CN113459199A - Hole making method for porous similar skin part - Google Patents
Hole making method for porous similar skin part Download PDFInfo
- Publication number
- CN113459199A CN113459199A CN202110702826.2A CN202110702826A CN113459199A CN 113459199 A CN113459199 A CN 113459199A CN 202110702826 A CN202110702826 A CN 202110702826A CN 113459199 A CN113459199 A CN 113459199A
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- hole
- skin part
- trepanning tool
- skin
- tool
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- 238000000034 method Methods 0.000 title claims abstract description 31
- 239000004744 fabric Substances 0.000 claims abstract description 48
- 239000000463 material Substances 0.000 claims abstract description 21
- 238000012545 processing Methods 0.000 claims abstract description 13
- 238000013499 data model Methods 0.000 claims abstract description 7
- 238000005553 drilling Methods 0.000 claims description 30
- 238000003825 pressing Methods 0.000 claims description 16
- 229920000122 acrylonitrile butadiene styrene Polymers 0.000 claims description 13
- 239000003086 colorant Substances 0.000 claims description 11
- 238000007639 printing Methods 0.000 claims description 6
- 239000003292 glue Substances 0.000 claims description 4
- 238000001179 sorption measurement Methods 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 238000003754 machining Methods 0.000 abstract description 4
- 238000010146 3D printing Methods 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 abstract description 2
- 239000002131 composite material Substances 0.000 description 9
- 229920001343 polytetrafluoroethylene Polymers 0.000 description 8
- 239000004810 polytetrafluoroethylene Substances 0.000 description 8
- 229920000049 Carbon (fiber) Polymers 0.000 description 7
- 230000006835 compression Effects 0.000 description 7
- 238000007906 compression Methods 0.000 description 7
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 7
- 239000004917 carbon fiber Substances 0.000 description 6
- 238000005520 cutting process Methods 0.000 description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 4
- 239000000853 adhesive Substances 0.000 description 3
- 230000001070 adhesive effect Effects 0.000 description 3
- 230000006872 improvement Effects 0.000 description 3
- 230000001788 irregular Effects 0.000 description 3
- -1 polytetrafluoroethylene Polymers 0.000 description 3
- 238000002360 preparation method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 239000004809 Teflon Substances 0.000 description 2
- 229920006362 Teflon® Polymers 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 238000012797 qualification Methods 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 241001391944 Commicarpus scandens Species 0.000 description 1
- 229920006231 aramid fiber Polymers 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003738 black carbon Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000001035 drying Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000012778 molding material Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
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- 238000002791 soaking Methods 0.000 description 1
- 230000008719 thickening Effects 0.000 description 1
- 238000009736 wetting Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B26—HAND CUTTING TOOLS; CUTTING; SEVERING
- B26D—CUTTING; DETAILS COMMON TO MACHINES FOR PERFORATING, PUNCHING, CUTTING-OUT, STAMPING-OUT OR SEVERING
- B26D7/00—Details of apparatus for cutting, cutting-out, stamping-out, punching, perforating, or severing by means other than cutting
- B26D7/01—Means for holding or positioning work
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B26—HAND CUTTING TOOLS; CUTTING; SEVERING
- B26F—PERFORATING; PUNCHING; CUTTING-OUT; STAMPING-OUT; SEVERING BY MEANS OTHER THAN CUTTING
- B26F1/00—Perforating; Punching; Cutting-out; Stamping-out; Apparatus therefor
- B26F1/16—Perforating by tool or tools of the drill type
Abstract
The invention discloses a hole making method for a porous similar skin part, which relates to the technical field of aircraft skin processing, reserves a method for sticking demolding cloth, and adopts a data model for establishing an auxiliary tool-a trepanning tool for the skin part; selecting a suitable material to print out the trepanning tool object by utilizing a 3D printing technology; then, sticking demolding cloth, positioning by using a trepanning tool and determining a hole making position; finally, hole making is carried out, the skin part which meets the requirements after hole making is obtained, the problem that demolding cloth is difficult to attach is effectively solved, compared with the prior art, hole making efficiency is remarkably improved, the hole making qualified rate can reach 98%, the rejection rate is reduced to 0, and machining cost is remarkably reduced.
Description
Technical Field
The invention relates to the technical field of aircraft skin machining, in particular to a hole making method for a porous similar skin part, which is commonly used in machining operation of irregular porous similar parts of aircraft skins.
Background
With continuous optimization and improvement of modern design means and processing methods, aircraft structural parts gradually develop towards light weight, complexity and integration, and a large number of composite skin parts with similar parts, multiple hole positions, complicated hole positions and irregular drilling surfaces appear in the aircraft structural parts. The parts have the problems of many similar parts, large quantity of drilled holes, complex hole position distribution, severe working condition of composite materials formed by layer-by-layer overlapping and poor orifice quality.
In practical application, when the drill bit is used for drilling holes, strict requirements are required on the sharpness of the drill bit and the reasonable selection of drilling parameters, but the problem that the drill bit peels off a lower-layer composite material when drilling out a skin part to cause wire shedding is easily caused, and the quality of the part is influenced.
In practical application, the demolding cloth is generally adhered to the skin part by using an opaque and black carbon fiber skin material, and the method for adhering the demolding cloth at present comprises the following steps: the sealing strip at the drilling part of the part tool is wetted by water, the part is placed on the tool, the part drilling processing approximate area is pressed by one hand, then the part is taken down, the part drilling position should be soaked by water, the demolding cloth is pasted at the water soaking part, when the number of holes is large, part of water is dried in the pasting process or part of holes is not sufficiently or partially dried in the wetting process of the sealing strip, the hole position cannot be judged, the condition of leakage pasting is caused, the steps are repeated subsequently, in the multi-time clamping process, the carrying is carried for many times, the manual participation degree is improved, the falling risk of the carbon fiber material is increased, the transverse resistance of the carbon fiber material is poor, once the carbon fiber material falls, the part is easy to break down and even scrapped, the cost of the carbon fiber material is high, and great economic loss is caused. However, without using a release cloth, the wire stripping at the hole-making opening is very easy to cause, as shown in fig. 7, which is not in accordance with the processing requirements.
From the background, whether the method of sticking the release cloth is adopted or not, the processing time is greatly increased, and the delivery progress is influenced.
The national intellectual property office discloses an invention patent with the application number of 'CN 201810763532.9' in 7/14/2020, and discloses a composite material drilling method, which comprises the following steps:
preparing a mould:
1) preparing a tetrafluoro rod according to the size of a positioning hole of a forming die, and processing the tetrafluoro rod into a structure the same as that of the positioning hole;
2) inserting the PTFE rod into the positioning hole, and cutting off the PTFE rod, wherein the cut-off surface of the PTFE rod is 2-5 mm higher than the tooling surface of the die;
3) knocking the PTFE bar higher than the tooling surface of the die to enable the PTFE bar to be tightly assembled with the positioning hole;
4) the part, higher than the polytetrafluoroethylene rod, of the polytetrafluoroethylene rod is flattened, so that the end part of the polytetrafluoroethylene rod is flush with the tool surface of the die;
5) cutting a 10mm multiplied by 10mm demoulding cloth with glue, sticking the cloth on the mounting surface of a mould, and covering a tetrafluoro rod; the distance between one side of the demoulding cloth with the rubber, which faces the blank side, and the outer diameter of the positioning hole is not more than 1 mm;
6) covering a layer of glass cloth prepreg which is slightly smaller than the size of the demoulding cloth and has the same resin with the blank on the demoulding cloth, and compacting;
molding:
placing the blank on a mould, and then carrying out hot press molding;
drilling:
after the die is opened, drilling a hole from one side of the molding material far away from the tetrafluoro rod to the other side;
and (6) demolding.
The above documents disclose a drilling method in which a tetrafluoro rod is required to be provided and cut during the operation, and although the problem of layered tearing of the hole wall and the hole edge is solved, the operation steps are complicated, and a new problem such as scrap is generated during the cutting of the tetrafluoro rod.
Disclosure of Invention
The invention aims to provide a hole making method of a porous similar skin part, which reserves a method for sticking demolding cloth, further optimizes the method for sticking the demolding cloth, effectively solves the problem of difficulty in sticking the demolding cloth by combining the existing 3D printing technology and has high sticking efficiency.
The invention is realized by the following technical scheme:
a hole making method of a porous similar skin part comprises the following steps:
a. designing a data model of a trepanning tool matched with the surface of the skin part according to the digital model of the skin part and the information of the position of a positioning hole to be drilled, designing a avoiding hole matched with the positioning hole on the data model of the trepanning tool, and arranging a pressing hole I matched with the pressing hole of the skin part on the data model of the trepanning tool so as to obtain the digital model of the trepanning tool;
b. b, printing a trepanning tool entity by using a 3D printer according to the digital model of the trepanning tool in the step a, tightly covering the trepanning tool on the surface of the skin part, matching and fixing a compression hole I of the trepanning tool with a compression hole of the skin part, and determining the avoidance hole position as the position of a positioning hole to be drilled;
c. then the surface with the glue of the demoulding cloth faces the part and is stuck to the part to be punched in the avoiding hole;
d. and placing the skin part adhered with the demolding cloth on a vacuum adsorption tool, pressing, drilling, taking down the skin part after drilling, and tearing off the demolding cloth to obtain the skin part after drilling.
Furthermore, the tolerance of the positions of the avoidance hole position and the skin part processing hole position is less than or equal to 0.1, and the tolerance of the hole diameter is +/-0.1.
Furthermore, the trepanning tool is made of ABS plastic materials.
Furthermore, the trepanning tool is formed by printing ABS plastic materials with colors different from the colors of the skin parts.
Furthermore, the similar structural skin part is printed into a matched trepanning tool by adopting ABS plastic materials with different colors, and the thickness of the trepanning tool is 0.2-0.5 mm.
Furthermore, the adhesive strength of the release cloth is 28N/dm, the extension coefficient is less than 5 per thousand, the surface friction coefficient is 0.05-0.1, and the temperature resistance range is-70-300 ℃.
Compared with the prior art, the invention has the following advantages and beneficial effects:
according to the method, a digital model of a trepanning tool is designed by utilizing a digital model of a skin part and hole site information needing drilling, a reasonable space avoidance hole is reserved according to processing requirements, and a trepanning tool real object meeting expected requirements is printed by using an ABS plastic material through a 3D printer and used for auxiliary drilling of the skin part; the demolding cloth can support the bottom of a composite material skin part which is formed by being layered layer by layer, so that the phenomenon that the lower layer of composite material is stripped to generate wire stripping when a drill drills out the skin part is prevented, and the drilled hole can meet the processing requirement.
Secondly, according to the digital model of the pre-stressed part and the hole site information needing to be drilled, the avoiding hole site is designed according to the needs of CATIA software, so that the digital model of the trepanning tool is designed, and a trepanning tool real object printed by a 3D printer can be used for ensuring that the hole site tolerance is less than or equal to 0.1 and the aperture tolerance is +/-0.1, so that the demoulding cloth and the drilling position are consistent and the processing requirements are met.
In the invention, the trepanning tool is made of ABS plastic materials and is generally designed into a trepanning tool with the thickness of 0.2-0.5 mm, and the trepanning tool made of the materials is light in weight, high in strength and capable of being well attached to the molded surface of a part.
Fourthly, the trepanning tool is printed by ABS plastic materials with colors different from the colors of the parts, and hole positions needing drilling are easy to find obviously according to the color difference.
In the invention, the similar structural parts are printed into matched trepanning tools by adopting ABS plastic materials with different colors, so that the similar parts can be quickly distinguished, the problem that the similar parts are more in skin parts and are easy to be confused is solved, the same trepanning tool can be used for the same part, and the trepanning efficiency is improved.
Sixthly, the surface of the demolding cloth is smooth, the adhesion strength of the demolding cloth is 28N/dm, the extension coefficient is less than 5 thousandth, the surface friction coefficient is 0.05-0.1, the temperature resistance range is-70-300 ℃, the demolding cloth can be tightly attached to a sealing strip protruding from a vacuum adsorption tool, air is not leaked, the strength of the demolding cloth is high, the bottom of a composite material skin part formed by being layered can be supported, and the phenomenon that a drill bit peels off a lower-layer composite material to generate wire stripping when drilling the skin part is avoided.
Drawings
FIG. 1 is a schematic view of a trepanning tool in engagement with a part.
Fig. 2 is a schematic structural view of the trepanning tool fixed with a part through a pressing hole.
Fig. 3 is a left part of a skin part to be perforated.
Fig. 4 is a left part of a skin part to be perforated.
FIG. 5 is a schematic view of the structure of the trepanning tool in close engagement with the part.
FIG. 6 is a schematic view of a hole to be drilled to produce a qualified non-run hole.
FIG. 7 is a schematic illustration of the production of a filament-removing hole.
Wherein, 1, covering parts; 2. a trepanning tool; 3. positioning holes; 4. avoiding holes; 5. pressing the hole; 6. pressing the hole I; 7. demolding the cloth; 8. removing the silk holes; 9. no filament holes were removed.
Detailed Description
The present invention will be described in further detail with reference to examples, but the embodiments of the present invention are not limited thereto.
Example (b):
in the embodiment, a special-shaped skin part 1 with large curvature change is taken as an example by the company, the invention relates to the technical field of aircraft skin processing, and the invention is further described, a hole needs to be formed in the special-shaped skin part 1, the hole drilled in the skin part 1 is generally a positioning hole 3, the hole is subsequently used for assembling and positioning, the carbon fiber skin is positioned on an aircraft appearance aerodynamic surface, if the hole is subjected to wire stripping, a molded surface of a wire stripping part is raised, so that the molded surface interferes with an aircraft assembling and positioning device in an assembling process, the positioning function is invalid, the carbon fiber skin is uniformly distributed on the aircraft aerodynamic outer molded surface, and the wire stripping is carried out at the drilling position, so that the aircraft aerodynamic appearance performance is reduced, and the normal flight of the aircraft is influenced. Therefore, positioning holes 3 which do not have wire shedding and have the apertures and the hole positions meeting the requirements are manufactured on the special-shaped skin parts.
The special-shaped skin parts 1 are concave and convex, and by taking a certain group of skin parts 1 with similar structures as an example, referring to fig. 3-4, the number of holes is 50, the positions are distributed, and the required hole diameter is phi 3.
Aiming at the hole making of the porous similar skin part 1, a new method is adopted, and the method specifically comprises the following steps:
a. designing a digital model of the trepanning tool 2:
the specific operation method comprises the following steps: according to part surface model data given in a previous procedure for producing the skin part 1, a digital model of the trepanning tool 2 is established, and hole positions and sizes of the avoidance holes 4 are reasonably designed on the digital model of the trepanning tool 2, the embodiment adopts offset thickening operation in CATIA software of an existing machine tool, any surface can be thickened to an expected thickness along a normal line, the precision can reach 0.01mm, the requirement of machining tolerance is met, and the aperture of the avoidance holes 4 is set to phi 25 +/-1;
designing compression holes I6 matched with the compression holes 5 on the skin part on a digital model of the trepanning tool 2, wherein the compression holes I6 are distributed on the peripheral side of the trepanning tool 2, and the sizes of the compression holes 5 and the compression holes I6 are set to be phi 8;
b. b, printing a real object of the trepanning tool 2 by using a 3D printer according to the digital model of the trepanning tool 2 in the step a, covering the trepanning tool 2 on the surface of the skin part 1 tightly, matching and fixing a pressing hole I6 of the trepanning tool 2 with a pressing hole 5 of the skin part, so as to realize the positioning of the trepanning tool 2, referring to the figure 2 or 5, wherein an area of an avoiding hole 4 phi 25 on the trepanning tool 2 is the position of a positioning hole 3 to be drilled, as shown in figure 1;
c. cutting the demoulding cloth 7 into small demoulding cloth with the size of phi 20 +/-1, and sticking the surface with the glue of the demoulding cloth 7 to the part at the position to be punched in the avoiding hole 4, referring to fig. 2;
d. and placing the skin part adhered with the demolding cloth 7 on a vacuum adsorption tool, pressing, drilling, taking down the skin part 1 after drilling, and tearing off the demolding cloth 7 to obtain the skin part 1 after drilling.
Fig. 6 shows a schematic diagram of the overall qualification of the drilled holes after the release cloth 7 is completely attached by using the trepanning tool 2.
Compared with the prior method for attaching the whole piece of demolding cloth 7, the method for attaching the demolding cloth 7 can save the demolding cloth 7 as much as possible and obviously reduce the processing and manufacturing cost.
Furthermore, when the trepanning tool 2 is manufactured, the tolerance of the hole position of the avoiding hole 4 and the hole position of the skin part 1 is less than or equal to 0.1, the part is processed by positioning and clamping the 4 phi 8 pressing holes 5 on the part, the pressing holes I6 identical to the hole positions of the pressing holes 5 can be formed in the trepanning tool 2, the tolerance of the hole position is less than or equal to 0.1, the tolerance of the hole position is +/-0.1, the demoulding cloth 7 can be covered above the drilling position according to the 4 hole positions, and the position of the avoiding hole 4 on the trepanning tool 2 is the expected drilling position, so that the drilled hole is not easy to generate a wire-off hole under the assistance of the demoulding cloth 7.
Further, in the technical scheme, the trepanning tool 2 is made of ABS plastic materials, and the trepanning tool 2 is 0.5mm thick and can be tightly attached to the molded surface of the part.
In actual use, the thickness of the trepanning tool 2 is designed to be 0.2-0.5 mm, but the trepanning tool 2 with the thickness of 0.5mm is more convenient to move and install.
In the technical scheme, another preferable scheme is adopted, the trepanning tool 2 is made of ABS plastic materials with colors different from the colors of parts by printing, and hole positions needing drilling are obviously easy to find according to the color difference.
Further, in the present technical solution, there is another preferred solution, the similar structural parts are printed with different color ABS plastic materials to form the matched trepanning tool 2. Similar parts can be distinguished fast, the problems that the number of the similar parts in the skin part is large and the similar parts are easy to confuse are solved, the same part can also use the same trepanning tool 2, and the hole making efficiency is improved.
Furthermore, the demolding cloth 7 is a high-strength reticular base cloth woven by adopting high-quality glass fiber and aramid fiber as base materials, and then coated with Teflon resin with excellent characteristics to prepare the base cloth of the Teflon reticular drying room conveyor belt, wherein the thickness of the base cloth is 0.08mm, the adhesive coating is 0.05mm, the extension coefficient is less than 5 per thousand, the surface friction coefficient is 0.05-0.1, the adhesive strength (to steel) is not less than 28N/dm, the tensile strength is 1700N/dm, and the temperature resistance range is-70-300 ℃. Generally, the adhesion strength (to steel) is 28N/dm or slightly higher than 28N/dm.
The parts not involved in the present invention are the same as or can be implemented using the prior art.
By adopting the technical scheme, the working efficiency of the composite skin part with similar parts, more hole positions, complicated hole positions and irregular drilling surface can be obviously improved, for example, the preparation time before processing of a certain hole-making part needs 1.5 hours, the preparation time after improvement only needs 0.5 hour, and the preparation time is shortened by 66.67 percent; the rejection rate of the part reaches 42 percent (the part is rejected according to the total length of the wire stripping of the file exceeding 25 mm), the qualification rate of hole making after improvement reaches 98 percent, the rejection rate is reduced to 0, and the rejection rate of the part is obviously reduced.
The technical scheme can be used for other similar parts, particularly in the hole-making environment with higher hole-making requirements and needing to be adhered with the film-removing cloth.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (6)
1. A hole making method of a porous similar skin part is characterized by comprising the following steps:
a. designing a data model of a trepanning tool (2) matched with the surface of the skin part according to the digital model of the skin part and hole site information of a positioning hole (3) to be drilled, designing a yielding hole (4) matched with the positioning hole (3) on the data model of the trepanning tool (2), and arranging a pressing hole I (6) matched with a skin part pressing hole (5) on the data model of the trepanning tool (2) so as to obtain the digital model of the trepanning tool (2);
b. b, printing a real object of the trepanning tool (2) by using a 3D printer according to the digital model of the trepanning tool (2) in the step a, tightly covering the trepanning tool (2) on the surface of the skin part, matching and fixing a pressing hole I (6) of the trepanning tool (2) with a pressing hole (5) of the skin part, and then determining the position of the avoidance hole (4) as the position of the positioning hole (3) to be drilled;
c. then, the surface with the glue of the demolding cloth (7) faces the part and is stuck to the part to be punched in the avoiding hole (4);
d. and placing the skin part adhered with the demolding cloth (7) on a vacuum adsorption tool for compressing, then drilling, then taking down the skin part after drilling, and tearing off the demolding cloth (7) to obtain the skin part after drilling.
2. The method for making the hole of the porous similar skin part according to the claim 1, wherein the method comprises the following steps: the tolerance of the positions of the hole positions of the avoidance holes (4) and the positions of the holes of the skin part processing holes is less than or equal to 0.1, and the tolerance of the hole diameter is +/-0.1.
3. The method for making the hole of the porous similar skin part according to the claim 2, wherein the method comprises the following steps: the trepanning tool (2) is made of ABS plastic materials.
4. A method of making a porous skin-like part according to claim 3, wherein: the trepanning tool (2) is formed by printing ABS plastic materials with colors different from the colors of the skin parts.
5. The method for making the hole of the porous similar skin part according to claim 4, wherein the method comprises the following steps: the similar structural skin part is printed into a matched trepanning tool (2) by adopting ABS plastic materials with different colors, and the thickness of the trepanning tool (2) is 0.2-0.5 mm.
6. A method for making a porous similar skin element according to any of claims 1-5, wherein: the adhesion strength of the demolding cloth (7) is not lower than 28N/dm, the extension coefficient is less than 5 per thousand, the surface friction coefficient is 0.05-0.1, and the temperature resistance range is-70-300 ℃.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110702826.2A CN113459199A (en) | 2021-06-24 | 2021-06-24 | Hole making method for porous similar skin part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110702826.2A CN113459199A (en) | 2021-06-24 | 2021-06-24 | Hole making method for porous similar skin part |
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| Publication Number | Publication Date |
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| CN113459199A true CN113459199A (en) | 2021-10-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110702826.2A Pending CN113459199A (en) | 2021-06-24 | 2021-06-24 | Hole making method for porous similar skin part |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102240824A (en) * | 2011-05-11 | 2011-11-16 | 西安飞机工业（集团）有限责任公司 | Wall panel skin shape drilling die and manufacturing method thereof |
| CN102658378A (en) * | 2012-05-22 | 2012-09-12 | 西安飞机工业（集团）有限责任公司 | Drilling method for wall plate skin of airplane |
| 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 |
| CN108943545A (en) * | 2018-07-12 | 2018-12-07 | 安徽佳力奇碳纤维科技股份公司 | A kind of composite material boring method |
| US20200113054A1 (en) * | 2018-10-08 | 2020-04-09 | Quest Integrated, Llc | Printed multifunctional skin for aerodynamic structures and associated systems and methods |
| CN111331179A (en) * | 2020-02-18 | 2020-06-26 | 北京航空航天大学 | 3D printing drill plate for self-adaptive airplane curved surface skin hole making |
-
2021
- 2021-06-24 CN CN202110702826.2A patent/CN113459199A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102240824A (en) * | 2011-05-11 | 2011-11-16 | 西安飞机工业（集团）有限责任公司 | Wall panel skin shape drilling die and manufacturing method thereof |
| CN102658378A (en) * | 2012-05-22 | 2012-09-12 | 西安飞机工业（集团）有限责任公司 | Drilling method for wall plate skin of airplane |
| 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 |
| CN108943545A (en) * | 2018-07-12 | 2018-12-07 | 安徽佳力奇碳纤维科技股份公司 | A kind of composite material boring method |
| US20200113054A1 (en) * | 2018-10-08 | 2020-04-09 | Quest Integrated, Llc | Printed multifunctional skin for aerodynamic structures and associated systems and methods |
| CN111331179A (en) * | 2020-02-18 | 2020-06-26 | 北京航空航天大学 | 3D printing drill plate for self-adaptive airplane curved surface skin hole making |
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Application publication date: 20211001 |