CN110001991A - Clamping device and the airplane tractor for using the clamping device - Google Patents
Clamping device and the airplane tractor for using the clamping device Download PDFInfo
- Publication number
- CN110001991A CN110001991A CN201810007848.5A CN201810007848A CN110001991A CN 110001991 A CN110001991 A CN 110001991A CN 201810007848 A CN201810007848 A CN 201810007848A CN 110001991 A CN110001991 A CN 110001991A
- Authority
- CN
- China
- Prior art keywords
- clamping
- contact pin
- shell
- clamping device
- head
- 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.)
- Withdrawn
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/22—Ground or aircraft-carrier-deck installations installed for handling aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/22—Ground or aircraft-carrier-deck installations installed for handling aircraft
- B64F1/224—Towing bars
Abstract
The present invention relates to clamping device and use the airplane tractor of the clamping device；Clamping device includes two clamping heads being oppositely arranged and the clamp system for driving two clamping heads close to each other or separate, the clamping head includes shell and contact pin disposed in the housing in array, each contact pin be parallel to shell axis setting and it is adjustable along shell axial position, be additionally provided in the shell for contact pin apply towards another clamping head elastic force elastic component.It drives two clamping heads along aircraft wheel hollow shaft axial grip aircraft wheel hollow shaft by clamp system when use, is lifted clamping device by the lifting mechanism on airplane tractor, aircraft walking is driven by tractor later；Compared with the prior art, the driving form of clamping device is simplified, the accuracy of alignment requirement of clamping head and aircraft wheel hollow shaft is lower, and clamping efficiency is higher, and the force application part in clamping process is aircraft nose wheel hollow shaft, will not cause to damage to aircraft wheel.
Description
Technical field
The present invention relates to a kind of clamping device and use the airplane tractor of the clamping device.
Background technique
Airplane tractor is the important equipment for ensureing that aircraft floor is mobile.According to mode of traction difference, towing aircraft can divide
To there is bar to draw and being drawn without bar.There is bar traction to refer to that airplane tractor is connected by rising before draw bar and aircraft, realizes aircraft
Traction or pushing tow；The traction of no bar is then that airplane tractor will rise before aircraft and carry volt on the back, and tractor and aircraft form an entirety, realization
Aircraft towage.
No bar traction is opposite to have bar traction to have the following advantages: (1) easy to operate, operating efficiency is high；(2) turning radius is small,
Frame body is light-weight, manoeuvrable；(3) support personnel is few, and operating cost is low；(4) versatility is good.There is bar since the traction of no bar is opposite
Traction has significant advantage, has the tendency that bar traction has and is gradually eliminated.
Clamping device on poleless aircraft tractor is the key device that tractor is docked with aircraft nose wheel, and performance will
Directly affect aircraft towage.Common clamping device includes preceding shelves, rear shelves and the various components such as perform, and structure is complicated, behaviour
Make cumbersome, clamping device is directly contacted with aero tyre, this key components and parts can cause to damage to aero tyre.
Summary of the invention
The purpose of the present invention is to provide a kind of clamping devices, to solve the clamping device knot on existing airplane tractor
Structure is complicated, cumbersome, is easy the problem of damage is caused to aircraft wheel；The folder is used the object of the invention is also to provide a kind of
Hold the airplane tractor of mechanism.
To achieve the above object, the scheme 1 of clamping device of the invention is: clamping device includes two clampings being oppositely arranged
Head and the clamp system for driving two clamping heads close to each other or separate, the clamping head include shell and are arranged in array
Contact pin in the shell, each contact pin be parallel to shell axis setting and it is adjustable along shell axial position, also set in the shell
Have for applying the elastic component towards the elastic force of another clamping head to contact pin.
Scheme 2 is clamping device according to scheme 1, and the shell further includes separate another folder that shell is arranged in
The cover board at first end is held, cover board is equipped with the pin holes for guiding the contact pin mobile.
Scheme 3 is, according to clamping device described in scheme 2, is arranged on the contact pin for applying to contact pin towards another
The spring of the elastic force of one clamping head, spring form the elastic component, and one end far from another clamping head of contact pin is additionally provided with use
In the stop part with the shell along the cooperation of shell axial direction block to prevent contact pin from deviating from from the shell.
Scheme 4 is, according to the described in any item clamping devices of scheme 1 to 3, the one of close another clamping head of the contact pin
End is the tapered end for guiding part to be held to enter.
Scheme 5 is, according to the described in any item clamping devices of scheme 1 to 3, the contact pin is cylinder type contact pin.
Scheme 6 is, according to the described in any item clamping devices of scheme 1 to 3, the clamp system includes that rotational plane is coplanar
Two clamping limbs and clamping limb driving device for driving two clamping limbs to rotate towards each other or be located remotely from each other, two clamping heads point
The end of two clamping limbs is not set.
Scheme 7 is clamping device according to scheme 6, and the clamping limb is by arranged side by side and spaced two supporting rod
It is formed.
The scheme 1 of airplane tractor of the invention is: airplane tractor include frame body and be arranged on frame body for pressing from both sides
Clamping device, the lifting mechanism for being lifted the clamping device for holding aircraft nose wheel, the clamping device include being oppositely arranged
Two clamping heads and clamp system for driving two clamping heads close to each other or separate, the clamping head includes shell and array
Contact pin disposed in the housing, each contact pin be parallel to shell axis setting and, the shell adjustable along shell axial position
It is additionally provided in body for applying the elastic component towards the elastic force of another clamping head to contact pin.
Scheme 2 is airplane tractor according to scheme 1, the shell further include be arranged in shell far from another
The cover board of clamping head one end, cover board are equipped with the pin holes for guiding the contact pin mobile.
Scheme 3 is, according to airplane tractor described in scheme 2, is arranged on the contact pin for applying direction to contact pin
The spring of the elastic force of another clamping head, spring form the elastic component, and one end far from another clamping head of contact pin is additionally provided with
For cooperating the stop part to prevent contact pin from deviating from from the shell along shell axial direction block with the shell.
Scheme 4 is, according to the described in any item airplane tractors of scheme 1 to 3, close another clamping head of the contact pin
One end is the tapered end for guiding part to be held to enter.
Scheme 5 is, according to the described in any item airplane tractors of scheme 1 to 3, the contact pin is cylinder type contact pin.
Scheme 6 is, according to the described in any item airplane tractors of scheme 1 to 3, the clamp system includes that rotational plane is total
Two clamping limbs in face and clamping limb driving device for driving two clamping limbs to rotate towards each other or be located remotely from each other, two clamping heads
It is separately positioned on the end of two clamping limbs.
Scheme 7 is airplane tractor according to scheme 6, and the clamping limb is by arranged side by side and spaced two clamping
Bar is formed.
Scheme 8 is, according to the described in any item airplane tractors of scheme 1 to 3, the lifting mechanism includes supplying the clamping
The lifting rotary shaft that mechanism is fixedly connected and the lifting driving structure for driving lifting rotary shaft rotation.
Scheme 9 is that, according to airplane tractor described in scheme 8, being lifted driving structure includes that rotation stop is mounted on lifting rotation
Lifting connecting lever on axis and the lifting oil cylinder for driving lifting connecting lever to swing, the one end for being lifted oil cylinder is hinged on the frame body
The upper, other end is hinged on the end of the lifting connecting lever.
Scheme 10 is, according to the described in any item airplane tractors of scheme 1 to 3, frame body width direction middle section
The sunk structure for avoiding the aircraft accessory that plane nose bottom is arranged in is equipped with frame body front end face adjacent part.
The beneficial effects of the present invention are: driving two clamping heads along aircraft wheel hollow shaft axial grip by clamp system when using
Aircraft wheel hollow shaft is lifted clamping device by the lifting mechanism on airplane tractor, drives aircraft walking by tractor later；
Compared with the prior art, simplify the driving form of clamping device, the accuracy of alignment of clamping head and aircraft wheel hollow shaft require compared with
Low, clamping efficiency is higher, and the force application part in clamping process is aircraft nose wheel hollow shaft, and aircraft nose wheel hollow shaft is that tractor is special
With part, clamping device will not directly be contacted with aero tyre, substantially increase the safety of aircraft.
Further, shell includes cover board, and cover board is equipped with the pin holes mobile for guide pin, guarantees contact pin movement
Reliably.
Further, one end close to another clamping head of contact pin is tapered end, and workpiece to be held is facilitated to enter contact pin
Among array.
Further, clamp system includes two clamping limbs and clamping limb driving device, and clamping limb is arranged by arranged side by side and interval
Two supporting rods formed, clamping head is mounted on clamping limb；Guarantee clamping limb swing process in clamping head axis with it is to be held
Aircraft nose wheel hollow shaft axis it is parallel.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the embodiment one of airplane tractor of the invention；
Fig. 2 is the structural schematic diagram of clamping device；
Fig. 3 is the perspective view that frame body removes front side board；
Fig. 4 is the front view of frame body；
Fig. 5 is the exploded view of clamping head；
Fig. 6 is the cooperation figure of wheel connector and clamping head；
In figure: 1- frame body, the working cell 2-, 3- battery group, 4- walking unit, 5- control system, 6- aircraft nose wheel, 7- wheel
Connector, 8- driving wheel, 9- deflecting roller, 10- steering motor, 11- holding frame, 12- clamping limb, 13- clamping head, 14- clamp oil
Cylinder, 15- lifting rotary shaft, 16- lifting oil cylinder, 17- are lifted connecting lever, 18- shell, 19- contact pin, 20- spring, 21- cover board, 22-
Engaging lug, 23- connecting column.
Specific embodiment
Embodiments of the present invention are described further with reference to the accompanying drawing.
The embodiment one of airplane tractor of the invention, as shown in Figures 1 to 6, frame body 1 and setting including frame structure
Working cell 2, battery group 3, walking unit 4 and control system 5 on frame body 1, frame body 1 are used for whole physical support, work
Making unit 2 includes clamping device and the hydraulic system for driving clamping device to act, and battery group 3 is electronic for storing, and is
It is whole that energy is provided；Walking unit 4 includes driving wheel group and assisted diversion wheel group, for whole walking, steering, braking etc., control
System 5 processed is controlled for whole.Aircraft nose wheel 6 is clamped by clamping device in the course of work, lifting, is drawn later by tractor
Aircraft walking, realizes aircraft towage.
Walking unit 4 includes the traveling wheel being arranged on frame body 1, and traveling wheel includes close to the two of the setting of 1 front end face of frame body
Deflecting roller 9 and two driving wheels 8 that are arranged of rear end face close to frame body 1, are nearby respectively provided on frame body 1 in two deflecting rollers 9
The steering motor 10 for driving corresponding deflecting roller 9 to rotate；The centre that two driving wheels are arranged in the impetus of tractor is played before aircraft
Position increases the coefficient of friction of driving wheel and ground, mitigates tractor frame body weight, mitigates 9 stress of assisted diversion wheel, and then subtract
Small steering resistence is guaranteed two driving wheel differential steering flexibilities, can be turned to the no-radius of airplane tractor, in certain shakings
Occasion solves the problems, such as tractor direction out of control in the case where situation is waved in warship face when as used airplane tractor on warship face.
Clamping device includes holding frame 11, clamping limb 12, clamping head 13, clamping cylinder 14, lifting rotary shaft 15 and lifting
Oil cylinder 16, holding frame 11 pass through the connection structure being arranged in the middle part of its length direction and are fixedly connected with lifting rotary shaft 15, be lifted
The both ends of the length direction of rotary shaft 15 are respectively equipped with lifting connecting lever 17, and one end of lifting oil cylinder 16 is hinged on frame body 1, is another
End is hinged on lifting connecting lever 17, and two lifting 16 synchronization actions of oil cylinder, lifting oil cylinder 16 passes through lifting connecting lever 17, lifting rotary shaft
Axis rotation of the 15 driving holding frames 11 around lifting rotary shaft 15.
There are two clamping limbs 12, and one end of two clamping limbs 12 is respectively hinged at the both ends of 11 length direction of holding frame, each to press from both sides
Gripping arm 12 is formed by two supporting rods being set side by side respectively, and the both ends of each supporting rod are respectively hinged at holding frame 11 and clamping head 13
On.Clamping head 13, two supporting rods and holding frame 11 form parallelogram mechanism, guarantee that clamping head 13 is moved through with clamping limb 12
13 axis of clamping head is parallel with the axis of aircraft nose wheel hollow shaft always in journey.It is equipped between two clamping limbs 12 on holding frame 11
Two clamping cylinders 14, one end of each clamping cylinder 14 is hinged on holding frame 11, the other end is hinged on corresponding clamping limb 12,
Two clamping cylinders, 14 synchronization action drives clamping limb 12 to rotate by clamping cylinder 14.
Clamping head 13 in the present embodiment is array type clamping head 13, array type clamping head 13 include shell 18, contact pin 19,
Spring 20 and cover board 21, shell 18 are equipped with the shell 18 for the engaging lug 22 and regular hexagon hinged with corresponding clamping limb 12
Centre bore, engaging lug 22 are equipped with two hinge holes, and contact pin 19 is parallel to the setting of 18 axis of shell and there are two more than, each contact pin 19
It is arranged in 18 centre bore of shell in regular hexagon array, is respectively installed with spring 20 on contact pin 19；Cover board 21 is arranged in shell 18
End, cover board 21 are equipped with connecting hole for connect with shell 18 and pass through 19 hole of contact pin for contact pin 19, and each contact pin 19 is along shell
18 axial position of body is adjustable, spring 20 be used for contact pin 19 provide reset force, 19 end of contact pin be equipped with circlip, avoid contact pin 19 from
Deviate from shell 18.
Clamping device further includes for installation into the wheel connector 7 on aircraft nose wheel hollow shaft, and wheel connector 7 has two
It is a, it is respectively used to be installed to wheel hollow shaft axial ends, wheel connector 7 has for inserting to the column in wheel hollow shaft
Body portion and the connecting column 23 for being vertically disposed at columnar part end, the cross section of connecting column 23 are regular hexagonal section；It inserts
One end of the separate cover board 21 of needle 19 is for guiding connecting column 23 to enter the tapered end in pin array.
When off working state, each contact pin 19 front end face of 19 front end of contact pin and shell 18 under the effect of spring 20 keeps flat
Together；Two wheel connectors 7 are pressed on wheel hollow shaft by two clamping heads 13 when clamp structure clamps 6 operation of aircraft nose wheel
On, the connecting column 23 on wheel connector 7 is contacted with part contact pin 19, and compression contact pin 19 bounces back, the spring on corresponding contact pin 19
20 are compacted, and connecting column 23 enters by being applied from the contact pin 19 not bounced back to tooling and being lifted in the cavity that contact pin 19 forms that do not bounce back
Lift.
During the work time, two clamping limbs 12 are clamped and installed in aircraft nose wheel under the action of corresponding clamping cylinder in parallel
Wheel connector 7 on hollow shaft is then lifted rotary shaft 15 under the action of being lifted oil cylinder 16, passes through clamping limb 12, clamping
First 13 connect with wheel aircraft nose wheel 6 being lifted away from ground.And since the array area of the contact pin 19 on clamping head 13 is several times as much as
The area of the cross section of connecting column 23 on wheel connector 7, in this way in operation tractor and 6 alignment procedure of aircraft nose wheel,
Without precisely aligning, can greatly improve tractor and aircraft docks efficiency.
In addition, being taken the photograph to meet certain traction requirements for having special functional demands aircraft as aircraft nosing bottom carries
The rescue aircraft etc. of camera, the frame body 1 of tractor are designed using flattening, the middle position of 1 front part of frame body to lower recess,
It avoids frame body 1 and the fuselage attachment of airframe leading portion bottom from interfering, meets such aircraft without bar traction requirements.
Embodiment two, embodiment two and embodiment one the difference is that: the clamping machine of other forms can also be used
Structure drives clamping limb；For example, holding frame is equipped with the guide rail extended along holding frame length direction, one end of two clamping limbs is led
To being mounted on guide rail, the clamping device for driving two clamping limbs to be translatable or be located remotely from each other in opposite directions is additionally provided on holding frame.
Embodiment three, embodiment three and embodiment one the difference is that: the lifting machine of other forms can also be used
Structure；Such as using the elevating mechanism driving clamping device lifting of upper and lower translation formula.
Example IV, example IV and embodiment one the difference is that: holding frame can also be mounted on lift by rotation stop
The clamping limb mounting base risen in rotary shaft is formed, and one end of clamping cylinder is hinged on frame body, the other end is hinged on clamping limb.
Embodiment five, embodiment five and embodiment one the difference is that: the periphery of each contact pin of array setting
Face contacts with each other with successive pins, mobile by the outer peripheral surface guidance compression contact pin of successive pins；It is simple to clamp header structure, production
It is convenient.
Any embodiment of the airplane tractor of the embodiment of clamping device of the invention, clamping device and aforementioned present invention
In clamping device structure it is identical, therefore, be not repeated to illustrate.In addition, clamping device can be used for other occasions, such as object
Haulage vehicle and the rapid abutting joint of package etc. are realized in popular industry.
Claims (10)
1. clamping device, it is characterised in that: including two clamping heads that are oppositely arranged and for driving two clamping heads close to each other or
Separate clamp system, the clamping head include shell and contact pin disposed in the housing in array, and each contact pin is parallel to
Shell axis setting and adjustable along shell axial position, is additionally provided with for applying to contact pin towards another clamping head in the shell
Elastic force elastic component.
2. clamping device according to claim 1, it is characterised in that: the shell further include be arranged in shell far from another
The cover board of one clamping head one end, cover board are equipped with the pin holes for guiding the contact pin mobile.
3. clamping device according to claim 2, it is characterised in that: be arranged on the contact pin for applying court to contact pin
To the spring of the elastic force of another clamping head, spring forms the elastic component, and one end far from another clamping head of contact pin is also set
Have for cooperating the stop part to prevent contact pin from deviating from from the shell along shell axial direction block with the shell.
4. clamping device according to any one of claims 1 to 3, it is characterised in that: close another clamping of the contact pin
One end of head is the tapered end for guiding part to be held to enter.
5. clamping device according to any one of claims 1 to 3, it is characterised in that: the contact pin is cylinder type contact pin.
6. clamping device according to any one of claims 1 to 3, it is characterised in that: the clamp system includes that rotation is flat
Two coplanar clamping limbs of face and the clamping limb driving device for driving two clamping limbs to rotate towards each other or be located remotely from each other, two folders
Hold the end that head is separately positioned on two clamping limbs.
7. clamping device according to claim 6, it is characterised in that: the clamping limb is by arranged side by side and spaced two folder
Bar is held to be formed.
8. airplane tractor, including frame body and be arranged on frame body for clamping the clamping device of aircraft nose wheel, for being lifted
The lifting mechanism of the clamping device, it is characterised in that: the clamping device includes two clamping heads being oppositely arranged and for driving
Dynamic two clamping heads clamp system close to each other or separate, the clamping head include the disposed in the housing of shell and array
Contact pin, each contact pin be parallel to shell axis setting and it is adjustable along shell axial position, be additionally provided in the shell for insert
Needle applies the elastic component towards the elastic force of another clamping head.
9. airplane tractor according to claim 8, it is characterised in that: the shell further includes shell is arranged in separate
The cover board of another clamping head one end, cover board are equipped with the pin holes for guiding the contact pin mobile.
10. airplane tractor according to claim 9, it is characterised in that: be arranged on the contact pin for being applied to contact pin
Add the spring of the elastic force towards another clamping head, spring forms the elastic component, one end far from another clamping head of contact pin
It is additionally provided with for cooperating the stop part to prevent contact pin from deviating from from the shell along shell axial direction block with the shell.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810007848.5A CN110001991A (en) | 2018-01-04 | 2018-01-04 | Clamping device and the airplane tractor for using the clamping device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810007848.5A CN110001991A (en) | 2018-01-04 | 2018-01-04 | Clamping device and the airplane tractor for using the clamping device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110001991A true CN110001991A (en) | 2019-07-12 |
Family
ID=67164335
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810007848.5A Withdrawn CN110001991A (en) | 2018-01-04 | 2018-01-04 | Clamping device and the airplane tractor for using the clamping device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110001991A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111216758A (en) * | 2019-12-20 | 2020-06-02 | 中国航空工业集团公司北京航空精密机械研究所 | Bidirectional traction device for high-speed rail wheel pair |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5259572A (en) * | 1991-09-04 | 1993-11-09 | Man Gutehoffnungshutte Aktiengesellschaft | Towing vehicle without draw tongue for towing aircraft |
| US20050186055A1 (en) * | 2004-02-19 | 2005-08-25 | Hyatt Daniel W. | Aircraft handler |
| CN102239087A (en) * | 2008-11-25 | 2011-11-09 | 以色列宇航工业有限公司 | Towbarless airplane tug |
| CN203127150U (en) * | 2013-01-25 | 2013-08-14 | 长安大学 | Rodless aircraft tractor |
| CN204623852U (en) * | 2015-04-07 | 2015-09-09 | 中国农业机械化科学研究院 | Travel three-wheel non-rod aircraft tractor |
| CN207712315U (en) * | 2018-01-04 | 2018-08-10 | 新乡平原航空技术工程有限公司 | A kind of clamping device and the airplane tractor using the clamping device |
-
2018
- 2018-01-04 CN CN201810007848.5A patent/CN110001991A/en not_active Withdrawn
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5259572A (en) * | 1991-09-04 | 1993-11-09 | Man Gutehoffnungshutte Aktiengesellschaft | Towing vehicle without draw tongue for towing aircraft |
| US20050186055A1 (en) * | 2004-02-19 | 2005-08-25 | Hyatt Daniel W. | Aircraft handler |
| CN102239087A (en) * | 2008-11-25 | 2011-11-09 | 以色列宇航工业有限公司 | Towbarless airplane tug |
| CN203127150U (en) * | 2013-01-25 | 2013-08-14 | 长安大学 | Rodless aircraft tractor |
| CN204623852U (en) * | 2015-04-07 | 2015-09-09 | 中国农业机械化科学研究院 | Travel three-wheel non-rod aircraft tractor |
| CN207712315U (en) * | 2018-01-04 | 2018-08-10 | 新乡平原航空技术工程有限公司 | A kind of clamping device and the airplane tractor using the clamping device |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111216758A (en) * | 2019-12-20 | 2020-06-02 | 中国航空工业集团公司北京航空精密机械研究所 | Bidirectional traction device for high-speed rail wheel pair |
| CN111216758B (en) * | 2019-12-20 | 2021-04-20 | 中国航空工业集团公司北京航空精密机械研究所 | Bidirectional traction device for high-speed rail wheel pair |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190712 |