CN105690057A - Process joint for aircraft panel component assembly, and assembly method - Google Patents
Process joint for aircraft panel component assembly, and assembly method Download PDFInfo
- Publication number
- CN105690057A CN105690057A CN201610177399.XA CN201610177399A CN105690057A CN 105690057 A CN105690057 A CN 105690057A CN 201610177399 A CN201610177399 A CN 201610177399A CN 105690057 A CN105690057 A CN 105690057A
- Authority
- CN
- China
- Prior art keywords
- assembly
- process connection
- location
- aircraft
- target ship
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 54
- 230000002787 reinforcement Effects 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 210000000744 eyelid Anatomy 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
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
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
- F16B5/0004—Joining sheets, plates or panels in abutting relationship
-
- 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
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Automatic Assembly (AREA)
- Connection Of Plates (AREA)
Abstract
The invention belongs to the technical field of aircraft manufacturing, relates to assembly for aircraft body panel components, and specifically relates to a process joint for aircraft panel component assembly, and an assembly method. An aircraft body is generally formed by carrying out riveting assembly on a plurality of panel components, the aerodynamic shapes of modern aircrafts are mainly complex hyperboloids, and the shapes of surface covering parts, that is, skin panels, of the modern aircrafts, are also mostly hyperboloids, thus difficulty is brought to assembly location. The invention designs a process joint for aircraft panel component assembly, and an assembly method, for keeping accurate riveting assembly positions of the panel components and increasing the assembly efficiency. Assembly location among the panel components is carried out by virtue of the method, a digitized assembly method is realized, allowance reservation is not required for the panel components, and field manual repair is not needed any more; the assembled products are high in accuracy and accurate in position; and the production efficiency is also greatly improved.
Description
Technical field
The invention belongs to aircraft manufacturing technical field, for the assembling of airframe wallboard base part, be specifically related to process connection and the assembly method of a kind of aircraft target ship parts。
Background technology
Airframe is generally assembled by the riveted joint of multiple wall members, the hyperboloid that the aerodynamic configuration of present generation aircraft is mainly complicated, and the shape of its surface covering parts skinpiston is also hyperboloid mostly, and this brings difficulty to assembling location。Aircraft target ship parts reliably do not position in assembly tooling, just with the profile of eyelid covering, skeleton profile and locating clamp plate, and wall panel skin is also required to reserve surplus, operator adjusts eyelid covering position by rule of thumb, clamps by clamp, rubber rope and C type and is tightened by the frame beam framework of eyelid covering Yu fuselage, joins and get out rivet hole, plug spring catch, marking edge line by hand, it is determined that the eyelid covering surplus that excise, on-the-spot manual grinding falls surplus。The Product Assembly precision so assembled out is low, and position is inaccurate, can cause skin shape and frame configuration dislocation, add the form error of eyelid covering itself, cause rivet deformation big, and fuselage presentation quality is poor；And line error is big by hand, repeatable accuracy is low, and efficiency is low, and eyelid covering seam quality is poor；The on-the-spot manual grinding surplus of riveted joint, efficiency is low, of poor quality。
Summary of the invention
The technical problem to be solved is to make the riveted joint rigging position of wall member accurate, improving efficiency of assembling, devises a kind of process connection for the assembling of aircraft target ship parts and assembly method。
The process connection for the assembling of aircraft target ship parts of the present invention, this process connection is connected by connecting plate and location-plate are fixing, on described connecting plate, wherein there is the connecting hole can being connected with aircraft target ship, described location-plate has the hole, location can being connected with localizer, described process connection is positioned in aircraft target ship by adjusting localizer and connects。
Further, between described connecting plate and location-plate, also has reinforcement。
A kind of positioning assembly method of aircraft target ship parts, adopt above-mentioned process connection, first pass through localizer and 4 process connection are arranged on aircraft target ship parts allocation place really, punched on aircraft target ship parts by the connecting hole on described process connection connecting plate；Secondly the connecting plate of process connection is connected with aircraft target ship；By the hole, location of described process connection between last wallboard, mutually coordinated determine that relative position is attached。
The invention has the beneficial effects as follows: the assembling location utilizing the method to carry out between wall member and parts, the method achieving numeric terminal, wall member need not leave surplus, on-the-spot manual repairing need not be carried out again, the Product Precision assembled out is high, position is accurate, also substantially increases production efficiency。
Accompanying drawing explanation
Fig. 1 is wall member location riveted joint on assembling jig；
Fig. 2 is the connection diagram of process connection and localizer；
Fig. 3 is the structural representation of process connection；
Fig. 4 is the wall member with process connection；
Fig. 5 is wall member location riveted joint on general assembly gripper；
Fig. 6 is the detail view of Fig. 5。
1-process connection, 2-localizer, 3-connecting plate, 4-location-plate, 5-reinforcement, 6-connecting hole, 7-position hole
Detailed description of the invention
A kind of process connection for the assembling of aircraft target ship parts, by connecting plate 3 and the fixing connection of location-plate 4, on described connecting plate 3, wherein there is the connecting hole 6 can being connected with aircraft target ship, described location-plate 4 has the hole, location 7 can being connected with localizer 2, described process connection is positioned in aircraft target ship by adjusting localizer 2 and connects。Reinforcement 5 is also had between described connecting plate 3 and location-plate 4。
A kind of positioning assembly method of aircraft target ship parts, adopt above-mentioned process connection, first pass through localizer 2 and 4 process connection are arranged on aircraft target ship parts allocation place really, punched on aircraft target ship parts by the connecting hole on described process connection connecting plate 3；Secondly the connecting plate of process connection is connected with aircraft target ship；By the hole, location 7 of described process connection between last wallboard, mutually coordinated determine that relative position is attached。
With rivet location hole in process connection, the size in rivet location hole takes from wall member drawing, utilize the rivet location hole in process connection to drill the rivet hole of wall member, undercarriage after wall member riveted joint, process connection is pulled down from assembling jig, by rivet hole, process connection is connected on wall member with bolt。So each wall member is with process connection, process connection has again mutually coordinated hole, location, when carrying out wall member with parts assembling, design technology terminal position in wall member general assembly gripper, positioning each wall member with technique terminal position, the riveted joint completing wall member and parts is assembled。
Claims (3)
1. the process connection for the assembling of aircraft target ship parts, it is characterized in that: this process connection is connected by connecting plate (3) and location-plate (4) are fixing, on described connecting plate (3), wherein there is the connecting hole (6) can being connected with aircraft target ship, described location-plate (4) has the hole, location (7) can being connected with localizer (2), described process connection is positioned in aircraft target ship by adjusting localizer (2) and connects。
2. process connection according to claim 1, it is characterised in that: between described connecting plate (3) and location-plate (4), also have reinforcement (5)。
3. the positioning assembly method of aircraft target ship parts, adopt the process connection described in claim 1-2, it is characterized in that: first pass through localizer (2) and 4 process connection are arranged on aircraft target ship parts allocation place really, punched on aircraft target ship parts by the connecting hole on described process connection connecting plate (3)；Secondly the connecting plate of process connection is connected with aircraft target ship；By the hole, location (7) of described process connection between last wallboard, mutually coordinated determine that relative position is attached。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610177399.XA CN105690057A (en) | 2016-03-25 | 2016-03-25 | Process joint for aircraft panel component assembly, and assembly method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610177399.XA CN105690057A (en) | 2016-03-25 | 2016-03-25 | Process joint for aircraft panel component assembly, and assembly method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105690057A true CN105690057A (en) | 2016-06-22 |
Family
ID=56231562
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610177399.XA Pending CN105690057A (en) | 2016-03-25 | 2016-03-25 | Process joint for aircraft panel component assembly, and assembly method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105690057A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106271498A (en) * | 2016-08-24 | 2017-01-04 | 北京星航机电装备有限公司 | A kind of method installing metal rack in Composite Cabin body |
| CN107020597A (en) * | 2017-04-21 | 2017-08-08 | 陕西飞机工业（集团）有限公司 | A kind of process assembled for aircraft big opening |
| CN110239736A (en) * | 2019-05-17 | 2019-09-17 | 陕西飞机工业（集团）有限公司 | One kind changes the outfit tooling and costume changing method |
| CN110712032A (en) * | 2018-07-12 | 2020-01-21 | 波音公司 | Wing panel assembly system and method |
| CN110842845A (en) * | 2019-12-11 | 2020-02-28 | 江苏新扬新材料股份有限公司 | Large-curvature composite material cone structural member assembling tool and assembling process thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200975383Y (en) * | 2006-07-03 | 2007-11-14 | 陈健 | Connection element |
| US20120321378A1 (en) * | 2011-06-14 | 2012-12-20 | Whalen Furniture Manufacturing, Inc. | Corner joint system for furniture panels |
| CN203067438U (en) * | 2012-11-22 | 2013-07-17 | 深圳市易尚展示股份有限公司 | Connecting device |
| CN103405076A (en) * | 2013-08-08 | 2013-11-27 | 杭州高脚马科技有限公司 | Spliced and assembled display body |
| CN105035354A (en) * | 2015-08-04 | 2015-11-11 | 航天材料及工艺研究所 | Composite material skin net edge coordination tools and assembling method for skins |
-
2016
- 2016-03-25 CN CN201610177399.XA patent/CN105690057A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200975383Y (en) * | 2006-07-03 | 2007-11-14 | 陈健 | Connection element |
| US20120321378A1 (en) * | 2011-06-14 | 2012-12-20 | Whalen Furniture Manufacturing, Inc. | Corner joint system for furniture panels |
| CN203067438U (en) * | 2012-11-22 | 2013-07-17 | 深圳市易尚展示股份有限公司 | Connecting device |
| CN103405076A (en) * | 2013-08-08 | 2013-11-27 | 杭州高脚马科技有限公司 | Spliced and assembled display body |
| CN105035354A (en) * | 2015-08-04 | 2015-11-11 | 航天材料及工艺研究所 | Composite material skin net edge coordination tools and assembling method for skins |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106271498A (en) * | 2016-08-24 | 2017-01-04 | 北京星航机电装备有限公司 | A kind of method installing metal rack in Composite Cabin body |
| CN106271498B (en) * | 2016-08-24 | 2018-08-17 | 北京星航机电装备有限公司 | A method of metallic support is installed in Composite Cabin body |
| CN107020597A (en) * | 2017-04-21 | 2017-08-08 | 陕西飞机工业（集团）有限公司 | A kind of process assembled for aircraft big opening |
| CN110712032A (en) * | 2018-07-12 | 2020-01-21 | 波音公司 | Wing panel assembly system and method |
| CN110712032B (en) * | 2018-07-12 | 2022-10-18 | 波音公司 | Wing panel assembly system and method |
| CN110239736A (en) * | 2019-05-17 | 2019-09-17 | 陕西飞机工业（集团）有限公司 | One kind changes the outfit tooling and costume changing method |
| CN110842845A (en) * | 2019-12-11 | 2020-02-28 | 江苏新扬新材料股份有限公司 | Large-curvature composite material cone structural member assembling tool and assembling process thereof |
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| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
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| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160622 |