CN111731505B - Method for assembling common frame edge of airplane - Google Patents
Method for assembling common frame edge of airplane Download PDFInfo
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- CN111731505B CN111731505B CN202010535718.6A CN202010535718A CN111731505B CN 111731505 B CN111731505 B CN 111731505B CN 202010535718 A CN202010535718 A CN 202010535718A CN 111731505 B CN111731505 B CN 111731505B
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- clamping plate
- shear
- rim
- frame
- auxiliary clamping
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- 238000000034 method Methods 0.000 title claims abstract description 28
- 238000005553 drilling Methods 0.000 claims abstract description 11
- 230000006835 compression Effects 0.000 claims abstract description 4
- 238000007906 compression Methods 0.000 claims abstract description 4
- 238000010008 shearing Methods 0.000 claims description 9
- 238000009434 installation Methods 0.000 claims description 5
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 230000007547 defect Effects 0.000 abstract 1
- 238000003825 pressing Methods 0.000 description 5
- 239000002184 metal Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 1
- 210000001503 joint Anatomy 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
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
Abstract
The invention belongs to the field of aviation manufacturing, and discloses an aircraft ordinary rim assembly method, wherein when a wallboard is preassembled into a frame, an inner clamping plate is arranged on the inner side of the frame; a detachable auxiliary clamping plate is arranged on the inner clamping plate, and the molded surface of the auxiliary clamping plate is matched with the theoretical molded surface of the shear plate; when the shear sheet is positioned, the shear sheet is tightly attached to the auxiliary clamping plate, and then the compression piece is used for compressing the shear sheet; the method comprises the steps of connecting a shear sheet with a skin through a connecting hole, removing an auxiliary clamping plate, and riveting the shear sheet and the skin; positioning the rim according to a rim positioner on the inner clamping plate; and drilling fastener holes for connecting the shear sheets with the frame edge, and riveting the shear sheets with the frame edge and the stringers. The positioning accuracy of the shear sheet is greatly improved after the auxiliary clamping plate is adopted to position the shear sheet, and the defect that the frame assembly accuracy caused by a common frame traditional assembly process method is influenced by part manufacturing errors and human factors of operators is overcome.
Description
Technical Field
The invention belongs to the technical field of aviation assembly, relates to an assembly method of a rim, and in particular relates to an assembly method of an ordinary rim of an airplane.
Background
In civil aircraft development, users have placed more stringent demands on aircraft appearance and manufacturing quality, requiring components to be assembled accurately and stress-free. The common frame edge of the wallboard is generally formed by riveting a Z-shaped frame edge and a shear sheet, the common frame edge of the wallboard of the fuselage is assembled by adopting a traditional process flow and a positioning method, and the common frame edge shear sheet is influenced by the manufacturing precision of sheet metal parts, the artificial factors of operators and the like, so that the common frame edge shear sheet is no longer in the same plane along the circumferential direction of the fuselage after being installed, and rivets on the outer surface of the fuselage are no longer arranged in the same plane in appearance; meanwhile, the deviation between the positioning of the shear sheet and the setting of the counting die is large, so that the stress condition of a common frame mechanism is changed, and the assembly quality of the aircraft is influenced.
Disclosure of Invention
In order to solve the problems, the invention provides an assembly method of an ordinary rim of an airplane, and the positioning accuracy of a shear sheet is improved by improving the assembly process and tooling, so that the assembly accuracy of the ordinary rim is greatly improved.
The technical scheme of the invention is as follows: an aircraft ordinary rim assembly method comprises the following steps:
step one, arranging an inner clamping plate on the inner side of a wall plate preassembling frame;
Step two, a detachable auxiliary clamping plate is arranged on the inner clamping plate, and the molded surface of the auxiliary clamping plate is matched with the theoretical molded surface of the shear plate;
step three, when the shear force piece is positioned, the shear force piece is tightly attached to the auxiliary clamping plate, and then the compression piece is used for compressing the shear force piece;
fourthly, connecting the shear force sheet with the skin through a connecting hole, removing the auxiliary clamping plate, and riveting the shear force sheet and the skin;
fifthly, positioning the rim according to a rim positioner on the inner clamping plate;
and step six, drilling fastener holes for connecting the shear sheets with the frame edge, and riveting the shear sheets with the frame edge and the stringers.
Further, the accuracy of the clamping plate surface of the inner clamping plate is 0-0.5 mm.
Further, the accuracy of the clamping plate profile of the inner clamping plate is 0.2mm.
Further, the inner type clamping plate is arranged at a position 50mm away from the axis of the product frame. The riveting passage of the shear blade and the frame edge can be ensured.
Further, the molded surface of the auxiliary clamping plate is 1-8 mm lower than the theoretical molded surface, and the installation accuracy of the auxiliary clamping plate is 0-0.5 mm.
Further, the molded surface of the auxiliary clamping plate is 3-5 mm lower than the theoretical molded surface, and the installation accuracy of the auxiliary clamping plate is 0.2mm. The profile of the auxiliary clamping plate is slightly lower than the theoretical profile, and a reasonable installation gap is reserved.
Furthermore, the positioning precision of the frame edge is 0-0.5 mm.
Further, the positioning precision of the frame edge is 0.2mm, the course direction freedom degree of the frame edge positioning is released, and the frame edge is attached to the shear sheet.
The invention has the advantages that:
1. Improving the appearance quality of the wallboard
After the shear sheet is positioned according to the tooling positioner, the manufacturing error of the frame edge and the positioning error of the shear sheet are eliminated, and the circumferential deviation of the shear sheet and the outer skin connecting rivet on the machine body is not more than 0.5mm.
2. Reducing the positioning deviation of the common frame edge
In the development of the aircraft, a common frame adopts a traditional positioning method, and the positioning deviation of the frame edge is larger. When the assembly wallboard assembly of the component is assembled, the deviation of part of the frame edge reaches 2-3 mm, and in order to reduce the assembly stress, the butt joint end of the frame edge is often required to be subjected to riveting. After the frame edge assembly method is improved, the frame edge positioning deviation is greatly reduced, the assembly stress is eliminated, and the product assembly quality is improved.
3. Automatic drilling and riveting rate of wallboard
Currently, the automatic drilling and riveting application of fuselage wall panels is gradually promoted in the domestic aviation industry, and automatic drilling and riveting of the connection of stringers and skins is primarily realized. The wallboard is preassembled according to the assembly sequence after the common rim is adjusted, so that the interference of the Z-shaped flange of the rim on the lower riveting die of the automatic drilling and riveting machine is avoided, the automatic drilling and riveting of the shear sheet and the skin connection can be realized gradually, and the automatic drilling and riveting rate of the wallboard is improved.
Drawings
FIG. 1 is a schematic view of a conventional rim structure;
FIG. 2 is a schematic view of an inner card and an auxiliary card;
FIG. 3 is a schematic view of an auxiliary cardboard positioning shear blade;
FIG. 4 is a schematic view of rim positioning;
FIG. 5 is a block diagram of a rear wall panel of a shear blade;
FIG. 6 is a flow chart of the assembly of a conventional frame to a wall panel;
Fig. 7 is an assembly flow chart after the assembly sequence of the common frame is adjusted.
Detailed Description
This section is an embodiment of the present invention for explaining and explaining the technical solution of the present invention.
An aircraft ordinary rim assembly method comprises the following steps:
step one, arranging an inner clamping plate on the inner side of a wall plate preassembling frame;
Step two, a detachable auxiliary clamping plate is arranged on the inner clamping plate, and the molded surface of the auxiliary clamping plate is matched with the theoretical molded surface of the shear plate;
step three, when the shear force piece is positioned, the shear force piece is tightly attached to the auxiliary clamping plate, and then the compression piece is used for compressing the shear force piece;
fourthly, connecting the shear force sheet with the skin through a connecting hole, removing the auxiliary clamping plate, and riveting the shear force sheet and the skin;
fifthly, positioning the rim according to a rim positioner on the inner clamping plate;
and step six, drilling fastener holes for connecting the shear sheets with the frame edge, and riveting the shear sheets with the frame edge and the stringers.
Wherein, cardboard profile precision of interior cardboard is 0.2mm, and interior cardboard sets up on 50 mm's the position apart from the product frame axis. The riveting passage of the shear blade and the frame edge can be ensured.
The molded surface of the auxiliary clamping plate is 3-5 mm lower than the theoretical molded surface, and the installation accuracy of the auxiliary clamping plate is 0.2mm.
The positioning precision of the frame edge is 0.2mm, the course direction freedom degree of the frame edge positioning is released, and the frame edge is attached to the shear sheet.
Another embodiment of the present invention will be described below with reference to the accompanying drawings.
Analysis is selected from the assembly sequence of the common rim on the wallboard and the part positioning method, and the dominant factors of the common rim which are not in the same plane any more in the circumferential direction are as follows:
1. The shear force sheet positioning method has low precision
The shear sheet positioning adopts a reference piece positioning method, and the reference pieces are a frame edge, a stringer and a skin. The positioning accuracy of the reference piece positioning method depends on the rigidity and the position accuracy of the reference piece, and the frame edge belongs to a weak-rigidity sheet metal part and has great influence on the positioning of the shear piece.
2. Manufacturing precision of frame edge part
The flatness tolerance of the sheet metal rim manufactured according to the general technical requirement of sheet metal parts is 1.5mm, and the positioning deviation of the shear sheet can reach 1.5mm at maximum after the shear sheet is attached to the rim.
3. Excessive pressing force causes deformation of the rim
At present, the common frame edge is positioned by adopting a positioning hole system when being assembled, the frame edge positioner is arranged on the assembly tool, and the positioning is performed by utilizing a positioning hole with the diameter of 5.2mm on the frame edge. 2-3 positioning holes are generally formed in the frame edge, the hole distance is about 500-600 mm, when the shear force sheet is positioned, an operator manually attaches the shear force sheet to the frame edge, the stringers and the outer skin, when the pressing force P (see figure 1) is too large, the frame edge deforms, the positioning deviation of the shear force sheet is caused, and the deviation is related to the value P.
4. The shearing force sheet and the frame edge are not completely attached
When the position of the pressing force P is unreasonable (see FIG. 1), the shearing force P cannot be completely attached to the frame, the positioning deviation of the shearing force P occurs, and the local gap between the shearing force P and the frame is the positioning deviation of the shearing force P.
Therefore, in order to solve the problems existing in the assembly of the original common frame of a certain machine, the original process method is improved:
1. adopt frock locator to guarantee shear force piece assembly
The external shape of the wallboard is controlled by adopting an internal clamping plate when the wallboard is assembled and erected, and the internal clamping plate is arranged at a distance of more than 50mm from the axis of the frame in order to ensure the riveting passage of the shear sheet and the frame edge. The detachable auxiliary clamping plate is added on the inner clamping plate to control the positioning flatness of the shear plates (see figure 2), and the shear plates are pressed by the pressing piece after being positioned to the correct positions, so that the assembly errors caused by human factors in the assembly process are solved.
2. Adjusting the assembly sequence to solve the problem of flatness of the frame edge
After the shear sheet is positioned to the correct position, the frame edge is positioned according to the frame edge positioner on the tool, the course degree of freedom is released, and the attachment with the shear sheet is ensured. After the assembly sequence of the common frames is adjusted, common frame assembly errors caused by flatness deviation of the frame edges are avoided.
The invention relates to a process method for assembling a common frame edge, which is described in detail by referring to the accompanying drawings:
1. When the wallboard is preassembled, an inner clamping plate is generally arranged on the inner molded surface, and the inner clamping plate is arranged at a distance of more than 50mm from the axis of the frame in order to ensure the riveting passage of the shear sheet and the frame edge. The detachable auxiliary clamping plate is added on the inner clamping plate, the shear plates are tightly attached to the auxiliary clamping plate when positioned, the auxiliary clamping plate is used for positioning the shear plates, the flatness of the shear plates on the same frame edge is controlled (see fig. 2 and 3), and the shear plates are pressed by the pressing piece after being positioned to the correct positions. And after the shearing force piece and the skin are connected, the auxiliary clamping plate is dismantled for riveting after the fastening piece connected with the skin is perforated.
Note that: the auxiliary clamping plate must be removed when the shear plates are riveted, otherwise, the impact force of the rivet gun can damage the skin.
2. The assembly sequence of the common frame edge is adjusted (the assembly sequence before and after adjustment is shown in fig. 6 and 7). After the shear sheets are positioned and riveted, the frame edge is positioned according to a frame edge positioner on the tool, the course degree of freedom is released, and the joint with the shear sheets is ensured. And drilling fastener holes for connecting the shearing force sheets and the frame rims, and riveting. After the assembly sequence of the common frames is adjusted, common frame assembly errors caused by flatness deviation of the frame edges are avoided.
Claims (3)
1. The method for assembling the common rim of the aircraft is characterized by comprising the following steps of:
step one, arranging an inner clamping plate on the inner side of a wall plate preassembling frame;
Installing a detachable auxiliary clamping plate on the inner clamping plate, wherein the profile of the auxiliary clamping plate is matched with the theoretical profile of the shear plate, and the profile of the auxiliary clamping plate is slightly lower than the theoretical profile of the shear plate;
step three, when the shear force piece is positioned, the shear force piece is tightly attached to the auxiliary clamping plate, and then the compression piece is used for compressing the shear force piece;
Fourthly, connecting the shearing force piece with the skin, making holes, removing the auxiliary clamping plate, and riveting the shearing force piece and the skin;
fifthly, positioning the rim according to a rim positioner on the inner clamping plate;
step six, drilling fastener holes for connecting the shear sheets with the frame edge, and riveting the shear sheets with the frame edge and the stringers;
The accuracy of the clamping plate profile of the inner clamping plate is 0.2mm;
The inner clamping plate is arranged at a position 50mm away from the axis of the product frame;
the molded surface of the auxiliary clamping plate is 3-5 mm lower than the theoretical molded surface, and the installation accuracy of the auxiliary clamping plate is 0.2mm.
2. The method for assembling the ordinary rim of the aircraft according to claim 1, wherein the positioning accuracy of the rim is 0-0.5 mm.
3. The method for assembling the ordinary rim of the airplane according to claim 2, wherein the positioning precision of the rim is 0.2mm, the freedom degree of the heading direction of the positioning of the rim is released, and the rim is attached to the shear sheet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010535718.6A CN111731505B (en) | 2020-06-12 | 2020-06-12 | Method for assembling common frame edge of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010535718.6A CN111731505B (en) | 2020-06-12 | 2020-06-12 | Method for assembling common frame edge of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111731505A CN111731505A (en) | 2020-10-02 |
| CN111731505B true CN111731505B (en) | 2024-09-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010535718.6A Active CN111731505B (en) | 2020-06-12 | 2020-06-12 | Method for assembling common frame edge of airplane |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113059372A (en) * | 2021-03-26 | 2021-07-02 | 陕西飞机工业有限责任公司 | Flexible drilling and riveting bracket |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5560102A (en) * | 1992-10-13 | 1996-10-01 | The Boeing Company | Panel and fuselage assembly |
| CN201597759U (en) * | 2009-11-23 | 2010-10-06 | 西安飞机工业（集团）有限责任公司 | Airplane flange locator |
| CN202481303U (en) * | 2012-02-06 | 2012-10-10 | 哈尔滨飞机工业集团有限责任公司 | Connecting structure of aircraft panel and frame |
| CN103447792B (en) * | 2013-08-08 | 2016-02-10 | 上海飞机制造有限公司 | Large complicated shape is faced the wall and meditated plate Flexible Measurement & Control fixture system and investigating method |
| CN203611175U (en) * | 2013-12-09 | 2014-05-28 | 陕西飞机工业（集团）有限公司 | Locating and compressing device for mounting rotatable airframe component |
| CN103921116B (en) * | 2014-04-24 | 2016-05-11 | 浙江大学 | A kind of aircraft target ship flexible assembly system |
| JP6580495B2 (en) * | 2016-02-02 | 2019-09-25 | 三菱重工業株式会社 | Holding jig |
| CN108557111B (en) * | 2018-04-28 | 2020-07-28 | 成都致冠科技有限公司 | Coordination assembly method for unmanned fixed-wing aircraft body |
-
2020
- 2020-06-12 CN CN202010535718.6A patent/CN111731505B/en active Active
Non-Patent Citations (1)
| Title |
|---|
| 基于双机器人协同的自动钻铆终端器及其自动供钉装置的设计与研究;李菡;《优秀硕士论文全文数据库信息科技》;20100716;第9-16页 * |
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