CN111702200B - Processing method of skin mold assembly positioning hole - Google Patents
Processing method of skin mold assembly positioning hole Download PDFInfo
- Publication number
- CN111702200B CN111702200B CN202010535716.7A CN202010535716A CN111702200B CN 111702200 B CN111702200 B CN 111702200B CN 202010535716 A CN202010535716 A CN 202010535716A CN 111702200 B CN111702200 B CN 111702200B
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- China
- Prior art keywords
- skin
- assembly positioning
- hole
- holes
- machining
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- 238000003672 processing method Methods 0.000 title claims abstract description 8
- 238000000034 method Methods 0.000 claims abstract description 26
- 238000005553 drilling Methods 0.000 claims abstract description 15
- 238000006243 chemical reaction Methods 0.000 claims abstract description 7
- 238000003754 machining Methods 0.000 claims description 15
- 238000009434 installation Methods 0.000 claims description 6
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 3
- 238000000465 moulding 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
- 239000000463 material Substances 0.000 claims description 2
- 229920000647 polyepoxide Polymers 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 239000004033 plastic Substances 0.000 description 2
- 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
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
Abstract
The invention belongs to the field of skin mold manufacturing, and discloses a rapid and accurate processing method of a skin mold assembly positioning hole. According to the method, the skin die is subjected to numerical control processing, and the skin assembly positioning holes are subjected to reference conversion through the drilling template, so that the assembly positioning holes with the bushings are accurately manufactured on the skin die and are used for skin part forming and positioning and subsequent assembly.
Description
Technical Field
The invention belongs to the field of skin mould manufacture, and aims to accurately manufacture an assembly positioning hole on a skin mould by performing secondary conversion on a reference by using a drilling template. In particular to a processing method of a skin mold assembly positioning hole.
Background
In order to improve the aircraft skin assembly efficiency, certain interchangeability and consistency of skin parts are required, namely the overall dimension and the heat meter state of the parts are required, namely the parts with the same drawing number can be directly used by taking one part at will, and the parts are not required to be installed in an assembly frame through lofting and allowance distribution. The skin mold is provided with the assembly positioning holes which are consistent with the hole positions on the assembly frame, so that the skin is rapidly and correctly placed in the frame for assembly. Therefore, in the design and manufacture of the skin mold, the assembly positioning hole relative to the aircraft space needs to be manufactured. The assembly positioning holes are consistent with the assembly type frame (or the space posture of the airplane). And are all 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 mold assembly positioning hole.
The method is used for accurately reflecting the assembly positioning holes on the aircraft skin to the skin mould of the forming tool. Firstly, carrying out numerical control processing on the skin die, wherein the numerical control processing comprises normal holes of the molded surface and assembly positioning holes. Secondly, according to the normal assembly positioning hole, a positioning pin is inserted to accurately position the drill plate, the drill plate is molded (resin curing period 24H), and the positioning pin of the drill plate is configured. Finally, after the drilling template is molded (resin curing period 24H), the drilling template is removed, the assembly positioning holes on the molded surface of the mold are reamed, the drilling template is reinstalled, and the assembly positioning holes with the bushings are newly manufactured on the skin mold according to the installed drilling template, so that the manufacturing of the assembly positioning holes is completed.
Technical proposal
And carrying out numerical control processing on the skin die, and carrying out reference conversion on the skin assembly positioning holes through the drill jig plate, so that the assembly positioning holes are accurately manufactured for the skin part forming positioning and subsequent assembly.
A processing method of a skin mold assembly positioning hole comprises the following steps:
the method comprises the steps of 1, adopting five-axis numerical control to process the molded surface and the mounting hole of the skin mold 4 and the assembly positioning hole 2 normal to the molded surface.
2, inserting a locating pin A5 according to the machined assembly locating hole 2 on the skin die 4 as a reference, and accurately locating the two locating pins B6 on the plastic drilling template 3, thereby completing the installation work of the drilling template 3.
And 3, dismantling the drill jig plate 3, reaming the assembly positioning hole 2 on the skin die 4, and ensuring the normal installation of the bushing by using the big and small holes of the hole diameter.
4, inserting a locating pin B6 on the skin die 4 to reinstall the drill jig plate 3, simultaneously inserting a locating pin A5 on the drill jig plate 3, and carrying out a bushing molding process on the assembly locating hole 2 of the skin die 4, and ensuring that the top end face of the bushing is lower than the molded surface of the skin die 4.
In the steps 1-4:
1) The assembly positioning holes 2 on the skin mould 4 correspond to the assembly positioning holes on the aircraft skin 1, and the aperture and the hole position are consistent.
2) In all the hole sites on the skin die 4, the precision requirement of the assembly positioning hole 2 is far higher than that of the other hole sites.
3) The depth of all holes in the skin mold 4 must be greater than the height of the pre-buried bushings.
4) The machining equipment used in the method is limited to five-axis numerical control equipment, and machining of the normal holes must be completed.
5) In the method, the drill plate 3 is made of 45# steel, and the quenching heat treatment ensures hardness and wear resistance.
6) In the method, reference conversion is ensured and realized through the aperture on the drill jig plate 3 and the hole site.
7) In this method the drill plate 3 is a detachable part.
The secondary machining of the assembly positioning holes is carried out by the drill jig plate, so that the machining precision of the drill jig plate can directly influence the precision of the assembly positioning holes of the skin mold.
Technical effects
Compared with the conventional operation method, the invention has the beneficial effects that:
1. the skin with the assembly positioning holes is adopted, so that the assembly efficiency of the aircraft skin is improved.
2. The aircraft skin is assembled through the assembly positioning holes, zero allowance assembly is realized, and the aircraft skin assembly period and cost are saved.
3. The skin die assembly positioning hole is processed in a numerical control mode, and a bushing is molded on the skin die assembly positioning hole by means of secondary positioning through a drilling template; the aperture precision is guaranteed, and the durability of the assembly positioning hole is guaranteed.
Drawings
FIG. 1 is a schematic view of a part processing architecture;
FIG. 2 is a cross-sectional view of a part process;
wherein: 1-aircraft skin 2-assembly positioning holes 3-drilling jig plates 4-skin mould tires 5-positioning pins A6-positioning pins B.
Detailed Description
The present invention will be described in further detail below.
The specific manufacturing process of the invention comprises the following steps:
1. the molded surface and the mounting holes of the skin mold 4 and the assembly positioning holes 2 normal to the molded surface are processed by adopting 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 the drill jig plate 3, and the molded surface and the mounting holes of the skin mold 4 are in a formal state after all the holes are accurately mounted with the bushing).
2, inserting a locating pin A5 according to the machined assembly locating hole 2 on the skin die 4 as a reference, and accurately locating the two locating pins B6 on the plastic drilling template 3, thereby completing the installation work of the drilling template 3.
And 3, dismantling the drill jig plate 3, reaming the assembly positioning hole 2 on the skin die 4, and ensuring the normal installation of the bushing by using the big and small holes of the hole diameter.
4 reinstalling the drill plate 3 by inserting a locating pin B6 on the skin die 4 on the premise of ensuring the aperture size, the hole position size relation and the tolerance requirement on the drill plate 3, inserting a locating pin A5 on the drill plate 3, and performing a bushing molding process on the assembly locating hole 2 of the skin die 4, wherein the topmost end face of the bushing is ensured to be 1mm lower than the molded surface of the skin die 4. Thus, the processing method of the invention about the skin mold assembly positioning hole 2 is completed.
The assembly positioning holes 2 on the skin mould 4 correspond to the assembly positioning holes on the aircraft skin 1, and the aperture and the hole position are consistent.
In all the hole sites on the skin die 4, the precision requirement of the assembly positioning hole 2 is far higher than that of the other hole sites.
The depth of all holes on the skin die 4 is required to be larger than the height of the embedded bushings, so that the bushings installed on all holes are ensured to be 1mm lower than the molded surface of the skin die 4, and the normal use of the skin die 4 is avoided.
The machining equipment used in the method is limited to five-axis numerical control equipment, and machining of the normal holes must be completed.
In the method, the drill plate 3 is made of 45# steel, and the quenching heat treatment ensures hardness and wear resistance. The skin mould 4 is made of epoxy resin material and is of a wooden frame structure.
In the method, reference conversion is ensured and realized through the aperture on the drill jig plate 3 and the hole site.
In the method, the drill plate 3 is a detachable part and is a part of a tooling of the skin die 4.
Three holes are formed in the drill jig plate 3, wherein the assembly positioning holes 2 are phi 5.2mm, and the positioning pins A5 matched with the assembly positioning holes are phi 5.2mm; the aperture of the rest two holes is phi 8mm, and the locating pin B6 matched with the rest two holes is phi 8mm; the tolerance of the fit between all the positioning pins and the holes on the drill jig plate 3 is H7/H6. The position tolerance between the holes on the drill plate 3 is less than 0.05mm.
The locating pin A5 is used for assembling the locating hole 2, and the aperture is phi 5.2mm. The locating pin B6 is used for installing and fixing the drill jig plate 3, and the aperture is phi 8mm.
1) The invention realizes the processing of the assembly positioning holes mainly through reference conversion, so that deviation can be generated necessarily; but the deviation is controlled properly without affecting the skin assembly.
2) The invention needs to carry out secondary machining of the assembly positioning hole by the drill jig plate, so that the machining precision of the drill jig plate can directly influence the precision of the assembly positioning hole of the skin mold.
3) The processing equipment adopted by the invention is limited to five-axis numerical control processing.
Claims (8)
1. The processing method of the skin mold assembly positioning hole is characterized by comprising the following steps of:
1) Adopting five-axis numerical control to process the molded surface and the mounting hole of the skin mold (4) and the assembly positioning hole (2) normal to the molded surface;
2) According to the machined assembly positioning holes (2) on the skin mould (4) as a reference, positioning pins A (5) are inserted, accurate positioning is performed, two positioning pins B (6) on the drilling template (3) are molded, and therefore the drilling template (3) installation work is completed;
3) Removing the drill jig plate (3), reaming the assembly positioning hole (2) on the skin mold (4), and ensuring the normal installation of the bushing by the big and small holes of the hole diameter;
4) And (3) is reinstalled by inserting a locating pin B (6) on the skin die (4), and meanwhile, a locating pin A (5) is inserted on the drilling template (3), so that the assembly locating hole (2) of the skin die (4) is subjected to a bushing molding process, and the topmost end face of the bushing is ensured to be lower than the molded surface of the skin die (4).
2. The method for machining the skin mold assembly positioning holes according to claim 1, wherein the assembly positioning holes (2) on the skin mold (4) correspond to the assembly positioning holes on the aircraft skin (1), and the hole diameters are consistent with the hole positions.
3. The method for machining the skin mold assembly positioning holes according to claim 1, wherein the accuracy requirement of the assembly positioning holes (2) is higher than that of the rest hole positions in all hole positions on the skin mold (4).
4. The method for machining the skin mold assembly positioning holes according to claim 1, wherein the depth of all holes on the skin mold (4) is larger than the height of the embedded bushing.
5. A method for machining a skin mold assembly positioning hole according to claim 1, wherein the machining equipment adopted in the method is defined as five-axis numerical control equipment.
6. The method for processing the skin mold assembly positioning hole according to claim 1, wherein the drill plate (3) is made of 45# steel, and the quenching heat treatment ensures hardness and wear resistance; the skin mould (4) is made of epoxy resin material and is of a wooden frame structure.
7. The method for machining the skin mold assembly positioning hole according to claim 1, wherein the reference conversion is ensured and realized through the aperture on the drill plate (3) and the hole position.
8. A method of machining a pilot hole in a skin mould according to claim 1, characterised in that the jig plate (3) is a removable 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 CN111702200A (en) | 2020-09-25 |
| CN111702200B true CN111702200B (en) | 2024-04-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010535716.7A Active CN111702200B (en) | 2020-06-12 | 2020-06-12 | Processing method of skin mold assembly positioning hole |
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| CN (1) | CN111702200B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112496681B (en) * | 2020-11-19 | 2022-10-11 | 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 |
| CN113618101B (en) * | 2021-08-18 | 2022-09-20 | 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 |
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| US6435781B1 (en) * | 2001-02-28 | 2002-08-20 | Stanley R. Jones | Template guide for centering drill in removing of broken stud |
| CN102677057A (en) * | 2012-05-22 | 2012-09-19 | 西安飞机工业（集团）有限责任公司 | Method for manufacturing sheet metal part stereo chemical milling sample plate |
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| CN203044979U (en) * | 2013-01-10 | 2013-07-10 | 哈尔滨飞机工业集团有限责任公司 | Tooling clamping plate positioning hole drill jig |
| CN105880918A (en) * | 2014-05-16 | 2016-08-24 | 哈尔滨飞机工业集团有限责任公司 | Composite material skin digital manufacture method |
| CN107413948A (en) * | 2017-03-16 | 2017-12-01 | 成都飞机工业（集团）有限责任公司 | The pull-shaped mould and its manufacture method of a kind of composite construction |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7195429B2 (en) * | 2003-10-20 | 2007-03-27 | The Boeing Company | Drill template with integral vacuum attach |
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2020
- 2020-06-12 CN CN202010535716.7A patent/CN111702200B/en active Active
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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 |
| 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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| CN107413948A (en) * | 2017-03-16 | 2017-12-01 | 成都飞机工业（集团）有限责任公司 | The pull-shaped mould and its manufacture method of a kind of composite construction |
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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 |
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| Publication number | Publication date |
|---|---|
| CN111702200A (en) | 2020-09-25 |
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