CN101417710A - Slipping steerage device of aircraft tractor - Google Patents
Slipping steerage device of aircraft tractor Download PDFInfo
- Publication number
- CN101417710A CN101417710A CNA200810158182XA CN200810158182A CN101417710A CN 101417710 A CN101417710 A CN 101417710A CN A200810158182X A CNA200810158182X A CN A200810158182XA CN 200810158182 A CN200810158182 A CN 200810158182A CN 101417710 A CN101417710 A CN 101417710A
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- wheel
- gear box
- reversing valve
- hydraulic pump
- speed gear
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Abstract
The invention relates to an aircraft tractor sliding steering apparatus, belonging to the aviation ground equipment field. The apparatus comprises a power source, a gear box and a PLC control system and is characterized in that the power source is directly connected with the gear box; a hydraulic pump is arranged on the gear box and is connected with wheels through a two-way driving motor; each wheel is rigidly connected with the tractor body; a front-left wheel and a back-left wheel are connected with the hydraulic pump through one hydraulic pipeline and a left-proportion reversing valve; and a front-right wheel and a back-right wheel are connected with the hydraulic pump through another hydraulic pipeline and a right-proportion reversing valve. The invention adopts the sliding steering mechanism to independently control the angles and steering of four tires so as to meet the requirements of small radius of the turning of the aircraft tractor and realize the local steering by 360 degrees.
Description
Technical field
The present invention relates to aviation surface facility field, say it is a kind of slipping steerage device of aircraft tractor that is used for aircraft traction or pushing tow in detail.
Background technology
As everyone knows, aircraft towing is operated under aircraft or the shelter bridge, and working space is limited, so require aircraft towing that turn radius is limited; The aircraft towing deadweight is bigger, requires aircraft towing oad and vehicle bridge to satisfy the load distribution requirement, because there is the steering locking angle degree in vehicle bridge, thus there is minimum turning radius, and can not realize pivot stud.
At present, the airliner place uses the deadweight tonnage of aircraft increasing, and airport service equipment and vehicle are more and more, and working space is subjected to very big restriction.Require deadweight proportional increase along with the increase of aircraft tonnage of aircraft towing, and adopt bigger load-carrying capacity to drive steeraxle, there is greatest measure in the steering angle of steeraxle, causes the aircraft towing turn radius to increase.
Chinese patent 200420039065.9 discloses " Airtow power transmitting means ", this device adopts driving engine, change speed gear box, drive axle arranged crosswise, driving engine and change speed gear box direct connection also are arranged in the top of drive axle, change speed gear box is connected with drive axle by the transmission shaft that has universal-joint, be characterized in compact conformation, stable drive, be fit to compact tractor.
Chinese patent 200420039064.4 discloses " aircraft towing engine installation ", this device driving engine, change speed gear box, drive axle are arranged apart, direct connection not between driving engine and the change speed gear box, but connect by the transmission shaft that has universal-joint, the power of driving engine is connected with coupler through flywheel, coupler is connected with transmission shaft, and transmission shaft is connected with change speed gear box/tor-con, the output that tor-con is regulated moment of torsion according to the service condition and the condition of loading of tractor truck.Be characterized in: owing to adopt universal drive shaft to be connected between driving engine and the change speed gear box, changed engine location and it is highly reduced.
200420039065.9 and the deficiency of 200420039064.4 technology is: its steering drive axle that adopts exists steering locking angle, so can't realize the original place turns to for 360 °, because the existence of front and back bridge, whole width of vehicle and wheelbase are retrained, and Turning radius is directly determined by the configuration of drive axle.
Because existing aircraft towing all adopts steering drive axle, entad turns to even be designed to four-wheel, Turning radius also is bigger, and can't realize that the original place turns to for 360 °.The front and back bridge is connected with driving engine by transmission shaft, change speed gear box, and height of car, length, width are had constraint, has strengthened the aircraft towing oad.
Summary of the invention
There is steering locking angle in order to overcome existing steering drive axle, and vehicle overall size is subjected to the constraint of auxiliary equipment sizes such as vehicle bridge, driving engine, change speed gear box, cause the aircraft towing Turning radius bigger on the one hand, can't realize that the original place turns to for 360 °, the tractor truck oad is strengthened, increased production car operation place; Adopt transmission shaft to be connected between vehicle bridge and the change speed gear box, increased the deficiency of tractor truck length dimension, the object of the present invention is to provide a kind of slipping steerage device of aircraft tractor, this device is taked propulsion source and change speed gear box direct connection, Hydraulic Pump is installed on the change speed gear box, each wheel can realize that by the magnanimous control of PLC control system Turning radius is little, but and the original place turn to for 360 °.
The present invention adopts following technical solution: a kind of slipping steerage device of aircraft tractor, be provided with propulsion source, change speed gear box and PLC control system, it is characterized in that: propulsion source and change speed gear box direct connection, Hydraulic Pump is installed on the change speed gear box, be connected with wheel by the bi-directional drive motor, each wheel is connected with the car body rigidity, front left wheel is connected with Hydraulic Pump through left proportional reversing valve by same hydraulic tubing with left back wheel, and right front wheel is connected with Hydraulic Pump through right proportional reversing valve by another hydraulic tubing with right rear wheel.
The present invention can realize that also the PLC control system is connected with steering-by-wire device signal by following measure.The PLC control system is connected with the proportional reversing valve signal of each wheel of control.Proportional reversing valve is connected by the road with CD-ROM drive motor.
The invention has the beneficial effects as follows, owing to adopt glide steering mechanism, four tire angles and turn to and can control separately, it is little to satisfy the aircraft towing turn radius, but the original place is carried out 360 ° and is turned to.
Description of drawings
The present invention is further described below in conjunction with drawings and Examples.
Fig. 1 is the structural representation of slipping steerage device of aircraft tractor of the present invention.
Fig. 2 is that slipping steerage device of aircraft tractor of the present invention turns to scheme drawing
Among Fig. 1,1, the steering-by-wire device, 2, tire, 3, CD-ROM drive motor, 4, propulsion source, 5, Hydraulic Pump, 6, hydraulic reservoir, 7, proportional reversing valve, 8, the PLC control system, 9, change speed gear box.
The specific embodiment
The invention will be further described below in conjunction with the drawings and specific embodiments, to help understanding content of the present invention.
As Fig. 1, shown in Figure 2, the present invention is provided with propulsion source 4, change speed gear box 9 and PLC control system 8, propulsion source 4 and change speed gear box 9 direct connections, Hydraulic Pump 5 is installed on the change speed gear box 9, by about two bi-directional drive motors 3 be connected with the left and right sides wheel respectively, tire 2 is installed on the wheel, the left and right sides wheel is connected with the car body rigidity, front left wheel is connected with Hydraulic Pump 5 through left proportional reversing valve 7 by same hydraulic tubing with left back wheel, right front wheel is connected with Hydraulic Pump 5 through right proportional reversing valve 7 by another hydraulic tubing with right rear wheel, Hydraulic Pump 5 is connected with hydraulic reservoir 6, PLC control system 8 is connected with steering-by-wire device 1 signal, PLC control system 8 is connected with left and right sides proportional reversing valve 7 signals of control left and right sides wheel, and left and right sides proportional reversing valve 7 is connected by the road with left and right sides CD-ROM drive motor 3 respectively.
The present invention has adopted propulsion source 4 to be connected with change speed gear box 9, and Hydraulic Pump 5 is installed on the change speed gear box 9, and each drive wheel is connected with the car body rigidity, and drive wheel drives by hydraulic bidirectional CD-ROM drive motor 3, and whole device does not have drive axle and transmission shaft.Propulsion source 4 and change speed gear box 9 can require to distribute according to the vehicle overall load.Reduced car body front and back size, reduced the car load height, it is even to reach distribution of load on distribution of load, and makes full use of the car body zone line, easy to maintenance.
Suppose that the motor-driven aircraft towing of this slippage advances when turning to the left in the process, chaufeur is steering wheel rotation to the left, steering-by-wire device 1 sends corresponding electric signal PLC control system 8 according to the electric signal that receives according to the angle that bearing circle turns over to PLC control system 8, and the left and right sides proportional reversing valve 7 that calculates to control left and right sides CD-ROM drive motor 3 by its in-to-in program sends electric signal; Left and right sides proportional reversing valve 7 is after receiving electric signal, and the proportional reversing valve 7 spool apertures of control right side CD-ROM drive motor 3 are greater than the proportional reversing valve 7 spool apertures of control left side CD-ROM drive motor 3; Since about two proportional reversing valve 7 spool aperture differences, CD-ROM drive motor 3 rotating speeds in right side are greater than left side CD-ROM drive motor 3 rotating speeds, thereby produce different linear velocities, so realize Vehicular turn.Because each drive wheel of vehicle is that rigidity is connected on the car body, each wheel turns to center of circle radius difference relatively in the steering procedure, and the propulsive effort of vehicle right side tire 2 is greater than the ground side friction resistance of left side tire 2, so the transverse slip phenomenon appears in left side tire 2.Steering angle is big more, and the sliding phenomenon of vehicle left side tire 2 is big more.
Suppose the motor-driven aircraft towing of slippage left face to the time, vehicle left side does not rotatablely move.Invention can be used for the motor-driven steering hardware of large aircraft tractor truck slippage.
Claims (4)
1, a kind of slipping steerage device of aircraft tractor, be provided with propulsion source, change speed gear box and PLC control system, it is characterized in that: propulsion source and change speed gear box direct connection, Hydraulic Pump is installed on the change speed gear box, be connected with wheel by the bi-directional drive motor, each wheel is connected with the car body rigidity, and front left wheel is connected with Hydraulic Pump through left proportional reversing valve by same hydraulic tubing with left back wheel, and right front wheel is connected with Hydraulic Pump through right proportional reversing valve by another hydraulic tubing with right rear wheel.
2,, it is characterized in that said PLC control system is connected with steering-by-wire device signal according to the described slipping steerage device of aircraft tractor of claim 1.
3,, it is characterized in that said PLC control system is connected with the proportional reversing valve signal of each wheel of control according to the described slipping steerage device of aircraft tractor of claim 1.
4,, it is characterized in that said proportional reversing valve is connected by the road with CD-ROM drive motor according to the described slipping steerage device of aircraft tractor of claim 1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA200810158182XA CN101417710A (en) | 2008-10-30 | 2008-10-30 | Slipping steerage device of aircraft tractor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA200810158182XA CN101417710A (en) | 2008-10-30 | 2008-10-30 | Slipping steerage device of aircraft tractor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101417710A true CN101417710A (en) | 2009-04-29 |
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ID=40628746
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA200810158182XA Pending CN101417710A (en) | 2008-10-30 | 2008-10-30 | Slipping steerage device of aircraft tractor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101417710A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103662072A (en) * | 2012-09-17 | 2014-03-26 | 上海航福机场设备有限公司 | Aircraft tractor |
| CN105691601A (en) * | 2016-01-28 | 2016-06-22 | 北京航空航天大学 | Aircraft propelling device based on hydraulic motor and propelling control system |
| CN107264830A (en) * | 2017-07-31 | 2017-10-20 | 威海广泰空港设备股份有限公司 | Air Ground Equipment active safety docks aircraft system |
-
2008
- 2008-10-30 CN CNA200810158182XA patent/CN101417710A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103662072A (en) * | 2012-09-17 | 2014-03-26 | 上海航福机场设备有限公司 | Aircraft tractor |
| CN103662072B (en) * | 2012-09-17 | 2016-04-13 | 上海航福机场设备有限公司 | A kind of aircraft towing |
| CN105691601A (en) * | 2016-01-28 | 2016-06-22 | 北京航空航天大学 | Aircraft propelling device based on hydraulic motor and propelling control system |
| CN107264830A (en) * | 2017-07-31 | 2017-10-20 | 威海广泰空港设备股份有限公司 | Air Ground Equipment active safety docks aircraft system |
| CN107264830B (en) * | 2017-07-31 | 2023-06-02 | 威海广泰空港设备股份有限公司 | Active safety docking aircraft system for aviation ground equipment |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20090429 |