CN114043002A - Carbon fiber composite material hole making process method - Google Patents
Carbon fiber composite material hole making process method Download PDFInfo
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- CN114043002A CN114043002A CN202111318389.0A CN202111318389A CN114043002A CN 114043002 A CN114043002 A CN 114043002A CN 202111318389 A CN202111318389 A CN 202111318389A CN 114043002 A CN114043002 A CN 114043002A
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- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 78
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 78
- 238000005553 drilling Methods 0.000 claims abstract description 68
- 238000002360 preparation method Methods 0.000 claims abstract description 16
- 238000005520 cutting process Methods 0.000 claims abstract description 15
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- 239000010936 titanium Substances 0.000 claims description 25
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 24
- 229910052719 titanium Inorganic materials 0.000 claims description 24
- 229910045601 alloy Inorganic materials 0.000 claims description 20
- 239000000956 alloy Substances 0.000 claims description 20
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- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 20
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Images
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 And Boring (AREA)
- Drilling Tools (AREA)
Abstract
The application discloses a carbon fiber composite material hole making process method, which belongs to the technical field of aviation manufacturing, and the method firstly completes 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 machining technological parameters of a hole making tool and a hole making cutter; positioning and compressing a laminated structure, wherein the laminated structure comprises a first carbon fiber composite structural member; determining a hole position; adopting a hole making tool and a hole making cutter to make a hole and countersink, using drilling lubricating oil in the hole making operation, and enabling a countersink drill to enter a 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 geometric parameters of the reamer comprise a taper angle of a main cutting edge of 45 degrees, a helical angle of the reamer of 7-12 degrees, a relief angle of the main cutting edge of 12-20 degrees, a circumferential relief angle of 20-25 degrees and a cylindrical land of 0.1-0.15 mm.
Description
Technical Field
The application belongs to the technical field of aviation manufacturing, and particularly relates to a carbon fiber composite (CCF300/BA9916-II) hole making process method.
Background
At present, a structural member of an airplane body is usually made of a carbon fiber composite material (for short, carbon fiber composite material), the carbon fiber composite material structural member is assembled on the airplane body, hole machining must be carried out on the carbon fiber composite material structural member and the airplane body, but the defects of layering, splitting, burrs and the like often occur in the hole machining process of the carbon fiber composite material structural member, and meanwhile, during machining, due to the fact that a cutter and machining parameters are unreasonably arranged, faults such as cutter edge breakage, abrasion and the like easily occur.
Disclosure of Invention
In order to solve the technical problems of layering, splitting, deburring, tool tipping and abrasion of carbon fiber composites in the hole making process in the related technology, the application provides a hole making process method for the carbon fiber composites. The technical scheme is as follows:
provided is a carbon fiber composite hole making process method, which comprises the following steps:
firstly, completing preparation work before drilling, including preparation of process auxiliary materials, preparation of a drilling tool and a drilling cutter and preparation of dust collection equipment;
determining machining technological parameters of a hole making tool and a hole making cutter;
positioning and compressing a laminated structure, the laminated structure comprising a first carbon fiber composite structural member;
determining a hole position;
adopting a hole making tool and a hole making cutter to make a hole and countersink, using drilling lubricating oil in the hole making operation, and enabling a countersink drill to enter a 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 system hole cutter is the reamer, the cutting geometry parameter of reamer includes: the taper angle of the main cutting edge is 45 degrees, the helical angle of the reamer is 7-12 degrees, the relief angle of the main cutting edge is 12-20 degrees, the circumferential relief angle is 20-25 degrees, and the cylindrical land is 0.1-0.15 mm.
Optionally, during the drilling through, 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 larger than or equal to 6mm, the rotating speed of the hole-making cutter is 6000-10000 r/min,
the single-side processing allowance is 1 mm-6 mm;
optionally, during the hole making and reaming process, 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 larger than or equal to 6mm, the rotating speed of the hole-making cutter is 500-800 r/min,
the single-side processing allowance is 0.15-0.4 mm;
optionally, during the countersinking:
when the countersinking tool is a dagger drill, the rotating speed is 800-1400 r/min,
when the dimple 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 compressing the laminated structure comprises:
the laminate structure is positioned and compacted using fasteners that do not include cadmium plated and cadmium coated process fasteners.
Optionally, the process of making the hole comprises:
supporting a first carbon fiber composite structural member by using a process base plate;
drilling through the first carbon fiber composite structural member by adopting an auger bit or a dagger bit, wherein the drill bit of the auger bit is subjected to diamond coating treatment;
and when the hole tolerance required to meet the specified requirement is met, reaming by using a hard alloy reamer.
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 an auger bit or a dagger drill according to the speed and the feeding amount specified by the machine body material;
and when the hole tolerance required to meet the specified requirement is met, reaming by using a hard alloy reamer.
Optionally, the laminated structure further includes a body located on the 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 a first carbon fiber composite structural member by using a process base plate;
drilling through the laminated structure by adopting an auger bit or a dagger drill according to the speed and the feeding amount specified by the machine body material;
and when the hole tolerance required to meet the specified requirement is met, reaming by using a hard alloy reamer.
Optionally, the laminated structure further includes a first body located at a bottom of the first carbon fiber composite structural member, a second body located at an upper portion of the first carbon fiber composite structural member, and a second carbon fiber composite structural member located at an upper portion of the second body, the first body and the second body are made of aluminum or titanium, and the drilling process includes:
drilling from the second carbon fiber composite structural member to the second machine body by adopting a twist drill;
according to the feeding amount and speed specified for the second machine body, a twist drill is adopted to drill titanium from the second machine body to the first carbon fiber composite structural part;
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 reaming by using a hard alloy reamer according to the specified feeding amount and speed of the second machine body.
The process technology for manufacturing the hole by the carbon fiber composite material realizes high-quality hole manufacturing of the carbon fiber composite material, and the successful application of the process technology enables the structural member of the carbon fiber composite material to be assembled on an airplane body in a qualified mode. The composite material structural member is applied to achieve the comprehensive effect of qualitative leap and improvement on the load, flight performance, operation performance and structural performance of the airplane.
Drawings
FIG. 1 is a flow chart of a carbon fiber composite hole making process provided by the present application;
FIG. 2 is a schematic diagram of a carbon fiber composite hole making process provided by the present application;
FIG. 3 is a schematic view of a carbon fiber composite hole provided herein;
FIG. 4 is a schematic view of a step of drilling a carbon fiber composite laminate hole (drilled from the composite surface) according to the present application;
FIG. 5 is a schematic view of a carbon fiber composite hole stack (drilled from the composite face) provided herein;
FIG. 6 is a drawing of a carbon fiber composite laminate hole making (aluminum or titanium face drilling) step provided by the present application;
FIG. 7 is a schematic illustration of a carbon fiber composite laminate via drilling (aluminum or titanium face drilling) provided herein;
FIG. 8 is a schematic diagram of a process for forming a hole (composite/Ti/composite/Al laminated structure) in a multi-layer laminated carbon fiber composite structure according to the present invention;
FIG. 9 is a schematic view of a carbon fiber composite multi-layer laminated hole (composite/titanium/composite/aluminum laminated structure) provided by the present application;
fig. 10 is a schematic diagram of a chamfer angle formed on a carbon fiber composite part according to the present application.
Detailed Description
The present application will now be described in further detail with reference to the following detailed description of illustrative embodiments thereof, which are illustrated in the accompanying drawings.
The application provides a carbon fiber composite material hole making process method, as shown in fig. 1, the method comprises the following steps:
and 110, completing preparation work before drilling, including preparation of process auxiliary materials, preparation of a drilling tool and a drilling cutter and preparation of dust collection equipment.
Wherein, the composite material surface cleaning agent (butanone), the pore-forming lubricant (cetyl alcohol and industrial cetyl alcohol), the protective paint (epoxy polyamide primer) after the pore-forming of the composite material and other articles are prepared according to the specified marks. Wherein, the tool for making the hole is a drill bit, a reamer (a reaming bit), a counter boring drill, a reamer and the like, the material of the tool for making the hole is selected from a hard alloy tool, and the surface of the tool can be processed by diamond coating; when only holes of composite materials or composite material laminated structures are machined, dagger drills are preferably selected, and hard alloy tools with diamond coatings are selected for machining holes of composite materials and metal laminated structures. The end parts of the manual hole expanding drill bit and the manual reamer are provided with guide columns, so that splitting, burrs or other forms of damage to the surface of the composite material inlet is avoided in the hole expanding and reaming process.
And step 120, determining machining technological parameters of the hole making tool and the hole making cutter.
The tool requirements are as follows: manual pneumatic drilling, portable or stationary drilling equipment, the rated rotational speed should be clearly indicated; in the process of drilling the composite material, high-power dust collection equipment (a drilling and sucking integrated tool is recommended) is arranged, so that the environment of a machining area is clean and no dust pollution is caused; all tooling, testing and measurement related tools and equipment, when used, should be in a valid calibration state for a valid pass-through period.
The requirements of the cutter are as follows:
the composite material hole-making cutter is a hard alloy cutter, and the surface of the cutter can be subjected to diamond coating treatment;
the main types of the drill bit are a common twist drill and a dagger drill (preferred). The common twist drill can be used for coping with the chisel edge, the rear angle and the top angle, so that the drill bit is ensured to have enough strength and sharpness, and the drill bit is ensured not to generate layering, splitting or other forms of damage on a composite material structural member in the drilling process. If manual hole making is carried out on the composite material structural member and the titanium alloy lamination, a drill bit with a double-ligament structure can be adopted, and the stability of the drill bit in the hole making process is ensured. Dagger drills are generally used for drilling holes in composite materials, and are not generally used for drilling holes in composite material structural members and metal laminates;
the end part of the manual reaming drill bit is provided with a guide pillar, the manual reaming drill with a smaller spiral angle is recommended, and a straight-groove reaming reamer is adopted to perform reaming processing on the composite material structural part if necessary, so that splitting, burrs or other forms of damage to the surface of the composite material inlet is avoided in the reaming process;
the end part of the manual reamer is provided with a guide post, so that splitting, burrs or other damage to the surface of the composite material inlet is avoided in the reaming process.
The reaming cutter is a reamer, and the cutting geometric parameters of the reamer comprise: the taper angle of the main cutting edge is 45 degrees, the helical angle of the reamer is 7-12 degrees, the relief angle of the main cutting edge is 12-20 degrees, the circumferential relief angle is 20-25 degrees, and the cylindrical land is 0.1-0.15 mm.
Positioning and clamping requirements: and marking, positioning holes, mounted parts or assembling fixtures are used for positioning the relative positions of the parts and the components. After the positioning of the part is finished, the part is reliably clamped at the position where the hole needs to be manufactured, and the gap is eliminated. Secondly, when the carbon fiber composite material is positioned and clamped, fasteners or process fasteners made of titanium alloy or stainless steel materials are adopted as much as possible, and cadmium-plated fasteners or cadmium-plated process fasteners are forbidden. In addition, when a process bolt, a process screw or other metal compactors are used, a gasket or a shim is added on the surface of the composite material part to prevent the surface from being damaged; finally, the positioning and pressing should avoid as much as possible the use of a washer or spacer larger than the countersunk socket under the pressing member when pressing at the countersunk socket, if necessary at the countersunk hole. If the countersunk head bolt is used for protecting the countersunk head socket, the angle of the countersunk head bolt is the same as that of the socket.
And step 140, determining hole positions.
And determining the hole positions by methods such as marking, guide holes, templates or tools and the like. The hole pitch, edge pitch and row pitch should meet the requirements of the pattern and the technology.
And 150, drilling and reaming by adopting a drilling tool and a drilling cutter, wherein drilling lubricating oil is used in the drilling operation, and the reaming drill enters the first carbon fiber composite structural member in a rotating state in the reaming operation process.
Wherein, in the process of drilling through in the drilling, the technological 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 larger than or equal to 6mm, the rotating speed of the hole-making cutter is 6000-10000 r/min,
the single-side processing allowance is 1 mm-6 mm;
in the process of hole making 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 larger than or equal to 6mm, the rotating speed of the hole-making cutter is 500-800 r/min,
the single-side processing allowance is 0.15-0.4 mm;
in the process of dimple sinking:
when the countersinking tool is a dagger drill, the rotating speed is 800-1400 r/min,
when the dimple 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 compression stack, comprising:
the laminate structure is positioned and compacted using fasteners that do not include cadmium plated and cadmium coated process fasteners.
Burrs generated after hole making are removed by the following method: the composite part was deburred or deburred with alumina sandpaper (240 grit or finer) or a special deburring tool, but care was taken: used sandpaper on composite materials should not be reused on metal, nor should used sandpaper on metal be reused on composite materials.
In a first aspect, as shown in fig. 2 and 3, the process of making the hole includes:
and 210, supporting the first carbon fiber composite structural member by using a process base plate.
As shown in fig. 3, a process mat 1 is used to support a first carbon fiber composite structural member 2.
And step 220, drilling through the first carbon fiber composite structural member by adopting an auger bit or a dagger drill, wherein the drill bit of the auger bit is subjected to diamond coating treatment.
The dagger drill (no backing plate is needed) or the special edge type twist drill is used for drilling through the carbon fiber composite material. The hard alloy drill bit can be treated by diamond coating to prolong the service life of the drill bit, and can adopt pneumatic drill and automatic feeding drill.
When the hard alloy cutter is adopted, in order to avoid splitting or layering of the outlet surface, on one hand, the feeding speed should be slowed down when the drill is nearly penetrated, on the other hand, a process base plate should be added on the outlet surface, and the process base plate does not need to be processed for a dagger drill.
If required to meet the specified hole tolerances, a cemented carbide reamer may be used to ream the holes. The exit side of the bit is supported as needed to prevent chipping and delamination. If a hand held air drill is used for reaming without back support, the material removal (in diameter) of a reaming pass is 0.1mm maximum.
If the hole-making operation space is limited and the openness is poor, a thread handle cutter (a tool matched with the thread handle cutter is an eccentric drill.)
And step 230, when the hole tolerance required to meet the requirement is met, reaming by using a hard alloy reamer.
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:
and 310, drilling through the laminated structure by adopting an auger bit or a dagger drill according to the speed and the feeding amount specified by the machine body material.
And step 320, when the hole tolerance required to meet the requirement is met, reaming by using a hard alloy reamer.
When drilling from the composite face, the structure can be drilled through with a carbide twist drill at a speed and feed rate specified for aluminum or titanium, without backing plate support. Holes are made for composite structural members and titanium alloy or aluminum alloy laminates.
If the composite material has good openness at the outlet side and is easy to be padded, the hole is preferably formed from the metal member side and pressed tightly at the drill bit outlet by using a cloth-sandwiched bakelite or the like. The interlayer is decomposed after the hole is made, and burrs are removed. If the interlayer can not be decomposed and the hole making opening is good, the hole making can be carried out by two steps, namely: the primary holes are made from the metal side in sizes 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 and the openness is poor, a threaded handle cutter can be used for machining.
If the hole tolerance is required to meet the specified requirements, a hard alloy type reamer is used for reaming to the final size, a margin of 0.2mm is reserved on one side in front of the reaming, and then reaming is carried out to the final size. Drilling oil (cetyl alcohol or industrial cetyl alcohol) must be used in the reaming operation, with the greatest possible use being made of pecking drills during the drilling process.
In a third aspect, as shown in fig. 6 and 7, the laminated structure further includes a body 3 located on an upper portion of the first carbon fiber composite structural member 2, the body is made of aluminum or titanium, and the hole making process includes:
and step 410, supporting the first carbon fiber composite structural member by using a process base plate.
And step 420, drilling through the laminated structure by adopting an auger bit or a dagger drill according to the speed and the feeding amount specified by the machine body material.
And 430, when the hole tolerance required to meet the requirement is met, reaming by using a hard alloy reamer.
The structure is drilled through with a carbide twist drill at a speed and feed rate dictated by the aluminum or titanium. Holes are made for composite structural members and titanium alloy or aluminum alloy laminates. If the composite material has good openness at the outlet side and is easy to be padded, the hole is preferably formed from the metal member side and pressed tightly at the drill bit outlet by using a cloth-sandwiched bakelite or the like. The interlayer is decomposed after the hole is made, and burrs are removed. If the interlayer can not be decomposed and the hole making opening is good, the hole making can be carried out by two steps, namely: the primary holes are made from the metal side in sizes 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 and the openness is poor, a threaded handle cutter can be used for machining.
If the hole tolerance required to meet the specified requirements is required, a hard alloy type reamer is used for reaming to the final size, a margin of 0.2mm is reserved on the single side of the hole to be reamed, and then reaming is carried out to the final size. Drilling lubricants, such as cetyl alcohol or industrial cetyl alcohol, must be used in the reaming operation, with the greatest possible use of pecking drills during drilling.
In a fourth aspect, as shown in fig. 8 and 9, the laminated structure further includes a first body 4 located at a bottom of the first carbon fiber composite structural member 2, a second body 5 located at an upper portion of the first carbon fiber composite structural member 2, and a second carbon fiber composite structural member 6 located at an upper portion 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 carbon fiber composite structural member to the second machine body by adopting a twist drill.
And 520, adopting a twist drill to drill titanium from the second machine body to the first carbon fiber composite structural member according to the specified feeding amount and speed of the second machine body.
And step 530, drilling through the first carbon fiber composite structural member and the first machine body according to the feeding amount and the speed specified for the first machine body.
And 540, reaming by using a hard alloy reamer according to the specified feeding amount and speed of the second machine body.
When making holes in a composite/titanium/composite/aluminum laminate structure, the following stepwise procedure was used:
firstly, drilling the carbon fiber composite material to a titanium piece by using a twist drill; then according to the specified feeding amount and speed for the titanium hole making, a hard alloy twist drill is used for drilling the titanium into the carbon fiber composite material; the carbon fiber composite material and aluminum were further drilled through at the feed rate and speed specified for the aluminum hole. Finally, drilling oil must be used in the drilling or reaming operation, and the pecking mode is adopted as much as possible in the drilling process, and the automatic feed drill can be preferably adopted.
Considerations in the hole making process:
the surface of the hole should be free of signs of overheating. When the pore surface of the composite material has a discolored ring (brownish black) or pungent smell of resin scorching, the surface is overheated;
when the tool vibrates, the composite material is overheated, the cutting edge of the cutter is excessively worn, the cutting edge of the cutter is broken or other abnormal cutting operation phenomena occur in the drilling process, the cutter is required to be replaced;
when the carbon fiber composite material with the honeycomb core layer is drilled or reamed, a drilling lubricant is not used;
when holes are made, the feeding speed is not too high, and the feeding speed is slowed down when the holes are drilled completely so as to prevent the outlet surfaces of the holes from being layered or split;
in the process of drilling, a brush or a cleaning cloth dipped with trichloroethane is often used for wiping the drill bit, the reamer and the reamer so as to remove the chips accumulated on the cutter.
After the carbon fiber composite material part is drilled, the edge of the carbon fiber composite material part is coated with epoxy polyamide primer protective paint.
The guide pillar of dimple for avoiding the dimple causes the damage to the hole wall, and the dimple process should be arranged and is bored, reamed after, goes on before the reaming process. When the workpiece needs to be provided with the countersunk socket, the drilling and reaming integrated cutter is preferably used for drilling. When the countersink needs to be manually drilled, the diameter of the guide post is smaller than the nominal diameter of the nail hole by less than 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 fiber on the surface of the inlet of the dimple drill from splitting, the dimple drill must enter the inlet in a rotating state; for raised-head fasteners, when chamfering is required, it is recommended to chamfer the part using a diamond-tipped countersink drill, as shown in fig. 10, where 2 is carbon fiber composite.
After the drilling is finished, contaminants such as residual lubricant, powder or swarf are not allowed to exist. For the lamination member to make holes, the material residue of one layer can not be retained on the material of the other layer, and the brush or rag can be dipped into butanone for cleaning.
If the engineering pattern is not specified, the surface quality (mainly including cracks, burrs, delamination, splitting, overheating, etc.) of the holes and the dimples is generally checked visually. And detecting holes with precision requirements in the engineering pattern by using special tools such as a hole plug gauge and the like. When the engineering pattern is specified, the hole is subjected to ultrasonic manual scanning detection according to the specification.
The application provides a carbon fiber composite material hole making technology, through the implementation of the technology, the high-quality hole making of the carbon fiber composite material is realized, and the successful application of the technology enables the structural member of the carbon fiber composite material to be assembled on an airplane body in a qualified mode. The composite material structural member is applied to achieve the comprehensive effect of qualitative leap and improvement on the load, flight performance, operation performance and structural performance of the airplane.
The foregoing merely represents embodiments of the present application, which are described in greater detail and detail, and therefore should not be construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the concept of the present application, which falls within the scope of protection of the present application.
Claims (9)
1. A carbon fiber composite material hole making process method is characterized by comprising the following steps:
firstly, completing preparation work before drilling, including preparation of process auxiliary materials, preparation of a drilling tool and a drilling cutter and preparation of dust collection equipment;
determining machining technological parameters of a hole making tool and a hole making cutter;
positioning and compressing a laminated structure, the laminated structure comprising a first carbon fiber composite structural member;
determining a hole position;
adopting a hole making tool and a hole making cutter to make a hole and countersink, using drilling lubricating oil in the hole making operation, and enabling a countersink drill to enter a 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 system hole cutter is the reamer, the cutting geometry parameter of reamer includes: the taper angle of the main cutting edge is 45 degrees, the helical angle of the reamer is 7-12 degrees, the relief angle of the main cutting edge is 12-20 degrees, the circumferential relief angle is 20-25 degrees, and the cylindrical land is 0.1-0.15 mm.
2. The method of claim 1, wherein during the drilling through, the process 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 larger than or equal to 6mm, the rotating speed of the hole-making cutter is 6000-10000 r/min,
the single-side processing allowance is 1 mm-6 mm.
3. The method of claim 1, wherein during 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 larger than or equal to 6mm, the rotating speed of the hole-making cutter is 500-800 r/min,
the single-side machining allowance is 0.15-0.4 mm.
4. The method of claim 1, wherein:
in the process of dimple sinking:
when the countersinking tool is a dagger drill, the rotating speed is 800-1400 r/min,
when the dimple 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.
5. The method of claim 1, wherein said positioning and compressing the laminated structure comprises:
the laminate structure is positioned and compacted using fasteners that do not include cadmium plated and cadmium coated process fasteners.
6. The method of claim 1, wherein the drilling process comprises:
supporting a first carbon fiber composite structural member by using a process base plate;
drilling through the first carbon fiber composite structural member by adopting an auger bit or a dagger bit, wherein the drill bit of the auger bit is subjected to diamond coating treatment;
and when the hole tolerance required to meet the specified requirement is met, reaming by using a hard alloy reamer.
7. The method of claim 1, wherein the laminated structure further comprises a body made of aluminum or titanium at a bottom of the first carbon fiber composite structural member, and the drilling comprises:
drilling through the laminated structure by adopting an auger bit or a dagger drill according to the speed and the feeding amount specified by the machine body material;
and when the hole tolerance required to meet the specified requirement is met, reaming by using a hard alloy reamer.
8. The method of claim 1, wherein the laminated structure further comprises a body on top of the first carbon fiber composite structural member, the body being made of aluminum or titanium, and the drilling comprises:
supporting a first carbon fiber composite structural member by using a process base plate;
drilling through the laminated structure by adopting an auger bit or a dagger drill according to the speed and the feeding amount specified by the machine body material;
and when the hole tolerance required to meet the specified requirement is met, reaming by using a hard alloy reamer.
9. The method of claim 1, wherein the laminated structure further comprises a first body located at a bottom of the first carbon fiber composite structural member, a second body located at an upper portion of the first carbon fiber composite structural member, and a second carbon fiber composite structural member located at an upper portion of the second body, the first body and the second body being made of aluminum or titanium, and the hole forming process comprises:
drilling from the second carbon fiber composite structural member to the second machine body by adopting a twist drill;
according to the feeding amount and speed specified for the second machine body, a twist drill is adopted to drill titanium from the second machine body to the first carbon fiber composite structural part;
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 reaming by using a hard alloy reamer according to the specified feeding amount and speed of the second machine body.
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