CN114633133B - Airplane special-shaped part clamping auxiliary device and clamping method thereof - Google Patents
Airplane special-shaped part clamping auxiliary device and clamping method thereof Download PDFInfo
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- CN114633133B CN114633133B CN202210546297.6A CN202210546297A CN114633133B CN 114633133 B CN114633133 B CN 114633133B CN 202210546297 A CN202210546297 A CN 202210546297A CN 114633133 B CN114633133 B CN 114633133B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
- B23Q3/02—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine for mounting on a work-table, tool-slide, or analogous part
- B23Q3/06—Work-clamping means
- B23Q3/062—Work-clamping means adapted for holding workpieces having a special form or being made from a special material
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention discloses an auxiliary clamping device and a clamping method for airplane special-shaped parts, wherein the auxiliary clamping device comprises a cylindrical revolving body, and two ends of the revolving body are respectively provided with a cylindrical clamping end and a cylindrical fixed end; the surface that is close to stiff end one side on the solid of revolution is provided with two planes, and two planes are provided with on the plane with the axis symmetry of the solid of revolution and test the sword hole, test being provided with on the sword hole and test the sword piece, and equal symmetry is provided with two clamping face between two planes, has seted up a plurality of screw holes on the clamping face, and the both ends of clamping face all are provided with two bolt holes of having seted up on the fixed boss of fixed boss, are provided with the pinhole between two bolt holes. The clamping method comprises the following steps: steps S1-S14. According to the invention, different stations are designed on the same revolving body, so that the numerical control machine tool can be assisted to process airplane special-shaped parts which are difficult to process, multiple clamping and special tools in the processing process are avoided, the processing benefit is improved, and the size precision and the shape and position precision of the parts are ensured.
Description
Technical Field
The invention relates to the technical field of processing of airplane special-shaped parts, in particular to an auxiliary device for clamping airplane special-shaped parts and a clamping method thereof.
Background
At present, in the machining of small-size special-shaped parts of an airplane, special customized tools and multiple clamping are generally adopted for special-shaped parts difficult to clamp, and the parts are machined through a three-axis numerical control device, or five-axis and other high-end numerical control machines are adopted for machining: for parts which are difficult to clamp in special shapes, different in size and thin in wall thickness, the clamping difficulty and the machining difficulty are often large, the machining period is long, the technical requirement is high, the machining precision is affected even the parts are scrapped due to carelessness, and the cost is increased and the machining efficiency is low.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides an auxiliary device for clamping an airplane special-shaped part with high machining precision and a clamping method thereof.
In order to achieve the purpose of the invention, the technical scheme adopted by the invention is as follows:
the clamping auxiliary device comprises a cylindrical revolving body, wherein a cylindrical clamping end and a cylindrical fixed end are respectively arranged at two ends of the revolving body, and the clamping end, the fixed end and the revolving body are coaxial; the clamping end is fixed on a chuck of the machine tool, and the fixed end is arranged on the bearing seat; the surface that is close to stiff end one side on the solid of revolution is provided with two planes, two planes are symmetrical with the axis of the solid of revolution, be provided with on the plane and test the sword hole, it tests the sword piece to be provided with on testing the sword hole, equal symmetry is provided with two clamping faces between two planes, two clamping faces and two planes become cross distribution on the outer circumference of the solid of revolution, a plurality of screw holes have been seted up on the clamping face, the both ends of clamping face all are provided with fixed boss, fixed boss highly surpasss the clamping face, two bolt holes have been seted up on the fixed boss, be provided with the pinhole between two bolt holes.
Furthermore, both sides of the clamping surface are provided with sinking platforms, and both ends of the fixed boss are provided with sinking grooves.
Further, the bearing seat comprises a lower seat body, a semicircular groove for placing the bearing is formed in the upper end of the lower seat body, a semicircular bearing cover is arranged at the upper end of the lower seat body, the bearing is packaged between the bearing cover and the semicircular groove, the bearing sleeve is arranged at the fixed end, and the bearing cover is fixed on the lower seat body through a bolt.
Furthermore, the lower end of the lower seat body is fixed on a workbench of a milling machine, a plurality of parallel fixing grooves are formed in the workbench, the fixing grooves are T-shaped grooves, and the lower end of the lower seat body is fixed on the T-shaped grooves through bolts.
Furthermore, one side of the revolving body, which is close to the clamping end, is provided with four fixing surfaces, and the four fixing surfaces are distributed on the surface of the revolving body in a cross manner.
The clamping method for machining the special-shaped part of the aircraft landing gear by using the special-shaped part clamping auxiliary device comprises the following steps:
s1: assembling the fixed end of the machined revolving body into a bearing, packaging the bearing on a bearing seat, and fixing the bearing through a bolt by a bearing cover;
s2: fixing the clamping end of the revolving body on a chuck of a milling machine, and mounting a level gauge on the revolving body;
s3: the height of the bearing seat and the position of the bearing seat on a workbench of the milling machine are adjusted by the reference level gauge, the axis of the revolving body is ensured to be coincided with the rotating central line of the chuck, and the lower seat body is fixed on the T-shaped groove through a bolt;
s4: taking a special-shaped part to be processed, positioning by using pin holes at two ends of a clamping surface, fixing two ends of the special-shaped part on a fixed boss through bolts, and locking the middle part of the special-shaped part on the clamping surface through a screw;
s5: repeating the step S4, and mounting the special-shaped parts to be processed on the two clamping surfaces of the revolving body;
s6: the chuck drives the revolving body to rotate, and the special-shaped part on one clamping surface is positioned right above the revolving body by referring to the level gauge, so that a machining point A of the special-shaped part needing to be machined by the milling cutter is determined;
s7: taking a workbench in the milling machine as an xoy reference plane, measuring coordinates (x1, y1, z1) of a processing point A in a space rectangular coordinate system o-xyz, wherein the origin of the coordinates of the space rectangular coordinate system o-xyz is the middle point of the workbench;
s8: the chuck drives the revolving body to rotate by 90 degrees, the cutter checking block is installed in the cutter checking hole of the plane at the uppermost end, and the contact point of the cutter checking block and the milling cutter is ensured to be positioned at a machining point A (x1, y1, z 1);
s9: controlling the milling cutter of the milling machine to move to the cutter checking block, enabling the milling cutter to be in contact with the contact point of the cutter checking block, and recording the coordinates of the milling cutter in the milling machine coordinate system at the moment as machining coordinates (X1, Y1, Z1);
s10: the chuck drives the revolving body to rotate by-90 degrees, and the milling machine drives the milling cutter to process the special-shaped part according to processing coordinates (X1, Y1 and Z1);
s11: after the machining is finished, measuring the coordinates (x2, y2, z2) of the machined point A' in a space rectangular coordinate system o-xyz;
s12: calculating a first machining error coordinate (x2-x1, y2-y1, z2-z1) = (x2, y2, z2) - (x1, y1, z 1);
s13: the chuck drives the revolving body to rotate 180 degrees, the steps S11-S13 are repeated, the coordinates (x3, y3 and z3) of a machining point A '' after the machining of the special-shaped part on the other clamping surface is completed in a space rectangular coordinate system o-xyz are measured, and the second machining error coordinates (x3-x1, y3-y1, z3-z1) = (x3, y3, z3) - (x1, y1 and z1) of the special-shaped part are calculated;
s14: judging whether the first machining error coordinate and the second machining error coordinate are within an error allowable range:
if the first machining error coordinate and the second machining error coordinate both exceed the error allowable range, the machining of the two special-shaped parts is proved to not meet the requirements, the step S4 is returned, the position of the special-shaped part on the clamping surface is adjusted, and the machining coordinate of the milling cutter is positioned again;
if one of the first machining error coordinate and the second machining error coordinate meets an error allowable range, measuring the magnitude of the machining error of the two machined special-shaped parts;
if the machining error corresponding to the first machining error coordinate is minimum, converting the first machining error coordinate into a machining coordinate corrected by the milling cutter in a milling machine coordinate system: (X1-X1+ X2, Y1-Y1+ Y2, Z1-Z1+ Z2) = (X1, Y1, Z1) + (X2-X1, Y2-Y1, Z2-Z1), and the corrected machining coordinates (X1-X1+ X2, Y1-Y1+ Y2, Z1-Z1+ Z2) are used as machining coordinates for machining the special-shaped part at the next time; adjusting the fixed position of the special-shaped part corresponding to the second machining error coordinate on the clamping surface, and aligning the machining point of the special-shaped part to be machined with a coordinate point A' (x2, y2, z2) when the special-shaped part to be machined is fixed;
if the machining error corresponding to the second machining error coordinate is minimum, converting the second machining error coordinate into a machining coordinate corrected by the milling cutter in a milling machine coordinate system: (X1-X1+ X3, Y1-Y1+ Y3, Z1-Z1+ Z3) = (X1, Y1, Z1) + (X3-X1, Y3-Y1, Z3-Z1), and the corrected machining coordinates (X1-X1+ X3, Y1-Y1+ Y3, Z1-Z1+ Z3) are used as machining coordinates for machining the special-shaped part at the next time; and adjusting the fixed position of the special-shaped part corresponding to the first machining error coordinate on the clamping surface, wherein when the fixed position is fixed, the machining point of the special-shaped part to be machined is aligned with the coordinate point A '' (x3, y3, z 3).
The invention has the beneficial effects that: according to the invention, different stations are designed on the same revolving body, so that the numerical control machine tool can be assisted to process airplane special-shaped parts which are difficult to process, multiple clamping and special tools in the processing process are avoided, the processing benefit is improved, and the size precision and the shape and position precision of the parts are ensured. The rotary main body can be provided with two or more stations according to the requirement, the rotary main body is driven to rotate by the rotation of the chuck of the numerical control machine tool, a plurality of parts of the same type are processed at one time, and the working efficiency is greatly improved. The tool has a stable overall structure, components made of different materials can well keep parts stable in the milling engineering of a machine tool, the cutting precision is improved, and the service life of the tool can be prolonged.
The processing method of the invention establishes a spatial rectangular coordinate system on the machine tool workbench to position the processing point of the special-shaped part, establishes a connection with a coordinate system of an auxiliary numerical control machine tool, adjusts the processing coordinate, can gradually reduce the processing error, avoids the processing error caused by inaccurate clamping position, realizes real-time error correction, can use the error of the special-shaped part processed in the previous round to correct the error of the special-shaped part to be processed in the next round, gradually improves the processing precision, constantly ensures the processing precision, and meets the requirement of fine processing of the part on the airplane.
Drawings
Fig. 1 is a structural diagram of an aircraft special-shaped part clamping auxiliary device.
The fixture comprises a chuck 1, a chuck 2, a fixing surface 3, a sinking groove 4, a revolving body 5, a sinking platform 6, a plane 7, a tool checking block 8, a bearing 9, a bearing cover 10, a fixing end 11, a lower seat body 12, a T-shaped groove 13, a workbench 14, a clamping surface 15, a clamping end 16, a bolt hole 17, a fixing boss 18 and a pin hole.
Detailed Description
The following description of the embodiments of the present invention is provided to facilitate the understanding of the present invention by those skilled in the art, but it should be understood that the present invention is not limited to the scope of the embodiments, and it will be apparent to those skilled in the art that various changes may be made without departing from the spirit and scope of the invention as defined and defined in the appended claims, and all matters produced by the invention using the inventive concept are protected.
As shown in fig. 1, the auxiliary device for clamping the special-shaped airplane part comprises a cylindrical revolving body 4, wherein a cylindrical clamping end 15 and a cylindrical fixed end 10 are respectively arranged at two ends of the revolving body 4, and the clamping end 15, the fixed end 10 and the revolving body 4 are coaxial; the clamping end 15 is fixed on a chuck 1 of a machine tool, and the fixed end 10 is arranged on a bearing seat; the surface that is close to stiff end 10 one side on the solid of revolution 4 is provided with two planes 6, two planes 6 are symmetrical with the axis of solid of revolution 4, be provided with on the plane 6 and test the sword hole, it tests sword piece 7 to be provided with on testing the sword hole, equal symmetry is provided with two clamping face 14 between two planes 6, two clamping face 14 and two plane 6 become cross distribution on the outer circumference of solid of revolution 4, a plurality of screw holes have been seted up on the clamping face 14, the both ends of clamping face 14 all are provided with fixed boss 17, fixed boss 17 highly surpasss clamping face 14, two bolt holes 16 have been seted up on fixed boss 17, be provided with pinhole 18 between two bolt holes 16.
The two sides of the clamping surface 14 are provided with the sinking platforms 5, and the two ends of the fixed lug bosses 17 are provided with the sinking grooves 3, so that the milling cutter can move conveniently during processing. The bearing frame includes lower pedestal 11, and the upper end of lower pedestal 11 is provided with the semicircular groove of placing bearing 8, and the upper end of lower pedestal 11 is provided with semicircular bearing cap 9, encapsulates bearing 8 between bearing cap 9 and the semicircular groove, and bearing 8 overlaps on stiff end 10, and bearing cap 9 passes through the bolt fastening under on pedestal 11.
The lower end of the lower seat body 11 is fixed on a workbench 13 of a milling machine, a plurality of parallel fixing grooves are formed in the workbench 13, each fixing groove is a T-shaped groove 12, and the lower end of the lower seat body 11 is fixed on the T-shaped groove 12 through a bolt. One side of the revolving body 4 close to the clamping end 15 is provided with four fixing surfaces 2, and the four fixing surfaces 2 are distributed on the surface of the revolving body 4 in a cross manner, so that the chuck 1 can be conveniently and firmly clamped.
According to the invention, different stations are designed on the same revolving body 4, so that the numerical control machine tool can be assisted to process airplane special-shaped parts which are difficult to process, multiple clamping and special tools in the processing process are avoided, the processing benefit is improved, and the size precision and the shape and position precision of the parts are ensured. The rotary main body can be provided with two or more stations according to the requirement, the rotary main body is driven to rotate by the rotation of the chuck 1 of the numerical control machine tool, a plurality of parts of the same type are processed at one time, and the working efficiency is greatly improved. The tool has a stable overall structure, components made of different materials can well keep parts stable in the milling engineering of a machine tool, the cutting precision is improved, and the service life of the tool can be prolonged.
In this embodiment, the clamping method for machining the special-shaped part of the aircraft landing gear by using the auxiliary device for clamping the special-shaped part of the aircraft includes the following steps:
s1: taking the processed revolving body 4, assembling the fixed end 10 into the bearing 8, packaging the bearing 8 on the bearing seat, and fixing the bearing 8 by the bearing cover 9 through bolts;
s2: fixing a clamping end 15 of the revolving body 4 on a chuck 1 of a milling machine, and mounting a level gauge on the revolving body 4;
s3: the height of the bearing seat and the position on a workbench 13 of the milling machine are adjusted by a reference level gauge, the axis of the revolving body 4 is ensured to be coincided with the rotating central line of the chuck 1, and the lower seat body 11 is fixed on the T-shaped groove 12 through a bolt;
s4: taking a special-shaped part to be processed, positioning by using pin holes 18 at two ends of a clamping surface 14, fixing two ends of the special-shaped part on a fixing boss 17 through bolts, and locking the middle part of the special-shaped part on the clamping surface 14 through a screw;
s5: repeating the step S4, and mounting the special-shaped parts to be processed on the two clamping surfaces 14 on the revolving body 4;
s6: the chuck 1 drives the revolving body 4 to rotate, and a level is referred to, so that the special-shaped part on one clamping surface 14 is positioned right above the revolving body 4, and a machining point A of the special-shaped part needing milling cutter machining is determined;
s7: taking a worktable 13 in the milling machine as an xoy reference plane 6, measuring coordinates (x1, y1, z1) of a processing point A in a space rectangular coordinate system o-xyz, wherein the origin of the coordinates of the space rectangular coordinate system o-xyz is the middle point of the worktable 13, and the x axis, the y axis and the z axis of the space rectangular coordinate system o-xyz are all parallel to the coordinate system of the milling machine;
s8: the chuck 1 drives the revolving body 4 to rotate 90 degrees, the cutter checking block 7 is installed in the cutter checking hole of the uppermost plane 6, and the point where the cutter checking block 7 contacts with the milling cutter is ensured to be positioned at a machining point A (x1, y1, z 1);
s9: controlling the milling cutter of the milling machine to move to the cutter checking block 7, enabling the milling cutter to be in contact with the contact point of the cutter checking block 7, recording the coordinates of the milling cutter in the milling machine coordinate system at the moment, and taking the coordinates as machining coordinates (X1, Y1, Z1);
s10: the chuck 1 drives the revolving body 4 to rotate by-90 degrees, and the milling machine drives the milling cutter to process the special-shaped part according to processing coordinates (X1, Y1 and Z1);
s11: after the machining is finished, measuring the coordinates (x2, y2, z2) of the machined point A' in a space rectangular coordinate system o-xyz; if an error exists during clamping, the machining point A' and the machining point A deviate, so that the error is generated;
s12: calculating a first machining error coordinate (x2-x1, y2-y1, z2-z1) = (x2, y2, z2) - (x1, y1, z 1);
s13: the chuck 1 drives the rotator 4 to rotate 180 degrees, repeats steps S10-S12, measures the coordinates (x3, y3, z3) of the machined point a ″ of the special-shaped part on the other clamping surface 14 in the spatial rectangular coordinate system o-xyz, and calculates the second machining error coordinates (x3-x1, y3-y1, z3-z1) = (x3, y3, z3) - (x1, y1, z1) of the special-shaped part;
s14: judging whether the first machining error coordinate and the second machining error coordinate are within an error allowable range:
if the first machining error coordinate and the second machining error coordinate both exceed the error allowable range, the machining of the two special-shaped parts is proved to not meet the requirements, the step S4 is returned, the position of the special-shaped part on the clamping surface 14 is adjusted, and the machining coordinate of the milling cutter is positioned again;
if one of the first machining error coordinate and the second machining error coordinate meets an error allowable range, measuring the magnitude of the machining error of the two machined special-shaped parts;
if the machining error corresponding to the first machining error coordinate is minimum or equal to the first machining error coordinate, converting the first machining error coordinate into a machining coordinate corrected by the milling cutter in a milling machine coordinate system: (X1-X1+ X2, Y1-Y1+ Y2, Z1-Z1+ Z2) = (X1, Y1, Z1) + (X2-X1, Y2-Y1, Z2-Z1), and the corrected machining coordinates (X1-X1+ X2, Y1-Y1+ Y2, Z1-Z1+ Z2) are used as machining coordinates for machining the special-shaped part at the next time; adjusting the fixed position of the special-shaped part corresponding to the second machining error coordinate on the clamping surface 14, wherein when the fixed position is fixed, the machining point of the special-shaped part to be machined is aligned with the coordinate point A' (x2, y2, z 2);
if the machining error corresponding to the second machining error coordinate is minimum, converting the second machining error coordinate into a machining coordinate corrected by the milling cutter in a milling machine coordinate system: (X1-X1+ X3, Y1-Y1+ Y3, Z1-Z1+ Z3) = (X1, Y1, Z1) + (X3-X1, Y3-Y1, Z3-Z1), and the corrected machining coordinates (X1-X1+ X3, Y1-Y1+ Y3, Z1-Z1+ Z3) are used as machining coordinates for machining the special-shaped part at the next time; the fixed position of the special-shaped part corresponding to the first machining error coordinate on the clamping surface 14 is adjusted, and when the fixed position is fixed, the machining point of the special-shaped part to be machined is aligned with the coordinate point A '' (x3, y3, z 3).
The processing clamping method of the invention utilizes a space rectangular coordinate system established on the machine tool workbench 13 to position the processing point of the special-shaped part, establishes a connection with the coordinate system of an auxiliary numerical control machine tool, adjusts the processing coordinate, can gradually reduce the processing error, avoids the processing error caused by inaccurate clamping position, realizes real-time error correction, can be used for correcting the error of the special-shaped part to be processed in the next round, gradually improves the processing precision, constantly ensures the processing precision, and meets the requirement of fine processing of the part on the airplane.
While there have been shown and described what are at present considered the fundamental principles and essential features of the invention and its advantages, it will be apparent to those skilled in the art that the invention is not limited to the details of the foregoing exemplary embodiments, but is capable of other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (5)
1. A clamping method for processing an aircraft undercarriage special-shaped part by using an aircraft special-shaped part clamping auxiliary device is characterized in that the aircraft special-shaped part clamping auxiliary device comprises a cylindrical revolving body, two ends of the revolving body are respectively provided with a cylindrical clamping end and a cylindrical fixed end, and the clamping end, the fixed end and the revolving body are coaxial; the clamping end is fixed on a chuck of the machine tool, and the fixed end is arranged on the bearing seat; the surface of one side, close to the fixed end, of the revolving body is provided with two planes, the two planes are symmetrical with the axis of the revolving body, the planes are provided with tool checking holes, the tool checking holes are provided with tool checking blocks, two clamping surfaces are symmetrically arranged between the two planes, the two clamping surfaces and the two planes are distributed on the outer circumference of the revolving body in a cross shape, the clamping surfaces are provided with a plurality of screw holes, two ends of each clamping surface are provided with fixing bosses, the heights of the fixing bosses exceed the clamping surfaces, the fixing bosses are provided with two bolt holes, and a pin hole is formed between the two bolt holes;
the clamping method for machining the special-shaped part of the aircraft landing gear by using the special-shaped part clamping auxiliary device comprises the following steps:
s1: assembling the fixed end of the machined revolving body into a bearing, packaging the bearing on a bearing seat, and fixing the bearing through a bolt by a bearing cover;
s2: fixing the clamping end of the revolving body on a chuck of a milling machine, and mounting a level gauge on the revolving body;
s3: the height of the bearing seat and the position of the bearing seat on a workbench of the milling machine are adjusted by the reference level gauge, the axis of the revolving body is ensured to be coincided with the rotating central line of the chuck, and the lower seat body is fixed on the T-shaped groove through a bolt;
s4: taking a special-shaped part to be processed, positioning by using pin holes at two ends of a clamping surface, fixing two ends of the special-shaped part on a fixed boss through bolts, and locking the middle part of the special-shaped part on the clamping surface through a screw;
s5: repeating the step S4, and mounting the special-shaped parts to be processed on the two clamping surfaces of the revolving body;
s6: the chuck drives the revolving body to rotate, and a level is referred to, so that the special-shaped part on one clamping surface is positioned right above the revolving body, and a processing point A of the special-shaped part needing to be processed by the milling cutter is determined;
s7: taking a workbench in the milling machine as an xoy reference plane, measuring coordinates (x1, y1, z1) of a processing point A in a space rectangular coordinate system o-xyz, wherein the origin of the coordinates of the space rectangular coordinate system o-xyz is the middle point of the workbench;
s8: the chuck drives the revolving body to rotate by 90 degrees, the cutter checking block is installed in the cutter checking hole of the plane at the uppermost end, and the contact point of the cutter checking block and the milling cutter is ensured to be positioned at a machining point A (x1, y1, z 1);
s9: controlling a milling cutter of the milling machine to move to the cutter checking block, enabling the milling cutter to be in contact with the contact point of the cutter checking block, and recording the coordinates of the milling cutter in a milling machine coordinate system at the moment as machining coordinates (X1, Y1, Z1);
s10: the chuck drives the revolving body to rotate by-90 degrees, and the milling machine drives the milling cutter to process the special-shaped part according to processing coordinates (X1, Y1 and Z1);
s11: after the machining is finished, measuring the coordinates (x2, y2, z2) of the machined point A' in a space rectangular coordinate system o-xyz;
s12: calculating first machining error coordinates (x2-x1, y2-y1, z2-z1) ═ x2, y2, z2) - (x1, y1, z 1;
s13: the chuck drives the revolving body to rotate 180 degrees, the steps S11-S13 are repeated, the coordinates (x3, y3 and z3) of a machining point A' in a space rectangular coordinate system o-xyz after the machining of the special-shaped part on the other clamping surface is completed are measured, and the second machining error coordinates (x3-x1, y3-y1 and z3-z1) of the special-shaped part are calculated as (x3, y3, z3) - (x1, y1 and z 1);
s14: judging whether the first machining error coordinate and the second machining error coordinate are within an error allowable range:
if the first machining error coordinate and the second machining error coordinate both exceed the error allowable range, the machining of the two special-shaped parts is proved to not meet the requirements, the step S4 is returned, the position of the special-shaped part on the clamping surface is adjusted, and the machining coordinate of the milling cutter is positioned again;
if one of the first machining error coordinate and the second machining error coordinate meets an error allowable range, measuring the magnitude of the machining error of the two machined special-shaped parts;
if the machining error corresponding to the first machining error coordinate is minimum, converting the first machining error coordinate into a machining coordinate corrected by the milling cutter in a milling machine coordinate system: (X1-X1+ X2, Y1-Y1+ Y2, Z1-Z1+ Z2) ═ X1, Y1, Z1) + (X2-X1, Y2-Y1, Z2-Z1), and the corrected machining coordinates (X1-X1+ X2, Y1-Y1+ Y2, Z1-Z1+ Z2) are used as machining coordinates for machining the special-shaped part at the next time; adjusting the fixed position of the special-shaped part corresponding to the second machining error coordinate on the clamping surface, and aligning the machining point of the special-shaped part to be machined with a coordinate point A' (x2, y2, z2) when the special-shaped part to be machined is fixed;
if the machining error corresponding to the second machining error coordinate is minimum, converting the second machining error coordinate into a machining coordinate corrected by the milling cutter in a milling machine coordinate system: (X1-X1+ X3, Y1-Y1+ Y3, Z1-Z1+ Z3) ═ X1, Y1, Z1) + (X3-X1, Y3-Y1, Z3-Z1), and the corrected machining coordinates (X1-X1+ X3, Y1-Y1+ Y3, Z1-Z1+ Z3) are used as machining coordinates for machining the special-shaped part at the next time; and adjusting the fixed position of the special-shaped part corresponding to the first machining error coordinate on the clamping surface, wherein when the fixed position is fixed, the machining point of the special-shaped part to be machined is aligned with the coordinate point A' (x3, y3, z 3).
2. The method for clamping the special-shaped part of the aircraft landing gear by using the auxiliary device for clamping the special-shaped part of the aircraft as claimed in claim 1, wherein sinking platforms are arranged on two sides of the clamping surface, and sinking grooves are arranged on two ends of the fixing boss.
3. The method as claimed in claim 1, wherein the bearing seat comprises a lower seat body, a semicircular groove is formed in an upper end of the lower seat body, a semicircular bearing cover is arranged on an upper end of the lower seat body, the bearing is packaged between the bearing cover and the semicircular groove, the bearing is sleeved on a fixed end, and the bearing cover is fixed on the lower seat body through a bolt.
4. The method as claimed in claim 3, wherein the lower end of the lower base body is fixed on a workbench of a milling machine, the workbench is provided with a plurality of parallel fixing grooves, the fixing grooves are T-shaped grooves, and the lower end of the lower base body is fixed on the T-shaped grooves through bolts.
5. The method for clamping the special-shaped part of the aircraft landing gear by using the auxiliary device for clamping the special-shaped part of the aircraft as claimed in claim 1, wherein the revolving body is provided with four fixing surfaces on one side close to the clamping end, and the four fixing surfaces are distributed on the surface of the revolving body in a cross manner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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