CN115352648A - Aircraft towing device - Google Patents
Aircraft towing device Download PDFInfo
- Publication number
- CN115352648A CN115352648A CN202211151900.7A CN202211151900A CN115352648A CN 115352648 A CN115352648 A CN 115352648A CN 202211151900 A CN202211151900 A CN 202211151900A CN 115352648 A CN115352648 A CN 115352648A
- Authority
- CN
- China
- Prior art keywords
- frame body
- aircraft
- driving wheel
- driving
- groove
- 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.)
- Pending
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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
- B62—LAND VEHICLES FOR TRAVELLING OTHERWISE THAN ON RAILS
- B62D—MOTOR VEHICLES; TRAILERS
- B62D7/00—Steering linkage; Stub axles or their mountings
- B62D7/06—Steering linkage; Stub axles or their mountings for individually-pivoted wheels, e.g. on king-pins
- B62D7/14—Steering linkage; Stub axles or their mountings for individually-pivoted wheels, e.g. on king-pins the pivotal axes being situated in more than one plane transverse to the longitudinal centre line of the vehicle, e.g. all-wheel steering
- B62D7/142—Steering linkage; Stub axles or their mountings for individually-pivoted wheels, e.g. on king-pins the pivotal axes being situated in more than one plane transverse to the longitudinal centre line of the vehicle, e.g. all-wheel steering specially adapted for particular vehicles, e.g. tractors, carts, earth-moving vehicles, trucks
- B62D7/144—Steering linkage; Stub axles or their mountings for individually-pivoted wheels, e.g. on king-pins the pivotal axes being situated in more than one plane transverse to the longitudinal centre line of the vehicle, e.g. all-wheel steering specially adapted for particular vehicles, e.g. tractors, carts, earth-moving vehicles, trucks for vehicles with more than two axles
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- 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
- B64F1/225—Towing trucks
- B64F1/227—Towing trucks adapted for directly connecting to aircraft, e.g. trucks without tow-bars
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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
- Y02T50/80—Energy efficient operational measures, e.g. ground operations or mission management
Abstract
The invention discloses an aircraft traction device, which comprises a frame body, a driving mechanism and a connecting mechanism, wherein the driving mechanism comprises a first driving wheel and a second driving wheel which are respectively and rotatably connected to two sides of the frame body, the first driving wheel and the second driving wheel are distributed to enable the frame body to be capable of steering on site on a reference axis, when the rotating speeds of the first driving wheel and the second driving wheel are the same and the rotating directions of the first driving wheel and the second driving wheel are opposite, the frame body rotates around the reference axis, the connecting mechanism comprises a connecting seat and a connecting part, the connecting part is fixedly connected to the connecting seat and used for being detachably connected with a nose landing gear of an aircraft, the connecting seat is rotatably connected to the frame body, and the rotating axis between the connecting seat and the frame body is superposed with the reference axis, so that after the connecting mechanism is combined with the nose landing gear, the frame body still can steer on site under the driving of the first driving wheel and the second driving wheel, the turning radius of the towed aircraft is greatly reduced, and the towing precision is improved.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an aircraft traction device.
Background
After a portion of the aircraft has landed on the runway, it needs to be towed by an aircraft tractor to a hangar or other parking location. The aircraft tow vehicle is connected to the nose landing gear of the aircraft by a tow bar having a damping device, through which the aircraft tow vehicle is towed along with the travel of the aircraft. However, the aircraft towing vehicle has a large steering radius, and both the aircraft towing vehicle and the nose landing gear of the aircraft can steer, so that the difficulty of driving by the aircraft towing vehicle is high, and it is difficult to achieve precise towing of the aircraft.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to provide an aircraft traction device to solve the problems that the turning radius is large and precise dragging is difficult to realize when the existing aircraft tractor drags an aircraft.
The purpose of the invention is realized by adopting the following technical scheme:
an aircraft traction device comprises a frame body, a driving mechanism and a connecting mechanism;
the driving mechanism comprises a first driving wheel and a second driving wheel which are respectively connected to two sides of the frame body in a rotating mode, and when the first driving wheel and the second driving wheel have the same rotating speed and opposite rotating directions, the frame body rotates around a reference axis;
the connecting mechanism comprises a connecting seat and a connecting part, the connecting part is fixedly connected to the connecting seat and used for being detachably connected with a nose landing gear of an aircraft, the connecting seat is rotatably connected to the frame body, and a rotating axis between the connecting seat and the frame body is coincident with the reference axis.
In some optional embodiments, the connecting part is provided with a connecting groove, the extending direction of the connecting groove is inclined to the reference axis, and the nose landing gear can be embedded in the connecting groove.
In some optional embodiments, the coupling member further comprises a locking member slidably coupled to the coupling slot, the locking member forming a closed structure with the coupling slot to surround the nose landing gear in the locked state.
In some optional embodiments, a visual recognition mechanism is disposed at one end of the frame body, the visual recognition mechanism includes a support rod and an image acquisition component, one end of the support rod is fixedly connected to the frame body, and the other end of the support rod is rotatably connected to the image acquisition component.
In some optional embodiments, one end of the frame body is provided with a yielding groove, and the first driving wheel and the second driving wheel are respectively located on two sides of the yielding groove.
In some optional embodiments, the abdicating groove is fan-shaped, and the center of the fan-shaped abdicating groove is located on the reference axis.
In some optional embodiments, the number of the first driving wheels is two, the number of the second driving wheels is two, and the two first driving wheels and the two second driving wheels are respectively arranged at four corners of the frame body.
In some optional embodiments, a side of the locking member opposite to the connecting groove is provided with a first buffering member having elasticity.
In some optional embodiments, the connecting member further comprises an electric cylinder, and two ends of the electric cylinder are respectively connected to the connecting groove and the locking member; alternatively, the first and second liquid crystal display panels may be,
the connecting part further comprises a motor and a transmission assembly, the motor is fixedly connected with the connecting groove, the transmission assembly comprises a gear connected with a main shaft of the motor and a rack slidably connected with the connecting groove, the rack is fixedly connected with the locking piece, and the gear is meshed with the rack.
In some optional embodiments, a second buffer member with elasticity is arranged in the connecting groove.
Compared with the prior art, the invention has the beneficial effects that:
the layout of first drive wheel and second drive wheel makes the support body can turn to on the original place on the reference axis, adapting unit can be connected with the nose landing gear detachably of aircraft, adapting unit and connecting seat all can rotate relative to the support body, and the axis of rotation between connecting seat and the support body coincides with the reference axis, this makes coupling mechanism and nose landing gear combine the back, the support body still can turn to on the original place under the drive of first drive wheel and second drive wheel, the turning radius of the aircraft that receives the drag has greatly been reduced, the precision of dragging has been improved.
Drawings
FIG. 1 is one of the overall structural schematics of the inventive aircraft towing installation;
FIG. 2 is a second schematic diagram of the overall configuration of the aircraft towing attachment of the present invention;
in the figure: 10. a frame body; 11. a yielding groove; 20. a first drive wheel; 30. a second drive wheel; 40. a connecting seat; 50. a connecting member; 51. connecting grooves; 52. a locking member; 60. a visual recognition mechanism; 61. a support bar; 62. an image acquisition component.
Detailed Description
To facilitate an understanding of the invention, the invention will now be described more fully with reference to the accompanying drawings. Preferred embodiments of the present invention are shown in the drawings. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.
It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. The terms "vertical," "horizontal," "left," "right," and the like as used herein are for illustrative purposes only.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
Example 1
Referring to fig. 1 and 2, an aircraft towing installation of the present invention is schematically illustrated, including a frame 10, a drive mechanism, and a linkage mechanism.
The frame body 10 is used for carrying the driving mechanism and the connecting mechanism. The driving mechanism comprises a first driving wheel 20 and a second driving wheel 30 which are respectively connected with two sides of the frame body 10 in a rotating way, the first driving wheel 20 and the second driving wheel 30 are used for driving the frame body 10 to move in an airport or other working areas, the first driving wheel 20 and the second driving wheel 30 have the same rotating speed and the same rotating direction, and the frame body 10 moves forwards or backwards; the first driving wheel 20 and the second driving wheel 30 have different rotating speeds and the same rotating direction, and the frame body 10 turns while moving forwards or backwards; when the first driving wheel 20 and the second driving wheel 30 rotate at the same speed and in opposite directions, the frame body 10 rotates around a reference axis.
The connecting mechanism comprises a connecting seat 40 and a connecting part 50, wherein the connecting part 50 is fixedly connected to the connecting seat 40 and is used for being detachably connected with the nose landing gear of the aircraft, the connecting seat 40 is rotatably connected to the frame body 10, and the connecting structure is used for connecting the nose landing gear of the aircraft with the frame body 10 through the connecting seat 40 and the connecting part 50 so as to achieve traction of the aircraft. The rotation axis between the connecting base 40 and the frame body 10 coincides with the reference axis, so that after the connecting mechanism is combined with the nose landing gear, the frame body 10 can still steer in situ under the driving of the first driving wheel 20 and the second driving wheel 30 (the connecting base 40 rotates relative to the frame body 10, so that the nose landing gear does not rotate spatially), the extremely small radius steering of the aircraft when the aircraft is towed is realized, and the towing track and the parking position of the aircraft can be accurately controlled.
Most of the existing aircraft tractors are front wheel or rear wheel steering, and when the aircraft needs to be towed to a certain preset position, a driver or an automatic steering device needs to drive the tractor to repeatedly drive back and forth and steer so as to finely adjust the parking position of the aircraft. This is very dependent on the driver's driving experience and is extremely time consuming, and if the autopilot drives the tractor, this process of fine-tuning the parking position requires complex algorithms.
Further, the connecting part 50 is provided with a connecting groove 51, the extending direction of the connecting groove 51 is inclined to the reference axis, and the nose landing gear can be embedded in the connecting groove 51. The obliquely arranged connecting groove 51 can be matched with the nose landing gear of an aircraft which is also obliquely arranged, so that the contact area of the connecting groove 51 and the nose landing gear is larger, and the condition that the contact area of the connecting groove 51 and the nose landing gear is too small to cause the local deformation of the nose landing gear is avoided. In this embodiment, the attachment slot 51 is C-shaped in cross-section to accommodate a cylindrical nose gear support rod 61. Of course, in some alternative embodiments, one end of the connecting member 50 may be rotatably connected to the connecting socket 40 to enable the connecting member 50 to be adjusted in pitch relative to the connecting socket 40, the connecting member 50 of the structure being able to accommodate a variety of aircraft nose landing gears at different angles of inclination; the pitch adjustment of the connection part 50 and the connection part 40 is adjusted by a hydraulic cylinder having both ends connected to the connection part 40 and the connection part 50, respectively, the hydraulic cylinder, the connection part 40 and the connection part 50 being arranged in a triangle.
In order to prevent the nose landing gear from being accidentally disengaged from the connecting groove 51, the connecting member 50 is further provided with a locking member 52, the locking member 52 is slidably connected to the connecting groove 51, the locking member 52 forms a closed structure with the connecting groove 51 to surround the nose landing gear in a locked state, and the locking member 52 avoids an opening of the connecting groove 51 to allow the nose landing gear to be inserted into or removed from the connecting groove 51 in an unlocked state. In the present embodiment, a first elastic buffer, preferably a rubber pad, is disposed on a side of the locking element 52 opposite to the connecting slot 51, so as to serve as a buffer structure between the locking element 52 and the nose landing gear, so as to prevent the nose landing gear from colliding with the locking element 52; similarly, a second buffer member with elasticity is arranged in the connecting groove 51, and the second buffer member is preferably a rubber pad to serve as a buffer structure between the connecting groove 51 and the nose landing gear so as to prevent the nose landing gear from colliding with the connecting groove 51. The connecting member 50 further includes an electric cylinder, both ends of the electric cylinder are respectively connected to the connecting groove 51 and the locking member 52, a telescopic direction of the electric cylinder is perpendicular to an extending direction of the connecting groove 51, the electric cylinder is extended to drive the locking member 52 to move to the opening of the connecting groove 51, and the electric cylinder is contracted to drive the locking member 52 to move to the opening of the connecting groove 51.
One side of the connecting part 50 is provided with a slide rail perpendicular to the connecting part, the locking piece 52 is slidably connected to the slide rail, the electric cylinder is fixedly connected to one end of the slide rail and is arranged in parallel with the slide rail, and the slide rail is arranged to enable the locking piece 52 to be stably connected with the connecting part 50.
One end of support body 10 is equipped with visual identification mechanism 60, visual identification mechanism 60 includes bracing piece 61 and image acquisition part 62, the one end fixed connection of bracing piece 61 in support body 10, the other end of bracing piece 61 rotates to be connected in image acquisition part 62, image acquisition part 62 is used for gathering the environment image around the support body 10, provide probably for autopilot, simultaneously, image acquisition part 62 can rotate relative to bracing piece 61, make image acquisition part 62 can pitch regulation, with the identification code of discernment aircraft fuselage bottom, and then pull target aircraft. The other end of the frame body 10 is provided with a recess 11, that is, the recess 11 and the visual recognition mechanism 60 are respectively located at two ends of the frame body 10, the first driving wheel 20 and the second driving wheel 30 are respectively located at two sides of the recess 11, and when the connecting member 50 is combined with a nose landing gear of an aircraft, the nose landing gear is located in the recess 11. The abdicating groove 11 is fan-shaped, the circle center of the abdicating groove 11 is located on the reference axis, the requirement of the visual identification error of the image acquisition component 62 can be reduced by the abdicating groove 11 with the structure, and the collision probability of the frame body 10 and the nose landing gear is reduced.
In the present embodiment, the number of the first driving wheels 20 is two, the number of the second driving wheels 30 is two, and the two first driving wheels 20 and the two second driving wheels 30 are respectively disposed at four corners of the frame body 10. The driving mechanism further comprises a first driving assembly and a second driving assembly, the first driving assembly comprises a first driving motor and two first transmission shafts, the first driving motor is fixedly connected to the frame body 10, the first driving motor is connected to the two first driving wheels 20 through the two first transmission shafts respectively, the first driving motor drives the first transmission shafts to rotate so as to drive the first driving wheels 20 to rotate relative to the frame body 10, a main shaft of the first driving motor is connected with the first transmission shafts through the existing bevel gear sets, and the first transmission shafts are also connected with the first driving wheels 20 through the existing bevel gear sets. The second drive assembly includes second driving motor and two second transmission shafts, second driving motor fixed connection is on support body 10, first driving motor and second driving motor are located the both sides of support body 10 respectively, second driving motor connects in two second drive wheels 30 through two second transmission shafts respectively, second driving motor drives the second transmission shaft and rotates, in order to drive the relative support body 10 rotation of second drive wheel 30, second driving motor's main shaft and the current bevel gear group of connection accessible of second transmission shaft are connected, the second transmission shaft also can be connected through current bevel gear group with being connected of second drive wheel 30.
Example 2
The present embodiment is different from embodiment 1 in that the connection member 50 includes a motor fixedly coupled to the coupling groove 51 and a transmission assembly including a gear coupled to a main shaft of the motor and a rack slidably coupled to the coupling groove 51, the rack is fixedly coupled to the locking member 52, and the gear and the rack are engaged with each other, and by means of the transmission assembly, it is possible to drive the locking member 52 to move relative to the coupling groove 51 using the motor.
In summary, the arrangement of the first driving wheel 20 and the second driving wheel 30 enables the frame body 10 to steer in situ on the reference axis, the connecting part 50 can be detachably connected with the nose landing gear of the aircraft, both the connecting part 50 and the connecting seat 40 can rotate relative to the frame body 10, and the rotation axis between the connecting seat 40 and the frame body 10 is coincident with the reference axis, so that after the connecting mechanism is combined with the nose landing gear, the frame body 10 can still steer in situ under the driving of the first driving wheel 20 and the second driving wheel 30, the turning radius of the towed aircraft is greatly reduced, and the towing accuracy is improved.
The above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes performed by the present specification and drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. An aircraft traction device is characterized by comprising a frame body, a driving mechanism and a connecting mechanism;
the driving mechanism comprises a first driving wheel and a second driving wheel which are respectively connected to two sides of the frame body in a rotating mode, and when the first driving wheel and the second driving wheel have the same rotating speed and opposite rotating directions, the frame body rotates around a reference axis;
the connecting mechanism comprises a connecting seat and a connecting part, the connecting part is fixedly connected to the connecting seat and used for being detachably connected with a nose landing gear of an aircraft, the connecting seat is rotatably connected to the frame body, and a rotating axis between the connecting seat and the frame body is coincident with the reference axis.
2. The aircraft towing device according to claim 1, wherein the connecting part is provided with a connecting groove, the extending direction of the connecting groove is arranged obliquely to the reference axis, and the nose landing gear can be embedded in the connecting groove.
3. The aircraft towing attachment according to claim 2, wherein the coupling member is further provided with a locking member slidably coupled to the coupling slot, the locking member forming a closed structure with the coupling slot to surround the nose landing gear in the locked state.
4. The aircraft towing device according to claim 1, wherein one end of the frame body is provided with a visual recognition mechanism, the visual recognition mechanism comprises a support rod and an image acquisition component, one end of the support rod is fixedly connected to the frame body, and the other end of the support rod is rotatably connected to the image acquisition component.
5. The aircraft towing device of claim 2 wherein one end of the frame body is provided with a relief groove, the first and second drive wheels being located on either side of the relief groove.
6. The aircraft towing device of claim 5 wherein the abdicating groove is sector shaped with its centre at the reference axis.
7. The aircraft towing device of claim 1 wherein there are two first drive wheels and two second drive wheels, the two first drive wheels and the two second drive wheels being disposed at respective four corners of the frame body.
8. The aircraft towing attachment according to claim 3, wherein a side of the locking element facing the attachment slot is provided with a resilient first buffer.
9. The aircraft towing apparatus according to claim 3, wherein the connecting member further comprises an electric cylinder, both ends of the electric cylinder being connected to the connecting groove and the lock member, respectively; alternatively, the first and second electrodes may be,
the connecting part further comprises a motor and a transmission assembly, the motor is fixedly connected with the connecting groove, the transmission assembly comprises a gear connected with a main shaft of the motor and a rack slidably connected with the connecting groove, the rack is fixedly connected with the locking piece, and the gear is meshed with the rack.
10. The aircraft towing attachment according to claim 2, wherein a second cushion member having elasticity is provided in the connecting groove.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211151900.7A CN115352648A (en) | 2022-09-21 | 2022-09-21 | Aircraft towing device |
| PCT/CN2023/118718 WO2024061089A1 (en) | 2022-09-21 | 2023-09-14 | Aircraft towing apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211151900.7A CN115352648A (en) | 2022-09-21 | 2022-09-21 | Aircraft towing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115352648A true CN115352648A (en) | 2022-11-18 |
Family
ID=84005696
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211151900.7A Pending CN115352648A (en) | 2022-09-21 | 2022-09-21 | Aircraft towing device |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN115352648A (en) |
| WO (1) | WO2024061089A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024061089A1 (en) * | 2022-09-21 | 2024-03-28 | 亿航智能设备（广州）有限公司 | Aircraft towing apparatus |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8967939B2 (en) * | 2006-10-13 | 2015-03-03 | Hammonds Technical Services, Inc. | Aircraft transporter dolly with hinged gate for moving aircraft |
| CN101920787A (en) * | 2009-06-10 | 2010-12-22 | 马世强 | Aircraft fuselage orientation adjustment steering wheel stand |
| DE202012101865U1 (en) * | 2012-05-22 | 2013-08-23 | Christian Kollmannsberger | Towing vehicle for maneuvering an aircraft and system |
| CN204399488U (en) * | 2014-12-25 | 2015-06-17 | 提坦科技（上海）有限公司 | A kind of drone version non-rod aircraft tractor |
| CN112937909B (en) * | 2021-03-29 | 2022-11-29 | 中国航空制造技术研究院 | Airplane complete machine transfer four-wheel tractor for pavement support self-adaption |
| CN113791621B (en) * | 2021-09-15 | 2023-06-02 | 北京航空航天大学 | Automatic steering tractor and airplane docking method and system |
| CN115352648A (en) * | 2022-09-21 | 2022-11-18 | 亿航智能设备（广州）有限公司 | Aircraft towing device |
| CN218431794U (en) * | 2022-09-21 | 2023-02-03 | 亿航智能设备（广州）有限公司 | Aircraft towing device |
-
2022
- 2022-09-21 CN CN202211151900.7A patent/CN115352648A/en active Pending
-
2023
- 2023-09-14 WO PCT/CN2023/118718 patent/WO2024061089A1/en unknown
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024061089A1 (en) * | 2022-09-21 | 2024-03-28 | 亿航智能设备（广州）有限公司 | Aircraft towing apparatus |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2024061089A1 (en) | 2024-03-28 |
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