CN114771865B - Auxiliary tooling for butt joint of plane skin panel end faces of airplane and using method - Google Patents
Auxiliary tooling for butt joint of plane skin panel end faces of airplane and using method Download PDFInfo
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- CN114771865B CN114771865B CN202210616739.XA CN202210616739A CN114771865B CN 114771865 B CN114771865 B CN 114771865B CN 202210616739 A CN202210616739 A CN 202210616739A CN 114771865 B CN114771865 B CN 114771865B
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- 210000001503 joint Anatomy 0.000 title claims abstract description 23
- 238000000034 method Methods 0.000 title claims abstract description 17
- 230000003068 static effect Effects 0.000 claims abstract description 44
- 238000004140 cleaning Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 6
- 238000003032 molecular docking Methods 0.000 claims description 4
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 238000005520 cutting process Methods 0.000 claims description 2
- 238000009434 installation Methods 0.000 claims 1
- 238000005259 measurement Methods 0.000 abstract description 2
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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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Abstract
The invention provides an auxiliary tool for butt joint of plane skin panel end surfaces of an airplane and a using method, belongs to the technical field of mechanical assembly, and is used for realizing the functions of auxiliary measurement, positioning, adjustment and the like of butt joint of two plane skin panel end surfaces at any angle. The invention integrates the indication, adjustment and positioning devices of the included angle of the end surfaces of the skin panels, adopts the counterforce springs to form clamping force, and can realize the random adjustment and the accurate positioning of the included angle of 30-180 degrees by taking the movable clamping plates and the static clamping plates as the auxiliary device for the butt joint of the end surfaces of the two skin panels. The invention has novel mechanical structure, high flexibility, wide application range, good stability, strong operability and greatly improves the working efficiency, and can lead operators to finish the follow-up riveting work accurately and efficiently.
Description
Technical Field
The invention belongs to the technical field of mechanical assembly, and relates to an auxiliary tool for butt joint of plane skin panel end surfaces of an airplane and a use method thereof, which are mainly used for realizing auxiliary measurement, positioning, adjustment and other functions of butt joint of two plane skin panel end surfaces at any angle, so that operators can accurately and efficiently finish subsequent riveting work.
Background
In the process of riveting and fixing the aircraft skin in butt joint through the bracket, the riveting work of forming different included angles by the end faces of the two plane skins is frequently encountered. If the included angle between the end faces of two skin panels is too large and too small or the gap between the end faces exceeds the standard in the riveting process, the assembly quality of the whole skin assembly can be directly affected, so that the assembly cannot be carried out, and therefore whether the butt joint work of the end faces of the skin panels in the earlier stage is accurate is very important. At present, the conventional practice is that an operator makes holes on two skin panels to be butted according to a specified position, then uses a special included angle butting die to fix the skin on the special die respectively through screws, then the operator sequentially completes hole making work on other parts of the skin, and after all hole making work is completed, the bracket is riveted on the specified position of the butted position of the two skin panels respectively through a riveter. While the above-described methods also work well for abutting skin panels, they present some problems. Firstly, for the special butt-joint mould used in the operation method, the included angle is fixed, so that for the butt-joint work of a plurality of skins with different included angles, a plurality of special fixtures are prepared in an intangible way, the number and the manufacturing cost of the fixture are increased, and the operation is not facilitated; secondly, because the specifications (diameters) of the rivets used for skins with different functions are different, for the special clamps in the operation, the dies with the same included angle also need to be prepared with a series of special clamps with different fixing holes, the number of the clamps is increased, and operators are very easy to use errors in the using process, so that the hole making positions and the butt joint quality of relevant parts on the skins are directly influenced, and finally the quality of the whole product is influenced.
In view of the above reasons, the auxiliary butt joint tool is novel in structure and convenient to operate, and more importantly, the auxiliary butt joint tool can efficiently and accurately assist an operator to finish the butt joint work of the end faces of the skin panels, and compared with the prior positioning tool and method, the working efficiency is greatly improved.
Disclosure of Invention
The invention provides an auxiliary tooling for butt joint of the end surfaces of plane skin panels of an airplane and a use method, wherein the tooling is a multifunctional tooling integrating adjustment and positioning, so that the difficulty of operators can be reduced, the working efficiency can be greatly improved, and the tooling can be widely applied to relevant skin butt joint working scenes in the manufacturing process of the airplane.
In order to achieve the above purpose, the invention adopts the following technical scheme:
the utility model provides an aircraft plane skin panel terminal surface butt joint auxiliary fixtures, the frock includes angle scale base 1, L splint 2, quiet splint 3, counter-force baffle 4, circular guide pillar 5, set screw 6, movable splint 7, locking lug 8, interior hexagonal fastening bolt 9, fastening screw 10, adjusting bolt 11, counter-force spring 12 and instrument screw 13.
The angle scale base 1 is of a square structure and provides a mounting support for the whole tool; the center position that the surface of the angle scale base 1 is close to a long side is provided with a round hole, meanwhile, the angle scale base 1 is provided with an angle scale plate and an arc-shaped groove by taking the center of the round hole as the center of a circle, the radius of the angle scale plate and the arc-shaped groove is smaller than the side length of the short side of the angle scale base 1, wherein the angle range of the angle scale plate is distributed from 30 degrees to 180 degrees from right to left, and the arc-shaped groove is in an inverted T shape.
The static clamping plate 3 and the movable clamping plate 7 are of plate-shaped structures with the same size, and are both positioned on the angle scale base 1; the static clamping plate 3 is contacted with one end of the movable clamping plate 7 to form an included angle, and the top end of the included angle is aligned with the circle center of the round hole on the angle scale base 1;
The bottom of one end of the movable clamp plate 7 is provided with a rotating shaft 7-1 which is a cylinder matched with the aperture of a round hole, the rotating shaft 7-1 is inserted into the round hole, the movable clamp plate 7 can rotate around the center of the round hole, the bottom surface of the other end of the movable clamp plate 7 is provided with an inverted T-shaped protruding sliding block 7-2, the sliding block 7-2 is clamped into an arc-shaped groove on the angle dial base 1 and is limited in the arc-shaped groove, the movable clamp plate 7 can slide along the arc-shaped groove, the side wall of the movable clamp plate 7 beside the sliding block 7-2 is fixed with a locking lug 8 through an instrument screw 13, and an adjusting bolt 11 is arranged on the locking lug 8 and is in threaded connection with the locking lug for fixing the position of the movable clamp plate 7.
The two ends of the static clamping plate 3 are fixed on the angle scale base 1 through fixing screws 6, and the inner side surface of the included angle of the static clamping plate 3 is aligned with the position of the angle scale plate at 0 DEG; the middle part of the static clamping plate 3 is provided with a square groove which penetrates through, one end of the L-shaped clamping plate 2 penetrates through the square groove from the inner side surface of an included angle of the static clamping plate 3 and then is connected with the counter force baffle plate 4, the counter force baffle plate is fixed through a fastening screw 10, a counter force spring 12 is arranged between the counter force baffle plate 4 and the static clamping plate 3, and the counter force baffle plate 4 provides a counter force supporting surface for the counter force spring 12, so that the L-shaped clamping plate 2 can firmly clamp a skin panel on the static clamping plate 3; the circular guide post 5 penetrates through the counter force baffle plate 4 and then goes deep into the counter force spring 12, a telescopic guide post is provided for the counter force spring 12, the counter force spring 12 is prevented from falling off in the working process, meanwhile, the circular guide post 5 is fixed on the counter force baffle plate 4 through the inner hexagonal fastening bolt 9, wherein the L-shaped clamping plate 2, the counter force baffle plate 4, the counter force spring 12 and the circular guide post 5 form a clamping structure, and the clamping of the skin panel is completed together with the static clamping plate 3; the movable clamping plate 7 and the static clamping plate 3 are provided with the same square grooves at the same positions, and the other group of clamping structures are assembled on the movable clamping plate 7 in the same mode to jointly finish the clamping of the other skin panel together with the movable clamping plate 7.
Furthermore, the angle scale base 1, the L-shaped clamping plate 2, the static clamping plate 3, the counter force baffle 4, the circular guide post 5 and the movable clamping plate 7 are made of wear-resistant aluminum materials.
The application method of the auxiliary tool for butt joint of the plane skin panel end faces of the aircraft comprises the following steps:
S1, selecting two skin panels, rivets, sectional materials, related parts and related riveting tools to be butted according to the assembly requirement of the aircraft skin panels.
S2, after checking the integrity of the tool, placing the tool on an operation table.
S3, determining an included angle between the end faces of the two skin panels to be butted, unscrewing the adjusting bolt 11, moving the movable clamping plate 7, forming a required included angle between the movable clamping plate 7 and the static clamping plate 3, and then screwing the adjusting bolt 11 to fix the position of the movable clamping plate 7.
S4, pushing the counterforce baffle 4, placing the lower end face of one skin panel between the L-shaped clamping plate 2 and the static clamping plate 3, and then slowly loosening the counterforce baffle 4 to clamp the skin panel.
S5 is performed in the same way as S4, and the other Zhang Mengpi wall plate is clamped between the L-shaped clamping plate 2 and the movable clamping plate 7.
S6, pushing the two counterforce baffles 4, and adjusting the positions of the riveting sections of the two skins until the end faces of the two skins are tightly attached.
S7, repeating the steps S2-S6, and clamping the other tooling at the other included angle end of the two skin panels.
And S8, after all clamping work is finished, sequentially completing hole making and nest cutting work at the position of an included angle of the end surfaces of the two skin panels according to the specified position.
And S9, after the S8 is completed, riveting the brackets on the two skin panels one by one according to the specified positions.
And S10, after the riveting work is finished, pushing the counterforce baffle 4, detaching the riveted wallboard, and placing the wallboard at a designated position.
S11, cleaning the surplus on the work station by using a cleaning tool, and then placing the work station at a specified position.
The beneficial effects of the invention are as follows:
(1) The invention has novel mechanical structure, high flexibility, good stability and strong operability, and can realize arbitrary adjustment and accurate positioning of an included angle of 30-180 degrees by taking the movable clamping plate and the static clamping plate as the auxiliary device for butt joint of the end faces of two skin panels, thereby widening the application range of the tool and improving the positioning precision.
(2) According to the invention, the skin panel end face included angle indicating, adjusting and positioning device is integrated, so that the operation difficulty of operators is reduced, and the number of operators is reduced from more than 2 to single operation.
(3) The invention adopts the counterforce spring to form the clamping force, thereby not only being convenient to operate, but also reducing the time for clamping, adjusting and positioning the skin and greatly improving the working efficiency.
(4) The invention has universality, can be applied to the field of riveting processing, and can be popularized to the technical field of welding processing of butt joint of the end faces of metal wall plates in the manufacturing industries of automobiles, ships and the like.
Drawings
FIG. 1 is a top view of an aircraft planar skin panel end-face docking aid.
Fig. 2 is a front view of an aircraft planar skin panel end face docking aid.
FIG. 3 is a side view of an aircraft planar skin panel end-face docking aid.
Fig. 4 (a) is a front view of the movable clamp plate.
Fig. 4 (b) is a side view of the movable clamp plate.
Fig. 4 (c) is a bottom view of the movable clamp plate.
In the figure: 1, an angle scale base; 2L-shaped clamping plates; 3, static clamping plates; 4, a counterforce baffle; 5, a circular guide post; 6, fixing a screw; 7, moving the clamping plate; 8 locking lugs; 9, inner hexagon fastening bolts; 10 fastening a screw; 11 adjusting bolts; 12 reaction force springs; 13 meter screw; 7-1 rotation axis; 7-2 sliders.
Detailed Description
The following describes the embodiments of the present invention further with reference to the drawings and technical schemes.
Examples
As shown in fig. 1,2,3,4 (a), 4 (b) and 4 (c), an auxiliary tool for butt joint of plane skin panels of an aircraft comprises an angle scale base 1, an L-shaped clamping plate 2, a static clamping plate 3, a counter force baffle 4, a circular guide post 5, a fixing screw 6, a movable clamping plate 7, a locking lug 8, an inner hexagonal fastening bolt 9, a fastening screw 10, an adjusting bolt 11, a counter force spring 12 and an instrument screw 13.
The angle scale base 1 is of a square structure and provides a mounting support for the whole tool; the center position that the surface of the angle scale base 1 is close to a long side is provided with a round hole, meanwhile, the angle scale base 1 is provided with an angle scale plate and an arc-shaped groove by taking the center of the round hole as the center of a circle, the radius of the arc-shaped groove is smaller than the side length of the short side of the angle scale base 1, the angle range of the angle scale plate is distributed from 30 degrees to 180 degrees from right to left, and the arc-shaped groove is in an inverted T shape.
The static clamping plate 3 and the movable clamping plate 7 are of plate-shaped structures with the same size, and are both positioned on the angle scale base 1; the static clamping plate 3 is contacted with one end of the movable clamping plate 7 to form an included angle, and the top end of the included angle is aligned with the circle center of the round hole on the angle scale base 1;
The bottom of one end of the movable clamp plate 7 is provided with a rotating shaft 7-1 which is a cylinder matched with the aperture of a round hole, the rotating shaft 7-1 is inserted into the round hole, the movable clamp plate 7 can rotate around the center of the round hole, the bottom surface of the other end of the movable clamp plate 7 is provided with an inverted T-shaped protruding sliding block 7-2, the sliding block 7-2 is clamped into an arc-shaped groove on the angle dial base 1 and is limited in the arc-shaped groove, the movable clamp plate 7 can slide along the arc-shaped groove, the side wall of the movable clamp plate 7 beside the sliding block 7-2 is fixed with a locking lug 8 through an instrument screw 13, and an adjusting bolt 11 is arranged on the locking lug 8 and is in threaded connection with the locking lug for fixing the position of the movable clamp plate 7.
The two ends of the static clamping plate 3 are fixed on the angle scale base 1 through fixing screws 6, and the inner side surface of the included angle of the static clamping plate 3 is aligned with the position of the angle scale plate at 0 DEG; the middle part of the static clamping plate 3 is provided with a square groove which penetrates through, one end of the L-shaped clamping plate 2 penetrates through the square groove from the inner side surface of an included angle of the static clamping plate 3 and then is connected with the counter force baffle plate 4, the counter force baffle plate is fixed through a fastening screw 10, a counter force spring 12 is arranged between the counter force baffle plate 4 and the static clamping plate 3, and the counter force baffle plate 4 provides a counter force supporting surface for the counter force spring 12, so that the L-shaped clamping plate 2 can firmly clamp a skin panel on the static clamping plate 3; the circular guide post 5 penetrates through the counter force baffle plate 4 and then goes deep into the counter force spring 12, a telescopic guide post is provided for the counter force spring 12, the counter force spring 12 is prevented from falling off in the working process, meanwhile, the circular guide post 5 is fixed on the counter force baffle plate 4 through the inner hexagonal fastening bolt 9, wherein the L-shaped clamping plate 2, the counter force baffle plate 4, the counter force spring 12 and the circular guide post 5 form a clamping structure, and the clamping of the skin panel is completed together with the static clamping plate 3; the movable clamping plate 7 and the static clamping plate 3 are provided with the same square grooves at the same positions, and the other group of clamping structures are assembled on the movable clamping plate 7 in the same mode to jointly finish the clamping of the other skin panel together with the movable clamping plate 7.
Furthermore, the angle scale base 1, the L-shaped clamping plate 2, the static clamping plate 3, the counter force baffle 4, the circular guide post 5 and the movable clamping plate 7 are made of aluminum materials.
The application method of the auxiliary tool for butt joint of the plane skin panel end faces of the aircraft comprises the following steps:
S1, selecting two skin panels, rivets, sectional materials, related parts and related riveting tools to be butted according to the assembly requirement of the aircraft skin panels.
S2, after checking the integrity of the tool, placing the tool on an operation table.
S3, determining an included angle between the end faces of the two skin panels to be butted, unscrewing the adjusting bolt 11, moving the movable clamping plate 7, forming a required included angle between the movable clamping plate 7 and the static clamping plate 3, and then screwing the adjusting bolt 11 to fix the position of the movable clamping plate 7.
S4, pushing the counterforce baffle 4, placing the lower end face of one skin panel between the L-shaped clamping plate 2 and the static clamping plate 3, and then slowly loosening the counterforce baffle 4 to clamp the skin panel.
S5 is performed in the same way as S4, and the other Zhang Mengpi wall plate is clamped between the L-shaped clamping plate 2 and the movable clamping plate 7.
S6, pushing the two counterforce baffles 4, and adjusting the positions of the riveting sections of the two skins until the end faces of the two skins are tightly attached.
S7, repeating the steps S2-S6, and clamping the other tooling at the other included angle end of the two skin panels.
S8, after all clamping work is finished, drilling holes and scribing work are sequentially carried out at the included angle of the end faces of the two skin panels according to the specified positions by using an air drill.
And S9, after the S8 is finished, riveting the brackets on the two skin panels one by one according to the specified positions by using a riveter.
And S10, after the riveting work is finished, pushing the counterforce baffle 4, detaching the riveted wallboard, and placing the wallboard at a designated position.
S11, cleaning the surplus on the work station by using a cleaning tool, and then placing the work station at a specified position.
The examples described above represent only embodiments of the invention and are not to be understood as limiting the scope of the patent of the invention, it being pointed out that several variants and modifications may be made by those skilled in the art without departing from the concept of the invention, which fall within the scope of protection of the invention.
Claims (3)
1. The auxiliary tooling for butt joint of the plane skin panel end faces of the aircraft is characterized by comprising an angle scale base (1), an L-shaped clamping plate (2), a static clamping plate (3), a counter force baffle (4), a circular guide post (5), a fixing screw (6), a movable clamping plate (7), a locking lug (8), an inner hexagonal fastening bolt (9), a fastening screw (10), an adjusting bolt (11), a counter force spring (12) and an instrument screw (13);
The angle scale base (1) is of a square structure and provides an installation support for the whole tool; the surface of the angle dial base (1) is provided with a round hole near the center of a long side, meanwhile, the angle dial base (1) is provided with an angle scale plate and an arc-shaped groove by taking the center of the round hole as the center of a circle, the radius of the angle scale plate and the arc-shaped groove is smaller than the side length of a short plate of the angle dial base (1), wherein the angle range of the angle scale plate is distributed from 30 degrees to 180 degrees from right to left, and the arc-shaped groove is in an inverted T shape;
the static clamping plate (3) and the movable clamping plate (7) are of plate-shaped structures with the same size, and are both positioned on the angle scale base (1); the static clamping plate (3) is contacted with one end of the movable clamping plate (7) to form an included angle, and the top end of the included angle is aligned with the circle center of the round hole on the angle scale base (1);
The bottom of one end of the movable clamp plate (7) is inserted into the round hole through the rotary shaft (7-1), so that the movable clamp plate (7) can rotate around the center of the round hole, the bottom surface of the other end of the movable clamp plate (7) is provided with an inverted T-shaped protruding sliding block (7-2) which is used for being matched with the arc-shaped groove of the angle scale plate, the movable clamp plate (7) can slide along the arc-shaped groove, the side wall of the movable clamp plate (7) beside the sliding block (7-2) is fixedly provided with a locking lug (8) through an instrument screw (13), and the locking lug (8) is provided with an adjusting bolt (11) which is connected through threads and used for fixing the position of the movable clamp plate (7);
two ends of the static clamping plate (3) are fixed on the angle scale base (1) through fixing screws (6), and the inner side surface of an included angle of the static clamping plate (3) is aligned with the position of the angle scale plate at 0 DEG; the middle part of the static clamping plate (3) is provided with a square groove which penetrates through, one end of the L-shaped clamping plate (2) penetrates through the square groove from the inner side face of an included angle of the static clamping plate (3) and then is connected with the counter force baffle plate (4) and is fixed through a fastening screw (10), a counter force spring (12) is arranged between the counter force baffle plate (4) and the static clamping plate (3), and the counter force baffle plate (4) provides a counter force supporting surface for the counter force spring (12), so that the L-shaped clamping plate (2) can firmly clamp a skin panel on the static clamping plate (3); the circular guide post (5) penetrates through the counter force baffle plate (4) and then goes deep into the counter force spring (12) to prevent the counter force spring (12) from falling off in the working process, and meanwhile, the circular guide post (5) is fixed on the counter force baffle plate (4) through the inner hexagonal fastening bolt (9), wherein the L-shaped clamping plate (2), the counter force baffle plate (4), the counter force spring (12) and the circular guide post (5) form a clamping structure, and the clamping of the skin panel is completed together with the static clamping plate (3);
The movable clamping plate (7) and the static clamping plate (3) are provided with the same square grooves at the same positions, and the other group of clamping structures are assembled on the movable clamping plate (7) in the same mode to jointly complete the clamping of the other skin panel with the movable clamping plate (7).
2. The auxiliary tooling for butt joint of the plane skin panel end faces of the airplane according to claim 1, wherein the angle plate base (1), the L-shaped clamping plate (2), the static clamping plate (3), the counter force baffle plate (4), the circular guide post (5) and the movable clamping plate (7) are made of aluminum materials.
3. A method of using the aircraft planar skin panel end face docking aid of claim 1 or 2, comprising the steps of:
S1, selecting two skin panels, rivets, sectional materials, related parts and related riveting tools to be butted according to the assembly requirement of aircraft skin panels;
S2, after checking the integrity of the tool, placing the tool on an operation table;
S3, determining an included angle between end faces of two skin panels to be butted, unscrewing an adjusting bolt (11), moving a movable clamping plate (7), forming a required included angle between the movable clamping plate (7) and a static clamping plate (3), and then screwing the adjusting bolt (11) to fix the position of the movable clamping plate (7);
s4, pushing the counterforce baffle (4), placing the lower end surface of one skin panel between the L-shaped clamping plate (2) and the static clamping plate (3), and then slowly loosening the counterforce baffle (4) to clamp the skin panel;
S5, the same operation as that of S4 is carried out, and the other Zhang Mengpi wall plate is clamped between the L-shaped clamping plate (2) and the movable clamping plate (7);
S6, pushing the two counterforce baffles (4), and adjusting the positions of the riveting sections of the two skins until the end surfaces of the two skins are tightly attached;
s7, repeating the steps S2-S6, and clamping the other tooling at the other included angle end of the two skin panels;
S8, after all clamping work is finished, hole making and nest cutting work is sequentially finished at the position of an included angle of the end surfaces of the two skin panels according to a specified position;
S9S 8, after the completion of the S8, riveting the brackets on the two skin panels one by one according to the specified positions;
S10, pushing a counterforce baffle (4) after the riveting work is finished, detaching the riveted wallboard, and placing the wallboard at a designated position;
s11, cleaning the surplus on the work station by using a cleaning tool, and then placing the work station at a specified position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210616739.XA CN114771865B (en) | 2022-06-01 | 2022-06-01 | Auxiliary tooling for butt joint of plane skin panel end faces of airplane and using method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210616739.XA CN114771865B (en) | 2022-06-01 | 2022-06-01 | Auxiliary tooling for butt joint of plane skin panel end faces of airplane and using method |
Publications (2)
| Publication Number | Publication Date |
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| CN114771865A CN114771865A (en) | 2022-07-22 |
| CN114771865B true CN114771865B (en) | 2024-10-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210616739.XA Active CN114771865B (en) | 2022-06-01 | 2022-06-01 | Auxiliary tooling for butt joint of plane skin panel end faces of airplane and using method |
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| CN (1) | CN114771865B (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106697327A (en) * | 2016-12-19 | 2017-05-24 | 中航成飞民用飞机有限责任公司 | Aircraft panel butt joint structure |
| CN107499530A (en) * | 2017-08-21 | 2017-12-22 | 大连四达高技术发展有限公司 | Digital processing and assembly system for aircraft panels |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5560102A (en) * | 1992-10-13 | 1996-10-01 | The Boeing Company | Panel and fuselage assembly |
| DE102010047561B4 (en) * | 2010-10-07 | 2013-07-25 | Airbus Operations Gmbh | Clamping device and method for assembling stringers clutches |
| CN111438393B (en) * | 2020-05-15 | 2024-07-23 | 沈阳飞机工业（集团）有限公司 | Quick positioning guide hole device for aircraft skin riveting hole and use method |
-
2022
- 2022-06-01 CN CN202210616739.XA patent/CN114771865B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106697327A (en) * | 2016-12-19 | 2017-05-24 | 中航成飞民用飞机有限责任公司 | Aircraft panel butt joint structure |
| CN107499530A (en) * | 2017-08-21 | 2017-12-22 | 大连四达高技术发展有限公司 | Digital processing and assembly system for aircraft panels |
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| Publication number | Publication date |
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| CN114771865A (en) | 2022-07-22 |
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