CN210592478U

CN210592478U - Aircraft tractor

Info

Publication number: CN210592478U
Application number: CN201921640857.4U
Authority: CN
Inventors: 高关中; 胡述静; 刘忠奇
Original assignee: Wolong Electric Shanghai Central Research Institute Co Ltd; Wolong Electric Group Co Ltd
Current assignee: Wolong Electric Shanghai Central Research Institute Co Ltd; Wolong Electric Drive Group Co Ltd
Priority date: 2019-09-27
Filing date: 2019-09-27
Publication date: 2020-05-22
Anticipated expiration: 2029-09-27

Abstract

The utility model discloses an aircraft tractor, which comprises a tractor chassis with rollers and a motor which is connected with the wheel hub of the rollers and is 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

Aircraft tractor

Technical Field

The utility model relates to an aircraft pulls technical field, especially relates 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.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing an aircraft tractor, its small, convenient control and regulation.

In order to achieve the above object, the utility model provides an aircraft tractor, include:

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.

Compared with the prior art, the aircraft tractor provided by the utility model is driven by the 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 required to be 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 motor comprises a traction vehicle chassis, a 3-motor, a 31-outer stator, a 311-second stator coil winding, a 32-inner stator, a 321-first stator coil winding, a 33-inner rotor, a 34-outer rotor, a 35-permanent magnet, a 36-motor shell and a 4-battery pack, wherein the traction vehicle chassis is connected with the motor through a power line.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

In order to make the technical field of the present invention better understand, the present invention will be described in detail with reference to the accompanying drawings and the detailed description.

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 utility model provides an aircraft tractor, which is driven by a motor 3, the motor 3 is connected with the wheel hub of the roller of the aircraft tractor, and the motion state of the roller can be quickly adjusted by adjusting the state of the motor 3; wherein, the utility model discloses the motor 3 that uses is the motor 3 of double stator, birotor, and in the outer stator 31 of motor 3 and the coaxial cover of inner stator 32 established and motor housing 36, the periphery of outer stator 31 is located to outer rotor 34 cover, and inner rotor 33 inserts the inside of inner stator 32 to form the motor 3 of double stator, birotor. 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 following provides a further description of the aircraft tractor according to the present invention with reference to the accompanying drawings and embodiments.

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.

Except that first stator coil winding 321 and second stator coil winding 311 are improved, the utility model provides a motor 3 still includes a plurality of attached permanent magnet 35 in outer rotor 34 surface and inner rotor 33 surface to improve motor 3 performance.

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 utility model provides an aircraft tractor possesses two modes to the power supply of 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.

The arrangement mode of other structures of the aircraft tractor can refer to the prior art, and the utility model discloses do not improve other structures, therefore no longer expand the explanation here.

It is right above that the utility model provides an aircraft tractor has carried out detailed introduction. The principles and embodiments of the present invention have been explained herein using specific examples, and the above descriptions of the embodiments are only used to help understand the method and its core ideas of the present invention. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, the present invention can be further modified and modified, and such modifications and modifications also fall within the protection scope of the appended claims.

Claims

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).