CN115946865A - Assembly tool for righting integration of lower assembly of large airplane and construction method thereof - Google Patents
Assembly tool for righting integration of lower assembly of large airplane and construction method thereof Download PDFInfo
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- CN115946865A CN115946865A CN202310173825.2A CN202310173825A CN115946865A CN 115946865 A CN115946865 A CN 115946865A CN 202310173825 A CN202310173825 A CN 202310173825A CN 115946865 A CN115946865 A CN 115946865A
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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
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Abstract
The invention discloses an assembly tool for righting integration of a lower assembly of a large airplane and a construction method thereof, and belongs to the technical field of civil aircraft production and manufacturing process equipment. The assembly tool for the righting integration of the lower assembly of the large airplane and the construction method thereof have the advantages that the number of tools is relatively small, and the lower assembly completed in an integrated mode does not need to be turned over. The assembly tool comprises a positioner, a support framework and a positioning base frame assembly, wherein at least one part of the positioner is arranged on the support framework through the positioning base frame assembly; in the process of righting and integrating the lower assembly of the large airplane, the bulkhead and the skin of the lower assembly of the large airplane are respectively positioned and fixed by the positioner under the matching of the positioning pedestal assembly, and the stringer of the lower assembly of the large airplane is positioned and fixed by the matching of the self-coordinating hole of the stringer on the bulkhead.
Description
Technical Field
The invention relates to an assembly tool, in particular to an assembly tool for righting integration of a lower assembly of a large airplane, and belongs to the technical field of civil aircraft production and manufacturing process equipment. The invention also relates to a construction method for rightly integrating the lower assembly of the large airplane by adopting the assembly tool.
Background
The modern large-scale aircraft fuselage mainly comprises a bulkhead, a stringer and a skin to form a thin-shell type closed structure, and is generally divided into an upper part and a lower part by taking a cabin-through floor as a boundary. In the process of airplane assembly, an upper assembly and a lower assembly are assembled respectively, and then a closed structure is formed by upper and lower involutions.
The assembly of the lower part assembly of the airplane refers to the steps of respectively positioning parts such as a bulkhead, a stringer and a skin through a positioner on a tool, ensuring the position precision, and forming the parts into a complete lower part assembly through hole making and riveting.
The assembly of the lower components of an aircraft is generally carried out in the following manner and sequence:
1) Assembling each wall plate:
(1) positioning the partition frames of the wall plates by the tool;
(2) the clamping plate and the positioning pin position each wall plate skin;
(3) the inner shapes of the stop block and the skin are used for positioning the stringers of the wallboard;
(4) and riveting the partition frame, the stringer and the skin to form the wallboard assembly.
2) And the wall plate assembly is involuted, the small assembly is involuted, and finally the lower assembly is formed.
3) The lower component turns over from the inverted state to the normal state.
Because the frock is the console mode, each locator sets up from ground top, consequently utilizes prior art scheme when assembling the lower part subassembly, adopts the back-off form usually to guarantee that bulkhead, stringer are located the skin below, can use the frock locator to fix a position.
Disadvantages of the prior art
1) The existing scheme needs a plurality of sets of wallboard assembling type frames, small component involution type frames and 1 set of turnover type frames, so that the number of tools is large, the occupied area is large, and the cost is high.
2) The existing scheme has poor man-machine engineering cooperativity, and particularly when holes are formed in the top of a product and riveted, operators cannot adopt comfortable operation postures, so that the production efficiency is reduced, and faults are easily caused.
3) After the lower part assembly of the existing scheme is assembled, the lower part assembly needs to be turned over, the length of the lower part assembly of the large airplane is usually large, the procedures of hoisting and turning over the large assembly are increased, the production efficiency is reduced, and the risk is increased.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the assembly tool for righting and integrating the lower components of the large airplane is relatively small in tool number, the lower components which are integrated do not need to be turned over, and the construction method for righting and integrating the lower components of the large airplane by the assembly tool is provided.
The technical scheme adopted for solving the technical problems is as follows: the assembly tool for the righting integration of the lower components of the large airplane comprises a positioner, a support framework and a positioning base frame component, wherein at least one part of the positioner is arranged on the support framework through the positioning base frame component; in the process of righting and integrating the lower assembly of the large airplane, the bulkhead and the skin of the lower assembly of the large airplane are respectively positioned and fixed by the positioner under the matching of the positioning pedestal assembly, and the stringer of the lower assembly of the large airplane is positioned and fixed by the matching of the self-coordinating hole on the bulkhead.
Furthermore, the positioner comprises a telescopic pull rod positioner and a rotary compaction positioner, and the telescopic pull rod positioner and the rotary compaction positioner are respectively and movably arranged at corresponding positions of the supporting framework directly or through the positioning base frame assembly; in the process of righting and integrating lower components of a large airplane, the partition frame is positioned and fixed under the matching of the supporting framework and the positioning base frame component through the telescopic pull rod positioner, and the skin is positioned and fixed through the matching of the rotary compression positioner and the telescopic pull rod positioner.
The supporting framework comprises an adjusting assembly and a box-type supporting truss, the top of the box-type supporting truss is of an open structure, the adjusting assembly is telescopically arranged on the outer side of the bottom of the box-type supporting truss along the height direction, and the positioner is arranged inside or at the top of the box-type supporting truss through the positioning base frame assembly or independently.
Furthermore, the tail part of the box type supporting truss is in a V-shaped structure which is gradually reduced in the length direction and is matched with the shape of a large airplane lower component to be integrated, and a positioner is arranged in the V-shaped structure through the positioning base frame component or independently.
In a preferred mode of the above scheme, the adjusting assembly includes a plurality of sets of lifting adjusting rotating members, and each set of lifting adjusting rotating members is fixedly mounted on the outer side of the bottom surface of the box-type supporting truss and can be lifted and lowered along the height direction according to a specified distance.
The positioning pedestal assembly comprises a large V-shaped support group, a small V-shaped support group and an M-shaped support group, the large V-shaped support group is arranged on the section with the upright column in the box-type supporting truss, the small V-shaped support group is arranged in the box-type supporting truss between two adjacent groups of large V-shaped support groups, the M-shaped support group and parts of the lower assembly of the large airplane which need to be integrated are arranged on the section without the upright column in the box-type supporting truss in a position matching manner, and the positioner is arranged in the box-type supporting truss through the large V-shaped support group, the small V-shaped support group and the M-shaped support group respectively.
The construction method for righting and integrating the lower component of the large airplane by adopting the assembly tool is characterized in that the righting and integration of the lower component of the large airplane is completed at one time by the following steps on the basis of the assembly tool which is manufactured and erected,
1) Firstly, positioning all the partition frames by using a positioner;
2) Then positioning all the stringers under the matching of the coordination holes on the bulkheads through the coordination holes made on the stringers;
3) Then, all the partition frames and the stringers are subjected to hole-making riveting to form a rigid framework;
4) Then, a telescopic positioner for fixing the partition frame in the positioner is contracted to the outer side of the skin, and the skin is positioned by using a rigid framework formed by riveting, a telescopic pull rod positioner and a rotary compression positioner;
5) And finally, covering, perforating and riveting to form a complete assembly.
The preferable mode of the scheme is that when the assembly tool is manufactured and erected, firstly, an assembled box type supporting truss and an adjusting assembly at the bottom of the assembled box type supporting truss are manufactured, then a large V-shaped support group, a small V-shaped support group and an M-shaped support group are installed, and finally, telescopic pull rod positioners for positioning the separation frames and a rotary pressing positioner for pressing the skin are installed on the box type supporting truss, the V-shaped support group, the small V-shaped support group and the M-shaped support group to finish the manufacturing and erection of the assembly tool;
when the partition frames are positioned by the positioner, each partition frame station is positioned by 2-3 groups of telescopic positioners;
when the stringers are positioned, a connecting piece hole is used as a coordination hole at the connecting position of each stringer and the corresponding partition frame, and the stringers are positioned through the coordination hole;
when riveting the stringer and the bulkhead, firstly respectively manufacturing connecting holes on the stringer and the bulkhead, and then riveting to form a rigid framework;
after the rigid framework is riveted, the bulkhead telescopic positioner is contracted to the outer side of the skin, the rigid framework formed by riveting is used for positioning the skin, the skin is compressed by adopting the telescopic pull rod positioner and the rotary compression positioner arranged on the outer side, and finally the skin is riveted to form the normal position integration of the lower assembly of the complete large airplane.
The invention has the beneficial effects that: the technical scheme provided by the application is based on the existing positioner, a new assembly tool is formed by additionally arranging a supporting framework and a positioning base frame assembly, and then at least one part of the positioner is arranged on the supporting framework through the positioning base frame assembly; therefore, when the lower assembly of the large airplane is integrated, upward righting can be adopted for integration, in the righting integration process, the bulkhead and the skin of the lower assembly of the large airplane are respectively positioned and fixed under the matching of the positioning base frame assembly through the positioner, and then the stringer of the lower assembly of the large airplane is positioned and fixed under the matching of the coordinating hole of the stringer on the bulkhead through the coordinating hole of the stringer. In the specific construction process, 1) positioning all the partition frames by adopting a positioner; 2) Then positioning all the stringers under the matching of the coordination holes on the partition frames through the coordination holes made on the stringers; 3) Then, all the partition frames and the stringers are subjected to hole-making riveting to form a rigid framework; 4) Then, a telescopic positioner for fixing the partition frame in the positioner is contracted to the outer side of the skin, and the skin is positioned by using a rigid framework formed by riveting, a telescopic pull rod positioner and a rotary positioner; 5) And finally, covering, perforating and riveting to form a complete assembly. Like this, accomplish the bulkhead through disposable frock and under the cooperation of locator, stringer and external skin's location, equipment and fixed, the quantity of reduction frock that not only can show, and because what this application adopted when the lower part subassembly of integrated big aircraft is just integrated, it is integrated that "just position" state that the opening is ascending is integrated to not "back-off" integration promptly, thereby also need not turn over the operation after the integration is accomplished, the operation risk has been reduced, the production efficiency is improved, simultaneously can also furthest guarantee integrated quality.
Drawings
FIG. 1 is a schematic three-dimensional structure diagram of an assembly fixture for righting integration of lower components of a large airplane according to the invention;
FIG. 2 is a front view of the assembly fixture for the righting integration of the lower components of the large aircraft according to the present invention;
FIG. 3 is a top view of FIG. 2;
fig. 4 is a side view of fig. 2.
Labeled as: the device comprises a positioner 1, a supporting framework 2, a positioning pedestal assembly 3, a telescopic pull rod positioner 4, a rotary compaction positioner 5, an adjusting assembly 6, a box-type supporting truss 7, a lifting adjusting rotating assembly 8, a large V-shaped support assembly 9, an M-shaped support assembly 10 and a small V-shaped support assembly 11.
Detailed Description
Fig. 1 to 4 show an assembly tool for righting and integrating a lower assembly of a large airplane, which has a relatively small number of tools and does not need to turn over the assembled lower assembly, and a construction method for righting and integrating the lower assembly of the large airplane by using the assembly tool. The assembly tool comprises a positioner 1, a support framework 2 and a positioning base frame component 3, wherein at least one part of the positioner 1 is arranged on the support framework 2 through the positioning base frame component 3; in the process of righting and integrating the lower assembly of the large airplane, the bulkhead and the skin of the lower assembly of the large airplane are positioned and fixed under the matching of the positioning pedestal assembly 3 through the positioner 1, and the stringer of the lower assembly of the large airplane is positioned and fixed under the matching of the upper coordinating hole of the bulkhead through the self coordinating hole. The technical scheme provided by the application is based on the existing positioner, a new assembly tool is formed by additionally arranging a supporting framework and a positioning base frame assembly, and then at least one part of the positioner is arranged on the supporting framework through the positioning base frame assembly; therefore, when the lower assembly of the large airplane is integrated, upward righting can be adopted for integration, in the righting integration process, the bulkhead and the skin of the lower assembly of the large airplane are respectively positioned and fixed under the matching of the positioning base frame assembly through the positioner, and then the stringer of the lower assembly of the large airplane is positioned and fixed under the matching of the coordination hole on the bulkhead through the coordination hole of the stringer. In the specific construction process, 1) positioning all the partition frames by adopting a positioner; 2) Then positioning all the stringers under the coordination of the partition frames through the coordination holes made on the stringers; 3) Then, all the partition frames and the stringers are subjected to hole-making riveting to form a rigid framework; 4) Then, a telescopic positioner for fixing the partition frame in the positioner is contracted to the outer side of the skin, and the skin is positioned by utilizing a rigid framework formed by riveting, a telescopic pull rod positioner and a rotary positioner; 5) And finally, covering, perforating and riveting to form a complete assembly. Like this, through disposable frock and accomplish the bulkhead under the cooperation of locator, stringer and external skin's location, equipment and fixed, the quantity of reduction frock that not only can show, moreover because what this application adopted when the lower part subassembly of integrated big aircraft is just integrated, it is integrated that "just position" state of opening is ascending promptly not "back-off" is integrated, thereby also need not turn over the operation after integrated completion, the operation risk has been reduced, the production efficiency is improved, simultaneously can also furthest's assurance integrated quality.
Correspondingly, as the integration mode of the application and the innovative improvement of the inverted buckle type in the prior art are integrated for the upright position with the opening upwards, and for the purpose of facilitating the support of the bulkhead, the stringer and the external skin, the application divides the positioner 1 into a telescopic pull rod positioner 4 and a rotary compression positioner 5, and the telescopic pull rod positioner 4 and the rotary compression positioner 5 are respectively and directly or movably arranged at corresponding positions of the support framework 2 through the positioning base frame assembly 3; therefore, in the process of righting and integrating the lower assembly of the large airplane, the bulkhead can be positioned and fixed by the telescopic pull rod positioner 4 under the matching of the supporting framework and the positioning base frame assembly 3, and the skin is positioned and fixed by the rotating compression positioner 5 and the telescopic pull rod positioner 4. Simultaneously, for the quantity of furthest's reduction frock, simultaneously again can once only accomplish the fixed riveting of bulkhead and stringer to and the compressing tightly of epilogue covering, location and riveting, this application support chassis 2 include adjusting part 6 and box support truss 7, box support truss 7's top is for opening the structure, adjusting part 6 arrange the outside in box support truss 7 bottom surface along the direction of height telescopic, locator 1 pass through location bed frame subassembly 3 or independent arrange at box support truss 7's inside or top. In combination with the shape and structure of the lower assembly of the large airplane, the tail part of the box-type supporting truss 7 is in a V-shaped structure which is gradually reduced in the length direction and is matched with the shape of the lower assembly of the large airplane to be integrated, and the positioner 1 is also arranged in the V-shaped structure through the positioning pedestal assembly 3 or independently. At this moment, this application combines the actual condition of production to and big aircraft self structural feature, this application location bed frame subassembly 3 include big V type support group 9, little V type support group 11 and M type support group 10, big V type support group 9 arrange in box supporting truss 7 on the cross-section that has stand 10, little V type support group 11 arrange in box supporting truss 7 between two sets of adjacent big V type support groups 9, M type support group 10 and big aircraft lower part subassembly need the integrated spare part position suited arrange in box supporting truss 7 on the cross-section that does not set up the stand, locator 1 respectively through big V type support group 9, little V type support group 11 with M type support group 10 arrange in box supporting truss 7.
Further, in order to adjust the assembly fixture during use, the adjusting assembly 6 includes a plurality of sets of lifting adjusting rotating members 8, and each set of lifting adjusting rotating members 8 is fixedly mounted at the outer side of the bottom of the box-type supporting truss 7 and can be extended and lifted along the height direction according to a specified distance.
The assembly tool is required to be manufactured and erected before the lower assembly of the large airplane is integrated, and the specific process comprises the steps of manufacturing and assembling a box type supporting truss and an adjusting assembly at the bottom of the box type supporting truss, mounting a large V-shaped support group, a small V-shaped support group and an M-shaped support group, and finally mounting a telescopic pull rod positioner of a positioning bulkhead and a rotary pressing positioner of a pressing skin on the box type supporting truss, the large V-shaped support group, the small V-shaped support group and the M-shaped support group to finish the manufacturing and erection of the assembly tool;
when the partition frames are positioned by the positioner, each partition frame station is positioned by 2-3 groups of telescopic positioners;
when the stringers are positioned, a connecting piece hole is used as a coordination hole at the connecting position of each stringer and the corresponding partition frame, and the stringers are positioned through the coordination hole;
when riveting the stringer and the bulkhead, firstly respectively manufacturing connecting holes on the stringer and the bulkhead, and then riveting to form a rigid framework;
after the rigid framework is riveted, the bulkhead telescopic positioner is contracted to the outer side of the skin, the rigid framework formed by riveting is used for positioning the skin, the skin is compressed by adopting the telescopic pull rod positioner and the rotary compression positioner arranged on the outer side, and finally the skin is riveted to form the normal position integration of the lower assembly of the complete large airplane.
The coordination hole of this application: refers to a hole which is opened at the position of a connecting piece and is used for coordinating and positioning parts or components during assembly, and the hole diameter is generally phi 3.2mm.
In conclusion, by adopting the technical scheme provided by the application, a plurality of sets of tool functions are integrated on 1 set of tool, so that the number of tools and the occupied area are reduced, and the cost is reduced; the assembly mode and sequence are optimized, the telescopic pull rod positioner and the like are adopted, the man-machine engineering cooperativity is improved, and the production efficiency and quality are improved; the turning-over process is cancelled by adopting the normal position assembly, so that the production efficiency is improved, and the potential safety hazard of turning-over is avoided.
In the technical scheme provided by the application, the lower component is assembled in a correct position in the following assembling mode and sequence:
1) Positioning all the partition frames by a tool;
2) The coordination holes position all the stringers;
3) Riveting all the partition frames and the stringer holes to form a rigid framework;
4) The spacer frame telescopic positioner is contracted to the outer side of the skin, and the skin is positioned by utilizing a rigid framework formed by riveting;
5) And (5) carrying out skin hole-making riveting to form a complete assembly. The complete tool is shown in figures 1 to 4, a telescopic pull rod positioner is arranged on the tool and used for positioning a bulkhead, and a rotary compressor is arranged and used for compressing a skin;
each partition frame station is provided with 2-3 groups of telescopic positioners for positioning the partition frame;
the connection position of each stringer and each partition frame is provided with a coordination positioning hole by means of a connecting piece hole, and the stringers are positioned;
manufacturing a stringer and a bulkhead connecting hole, and riveting to form a rigid framework;
the spacer frame telescopic positioner is contracted to the outer side of the skin, the skin is positioned by utilizing a rigid framework formed by riveting, and a rotary compressor is arranged on the outer side of the skin and used for compressing the skin;
and riveting the skin to form the complete assembly.
Claims (8)
1. A assembly fixture for big aircraft lower part subassembly normal position is integrated, including locator (1), its characterized in that: the assembling tool further comprises a supporting framework (2) and a positioning base frame component (3), and at least one part of the positioner (1) is arranged on the supporting framework (2) through the positioning base frame component (3); in the process of righting and integrating the lower assembly of the large airplane, the bulkhead and the skin of the lower assembly of the large airplane are respectively positioned and fixed under the matching of the positioning base frame assembly (3) through the positioner (1), and the stringer of the lower assembly of the large airplane is positioned and fixed under the matching of the coordination holes on the bulkhead through the coordination holes of the stringer.
2. The assembly tool for the normal position integration of the lower assembly of the large airplane as claimed in claim 1, wherein: the positioner (1) comprises a telescopic pull rod positioner (4) and a rotary compaction positioner (5), wherein the telescopic pull rod positioner (4) and the rotary compaction positioner (5) are respectively and movably arranged at corresponding positions of the supporting framework (2) directly or through the positioning base frame assembly (3); in the process of righting and integrating the lower assembly of the large airplane, the spacer frame is positioned and fixed under the matching of the supporting framework (2) and the positioning pedestal assembly (3) through the telescopic pull rod positioner (4), and the skin is positioned and fixed through the matching of the rotary compression positioner (5) and the telescopic pull rod positioner (4).
3. The assembly tool for the normal position integration of the lower assembly of the large airplane as claimed in claim 1 or 2, wherein: the supporting framework (2) comprises an adjusting component (6) and a box-type supporting truss (7), the top of the box-type supporting truss (7) is of an open structure, the adjusting component (6) is arranged on the outer side of the bottom of the box-type supporting truss (7) in a telescopic mode along the height direction, and the positioner (1) is arranged inside or at the top of the box-type supporting truss (7) through the positioning pedestal component (3) or independently.
4. The assembly tool for the normal position integration of the lower assembly of the large airplane as claimed in claim 3, wherein: the tail part of the box type supporting truss (7) is of a V-shaped structure which is gradually reduced in the length direction and is adaptive to the shape of a lower component of a large airplane to be integrated, and a positioner (1) is arranged in the V-shaped structure through the positioning base frame component (3) or independently.
5. The assembly tool for the righting integration of the lower assembly of the large airplane as claimed in claim 4, wherein: the adjusting assembly (6) comprises a plurality of groups of lifting adjusting rotating member groups (8), and each group of lifting adjusting rotating member group (8) can be fixedly arranged on the outer side of the bottom surface of the box-type supporting truss (7) in a stretching and lifting manner along the height direction according to a specified interval.
6. The assembly tool for the normal position integration of the lower assembly of the large airplane as claimed in claim 5, wherein: the positioning pedestal assembly (3) comprises large V-shaped support groups (9), small V-shaped support groups (11) and M-shaped support groups (10), wherein the large V-shaped support groups (9) are arranged on the section with the upright posts (10) in the box-type supporting truss (7), the small V-shaped support groups (11) are arranged in the box-type supporting truss (7) between the two adjacent large V-shaped support groups (9), the M-shaped support groups (10) and components of the lower part of the large airplane, which need to be integrated, are arranged on the section without the upright posts in the box-type supporting truss (7) in a position matching mode, and the positioner (1) is arranged in the box-type supporting truss (7) through the large V-shaped support groups (9), the small V-shaped support groups (11) and the M-shaped support groups (10) respectively.
7. A construction method using the assembly fixture of claim 6, characterized in that: the construction method is based on the assembly tool which is manufactured and erected, and completes the normal integration of the lower component of the large airplane at one time according to the following steps,
1) Firstly, positioning all the partition frames by using a positioner;
2) Then positioning all the stringers under the matching of the coordination holes on the bulkheads through the coordination holes made on the stringers;
3) Then, all the partition frames and the stringers are subjected to hole-making riveting to form a rigid framework;
4) Then, a telescopic positioner for fixing the partition frame in the positioner is contracted to the outer side of the skin, and the skin is positioned by utilizing a rigid framework formed by riveting, a telescopic pull rod positioner and a rotary compaction positioner;
5) And finally, covering, drilling holes and riveting to form a complete assembly.
8. The construction method according to claim 7, wherein: when the assembly tool is manufactured and erected, firstly manufacturing an assembly box type support truss and an adjusting assembly at the bottom of the assembly box type support truss, then installing a large V-shaped support group, a small V-shaped support group and an M-shaped support group, and finally installing a telescopic pull rod positioner for positioning a separation frame and a rotary pressing positioner for pressing a skin on the box type support truss, the large V-shaped support group, the small V-shaped support group and the M-shaped support group to finish the manufacturing and erection of the assembly tool;
when the partition frames are positioned by the positioner, each partition frame station is positioned by 2-3 groups of telescopic positioners;
when the stringers are positioned, a connecting piece hole is used as a coordination hole at the connecting position of each stringer and the corresponding partition frame, and the stringers are positioned through the coordination hole;
when the stringer and the bulkhead are riveted, connecting holes on the stringer and the bulkhead are respectively manufactured firstly, and then the stringer and the bulkhead are riveted to form a rigid framework;
after the rigid framework is riveted, the bulkhead telescopic positioner is contracted to the outer side of the skin, the rigid framework formed by riveting is used for positioning the skin, the skin is compressed by adopting the telescopic pull rod positioner and the rotary compression positioner arranged on the outer side, and finally the skin is riveted to form the normal position integration of the lower assembly of the complete large airplane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310173825.2A CN115946865B (en) | 2023-02-28 | 2023-02-28 | Assembly fixture for righting integration of lower assembly of large aircraft and construction method of assembly fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310173825.2A CN115946865B (en) | 2023-02-28 | 2023-02-28 | Assembly fixture for righting integration of lower assembly of large aircraft and construction method of assembly fixture |
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| CN115946865A true CN115946865A (en) | 2023-04-11 |
| CN115946865B CN115946865B (en) | 2023-05-12 |
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Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050045693A1 (en) * | 2003-08-25 | 2005-03-03 | Buchheit Jack G. | Adaptable spring force clamping apparatus and methods |
| EP2277777A1 (en) * | 2008-05-19 | 2011-01-26 | Airbus Operations S.L. | Method and tool for mounting torsion boxes for use in aeronautics |
| CN102745338A (en) * | 2012-07-05 | 2012-10-24 | 浙江大学 | Digitalized assembly system for bodies of large planes |
| US20130019446A1 (en) * | 2011-07-21 | 2013-01-24 | Spirit Aerosystems, Inc. | System and method for assembling aircraft components |
| CN103921116A (en) * | 2014-04-24 | 2014-07-16 | 浙江大学 | Flexible assembly system for aircraft panel |
| 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 |
| CN106742041A (en) * | 2016-12-19 | 2017-05-31 | 中航成飞民用飞机有限责任公司 | Aircraft skin positioning compression device |
| US20200094991A1 (en) * | 2018-09-25 | 2020-03-26 | Airbus Operations Sas | Method for assembling an aircraft fuselage section from two superposed upper and lower parts, multipurpose mounting support, gear and fuselage section production unit for implementing said method |
| CN212399311U (en) * | 2020-04-24 | 2021-01-26 | 成都飞机工业（集团）有限责任公司 | Flexible assembly of aircraft wallboard and confined space system hole frock |
| CN113120255A (en) * | 2021-04-30 | 2021-07-16 | 成都飞机工业（集团）有限责任公司 | Full quick-witted assembly fixture of integral type |
| CN216611660U (en) * | 2021-12-30 | 2022-05-27 | 中航成飞民用飞机有限责任公司 | Automatic drilling and riveting assembly tool for aircraft panel |
| CN216781624U (en) * | 2021-10-29 | 2022-06-21 | 长春恒翔航空技术装备有限公司 | Assembly fixture for wall plate at rear upper part of rear fuselage of airplane |
-
2023
- 2023-02-28 CN CN202310173825.2A patent/CN115946865B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050045693A1 (en) * | 2003-08-25 | 2005-03-03 | Buchheit Jack G. | Adaptable spring force clamping apparatus and methods |
| EP2277777A1 (en) * | 2008-05-19 | 2011-01-26 | Airbus Operations S.L. | Method and tool for mounting torsion boxes for use in aeronautics |
| ES2357489A1 (en) * | 2008-05-19 | 2011-04-27 | Airbus Operations, S.L. | Method and tool for mounting torsion boxes for use in aeronautics |
| US20130019446A1 (en) * | 2011-07-21 | 2013-01-24 | Spirit Aerosystems, Inc. | System and method for assembling aircraft components |
| CN102745338A (en) * | 2012-07-05 | 2012-10-24 | 浙江大学 | Digitalized assembly system for bodies of large planes |
| CN103921116A (en) * | 2014-04-24 | 2014-07-16 | 浙江大学 | Flexible assembly system for aircraft panel |
| 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 |
| CN106742041A (en) * | 2016-12-19 | 2017-05-31 | 中航成飞民用飞机有限责任公司 | Aircraft skin positioning compression device |
| US20200094991A1 (en) * | 2018-09-25 | 2020-03-26 | Airbus Operations Sas | Method for assembling an aircraft fuselage section from two superposed upper and lower parts, multipurpose mounting support, gear and fuselage section production unit for implementing said method |
| CN212399311U (en) * | 2020-04-24 | 2021-01-26 | 成都飞机工业（集团）有限责任公司 | Flexible assembly of aircraft wallboard and confined space system hole frock |
| CN113120255A (en) * | 2021-04-30 | 2021-07-16 | 成都飞机工业（集团）有限责任公司 | Full quick-witted assembly fixture of integral type |
| CN216781624U (en) * | 2021-10-29 | 2022-06-21 | 长春恒翔航空技术装备有限公司 | Assembly fixture for wall plate at rear upper part of rear fuselage of airplane |
| CN216611660U (en) * | 2021-12-30 | 2022-05-27 | 中航成飞民用飞机有限责任公司 | Automatic drilling and riveting assembly tool for aircraft panel |
Non-Patent Citations (3)
| Title |
|---|
| 常颂扬;王鸿昇，上官敬益，朱雷，冯军，郑晨绩，方强: "基于蒙皮内形定位的飞机壁板柔性装配系统", 航空制造技术 * |
| 成书民;张海宝;康永刚;: "数字化装配技术及工艺装备在大型飞机研制中的应用", 航空制造技术 * |
| 王焰，郭宏伟，邓伯孟，尧智: "基于MBD的公务机机头孔系定位装配技术应用与研究", 装备制造技术 * |
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