CN218966900U - Novel pure electric aircraft tractor line control electric system - Google Patents
Novel pure electric aircraft tractor line control electric system Download PDFInfo
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- CN218966900U CN218966900U CN202320008756.5U CN202320008756U CN218966900U CN 218966900 U CN218966900 U CN 218966900U CN 202320008756 U CN202320008756 U CN 202320008756U CN 218966900 U CN218966900 U CN 218966900U
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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
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Abstract
The utility model discloses a novel line control braking system of an electric aircraft tractor, which comprises a double-way liquid filling valve, an electric service foot brake pedal and a service foot brake valve driver, wherein the double-way liquid filling valve is respectively connected with a first energy accumulator and a second energy accumulator through pipelines, the first energy accumulator is connected with a front axle hydraulic brake through a front axle electrohydraulic brake valve, the second energy accumulator is connected with a rear axle hydraulic brake through a rear axle electrohydraulic brake valve, and the service foot brake valve driver is respectively electrically connected with the electric service foot brake pedal, the front axle electrohydraulic brake valve and the rear axle electrohydraulic brake valve.
Description
Technical Field
The utility model relates to the field of braking, in particular to a novel linear control power system of a pure electric aircraft tractor.
Background
At present, with the rapid development of national economy, airport construction as air transportation and airport ground supporting equipment serving the airport are advancing into a rapid development period, especially new energy type equipment with zero emission and environmental protection is greatly popularized and used, a pure electric aircraft tractor is one of the airport ground supporting equipment, a braking system is the most important and critical part, and the aircraft tractor is directly connected with an aircraft to operate, so that the braking system of the aircraft tractor is required to be relatively high and complex, and the working processes such as starting, accelerating, decelerating and stopping have strict requirements on acceleration, deceleration and braking force, are different in braking parameters of each aircraft model, and are subjected to strict system detection by an industry-specified professional detection mechanism; the system mainly comprises a service brake system, a parking brake system, an emergency brake system and the like, wherein the service brake system is the most important and critical, and because the service brake systems of the aircraft tractors at home and abroad are basically implemented by foot control direct-acting hydraulic pressure at present, the main problems are that the braking force is too hard and not soft enough, the aircraft is impacted, the accurate control is difficult, the connection of electro-hydraulic pipelines is more troublesome, particularly for the middle-large aircraft tractors with cabs needing lifting, the electro-hydraulic connection pipelines between the cabs and the vehicle body are more, the arrangement is difficult, the installation, the debugging and the maintenance are time-consuming, the trouble is very much, the normal work is inconvenient, and the work efficiency is reduced.
Disclosure of Invention
The utility model aims to overcome the defects of the prior art and provide a novel linear control and braking system of a pure electric aircraft tractor, so as to solve the technical problems in the technical background.
The aim of the utility model is realized by the following technical scheme: the utility model provides a novel pure electric aircraft tractor line control driving system, includes double-circuit liquid filling valve, electron service foot brake pedal and service foot brake valve driver, the double-circuit liquid filling valve is connected with first energy storage ware and second energy storage ware through the pipeline respectively, first energy storage ware is connected with front axle hydraulic brake through front axle electrohydraulic brake valve, the second energy storage ware is connected with rear axle hydraulic brake through rear axle electrohydraulic brake valve, service foot brake valve driver respectively with electron service foot brake pedal, front axle electrohydraulic brake valve and rear axle electrohydraulic brake valve electric connection.
In the above summary of the utility model, further, a third accumulator is further connected to the two-way charging valve, and the third accumulator is connected to a parking hydraulic brake through a parking hydraulic brake valve.
In the above summary of the utility model, further, the novel brake-by-wire system for the electric aircraft tractor further comprises a hydraulic oil tank, wherein the front axle electrohydraulic brake valve, the rear axle electrohydraulic brake valve and the parking hydraulic brake valve are all communicated with the hydraulic oil tank through oil pipes, a gear pump is connected to the double-way liquid filling valve, and hydraulic oil in the hydraulic oil tank is fed into the double-way liquid filling valve through a motor by the gear pump.
In the above summary, further, a liquid inlet end of the gear pump is connected with an oil filter, and a liquid outlet end of the gear pump is connected with a third check valve.
In the above summary of the utility model, further, oil inlet ends of the front axle electro-hydraulic brake valve and the rear axle electro-hydraulic brake valve are respectively connected with a first check valve and a second check valve.
In the above summary, further, a brake lamp signal pressure switch is connected to the front axle hydraulic brake.
In the above summary of the utility model, further, a driving brake pressure sensor is connected to the rear axle hydraulic brake.
In the above summary of the utility model, further, a throttle valve and a parking brake pressure sensor are connected to the parking hydraulic brake.
In the above summary, further, a parking brake indicator pressure switch is connected to the parking hydraulic brake valve.
In the above summary, further, the two-way filling valve is connected with a service brake low-pressure alarm switch.
The beneficial effects of the utility model are as follows:
the utility model provides a braking system simple structure, the operation is light, and the reliability is high, can carry out accurate control to the braking of tractor, reduces the impact to the aircraft in the braking process to the utility model discloses still overcome the drawback that needs laid hydraulic line between driver's cabin and automobile body, braking system's layout is more simple nimble, makes the utility model has the advantages of installation, debugging and maintenance are convenient.
Drawings
Fig. 1 is a schematic structural view of the present utility model.
In the figure, a 1-two-way liquid filling valve, a 2-electronic service foot brake pedal, a 3-service foot brake valve driver, a 4-first energy accumulator, a 5-second energy accumulator, a 6-front axle electrohydraulic brake valve, a 7-front axle hydraulic brake, an 8-rear axle electrohydraulic brake valve, a 9-rear axle hydraulic brake, a 10-third energy accumulator, an 11-parking hydraulic brake valve, a 12-parking hydraulic brake, a 13-hydraulic oil tank, a 14-gear pump, a 15-motor, a 16-oil filter, a 17-third one-way valve, a 18-first one-way valve, a 19-second one-way valve, a 20-brake lamp signal pressure switch, a 21-service brake pressure sensor, a 22-throttle valve, a 23-parking brake pressure sensor and a 24-parking brake indicator lamp pressure switch.
Detailed Description
Other advantages and effects of the present utility model will become apparent to those skilled in the art from the following disclosure, which describes the embodiments of the present utility model with reference to specific examples. The utility model may be practiced or carried out in other embodiments that depart from the specific details, and the details of the present description may be modified or varied from the spirit and scope of the present utility model. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict.
It should be noted that the illustrations provided in the following embodiments merely illustrate the basic concept of the present utility model by way of illustration, and only the components related to the present utility model are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
Examples:
referring to fig. 1, the novel electric aircraft tractor line control system comprises a double-way liquid filling valve 1, an electronic service foot brake pedal 2 and a service foot brake valve driver 3, wherein the double-way liquid filling valve 1 is respectively connected with a first energy accumulator 4 and a second energy accumulator 5 through pipelines, the first energy accumulator 4 is connected with a front axle hydraulic brake 7 through a front axle electrohydraulic brake valve 6, the second energy accumulator 5 is connected with a rear axle hydraulic brake 9 through a rear axle electrohydraulic brake valve 8, and the service foot brake valve driver 3 is respectively electrically connected with the electronic service foot brake pedal 2, the front axle electrohydraulic brake valve 6 and the rear axle electrohydraulic brake valve 8, and oil inlet ends of the front axle electrohydraulic brake valve 6 and the rear axle electrohydraulic brake valve 8 are respectively connected with a first check valve 18 and a second check valve 19.
The novel electric aircraft tractor line control braking system further comprises a hydraulic oil tank 13, the front axle electrohydraulic brake valve 6, the rear axle electrohydraulic brake valve 8 and the parking hydraulic brake valve 11 are all communicated with the hydraulic oil tank 13 through oil pipes, the double-way filling valve 1 is connected with a gear pump 14, hydraulic oil in the hydraulic oil tank 13 is fed into the double-way filling valve 1 through a motor 15 by the gear pump 14, the double-way filling valve 1 charges the first energy accumulator 4 and the second energy accumulator 5, further, the hydraulic oil in the first energy accumulator 4 and the second energy accumulator 5 always meets braking requirements and braking demands, and as an optimization, the liquid inlet end of the gear pump 14 is connected with an oil filter 16, and the liquid outlet end of the gear pump 14 is connected with a third one-way valve 17. When braking is needed in the running process, a driver uses foot to press the electronic running foot brake pedal 2, the electronic running foot brake pedal 2 automatically detects the rotation angle of the electronic pedal, then the rotation angle signal is converted into an electric signal and transmitted to the running foot brake valve driver 3, the running foot brake valve driver 3 controls the front axle electrohydraulic brake valve 6 and the rear axle electrohydraulic brake valve 8 to input hydraulic oil corresponding to the electric signal to the front axle hydraulic brake 7 and the rear axle hydraulic brake 9 for braking, so that the braking force of the tractor is softer in the braking process, the braking impact on an airplane is smaller, the braking control is more accurate and easier to realize, and the working efficiency and the working reliability are improved. In the process, the pedal rotation angle and the braking force are regulated and set proportionally, the stroke of the pedal is proportional to the output hydraulic pressure, and the larger the pedal stroke is, the larger the output hydraulic pressure is, and vice versa.
In this novel, owing to be the signal transmission to service foot brake valve driver 3 of the 2 corners of electron service foot brake pedal, overcome traditional braking mode and need lay the drawback of hydraulic pressure pipeline between driver's cabin and automobile body, braking system's layout is more simple nimble, and whole braking system is more favorable to installation, debugging and maintenance.
In the above embodiment, as a preferable mode, the front axle hydraulic brake 7 is connected with the brake lamp signal pressure switch 20, so as to display the working state of the front axle hydraulic brake 7, the rear axle hydraulic brake 9 is connected with the driving brake pressure sensor 21, so as to monitor the hydraulic pressure of the rear axle hydraulic brake 9 during braking, and the two-way filling valve 1 is connected with the driving brake low pressure alarm switch 25, so that when the two-way filling valve 1 fails to fill liquid and the hydraulic pressure is insufficient, the driving brake low pressure alarm switch 25 alarms.
More specifically, the two-way liquid filling valve 1 is further connected with a third energy accumulator 10, the third energy accumulator 10 is connected with a parking hydraulic brake 12 through a parking hydraulic brake valve 11, the parking hydraulic brake 12 is used for parking and braking a tractor, the parking hydraulic brake 12 is connected with a throttle valve 22 and a parking brake pressure sensor 23, the parking brake pressure sensor 23 is used for monitoring the pressure of parking hydraulic oil, and the parking hydraulic brake valve 11 is connected with a parking brake indicator pressure switch 24 for displaying the working state of the parking hydraulic brake 12.
The foregoing examples merely illustrate specific embodiments of the utility model, which are described in greater detail and are not to be construed as limiting the scope of the utility model. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the utility model, which are all within the scope of the utility model.
Claims (10)
1. The utility model provides a novel pure electric aircraft tractor line control driving system, its characterized in that includes double-circuit liquid filling valve, electron service foot brake pedal and service foot brake valve driver, the double-circuit liquid filling valve is connected with first energy storage ware and second energy storage ware respectively through the pipeline, first energy storage ware is connected with front axle hydraulic brake through front axle electrohydraulic brake valve, the second energy storage ware is connected with rear axle hydraulic brake through rear axle electrohydraulic brake valve, service foot brake valve driver respectively with electron service foot brake pedal, front axle electrohydraulic brake valve and rear axle electrohydraulic brake valve electric connection.
2. The novel electric aircraft tractor brake-by-wire system of claim 1, wherein the two-way charge valve is further connected with a third accumulator, and the third accumulator is connected with a parking hydraulic brake through a parking hydraulic brake valve.
3. The novel electric aircraft tractor line control system according to claim 2, further comprising a hydraulic oil tank, wherein the front axle electrohydraulic brake valve, the rear axle electrohydraulic brake valve and the parking hydraulic brake valve are all communicated with the hydraulic oil tank through oil pipes, a gear pump is connected to the double-way liquid filling valve, and hydraulic oil in the hydraulic oil tank is fed into the double-way liquid filling valve through a motor by the gear pump.
4. A novel electric aircraft tractor line control power system according to claim 3, wherein the liquid inlet end of the gear pump is connected with an oil filter, and the liquid outlet end of the gear pump is connected with a third one-way valve.
5. The novel electric aircraft tractor line control system of claim 4, wherein the oil inlet ends of the front axle electro-hydraulic brake valve and the rear axle electro-hydraulic brake valve are respectively connected with a first check valve and a second check valve.
6. A novel electric only aircraft tractor line control power system as claimed in claim 1 wherein said front axle hydraulic brake is connected with a brake light signal pressure switch.
7. A new electric only aircraft tractor line control power system as claimed in claim 1 wherein a drive brake pressure sensor is connected to the rear axle hydraulic brake.
8. A new electric only aircraft tractor line control brake system as claimed in claim 2, wherein the parking hydraulic brake is connected with a throttle valve and a parking brake pressure sensor.
9. A new electric only aircraft tractor line control power system as claimed in claim 2 wherein the park hydraulic brake valve is connected with a park brake pilot pressure switch.
10. The novel electric aircraft tractor line control system of claim 1, wherein the two-way charge valve is connected with a service brake low pressure alarm switch.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320008756.5U CN218966900U (en) | 2023-01-03 | 2023-01-03 | Novel pure electric aircraft tractor line control electric system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320008756.5U CN218966900U (en) | 2023-01-03 | 2023-01-03 | Novel pure electric aircraft tractor line control electric system |
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| Publication Number | Publication Date |
|---|---|
| CN218966900U true CN218966900U (en) | 2023-05-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320008756.5U Active CN218966900U (en) | 2023-01-03 | 2023-01-03 | Novel pure electric aircraft tractor line control electric system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218966900U (en) |
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2023
- 2023-01-03 CN CN202320008756.5U patent/CN218966900U/en active Active
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