CN109664098A - Flexible frock and its assembly technology for aircraft door assembly - Google Patents
Flexible frock and its assembly technology for aircraft door assembly Download PDFInfo
- Publication number
- CN109664098A CN109664098A CN201811533286.4A CN201811533286A CN109664098A CN 109664098 A CN109664098 A CN 109664098A CN 201811533286 A CN201811533286 A CN 201811533286A CN 109664098 A CN109664098 A CN 109664098A
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- assembly
- frame
- main body
- positioning
- flexible
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P21/00—Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
- B23Q3/02—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine for mounting on a work-table, tool-slide, or analogous part
- B23Q3/06—Work-clamping means
- B23Q3/062—Work-clamping means adapted for holding workpieces having a special form or being made from a special material
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Automatic Assembly (AREA)
Abstract
The present invention relates to a kind of flexible frocks for aircraft door assembly, are made of main body frame and assembly jig；It is equipped with concave curvature on the surface of main body frame, several equally distributed flexible positioning components, the vacuum absorption device on flexible positioning component are equipped on concave curvature, and adsorb aircraft skin to be assembled；The bottom of assembly jig is equipped with mobile base, and assembly jig is equipped with curved-surface structure, and corresponding with the curvature of main body frame concave curvature；Several zero-point positioning devices are equipped on the surface of main body frame, are equipped with zero-point positioning connector in the corresponding position of assembly jig, zero-point positioning connector and zero-point positioning device cooperate.The tooling can control program by changing, the absorption point that electric-control system can drive flexible positioning component production to comply fully with door panels component curved surface, to accurately, reliable position and clamp covering, when hatch door shape changes, absorption point can carry out digitlization adjustment, to adapt to different door panels component shapes.
Description
Technical field
The present invention relates to a kind of flexible frocks and its assembly technology for aircraft door assembly, belong to mechanical assembly technique
Field.
Background technique
Aircraft tooling accounts in Aircraft Production as the special equipment for guaranteeing that aircraft manufacturing and Assembly veracity require
Play the role of very important.Traditional aircraft door technological equipment largely uses rigid structure, manufactures and designs period length, is developed into
This height, opening character be poor, using single, and each hatch door Product Assembly requires to be equipped with dedicated technological equipment, for product structure
Variation, can not accomplish quickly to respond.Flexible frock of the invention includes the flexible positioning type frame and positioning for positioning door panels
Framework location type frame two parts of hatch door skeleton, door panels positioning type frame can satisfy multiple hatch door Assembling Productions, and hatch door covers
The positioning of skin shape positions type frame using the sucking disc type flexible that array multiple spot vacuum chuck forms, and sucker is in the case where controlling process control
Running fix is carried out, the absorption dot matrix complied fully with door panels component curved surface is generated, to accurately, reliable position and press from both sides
Covering is held, when hatch door shape changes, absorption dot matrix can carry out numeralization adjustment, to adapt to different door panels groups
The framework location of part shape, every set hatch door is equipped with dedicated type frame, combines with door panels positioning type frame and completes a set of hatch door
Assembling Production.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of flexible frock for aircraft door assembly and its assemblers
Skill, the tooling can satisfy the Assembling Production of multiple hatch doors, control program by changing, electric-control system can drive flexible positioning
The absorption point that component production is complied fully with door panels component curved surface works as cabin to accurately, reliable position and clamp covering
When shape changes outdoors, absorption point can carry out digitlization adjustment, to adapt to different door panels component shapes.
In order to solve the above problem, the specific technical solution of the present invention is as follows: a kind of flexible work for aircraft door assembly
Dress, is made of main body frame and assembly jig；It is equipped with concave curvature on the surface of main body frame, is equipped on concave curvature several
A equally distributed flexible positioning component, the vacuum absorption device on flexible positioning component, and adsorb aircraft skin to be assembled；Dress
Bottom with type frame is equipped with mobile base, and assembly jig is equipped with curved-surface structure, and corresponding with the curvature of main body frame concave curvature；
Several zero-point positioning devices are equipped on the surface of main body frame, are equipped with zero-point positioning connector in the corresponding position of assembly jig,
Zero-point positioning connector and zero-point positioning device cooperate.
The flexible positioning component is sequentially connected by sucker group, cup holder, electric pushrod and servo motor to be formed；Sucker group
It is arranged in outside the concave curvature of main body frame with cup holder；In the front end of electric pushrod, connecting plate, connecting plate and main body frame are set
Surface connection；Support is set in the rear end of electric pushrod, support is connect with main body frame inner frame.
The main body of the cup holder is equipped with hemisphere face groove, and spherical groove bottom is equipped with magnet；Sucker group is by hemisphere
It is formed with sucker, sucker is located on hemisphere end face, and hemisphere is landed in the hemisphere groove of cup holder, and attracting with magnet.
The both ends of the assembly jig are respectively equipped with shaft, are equipped with bearing block, shaft and axis in mobile base upper surface
Seat assembly is held, and one end of shaft is connect with operated motor.
The main body of the assembly jig is frame, blade assemblies is respectively equipped on frame, shaft assembly, side frame in promotion
Positioning component holds down assembly and examines component with covering.
Two supporting plates are symmetrical arranged on the frame, each supporting plate is welded on frame by positioning angle section respectively up and down
In length sides；It is uniformly distributed three limit plates vertically on positioning angle section, limit plate surface limits hatch door skeleton；One wherein
The middle part of supporting plate, which is flexibly connected, promotes upper shaft assembly, and shaft assembly is equipped with locating shaft in promotion, and locating shaft positions hatch door skeleton
Three through-holes, guarantee its concentricity.
The frame upper and lower side frame is respectively equipped with side frame positioning component, the structure of side frame positioning component are as follows: connects with frame
Locating shaft is set on the support connect, and the end of locating shaft is equipped with handle and passes through support, and the surface of support is equipped with cover board, on cover board
It is sold equipped with compressing, compresses pin and held out against across cover board and locating shaft.
Described holding down assembly is divided into several, and is uniformly arranged on the upper and lower side frame of frame, wherein holding down assembly as T
Font structure, is equipped with hold-down bolt in fact, and hold-down bolt is pressed on corresponding hatch door skeleton.
The covering examines that component is rectangular to be distributed on the upper and lower side frame of frame.
The assembly technology that aircraft door is assembled using the flexible frock that aircraft door assembles, comprising the following steps:
1) aircraft door covering is mounted in hatch door Skeleton assembly type frame；
2) mobile base of mobile main body frame bottom, by the zero-point positioning of Zero-point positioning system and the corresponding position of assembly jig
Connector cooperation realizes that assembly jig and main body frame link together；
3) flexible positioning component is driven to form positioning door panels shape by external electric-control system；
4) gas source is opened, after stable gas pressure, vacuum absorption device completion is opened and vacuumizes, cover flexible positioning component and hatch door
Leather block is combined；
5) other components by hatch door in addition to covering carry out the assembly of hatch door in hatch door Skeleton assembly type frame.
The flexible frock for being used for aircraft door assembly positions door panels by vacuum suction, effectively maintains hatch door
Original form, and hatch door skeleton is installed using assembly jig, to realize assembly precision, guarantee the efficiency and matter integrally assembled
Amount.
Sucker connects to form vacuum absorption device with cup holder in flexible positioning component, and utilizes electric pushrod and servo motor
The extended position of sucker is controlled, guarantees to be formed and the consistent curved-surface shape of Skinning Surfaces when whole sucker working conditions.
Vacuum chuck and cup holder mating spherical surfaces are simultaneously adsorbed using magnet, guarantee the universal structure of vacuum chuck, with suitable
Answer the cabin door structure of different model.
Assembly jig is connect with mobile base using bearing block, keeps assembly jig rotatable, convenient in assembly jig upper-deck cabin
The installation positioning of door skeleton, improves assembly efficiency.
The main body of assembly jig is frame, blade assemblies is respectively equipped on frame, shaft assembly, side frame positioning group in promotion
Part holds down assembly and examines component with covering, each serves as the effect of positioning or limit, guarantees the positioning accuracy of hatch door skeleton.Its
Three limit plates on middle supporting plate limit hatch door skeleton；Locating shaft in promotion on shaft assembly is for limiting hatch door skeleton
On three holes coaxially set；Side frame positioning component is for limiting side frame position；It holds down assembly and hatch door component is compressed；
Covering examines component to check the position of covering.
The tooling of the application uses above-mentioned processing step to the assembly technology that aircraft door assembles, and it is fixed can to fast implement covering
Position, hatch door skeleton and covering can Fast Installation, realize that worker operation is convenient, labor intensity is low, highly-safe, improve production effect
Rate.
Detailed description of the invention
Fig. 1 is the main view of the flexible frock assembled for aircraft door.
Fig. 2 is the top view of the flexible frock assembled for aircraft door.
Fig. 3 is the structural schematic diagram of flexible positioning component.
Fig. 4 is the assembling schematic diagram of sucker group and cup holder
Fig. 5 is the main view of assembly jig.
Fig. 6 is support board structure schematic diagram.
Fig. 7 is to promote upper shaft assembly structural schematic diagram.
Fig. 8 is side frame positioning component structural schematic diagram.
Specific embodiment
As depicted in figs. 1 and 2, a kind of flexible frock for aircraft door assembly, by main body frame 3 and assembly jig 5
Composition；It is equipped with concave curvature on the surface of main body frame 3, several equally distributed flexible positioning groups are equipped on concave curvature
Part 4, the vacuum absorption device on flexible positioning component 4, and adsorb aircraft skin to be assembled；The bottom of assembly jig 5, which is equipped with, to be moved
Dynamic pedestal 6, assembly jig 5 are equipped with curved-surface structure, and corresponding with the curvature of 3 concave curvature of main body frame；In the table of main body frame 3
Face is equipped with several zero-point positioning devices 8, is equipped with zero-point positioning connector, zero-point positioning connector in the corresponding position of assembly jig 5
Cooperate with zero-point positioning device 8.
As shown in figure 3, the flexible positioning component 4 by sucker group 46, cup holder 45, electric pushrod 44 and servo motor according to
Secondary connection composition；Sucker group 46 and cup holder 45 are arranged in outside the concave curvature of main body frame 3；It is arranged in the front end of electric pushrod 44
Connecting plate 41, connecting plate 41 are connect with 3 surface of main body frame；In the rear end of electric pushrod 44, support 42, support 42 and master are set
The connection of 3 inner frame of body frame.
As shown in figure 4, the main body of the cup holder 45 is equipped with hemisphere face groove, spherical groove bottom is equipped with magnet 452；
Sucker group 46 is made of hemisphere 464 and sucker 461, and sucker 461 is located on 464 end face of hemisphere, and hemisphere 464 is landed in
In the hemisphere groove of cup holder 45, and it is attracting with magnet 452.
As shown in figure 5, the both ends of the assembly jig 5 are respectively equipped with shaft, bearing is equipped in 6 upper surface of mobile base
Seat, shaft and bearing block assemble, and one end of shaft is connect with operated motor 58.
As shown in fig. 6, the main body of the assembly jig 5 be frame 51, be respectively equipped on frame 51 blade assemblies 52,
Shaft assembly 53, side frame positioning component 54 in promotion, hold down assembly 55 and covering examine component 56.
As shown in fig. 7, being symmetrical arranged two supporting plates 52 on the frame 51, each about 52 supporting plate passes through positioning respectively
Angle section 521 is welded in the length sides of frame 51；It is uniformly distributed three limit plates 522, limit plate vertically on positioning angle section 521
522 surfaces limit hatch door skeleton；It is flexibly connected at the middle part of a wherein supporting plate 52 and promotes upper shaft assembly 53, shaft assembly in promotion
53 are equipped with locating shaft 534, and locating shaft 534 positions three through-holes of hatch door skeleton, guarantees its concentricity.
As shown in figure 8,51 upper and lower side frame of frame is respectively equipped with side frame positioning component 54, side frame positioning component 54
Structure are as follows: locating shaft 546 is set on the support 545 connecting with frame 51, and the end of locating shaft 546 is equipped with handle 541 and passes through
Support 545, the surface of support 545 are equipped with cover board 543, and cover board 543, which is equipped with, compresses pin 544, compress pin 544 and pass through cover board 543
It is held out against with locating shaft 546.
Described holds down assembly 55 points as several, and is uniformly arranged on the upper and lower side frame of frame 51, wherein compression group
Part 55 is T font structure, is equipped with hold-down bolt in fact, and hold-down bolt is pressed on corresponding hatch door skeleton；The covering
It examines on the rectangular upper and lower side frame for being distributed in frame 51 of component 56.
The assembly technology that aircraft door is assembled using the flexible frock that aircraft door assembles, comprising the following steps:
1) aircraft door covering is mounted in hatch door Skeleton assembly type frame 5；
2) mobile base 6 of mobile 3 bottom of main body frame, by the zero point of Zero-point positioning system 8 and the corresponding position of assembly jig 5
Landing nipple cooperation realizes that assembly jig 5 and main body frame 3 link together；
3) flexible positioning component 4 is driven to form positioning door panels shape by external electric-control system；
4) gas source is opened, after stable gas pressure, vacuum absorption device completion is opened and vacuumizes, make flexible positioning component 4 and hatch door
Covering is combined together；
5) other components by hatch door in addition to covering carry out the assembly of hatch door in hatch door Skeleton assembly type frame 5.
Claims (10)
1. a kind of flexible frock for aircraft door assembly, it is characterised in that: by main body frame (3) and assembly jig (5) group
At；It is equipped with concave curvature on the surface of main body frame (3), several equally distributed flexible positioning groups are equipped on concave curvature
Part (4), the vacuum absorption device on flexible positioning component (4), and adsorb aircraft skin to be assembled；The bottom of assembly jig (5)
Equipped with mobile base (6), assembly jig (5) is equipped with curved-surface structure, and corresponding with the curvature of main body frame (3) concave curvature；?
The surface of main body frame (3) is equipped with several zero-point positioning devices (8), fixed equipped with zero point in the corresponding position of assembly jig (5)
Position connector, zero-point positioning connector and zero-point positioning device (8) cooperate.
2. the flexible frock for aircraft door assembly as described in claim 1, it is characterised in that: the flexible positioning group
Part (4) is sequentially connected and is formed by sucker group (46), cup holder (45), electric pushrod (44) and servo motor；Sucker group (46) and cup
Seat (45) is arranged outside the concave curvature of main body frame (3)；Connecting plate (41) are set in the front end of electric pushrod (44), connecting plate
(41) it is connect with main body frame (3) surface；Support (42) are set in the rear end of electric pushrod (44), support (42) and main body frame
(3) inner frame connects.
3. the flexible frock for aircraft door assembly as claimed in claim 2, it is characterised in that: the cup holder (45)
Main body is equipped with hemisphere face groove, and spherical groove bottom is equipped with magnet (452)；Sucker group (46) is by hemisphere (464) and sucker
(461) it forms, sucker (461) is located on hemisphere (464) end face, and hemisphere (464) is landed in half ball impression of cup holder (45)
In slot, and it is attracting with magnet (452).
4. the flexible frock for aircraft door assembly as described in claim 1, it is characterised in that: the assembly jig
(5) both ends are respectively equipped with shaft, are equipped with bearing block in mobile base (6) upper surface, and shaft and bearing block assemble, and shaft
One end is connect with operated motor (58).
5. the flexible frock for aircraft door assembly as described in claim 1, it is characterised in that: the assembly jig
(5) main body is frame (51), is respectively equipped with that blade assemblies (52), shaft assembly (53), side frame are fixed in promotion on frame (51)
Hyte part (54), hold down assembly (55) and covering examine component (56).
6. the flexible frock for aircraft door assembly as claimed in claim 5, it is characterised in that: on the frame (51)
It is symmetrical arranged two supporting plates (52), the length that each supporting plate (52) is welded on frame (51) by positioning angle section (521) respectively up and down
It spends on side；It is uniformly distributed three limit plates (522) vertically in positioning angle section (521), limit plate (522) surface limits hatch door bone
Frame；The middle part of a supporting plate (52), which is flexibly connected, wherein is promoted upper shaft assembly (53), and shaft assembly (53) is equipped with fixed in promotion
Position axis (534), locating shaft (534) position three through-holes of hatch door skeleton, guarantee its concentricity.
7. the flexible frock for aircraft door assembly as claimed in claim 5, it is characterised in that: on the frame (51)
Lower frame is respectively equipped with side frame positioning component (54), the structure of side frame positioning component (54) are as follows: the support connecting with frame (51)
(545) locating shaft (546) are set on, the end of locating shaft (546) is equipped with handle (541) and passes through support (545), support
(545) surface is equipped with cover board (543), and cover board (543), which is equipped with, compresses pin (544), compresses pin (544) and passes through cover board (543)
It is held out against with locating shaft (546).
8. the flexible frock for aircraft door assembly as claimed in claim 5, it is characterised in that: described holds down assembly
(55) be divided into several, and be uniformly arranged on the upper and lower side frame of frame (51), wherein hold down assembly (55) be T font structure,
It is equipped with hold-down bolt in fact, hold-down bolt is pressed on corresponding hatch door skeleton.
9. the flexible frock for aircraft door assembly as claimed in claim 5, it is characterised in that: the covering check groups
On the rectangular upper and lower side frame for being distributed in frame (51) of part (56).
10. the assembly technology that aircraft door is assembled using the flexible frock of aircraft door as described in claim 1 assembly,
Be characterized in that the following steps are included:
1) aircraft door covering is mounted in hatch door Skeleton assembly type frame (5)；
2) mobile base (6) of mobile main body frame (3) bottom, by the corresponding position of Zero-point positioning system (8) and assembly jig (5)
The zero-point positioning connector cooperation set, realizes that assembly jig (5) and main body frame (3) link together；
3) flexible positioning component (4) is driven to form positioning door panels shape by external electric-control system；
4) gas source is opened, after stable gas pressure, vacuum absorption device completion is opened and vacuumizes, make flexible positioning component (4) and cabin
Door covering is combined together；
5) other components by hatch door in addition to covering carry out the assembly of hatch door in hatch door Skeleton assembly type frame (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811533286.4A CN109664098A (en) | 2018-12-14 | 2018-12-14 | Flexible frock and its assembly technology for aircraft door assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811533286.4A CN109664098A (en) | 2018-12-14 | 2018-12-14 | Flexible frock and its assembly technology for aircraft door assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109664098A true CN109664098A (en) | 2019-04-23 |
Family
ID=66143877
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811533286.4A Pending CN109664098A (en) | 2018-12-14 | 2018-12-14 | Flexible frock and its assembly technology for aircraft door assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109664098A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110216235A (en) * | 2019-06-03 | 2019-09-10 | 西安飞机工业（集团）有限责任公司 | A kind of flexible fuselage wallboard assembly tooling and assembly method based on measured data |
| CN111731504A (en) * | 2020-06-12 | 2020-10-02 | 陕西飞机工业（集团）有限公司 | Positioning method of cockpit glass framework |
| CN112676880A (en) * | 2020-12-17 | 2021-04-20 | 中航沈飞民用飞机有限责任公司 | Integrated process equipment suitable for automatically drilling and riveting multiple cabin doors |
| CN112977676A (en) * | 2021-03-05 | 2021-06-18 | 奇瑞商用车（安徽）有限公司 | Aluminum side wall skin assembling device and assembling method |
| CN115070393A (en) * | 2022-07-04 | 2022-09-20 | 上海应用技术大学 | Automatic it prevents weighing down and falls set cabin device to change upset |
| CN115489611A (en) * | 2022-09-09 | 2022-12-20 | 中国第一汽车股份有限公司 | Method for bonding carbon fiber outer skin and aluminum alloy framework minibus body |
| CN115502747A (en) * | 2022-09-26 | 2022-12-23 | 沈阳飞机工业（集团）有限公司 | Positioning and pressing device for skin or wall plate forming assembly closed area |
| CN115958318A (en) * | 2023-01-20 | 2023-04-14 | 中航西安飞机工业集团股份有限公司 | Aircraft skin chemical milling machine tool fixing device |
| CN117444886A (en) * | 2023-12-21 | 2024-01-26 | 四川安德科技有限公司 | Aviation part assembly fixture |
| CN117602092A (en) * | 2024-01-23 | 2024-02-27 | 上海上飞飞机装备制造股份有限公司 | Method for assembling passenger-to-cargo main cargo compartment door, compartment door assembling tool and grouping process equipment |
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| CN102069457A (en) * | 2010-12-07 | 2011-05-25 | 成都飞机工业（集团）有限责任公司 | Self-centering positioning process equipment for fixing curved skin parts |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110216235B (en) * | 2019-06-03 | 2024-02-09 | 西安飞机工业（集团）有限责任公司 | Flexible fuselage wall plate assembly tool and assembly method based on measured data |
| CN110216235A (en) * | 2019-06-03 | 2019-09-10 | 西安飞机工业（集团）有限责任公司 | A kind of flexible fuselage wallboard assembly tooling and assembly method based on measured data |
| CN111731504A (en) * | 2020-06-12 | 2020-10-02 | 陕西飞机工业（集团）有限公司 | Positioning method of cockpit glass framework |
| CN112676880A (en) * | 2020-12-17 | 2021-04-20 | 中航沈飞民用飞机有限责任公司 | Integrated process equipment suitable for automatically drilling and riveting multiple cabin doors |
| CN112676880B (en) * | 2020-12-17 | 2021-12-03 | 中航沈飞民用飞机有限责任公司 | Integrated process equipment suitable for automatically drilling and riveting multiple cabin doors |
| CN112977676A (en) * | 2021-03-05 | 2021-06-18 | 奇瑞商用车（安徽）有限公司 | Aluminum side wall skin assembling device and assembling method |
| CN112977676B (en) * | 2021-03-05 | 2023-10-27 | 奇瑞商用车（安徽）有限公司 | Aluminum side wall skin assembling device and assembling method |
| CN115070393A (en) * | 2022-07-04 | 2022-09-20 | 上海应用技术大学 | Automatic it prevents weighing down and falls set cabin device to change upset |
| CN115489611A (en) * | 2022-09-09 | 2022-12-20 | 中国第一汽车股份有限公司 | Method for bonding carbon fiber outer skin and aluminum alloy framework minibus body |
| CN115502747A (en) * | 2022-09-26 | 2022-12-23 | 沈阳飞机工业（集团）有限公司 | Positioning and pressing device for skin or wall plate forming assembly closed area |
| CN115502747B (en) * | 2022-09-26 | 2024-03-08 | 沈阳飞机工业（集团）有限公司 | Positioning and compacting device for a skin or panel forming an assembly enclosure |
| CN115958318A (en) * | 2023-01-20 | 2023-04-14 | 中航西安飞机工业集团股份有限公司 | Aircraft skin chemical milling machine tool fixing device |
| CN117444886A (en) * | 2023-12-21 | 2024-01-26 | 四川安德科技有限公司 | Aviation part assembly fixture |
| CN117444886B (en) * | 2023-12-21 | 2024-03-19 | 四川安德科技有限公司 | Aviation part assembly fixture |
| CN117602092A (en) * | 2024-01-23 | 2024-02-27 | 上海上飞飞机装备制造股份有限公司 | Method for assembling passenger-to-cargo main cargo compartment door, compartment door assembling tool and grouping process equipment |
| CN117602092B (en) * | 2024-01-23 | 2024-04-12 | 上海上飞飞机装备制造股份有限公司 | Method for assembling passenger-to-cargo main cargo compartment door, compartment door assembling tool and grouping process equipment |
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