CN110550225A - Aircraft tractor - Google Patents
Aircraft tractor Download PDFInfo
- Publication number
- CN110550225A CN110550225A CN201910926662.4A CN201910926662A CN110550225A CN 110550225 A CN110550225 A CN 110550225A CN 201910926662 A CN201910926662 A CN 201910926662A CN 110550225 A CN110550225 A CN 110550225A
- Authority
- CN
- China
- Prior art keywords
- motor
- tractor
- aircraft
- stator
- chassis
- 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
Links
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 25
- 238000004804 winding Methods 0.000 claims description 17
- 229910052802 copper Inorganic materials 0.000 claims description 14
- 239000010949 copper Substances 0.000 claims description 14
- 238000001514 detection method Methods 0.000 claims description 13
- 239000002826 coolant Substances 0.000 claims description 6
- 238000005516 engineering process Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 4
- 230000006872 improvement Effects 0.000 description 4
- 230000033001 locomotion Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000003247 decreasing effect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 239000000110 cooling liquid Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60K—ARRANGEMENT OR MOUNTING OF PROPULSION UNITS OR OF TRANSMISSIONS IN VEHICLES; ARRANGEMENT OR MOUNTING OF PLURAL DIVERSE PRIME-MOVERS IN VEHICLES; AUXILIARY DRIVES FOR VEHICLES; INSTRUMENTATION OR DASHBOARDS FOR VEHICLES; ARRANGEMENTS IN CONNECTION WITH COOLING, AIR INTAKE, GAS EXHAUST OR FUEL SUPPLY OF PROPULSION UNITS IN VEHICLES
- B60K7/00—Disposition of motor in, or adjacent to, traction wheel
- B60K7/0007—Disposition of motor in, or adjacent to, traction wheel the motor being electric
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60P—VEHICLES ADAPTED FOR LOAD TRANSPORTATION OR TO TRANSPORT, TO CARRY, OR TO COMPRISE SPECIAL LOADS OR OBJECTS
- B60P3/00—Vehicles adapted to transport, to carry or to comprise special loads or objects
-
- 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
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K16/00—Machines with more than one rotor or stator
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K3/00—Details of windings
- H02K3/04—Windings characterised by the conductor shape, form or construction, e.g. with bar conductors
- H02K3/24—Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K3/00—Details of windings
- H02K3/04—Windings characterised by the conductor shape, form or construction, e.g. with bar conductors
- H02K3/28—Layout of windings or of connections between windings
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
- H02K7/10—Structural association with clutches, brakes, gears, pulleys or mechanical starters
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P5/00—Arrangements specially adapted for regulating or controlling the speed or torque of two or more electric motors
- H02P5/46—Arrangements specially adapted for regulating or controlling the speed or torque of two or more electric motors for speed regulation of two or more dynamo-electric motors in relation to one another
Abstract
The invention discloses an aircraft tractor which comprises a tractor chassis with rollers and a motor, wherein the motor is connected with hubs of the rollers and used for driving the tractor chassis to move; the motor comprises an outer stator and an inner stator which are coaxially sleeved, an inner rotor sleeved inside the inner stator and an outer rotor sleeved outside the outer stator, and the outer rotor and the inner rotor are connected to the hub. Compared with a conventional turbine, on one hand, the motor of the aircraft tractor has the advantages that the technology of electric drive control is improved, so that the arrangement of a control system of the whole tractor can be simplified by adopting the motor drive, and the control system occupies a small space; on the other hand, the motor has a double-rotor and double-stator structure, and the size of the motor can be reduced on the premise of ensuring the output power.
Description
Technical Field
The invention relates to the technical field of aircraft traction, in particular to an aircraft tractor.
Background
The aircraft tractor is a guarantee device for dragging an aircraft on the ground, and can be used for moving large parts of the aircraft or the aircraft in the aircraft manufacturing process. The traditional aircraft ground tractor adopts turbines to drive more, has large models, high fuel consumption and complex control, and brings hidden danger to the safe operation of an airport.
In summary, how to reduce the volume of the aircraft tractor and simplify the control mode of the aircraft tractor becomes a problem to be solved urgently by those skilled in the art.
Disclosure of Invention
the invention aims to provide an aircraft tractor which is small in size and convenient to control and adjust.
To achieve the above object, the present invention provides an aircraft tractor comprising:
A tractor chassis having rollers;
the motor is connected with the wheel hub of the roller and used for driving the chassis of the tractor to move; the motor comprises an outer stator and an inner stator which are coaxially sleeved, an inner rotor sleeved inside the inner stator and an outer rotor sleeved outside the outer stator, and the outer rotor and the inner rotor are connected to the hub.
Preferably, the motor further includes a plurality of first stator coil windings embedded in the stator core of the inner stator and a plurality of second stator coil windings embedded in the stator core of the outer stator; and channels for cooling medium to circulate are arranged in the conducting wires of any one of the first stator coil winding and any one of the second stator coil winding so as to realize temperature reduction.
preferably, any one of the wires is a flat copper wire; the passageway is located flat type copper line's middle part just follows flat type copper line's length direction extends, so that flat type copper line forms hollow structure.
Preferably, any one of the leads is an enameled round copper wire; the passageway is located the middle part of enameled round copper line and edge the length direction of enameled round copper line extends, so that enameled round copper line forms the tubular structure.
Preferably, the tractor further comprises a battery pack which is arranged on the tractor chassis, connected with the motor and used for providing electric energy for the motor, and a power interface which is arranged on the tractor chassis, connected with the motor and used for connecting an external power supply to the motor.
Preferably, the number of said motors is in particular two; the motor driving device further comprises a driving unit which is connected with the two motors and used for controlling the motors to start and brake and adjusting the rotating speed and the rotating direction of the motors.
Preferably, the method further comprises the following steps:
The mechanical connector is arranged on the chassis of the tractor and used for connecting an aircraft landing gear;
And the tractor chassis, the mechanical connector and the motor are connected and used for realizing remote control, and the tractor chassis, the mechanical connector and the remote control unit of the motor are connected.
Preferably, the vehicle further comprises a fault detection unit which is connected with the tractor chassis, the mechanical connector and the motor and is used for detecting and diagnosing the tractor chassis, the mechanical connector and the motor.
Compared with the prior art, the aircraft tractor provided by the invention is driven by a motor; the motor is connected with a hub of a roller wheel arranged on the chassis of the tractor so as to drive the roller wheel to roll and realize the driving of the tractor; the motor is driven by the double stators and the double rotors, so that the size of the motor can be reduced under the condition of ensuring power, and the size of the aircraft tractor is further reduced.
Compared with a turbine, the motor of the aircraft tractor has the characteristic of small size, and the technology of electric drive control is improved, so that the control system of the whole tractor can be simplified by adopting the motor drive, the occupied space of the system is small, and the size of the aircraft tractor can be further reduced.
drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
Fig. 1 is a schematic structural diagram of an aircraft tractor according to an embodiment of the present invention;
FIG. 2 is a schematic view of the structure of FIG. 1 in another orientation;
Fig. 3 is a schematic structural diagram of a motor according to an embodiment of the present invention;
The airplane comprises an airplane landing gear 01, a tractor chassis 1, a mechanical connector 2, a motor 3, an outer stator 31, a second stator coil winding 311, an inner stator 32, a first stator coil winding 321, an inner rotor 33, an outer rotor 34, a permanent magnet 35, a motor shell 36 and a battery pack 4.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
referring to fig. 1 to 3, fig. 1 is a schematic structural diagram of an aircraft tractor according to an embodiment of the present invention; FIG. 2 is a schematic view of the structure of FIG. 1 in another orientation; fig. 3 is a schematic structural diagram of a motor according to an embodiment of the present invention.
The invention provides an aircraft tractor, which is driven by a motor 3, wherein the motor 3 is connected with a hub of a roller of the aircraft tractor, and the motion state of the roller can be quickly adjusted by adjusting the state of the motor 3; the motor 3 used in the present invention is a double-stator and double-rotor motor 3, the outer stator 31 and the inner stator 32 of the motor 3 are coaxially sleeved in the motor housing 36, the outer rotor 34 is sleeved on the outer circumference of the outer stator 31, and the inner rotor 33 is inserted into the inner stator 32, thereby forming the double-stator and double-rotor motor 3. The outer rotor 34 and the inner rotor 33 of the motor 3 are both connected with the hub, and when the inner rotor 34 and the outer rotor 34 rotate synchronously, the rollers are driven to rotate at the same rotating speed; the motion state of the tractor chassis 1 is adjusted by adjusting the state of the motor 3, such as on and off, the magnitude and direction of the rotation speed, the magnitude of the output power, and the like.
on one hand, the size of the motor 3 is reduced by arranging the double stators and the double rotors, so that the volume of the aircraft tractor is reduced; on the other hand, the movement of the tractor chassis 1 is adjusted and controlled through electric power; the aircraft tractor can be further reduced in size since the control technology for the electric drive is more advanced, both in design and in operation, and the associated space occupied in the aircraft tractor for achieving the electric control is smaller compared to the turbine.
The aircraft tractor provided by the invention is further described with reference to the accompanying drawings and the embodiment.
A channel for cooling medium to circulate is arranged in a lead of a stator coil winding of the motor 3 provided by the present application, more specifically, the stator coil includes a plurality of sets of first stator coil windings 321 embedded in a stator core of the inner stator 32 and a plurality of sets of second stator coil windings 311 embedded in a stator core of the outer stator 31, and a channel for cooling medium to circulate is arranged in a lead of any one of the first stator coil windings 321; the cooling medium may be cooling liquid or air. Similarly, a passage through which a cooling medium flows is provided in the lead wire of any of the second stator coil windings 311.
The specific position of the channel relative to the lead can be set according to the shape of the lead and the section size of the lead, and taking the lead as a flat copper wire as an example, the channel is arranged in the middle of the flat copper wire and extends along the length direction of the flat copper wire; the cross section of the channel can be circular, and can also be similar to the cross section of the flat copper wire, and for the latter, the heat conduction capability of the flat copper wire in all directions along the radial extension is equivalent and the strength is equivalent, so that the service life of the wire can be prolonged.
The flat copper wire can also be replaced by an enameled round copper wire, specifically, the conducting wires of any first stator coil and any second stator coil are all enameled round copper wires, and the cross section of a channel arranged in the enameled round copper wires is circular so that the conducting wires form a tubular structure. The arrangement mode can simplify the arrangement mode of the channel in the lead and reduce the cost of the lead.
In addition to the improvement of the first stator coil winding 321 and the second stator coil winding 311, the motor 3 provided by the present invention further includes a plurality of permanent magnets 35 attached to the surfaces of the outer rotor 34 and the inner rotor 33 to improve the performance of the motor 3.
On the basis of any embodiment, the aircraft tractor further comprises a battery pack 4 and a power interface which are arranged on the chassis 1 of the tractor, wherein the battery pack 4 and the power interface are both connected with the motor 3, the motor 3 can be independently supplied with electric energy through the battery pack 4, the motor 3 can be connected with an external power supply through a cable through the power interface, and then the external power supply supplies electric energy to the motor 3; in other words, the aircraft tractor provided by the invention has two modes of supplying power to the motor 3: firstly, a battery pack 4 independently supplies power to a motor 3; and secondly, supplying power to the motor 3 by an external power supply. The aircraft tractor does not need to use cables, so that the aircraft tractor is free from the limitation of the cables and can be used in different places; the latter requires a cable to connect an external power source and a power source interface, and thus the latter has a limited application area, and in order to shorten the length of the cable and improve safety, the latter has a small application area and should have an interface for an external power source.
In order to improve the performance of the aircraft tractor, in any of the above embodiments, the number of the motors 3 is specifically two; the aircraft tractor further comprises a driving unit which is connected with the two motors 3 and used for controlling the starting and braking of the motors 3 and adjusting the rotating speed of the motors 3.
The driving unit can adopt a common direct current bus control mode or a multi-inverter unit independent control mode for the control modes of the two motors 3, and can also be specifically set according to the applicable model of the aircraft tractor.
Further, the aircraft tractor provided by the invention further comprises a mechanical connector 2 and a remote control unit which is connected with the tractor chassis 1, the mechanical connector 2 and the motor 3 and used for remotely controlling the tractor chassis 1, the mechanical connector 2 and the motor 3. The remote control unit is used for remotely controlling the tractor chassis 1, the mechanical connector 2 and the motor 3 without direct operation, and the specific implementation manner can refer to related arrangements in the prior art, for example, a single chip microcomputer can be used for connecting the driving unit and the mechanical connector 2 in the above embodiments.
When a control signal is manually and remotely input to the single chip microcomputer, for example, a signal for increasing or decreasing the rotating speed of the motor 3 is input, the single chip microcomputer controls the driving unit to operate, and then the driving unit adjusts the frequency converter connected with the motor 3, so that the rotating speed of the motor 3 is increased or decreased.
When the model of the aircraft to be towed is large and the aircraft to be towed has a plurality of aircraft undercarriage 01, artificial long-range singlechip input signal to a plurality of aircraft tractors, the operation of the motor 3 of each aircraft tractor of single chip microcomputer control of every aircraft tractor and with tractor chassis 1 remove to the assigned position, and then open a plurality of aircraft undercarriage 01 of the same aircraft to be towed with the joint connection of mechanical connector 2 of each aircraft tractor.
Any aircraft tractor can be provided with a switch which is connected with the mechanical connector 2, is connected with the remote control unit and is used for controlling the opening and closing of the mechanical connector 2, and when the single chip microcomputer of the aircraft tractor receives a signal for opening the mechanical connector 2, the switch is controlled to adjust the position and the direction of the mechanical connector 2, so that the mechanical connector 2 is opposite to an aircraft landing gear 01. The plurality of aircraft tractors can be cooperatively matched to drag a large-size aircraft, and the model of the aircraft tractor does not need to be improved to conform to the model of the aircraft to be dragged.
The control modes of other functions of the remote control unit can be realized by referring to the control modes of the two functions, and are not described in detail herein. Since the remote control unit is usually formed by an electric circuit, the improvement of the invention consists in replacing the turbine with an electric motor 3, so that the entire aircraft tractor can be controlled purely by electric power, and both the drive and regulation control can be simplified.
Considering that various faults can occur to the aircraft tractor in the working process, the aircraft tractor further comprises a fault detection unit, the fault detection unit is connected with each structure of the aircraft tractor, and each part of the aircraft tractor can be monitored in time. For example, the fault detection unit is connected to the rotation speed detection portion of the motor 3, and can obtain the current rotation speed of the motor 3, compare the current rotation speed with the theoretical rotation speed set by the driving unit, and determine whether the current rotation speed of the motor 3 meets the theoretical rotation speed, if the current rotation speed is less than or greater than the theoretical rotation speed, the fault detection unit knows that the motor 3 is faulty, otherwise, the motor 3 operates normally. Wherein, the rotating speed monitoring part of the motor 3 can be set as a rotating speed detector fixed on the motor 3.
In addition, the fault detection unit is connected with tractor chassis 1, can acquire tractor chassis 1's position through setting up in a plurality of sensor of tractor chassis 1, and is more specific, and the fault detection unit links to each other with all sensors on tractor chassis 1, can synthesize all sensors and learn tractor chassis 1 and advance in order to judge whether whole aircraft tractor advances according to the route that the drive unit set for the position of aircraft, if then fault detection unit learns tractor chassis 1 normal operating, otherwise then tractor chassis 1 abnormal operation.
Further, the fault detection unit is also connected to the mechanical connector 2, and can monitor the mechanical connector 2, for example, a pressure sensor or a circuit switch may be disposed on the mechanical connector 2, and accordingly, the fault detection unit is connected to the pressure sensor or the circuit switch, and when the mechanical connector 2 is normally connected to the landing gear 01, the fault detection unit learns a feedback signal of the pressure sensor or learns a state of the circuit switch so as to determine whether the mechanical connector 2 is normally opened, whether the mechanical connector 2 is normally connected to the landing gear 01, and the like.
Other structures of the aircraft tractor can be arranged according to the prior art, and the invention does not improve other structures, so that the description is not provided herein.
The aircraft tractor provided by the invention is described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (8)
1. An aircraft towing vehicle, comprising:
A tractor chassis (1) with rollers;
the motor (3) is connected with the wheel hub of the roller and used for driving the tractor chassis (1) to move; the motor (3) comprises an outer stator (31) and an inner stator (32) which are coaxially sleeved, an inner rotor (33) sleeved inside the inner stator (32) and an outer rotor (34) sleeved outside the outer stator (31), and the outer rotor (34) and the inner rotor (33) are connected to the hub.
2. The aircraft tractor according to claim 1, characterized in that the electric machine (3) further comprises a plurality of first stator coil windings (321) embedded in the stator core of the inner stator (32) and a plurality of second stator coil windings (311) embedded in the stator core of the outer stator (31); and a channel for cooling medium to circulate is arranged in the conducting wire of any first stator coil winding (321) and any second stator coil winding (311).
3. The aircraft tractor of claim 2, wherein any of the wires is flat copper wire; the passageway is located flat type copper line's middle part just follows flat type copper line's length direction extends, so that flat type copper line forms hollow structure.
4. the aircraft tractor of claim 2, wherein any of the wires is an enameled round copper wire; the passageway is located the middle part of enameled round copper line and edge the length direction of enameled round copper line extends, so that enameled round copper line forms the tubular structure.
5. The aircraft tractor according to any one of claims 1 to 4, characterized by further comprising a battery pack (4) arranged on the tractor chassis (1) and connected with the motor (3) for supplying electric energy to the motor (3), and a power interface arranged on the tractor chassis (1) and connected with the motor (3) for connecting an external power source for the motor (3).
6. The aircraft tractor according to claim 5, characterized in that the number of said electric motors (3) is in particular two; the motor is characterized by further comprising a driving unit which is connected with the two motors (3) and used for controlling the starting and braking of the motors (3) and adjusting the rotating speed of the motors (3).
7. The aircraft tractor of claim 6, further comprising:
the mechanical connector (2) is arranged on the chassis (1) of the tractor and used for connecting an aircraft landing gear (01);
with tractor chassis (1) mechanical connector (2) with motor (3) all link to each other, are used for realizing remote control tractor chassis (1) mechanical connector (2) with the remote control unit of motor (3).
8. The aircraft tractor of claim 7, further comprising:
And the fault detection unit is connected with the tractor chassis (1), the mechanical connector (2) and the motor (3) and used for detecting and diagnosing the tractor chassis (1), the mechanical connector (2) and the motor (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910926662.4A CN110550225A (en) | 2019-09-27 | 2019-09-27 | Aircraft tractor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910926662.4A CN110550225A (en) | 2019-09-27 | 2019-09-27 | Aircraft tractor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110550225A true CN110550225A (en) | 2019-12-10 |
Family
ID=68741706
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910926662.4A Pending CN110550225A (en) | 2019-09-27 | 2019-09-27 | Aircraft tractor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110550225A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113002799A (en) * | 2021-04-13 | 2021-06-22 | 重庆达航工业有限公司 | Electric aircraft tractor control system and method |
| CN117097100A (en) * | 2023-10-20 | 2023-11-21 | 盛视科技股份有限公司 | Outer rotor motor and gate |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS562237A (en) * | 1979-06-14 | 1981-01-10 | Shinko Electric Co Ltd | Airplane towing tractor |
| US7466053B1 (en) * | 2008-04-10 | 2008-12-16 | Vladimir Radev | Dual-rotor electric traction motor |
| JP2010178564A (en) * | 2009-01-30 | 2010-08-12 | Honda Motor Co Ltd | Control device of electric motor |
| CN103803096A (en) * | 2007-05-16 | 2014-05-21 | 以色列宇航工业有限公司 | System And Method For Transferring Airplanes |
| CN204674377U (en) * | 2015-05-12 | 2015-09-30 | 比亚迪股份有限公司 | For aircraft towing dual-motor drive system and there is its aircraft towing |
| CN204846391U (en) * | 2015-07-29 | 2015-12-09 | 中国舰船研究设计中心 | Remote controlled electric does not have pole aircraft tractor |
| US20160096636A1 (en) * | 2014-10-04 | 2016-04-07 | Gregory Bryl | Electromagnetic Tow System For Nonpowered Ultralight Aircraft |
| CN106627101A (en) * | 2016-12-15 | 2017-05-10 | 中国北方车辆研究所 | Double rotor motor hub driving system for electric automobile |
| CN206750174U (en) * | 2017-02-28 | 2017-12-15 | 天津航天机电设备研究所 | Non-rod aircraft tractor guider and non-rod aircraft tractor |
| CN206900682U (en) * | 2017-05-31 | 2018-01-19 | 腾达航勤设备（无锡）有限公司 | A kind of power control unit of electrodynamic type aircraft tractor |
| CN207809807U (en) * | 2017-12-12 | 2018-09-04 | 北京国信智科科技有限公司 | A kind of universal tractor |
| CN210592478U (en) * | 2019-09-27 | 2020-05-22 | 卧龙电气(上海)中央研究院有限公司 | Aircraft tractor |
-
2019
- 2019-09-27 CN CN201910926662.4A patent/CN110550225A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS562237A (en) * | 1979-06-14 | 1981-01-10 | Shinko Electric Co Ltd | Airplane towing tractor |
| CN103803096A (en) * | 2007-05-16 | 2014-05-21 | 以色列宇航工业有限公司 | System And Method For Transferring Airplanes |
| US7466053B1 (en) * | 2008-04-10 | 2008-12-16 | Vladimir Radev | Dual-rotor electric traction motor |
| JP2010178564A (en) * | 2009-01-30 | 2010-08-12 | Honda Motor Co Ltd | Control device of electric motor |
| US20160096636A1 (en) * | 2014-10-04 | 2016-04-07 | Gregory Bryl | Electromagnetic Tow System For Nonpowered Ultralight Aircraft |
| CN204674377U (en) * | 2015-05-12 | 2015-09-30 | 比亚迪股份有限公司 | For aircraft towing dual-motor drive system and there is its aircraft towing |
| CN204846391U (en) * | 2015-07-29 | 2015-12-09 | 中国舰船研究设计中心 | Remote controlled electric does not have pole aircraft tractor |
| CN106627101A (en) * | 2016-12-15 | 2017-05-10 | 中国北方车辆研究所 | Double rotor motor hub driving system for electric automobile |
| CN206750174U (en) * | 2017-02-28 | 2017-12-15 | 天津航天机电设备研究所 | Non-rod aircraft tractor guider and non-rod aircraft tractor |
| CN206900682U (en) * | 2017-05-31 | 2018-01-19 | 腾达航勤设备（无锡）有限公司 | A kind of power control unit of electrodynamic type aircraft tractor |
| CN207809807U (en) * | 2017-12-12 | 2018-09-04 | 北京国信智科科技有限公司 | A kind of universal tractor |
| CN210592478U (en) * | 2019-09-27 | 2020-05-22 | 卧龙电气(上海)中央研究院有限公司 | Aircraft tractor |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113002799A (en) * | 2021-04-13 | 2021-06-22 | 重庆达航工业有限公司 | Electric aircraft tractor control system and method |
| CN117097100A (en) * | 2023-10-20 | 2023-11-21 | 盛视科技股份有限公司 | Outer rotor motor and gate |
| CN117097100B (en) * | 2023-10-20 | 2024-02-02 | 盛视科技股份有限公司 | Outer rotor motor and gate |
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