CN114043002B - Hole making process method for carbon fiber composite material - Google Patents
Hole making process method for carbon fiber composite material Download PDFInfo
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- CN114043002B CN114043002B CN202111318389.0A CN202111318389A CN114043002B CN 114043002 B CN114043002 B CN 114043002B CN 202111318389 A CN202111318389 A CN 202111318389A CN 114043002 B CN114043002 B CN 114043002B
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- 239000002131 composite material Substances 0.000 title claims abstract description 125
- 238000000034 method Methods 0.000 title claims abstract description 85
- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 80
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 80
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 80
- 238000005553 drilling Methods 0.000 claims abstract description 46
- 238000005520 cutting process Methods 0.000 claims abstract description 17
- 238000012545 processing Methods 0.000 claims abstract description 16
- 239000000463 material Substances 0.000 claims abstract description 14
- 238000004140 cleaning Methods 0.000 claims abstract description 6
- 239000000428 dust Substances 0.000 claims abstract description 6
- 239000010687 lubricating oil Substances 0.000 claims abstract description 6
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 25
- 239000010936 titanium Substances 0.000 claims description 25
- 229910052719 titanium Inorganic materials 0.000 claims description 25
- 229910052782 aluminium Inorganic materials 0.000 claims description 21
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 21
- 229910045601 alloy Inorganic materials 0.000 claims description 16
- 239000000956 alloy Substances 0.000 claims description 16
- BXWNKGSJHAJOGX-UHFFFAOYSA-N hexadecan-1-ol Chemical compound CCCCCCCCCCCCCCCCO BXWNKGSJHAJOGX-UHFFFAOYSA-N 0.000 claims description 14
- 238000002360 preparation method Methods 0.000 claims description 12
- 229910052751 metal Inorganic materials 0.000 claims description 10
- 239000002184 metal Substances 0.000 claims description 10
- 229910003460 diamond Inorganic materials 0.000 claims description 9
- 239000010432 diamond Substances 0.000 claims description 9
- 229910052793 cadmium Inorganic materials 0.000 claims description 8
- BDOSMKKIYDKNTQ-UHFFFAOYSA-N cadmium atom Chemical compound [Cd] BDOSMKKIYDKNTQ-UHFFFAOYSA-N 0.000 claims description 8
- 229960000541 cetyl alcohol Drugs 0.000 claims description 8
- 239000011248 coating agent Substances 0.000 claims description 8
- 238000000576 coating method Methods 0.000 claims description 8
- 238000003754 machining Methods 0.000 claims description 6
- 230000001105 regulatory effect Effects 0.000 claims description 5
- 239000004593 Epoxy Substances 0.000 claims description 3
- 239000004952 Polyamide Substances 0.000 claims description 3
- 229920002647 polyamide Polymers 0.000 claims description 3
- 230000001681 protective effect Effects 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 239000011229 interlayer Substances 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 5
- ZWEHNKRNPOVVGH-UHFFFAOYSA-N 2-Butanone Chemical compound CCC(C)=O ZWEHNKRNPOVVGH-UHFFFAOYSA-N 0.000 description 4
- 229910001069 Ti alloy Inorganic materials 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 239000010410 layer Substances 0.000 description 4
- 238000005299 abrasion Methods 0.000 description 3
- 239000000314 lubricant Substances 0.000 description 3
- 238000013021 overheating Methods 0.000 description 3
- 238000003825 pressing Methods 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 229920001342 Bakelite® Polymers 0.000 description 2
- 239000002519 antifouling agent Substances 0.000 description 2
- 239000004637 bakelite Substances 0.000 description 2
- 230000006378 damage Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000007747 plating Methods 0.000 description 2
- UOCLXMDMGBRAIB-UHFFFAOYSA-N 1,1,1-trichloroethane Chemical compound CC(Cl)(Cl)Cl UOCLXMDMGBRAIB-UHFFFAOYSA-N 0.000 description 1
- 102100040428 Chitobiosyldiphosphodolichol beta-mannosyltransferase Human genes 0.000 description 1
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 239000012459 cleaning agent Substances 0.000 description 1
- 239000000356 contaminant Substances 0.000 description 1
- 239000012792 core layer Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000032798 delamination Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000013467 fragmentation Methods 0.000 description 1
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- 239000003921 oil Substances 0.000 description 1
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
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- 229920005989 resin Polymers 0.000 description 1
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- 239000010935 stainless steel Substances 0.000 description 1
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- 238000012360 testing method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23D—PLANING; SLOTTING; SHEARING; BROACHING; SAWING; FILING; SCRAPING; LIKE OPERATIONS FOR WORKING METAL BY REMOVING MATERIAL, NOT OTHERWISE PROVIDED FOR
- B23D75/00—Reaming machines or reaming devices
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Drilling Tools (AREA)
- Drilling And Boring (AREA)
Abstract
The application discloses a carbon fiber composite material hole making process method, which belongs to the technical field of aviation manufacturing, and comprises the steps of preparing process auxiliary materials, preparing a hole making tool and a hole making cutter, and preparing dust collection equipment; determining processing technological parameters of a hole making tool and a hole making cutter; positioning and compacting a laminated structure, wherein the laminated structure comprises a first carbon fiber composite structural member; determining a hole site; hole making is carried out by adopting a hole making tool and a hole making cutter, and a drilling lubricating oil is used in the hole making operation, and a countersink drill enters the first carbon fiber composite structural member in a rotating state in the countersink operation process; cleaning the surface of the hole and checking the quality of the hole; the hole making cutter is a reamer, and the cutting geometrical parameters of the reamer comprise a main cutting edge taper angle of 45 degrees, a reamer helix angle of 7 degrees to 12 degrees, a main cutting edge relief angle of 12 degrees to 20 degrees, a circumference relief angle of 20 degrees to 25 degrees and a cylindrical cutting edge margin of 0.1mm to 0.15mm.
Description
Technical Field
The application belongs to the technical field of aviation manufacturing, and particularly relates to a hole-making process method for a carbon fiber composite material (CCF 300/BA 9916-II).
Background
At present, a structural member of an aircraft body is often made of a carbon fiber composite material (carbon fiber composite material for short), and the carbon fiber composite material structural member is assembled on the aircraft body, so that hole forming processing is required to be carried out on the carbon fiber composite material structural member and the aircraft body, but defects such as layering, splitting, burrs and the like often occur in the hole forming process of the carbon fiber composite material structural member, and meanwhile, during processing, faults such as cutter tipping, abrasion and the like are easy to occur due to unreasonable cutter and processing parameter setting.
Disclosure of Invention
In order to solve the technical problems of layering, splitting, burr and tipping and abrasion of a processing cutter in the process of preparing the carbon fiber composite material in the related art, the application provides a process method for preparing the carbon fiber composite material. The technical scheme is as follows:
the method for preparing the hole of the carbon fiber composite material comprises the following steps:
firstly, finishing preparation work before hole making, including preparation of process auxiliary materials, preparation of a hole making tool and a hole making cutter and preparation of dust collection equipment;
determining processing technological parameters of a hole making tool and a hole making cutter;
positioning and compacting a laminated structure, wherein the laminated structure comprises a first carbon fiber composite structural member;
determining a hole site;
hole making is carried out by adopting a hole making tool and a hole making cutter, and a drilling lubricating oil is used in the hole making operation, and a countersink drill enters the first carbon fiber composite structural member in a rotating state in the countersink operation process;
cleaning the surface of the hole and checking the quality of the hole;
wherein, the hole making cutter is a reamer, the cutting geometrical parameters of reamer include: the angle of the main cutting edge taper is 45 degrees, the angle of the reamer helix is 7 degrees to 12 degrees, the angle of the main cutting edge relief is 12 degrees to 20 degrees, the angle of the circumference relief is 20 degrees to 25 degrees, and the cylindrical cutting edge margin is 0.1mm to 0.15mm.
Optionally, during the drilling process, the process parameters include:
when the aperture is less than or equal to 3mm, the rotating speed of the hole making cutter is 16000-20000 r/min,
when the aperture is 3 mm-6 mm, the rotating speed of the hole making cutter is 10000-16000 r/min,
when the aperture is more than or equal to 6mm, the rotating speed of the hole making cutter is 6000-10000 r/min,
the unilateral machining allowance is 1 mm-6 mm;
optionally, during the process of making the hole and reaming, the process parameters include:
when the aperture is less than or equal to 3mm, the rotating speed of the hole making cutter is 1800-2500 r/min,
when the aperture is 3 mm-6 mm, the rotating speed of the hole making cutter is 800-1800 r/min,
when the aperture is more than or equal to 6mm, the rotating speed of the hole making cutter is 500-800 r/min,
the unilateral machining allowance is 0.15-0.4 mm;
optionally, during countersinking:
when the countersink cutter is a dagger drill, the rotating speed is 800-1400 r/min,
when the countersink cutter is a twist drill, the rotating speed is 500-800 r/min,
when the cutter is a dagger drill or a twist drill, the feeding amount is 0.01-0.06 mm/r,
when the machine body is made of aluminum, the rotating speed of the cutter is 1500-3500 r/min;
when the machine body is made of titanium, the rotating speed of the cutter is 500-1800 r/min.
Optionally, the positioning and compacting the laminate structure comprises:
the laminate structure is positioned and compacted using fasteners that do not include cadmium and cadmium coated process fasteners.
Optionally, the hole making process includes:
supporting the first carbon fiber composite structural member by adopting a process backing plate;
drilling through the first carbon fiber composite structural member by adopting a twist drill bit or a dagger drill, wherein the drill bit of the twist drill bit is subjected to diamond coating treatment;
cemented carbide reamer reaming was used when required to meet the prescribed Kong Rongcha.
Optionally, the laminated structure further includes a body located at the bottom of the first carbon fiber composite structural member, the body is made of aluminum or titanium, and the hole making process includes:
drilling through the laminated structure by adopting a twist drill bit or a dagger according to the speed and the feeding amount specified by the machine body material;
cemented carbide reamer reaming was used when required to meet the prescribed Kong Rongcha.
Optionally, the laminated structure further includes a body located at an upper portion of the first carbon fiber composite structural member, the body is made of aluminum or titanium, and the hole making process includes:
supporting the first carbon fiber composite structural member by adopting a process backing plate;
drilling through the laminated structure by adopting a twist drill bit or a dagger according to the speed and the feeding amount specified by the machine body material;
cemented carbide reamer reaming was used when required to meet the prescribed Kong Rongcha.
Optionally, the laminated structure further includes a first body located at the bottom of the first carbon fiber composite structural member, a second body located at the upper part of the first carbon fiber composite structural member, and a second carbon fiber composite structural member located at the upper part of the second body, where the first body and the second body are made of aluminum or titanium, and the hole making process includes:
drilling from the second carbon fiber composite structural member to the second machine body by using a twist drill;
according to the specified feeding amount and speed of the second machine body, a twist drill is adopted to drill titanium from the second machine body to the first carbon fiber composite structural member;
drilling through the first carbon fiber composite structural member and the first machine body according to the feeding amount and the feeding speed which are regulated for the first machine body;
and reaming by adopting a hard alloy reamer according to the specified feeding amount and speed of the second machine body.
The technology for making holes of the carbon fiber composite material realizes high-quality hole making of the carbon fiber composite material, and the successful application of the technology enables the structural member of the carbon fiber composite material to be assembled on an aircraft body in a one-time qualified manner. The composite structural member is applied to achieve the comprehensive effects of quality leaping and improvement of airplane loading, flight performance, operation performance and structural performance.
Drawings
FIG. 1 is a flow chart of a method for making holes in a carbon fiber composite material;
FIG. 2 is a step chart of hole forming of a carbon fiber composite provided by the application;
FIG. 3 is a schematic drawing of a carbon fiber composite hole;
FIG. 4 is a step diagram of a carbon fiber composite laminate hole making (drilling from the composite face) provided herein;
FIG. 5 is a schematic illustration of a carbon fiber composite hole-making laminate hole-making (drilling into from the composite face) provided herein;
FIG. 6 is a step diagram of hole making (aluminum or titanium face drilling) of a carbon fiber composite laminate provided by the present application;
FIG. 7 is a schematic illustration of a carbon fiber composite laminate hole (aluminum or titanium face drilled) provided herein;
FIG. 8 is a step chart of a multi-layer laminated hole forming (composite/titanium/composite/aluminum laminated structure) of a carbon fiber composite provided in the present application;
FIG. 9 is a schematic diagram of a multi-layer laminated hole forming (composite/titanium/composite/aluminum laminate structure) of a carbon fiber composite provided in the present application;
fig. 10 is a schematic diagram of chamfering a carbon fiber composite part provided in the present application.
Detailed Description
The present application is described in further detail below with reference to the following detailed description of the invention and the accompanying drawings.
The application provides a carbon fiber composite material hole making process method, as shown in fig. 1, which comprises the following steps:
step 110, preparation work before hole making is finished firstly, including preparation of process auxiliary materials, preparation of hole making tools and hole making cutters and preparation of dust collection equipment.
Wherein, the composite material surface cleaning agent (butanone), the pore-forming lubricant (cetyl alcohol, industrial cetyl alcohol) and the protective paint (epoxy polyamide primer) after the composite material pore-forming are prepared according to the specified brands. The cutter for hole making is a hard alloy cutter with materials selected from a drill bit, a reamer, a countersink drill, a reamer and the like, and the surface of the cutter can be subjected to diamond coating treatment; when only holes of the composite material or the composite material laminated structure are processed, a dagger drill is preferably selected, and a hard alloy diamond coated cutter is selected for processing the holes of the composite material and the metal laminated structure. The end parts of the manual reaming bit and the manual reamer are provided with guide posts, so that the surface of the composite material inlet is not cracked, burred or damaged in other forms in the reaming and reaming processes.
Step 120, determining processing technological parameters of the hole making tool and the hole making cutter.
The tool requirements are as follows: manual air drills, portable or stationary drilling equipment, the rated rotational speed should be clearly indicated; in the process of hole making of the composite material, high-power dust collection equipment (recommended drilling and sucking integrated tools) is required to be equipped, so that the environment of a processing area is clean, and dust pollution is avoided; all tooling, test and measurement related tools and equipment should be in an effective calibration state during an effective qualification period when in use.
The cutter requires:
the composite material hole making cutter is a hard alloy cutter which is required to be selected, and the surface of the cutter can be subjected to diamond coating treatment;
the main type of drill bit is common twist drill and dagger drill (preferential). Common twist drills should be sharpened to chisel edge, relief angle, apex angle, ensure that the drill bit possesses sufficient intensity and sharpness, guarantee that the drill bit does not produce layering, split or other forms of destruction at the composite material structure in drilling process. If the composite structural member and the titanium alloy laminate are manually made into holes, a drill bit with a double-ligament structure can be adopted, so that the stability of the drill bit in the hole making process is ensured. Dagger drills are generally used for making holes of composite materials, and are not generally used for making holes of composite material structural members and metal laminates;
the end part of the manual reaming bit is provided with a guide post, a manual reamer with a smaller spiral angle is recommended to be adopted, and if necessary, a straight flute reamer is adopted to perform reaming processing on the composite structural member, so that the surface of the composite inlet is not broken by splitting, burrs or other forms in the reaming process;
the end of the manual reamer is provided with a guide post, so that the surface of the composite material inlet is not cracked, burred or damaged in other forms in the reaming process.
The reaming cutter is a reamer, and the cutting geometrical parameters of the reamer comprise: the angle of the main cutting edge taper is 45 degrees, the angle of the reamer helix is 7 degrees to 12 degrees, the angle of the main cutting edge relief is 12 degrees to 20 degrees, the angle of the circumference relief is 20 degrees to 25 degrees, and the cylindrical cutting edge margin is 0.1mm to 0.15mm.
Step 130, positioning and compacting a laminate structure, the laminate structure comprising a first carbon fiber composite structural member.
Positioning and clamping requirements: the relative positions of the components and assemblies are positioned according to scribing lines, positioning holes, installed parts or assembly fixtures. After the positioning of the parts is finished, the parts are reliably clamped at the positions where the holes are required to be made, and gaps are eliminated. Secondly, when the carbon fiber composite material is positioned and clamped, a fastener or a process fastener made of titanium alloy or stainless steel material is adopted as much as possible, and a cadmium plating fastener or a cadmium plating process fastener is forbidden to be adopted. In addition, when using the process bolt, the process screw or other metal compactors, a gasket or a gasket is added on the surface of the composite material part to prevent the surface from being damaged; finally, the positioning and pressing should be as free as possible from the use of washers or shims larger than the countersink under the pressing element, if pressing is to be performed at the countersink. If countersunk bolts are used to protect the countersunk holes, the angles of the countersunk holes are the same as the angles of the holes.
And 140, determining the hole site.
And determining the hole site according to methods such as scribing, guide holes, templates or tools. The hole spacing, the edge spacing and the row spacing meet the pattern and technical requirements.
And 150, hole making is carried out by adopting a hole making tool and a hole making cutter, and a hole is reamed, drilling lubricating oil is used in the hole making operation, and a hole is reamed in a rotating state in the hole reaming operation process into the first carbon fiber composite structural member.
Wherein, in the process of drilling, the technological parameters comprise:
when the aperture is less than or equal to 3mm, the rotating speed of the hole making cutter is 16000-20000 r/min,
when the aperture is 3 mm-6 mm, the rotating speed of the hole making cutter is 10000-16000 r/min,
when the aperture is more than or equal to 6mm, the rotating speed of the hole making cutter is 6000-10000 r/min,
the unilateral machining allowance is 1 mm-6 mm;
in the process of drilling and reaming, the technological parameters comprise:
when the aperture is less than or equal to 3mm, the rotating speed of the hole making cutter is 1800-2500 r/min,
when the aperture is 3 mm-6 mm, the rotating speed of the hole making cutter is 800-1800 r/min,
when the aperture is more than or equal to 6mm, the rotating speed of the hole making cutter is 500-800 r/min,
the unilateral machining allowance is 0.15-0.4 mm;
during the countersinking process:
when the countersink cutter is a dagger drill, the rotating speed is 800-1400 r/min,
when the countersink cutter is a twist drill, the rotating speed is 500-800 r/min,
when the cutter is a dagger drill or a twist drill, the feeding amount is 0.01-0.06 mm/r,
when the machine body is made of aluminum, the rotating speed of the cutter is 1500-3500 r/min;
when the machine body is made of titanium, the rotating speed of the cutter is 500-1800 r/min.
The positioning and compacting laminate structure includes:
the laminate structure is positioned and compacted using fasteners that do not include cadmium and cadmium coated process fasteners.
The burrs generated after the hole is made are removed according to the following method: the composite parts are sanded or deburred with aluminum oxide sandpaper (240 grit or finer) or a special deburring tool, but care is taken: the used sandpaper on the composite should not be reused on the metal nor should the used sandpaper on the metal be reused on the composite.
In a first aspect, as shown in fig. 2 and 3, the hole making process includes:
step 210, supporting the first carbon fiber composite structural member by adopting a process backing plate.
As shown in fig. 3, a first carbon fiber composite structural member 2 is supported using a process mat 1.
And 220, drilling through the first carbon fiber composite structural member by adopting a twist drill bit or a dagger, wherein the drill bit of the twist drill bit is subjected to diamond coating treatment.
The carbon fiber composite material is drilled through by using a dagger drill (a backing plate can be omitted) or a twist drill bit with special blade treatment. The hard alloy drill bit can be subjected to diamond coating treatment so as to prolong the service life of the drill bit, and an air drill and an automatic feeding drill can be adopted.
When the hard alloy cutter is adopted, in order to avoid splitting or layering of the outlet face, on one hand, the feeding speed should be slowed down when approaching to penetration of the drill, on the other hand, the process backing plate should be processed on the outlet face, and the dagger drill does not need to process the process backing plate.
If required to meet the specified hole tolerances, a carbide reamer may be used to ream the holes. The drill bit exit side is supported as necessary to prevent chipping and delamination. If a hand held air drill is used to ream without back support, the amount of material removed (in diameter) for one reaming is at most 0.1mm.
If the operation space for hole making is limited, a screw shank cutter (the tool matched with the screw shank cutter is an eccentric drill) can be adopted when the openness is poor
And 230, reaming by using a hard alloy reamer when the requirement meets the regulated Kong Rongcha.
In a second aspect, as shown in fig. 4 and 5, the laminated structure further includes a body 3 located at the bottom of the first carbon fiber composite structural member 2, the body is made of aluminum or titanium, and the hole making process includes:
step 310, drilling through the laminated structure by using a twist drill or a dagger drill according to the speed and the feeding amount specified by the machine body material.
And 320, reaming by adopting a hard alloy reamer when the requirements meet the regulated Kong Rongcha.
When drilling from the composite face, the structure can be drilled through with a cemented carbide twist drill at a rate and feed rate specified by the aluminum or titanium without the support of the shim plate. Holes are made for the composite structural member and the titanium alloy or aluminum alloy laminate.
If the opening of the outlet side of the composite material is good and the composite material is easy to be padded, the hole is preferably made from one side of the metal piece, and the hole is propped up at the outlet of the drill bit by using the cloth-covered bakelite and the like. After the interlayer is perforated, the interlayer should be separated and the burrs removed. If the interlayer cannot be decomposed and the hole making openness is good, the hole making can be performed in two steps, namely: the primary holes are made from the metal side in a size smaller than 1.0mm to 1.5mm in diameter, and then expanded from the composite side to the final size. If the hole making operation space is limited, when the openness is poor, a thread handle cutter can be adopted for processing.
If the required size meets the prescribed Kong Rongcha, reaming to the final size by using a hard alloy reamer, and then reaming to the final size after a margin of 0.2mm is reserved on the single side before reaming. Drilling lubricating oil (cetyl alcohol or industrial cetyl alcohol) must be used in the reaming operation, and the pecking mode is adopted as much as possible in the drilling process.
In a third aspect, as shown in fig. 6 and 7, the laminated structure further includes a body 3 located at an upper portion of the first carbon fiber composite structural member 2, the body is made of aluminum or titanium, and the hole forming process includes:
step 410, supporting the first carbon fiber composite structural member by using a process backing plate.
Step 420, drilling through the laminated structure by using a twist drill or a dagger drill according to the speed and the feeding amount specified by the machine body material.
And 430, reaming by using a hard alloy reamer when the requirement meets the regulated Kong Rongcha.
The structure is drilled through with a cemented carbide twist drill at a rate and feed rate specified by aluminum or titanium. Holes are made for the composite structural member and the titanium alloy or aluminum alloy laminate. If the opening of the outlet side of the composite material is good and the composite material is easy to be padded, the hole is preferably made from one side of the metal piece, and the hole is propped up at the outlet of the drill bit by using the cloth-covered bakelite and the like. After the interlayer is perforated, the interlayer should be separated and the burrs removed. If the interlayer cannot be decomposed and the hole making openness is good, the hole making can be performed in two steps, namely: the primary holes are made from the metal side in a size smaller than 1.0mm to 1.5mm in diameter, and then expanded from the composite side to the final size. If the hole making operation space is limited, when the openness is poor, a thread handle cutter can be adopted for processing.
If the required size meets the prescribed Kong Rongcha, reaming to the final size by using a hard alloy reamer, leaving a margin of 0.2mm on one side to be reamed, and then reaming to the final size. Drilling lubricating oils such as cetyl alcohol or industrial cetyl alcohol must be used in the reaming operation, and pecking is used as much as possible during the drilling process.
In a fourth aspect, as shown in fig. 8 and 9, the laminated structure further includes a first body 4 located at the bottom of the first carbon fiber composite structural member 2, a second body 5 located at the upper part of the first carbon fiber composite structural member 2, and a second carbon fiber composite structural member 6 located at the upper part of the second body 5, the first body and the second body are made of aluminum or titanium, and the hole making process includes:
and 510, drilling the second body from the second carbon fiber composite structural member by using a twist drill.
And step 520, adopting a twist drill bit to drill titanium from the second machine body to the first carbon fiber composite structural member according to the feeding amount and the feeding speed specified for the second machine body.
And 530, drilling through the first carbon fiber composite structural member and the first machine body according to the feeding amount and the feeding speed specified for the first machine body.
And 540, reaming by adopting a hard alloy reamer according to the feeding amount and the feeding speed specified for the second machine body.
When holes are made in a composite/titanium/composite/aluminum laminate component, the following step procedure is used:
firstly, drilling the carbon fiber composite material to a titanium piece by using a twist drill; then drilling titanium to the carbon fiber composite material by using a hard alloy twist drill according to the feeding amount and the feeding speed specified for titanium hole making; the carbon fiber composite material and aluminum were further drilled through at a feed rate and speed specified for the aluminum holes. Finally, drilling oil must be used in the drilling or reaming operation, and an automatic feed drill may be used preferentially in the manner of pecking as much as possible during the drilling process.
Notes in the hole making process:
the perforated surface should have no sign of overheating. When the surface of the orifice of the composite material has a color-changing ring (brownish black) or has a resin burnt pungent smell, the surface is overheated;
when tool chatter, overheating of composite materials, excessive abrasion of a cutter blade, fragmentation of the cutter blade or other abnormal cutting operation phenomena occur in the drilling process, the cutter should be replaced;
drilling or reaming the carbon fiber composite material with the honeycomb core layer without using drilling lubricant;
when the hole is made, the feeding speed is not too fast, and when the hole is drilled through quickly, the feeding speed is reduced so as to avoid layering or splitting of the outlet surface of the hole;
in the process of making holes, a brush or a rag dipped with trichloroethane is often used for wiping a drill bit, a reamer and a reamer to remove chips accumulated on a cutter.
After the carbon fiber composite material part is drilled, the edge should be coated with epoxy polyamide primer protective paint immediately.
The reaming process is carried out after drilling and reaming and before reaming in order to avoid damage to the hole wall caused by the guide post of the reaming. When the workpiece needs to be countersunk, the drilling priority is to use a drilling and countersinking integrated tool. When manual countersinking is needed, the diameter of the guide post is smaller than the nominal diameter of the nail hole by within 0.05mm so as to ensure the coaxiality of the hole and the countersink and prevent the generation of vibration marks. In order to prevent the surface fibers at the inlet of the countersink drill from being split, the countersink drill must enter the hole in a rotating state; for nose fasteners, when chamfering is required, it is recommended to chamfer the part using a diamond-tipped countersink, as shown in fig. 10, where 2 is a carbon fiber composite.
Step 160, cleaning the hole making surface and checking the hole making quality.
After the completion of the hole making, no contaminants such as residual lubricant, powder or chips are allowed. For laminate member perforation, the material residue of one layer cannot be retained on the other layer, and the brush or wipe can be used to dip the butanone for cleaning.
If the engineering pattern is not specified, the surface quality of the hole and the countersink (mainly comprising cracks, burrs, layering, splitting, overheating and the like) is checked visually. And detecting holes with precision requirements in the engineering patterns by adopting special tools such as a hole plug gauge and the like. When the engineering pattern is specified, the ultrasonic manual scanning detection is carried out on the hole according to the specification.
According to the technology for making the holes of the carbon fiber composite material, high-quality hole making of the carbon fiber composite material is achieved through implementation of the technology, and successful application of the technology enables structural members of the carbon fiber composite material to be assembled on an aircraft body in a one-time qualified mode. The composite structural member is applied to achieve the comprehensive effects of quality leaping and improvement of airplane loading, flight performance, operation performance and structural performance.
The foregoing has outlined only the embodiments of the present application, which have been described in some detail and are not to be construed as limiting the scope of the invention. It should be noted that it would be apparent to those skilled in the art that various modifications and improvements could be made without departing from the spirit of the present application, which would be within the scope of the present application.
Claims (6)
1. A process for making holes from carbon fiber composite materials, which is characterized by comprising the following steps:
firstly, preparation work before hole making is finished, including preparation of process auxiliary materials, preparation of hole making tools and hole making cutters and preparation of dust collection equipment: preparing composite material surface cleaning agent-butanone, pore-forming lubricant-cetyl alcohol and industrial cetyl alcohol, and protective paint-epoxy polyamide primer after composite material pore-forming according to a specified mark, wherein a pore-forming cutter comprises a drill bit, a reamer, a countersink drill and a reamer; selecting a hard alloy cutter as a hole making cutter, and carrying out diamond coating treatment on the surface of the cutter; when only processing holes of the composite material or the composite material laminated structure, a dagger drill is selected; and for the hole processing of the composite material and metal laminated structure, a hard alloy cutter with a diamond coating is selected for processing;
determining processing technological parameters of a hole making tool and a hole making cutter;
positioning and compacting a laminated structure, wherein the laminated structure comprises a first carbon fiber composite structural member;
determining a hole site;
hole making is carried out by adopting a hole making tool and a hole making cutter, and a drilling lubricating oil is used in the hole making operation, and a countersink drill enters the first carbon fiber composite structural member in a rotating state in the countersink operation process;
cleaning the surface of the hole and checking the quality of the hole;
wherein, the hole making cutter is a reamer, the cutting geometrical parameters of reamer include: the angle of the main cutting edge taper is 45 degrees, the angle of the reamer helix is 7-12 degrees, the angle of the main cutting edge relief is 12-20 degrees, the angle of the circumference relief is 20-25 degrees, and the cylindrical cutting edge margin is 0.1-0.15 mm;
in the process of drilling, the technological parameters comprise:
when the aperture is less than or equal to 3mm, the rotating speed of the hole making cutter is 16000-20000 r/min,
when the aperture is 3 mm-6 mm, the rotating speed of the hole making cutter is 10000-16000 r/min,
when the aperture is more than or equal to 6mm, the rotating speed of the hole making cutter is 6000-10000 r/min,
the unilateral machining allowance is 1 mm-6 mm;
in the process of drilling and reaming, the technological parameters comprise:
when the aperture is less than or equal to 3mm, the rotating speed of the hole making cutter is 1800-2500 r/min,
when the aperture is 3 mm-6 mm, the rotating speed of the hole making cutter is 800-1800 r/min,
when the aperture is more than or equal to 6mm, the rotating speed of the hole making cutter is 500-800 r/min,
the unilateral machining allowance is 0.15-0.4 mm;
during the countersinking process:
when the countersink cutter is a dagger drill, the rotating speed is 800-1400 r/min,
when the countersink cutter is a twist drill, the rotating speed is 500-800 r/min,
when the cutter is a dagger drill or a twist drill, the feeding amount is 0.01-0.06 mm/r,
when the machine body is made of aluminum, the rotating speed of the cutter is 1500-3500 r/min;
when the machine body is made of titanium, the rotating speed of the cutter is 500-1800 r/min.
2. The method of claim 1, wherein positioning and compacting the laminate structure comprises:
the laminate structure is positioned and compacted using fasteners that do not include cadmium and cadmium coated process fasteners.
3. The method of claim 1, wherein the process of making holes comprises:
supporting the first carbon fiber composite structural member by adopting a process backing plate;
drilling through the first carbon fiber composite structural member by adopting a twist drill bit or a dagger drill, wherein the drill bit of the twist drill bit is subjected to diamond coating treatment;
cemented carbide reamer reaming was used when required to meet the prescribed Kong Rongcha.
4. The method of claim 1, wherein the laminate structure further comprises a body at the bottom of the first carbon fiber composite structural member, the body being made of aluminum or titanium, the hole making process comprising:
drilling through the laminated structure by adopting a twist drill bit or a dagger according to the speed and the feeding amount specified by the machine body material;
cemented carbide reamer reaming was used when required to meet the prescribed Kong Rongcha.
5. The method of claim 1, wherein the laminate structure further comprises a body on top of the first carbon fiber composite structural member, the body being made of aluminum or titanium, the hole forming process comprising:
supporting the first carbon fiber composite structural member by adopting a process backing plate;
drilling through the laminated structure by adopting a twist drill bit or a dagger according to the speed and the feeding amount specified by the machine body material;
cemented carbide reamer reaming was used when required to meet the prescribed Kong Rongcha.
6. The method of claim 1, wherein the laminated structure further comprises a first body at a bottom of the first carbon fiber composite structure, a second body at an upper portion of the first carbon fiber composite structure, and a second carbon fiber composite structure at an upper portion of the second body, the first body and the second body being made of aluminum or titanium, the hole making process comprising:
drilling from the second carbon fiber composite structural member to the second machine body by using a twist drill;
according to the specified feeding amount and speed of the second machine body, a twist drill is adopted to drill titanium from the second machine body to the first carbon fiber composite structural member;
drilling through the first carbon fiber composite structural member and the first machine body according to the feeding amount and the feeding speed which are regulated for the first machine body;
and reaming by adopting a hard alloy reamer according to the specified feeding amount and speed of the second machine body.
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