CN108214002A - A kind of weak rigid machining distortion for aeronautical monolithic component control method - Google Patents
A kind of weak rigid machining distortion for aeronautical monolithic component control method Download PDFInfo
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- CN108214002A CN108214002A CN201711485021.7A CN201711485021A CN108214002A CN 108214002 A CN108214002 A CN 108214002A CN 201711485021 A CN201711485021 A CN 201711485021A CN 108214002 A CN108214002 A CN 108214002A
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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
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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
- B23Q1/00—Members which are comprised in the general build-up of a form of machine, particularly relatively large fixed members
- B23Q1/03—Stationary work or tool supports
- B23Q1/035—Stationary work or tool supports with an array of longitudinally movable rods defining a reconfigurable support surface
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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
- B23Q1/00—Members which are comprised in the general build-up of a form of machine, particularly relatively large fixed members
- B23Q1/03—Stationary work or tool supports
- B23Q1/037—Stationary work or tool supports comprising series of support elements whose relative distance is adjustable
-
- 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
- B23Q17/00—Arrangements for observing, indicating or measuring on machine tools
- B23Q17/002—Arrangements for observing, indicating or measuring on machine tools for indicating or measuring the holding action of work or tool holders
- B23Q17/005—Arrangements for observing, indicating or measuring on machine tools for indicating or measuring the holding action of work or tool holders by measuring a force, a pressure or a deformation
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Abstract
The invention discloses a kind of weak rigid machining distortion for aeronautical monolithic component control methods, part internal stress is discharged after roughing, then fixture clamping position is adjusted according to part weight distribution after part deformation state and roughing, make that inner stress of work field fully balances, machining deformation fully discharges, it is finished later, it can realize effective control of machining deformation, ensure final part processing precision.
Description
Technical field
The present invention relates to technical fields of mechanical processing, and in particular to a kind of weak rigid machining distortion for aeronautical monolithic component of large size
Control method.
Background technology
With the fast development of aircraft industry, the whole aerospace component of large size being directly process by Mega-boule is
It is widely used in modern passenger aircraft and fighter plane.Be conducive to lift fuselage intensity and reliability using large aerospace structural member, subtract
Light body weight reduces number of parts and assembly work amount etc., but because of factors such as its size is big, material removing rate is high, poor rigidities,
Large aerospace structural member machining deformation is often difficult to control.
Machining distortion for aeronautical monolithic component is overproof to be influenced subsequent parts assembling and part military service performance or even cause safe thing
Therefore.Therefore it after aerospace component machines, is required for testing its Form and position error, and to deforming slight overproof zero
Part corrects shape.But current school shape technique is also and immature, needs to expend a large amount of manpower and materials, and by introducing plastic deformation
Bearing calibration is easy to cause part macroscopic view or microcosmic damage, brings security risk, therefore processing is become in process
Shape control extremely important, can greatly improve the manufacture efficiency and quality of aerospace component.Cause using aerospace component as
The principal element of the thin-wall part overall processing deformation of representative is the differentiation of inner stress of work field in process, and rolling, is forged at casting
Make and it is various heat treatment and cold working large-scale residual stress can be all introduced in workpiece blank, which exists
It is self-balancing state before processing.Boundary condition caused by cutting force, thermal force and lot of materials remove in cutting process
The factors such as variation can break the former equilibrium state of the primary stress, and inner stress of work field develops the process for reaching new equilibrium state
In cause the deformation of workpiece.Because material removal is uneven, machining deformation is especially apparent single side frame structure aerospace component.
In production practices, technical staff has summed up a kind of effective machining deformation control method, i.e., thick, smart
Between manufacturing procedure, clamping is discharged, part is stood, its internal stress is made fully to discharge, the then deformation according to caused by stress release
State adjustment clamping is finished, and is deformed caused by preamble processing is cut off in finishing passes, can be reduced so final
Machining deformation.This stress release and clamping adjustment operation are high to the requirement of the technical merit of worker, less efficient and again
The deflection introduced in clamping process is difficult to estimate and control.There is the adjustable fixture that researcher starts research and development automation,
X, Y, the Z coordinate of clamping position can be adjusted in process, realization " unstressed clamping " is aimed at or " low stress fills
Folder ".
For large-scale weak rigid aerospace component, " unstressed " or " low stress " dress is blindly pursued in clamping process
Folder does not ensure that obtain optimal machining deformation control effect, and under certain supporting condition, large thin-wall element is in gravity
Under deflection deformation can occur.Therefore, machining deformation is effectively controlled, needs the more stress release of science and fixture adjustment side
Method.
Invention content
In view of this, the present invention provides a kind of weak rigid machining distortion for aeronautical monolithic component control method, it can realize and add
Effective control of work deformation, ensures final part processing precision.
Specific embodiments of the present invention are as follows：
A kind of weak rigid machining distortion for aeronautical monolithic component control method, the control method is discharges part after roughing
Then internal stress adjusts fixture clamping position according to part weight distribution after part deformation state and roughing, carries out later
Finishing.
Further, part weight distribution carries out model solution using finite element software after the roughing.
Further, the control method step is as follows：
Parts to be processed is fixed on platen by step 1, equating fixation surface using adjustable clamp system,
Make parts to be processed parallel with platen, and the X of each fixture unit in adjustable clamp system, Y-direction clamping power are
Zero or the threshold value less than setting；
Step 2 carries out roughing；
Step 3, using finite element software to the part modeling after roughing, and it is each under the effect of gravity to solve part
The power that fixture unit is born；
Step 4 adjusts the clamping position of deformation position fixture unit, and X, Y-direction clamping power is made to be zero or the threshold less than setting
Value, Z-direction clamping power are equal to the power or set with the difference of the power that obtained each fixture unit is born in step 3
Within the scope of；
Step 5 is finished, and part is removed after processing.
Further, further comprise after the step 5, using adjustable clamp system by parts to be processed turn-over
It is fixed on platen, then equating turn-over is processed.
Further, the adjustable clamp system includes three stationary fixture units and floating holder unit, geometrical clamp
Tool unit is arranged on the center of parts to be processed, distribution triangular in shape；Floating holder unit is arranged on the periphery of parts to be processed；
When adjusting clamping position, stationary fixture unit is motionless, adjusts the position of floating holder unit.
Further, the fixture unit detects clamping power by the three-dimensional force transducer set on fixture unit.
Further, the step 1 and step 4 further comprise, using the prod installed in machine tool chief axis, surveying
Measure the Z-direction contact force of fixture unit.
Further, by cushion block being set to increase Z-direction displacement under fixture unit.
Further, if the clamping position by adjusting fixture unit is unable to control deformation, by adjusting processing technology
Control deformation.
The fixture unit includes coordinate regulating member, three-dimensional force transducer and clamping component；
Further, coordinate regulating member includes X to motion guide rail, Y-direction motion guide rail and Z-direction movable cylinder；X is led to movement
Rail is arranged on Y-direction motion guide rail bottom, and Y-direction motion guide rail is fixedly connected by Z-direction movable cylinder with three-dimensional force transducer, three axis force
Sensor is fixedly connected with clamping component, and clamping component side walls are equipped with air pump interface, and clamping component top is equipped with aspirating hole and spiral shell
Pit, and sealed by sealing ring.
Advantageous effect：
1st, the present invention considers the deflection deformation occurred under the effect of gravity, according to after part deformation state and roughing zero
Part weight distribution adjusts fixture clamping position, makes that inner stress of work field fully balances, machining deformation fully discharges, it is ensured that secondary dress
In clip process, frock clamp is solely subjected to part gravity so as to reduce secondary clamping stress, so can effectively be cut in finishing
Except the machining deformation of preamble processing introducing, ensure final part processing precision.
2nd, stationary fixture unit distribution triangular in shape, the plane formed can be used as fixed Set and Positioning benchmark, with work
Dynamic fixture unit jointly provides part enough fix and support.Moreover, fixation can be realized pair by the way of vacuumizing
Parts to be processed is reliably fixed.
3rd, the present invention is assisted when adjusting fixture unit clamping position using lathe so that measurement result is more smart
Really.
Description of the drawings
Fig. 1 is the structure diagram of fixture unit used by machining deformation control method of the present invention；
Fig. 2 (I) is the green state schematic diagram of the embodiment of the present invention；
Fig. 2 (II) is the status diagram after roughing of the embodiment of the present invention；
Fig. 2 (III) is the status diagram after finishing of the embodiment of the present invention；
Fig. 3 is clamping position schematic diagram in the embodiment of the present invention；
Fig. 4 is the exemplary plot for carrying out finite element analysis in the embodiment of the present invention to model after roughing；
Fig. 5 is the schematic diagram of reverse side processing midfoot support three kinds of situations of fixing means in the embodiment of the present invention.
Wherein, 101- work stages, 102- sealing rings, 103- threaded holes, 104- aspirating holes, 105- air pump interfaces, 106- tri-
To force snesor, 107-Z is to movable cylinder, and 108-X is to motion guide rail, and 109-Y is to motion guide rail, 201- blanks, 202- activities
Fixture unit, 203- platens, 204- stationary fixture units, the part after 205- roughing, 206- fronts machine
Part afterwards, 301~316 be floating holder unit clamping position, and 317~319 be stationary fixture unit clamping position, and 401- is thick
Part limit element artificial module after processing；402- fixture unit simplified models；403- platen simplified models, 501- fronts
The part of turn-over after the completion of finishing, 502- stationary fixture units, 503- cushion blocks.
Specific embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
The mechanism of production of the overall processing deformation of large-scale weak rigid aerospace component is the work containing initial residual stress
Part blank, constraints variation etc. caused by clamping power load, cutting force load, cutting thermal force and lot of materials remove
Under the combined influence of factor, internal stress field gradually develops, and is machining, after removal clamping, internal stress field into
One step develops and causes part deformation, is finally reached the force self-balanced state of planted agent.
The present invention provides a kind of weak rigid machining distortion for aeronautical monolithic component control method, based on adjustable clamp system,
The adjustable clamp system is made of several fixture units, and adjustable clamp system can include having two kinds of fixing means
Fixture unit, respectively using the fixed stationary fixture unit of vacuum cup and the floating holder unit that is fixed by bolts or
On same fixture unit, fixture unit includes coordinate regulating member, 106 and of three-dimensional force transducer to person for design as shown in Figure 1
Clamping component；Coordinate regulating member includes X to motion guide rail 108, Y-direction motion guide rail 109 and Z-direction movable cylinder 107；X is to movement
Guide rail 108 is arranged on 109 bottom of Y-direction motion guide rail, and Y-direction motion guide rail 109 passes through Z-direction movable cylinder 107 and three-dimensional force transducer
106 are fixedly connected, and three-dimensional force transducer 106 is fixedly connected with clamping component, and clamping component includes work stage 101 and sealing ring
102,101 top of work stage is equipped with aspirating hole 104 and threaded hole 103, and pass through sealing ring 102 and seal, and 101 side wall of work stage is set
There is air pump interface 105.Three-dimensional force transducer 106 is for detecting clamping power, with fixture unit free state lower sensor X, Y, Z-direction
Power numerical value is zero.After coordinate regulating member is fixed in work stage 101, X, Y, the Z-direction of practical clamping position can be adjusted
Coordinate, the adjusting can be realized, and can be with latched position by the methods of manual adjustment or automatically controlled, pneumatic, hydraulic pressure.Fixture list
The X of member is to motion guide rail 108 and 203 mobilizable connection of platen.Platen 203 is equipped with and fixture unit
The a plurality of tracks that X matches to motion guide rail 108, the X of clamping apparatus unit to motion guide rail 108 can be moved, also may be used in X direction
With in different track up conversions.
The principle of the present invention is：Using the structure gravity that each fixture unit should be born as adjust its Z-direction position according to
According to.It is illustrated using the more significant single side frame structure aerospace component of machining deformation as embodiment.Have the one of frame structure
Face is known as front in the following description, and the one side of massive plate structure is known as reverse side.
Specific machining control deformation method is as follows：
A the blank of suitable dimension) is selected according to parts to be processed design requirement, aluminium alloy prestretching is used in the present embodiment
Plank is stretched as blank material, on parts to be processed size basis, reserves the material that allowance and false boss need.Hair
After base blanking, equating blank reverse side surface, shown position 301~316 according to fig. 3, in blank peripheral position spot-facing, for bolt
It is fixed.
B clamping technique for fixing) is determined according to parts to be processed and blank structure size.On the table, blank center
Near position, i.e. 317~319 positions in Fig. 3 set 3 stationary fixture units for having vacuum cup clamping function, this 3
A fixture unit distribution triangular in shape, the plane formed is as fixed Set and Positioning benchmark；On the table, blank periphery,
301~316 position in Fig. 3, setting 16 there is bolt clamping floating holder units (length direction per side setting 6,
Width direction sets 2 per side).Altogether using 19 fixture units, enough fix and support is provided part.For length and width
It is fixed using sucker can to place several more on platen, part the bottom surface for the larger aerospace component of size
Floating holder unit, to ensure having enough supports to part in process, reduction allows the mismachining tolerances such as knife deformation.
C 19 fixture units) are fixed on platen 203, in the cylindrical prod of machine tool chief axis installation, adjustment
Machine tool chief axis Z coordinate makes distance of the test plane rod end apart from work top be equal to the height of fixture unit free state.Adjustment machine
Bed major axis X, Y-direction coordinate are directed at the work stage 101 of each fixture unit successively, adjust the Z of each fixture unit work stage 101
Coordinate ensures that the Z coordinate of all clamp workpiece platforms 101 is identical, while the upper surface of work stage 101 is made to be contacted with test plane rod end
And 5 Ns of Z-direction contact force is generated, locking fixture unit Z-direction displacement after the completion of adjusting.
D) blank 201 is fixed in adjustable clamp system, the floating holder unit in Fig. 3 at position 301~316
202 are fixed using bolt, and the stationary fixture unit 204 at position 317~319 uses and vacuumizes secured blank part 201, and utilize
Sealing ring 102 seals, in the present embodiment shown in stationary state such as Fig. 2 (I).
E after the completion of) blank is fixed, X, the Y-direction position of each fixture unit are adjusted, and detect three-dimensional force transducer 106
Dynamometry numerical value, it is ensured that X, Y-direction clamping power are less than 5 Ns.
F it) according to design of part Identity Plan roughing technique, is removed using higher material is reached by the method that chamber is processed
Efficiency according to design of part feature and blank material residual stress level in roughing, retains more than 3mm, suitable surplus,
The aluminum alloy pre-stretching plate residual stress level applied in the present embodiment is relatively low, and allowance could be provided as 3mm.Roughing
Shown in 205 state of part such as Fig. 2 (II) afterwards.
G 1) is pressed in Solidworks softwares:1 ratio creates the geometrical model of part after roughing, is analyzed to improve
Efficiency has carried out simplified processing to features such as small round corner, the apertures in model；It builds and supports flat plate model, letter in the present embodiment
Turn to massive plate；Fixture unit simplified model 402 is built, cylinder is reduced in the present embodiment, structure platen simplifies
Model 403, as shown in Figure 4.Part model is assembled according to practical clamping strategy, part finite element is imitated after forming roughing
True mode 401.Model is imported in finite element emulation software ANSYS, setting workpiece material, contact performance and boundary constraint, with
3 points of stationary fixture unit clamping position are applied gravity (being added in a manner of acceleration of gravity), submitted as boundary condition
Analytic operation handles result, extracts each fixture unit and element stress information on feature contacts face, solves each connect
The power effect of contacting surface, i.e., the part gravity numerical value that each fixture unit is born.
H) 3 stationary fixture units are fixed, adjust X, Y, the Z-direction position of 16 floating holder units, observe simultaneously
The dynamometry numerical value of three-dimensional force transducer 106, it is ensured that X, Y-direction clamping power be less than 5 Ns, is calculated in Z-direction clamping power and step G
It is less than 5 Ns corresponding to the difference of the contact force of each floating holder unit.
I) using the method successively processed, part Facad structure finishing, state such as Fig. 2 (III) after the completion of finishing are carried out
It is shown, clamping is discharged after machining and removes the part 206 after front machines.
J part) is processed according to reverse side and fixes needs, adjusts the X of floating holder unit, Y-direction position (technique in the present embodiment
Boss is symmetrically arranged, so without adjustment).In the cylindrical prod of machine tool chief axis installation, machine tool chief axis Z coordinate is adjusted, is made
Test the height that distance of the plane rod end apart from work top is equal to fixture unit free state.Machine tool chief axis X, Y-direction coordinate are adjusted,
It is directed at the work stage 101 of each floating holder unit successively, adjusts the Z coordinate of each fixture unit work stage 101, makes work stage
101 upper surface contacts with test plane rod end and generates 5 Ns of Z-direction contact force, and each floating holder list is locked after the completion of adjusting
First Z-direction displacement.Part front main body is frame structure in the present embodiment, so reverse side processing needs to carry out in part web position
It is fixed.X, the Y-direction position of stationary fixture unit are adjusted, avoids feature side-wall.Machine tool chief axis Z coordinate is adjusted, makes test plane rod end
Distance apart from work top is equal to depth of the height plus part front chamber of fixture unit free state.Adjust machine tool chief axis
X, Y coordinate is allowed to be aligned each stationary fixture unit, and the Z coordinate of adjustment stationary fixture unit work stage 101 makes work stage 101
Upper surface contact with test plane rod end and generates 5 Ns of Z-direction contact force, adjust and lock each stationary fixture unit Z after the completion
To displacement.It, can be in the specific height of 502 underlay of stationary fixture unit when fixture unit Z-direction adjustment stroke is less than part cavities depth
The cushion block 503 of degree, the 501 installation way schematic diagram of part of turn-over is as shown in Figure 5 after the completion of the finishing of front.After adjustment is complete,
The position of fixed each fixture unit.
K) blank reverse side is fixed on fixture unit, is fixed at 16 floating holder units with bolt, 3 stationary fixtures
It is fixed at unit with vacuum cup.Equating part reverse side surface (bottom surface) after the completion of clamping.
L it) is required, part processing Form and position error etc. is tested, as become according to the processing quality of aerospace component
Shape is excessive or crosses situations such as cutting, owing to cut, the roughing surplus in suitably increasing step F in subsequent parts processing；If pass through control
Allowance processed is still unable to control deformation, then needs to be adjusted processing technology and optimize, such as to the batch blank material
Residual stress test is carried out, blank material is needed replacing if test failure or before processing blank material answer
Power processing.
In conclusion the foregoing is merely a prefered embodiment of the invention, it is not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in the present invention's
Within protection domain.
Claims (10)
1. a kind of weak rigid machining distortion for aeronautical monolithic component control method, which is characterized in that the control method is in roughing
Part internal stress is discharged afterwards, and fixture clamping position is then adjusted according to part weight distribution after part deformation state and roughing
It puts, is finished later.
2. weak rigid machining distortion for aeronautical monolithic component control method as described in claim 1, which is characterized in that the roughing
Part weight distribution carries out model solution using finite element software afterwards.
3. weak rigid machining distortion for aeronautical monolithic component control method as claimed in claim 2, which is characterized in that the controlling party
Method step is as follows：
Parts to be processed using adjustable clamp system is fixed on platen, makes to treat by step 1, equating fixation surface
Process part it is parallel with platen, and the X of each fixture unit in adjustable clamp system, Y-direction clamping power be zero or
Less than the threshold value of setting；
Step 2 carries out roughing；
Step 3 using finite element software to the part modeling after roughing, and solves part each fixture under the effect of gravity
The power that unit is born；
Step 4 adjusts the clamping position of deformation position fixture unit, and X, Y-direction clamping power is made to be zero or the threshold value less than setting, Z
To clamping power be equal to obtained each fixture unit is born in step 3 power or with the difference of the power setting model
Within enclosing；
Step 5 is finished, and part is removed after processing.
4. weak rigid machining distortion for aeronautical monolithic component control method as claimed in claim 3, which is characterized in that the step 5
Further comprise later, parts to be processed turn-over be fixed on platen using adjustable clamp system, equating turn-over,
Then it is processed.
5. weak rigid machining distortion for aeronautical monolithic component control method as claimed in claim 3, which is characterized in that described adjustable
Chucking appliance system includes three stationary fixture units and floating holder unit, and stationary fixture unit is arranged in parts to be processed
The heart, distribution triangular in shape；Floating holder unit is arranged on the periphery of parts to be processed；When adjusting clamping position, stationary fixture list
Member is motionless, adjusts the position of floating holder unit.
6. weak rigid machining distortion for aeronautical monolithic component control method as claimed in claim 3, which is characterized in that the fixture list
Member detects clamping power by the three-dimensional force transducer set on fixture unit.
7. weak rigid machining distortion for aeronautical monolithic component control method as claimed in claim 3, which is characterized in that the step 1
Further comprise utilizing the prod installed in machine tool chief axis, the Z-direction contact force of measured material unit with step 4.
8. the weak rigid machining distortion for aeronautical monolithic component control method as described in claim 3 or 4, which is characterized in that by
Cushion block is set to increase Z-direction displacement under fixture unit.
9. weak rigid machining distortion for aeronautical monolithic component control method as claimed in claim 3, which is characterized in that if by adjusting
The clamping position of fixture unit is unable to control deformation, then is deformed by adjusting control process.
10. weak rigid machining distortion for aeronautical monolithic component control method as claimed in claim 6, which is characterized in that the fixture
Unit includes coordinate regulating member, three-dimensional force transducer and clamping component；
Coordinate regulating member includes X to motion guide rail, Y-direction motion guide rail and Z-direction movable cylinder；X is arranged on Y-direction fortune to motion guide rail
Dynamic guide rail bottom, Y-direction motion guide rail are fixedly connected by Z-direction movable cylinder with three-dimensional force transducer, three-dimensional force transducer and clamping
Component is fixedly connected, and clamping component side walls are equipped with air pump interface, and clamping component top is equipped with aspirating hole and threaded hole, and passes through close
Seal seals.
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| CN109648369A (en) * | 2019-01-21 | 2019-04-19 | 南京航空航天大学 | A kind of two-sided machining deformation control method and equipment |
| CN111941103A (en) * | 2020-08-19 | 2020-11-17 | 山东理工大学 | Tandem type bidirectional constant machining force adjusting platform for cutting machining |
| CN111941147A (en) * | 2020-08-18 | 2020-11-17 | 山东理工大学 | Floating directional machining force measuring and compensating table for cutting machining |
| CN111993095A (en) * | 2020-08-26 | 2020-11-27 | 山东理工大学 | Bidirectional machining force adjusting platform for cutting machining |
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| CN111993097A (en) * | 2020-08-18 | 2020-11-27 | 山东理工大学 | Plane constant force machining adjusting platform for cutting machining |
| CN111993097B (en) * | 2020-08-18 | 2022-04-29 | 山东理工大学 | Plane constant force machining adjusting platform for cutting machining |
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Application publication date: 20180629 |