CN114370458A - Aviation spline coupling and machining process thereof - Google Patents
Aviation spline coupling and machining process thereof Download PDFInfo
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- CN114370458A CN114370458A CN202111490123.4A CN202111490123A CN114370458A CN 114370458 A CN114370458 A CN 114370458A CN 202111490123 A CN202111490123 A CN 202111490123A CN 114370458 A CN114370458 A CN 114370458A
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- 238000003754 machining Methods 0.000 title claims description 34
- 230000008878 coupling Effects 0.000 title claims description 32
- 238000010168 coupling process Methods 0.000 title claims description 32
- 238000012545 processing Methods 0.000 claims abstract description 100
- 229910052802 copper Inorganic materials 0.000 claims abstract description 19
- 239000010949 copper Substances 0.000 claims abstract description 19
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 18
- 238000007747 plating Methods 0.000 claims abstract description 16
- 230000033001 locomotion Effects 0.000 claims abstract description 14
- 239000000463 material Substances 0.000 claims abstract description 7
- 238000012360 testing method Methods 0.000 claims abstract description 7
- 238000005516 engineering process Methods 0.000 claims abstract description 6
- 238000004140 cleaning Methods 0.000 claims abstract description 4
- 238000004806 packaging method and process Methods 0.000 claims abstract description 4
- 238000010301 surface-oxidation reaction Methods 0.000 claims abstract description 4
- 238000007514 turning Methods 0.000 claims abstract description 4
- 238000000034 method Methods 0.000 claims description 34
- 238000005859 coupling reaction Methods 0.000 claims description 30
- 230000008569 process Effects 0.000 claims description 20
- 238000005520 cutting process Methods 0.000 claims description 12
- 238000007639 printing Methods 0.000 claims description 12
- 238000005452 bending Methods 0.000 claims description 8
- XFXPMWWXUTWYJX-UHFFFAOYSA-N Cyanide Chemical compound N#[C-] XFXPMWWXUTWYJX-UHFFFAOYSA-N 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 6
- 238000007689 inspection Methods 0.000 claims description 6
- 239000011148 porous material Substances 0.000 claims description 4
- 238000001514 detection method Methods 0.000 claims description 3
- 210000002268 wool Anatomy 0.000 claims description 3
- 238000012986 modification Methods 0.000 abstract description 10
- 230000004048 modification Effects 0.000 abstract description 10
- 239000010410 layer Substances 0.000 description 15
- 230000002708 enhancing effect Effects 0.000 description 5
- 238000007333 cyanation reaction Methods 0.000 description 4
- 238000004381 surface treatment Methods 0.000 description 4
- 238000004891 communication Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000004069 differentiation Effects 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 239000002344 surface layer Substances 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000009347 mechanical transmission Effects 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D3/00—Yielding couplings, i.e. with means permitting movement between the connected parts during the drive
- F16D3/02—Yielding couplings, i.e. with means permitting movement between the connected parts during the drive adapted to specific functions
- F16D3/06—Yielding couplings, i.e. with means permitting movement between the connected parts during the drive adapted to specific functions specially adapted to allow axial displacement
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C22/00—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
- C23C22/73—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals characterised by the process
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D1/00—Couplings for rigidly connecting two coaxial shafts or other movable machine elements
- F16D1/06—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end
- F16D1/08—Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end with clamping hub; with hub and longitudinal key
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Electroplating Methods And Accessories (AREA)
Abstract
The invention discloses an aviation spline coupler which comprises a coupler body, and the processing technology comprises the following steps: processing the blank through a test material and turning for multiple times to form rough blanks with allowance removed; copper plating protection is carried out on the non-cyaniding part of the blank, and the spline part needing cyaniding is in a to-be-cyanided state in a slow wire moving mode; cyaniding the spline in a to-be-cyanided state, and grinding the non-cyanided part to form a formed part in a final state; detecting the formed part for multiple times; performing plating treatment on the surface of the detected formed part, and performing surface oxidation treatment on the surface which is not plated with copper; and cleaning and checking, and then carrying out oil seal packaging. According to the invention, according to the motion characteristics of the spline coupler, different areas are subjected to targeted modification operation according to the surface modification requirement of the spline coupler so as to achieve better surface properties.
Description
Technical Field
The invention relates to the technical field of couplings, in particular to an aviation spline coupling and a machining process thereof.
Background
The spline shaft is a mechanical transmission type and mainly used for transmitting mechanical torque, a longitudinal key groove is formed in the outer surface of the shaft, and a rotating piece sleeved on the shaft is also provided with a corresponding key groove and can keep synchronous rotation with the shaft. While rotating, some of them can slide on the shaft longitudinally, such as the gear shifting gear of the gear box.
In the process of manufacturing the spline coupler, in order to enhance the properties of the spline coupler by enhancing the hardness and the like of the spline coupler, the surface of the spline coupler is subjected to cyaniding and the like, and meanwhile, the spline coupler is subjected to copper treatment and oxidation to protect the spline coupler. However, in the prior art, the surface treatment does not have a proper sequence and a proper distribution, so the surface treatment may affect subsequent processing, for example, the processing is difficult due to the high surface hardness of parts after cyanidation.
Disclosure of Invention
The invention aims to provide an aviation spline coupler and a machining process thereof, and aims to solve the technical problems that in the prior art, the surface layer is not strong in property and subsequent machining can be influenced by surface layer treatment.
In order to solve the technical problems, the invention specifically provides the following technical scheme:
the utility model provides an aviation spline shaft coupling, includes the shaft coupling body be provided with the intercommunicating pore on the shaft coupling body, be located be provided with the different connection position in aperture on the shaft coupling body at intercommunicating pore both ends respectively all be provided with the interior keyway that is used for cup jointing the transmission shaft on the connection position, shaft coupling body surface is provided with outer keyway, and is located adjacently on the shaft coupling body position between the outer keyway all is provided with the locating hole.
Furthermore, the end faces at two ends of the coupler body are provided with cyanation layers for enhancing surface hardness, and the surfaces of the inner key groove, the outer key groove and the connecting position are provided with copper plating layers.
Further, the thickness of the cyanide layer is 0.2-0.4 mm, and the thickness of the copper plating layer is 0.05-0.1 mm.
Further, the pilot hole positions are evenly distributed around the central axis of the coupler body.
In order to solve the above technical problems, the present invention further provides the following technical solutions: a machining process of an aviation spline coupler comprises the following steps:
step 100, preliminary processing, namely, processing the blank through a sample and turning for multiple times to form rough blank with allowance removed;
200, performing pre-cyaniding protection, namely performing copper plating protection on non-cyanided parts of the wool, and enabling the spline to be subjected to cyaniding to reach a to-be-cyanided state in a slow wire moving mode;
step 300, cyaniding the spline to be cyanided, and grinding the non-cyanided part to a formed part in a final state;
step 400, detecting the formed part for multiple times;
500, performing plating treatment on the surface of the detected formed part, and performing surface oxidation treatment on the surface which is not plated with copper;
and step 600, carrying out cleaning inspection and then carrying out oil seal packaging.
Further, in step 100, a specific method of sample processing includes:
randomly selecting one blank from the plurality of blanks as a test material block, processing the test material block according to a set processing sequence and parameters, and carrying out quality inspection on the processed product; ,
and when the quality detection is qualified, curing the processing parameters of the machine tool, recording all the parameters in a process record table, verifying the parameters according to the recorded parameters, and then processing the formal part.
Further, in step 200, the specific steps of achieving the to-be-cyanided state by adopting the slow-run processing mode are as follows:
a closed primary contour line needing cyaniding is defined at the spline, wherein a secondary contour line is established for discrete points or areas with secondary processing requirements in a secondary definition mode;
different primary processing areas which are mutually communicated or not communicated are defined on the basis of the primary contour lines, processing sequences are defined for the different primary processing areas, and a unidirectional motion path is established in the primary processing areas according to a path cut by an ignition wire to carry out cutting processing of the whole area;
and different discrete secondary processing areas which are not communicated with each other are defined on the basis of the secondary contour lines, the different secondary processing areas are numbered, the different secondary processing areas are cut according to the numbering sequence, and parallel line motion paths are established in each secondary processing area according to the ignition line cutting mode for carrying out all-area cutting processing.
Further, the one-way movement path adopts a loop-shaped path from inside to outside or from inside to outside, and a path overlapping area of the cutting process is established at the bending position, and the overlapping degree of the overlapping area is determined by the bending degree.
Further, in step 300, the specific steps of grinding the non-cyanided part to a final-state formed part are as follows:
step 301, determining a central axis on a spline, vertically processing two ends of a blank based on the central axis, and calibrating anchor points of the central axis on vertical planes at the two ends of the blank;
step 302, respectively making a plurality of concentric circles at two ends of the spline based on anchor points at the two ends, wherein the radiuses of the corresponding concentric circles at the two ends are the same, so as to establish a plurality of concentric cylinders, and each concentric cylinder is provided with an impact seal;
step 303, calibrating a machining point on the side wall of the spline by taking any one of the concentric circles as a reference, connecting the machining points on the same section to form a connecting circle, and calibrating a machining sequence and a machining depth on the connecting circle;
and step 304, repeating step 303 until a complete processing printing plate is formed on the side wall of the spline.
Further, the processing printing plate comprises a single-position multi-process processing sequence, a single-process processing sequence in different positions and grinding parameters processed in each process.
Compared with the prior art, the invention has the following beneficial effects:
(1) according to the motion characteristics of the spline coupler, different regions are subjected to targeted modification operation according to the surface modification requirement, so that the surface of the spline coupler has different reinforcement attributes, the spline coupler can meet different requirements, and better surface attributes are achieved;
(2) in addition, the invention carries out differentiation treatment on the parts needing important cyaniding in the processing treatment process, thereby realizing deep cyaniding while carrying out surface treatment and achieving the purpose of enhancing the strength.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.
FIG. 1 is a schematic overall structure diagram of an embodiment of the present invention;
FIG. 2 is a schematic cross-sectional view of an embodiment of the present invention;
FIG. 3 is a schematic cross-sectional view of another embodiment of the present invention;
FIG. 4 is a schematic structural diagram of the rotational section shown in FIG. 2 according to an embodiment of the present invention;
fig. 5 is a schematic flow chart of spline coupling processing in the embodiment of the present invention.
The reference numerals in the drawings denote the following, respectively:
1-a coupling body; 2-a communicating hole; 3-a linking site; 4-inner key groove; 5-external key groove; 6-positioning holes; a 7-cyanation layer; 8-copper plating layer.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1 to 4, the invention provides an aviation spline coupler, which is characterized by comprising a coupler body 1, wherein a communication hole 2 is formed in the coupler body 1, connecting positions 3 with different apertures are respectively arranged on the coupler body 1 at two ends of the communication hole 2, inner key grooves 4 for sleeving a transmission shaft are respectively arranged on the connecting positions 3, outer key grooves 5 are arranged on the surface of the coupler body 1, positioning holes 6 are respectively arranged on the coupler body 1 between the adjacent outer key grooves 5, and the positioning holes 6 are uniformly distributed around the central axis of the coupler body 1.
In the present embodiment, the coupling body 1 itself is similar to a conventional coupling body, and different connection positions 3, key grooves and inner key grooves 4 and outer key grooves 5 are arranged on the coupling body according to different purposes so as to adapt to different transmission requirements.
In the present embodiment, in order to enhance the wear resistance and the like and the hardness of the surface thereof, and thereby extend the service life of the spline coupling, according to the requirements of the surface properties thereof:
the coupling comprises a coupling body 1 and is characterized in that the end faces at the two ends of the coupling body are respectively provided with a cyanation layer 7 for enhancing the surface hardness, wherein the thickness of the cyanation layer 7 is 0.2-0.4 mm.
An oxide layer is provided in a region other than the above-described cyanide layer 7 and copper plating layer 8 (including a transition region other than the cyanide layer, and a region 3 mm away from the cyanide layer 7 is set as the transition region).
In the present embodiment, in order to achieve both the modification of the surface properties and the non-interference between the steps, the modification of the surface properties is performed as follows. As shown in fig. 5, the invention also provides a processing technology of the aviation spline coupler, which comprises the following steps:
and step 100, primary processing, namely, processing the blank through a sample and turning for multiple times to form rough blank with allowance removed.
In step 100, a specific method of sample processing includes:
randomly selecting one blank from the plurality of blanks as a test material block, processing the test material block according to a set processing sequence and parameters, and carrying out quality inspection on the processed product; ,
and when the quality detection is qualified, curing the processing parameters of the machine tool, recording all the parameters in a process record table, verifying the parameters according to the recorded parameters, and then processing the formal part.
In the sample processing, it is necessary to adopt the same process and technique as those of the main processing, and it is also necessary to clean the sharp edges, burrs and chamfers generated by the processing at any time in the processing.
In the processing of the formal part, parameters in the blank processing process are completely consistent, and the parameters comprise clamping of the blank and the like, such as clamping in a double-top mode or clamping in an outer diameter clamping mode.
And 200, performing pre-cyaniding protection, namely performing copper plating protection on non-cyanided parts of the wool, and enabling the spline parts needing to be cyanided to reach a to-be-cyanided state in a slow wire moving or spline inserting mode.
The method for achieving the to-be-cyanided state by adopting the slow-moving wire processing mode comprises the following specific steps:
a closed primary contour line needing cyaniding is defined at the spline, wherein a secondary contour line is established for discrete points or areas with secondary processing requirements in a secondary definition mode;
different primary processing areas which are mutually communicated or not communicated are defined on the basis of the primary contour lines, processing sequences are defined for the different primary processing areas, and a unidirectional motion path is established in the primary processing areas according to a path cut by an ignition wire to carry out cutting processing of the whole area;
and different discrete secondary processing areas which are not communicated with each other are defined on the basis of the secondary contour lines, the different secondary processing areas are numbered, the different secondary processing areas are cut according to the numbering sequence, and parallel line motion paths are established in each secondary processing area according to the ignition line cutting mode for carrying out all-area cutting processing.
In the present embodiment, the slow wire feeding method is adopted to strip the copper plating layer on the surface, and the surface of the workpiece can be processed while the copper plating layer is stripped, so that a better surface is provided for the subsequent cyaniding, and the cyaniding effect is improved.
The foregoing includes two aspects of the process:
the first, primary, process, during which a unidirectional motion path is used, wherein: the unidirectional movement path adopts a zigzag path from inside to outside or from outside to inside, and a path overlapping area of the cutting process is established at the bending position, and the overlapping degree of the overlapping area is determined by the bending degree.
Since the unidirectional motion path is a zigzag path, the paths are overlapped when meeting the bending position, and deep cyanidation is needed for the bending position which is just the stress concentration point of the part, so that the surface is deeply processed by adopting the zigzag path while the surface is processed, so that deeper processing can be realized.
The second, secondary treatment, is a compensation treatment according to the need in the process, i.e. the subsequent cyanidation process is not considered in the process, and only the part needing cyanidation needs to be ground out, therefore, the continuous or discontinuous operation is carried out in the process by adopting a parallel line path mode to achieve the full-coverage treatment process.
And 300, cyaniding the spline to be cyanided, and grinding the non-cyanided part to obtain the formed part in the final state.
In the present embodiment, due to the structural features of the ratchet, the surface structure is not uniform, and the structural shape is determined corresponding to the central axis thereof. In the prior art, the workpiece is clamped and then directly machined by combining a numerical control technology, and the clamping precision of the workpiece is required to be very high, because when any small deviation occurs in the clamped position, the workpiece can be greatly deviated after being machined. This is because the machining precision is limited by the machining according to this method in actual machining because the machining of the machine tool is dependent on the position of the workpiece as long as the machining is relative to the position of the workpiece.
In the present embodiment, since the requirement for the machining accuracy of the transmission inner shaft is relatively high, it is difficult to machine the transmission inner shaft with an appropriate accuracy by the conventional relative position method. In the present invention, in order to overcome the aforementioned problems and achieve the accuracy of design, the processing thereof depends on the workpiece itself, i.e., the processing plate of the workpiece itself.
The specific steps of grinding the non-cyanided part to a molded part in a final state are as follows:
step 301, determining a central axis on a spline, vertically processing two ends of a blank based on the central axis, and calibrating anchor points of the central axis on vertical planes at the two ends of the blank;
step 302, respectively making a plurality of concentric circles at two ends of the spline based on anchor points at the two ends, wherein the radiuses of the corresponding concentric circles at the two ends are the same, so as to establish a plurality of concentric cylinders, and each concentric cylinder is provided with an impact seal;
step 303, calibrating a machining point on the side wall of the spline by taking any one of the concentric circles as a reference, connecting the machining points on the same section to form a connecting circle, and calibrating a machining sequence and a machining depth on the connecting circle;
and step 304, repeating step 303 until a complete processing printing plate is formed on the side wall of the spline.
Wherein:
the processing printing plate comprises a single-position multi-process processing sequence, a single-process processing sequence in different positions and grinding parameters processed in each process.
In the present embodiment, the specific reference points are located on the workpiece itself, and the processing sequence, the processing points and the processing amount are determined by processing the printing plate, that is, the sequence, the position and the processing amount of each grinding process are determined by the processing printing plate, and since the processing printing plate is uniquely determined relative to the workpiece, the processing accuracy can be sufficiently high as long as the accuracy of the processing printing plate is sufficiently high, and it is very easy for the existing numerical control technology to carve the processing printing plate with sufficient accuracy. Therefore, in the embodiment, the mode of processing the printing plate for the first time can overcome the existing numerical control processing technology, and can effectively improve the processing error caused by the inherent factors of mechanical processing in the prior art so as to really improve the processing precision of the product.
And step 400, detecting the formed part for multiple times.
And 500, performing plating treatment on the surface of the detected formed part, and performing surface oxidation treatment on the surface which is not plated with copper.
And step 600, carrying out cleaning inspection and then carrying out oil seal packaging.
In summary, in the present invention:
(1) according to the motion characteristics of the spline coupler, different regions are subjected to targeted modification operation according to the surface modification requirement, so that the surface of the spline coupler has different reinforcement attributes, the spline coupler can meet different requirements, and better surface attributes are achieved;
(2) in addition, the invention carries out differentiation treatment on the parts needing important cyaniding in the processing treatment process, thereby realizing deep cyaniding while carrying out surface treatment and achieving the purpose of enhancing the strength.
The above embodiments are only exemplary embodiments of the present application, and are not intended to limit the present application, and the protection scope of the present application is defined by the claims. Various modifications and equivalents may be made by those skilled in the art within the spirit and scope of the present application and such modifications and equivalents should also be considered to be within the scope of the present application.
Claims (10)
1. The utility model provides an aviation spline shaft coupling, its characterized in that, includes shaft coupling body (1) be provided with intercommunicating pore (2) on shaft coupling body (1), be located be provided with connecting position (3) that the aperture is different on shaft coupling body (1) at intercommunicating pore (2) both ends all be provided with interior keyway (4) that are used for cup jointing the transmission shaft on connecting position (3), shaft coupling body (1) surface is provided with outer keyway (5), and is in it is adjacent to lie in on shaft coupling body (1) position between outer keyway (5) all is provided with locating hole (6).
2. The aircraft spline coupling of claim 1, wherein the coupling body (1) is provided with a cyanide layer (7) on the end surface of each end, and the surfaces of the inner key groove (4) and the outer key groove (5) and the surface of the connecting position (3) are provided with copper plating layers (8).
3. The aircraft spline coupling according to claim 1, wherein the thickness of the cyanide layer (7) is 0.2-0.4 mm, and the thickness of the copper plating layer (8) is 0.05-0.1 mm.
4. An aircraft spline coupling according to claim 1, characterized in that the pilot hole sites (6) are evenly distributed around the centre axis of the coupling body (1).
5. A machining process of an aviation spline coupler according to any one of claims 1 to 4, characterized by comprising the following steps of:
step 100, preliminary processing, namely, processing the blank through a sample and turning for multiple times to form rough blank with allowance removed;
200, performing pre-cyaniding protection, namely performing copper plating protection on non-cyanided parts of the wool, and enabling the spline to be subjected to cyaniding to reach a to-be-cyanided state in a slow wire moving mode;
step 300, cyaniding the spline to be cyanided, and grinding the non-cyanided part to a formed part in a final state;
step 400, detecting the formed part for multiple times;
500, performing plating treatment on the surface of the detected formed part, and performing surface oxidation treatment on the surface which is not plated with copper;
and step 600, carrying out cleaning inspection and then carrying out oil seal packaging.
6. The machining process of the aviation spline coupler according to claim 1, wherein in the step 100, the concrete method for machining the sample comprises the following steps:
randomly selecting one blank from the plurality of blanks as a test material block, processing the test material block according to a set processing sequence and parameters, and carrying out quality inspection on the processed product; ,
and when the quality detection is qualified, curing the processing parameters of the machine tool, recording all the parameters in a process record table, verifying the parameters according to the recorded parameters, and then processing the formal part.
7. The machining process of the aviation spline coupler according to claim 1, wherein in the step 200, the specific steps of achieving the to-be-cyanided state by adopting a slow-running wire machining mode are as follows:
a closed primary contour line needing cyaniding is defined at the spline, wherein a secondary contour line is established for discrete points or areas with secondary processing requirements in a secondary definition mode;
different primary processing areas which are mutually communicated or not communicated are defined on the basis of the primary contour lines, processing sequences are defined for the different primary processing areas, and a unidirectional motion path is established in the primary processing areas according to a path cut by an ignition wire to carry out cutting processing of the whole area;
and different discrete secondary processing areas which are not communicated with each other are defined on the basis of the secondary contour lines, the different secondary processing areas are numbered, the different secondary processing areas are cut according to the numbering sequence, and parallel line motion paths are established in each secondary processing area according to the ignition line cutting mode for carrying out all-area cutting processing.
8. The process for machining an aviation spline coupling according to claim 1, wherein the one-way movement path adopts a zigzag path from inside to outside or from inside to outside, and a cutting path overlapping region is established at the bending position, and the overlapping degree of the overlapping region is determined by the bending degree.
9. The processing technology of the aviation spline coupling according to claim 1, wherein in the step 300, the specific steps of grinding the non-cyanided part to the formed part in the final state are as follows:
step 301, determining a central axis on a spline, vertically processing two ends of a blank based on the central axis, and calibrating anchor points of the central axis on vertical planes at the two ends of the blank;
step 302, respectively making a plurality of concentric circles at two ends of the spline based on anchor points at the two ends, wherein the radiuses of the corresponding concentric circles at the two ends are the same, so as to establish a plurality of concentric cylinders, and each concentric cylinder is provided with an impact seal;
step 303, calibrating a machining point on the side wall of the spline by taking any one of the concentric circles as a reference, connecting the machining points on the same section to form a connecting circle, and calibrating a machining sequence and a machining depth on the connecting circle;
and step 304, repeating step 303 until a complete processing printing plate is formed on the side wall of the spline.
10. The machining process of the aviation spline coupler according to claim 1, wherein the machining printing plate comprises a single-position multi-process machining sequence, a single-process machining sequence of different positions and grinding parameters of each process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111490123.4A CN114370458A (en) | 2021-12-08 | 2021-12-08 | Aviation spline coupling and machining process thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111490123.4A CN114370458A (en) | 2021-12-08 | 2021-12-08 | Aviation spline coupling and machining process thereof |
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| CN114370458A true CN114370458A (en) | 2022-04-19 |
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