CN111702200A - Processing method of skin mold assembly positioning hole - Google Patents
Processing method of skin mold assembly positioning hole Download PDFInfo
- Publication number
- CN111702200A CN111702200A CN202010535716.7A CN202010535716A CN111702200A CN 111702200 A CN111702200 A CN 111702200A CN 202010535716 A CN202010535716 A CN 202010535716A CN 111702200 A CN111702200 A CN 111702200A
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- China
- Prior art keywords
- skin
- hole
- positioning hole
- assembly positioning
- processing
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- 238000003672 processing method Methods 0.000 title claims description 7
- 238000000034 method Methods 0.000 claims abstract description 24
- 238000005553 drilling Methods 0.000 claims abstract description 15
- 238000003754 machining Methods 0.000 claims abstract description 11
- 238000000465 moulding Methods 0.000 claims abstract description 9
- 238000009434 installation Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 5
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 3
- 238000010791 quenching Methods 0.000 claims description 3
- 230000000171 quenching effect Effects 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 239000003822 epoxy resin Substances 0.000 claims description 2
- 229920000647 polyepoxide Polymers 0.000 claims description 2
- 230000009466 transformation Effects 0.000 claims 1
- 238000006243 chemical reaction Methods 0.000 abstract description 6
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 229920005989 resin Polymers 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000011265 semifinished product Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B35/00—Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machines; Use of auxiliary equipment in connection with such methods
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B41/00—Boring or drilling machines or devices specially adapted for particular work; Accessories specially adapted therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B47/00—Constructional features of components specially designed for boring or drilling machines; Accessories therefor
- B23B47/28—Drill jigs for workpieces
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
Abstract
The invention belongs to the field of manufacturing of skin mould tires and discloses a method for quickly and accurately machining assembling positioning holes of skin mould tires. The method carries out numerical control processing on the skin mould, and then carries out reference conversion on the skin assembly positioning hole through the drilling template, so that the assembly positioning hole with the bush is accurately manufactured on the skin mould for skin part molding positioning and subsequent assembly.
Description
Technical Field
The invention belongs to the field of manufacturing of skin mould tires, and provides a method for accurately manufacturing assembly positioning holes on a skin mould tire by performing secondary conversion on a reference through a drill plate. In particular to a method for processing a skin mould assembling positioning hole.
Background
In order to improve the assembly efficiency of the aircraft skin, certain interchangeability and consistency of skin parts need to exist, namely the overall dimension and the heat meter state of the parts, namely the parts with the same figure number can be directly used by taking one part at will, and the parts do not need to be arranged in an assembly jig through sample placement and distribution allowance. The skin mould is provided with the assembling positioning holes which are consistent with the hole positions on the assembling jig, so that the skin is placed in the jig for assembling in a fast and correct posture. Therefore, when the skin mould is designed and manufactured, assembling positioning holes corresponding to the airplane space need to be manufactured. The assembly positioning hole is consistent with the assembly fixture (or the space attitude of the airplane). And are normal holes corresponding to the curved surface of the corresponding position of the skin.
Disclosure of Invention
In order to solve the problems, the invention provides a simple, quick and accurate processing method of the skin mould assembly positioning hole.
The method aims to correctly reflect the assembly positioning holes on the aircraft skin to the skin mould of the forming tool of the aircraft skin. Firstly, carrying out numerical control machining on the skin mould, wherein the skin mould comprises normal holes of a molded surface and assembling positioning holes. And secondly, assembling the positioning holes according to the normal direction, inserting positioning pins to accurately position the drill plate, molding the drill plate (the resin curing period is 24H), and configuring the positioning pins of the drill plate. And finally, after the drilling template is molded (in a resin curing period of 24H), removing the drilling template, reaming the assembly positioning hole on the molded surface of the mold core, reinstalling the drilling template, and then reinstalling the assembly positioning hole with the bush on the skin mold core according to the installed drilling template, thereby completing the manufacture of the assembly positioning hole.
Technical scheme
And carrying out numerical control machining on the skin mould, and carrying out reference conversion on the skin assembly positioning hole through the drilling template, so that the assembly positioning hole is accurately manufactured for skin part molding positioning and subsequent assembly.
A processing method of skin mould tire assembling positioning holes comprises the following steps:
1, machining a molded surface and a mounting hole of a skin mold 4 and an assembly positioning hole 2 normal to the molded surface by adopting five-axis numerical control.
2, inserting a positioning pin A5 according to the finished assembly positioning hole 2 on the skin mould tire 4 as a reference, accurately positioning, and molding two positioning pins B6 on the drill plate 3, thereby finishing the installation work of the drill plate 3.
And 3, removing the drilling template 3, and reaming the assembling positioning hole 2 on the skin mould 4, wherein the hole with the diameter is used for ensuring the normal installation of the bushing.
4, inserting a positioning pin B6 on the skin mould tire 4 to remount the drill plate 3, inserting a positioning pin A5 on the drill plate 3 at the same time, carrying out a bush molding process on the assembly positioning hole 2 of the skin mould tire 4, and ensuring that the topmost end face of the bush is lower than the molded surface of the skin mould tire 4.
In said steps 1-4:
1) the assembly positioning holes 2 on the skin mould tire 4 correspond to the assembly positioning holes on the aircraft skin 1, and the hole diameter and the hole position are consistent.
2) In all hole sites on the skin mould tire 4, the precision requirement of the assembly positioning holes 2 is far higher than that of the rest hole sites.
3) The depth of all holes in the skin mould 4 must be greater than the height of the embedded bushing.
4) The machining equipment adopted in the method is limited to five-axis numerical control equipment, and normal hole machining must be completed.
5) In the method, the material of the drill plate 3 is 45# steel, and the hardness and the wear resistance are ensured by quenching heat treatment.
6) In the method, the standard conversion is ensured and realized through the aperture and the hole position on the drill plate 3.
7) In this method the drilling template 3 is a detachable part.
According to the invention, the secondary processing of the assembly positioning hole is carried out by means of the drill jig plate, so that the processing precision of the drill jig plate can directly influence the precision of the assembly positioning hole of the skin mould.
Technical effects
Compared with the conventional operation method, the invention has the beneficial effects that:
1. and the skin with the assembling positioning holes is adopted, so that the assembling efficiency of the aircraft skin is improved.
2. The aircraft skin is assembled through the assembling positioning holes, zero allowance assembly is achieved, and the assembling period and cost of the aircraft skin are saved.
3. The assembly positioning hole of the skin mould is processed by numerical control, and secondary positioning is carried out on the skin mould to mould a lining for the assembly positioning hole by a drill plate; not only the aperture precision is ensured, but also the durability of the assembly positioning hole is ensured.
Drawings
FIG. 1 is a schematic view of a part processing structure;
FIG. 2 is a cross-sectional view of a part being machined;
wherein: 1-2-assembly positioning holes of an aircraft skin, 3-a drilling template 4-a skin mould tire 5-positioning pins A6-positioning pins B.
Detailed Description
The present invention is described in further detail below.
The specific manufacturing process of the invention is as follows:
1. the molded surface, the mounting holes and the assembly positioning holes 2 normal to the molded surface of the skin mold 4 are machined through five-axis numerical control (all the holes on the skin mold 4 are in a semi-finished product state and are only used for positioning and mounting a drill plate 3, and after the bushings are accurately mounted on all the hole positions, the hole can be in a formal state and is consistent with the assembly hole of the aircraft skin 1).
2, inserting a positioning pin A5 according to the finished assembly positioning hole 2 on the skin mould tire 4 as a reference, accurately positioning, and molding two positioning pins B6 on the drill plate 3, thereby finishing the installation work of the drill plate 3.
And 3, removing the drilling template 3, and reaming the assembling positioning hole 2 on the skin mould 4, wherein the hole with the diameter is used for ensuring the normal installation of the bushing.
4 on the premise of ensuring the aperture size, the hole site size relation and the tolerance requirement on the drill plate 3, inserting a positioning pin B6 on the skin mould blank 4 to remount the drill plate 3, simultaneously inserting a positioning pin A5 on the drill plate 3, carrying out a bush molding process on the assembling positioning hole 2 of the skin mould blank 4, and ensuring that the topmost end surface of the bush is lower than the molded surface of the skin mould blank 4 by 1 mm. Thereby completing the processing method of the invention about the skin mold assembly positioning hole 2.
The assembly positioning holes 2 on the skin mould tire 4 correspond to the assembly positioning holes on the aircraft skin 1, and the hole diameter and the hole position are consistent.
In all hole sites on the skin mould tire 4, the precision requirement of the assembly positioning holes 2 is far higher than that of the rest hole sites.
The depth of all holes on the skin mould tire 4 must be larger than the height of the embedded bushings, so that the bushings installed at all hole positions are ensured to be 1mm lower than the molded surface of the skin mould tire 4, and the normal use of the skin mould tire 4 is prevented from being influenced.
The machining equipment adopted in the method is limited to five-axis numerical control equipment, and normal hole machining must be completed.
In the method, the material of the drill plate 3 is 45# steel, and the hardness and the wear resistance are ensured by quenching heat treatment. The covering mould 4 is made of epoxy resin material and has a wooden frame structure.
In the method, the standard conversion is ensured and realized through the aperture and the hole position on the drill plate 3.
In the method, a drilling template 3 is a detachable part and is a part of a skin mould 4 tool.
The drill plate 3 is provided with three holes, wherein the assembly positioning hole 2 is 5.2mm phi, and the positioning pin A5 matched with the assembly positioning hole is 5.2mm phi; the aperture of the two remaining holes is phi 8mm, and the positioning pin B6 matched with the holes is phi 8 mm; the tolerance of the fit of all the positioning pins and the holes on the drilling template 3 is H7/H6. The position tolerance between each hole position on the drilling template 3 is less than 0.05 mm.
The positioning pin A5 is used for assembling the positioning hole 2, and the aperture is phi 5.2 mm. The positioning pin B6 is used for installing and fixing the drill plate 3, and the aperture is phi 8 mm.
1) The invention mainly realizes the processing of the assembly positioning hole through the reference conversion, thereby generating deviation certainly; but the deviation can not affect the skin assembly as long as the deviation is properly controlled.
2) The secondary processing of the assembly positioning hole needs to be carried out by the aid of the drill jig plate, so that the processing precision of the drill jig plate can directly influence the precision of the skin mould assembly positioning hole.
3) The processing equipment adopted by the invention is limited to five-axis numerical control processing.
Claims (8)
1. A processing method for skin mould assembling positioning holes is characterized by comprising the following steps:
1) machining a molded surface and a mounting hole of the skin mold (4) and an assembling positioning hole (2) normal to the molded surface by adopting five-axis numerical control;
2) according to the machined assembly positioning hole (2) on the skin mold (4) as a reference, inserting a positioning pin A (5), accurately positioning, and molding two positioning pins B (6) on the drill plate (3), thereby completing the installation work of the drill plate (3);
3) removing the drill plate (3), and reaming the assembling positioning hole (2) on the skin mould (4), wherein the hole with the diameter is ensured to be normally installed;
4) and inserting a positioning pin B (6) into the skin mold tyre (4) to remount the drill plate (3), inserting a positioning pin A (5) into the drill plate (3), performing a bush molding process on the assembling positioning hole (2) of the skin mold tyre (4), and ensuring that the end surface of the topmost end of the bush is lower than the molded surface of the skin mold tyre (4).
2. The method for processing the skin mould tire assembly positioning hole as claimed in claim 1, wherein the assembly positioning hole (2) on the skin mould tire (4) corresponds to the assembly positioning hole on the aircraft skin (1), and the hole diameter and the hole position are consistent with each other.
3. The method for processing the skin mould tire assembly positioning hole as claimed in claim 1, wherein the assembly positioning hole (2) has higher precision requirement than the rest of the hole positions in all the hole positions on the skin mould tire (4).
4. The method for processing the skin mould tire assembly positioning hole as claimed in claim 1, wherein the depth of all holes on the skin mould tire (4) is greater than the height of the embedded bushing.
5. The method for machining the skin mold tire assembly positioning hole as claimed in claim 1, wherein the machining equipment adopted in the method is limited to five-axis numerical control equipment.
6. The processing method for the skin mould tire assembly positioning hole is characterized in that 45# steel is adopted as a drilling template (3) material, and quenching heat treatment is performed to ensure hardness and wear resistance; the covering mould (4) is made of epoxy resin material and has a wooden frame structure.
7. The method for processing the skin mould tire assembly positioning hole as claimed in claim 1, wherein the datum transformation is ensured and realized through the hole diameter and the hole position on the drilling template (3).
8. The method for processing the skin mould tire assembly positioning hole as claimed in claim 1, wherein the drill plate (3) is a detachable part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010535716.7A CN111702200B (en) | 2020-06-12 | 2020-06-12 | Processing method of skin mold assembly positioning hole |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010535716.7A CN111702200B (en) | 2020-06-12 | 2020-06-12 | Processing method of skin mold assembly positioning hole |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111702200A true CN111702200A (en) | 2020-09-25 |
| CN111702200B CN111702200B (en) | 2024-04-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010535716.7A Active CN111702200B (en) | 2020-06-12 | 2020-06-12 | Processing method of skin mold assembly positioning hole |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112496681A (en) * | 2020-11-19 | 2021-03-16 | 中国航发沈阳黎明航空发动机有限责任公司 | Semi-ring matching part combination machining method |
| CN113618101A (en) * | 2021-08-18 | 2021-11-09 | 成都飞机工业（集团）有限责任公司 | Drilling device and drilling method for upper skin of closed box structure on wing |
| CN115502663A (en) * | 2022-09-26 | 2022-12-23 | 沈阳飞机工业（集团）有限公司 | Preparation method of large-scale fork-shaped skin contour |
| CN116852047A (en) * | 2023-07-28 | 2023-10-10 | 沈阳飞机工业（集团）有限公司 | Manufacturing method of double-sided sinking skin part |
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| CN110567374A (en) * | 2019-10-08 | 2019-12-13 | 江西洪都航空工业集团有限责任公司 | skin part assembly positioning hole position detection method |
| EP3587242A1 (en) * | 2018-06-28 | 2020-01-01 | BAE SYSTEMS plc | Method and apparatus for assembling aircraft airframes |
| CN111014762A (en) * | 2019-12-13 | 2020-04-17 | 西安飞机工业（集团）有限责任公司 | Assembly method of connecting assembly of airplane frame and beam |
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2020
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| RU2058914C1 (en) * | 1992-06-08 | 1996-04-27 | Ташкентское авиационное производственное объединение им.В.П.Чкалова | Method of manufacture of aircraft fuselage inner skin |
| US6435781B1 (en) * | 2001-02-28 | 2002-08-20 | Stanley R. Jones | Template guide for centering drill in removing of broken stud |
| US20050084344A1 (en) * | 2003-10-20 | 2005-04-21 | The Boeing Company | Drill template with integral vacuum attach |
| FR2975930A1 (en) * | 2011-06-01 | 2012-12-07 | Ngi Nouvelle Generation D Ind | DRILLING JIG COMPRISING INDEPENDENT GUIDING GUNS AND PROTECTIVE CROWN |
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| CN111014762A (en) * | 2019-12-13 | 2020-04-17 | 西安飞机工业（集团）有限责任公司 | Assembly method of connecting assembly of airplane frame and beam |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112496681A (en) * | 2020-11-19 | 2021-03-16 | 中国航发沈阳黎明航空发动机有限责任公司 | Semi-ring matching part combination machining method |
| CN113618101A (en) * | 2021-08-18 | 2021-11-09 | 成都飞机工业（集团）有限责任公司 | Drilling device and drilling method for upper skin of closed box structure on wing |
| CN115502663A (en) * | 2022-09-26 | 2022-12-23 | 沈阳飞机工业（集团）有限公司 | Preparation method of large-scale fork-shaped skin contour |
| CN116852047A (en) * | 2023-07-28 | 2023-10-10 | 沈阳飞机工业（集团）有限公司 | Manufacturing method of double-sided sinking skin part |
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| Publication number | Publication date |
|---|---|
| CN111702200B (en) | 2024-04-09 |
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