CN112355576B - Machining method for high-precision wing-shaped elastic shaft part - Google Patents
Machining method for high-precision wing-shaped elastic shaft part Download PDFInfo
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- CN112355576B CN112355576B CN202011108126.2A CN202011108126A CN112355576B CN 112355576 B CN112355576 B CN 112355576B CN 202011108126 A CN202011108126 A CN 202011108126A CN 112355576 B CN112355576 B CN 112355576B
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Abstract
The invention provides a method for processing a high-precision wing-shaped elastic shaft part, which comprises the following steps: splitting the target airfoil part into welding single parts according to the part structure; machining each welded singlet; assembling and welding single pieces to form a missile wing assembly, and vibrating to remove stress; taking two missile wing assemblies, and simultaneously clamping the two missile wing assemblies by adopting an auxiliary processing device, wherein the two missile wing assemblies and the auxiliary processing device form a revolving body structure; and (5) continuously machining, and removing the auxiliary machining device until the auxiliary machining device becomes the target airfoil part. The invention utilizes the auxiliary processing device to realize that the space virtual point of the central position of the missile wing is changed into the actually existing central axis, so that the circular arc of the missile wing forms a symmetrical measurable circle, the in-situ detection is completed, and the purpose of real-time monitoring is achieved; meanwhile, the design reference, the process reference and the detection reference are unified, positioning and detection errors are avoided in machining and detection, symmetrical machining of the missile wing is achieved, and the problem of dynamic balance in the grinding process is solved.
Description
Technical Field
The invention belongs to the technical field of metal part precision mechanics, and particularly relates to a machining method of a wing-shaped elastic shaft high-precision part.
Background
The elastic shaft detector is a necessary checking instrument in a certain key product, and the elastic wing is a weight-closing reference component of the elastic shaft detector. From structural analysis, the missile wing adopts an asymmetric lightweight design, follows the concept of small size and portability, simulates the appearance of a missile, specifically, the missile wing is made of steel 35 and is formed by welding 3 special-shaped parts with different thicknesses and 1 pipe, the appearance size is R86X670 (mm), a special-shaped long shaft is formed by a base body and connecting pieces of two fan-shaped parts, and the outer circular arc of each fan-shaped part simulates the missile wing of the missile.
The missile wing is used as a weight-closing reference component of the missile axis detector, the precision of the missile wing is far higher than that of a common part, and due to the uniqueness of the structure, the missile wing is influenced by the stress deformation of a process system in machining, the machining process of the part needs to be monitored in real time at any time, however, only a three-coordinate measuring instrument can be adopted in the process of measuring the space size generally, and the real-time monitoring of the missile wing on a station cannot be realized.
In addition, in order to simulate the missile structure more truly, two sections of high-precision arc surfaces are designed on an incomplete sector, the spatial connection line of the center point is a design reference, and the processing difficulty is mainly expressed in the aspects of high-precision welding forming, precision machining and in-place detection, for example, the asymmetric missile wing structure is easy to deform and distort under the action of factors such as cutting force, clamping force and the like, so that the high-precision requirement of a checking instrument is influenced; in addition, dynamic balancing of the missile wings in the process, precise positioning on the machine tool, and in-situ detection problems become bottlenecks in the process.
Disclosure of Invention
The invention aims to provide a method for processing a high-precision wing-shaped elastic shaft part, which overcomes the technical defects.
In order to solve the technical problem, the invention provides a method for processing a high-precision wing-shaped elastic shaft part, which comprises the following steps:
001, selecting raw materials for processing a target airfoil-shaped part and blanking;
002, splitting the target airfoil-shaped part into welding single pieces according to the part structure, and taking raw materials required by each welding single piece;
step 003, machining each welding single piece;
step 004, assembling and welding single pieces to form a missile wing assembly, and vibrating to remove stress;
005, taking two missile wing assemblies, and simultaneously clamping the two missile wing assemblies by using an auxiliary machining device, wherein the two missile wing assemblies and the auxiliary machining device form a revolving body structure, and the revolving body structure can rotate around a revolving center;
and 006, continuously machining the revolving body structure, and removing the auxiliary machining device until the revolving body structure becomes the target airfoil-shaped part.
Further, in step 002, the splitting the target airfoil part into welding single parts according to the part structure specifically includes:
dividing the target airfoil-shaped part into four welding single pieces according to the part structure;
respectively machining the welding single pieces by taking raw materials;
wherein the four welding single pieces are respectively a front sector missile wing, a rear sector missile wing, a seat body and a mandrel.
Further, the machining 003 of each of the welded singlets, wherein the machining of the front flail includes:
taking a bar stock;
two end surfaces of the bar stock are turned flat and cut into a turning groove;
cutting the bar stock into 2 pieces by adopting a linear cutting method;
continuously processing the bar until the front sector missile wing is formed;
wherein the center hole of the front fan-shaped missile wing is used as a positioning hole during welding.
Further, the machining 003 of each of the welded singlets, wherein machining the rear flail includes:
taking a bar stock;
two end surfaces of the bar stock are turned flat and cut into a turning groove;
cutting the bar stock into 2 pieces by adopting a linear cutting method;
continuing to process until a back sector missile wing is formed;
the central hole of the rear fan-shaped missile wing is used as a rear positioning pin hole during welding, and the U-shaped notch in the center of the fan-shaped edge is used as a rear positioning pin hole.
Further, the step 003 of machining each of the welded singlets, wherein machining the socket body includes:
taking a plate material;
milling a hexagon;
one end surface is provided with a front positioning pin hole, and the other end surface is milled with a process boss;
continuing to process until a seat body is formed;
the central axis of the front positioning pin hole is parallel to the central axis of the process boss and is not overlapped.
Further, the machining each of the welded singlets described in step 003, wherein machining the mandrel includes:
taking a section;
milling an end face and an inclined plane;
the process continues until the mandrel is formed.
Further, assembling and welding single pieces to form a missile wing assembly in the step 004, and performing vibration stress relief, wherein the method specifically comprises the following steps:
removing oil stains on the parts to be welded of the welding single pieces;
assembling and spot-welding single parts on a welding platform to form a missile wing assembly;
adopting a short-section multi-pass welding missile wing assembly;
before the welding seam is cooled, utilizing a vibration destressing expert system to carry out vibration destressing;
and (4) removing welding slag, polishing high points of the welding line, and checking the welding line to ensure no defect.
Further, the following steps are also included between step 004 and step 005:
firstly, low-temperature treatment is carried out, the low-temperature treatment temperature is 440-460 ℃, the temperature is kept for 2.8-3.2 h, the furnace is cooled to 200 ℃, the cold treatment is carried out after the air cooling is carried out to the room temperature, the temperature is-50-60 ℃, the temperature is kept for 1h, and the air cooling is carried out to the room temperature.
Further, step 005 said get two missile wing assembly parts, adopt the auxiliary processing device to press from both sides two missile wing assembly parts simultaneously, two missile wing assembly parts and auxiliary processing device constitute the revolution solid structure, and the revolution solid structure can be around the centre of gyration is rotatory, continues machining revolution solid structure, until it becomes the target airfoil type part, specifically includes:
the auxiliary processing device comprises a front clamp and a rear clamp which are both disc-shaped, wherein one disc surface of the front clamp is provided with two front positioning pins distributed at 180 degrees, and the other disc surface is provided with a front stepped shaft; one disc surface of the rear clamp is provided with two rear positioning pins distributed at 180 degrees and two rear orientation pins distributed at 180 degrees, the connecting lines of the central points of all the rear positioning pins and the connecting lines of the central points of all the rear orientation pins are overlapped, and the other disc surface is provided with a rear stepped shaft;
wherein, the front positioning pin hole, the front fan-shaped missile wing, the mandrel and the rear fan-shaped missile wing of the base body in the missile wing assembly are coaxially welded in sequence;
the two missile wing assemblies are clamped between the front clamp and the rear clamp, two front positioning pins of the front clamp are respectively inserted into front positioning pin holes in the two missile wing assemblies, two rear positioning pins of the rear clamp are respectively inserted into rear positioning pin holes in the two missile wing assemblies, and all adjacent parts are welded to form a revolving body structure taking the central axis of any clamp as a revolving center.
The invention has the following beneficial effects:
the processing method of the high-precision wing-shaped elastic shaft part is provided with the special clamp, so that a space virtual point at the center position of the elastic wing is changed into an actually existing central axis, the circular arc of the elastic wing forms a symmetrical and measurable circle, the in-situ detection is completed, and the purpose of real-time monitoring is achieved; meanwhile, the design reference, the process reference and the detection reference are unified, positioning and detection errors are avoided in machining and detection, symmetrical machining of the missile wing is achieved, and the problem of dynamic balance in the grinding process is solved.
In order to make the aforementioned and other objects of the present invention comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
FIG. 1 is a schematic structural view of a target airfoil part (missile wing assembly);
FIG. 2 is a schematic view of the auxiliary processing device holding the missile wing assembly;
FIG. 3 is a schematic structural view of the base;
FIG. 4 is a front view of the front clamp;
FIG. 5 is a side view of the front clamp;
FIG. 6 is a front view of the rear clamp;
FIG. 7 is a side view of the rear clamp;
figure 8 is a P-view of the front sector missile wing;
figure 9 is a Q-view of the front sector missile wing;
FIG. 10 is a P-direction view of the rear sector shaped missile wing;
figure 11 is a Q-direction view of the rear sector missile wing.
Description of reference numerals:
1. a front sector missile wing; 2. a rear fan-shaped missile wing; 3. a base body; 4. a mandrel; 5. a front clamp; 6. a rear clamp;
201. a rear positioning pin hole; 202. a rear orientation pin hole;
301. a front dowel hole; 302. a process boss;
501. a front locating pin; 502. a front step axis;
601. a rear positioning pin; 602. a rear orientation pin; 603. a back step axis.
Detailed Description
The following description of the embodiments of the present invention is provided for illustrative purposes, and other advantages and effects of the present invention will become apparent to those skilled in the art from the present disclosure.
In the present invention, the upper, lower, left and right in the drawings are regarded as the upper, lower, left and right of the method for machining the wing-shaped elastic shaft high-precision part described in the present specification.
The exemplary embodiments of the present invention will now be described with reference to the accompanying drawings, however, the present invention may be embodied in many different forms and is not limited to the embodiments described herein, which are provided for complete and complete disclosure of the present invention and to fully convey the scope of the present invention to those skilled in the art. The terminology used in the exemplary embodiments illustrated in the accompanying drawings is not intended to be limiting of the invention. In the drawings, the same units/elements are denoted by the same reference numerals.
Unless otherwise defined, terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. Further, it will be understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the relevant art and will not be interpreted in an idealized or overly formal sense.
First embodiment
The embodiment relates to a method for processing a high-precision wing-shaped elastic shaft part, which comprises the following steps:
001, selecting raw materials for processing a target airfoil-shaped part and blanking;
002, splitting the target airfoil-shaped part into welding single pieces according to the part structure, and taking raw materials required by each welding single piece;
step 003, machining each welding single piece;
step 004, assembling and welding single pieces to form a missile wing assembly, and vibrating to remove stress;
005, taking two missile wing assemblies, and simultaneously clamping the two missile wing assemblies by using an auxiliary machining device, wherein the two missile wing assemblies and the auxiliary machining device form a revolving body structure, and the revolving body structure can rotate around a revolving center;
and 006, continuously machining the revolving body structure, and removing the auxiliary machining device until the revolving body structure becomes the target airfoil-shaped part.
The missile wing assembly is a target airfoil part after being processed, so the structure is similar, and the structure of the target airfoil part is shown in fig. 1 in the embodiment, which can also be regarded as the structure of the missile wing assembly.
The reason that the missile wing generates deformation in the machining process is welding deformation caused by an asymmetric structure, and the mechanism of the welding deformation is as follows:
the welding process can be seen as a crystallization process in which the molten pool changes from a liquid phase to a solid phase, a non-equilibrium solidification. The volume of a welding pool is small, the cooling speed is high, and defects such as air holes, cracks, inclusions, segregation and the like are easily formed in weld metal; the liquid metal in the molten pool is in an overheated state, the metal at the edge belongs to a normal temperature state, and the temperature gradient generates larger thermal stress; the molten pool is crystallized in a motion state, and grows to the center of the heat source in the opposite heat radiation direction, and stops growing to the center of the welding seam. This region is an impurity accumulation prone region. Due to the characteristics, the missile wing cannot be fully extended and contracted due to rigid constraint when being locally heated and cooled in the welding process, and a large amount of stress is generated; when the tensile stress of each part is not uniform, one side of the part is contracted and extended, and the other side of the part is contracted and reduced, so that the weldment generates bending and twisting deformation. It can be said that the generation of these stresses and strains is inevitable. Therefore, the influence of the welding deformation on the missile wing welding structural part can be controlled from the aspect of welding process factors by utilizing the mechanism.
The vibration destressing in the above processing method has the following reasons:
the welding deformation is closely related to the welding residual stress, and the welding deformation is generated just because the welding residual stress exists in the welding seam. Therefore, after the assembly and welding of the workpieces, stress relief treatment and deformation adjustment and correction are generally performed, so that the workpieces can meet the requirements of drawings and use. Eliminating welding stress, performing heat treatment after welding to eliminate stress, and ensuring the shape and position requirements of flatness, verticality and the like of each part after heat treatment by adopting an object fixing method during heat treatment; correcting welding deformation, performing primary correction after welding, and applying mechanical pressure in the opposite direction to the deformed part by using an oil press to restore the deformed part; and then, carrying out heat treatment to eliminate stress, carrying out physical fixation on the part while carrying out heat treatment, and carrying out a heat correction process on the part in the heat treatment process through the fixation on the part so as to further reduce the deformation of the part.
The principle of the missile wing processing method is as follows:
the structure of the missile wing is complicated, but the missile wing has the common characteristics that: is asymmetric and has a fan-shaped structure. Particularly, the outer circular arc of the sector simulates missile wings of a missile, in order to simulate the structure of the missile more truly, two sections of high-precision circular arc surfaces are designed on an incomplete sector, the connecting line of the central point of the incomplete sector in space is a design reference, and referring to fig. 8, 9, 10 and 11, the asymmetric structure of the missile wings is easy to deform and distort under the action of factors such as cutting force, clamping force and the like, so that the high-precision requirement of a checking instrument is influenced, therefore, after the structure of the missile wings is analyzed, a symmetrical processing method is adopted to process the asymmetric missile wings, the symmetrical processing method is completed through an auxiliary processing device, namely two missile wing assemblies are simultaneously clamped in the auxiliary processing device to form a revolving body structure (as shown in fig. 2), the whole revolving body structure can rotate around the revolving center, and the space virtual point of the central position of the missile wings is changed into an actual central axis, the circular arc of the missile wing forms a symmetrical measurable circle, the in-place detection is completed by using a general measuring tool, the purpose of real-time monitoring is achieved, meanwhile, the design reference, the process reference and the detection reference are unified, the positioning and detection errors are avoided in the machining and the detection, the symmetrical machining of the missile wing is also achieved, and the problem of dynamic balance in the grinding process is solved.
Due to the complex structure of the missile wing, the missile wing is divided into welding single pieces according to the part structure and is respectively machined, the material cost is effectively reduced, the machining workload is reduced, the productivity is improved, the blanking of each welding single piece is machined, the machining allowance is required to be set according to the size and form and position tolerance requirements with high precision requirements, and the common size and action tolerance requirements are directly machined in place.
Second embodiment
The embodiment relates to a method for processing a high-precision wing-shaped elastic shaft part, which comprises the following steps:
001, selecting raw materials for processing a target airfoil-shaped part and blanking;
002, splitting the target airfoil-shaped part into welding single pieces according to the part structure, and taking raw materials required by each welding single piece;
step 003, machining each welding single piece;
step 004, assembling and welding single pieces to form a missile wing assembly, and vibrating to remove stress;
005, taking two missile wing assemblies, and simultaneously clamping the two missile wing assemblies by using an auxiliary machining device, wherein the two missile wing assemblies and the auxiliary machining device form a revolving body structure, and the revolving body structure can rotate around a revolving center;
and 006, continuously machining the revolving body structure, and removing the auxiliary machining device until the revolving body structure becomes the target airfoil-shaped part.
The configuration of the missile wing is various and complicated, and in order to clearly describe the processing method, the present embodiment will be described by taking the front sector missile wing 1 shown in fig. 8 and 9 as an example and the rear sector missile wing 2 shown in fig. 10 and 11 as an example, but the present invention is not limited thereto.
Wherein, step 002 is according to the part structure with the target airfoil part split into welding singleton, specifically includes:
dividing the target airfoil-shaped part into four welding single pieces according to the part structure;
respectively machining the welding single pieces by taking raw materials;
the four welding single pieces are respectively a front sector missile wing 1, a rear sector missile wing 2, a base body 3 and a mandrel 4.
The number of welding seams is reduced as much as possible under the condition that a blank permits, the heat input is reduced, and the deformation generated by welding is reduced. The missile wing structure is analyzed by considering the structural characteristics of the missile wing, the missile wing structure is divided into 4 parts such as a front sector missile wing 1, a rear sector missile wing 2, a seat body 3 and a mandrel 4, the front sector missile wing 1 and the rear sector missile wing 2 are connected through the mandrel 4, the seat body 3 is connected with the mandrel 4, the number of welding seams is effectively reduced, the concentration and the overlapping of the welding seams are avoided, the residual stress of the welded parts is effectively reduced, the welding deformation is reduced, and the part processing difficulty and the cost are reduced.
The welding process of each welding single piece is as follows:
preceding fan-shaped missile wing 1 of machining includes:
taking a bar stock;
two end surfaces of the bar stock are turned flat and cut into a turning groove;
cutting the bar stock into 2 pieces by adopting a linear cutting method;
continuously processing the bar until the front fan-shaped missile wing 1 is formed;
wherein the center hole of the front fan-shaped missile wing 1 is used as a positioning hole during welding.
Taking the front sector missile wing 1 shown in fig. 8 and 9 as an example, a bar stock with the specification of phi 180mm is adopted, two end faces are flattened, a groove is cut, and then the bar stock is cut into 2 pieces by adopting a linear cutting method, the machining workload and the residual stress in the material are reduced by adopting the linear cutting method, the material and labor cost are reduced, and the production efficiency is improved, wherein the central hole phi 42mm (the central hole in fig. 9) is used as a positioning hole during welding and is used for inserting the mandrel 4.
Machining the rear sector missile wing 2, comprising:
taking a bar stock;
two end surfaces of the bar stock are turned flat and cut into a turning groove;
cutting the bar stock into 2 pieces by adopting a linear cutting method;
continuing to process until a back sector missile wing 2 is formed;
the central hole of the rear fan-shaped missile wing 2 is used as a rear positioning pin hole 201 during welding, and the U-shaped notch at the center of the fan-shaped edge is used as a rear positioning pin hole 202.
Taking the rear sector elastic wing 2 shown in fig. 10 and 11 as an example, a bar material with the specification of phi 190mm is adopted, two end faces are flattened, a groove is cut, the bar material is cut into 2 pieces by the same linear cutting method, and a central hole phi 42mm (the central hole in fig. 11) is used as a positioning hole during welding and is used for inserting the mandrel 4.
taking a plate material;
milling a hexagon;
one end face is provided with a front positioning pin hole 301, and the other end face is milled with a process boss 302;
continuing to process until a seat body 3 is formed;
wherein the central axis of the front dowel hole 301 and the central axis of the process boss 302 are parallel to each other and do not overlap.
The structure of the seat body 3 is shown in fig. 3, the seat body 3 is made of a plate material with the thickness of 20mm, and after milling a hexagonal shape, an 18 × 18 process boss 302 is milled at the right end and used for positioning and orientation during welding.
taking a section;
milling an end face and an inclined plane;
the process continues until the mandrel 4 is formed.
The mandrel 4 is machined by a section bar, so that the material cost can be effectively reduced, the machining workload and the residual stress in the material can be reduced, and the left end face and the inclined plane can be milled, which is shown in fig. 1.
Wherein, step 004 is assembled and welded the singleton and constitute the missile wing sub-assembly, and the vibration destressing specifically includes:
removing oil stains on the parts to be welded of the welding single pieces;
assembling and spot-welding single parts on a welding platform to form a missile wing assembly;
adopting a short-section multi-pass welding missile wing assembly;
before the welding seam is cooled, utilizing a vibration destressing expert system to carry out vibration destressing;
and (4) removing welding slag, polishing high points of the welding line, and checking the welding line to ensure no defect.
It should be noted that the vibration stress relief expert system is a common stress relief device in the mechanical industry, belongs to the prior art, and is used only as a stress relief tool in the present embodiment, and the specific structure thereof is not within the protection scope of the present embodiment, for example, the HX-VAAI high intelligent vibration stress relief expert system may be selected.
Specifically, oil stains at parts to be welded of a front fan-shaped missile wing 1, a rear fan-shaped missile wing 2, a base body 3 and a mandrel 4 are removed, the missile wing is assembled on a welding platform according to the position shown in the figure 1 and is fixed in a spot mode, the size and the form and position requirements are guaranteed through correction, the missile wing assembly is welded in a short section and multiple ways (vertical joints are welded firstly, horizontal joints are welded secondly), welding heat input is reduced, and welding deformation is reduced; after each welding single piece is finished and before a welding seam is not cooled, homogenizing the stress after welding by using a vibration destressing expert system; cleaning welding seams and polishing high points: and removing welding slag, polishing high points of the welding line, and checking whether the welding line is defect-free.
The size of the to-be-welded part is reasonable and accurate, the shrinkage of the part is considered when the 4 parts are processed, the overall size of the part is slightly larger according to the length and the height of a welding line, and the upper limit of tolerance is processed during processing; the middle connecting part is lengthened by 1mm to compensate the contraction of the welding line; the precision of the tool and the welding platform is the key for ensuring the assembly welding size of a welding part to be accurate or not, the size requirement of the positioning tool is made clear on a part welding drawing, and the flatness of the welding platform is controlled within a range of 1 mm; a reasonable welding method is selected, and because the missile wing structure is complex and the welding seams are various in shape, all the welding seams are fully welded by adopting manual electric arc welding; the welding process parameters, the size of the welding seam is short, the thickness difference of parts is large, the welding deformation is controlled by adopting a proper welding process of small-diameter welding rods (wires), small current and large linear velocity, and the position welding position is selected at the corner part with large rigidity and small welding deformation, so that the position welding can be accurately positioned.
It is worth mentioning that the following steps are further included between step 004 and step 005:
1) annealing and removing welding stress:
controlling the annealing temperature at 440-460 ℃, keeping the temperature for 2.8-3 h, cooling the furnace to 200 ℃, and air-cooling to room temperature;
2) correcting by using a correction platform and a press;
3) and (4) hot and cold circulation is performed to stabilize tissues.
Firstly, low-temperature treatment is carried out, the low-temperature treatment temperature is 440-460 ℃, the temperature is kept for 2.8-3.2 h, the furnace is cooled to 200 ℃, the cold treatment is carried out after the air cooling is carried out to the room temperature, the temperature is-50-60 ℃, the temperature is kept for 1h, and the air cooling is carried out to the room temperature.
Step 005 takes two missile wing assemblies, adopts the auxiliary processing device to clamp two missile wing assemblies simultaneously, and two missile wing assemblies and the auxiliary processing device form a revolving body structure, and the revolving body structure can rotate around a revolving center, and continues to machine the revolving body structure until it becomes a target wing section part, specifically including:
the auxiliary processing device comprises a front clamp 5 (see fig. 4 and 5) and a rear clamp 6 (see fig. 6 and 7), which are both disc-shaped, wherein one disc surface of the front clamp 5 is provided with two front positioning pins 501 distributed at 180 degrees, and the other disc surface is provided with a front stepped shaft 502; one disk surface of the rear clamp 6 is provided with two rear positioning pins 601 distributed at 180 degrees and two rear orientation pins 602 distributed at 180 degrees, the connecting lines of the central points of all the rear positioning pins 601 are mutually overlapped with the connecting lines of the central points of all the rear orientation pins 602, and the other disk surface is provided with a rear stepped shaft 603;
wherein, the front positioning pin hole 301 of the seat body 3 in the missile wing assembly, the front sector missile wing 1, the mandrel 4 and the rear sector missile wing 2 are coaxially welded in sequence;
the two missile wing assemblies are clamped between a front clamp 5 and a rear clamp 6, two front positioning pins 501 of the front clamp 5 are respectively inserted into front positioning pin holes 301 in the two missile wing assemblies, two rear positioning pins 602 of the rear clamp 6 are respectively inserted into rear positioning pin holes 202 in the two missile wing assemblies, two rear positioning pins 601 of the rear clamp 6 are respectively inserted into rear positioning pin holes 201 in the two missile wing assemblies, and all adjacent parts are welded to form a revolving body structure with the central axis of any clamp as a revolving center.
The rear positioning pin 601 and the rear positioning pin 602 are coaxially connected and positioned with the rear positioning pin hole 201 and the rear positioning pin hole 202 respectively, the two front positioning pins 501 are coaxially inserted and positioned with the front positioning pin hole 301 of the base body 3, the front stepped shaft 502 of the front clamp 5 is jacked up by the tailstock of the machine tool, and the right stepped shaft of the rear clamp 6 is connected with the elastic tube of the machine tool.
The two missile wing assemblies are clamped at one time, the moving flatness during rotation is achieved, the space center rotation centers of the two missile wing assemblies are arranged on the center of the auxiliary tool, specifically, the left end step shaft of the front clamp 5 is jacked up by a machine tool tailstock, the right end step shaft of the rear clamp 6 is connected with an elastic machine tool pipe, after the machining of parts is completed through the excircle centering, the machine tool tailstock retreats, a gap is formed between a workpiece and a positioning surface of the mandrel 4, the elastic deformation is eliminated, and the workpiece can be freely dismounted.
Principle of mechanical working
The missile wing structure is analyzed, and according to the ideas of reducing machining allowance as much as possible, reducing clamping times in a centralized process and the like, the design process flow is as follows: assembling and welding parts → heat treatment annealing → correction → heat treatment stress relief annealing → scribing inspection → machining → … ….
1) In the aspect of measures for controlling deformation in machining, firstly, bench workers perform scribing to check blank machining allowance and provide rough machining reference; secondly, processing holes at two ends of each missile wing (a front sector missile wing 1 and a rear sector missile wing 2), wherein the coaxiality is 0.05, and the holes are used for grinding positioning and orientation; thirdly, grinding arcs R of two end surfaces to be used as a reference of a milling and grinding surface A; then, milling an end face, drilling holes and removing allowance by using a combined clamp; and finally grinding the end face. In the whole process flow, the machining allowance is reduced as much as possible, and the machining stress and deformation are reduced.
2) In the aspect of cutting tool selection, according to the selection principle of the cutting thinning tool, the arc of the tool tip is properly smaller, the extrusion amount is reduced, the front angle of the tool is increased, the cutting force is reduced, and therefore the thermal deformation is reduced. The tool relief angle is increased appropriately to reduce the friction of the flank face with the machined surface.
3) The clamping mode is reasonably selected, when a workpiece is clamped in a finish machining stage, a dial indicator is mounted on a spindle of a machine tool, a pointer is pressed on a base surface of the workpiece, the change after the pressing cannot exceed 0.05mm generally, and the deformation is controlled to be minimum. Before the workpiece enters the fine machining process, operators and inspectors need to carefully detect the fitting degree of each process reference and the table surface of the machine tool so as to control the deformation degree of the workpiece.
The machining of step 005 specifically includes:
1) drawing lines by a fitter, drawing a center correction, checking the straightness of parts and checking the machining allowance in each direction;
2) horizontal boring, wherein a Q-direction view end face and a bore phi 33H7 of the part are aligned, a U-shaped groove at the top of the part is milled to be used as a directional and rotary worktable for grinding, the P-direction view end face and the bore phi 10H7 are milled, the coaxiality of two holes (the bore phi 33H7 and the bore phi 10H 7) is ensured to be 0.05, and the coaxiality is used as a positioning reference for grinding;
3) grinding by using a grinding machine, namely clamping 2 missile wings by using a front clamp 5 and a rear clamp 6 as shown in fig. 2, enabling the rotation center of the 2 missile wings to be positioned at the center of a rotation body consisting of the front clamp 5, the rear clamp 6 and the missile wings, and grinding circular arcs and circular arc end surfaces;
4) numerical control machining, namely taking down parts from a revolving body, aligning the parts by using an assembled clamp with an arc as a reference, and milling and drilling the upper end surface of a view P shown in figure 1;
5) grinding, namely aligning the upper end face of the view P shown in figure 1 by taking an arc as a reference, and grinding the surface;
6) aligning parts, and roughly and finely milling U-shaped notches;
7) tapping and making threads, and checking finished dimension and action tolerance.
It should be particularly noted that, in the embodiment, the special auxiliary front clamp 5 and the special auxiliary rear clamp 6 are manufactured, so that the part rotates around the rotation center, the processing difficulty is reduced, the in-place detection is realized, and the processing precision of the part is improved; the welding adopts manual electric arc welding for full welding, the welding material adopts a structural steel welding rod J507, the welding speed can be changed according to the welding position, the size and the length of a welding seam, and the welding seam quality, the height and the width of the welding seam are ensured.
The auxiliary processing device consisting of the front clamp 5 and the rear clamp 6 enables the circular arc of the missile wing to form a symmetrical and measurable circle, realizes that a spatial virtual point at the central position of the missile wing becomes a central axis which is actually present and can be corrected and detected, simultaneously realizes the unification of a design reference, a process reference and a detection reference, ensures that no positioning and detection errors are generated in processing and detection, realizes the symmetrical processing of the asymmetric missile wing, and solves the dynamic balance problem in processing.
It will be understood by those of ordinary skill in the art that the foregoing embodiments are specific examples for carrying out the invention, and that various changes in form and details may be made therein without departing from the spirit and scope of the invention in practice.
Claims (8)
1. A method for processing a high-precision wing-shaped elastic shaft part is characterized by comprising the following steps:
001, selecting raw materials for processing a target airfoil-shaped part and blanking;
002, dividing the target airfoil-shaped part into four welding single pieces, and taking raw materials required by each welding single piece, wherein the four welding single pieces are respectively a front sector missile wing (1), a rear sector missile wing (2), a base body (3) and a mandrel (4);
step 003, machining each welding single piece;
step 004, assembling and welding single pieces to form a missile wing assembly, and vibrating to remove stress;
005, taking two missile wing assemblies, and simultaneously clamping the two missile wing assemblies by using an auxiliary machining device, wherein the two missile wing assemblies and the auxiliary machining device form a revolving body structure, and the revolving body structure can rotate around a revolving center;
and 006, continuously machining the revolving body structure, and removing the auxiliary machining device until the revolving body structure becomes the target airfoil-shaped part.
2. The method for machining high-precision wing-type missile shaft parts as claimed in claim 1, wherein the step 003 of machining each welded single piece is characterized in that the machining of the front fan-shaped missile wing (1) comprises the following steps:
taking a bar stock;
two end surfaces of the bar stock are turned flat and cut into a turning groove;
cutting the bar stock into 2 pieces by adopting a linear cutting method;
continuously processing the bar stock until a front fan-shaped missile wing (1) is formed;
wherein the center hole of the front fan-shaped missile wing (1) is used as a positioning hole during welding.
3. The method for machining high-precision wing-type missile shaft parts as claimed in claim 1, wherein the step 003 of machining each welded single piece is characterized in that the step of machining the rear fan-shaped missile wing (2) comprises the following steps:
taking a bar stock;
two end surfaces of the bar stock are turned flat and cut into a turning groove;
cutting the bar stock into 2 pieces by adopting a linear cutting method;
continuously processing until a back sector missile wing (2) is formed;
the central hole of the rear fan-shaped missile wing (2) is used as a rear positioning pin hole (201) during welding, and the U-shaped notch in the center of the fan-shaped edge is used as a rear directional pin hole (202).
4. The method for machining high-precision wing-type elastic shaft parts according to claim 1, wherein the step 003 of machining each welded single piece is to machine the seat body (3) by machining and comprises the following steps:
taking a plate material;
milling a hexagon;
one end face is provided with a front positioning pin hole (301), and the other end face is milled with a process boss (302);
continuing to process until a seat body (3) is formed;
the central axis of the front positioning pin hole (301) and the central axis of the process boss (302) are parallel to each other and do not overlap.
5. The method for machining the high-precision wing-type elastic shaft part according to claim 1, wherein the step 003 of machining each welding single piece is characterized in that the step of machining the mandrel (4) comprises the following steps of:
taking a section;
milling an end face and an inclined plane;
the machining is continued until a mandrel (4) is formed.
6. The method for processing the high-precision wing-shaped elastic shaft part as claimed in claim 1, wherein the assembling and welding single pieces to form the elastic wing assembly in the step 004, and the vibration stress relief specifically comprises the following steps:
removing oil stains on the parts to be welded of the welding single pieces;
assembling and spot-welding single parts on a welding platform to form a missile wing assembly;
adopting a short-section multi-pass welding missile wing assembly;
before the welding seam is cooled, utilizing a vibration destressing expert system to carry out vibration destressing;
and (4) removing welding slag, polishing high points of the welding line, and checking the welding line to ensure no defect.
7. The method for processing the high-precision wing-type elastic shaft part according to claim 1, wherein the method further comprises the following steps between step 004 and step 005:
firstly, low-temperature treatment is carried out, the low-temperature treatment temperature is 440-460 ℃, the temperature is kept for 2.8-3.2 h, the furnace is cooled to 200 ℃, the cold treatment is carried out after the air cooling is carried out to the room temperature, the temperature is-50-60 ℃, the temperature is kept for 1h, and the air cooling is carried out to the room temperature.
8. The method for processing a wing-shaped missile shaft high-precision part according to claim 5, wherein the step 005 is to take two missile wing assemblies, simultaneously clamp the two missile wing assemblies by using an auxiliary processing device, form a revolving body structure by the two missile wing assemblies and the auxiliary processing device, and continuously machine the revolving body structure by rotating around a revolving center until the revolving body structure becomes a target wing-shaped part, and specifically comprises the following steps:
the auxiliary processing device comprises a front clamp (5) and a rear clamp (6), which are both disc-shaped, wherein one disc surface of the front clamp (5) is provided with two front positioning pins (501) distributed at an angle of 180 degrees, and the other disc surface is provided with a front stepped shaft (502); one disc surface of the rear clamp (6) is provided with two rear positioning pins (601) distributed at an angle of 180 degrees and two rear orientation pins (602) distributed at an angle of 180 degrees, the connecting lines of the central points of all the rear positioning pins (601) and the connecting lines of the central points of all the rear orientation pins (602) are overlapped, and the other disc surface is provided with a rear stepped shaft (603);
the base body (3), the front sector missile wing (1), the mandrel (4) and the rear sector missile wing (2) in the missile wing assembly are sequentially welded, and the axial central lines of the front positioning pin hole (301), the front sector missile wing (1), the mandrel (4) and the rear sector missile wing (2) are superposed;
the two missile wing assemblies are clamped between a front clamp (5) and a rear clamp (6), two front positioning pins (501) of the front clamp (5) are respectively inserted into front positioning pin holes (301) in the two missile wing assemblies, two rear positioning pins (602) of the rear clamp (6) are respectively inserted into rear positioning pin holes (202) in the two missile wing assemblies, two rear positioning pins (601) of the rear clamp (6) are respectively inserted into rear positioning pin holes (201) in the two missile wing assemblies, and all adjacent parts are welded to form a revolving body structure with the central axis of any clamp as a rotation center.
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