CN106541591A - A kind of middle part bogey in the forming process for airframe - Google Patents
A kind of middle part bogey in the forming process for airframe Download PDFInfo
- Publication number
- CN106541591A CN106541591A CN201611220348.7A CN201611220348A CN106541591A CN 106541591 A CN106541591 A CN 106541591A CN 201611220348 A CN201611220348 A CN 201611220348A CN 106541591 A CN106541591 A CN 106541591A
- Authority
- CN
- China
- Prior art keywords
- bearing
- roller
- bearing assembly
- axle
- fuselage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Rolling Contact Bearings (AREA)
Abstract
The invention discloses the middle part bogey in a kind of forming process for airframe, belongs to fiber placement and apparatus field.It includes installation pedestal component, left bearing assembly and right bearing assembly.When fuselage does gyration under machine spindle drive, left bearing assembly, right bearing assembly are in main shaft both sides to the real-time carrying of fuselage, according to the position between two bearing wheels of fuselage attitude adjust automatically, it is rolling friction between fuselage and left bearing assembly and right bearing assembly.Apparatus of the present invention are suitable as the auxiliary device of fuselage numerical control former, it is mainly used in improving system stiffness and automaticity during fuselage laying forming, while the load bearing equipment can be additionally used in, and the weak rigid workpiece of other convex surfaces is Wrapping formed, and the auxiliary bogey of cutting process.
Description
Technical field
The invention belongs to aircraft manufacturing technical field, and in particular to the middle part in a kind of forming process for airframe carries
Device.
Background technology
Aeronautical and space technology is one of eight big cutting edge technology field of current China, and aerospace industries capacity for technological innovation is such as
What directly influences the international competitiveness and power of influence of national defense safety and a state.Aircraft forming technique is used as in aeronautical and space technology
One, represent the strength and power of influence of a state aviation technical field.Traditional aircaft configuration is using alloy material, knot
The metal materials such as structure steel, have many defects, and such as technological process is complicated, and difficulty of processing is big, long the production cycle, and quality is again etc..
The appearance of composite has great significance for the rapid shaping of aircraft.Composite has specific strength and specific modulus high,
And extensive material designability and it is easy to many excellent specific properties such as global formation.Use it on aircaft configuration, than often
The metal structure loss of weight 20%～30% of rule, and aircraft aeroelastic characteristic is can obviously improve, improve aeroplane performance.Meanwhile, by
There is more preferable resisting fatigue and anticorrosion properties in composite, rational life-span and the peace that aircraft can be improved using composite
Quan Xing, improves the maintainability of aircraft, reduces the life-cycle use cost of aircraft.
There is a key issue in airframe manufacture process：Making mold problem and construction weight optimization problem.
The overall dimensions of composite fuselage manufacture mould with which extremely close relationship.It is outer to ensure the design of composite fuselage
Shape and dimensional accuracy, fuselage are bigger, and requirement during molding to mold stiffness and intensity is higher, and the weight and cost of mould also can
Increase substantially.The fabrication cycle of mould is long, low production efficiency.
In sum, the mould process for using at present has certain disadvantages, it is impossible to meet scientific research and modernization is fast
The needs that fast-growing is produced, the fuselage molding mode closed so as to propose a kind of new paving to tangle.But because dress is carried existing
Put the carrying that cannot meet to bulky airframe in forming process, it is therefore desirable to develop a kind of new machine
Auxiliary bogey in body forming process, to meet the demand of correlation.
The content of the invention
For above-mentioned problems of the prior art, the invention provides in a kind of forming process for airframe
Middle part bogey, its reliability are high, and comprehensive function is higher, and disclosure satisfy that can be to non-rotating in body rotation forming process
Body section of outline is carried in real time, can be overcome common bogey poor rigidity and is difficult to the defect of Automated condtrol.
The present invention is employed the following technical solutions and is achieved：
Middle part bogey in a kind of forming process for airframe of the present invention, it includes installation pedestal component, a left side
Bearing assembly, right bearing assembly, the left bearing assembly, right bearing assembly are separately fixed at the top of installation pedestal component, institute
State left bearing assembly corresponding with right bearing assembly installation site, left bearing assembly and right bearing assembly are located at same level straight line,
Respectively and positioned at the both sides of fuselage.As shown in Figure 1, Figure 2.
Described installation pedestal component includes mounting base, A motor support bases, A bearings, A bearing blocks, guide rail, A slide blocks, B
Bearing, B axle bearing, B slide blocks, C bearings, C bearing blocks, B motor support bases, slide rail bearing, the A motor support bases, A bearing blocks, B axle
Bearing, C bearing blocks, B motor support bases are fixed by screws on mounting base from left to right respectively, and slide rail bearing is solid by screw
It is scheduled on mounting base, the guide rail on slide rail bearing is divided to before and after two both sides for being set in parallel in axle, two in the middle part of two guide rails
A slide blocks, B slide blocks are separately installed with side position；Guide rail is fixed by screws on slide rail bearing；The inner ring that A bearings, B axle are held
Respectively with leading screw interference fit, the outer ring that A bearings, B axle are held respectively with A bearing blocks, B axle bearing interference fit；The A bearings and
A bearing seats in the left side of mounting base, hold, B axle bearing is located at the middle part of mounting base, and in the middle of two guide rails by B axle.
Servomotor that the left bearing assembly includes being sequentially connected, shaft coupling, leading screw, feed screw nut, roller support, with
And bearing (ball) cover, rubber ring, roller, roller shaft, bearing, bearing holder (housing, cover), key；
The servomotor is bolted on the A motor support bases of left end, and the leading screw passes through shaft coupling and servo
Motor connection, leading screw are arranged on A bearings, B axle and hold, and are engaged with feed screw nut and are installed in the axis hole of roller support, institute
Roller and both sides rubber ring sleeve are stated on roller shaft, roller is keyed on roller shaft, prevent that roller is relative with roller shaft to be slided
Dynamic, the bearing is installed in bearing holder (housing, cover), and bearing holder (housing, cover) is enclosed within the lead screw hole of roller support, and the bearing (ball) cover is fitted in bearing
On, play dustproof effect.
The leading screw and A bearings and B axle are fixed by screws on roller support for tight fit, feed screw nut between holding,
And with axis hole interference fit, be tight fit between bearing inner race and roller shaft, bearing holder (housing, cover) is fixed by screws in bearing (ball) cover
On roller support, the both sides of roller support are connected with A slide blocks by screw, and roller support is done on guide rail back and forth with A slide blocks
Motion.
It is described for the middle part bogey in airframe forming process, the left bearing assembly and right bearing assembly
Bearing assembly structure it is identical, coaxial line, and being symmetrically installed.
It is described for the middle part bogey in airframe forming process, the roller in the left bearing assembly can be around
Roller shaft is freely rotated, and with the rotation of fuselage, on the direction parallel with leading screw axis, laminating fuselage does water to roller all the time
Flat to move back and forth, while roller is freely rotated around roller shaft, such design causes the force of sliding friction between fuselage and roller to turn
Become for force of rolling friction.
It is described for the middle part bogey in airframe forming process, the C bearings, C bearing blocks, B slide blocks are used
In right bearing assembly.
Roller, bearing and roller shaft on left bearing assembly constitutes the mechanics shifter during supporting, and it is by machine
Force of sliding friction between body and roller is converted to the force of rolling friction of roller.
The present invention has following significant advantage compared with prior art：
The research and development for being presently used for the increasing material manufacturing equipment of the large-scale composite material component laying forming such as airframe still have
Some problems need to be broken through, and the auxiliary bogey with real-time enabling capabilities is exactly one of them.The weak rigidity such as airframe
Part will bear larger vertical load during laying forming, be easily caused which and deform in laid course, have a strong impact on
Formed precision.The auxiliary that existing bogey is only capable of meeting in the rotation of circular cross-section part is carried, or on-circular cross-section
The static carrying of profile parts, the real-time auxiliary that cannot all meet in on-circular cross-section profile parts rotary motion are carried.The present invention
For this problem, the middle part bogey in a kind of forming process for airframe is invented, met airframe certainly
Rigidity requirement during dynamic laying forming type, significantly improves formed precision；Continuous automatic placement is ensure that, molding is improve
Efficiency；Bogey is to be in rolling contact with body parts, it is ensured that molded surface quality.Solve weak rigid on-circular cross-section profile
A difficult problem for part automatic placement molding.
Description of the drawings
Fig. 1 is present invention middle part bogey application schematic diagram.
Fig. 2 is present invention middle part bogey structural representation.
Fig. 3 is installation pedestal components mechanism schematic diagram of the present invention
Fig. 4 is left bearing assembly structural representation of the invention.
Fig. 5 is left bearing wheels of the invention and axle connection diagram.
Fig. 6 is left wheel seat structure schematic diagram of the present invention.
Specific embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
Referring to Fig. 1 to Fig. 6.
Each part description in figure：
1st, installation pedestal component；(2), left bearing assembly；(3), right bearing assembly；(4), fuselage；
Mounting base (101), A motor support bases (102), A bearings (103), A bearing blocks (104), guide rail (105), A slide blocks
(106), B axle holds (107), B axle bearing (108), B slide blocks (109), C bearings (110), C bearing blocks (111), B motor support bases
(112), slide rail bearing (113).
Servomotor (201), shaft coupling (202), leading screw (203), feed screw nut (204), roller support (205), bearing
End cap (206), rubber ring (207), roller (208), roller shaft (209), bearing (210), lead screw hole (211), bearing holder (housing, cover)
(212), key (213), axis hole (214).
Middle part bogey in a kind of forming process for airframe of the present invention, it include installation pedestal component (1),
Left bearing assembly (2), right bearing assembly (3), the left bearing assembly (2), right bearing assembly (3) are separately fixed at installation pedestal
The top of component (1), the left bearing assembly (2) are corresponding with right bearing assembly (3) installation site, left bearing assembly (2) and the right side
Bearing assembly (3) is positioned at same level straight line, difference the both sides positioned at fuselage (4).As shown in Figure 1, Figure 2.
Described installation pedestal component (1) includes mounting base (101), A motor support bases (102), A bearings (103), A
Bearing block (104), guide rail (105), A slide blocks (106), B axle hold (107), B axle bearing (108), B slide blocks (109), C bearings
(110), C bearing blocks (111), B motor support bases (112), slide rail bearing (113), the A motor support bases (102), A bearing blocks
(104), B axle bearing (108), C bearing blocks (111), B motor support bases (112) are fixed by screws in installation from left to right respectively
On base plate (101), slide rail bearing (113) is fixed by screws on mounting base (101), the guide rail on slide rail bearing (113)
(105) it is divided to before and after two both sides for being set in parallel in axle, A cunnings is separately installed with two side positions in the middle part of two guide rails (105)
Block (106), B slide blocks (109)；Guide rail (105) is fixed by screws on slide rail bearing (113)；A bearings (103), B axle are held
(107) inner ring respectively with leading screw (203) interference fit, A bearings (103), B axle hold the outer ring of (107) respectively with A bearing blocks
(104), B axle bearing (108) interference fit；The left side of the A bearings (103) and A bearing blocks (104) positioned at mounting base (101)
Sidepiece, B axle hold 107, B axle bearing (108) positioned at the middle part of mounting base (101), and in the middle of two guide rails.
The left bearing assembly (2) includes the servomotor (201), shaft coupling (202), leading screw (203), silk being sequentially connected
Thick stick nut (204), roller support (205), and bearing (ball) cover (206), rubber ring (207), roller (208), roller shaft
(209), bearing (210), bearing holder (housing, cover) (212), key (213)；
The servomotor (201) is bolted on the A motor support bases (102) of left end, and the leading screw (203) is led to
Cross shaft coupling (202) to be connected with servomotor (201), leading screw (203) is held on (107) installed in A bearings (103), B axle, and with
Feed screw nut (204) is engaged and is installed in the axis hole (214) of roller support (205), the roller (208) and both sides rubber ring
(207) be enclosed within roller shaft (209), roller (208) is fixed on roller shaft (209) with key (213), prevent roller (208) with
Roller shaft (209) is relative to slide, and the bearing (210) is installed in bearing holder (housing, cover) (212), and bearing holder (housing, cover) (212) is enclosed within roller support
(205) in lead screw hole (211), the bearing (ball) cover (206) is fitted on bearing (210), plays dustproof effect.
It is tight fit that the leading screw (203) and A bearings (103) and B axle are held between (107), and feed screw nut (204) is by spiral shell
Nail be fixed on roller support (205), and with axis hole (214) interference fit, between bearing (210) inner ring and roller shaft (209)
For tight fit, bearing holder (housing, cover) (212) is fixed by screws on roller support (205) with bearing (ball) cover (206), roller support
(205) both sides are connected with A slide blocks (106) by screw, and roller support (205) is done on guide rail back and forth with A slide blocks (106)
Motion.
It is described for the middle part bogey in airframe forming process, the left bearing assembly (2) and right carrying
The bearing assembly structure of component (3) is identical, coaxial line, and is symmetrically installed.
The described roller for the middle part bogey in airframe forming process, in the left bearing assembly (2)
(208) can freely rotate around roller shaft (209), with the rotation of fuselage (4), roller (208) all the time with leading screw (203) axis
Fuselage (4) of fitting on parallel direction does horizontal reciprocating movement, while roller (208) is freely rotated around roller shaft (209), this
The design of sample causes the force of sliding friction between fuselage (4) and roller (208) to change for force of rolling friction.
It is described for the middle part bogey in airframe forming process, the C bearings (110), C bearing blocks
(111), B slide blocks (109) are for right bearing assembly (3).Such as Fig. 4, Fig. 5.
During fuselage (4) are carried, bearing point is exactly the intersection point of fuselage contour curve and support wheel contour curve, machine
It is rolling friction between body 4 and bearing wheels, no relative motion.
During work, whole auxiliary bogey is located at the postmedian of fuselage (4), and fuselage (4) is under the drive of main shaft with one
Fixed speed rotates.Left bearing assembly (2) line, roller centered on its leading screw (203) axis with right bearing assembly (3)
Bearing (205) drives
(4) move reciprocatingly, while roller (208) rotates freely motion around roller shaft (209).According to the instantaneous appearance of fuselage rotation
State, respectively under the control of respective servomotor, the corresponding displacement of movement, bearing wheels are remained and fuselage foreign steamer two bearing wheels
Wide curve laminating motion.When bearing wheels are fitted with fuselage outline curve, bearing wheels freely rotate can by itself and fuselage it
Between force of sliding friction be converted into force of rolling friction, it is achieved thereby that auxiliary bogey reduce to bearing wheels and fuselage friction
Realize the real-time carrying to fuselage while loss again.
Apparatus of the present invention disclosure satisfy that and non-revolved body section of outline can be supported in real time in body rotation forming process,
Common support device poor rigidity can be overcome and the defect of Automated condtrol is difficult to, production efficiency is high, production capacity is big, product quality
It is stable, without the need for manually adjusting.
Claims (4)
1. the middle part bogey in a kind of forming process for airframe, is characterized in that, it includes installation pedestal component
(1), left bearing assembly (2), right bearing assembly (3), the left bearing assembly (2), right bearing assembly (3) are separately fixed at installation
The top of base assembly (1), the left bearing assembly (2) are corresponding with right bearing assembly (3) installation site, left bearing assembly (2)
With right bearing assembly (3) positioned at same level straight line, respectively and positioned at the both sides of fuselage (4)；
Described installation pedestal component (1) includes mounting base (101), A motor support bases (102), A bearings (103), A bearings
Seat (104), guide rail (105), A slide blocks (106), B axle hold (107), B axle bearing (108), B slide blocks (109), C bearings (110), C
Bearing block (111), B motor support bases (112), slide rail bearing (113), the A motor support bases (102), A bearing blocks (104), B axle
Bearing (108), C bearing blocks (111), B motor support bases (112) are fixed by screws in mounting base (101) from left to right respectively
On, slide rail bearing (113) is fixed by screws on mounting base (101), before the guide rail (105) on slide rail bearing (113) point
Two both sides for being set in parallel in axle, are being separately installed with A slide blocks (106), B on two side positions in the middle part of two guide rails (105) afterwards
Slide block (109)；Guide rail (105) is fixed by screws on slide rail bearing (113)；A bearings (103), B axle hold the inner ring of (107)
Respectively with leading screw (203) interference fit, A bearings (103), B axle hold the outer ring of (107) respectively with A bearing blocks (104), B axle bearing
(108) interference fit；, positioned at the left side of mounting base (101), B axle is held for the A bearings (103) and A bearing blocks (104)
(107), B axle bearing (108) is positioned at the middle part of mounting base (101), and in the middle of two guide rails；
The left bearing assembly (2) includes the servomotor (201), shaft coupling (202), leading screw (203), leading screw spiral shell being sequentially connected
Female (204), roller support (205), and bearing (ball) cover (206), rubber ring (207), roller (208), roller shaft (209), axle
Hold (210), bearing holder (housing, cover) (212), key (213)；
The servomotor (201) is bolted on the A motor support bases (102) of left end, and the leading screw (203) is by connection
Axle device (202) is connected with servomotor (201), and leading screw (203) is held on (107) installed in A bearings (103), B axle, and and leading screw
Nut (204) is engaged and is installed in the axis hole (214) of roller support (205), the roller (208) and both sides rubber ring
(207) be enclosed within roller shaft (209), roller (208) is fixed on roller shaft (209) with key (213), prevent roller (208) with
Roller shaft (209) is relative to slide, and the bearing (210) is installed in bearing holder (housing, cover) (212), and bearing holder (housing, cover) (212) is enclosed within roller support
(205) in lead screw hole (211), the bearing (ball) cover (206) is fitted on bearing (210), plays dustproof effect；
The leading screw (203) and A bearings (103) and B axle are held between (107) as tight fit, and feed screw nut (204) is solid by screw
Be scheduled on roller support (205), and with axis hole (214) interference fit, be tight between bearing (210) inner ring and roller shaft (209)
Coordinate, bearing holder (housing, cover) (212) is fixed by screws on roller support (205) with bearing (ball) cover (206), roller support (205)
Both sides are connected with A slide blocks (106) by screw, and roller support (205) moves reciprocatingly on guide rail with A slide blocks (106).
2. the middle part bogey being used in airframe forming process as claimed in claim 1, is characterized in that, the left side is held
Carry component (2) identical with the bearing assembly structure of right bearing assembly (3), coaxial line, and be symmetrically installed.
3. the middle part bogey being used in airframe forming process as claimed in claim 1, is characterized in that,
Roller (208) in the left bearing assembly (2) can be freely rotated around roller shaft (209), with the rotation of fuselage (4),
All the time on the direction parallel with leading screw (203) axis, horizontal reciprocating movement is done in laminating fuselage (4) to roller (208), while rolling
Wheel (208) is freely rotated around roller shaft (209), and such design causes the force of sliding friction between fuselage (4) and roller (208) to turn
Become for force of rolling friction.
4. the middle part bogey being used in airframe forming process as claimed in claim 1, is characterized in that, the C axles
(110), C bearing blocks (111), B slide blocks (109) are held for right bearing assembly (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611220348.7A CN106541591B (en) | 2016-12-26 | 2016-12-26 | A kind of middle part bogey in airframe forming process |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611220348.7A CN106541591B (en) | 2016-12-26 | 2016-12-26 | A kind of middle part bogey in airframe forming process |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106541591A true CN106541591A (en) | 2017-03-29 |
| CN106541591B CN106541591B (en) | 2019-01-11 |
Family
ID=58396161
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611220348.7A Active CN106541591B (en) | 2016-12-26 | 2016-12-26 | A kind of middle part bogey in airframe forming process |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106541591B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110924779A (en) * | 2018-11-30 | 2020-03-27 | 齐洛克工程有限公司 | Roller assembly and roller bearing piece using same |
| CN111469394A (en) * | 2020-04-13 | 2020-07-31 | 白建国 | Numerical control foam lines self-adhesion glass fiber mesh cloth parcel equipment |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0582160A1 (en) * | 1992-08-03 | 1994-02-09 | FINMECCANICA S.p.A., RAMO AZIENDALE ALENIA | System for the manufacturing of carbon fibre structures and relevant manufacturing process, suitable for aeronautic applications |
| CN101795852A (en) * | 2007-08-30 | 2010-08-04 | Gkn航天服务有限公司 | Composite structure and releted method to obtain it |
| CN206297156U (en) * | 2016-12-26 | 2017-07-04 | 河北科技大学 | A kind of middle part bogey in the forming process for airframe |
-
2016
- 2016-12-26 CN CN201611220348.7A patent/CN106541591B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0582160A1 (en) * | 1992-08-03 | 1994-02-09 | FINMECCANICA S.p.A., RAMO AZIENDALE ALENIA | System for the manufacturing of carbon fibre structures and relevant manufacturing process, suitable for aeronautic applications |
| CN101795852A (en) * | 2007-08-30 | 2010-08-04 | Gkn航天服务有限公司 | Composite structure and releted method to obtain it |
| CN206297156U (en) * | 2016-12-26 | 2017-07-04 | 河北科技大学 | A kind of middle part bogey in the forming process for airframe |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110924779A (en) * | 2018-11-30 | 2020-03-27 | 齐洛克工程有限公司 | Roller assembly and roller bearing piece using same |
| CN111469394A (en) * | 2020-04-13 | 2020-07-31 | 白建国 | Numerical control foam lines self-adhesion glass fiber mesh cloth parcel equipment |
| CN111469394B (en) * | 2020-04-13 | 2023-04-11 | 白建国 | Numerical control foam lines self-adhesion glass fiber mesh cloth parcel equipment |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106541591B (en) | 2019-01-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201346692Y (en) | Numerical control Longmen boring-milling-grinding machine | |
| CN103612185B (en) | Seven-axis linkage numerical control abrasive band milling and casting machine tool | |
| CN104772628B (en) | A kind of freedom degree parallel connection mainshaft head mechanism | |
| CN205414594U (en) | A numerical control equipment for plastic of solid rocket engine powder column | |
| CN202939899U (en) | Five-axis numerical control processing teaching demonstration machine | |
| CN102310354A (en) | Seven-axis numerical control automatic polishing machine for multidimensional space curved surface | |
| CN106827538B (en) | A kind of 3D printer that accuracy is high | |
| CN206297156U (en) | A kind of middle part bogey in the forming process for airframe | |
| CN103878409A (en) | Digital controlled drill | |
| CN105798634A (en) | Composite numerical control machining center | |
| CN106541591A (en) | A kind of middle part bogey in the forming process for airframe | |
| CN204843183U (en) | Complicated curved surface wire -electrode cutting diaxon numerical control revolving platform | |
| CN104723155A (en) | Four-line-rail ram double-lead-screw driving system | |
| CN202240853U (en) | Seven-axis numerical control automatic polishing-grinding machine applied for multidimensional space curved molded surface | |
| CN204935343U (en) | Roller sphere mill overcharge is put | |
| CN101456080A (en) | Method and device for finish-machining spherical ingot | |
| CN204135149U (en) | A kind of spinning roller shaped device of spoke spinning machine | |
| CN103878679A (en) | Double-freedom-degree plane polishing device | |
| CN101844233A (en) | Device used for machining ball-shaped parts for lathe | |
| CN202910296U (en) | Extra-large-diameter shield shell finish machining device with digital remote control function | |
| CN206135666U (en) | A eccentric shaft lift slip table feed mechanism for making perfect automatic balance corrective | |
| CN106626429B (en) | A kind of middle part bogey and its motion control method in airframe forming process | |
| CN2900079Y (en) | Numerical control precision round bench grinder special for non-metal | |
| CN201720444U (en) | Turn ball device | |
| CN204036260U (en) | A kind of digital control grinder grinding wheel trimmer |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |