CN113830324B - Splicing device and splicing method for middle section of airplane body - Google Patents
Splicing device and splicing method for middle section of airplane body Download PDFInfo
- Publication number
- CN113830324B CN113830324B CN202111174602.5A CN202111174602A CN113830324B CN 113830324 B CN113830324 B CN 113830324B CN 202111174602 A CN202111174602 A CN 202111174602A CN 113830324 B CN113830324 B CN 113830324B
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- splicing
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- lifting device
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- middle section
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- 238000000034 method Methods 0.000 title claims abstract description 17
- 230000000712 assembly Effects 0.000 claims abstract description 27
- 238000000429 assembly Methods 0.000 claims abstract description 27
- 238000003466 welding Methods 0.000 claims description 8
- 230000003028 elevating effect Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 2
- 230000006978 adaptation Effects 0.000 description 1
- 238000007792 addition Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- 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
Abstract
The invention discloses a semi-automatic splicing device and method for an airplane body middle section. The device comprises a main body frame, wherein roller assemblies are arranged on two side brackets, a stepping motor is arranged on the roller assemblies on at least one side of the roller assemblies, a power carrying platform and a lifting device arranged on the power carrying platform are arranged in the main body frame, and the middle sections of each section of the device body can be supported by the roller assemblies, driven to rotate by the stepping motor, lifted under the driving of the lifting device and moved back and forth in a reciprocating manner through the bearing of the power carrying platform. The advantages are that: the middle sections of the airframe to be spliced are quickly spliced together by workers easily, so that labor intensity is greatly reduced while manual labor is reduced, splicing efficiency is effectively improved, and the danger of manual splicing operation is effectively avoided; the splicing difficulty is effectively reduced, the operation is facilitated through the formed splicing gap, the splicing quality is improved, meanwhile, the riveting is also facilitated, and the splicing effect is further improved.
Description
Technical Field
The invention relates to a splicing device of an airplane fuselage, in particular to a semi-automatic splicing device and a splicing method of an airplane fuselage middle section.
Background
In the production process of aviation enterprises, for the assembly of large and medium-sized airplanes, the assembly difficulty is higher due to the large size, especially for the assembly of middle section fuselage of the airplane, at present, most enterprises adopt a mechanical manual assembly operation mode, and the operation mode is finished by a plurality of people at the same time, so that the labor intensity of workers is high, the operation time is long, and due to the importance of the fuselage section, the requirement on riveting workers is too high, the assembly difficulty coefficient is high, the assembly efficiency is low, and meanwhile, the problems of high danger and the like are solved.
Disclosure of Invention
The invention aims to solve the technical problem of providing the splicing device and the splicing method for the middle section of the airplane body, which are time-saving and labor-saving in splicing, high in splicing efficiency and capable of improving splicing quality and reducing danger.
In order to solve the technical problems, the splicing device for the middle section of the airplane fuselage comprises a main body frame formed by an underframe and two side supporting frames on the left side and the right side of the underframe, roller assemblies for supporting each section of fuselage are arranged on the two side supporting frames, a stepping motor for driving each section of fuselage middle section to rotate is arranged on at least one of the roller assemblies, a power carrier capable of moving back and forth and a lifting device arranged on the power carrier are arranged in the main body frame, and each section of fuselage middle section can be supported by the roller assemblies, driven to rotate by the stepping motor, lifted by the driving of the lifting device and moved back and forth by the bearing of the power carrier.
Each of the roll assemblies includes a support shaft mounted on the side stand and a plurality of support rolls mounted on the support shaft.
The chassis is provided with a track, and the power carrier is arranged on the track.
The lifting device is provided with V-shaped supporting blocks which are used for supporting the lower surface of each section of the machine body.
The power carrier is an electric carrier with a driving motor inside.
The lifting device is a hydraulic lifting device.
The side of main part frame is provided with the switch board, have the hydraulic press that is used for providing power to elevating gear in the switch board.
The splicing method based on the aircraft fuselage middle section splicing device is characterized by comprising the following steps of: the method comprises the following steps:
(1) Hanging a middle section of a machine body to be spliced onto two roller assemblies, and arranging one end of the middle section of the machine body to be spliced at the gap of two supporting rollers of each roller assembly;
(2) Hanging the other section of the machine body to the two roller assemblies, starting the power carrier to walk to the right lower part of the roller assemblies, and starting the lifting device to jack up the section of the machine body; the jack-up rear power carrier moves one end of the middle section of the machine body to the middle section of the front section of the machine body;
(3) Riveting or welding the two sections of the fuselage in step (1) and step (2) that are fully aligned;
(4) And (5) hanging down after riveting or welding is finished, and finishing splicing.
After the step (2) and before the step (3), if the assembly center lines of the two sections of the middle body sections are not aligned, starting a lifting device (8) to slightly jack up the middle body section of the later section, and then starting a stepping motor to drive a roller assembly to rotate, so that the middle body section of the later section is driven to rotate until the end parts of the middle body sections of the two sections are completely aligned.
And (5) repeating the steps (1) - (4) in the subsequent splicing mode of the middle sections of the airframe until the splicing is finished.
The invention has the advantages that:
through the main body frame, the roller assemblies arranged on the main body frame and the power carrier with the lifting device arranged in the main body frame, each cylindrical airframe middle section to be spliced can be directly arranged on the roller assemblies, and especially the airframe middle section can move in three dimensions through the power carrier, the roller assemblies and the hydraulic lifting device, so that workers can easily and quickly splice the airframe middle sections to be spliced together, labor intensity is greatly reduced while manual labor is reduced, splicing efficiency is effectively improved, and the danger of manual splicing operation is effectively avoided; in addition, each roller assembly is provided with a plurality of supporting rollers, gaps between two adjacent supporting rollers can be ingeniously utilized as splicing gaps, splicing difficulty is effectively reduced, operation is facilitated through the formed splicing gaps, splicing quality is improved, riveting is facilitated, and splicing effect is further improved.
Drawings
FIG. 1 is a schematic perspective view of an aircraft mid-body splicing apparatus of the present invention;
fig. 2 is a schematic view of the configuration of the mid-body splicing apparatus of the present invention in use.
Detailed Description
The aircraft fuselage midsection semi-automatic splicing apparatus of the present invention is described in further detail below with reference to the drawings and detailed description.
As shown in the drawings, the aircraft fuselage middle section splicing apparatus of the present invention includes a main body frame 3 composed of a chassis 1 and two side brackets 2 on the left and right sides of the chassis (the left side of the orientation shown in fig. 2 is defined as the chassis front side, the right side of the orientation shown is defined as the chassis rear side), specifically, the main body frame 3 has a channel-shaped section structure (front-rear section direction) composed of a bottom bracket and a plurality of uprights arranged on the left and right edges of the bottom bracket, two bottom brackets arranged side by side in front of and behind are provided in the channel as rails 9, thereby forming a channel in the main body frame 3, roller assemblies 5 for supporting each section of the fuselage middle section 4 are mounted on both the left side bracket and the right side bracket, the two roller assemblies 5 constitute a pair of supporting units, thus, each cylindrical fuselage section to be spliced can be placed on the two roller assemblies of the pair of supporting units, a stepping motor 6 for driving each section of fuselage to rotate is mounted on the roller assembly 5 of the left side support frame or/and the roller assembly 5 of the right side support frame, a power carrier 7 which is supported by a track 9 and can reciprocate back and forth in the track groove is arranged in the track groove of the main body frame 3, a hydraulic lifting device 8 is arranged on the power carrier 7, a V-shaped supporting block 10 for supporting the lower surface of each section of fuselage is arranged on the lifting device 8, each section of fuselage section can be supported by the roller assemblies 5, can also be driven to rotate by the stepping motor 6, and can also be lifted under the drive of the lifting device 8 and reciprocate back and forth through the bearing of the power carrier 7.
Further, each of the roll assemblies 5 includes a support shaft mounted on the side frame 2 and a plurality of support rolls mounted on the support shaft, the roll assemblies 5 of the left side frame and the roll assemblies 5 of the right side frame being positioned to correspond to each other, and it can be seen that the support shaft is supported through the respective vertical bars and the respective support rolls are disposed between the front and rear adjacent vertical bars, thereby forming a splice gap (space) between the adjacent respective support rolls.
Still further, the power carrier 7 is an electric carrier with a driving motor inside, a control cabinet 11 is arranged at the side of the main body frame 3, and an oil press for providing power for the lifting device and a control unit for controlling the stepping motor 6 and the driving motor of the power carrier 7 are arranged in the control cabinet 11.
Embodiment two:
the splicing method based on the splicing device for the middle section of the airplane body of the embodiment comprises the following steps:
(1) Hanging one section (section) of the airframe to be spliced onto two roller assemblies 5, and placing one end of the section of the airframe at the gap (space) between two support rollers of each roller assembly 5;
(2) The other section of the machine body middle section is hung on the two roller assemblies 5, a power carrying platform 7 is started to walk under the section of the machine body middle section, and a hydraulic lifting device 8 is started to jack up the section of the machine body middle section; jacking up the rear power carrier 7 to move one end of the middle section of the body to the middle section of the front section of the body;
(3) Riveting or welding the two sections of the completely aligned airframe middle sections in the step (1) and the step (2) according to the conventional assembly process, wherein the riveting or welding is according to the related design requirements;
(4) And (5) hanging down the two spliced fuselage middle sections after riveting or welding is finished, and finishing splicing.
(5) Repeating steps (1) - (4) in a subsequent splicing manner of the fuselage sections until the splicing is completed, for example: after riveting or welding, the two sections of the airframe middle sections which are spliced by butt joint are translated backwards by a crane or a power carrier 7, and then another section of airframe middle section is hoisted, and the splicing of the sections of airframe middle sections is the same as the steps 1-4, so that the method can continuously splice the sections of airframe middle sections until the splicing is finished.
Further, after step 2 and before step 3, if the assembly center lines of the two sections of the middle body are not aligned, the lifting device 8 is started to slightly jack up the middle body of the rear section, and then the stepping motor is started to drive the roller assembly to rotate, so that the middle body of the rear section is driven to rotate until the end parts of the middle body of the two sections are completely aligned.
It should be understood that the above description is not intended to limit the invention to the particular embodiments disclosed, but to limit the invention to the particular embodiments disclosed, and that the invention is not limited to the particular embodiments disclosed, but is intended to cover modifications, adaptations, additions and alternatives falling within the spirit and scope of the invention.
Claims (6)
1. A splicing method based on an aircraft middle section splicing device is characterized by comprising the following steps of: the machine comprises a main body frame (3) formed by a bottom frame (1) and two side brackets (2) on the left side and the right side of the bottom frame, wherein roller assemblies (5) for supporting each section of machine body middle section (4) are arranged on the two side brackets (2), a stepping motor (6) for driving each section of machine body middle section to rotate is arranged on at least one roller assembly (5), a power carrying table (7) capable of moving back and forth and a lifting device (8) arranged on the power carrying table (7) are arranged in the main body frame (3), and each section of machine body middle section can be supported by the roller assemblies (5), driven to rotate by the stepping motor (6) and can lift under the driving of the lifting device (8) and reciprocate back and forth through the bearing of the power carrying table (7); each roller assembly (5) comprises a support shaft mounted on the side support frame (2) and a plurality of support rollers mounted on the support shaft, and the splicing method comprises the following steps:
(1) Hanging one section of the middle body to be spliced onto two roller assemblies (5), and arranging one end of the middle body to be spliced at the gap between two supporting rollers of each roller assembly (5);
(2) The other section of the machine body middle section is hung on the two roller assemblies (5), a power carrying platform (7) is started to walk to the right lower part of the machine body middle section, and a lifting device (8) is started to jack up the machine body middle section; the jack-up rear power carrier (7) moves one end of the middle section of the machine body to the middle section of the front section of the machine body;
(3) Riveting or welding the two sections of the fuselage in step (1) and step (2) that are fully aligned;
(4) Hanging down after riveting or welding is finished, and finishing splicing;
after the step (2) and before the step (3), if the assembly center lines of the two sections of the middle body sections are not aligned, starting a lifting device (8) to slightly jack up the middle body section of the later section, and then starting a stepping motor to drive a roller assembly to rotate, so that the middle body section of the later section is driven to rotate until the end parts of the middle body sections of the two sections are completely aligned;
and (5) repeating the steps (1) - (4) in the subsequent splicing mode of the middle sections of the airframe until the splicing is finished.
2. A method of splicing based on aircraft mid-body splicing apparatus as defined in claim 1, wherein: the chassis (1) is provided with a track (9), and the power carrier (7) is arranged on the track.
3. A method of splicing based on aircraft mid-body splicing apparatus as defined in claim 2, wherein: the lifting device (8) is provided with V-shaped supporting blocks (10) which are used for being supported on the lower surface of each section of the machine body.
4. A splicing method based on an aircraft mid-body splicing device according to claim 1, 2 or 3, wherein: the power carrier (7) is an electric trolley with a driving motor inside.
5. A method of splicing based on an aircraft mid-body splicing device as defined in claim 4, wherein: the lifting device (8) is a hydraulic lifting device.
6. A method of splicing based on an aircraft mid-body splicing device as defined in claim 5, wherein: the side of main body frame (3) is provided with switch board (11), be provided with in switch board (11) and be used for providing the hydraulic press of power to elevating gear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111174602.5A CN113830324B (en) | 2021-10-09 | 2021-10-09 | Splicing device and splicing method for middle section of airplane body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111174602.5A CN113830324B (en) | 2021-10-09 | 2021-10-09 | Splicing device and splicing method for middle section of airplane body |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113830324A CN113830324A (en) | 2021-12-24 |
| CN113830324B true CN113830324B (en) | 2023-12-26 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111174602.5A Active CN113830324B (en) | 2021-10-09 | 2021-10-09 | Splicing device and splicing method for middle section of airplane body |
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Citations (10)
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|---|---|---|---|---|
| FR880050A (en) * | 1941-03-28 | 1943-03-11 | Messerschmitt Boelkow Blohm | Device for assembling aircraft fuselages with carrier wings, empennages and the like |
| US3465846A (en) * | 1967-07-10 | 1969-09-09 | Koor Ind & Crafts Co Ltd | Installation for approaching portions of an airplane |
| DE2823494A1 (en) * | 1978-05-30 | 1979-12-20 | Horst Hanschmann | Wing extension for glider - consists of triangle of fabric housed on rollers along fuselage and spread via sliders along wings |
| CN202607173U (en) * | 2012-04-12 | 2012-12-19 | 江苏保龙设备制造有限公司 | Splicing apparatus of log peeling machine drum body |
| CN103303491A (en) * | 2012-03-09 | 2013-09-18 | 陕西飞机工业（集团）有限公司 | Abutting technological equipment of airplane large components and abutting method thereof |
| CN105366072A (en) * | 2014-08-18 | 2016-03-02 | 空中客车德国运营有限责任公司 | Processing device for assembly of aircraft |
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| CN209078613U (en) * | 2018-09-25 | 2019-07-09 | 卓尔飞机制造（武汉）有限公司 | A kind of light-duty sport plane fuselage mounting tool |
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| CN112454250A (en) * | 2020-11-27 | 2021-03-09 | 广东智能无人系统研究院 | Inside subassembly dismouting device of large-scale ocean robot sealed cabin |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JP3752502B2 (en) * | 2004-03-26 | 2006-03-08 | 氣 木村 | Model flying toy that can change model |
| US7624488B2 (en) * | 2004-12-07 | 2009-12-01 | The Boeing Company | One-piece barrel assembly cart |
| EP3040265A1 (en) * | 2015-01-02 | 2016-07-06 | Airbus Operations GmbH | Method for joining two fuselage sections and mounting device |
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Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR880050A (en) * | 1941-03-28 | 1943-03-11 | Messerschmitt Boelkow Blohm | Device for assembling aircraft fuselages with carrier wings, empennages and the like |
| US3465846A (en) * | 1967-07-10 | 1969-09-09 | Koor Ind & Crafts Co Ltd | Installation for approaching portions of an airplane |
| DE2823494A1 (en) * | 1978-05-30 | 1979-12-20 | Horst Hanschmann | Wing extension for glider - consists of triangle of fabric housed on rollers along fuselage and spread via sliders along wings |
| CN103303491A (en) * | 2012-03-09 | 2013-09-18 | 陕西飞机工业（集团）有限公司 | Abutting technological equipment of airplane large components and abutting method thereof |
| CN202607173U (en) * | 2012-04-12 | 2012-12-19 | 江苏保龙设备制造有限公司 | Splicing apparatus of log peeling machine drum body |
| CN105366072A (en) * | 2014-08-18 | 2016-03-02 | 空中客车德国运营有限责任公司 | Processing device for assembly of aircraft |
| CN107108046A (en) * | 2014-09-22 | 2017-08-29 | 布勒特耶自动控制设备有限责任公司 | Process equipment for aircraft structure |
| CN209078613U (en) * | 2018-09-25 | 2019-07-09 | 卓尔飞机制造（武汉）有限公司 | A kind of light-duty sport plane fuselage mounting tool |
| CN110937132A (en) * | 2018-09-25 | 2020-03-31 | 空中客车德国运营有限责任公司 | Method for installing a system component in a section of an aircraft fuselage |
| CN112454250A (en) * | 2020-11-27 | 2021-03-09 | 广东智能无人系统研究院 | Inside subassembly dismouting device of large-scale ocean robot sealed cabin |
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| CN113830324A (en) | 2021-12-24 |
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