CN103586500A - Hole making method for honeycomb interlayer composite materials - Google Patents
Hole making method for honeycomb interlayer composite materials Download PDFInfo
- Publication number
- CN103586500A CN103586500A CN201310536985.5A CN201310536985A CN103586500A CN 103586500 A CN103586500 A CN 103586500A CN 201310536985 A CN201310536985 A CN 201310536985A CN 103586500 A CN103586500 A CN 103586500A
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- Prior art keywords
- drilling
- drill
- honeycomb sandwich
- sandwich composite
- hole
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- 239000002131 composite material Substances 0.000 title claims abstract description 31
- 238000000034 method Methods 0.000 title claims abstract description 25
- 239000011229 interlayer Substances 0.000 title abstract description 10
- 238000005553 drilling Methods 0.000 claims abstract description 54
- 229910003460 diamond Inorganic materials 0.000 claims description 9
- 239000010432 diamond Substances 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 5
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 230000013011 mating Effects 0.000 claims description 2
- 230000007547 defect Effects 0.000 abstract description 6
- 230000003247 decreasing effect Effects 0.000 abstract 1
- 230000017525 heat dissipation Effects 0.000 abstract 1
- 238000003754 machining Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 4
- 238000003475 lamination Methods 0.000 description 4
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 239000011521 glass Substances 0.000 description 2
- 239000000123 paper Substances 0.000 description 2
- 239000004593 Epoxy Substances 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 239000004760 aramid Substances 0.000 description 1
- 229920003235 aromatic polyamide Polymers 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000011094 fiberboard Substances 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Images
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B51/00—Tools for drilling machines
- B23B51/04—Drills for trepanning
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Forests & Forestry (AREA)
- Drilling Tools (AREA)
Abstract
The invention discloses a hole making method for honeycomb interlayer composite materials. The method is characterized by comprising the following steps that a cross central line of holes to be drilled is marked on the honeycomb interlayer composite materials; initial holes are drilled with the cross central line as the axis; with the initial holes as guiding, finished holes are drilled with a trepanning drill at least one time. According to the hole making method for honeycomb interlayer composite materials, the large-diameter hole drilling step is completed at least two times, the vertex angle of a drill is reduced when the initial holes are drilled so as to increase the length of a cutting edge, heat dissipation conditions are improved, and the width of a transverse edge is reduced so as to decrease the drilling axial force; the trepanning drill is used in the subsequent drilling process so as to decrease cutting amount, and therefore the drilling axial force is decreased, and the interlayer layering defects generated in the machining process are avoided.
Description
Technical field
The present invention relates to a kind of method for drilling of honeycomb sandwich composite, relate in particular to a kind of processing method drilling compared with macropore on honeycomb sandwich composite.
Background technology
The composite of honeycomb sandwich construction, owing to having higher specific strength and the advantage such as heat insulation, shock-resistant is extremely wide in many fields application such as Aeronautics and Astronautics, civil engineering preferably, is mainly as the structural material that replaces steel.Honeycomb sandwich composite is consisted of the thicker honeycomb core of upper and lower panel therebetween one, the grid configuration of honeycomb core has regular hexagon, square, rhombus etc., material can be paper, glass cloth, aluminium alloy, aramid paper etc., panel can adopt glued board, fiberboard, aluminium alloy plate, glass epoxy etc., when holing on honeycomb sandwich composite, due to honeycomb sandwich composite, to have interlaminar strength low, anisotropy, hardness is high, the features such as fragility is large, easily produce interlayer layering, the boring defects such as discrepancy end fiber splitting, especially process the hole that diameter is larger (hole that is greater than 8 millimeters as diameter), when processing bolt counterbore or stepped hole, because drilling axial force can sharply increase along with the increasing of bit diameter, thereby more easily produce interlayer lamination defect.
Summary of the invention
For solving the pore volume that diameter is larger that drills of prior art, easily produce interlayer lamination defect, the invention provides a kind of method for drilling of honeycomb sandwich composite, the method for drilling of a kind of honeycomb sandwich composite of the present invention, comprises the steps: to mark cross centre line to be holed on honeycomb sandwich composite; The cross centre line of take gets out just hole as axle center; With first hole, for guiding jacking at least one times, get out pore-forming.
The described cross centre line of take is fluted drill as axle center gets out the drilling tool using in the step in first hole.
The drift angle of described fluted drill is less than 118 °.
Described take first hole to get out the drilling tool using in the step of pore-forming be cylindrical drill in order to guide at least one times jacking.
Described cylindrical drill comprises drill bushing and drilling rod, it is characterized in that, described drill bushing is tubulose, drill bushing one end is provided with cutting edge, the drill bushing other end is provided with internal thread, and described drilling rod is stepped stem, and front end is first hole guide rod, on described first hole guide rod, be shaped with the external screw thread that the internal thread with drill bushing is spirally connected, the rear end of described drilling rod is the drillstock mating with pneumatic drill clamping part.
Described cutting edge is along drill bushing circumference equal dividing layout, and the tube wall between cutting edge has chip pocket, and the inner and outer wall of tube wall is all made back taper.
Described back taper is got 0.5 °.
The anterior angle of the cutting edge of described drill bushing is 6 °, and relief angle is 15 °～18 °, and centripetal drift angle is got 3 °, and end gap angle is got 6 °～8 °.
It is Polycrystalline diamond that the cutting edge of described drill bushing scribbles diamond PCD(, polycrystalline diamond) material coating.
The present invention has following good effect than prior art, the method for drilling of a kind of honeycomb sandwich composite of the present invention, the step that drills large diameter hole is at least divided into and is got out for twice, while drilling first hole, reduce drill head apical angle to increase cutting edge length, improve radiating condition, reduce chisel edge width, to reduce drilling axial force; Follow-up drilling in operation adopts cylindrical drill to reduce cutting output, thereby reduced drilling axial force, avoided producing interlayer lamination defect in processing.
Accompanying drawing explanation
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail.
Fig. 1 is the schematic diagram of cylindrical drill of the method for drilling of a kind of honeycomb sandwich composite of the present invention.
Fig. 2 is the schematic diagram of drill bushing of cylindrical drill of the method for drilling of a kind of honeycomb sandwich composite of the present invention.
Fig. 3 is the schematic diagram of drilling rod of cylindrical drill of the method for drilling of a kind of honeycomb sandwich composite of the present invention.
Schematic diagram.
In figure: 1. drill bushing, 2. drilling rod, 21. first hole guide rods, 22. drillstocks, 23. external screw threads.
The specific embodiment
The method for drilling of a kind of honeycomb sandwich composite of the present invention, comprises the steps: to mark cross centre line to be holed on honeycomb sandwich composite; The cross centre line of take gets out just hole as axle center; With first hole, for guiding jacking at least one times, get out pore-forming.
The described cross centre line of take is fluted drill as axle center gets out the drilling tool using in the step in first hole.
The drift angle of described fluted drill is less than 118 °.
Described take first hole to get out the drilling tool using in the step of pore-forming be cylindrical drill in order to guide at least one times jacking.
Fig. 1, Fig. 2 and Fig. 3 show cylindrical drill, comprise drill bushing 1 and drilling rod 2, it is characterized in that, described drill bushing 1 is tubulose, and drill bushing 1 one end is provided with cutting edge, and drill bushing 1 other end is provided with internal thread, described drilling rod 2 is stepped stem, front end is first hole guide rod 21, is shaped with the external screw thread 23 that the internal thread with drill bushing 1 is spirally connected on described first hole guide rod 21, and the rear end of described drilling rod 2 is the drillstocks 22 that mate with pneumatic drill clamping part.
Described cutting edge is along drill bushing 1 circumference equal dividing layout, and the tube wall between cutting edge has chip pocket, and the inner and outer wall of tube wall is all made back taper.
Described back taper is got 0.5 °, has formed the side clearance of cutting edge.
In Fig. 2, a is the anterior angle of cutting edge, and b is the relief angle of cutting edge, and the anterior angle of the cutting edge of described drill bushing 1 is 6 °, and relief angle is 15 °～18 °, and centripetal drift angle is got 3 °, and end gap angle is got 6 °～8 °.
It is Polycrystalline diamond that the cutting edge of described drill bushing 1 scribbles diamond PCD(, polycrystalline diamond) material coating.
During jacking drilling, adopt the technological parameter of higher rotation speed, lower feeding, with radial drilling machine, for example, when Z3040 radial drilling machine is holed, conventionally being controlled at rotating speed 2000rpm(is revolutions per minute, revolution per minute), the amount of feeding 0.04～0.06(mm/r represents millimeter/often turn) in scope; During with adjustable speed pneumatic drill spot-facing, be conventionally controlled within the scope of rotating speed 960rpm, the amount of feeding 0.01～0.04mm/r, drilling quality is better.
The method for drilling of a kind of honeycomb sandwich composite of the present invention, is at least divided into the step that drills large diameter hole and gets out for twice, reduces drill head apical angle to increase cutting edge length while drilling first hole, improves radiating condition, reduces chisel edge width, to reduce drilling axial force; Follow-up drilling in operation adopts cylindrical drill to reduce cutting output, thereby reduced drilling axial force, avoided producing interlayer lamination defect in processing.
Claims (9)
1. a method for drilling for honeycomb sandwich composite, is characterized in that, comprises the steps: to mark cross centre line to be holed on honeycomb sandwich composite; The cross centre line of take gets out just hole as axle center; With first hole, for guiding jacking at least one times, get out pore-forming.
2. the method for drilling of a kind of honeycomb sandwich composite according to claim 1, is characterized in that, the described cross centre line of take is fluted drill as axle center gets out the drilling tool using in the step in first hole.
3. the method for drilling of a kind of honeycomb sandwich composite according to claim 2, is characterized in that, the drift angle of described fluted drill is less than 118 °.
4. the method for drilling of a kind of honeycomb sandwich composite according to claim 1, is characterized in that, described take first hole to get out the drilling tool using in the step of pore-forming be cylindrical drill in order to guide at least one times jacking.
5. the method for drilling of a kind of honeycomb sandwich composite according to claim 4, it is characterized in that, cylindrical drill comprises drill bushing (1) and drilling rod (2), it is characterized in that, described drill bushing (1) is tubulose, drill bushing (1) one end is provided with cutting edge, drill bushing (1) other end is provided with internal thread, described drilling rod (2) is stepped stem, front end is first hole guide rod (21), on described first hole guide rod (21), be shaped with the external screw thread (23) that the internal thread with drill bushing (1) is spirally connected, the rear end of described drilling rod (2) is the drillstock (22) mating with pneumatic drill clamping part.
6. the method for drilling of a kind of honeycomb sandwich composite according to claim 5, is characterized in that, described cutting edge is along drill bushing (1) circumference equal dividing layout, and the tube wall between cutting edge has chip pocket, and the inner and outer wall of tube wall is all made back taper.
7. the method for drilling of a kind of honeycomb sandwich composite according to claim 6, is characterized in that, described back taper is got 0.5 °.
8. the method for drilling of a kind of honeycomb sandwich composite according to claim 5, is characterized in that, the anterior angle of the cutting edge of described drill bushing (1) is 6 °, and relief angle is 15 °～18 °, and centripetal drift angle is got 3 °, and end gap angle is got 6 °～8 °.
9. according to the method for drilling of any honeycomb sandwich composite described in claim 5 to 8, it is characterized in that, it is Polycrystalline diamond that the cutting edge of described drill bushing (1) scribbles diamond PCD(, polycrystalline diamond) material coating.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310536985.5A CN103586500A (en) | 2013-11-04 | 2013-11-04 | Hole making method for honeycomb interlayer composite materials |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310536985.5A CN103586500A (en) | 2013-11-04 | 2013-11-04 | Hole making method for honeycomb interlayer composite materials |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103586500A true CN103586500A (en) | 2014-02-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310536985.5A Pending CN103586500A (en) | 2013-11-04 | 2013-11-04 | Hole making method for honeycomb interlayer composite materials |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103586500A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107443434A (en) * | 2017-08-25 | 2017-12-08 | 陕西飞机工业（集团）有限公司 | A kind of composite method for drilling |
| CN107775720A (en) * | 2016-08-25 | 2018-03-09 | 成都飞机工业（集团）有限责任公司 | A kind of method that fastener is installed in sandwich |
| CN108068354A (en) * | 2016-11-14 | 2018-05-25 | 江西昌河航空工业有限公司 | A kind of positional punch method of composite material honeycomb interlayer part packing area |
| CN114851280A (en) * | 2022-05-27 | 2022-08-05 | 浙江微控智造有限公司 | Composite material antenna housing arc flange interface hole machining clamp and machining method |
| CN116197616A (en) * | 2023-02-17 | 2023-06-02 | 东方电气（武汉）核设备有限公司 | Nuclear reactor inner member processing method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1365660A (en) * | 1918-03-08 | 1921-01-18 | Collier Arthur | Bit and like boring-tool |
| US4352610A (en) * | 1980-07-07 | 1982-10-05 | The Boeing Company | Method and tool for generating holes in composite materials |
| EP0375526A1 (en) * | 1988-12-19 | 1990-06-27 | AEROSPATIALE Société Nationale Industrielle | Precision trepanning tool for panels of sandwiched materials |
| CN1986145A (en) * | 2006-12-22 | 2007-06-27 | 成都飞机工业（集团）有限责任公司 | Perforating process of composite carbon fiber material product |
| CN102380810A (en) * | 2011-11-18 | 2012-03-21 | 南京航空航天大学 | Drilling device |
| CN103071833A (en) * | 2013-02-06 | 2013-05-01 | 哈尔滨理工大学 | Diamond bit with brazing structure specially used for carbon fiber reinforced composite material |
-
2013
- 2013-11-04 CN CN201310536985.5A patent/CN103586500A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1365660A (en) * | 1918-03-08 | 1921-01-18 | Collier Arthur | Bit and like boring-tool |
| US4352610A (en) * | 1980-07-07 | 1982-10-05 | The Boeing Company | Method and tool for generating holes in composite materials |
| EP0375526A1 (en) * | 1988-12-19 | 1990-06-27 | AEROSPATIALE Société Nationale Industrielle | Precision trepanning tool for panels of sandwiched materials |
| CN1986145A (en) * | 2006-12-22 | 2007-06-27 | 成都飞机工业（集团）有限责任公司 | Perforating process of composite carbon fiber material product |
| CN102380810A (en) * | 2011-11-18 | 2012-03-21 | 南京航空航天大学 | Drilling device |
| CN103071833A (en) * | 2013-02-06 | 2013-05-01 | 哈尔滨理工大学 | Diamond bit with brazing structure specially used for carbon fiber reinforced composite material |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107775720A (en) * | 2016-08-25 | 2018-03-09 | 成都飞机工业（集团）有限责任公司 | A kind of method that fastener is installed in sandwich |
| CN108068354A (en) * | 2016-11-14 | 2018-05-25 | 江西昌河航空工业有限公司 | A kind of positional punch method of composite material honeycomb interlayer part packing area |
| CN107443434A (en) * | 2017-08-25 | 2017-12-08 | 陕西飞机工业（集团）有限公司 | A kind of composite method for drilling |
| CN114851280A (en) * | 2022-05-27 | 2022-08-05 | 浙江微控智造有限公司 | Composite material antenna housing arc flange interface hole machining clamp and machining method |
| CN114851280B (en) * | 2022-05-27 | 2024-04-02 | 浙江微控智造有限公司 | Composite material radome arc flange interface hole machining clamp and machining method |
| CN116197616A (en) * | 2023-02-17 | 2023-06-02 | 东方电气（武汉）核设备有限公司 | Nuclear reactor inner member processing method |
| CN116197616B (en) * | 2023-02-17 | 2025-11-18 | 东方电气（武汉）核设备有限公司 | A method for fabricating nuclear reactor internals |
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Application publication date: 20140219 |