplane.
5. The large aircraft leading edge assembly hanging tool according to claim 1, characterized in that: the lifting ring (4) is fixedly connected to the positioning device (2) through bolts and is connected to an external pulling device through a sling.
6. The large aircraft leading edge assembly hanging tool according to claim 1, characterized in that: the universal wheels (5) move horizontally and freely and are used for realizing ground movement of the hanging tool of the aircraft front edge assembly.
7. The large aircraft leading edge assembly hanging tool according to claim 1, characterized in that: the ground supporting device (6) is provided with telescopic supporting legs.
8. The large aircraft leading edge assembly hanging tool according to claim 1, characterized in that: and an angle measuring instrument (7) is arranged on the main truss (1) and is used for displaying the inclination angle of the aircraft leading edge component in the hoisting process of the aircraft leading edge component.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011097150.0A CN112373713B (en) | 2020-10-14 | 2020-10-14 | Large aircraft leading edge assembly hanging tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011097150.0A CN112373713B (en) | 2020-10-14 | 2020-10-14 | Large aircraft leading edge assembly hanging tool |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112373713A CN112373713A (en) | 2021-02-19 |
| CN112373713B true CN112373713B (en) | 2022-05-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011097150.0A Active CN112373713B (en) | 2020-10-14 | 2020-10-14 | Large aircraft leading edge assembly hanging tool |
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| CN (1) | CN112373713B (en) |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2961489B1 (en) * | 2010-06-22 | 2013-06-14 | Airbus Operations Sas | DEVICE FOR MAINTAINING INSULATING MATTRESS AND FASTENING TWO-PIECE SYSTEMS |
| CN205034955U (en) * | 2015-09-17 | 2016-02-17 | 四川江阳工程项目管理有限公司 | Can bear mobile platform that can hoist |
| CN105270981A (en) * | 2015-11-27 | 2016-01-27 | 中航成飞民用飞机有限责任公司 | Lifting tool for large skin panels |
| US10392131B2 (en) * | 2016-08-26 | 2019-08-27 | The Boeing Company | Additive manufactured tool assembly |
| CN210588970U (en) * | 2019-08-29 | 2020-05-22 | 中车青岛四方机车车辆股份有限公司 | Assembly positioning device |
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