CN202828102U - Airplane main wheel drive unit - Google Patents
Airplane main wheel drive unit Download PDFInfo
- Publication number
- CN202828102U CN202828102U CN2011205796813U CN201120579681U CN202828102U CN 202828102 U CN202828102 U CN 202828102U CN 2011205796813 U CN2011205796813 U CN 2011205796813U CN 201120579681 U CN201120579681 U CN 201120579681U CN 202828102 U CN202828102 U CN 202828102U
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- Prior art keywords
- wheel
- drive
- drive unit
- converter
- driving wheel
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Abstract
Provided is an airplane main wheel drive unit, which can assist to check an antiskid brake system of an airplane, and comprises a motor, a driving wheel, a driven wheel, a drive wheel, and an AC frequency converter. The driving wheel is a part of the motor, and the driven wheel and the drive wheel are coaxially fixed together side by side. The rotation of the motor drives the driving wheel to rotate, and the driving wheel drives the driven wheel and the drive wheel to rotate through a belt. The drive wheel drives the airplane main wheel, and the motor adopts an AC motor, and the AC frequency converter matches with the AC motor. The change of rotating speed of the AC motor is set through the AC frequency converter, and the transmission is conducted through the driving wheel, the driven wheel and the drive wheel, and the speed change of the airplane main wheel can be realized. The airplane main wheel drive unit is advantageous in that the speed change of the airplane main wheel can be realized by setting the rotating speed; work efficiency of detecting the antiskid brake system of the airplane main wheel can be improved; detection cost is saved, and the drive unit is simple in structure and convenient to maintain.
Description
Technical field
The utility model relates to the detection technique field, is specifically related to a kind of device that the driving aircraft main wheel of subsidiary inspection Aircraft Anti-skid Break Control is rotated.
Background technology
Mistake after aircraft landing lands, the anti-skid brake system (ABS) of aircraft main wheel is started working, thereby shortens landing time and the stroke of aircraft.If the anti-skid brake system (ABS) of aircraft main wheel breaks down, will affect the landing safety of aircraft, so in the production and maintenance process of aircraft, the anti-skid brake system (ABS) of aircraft detected just becomes more important operation.Along with the raising of airplane brake system technical merit, the anti-skid brake system (ABS) indices is more strict.In production or maintenance process, different power need to be provided, make the aircraft main wheel reach various rotating speeds, and then judge whether airplane brake system all reaches the brake system technical requirements under different rotating speeds.When in the prior art aircraft main wheel anti-skid brake system (ABS) being checked, drag runner with motor by belt and rotate, drive the aircraft main wheel and rotate the inspection of braking.The Aircraft Main wheel drive of this fixedly output speed dress can not satisfy the demand of present ground check brake system at present.The Aircraft Main wheel drive unit is to drive wheel when providing anti-skid brake system (ABS) to detect for aircraft to rotate required propulsion source, is used for the reliability of the normal and work of ground check main wheel anti-skid brake system (ABS).
Summary of the invention
For solving the problems of the technologies described above, the utility model provides a kind of and has driven runner driving aircraft main wheel rotation system by controlled variable-frequency motor, realizes that the band rotary speed is adjustable, satisfies the Aircraft Anti-skid Break Control Index for examination.
The Aircraft Main wheel drive unit, comprise electrical motor, driving wheel, flower wheel, drive wheel form, described driving wheel is a part, the flower wheel of electrical motor and drive wheel is coaxial captives joint side by side, and electrical motor rotates and drives driving wheel and rotate, driving wheel by belt drive flower wheel, drive wheel rotates, drive wheel drives the aircraft main wheel, it is characterized in that: comprise AC converter, described electrical motor is selected alternating current dynamo, and the frequency of AC converter and alternating current dynamo, rotating speed will be complementary; AC converter links to each other with alternating current dynamo, by the rotation speed change of AC converter setup control alternating-current motor/AC motor, and through driving wheel, flower wheel, drive wheel transmission, thus the velocity variations of realization aircraft main wheel.
The utility model is by introducing AC converter and alternating current dynamo, realized only setting the velocity variations that rotating speed just can be realized the aircraft main wheel, improved the work efficiency that detects aircraft main wheel anti-skid brake system (ABS), saved testing cost, and this driving device structure simple, be convenient to safeguard.
Description of drawings
Of the present utility model being described as follows:
Fig. 1 is that machinery of the present utility model uses scheme drawing;
Fig. 2 is structured flowchart of the present utility model;
Among the figure: 1. speed adjustment handle 2. AC converter 3. dollies 4. alternating current dynamos 5. driving wheels 6. flower wheels 7. drive wheels 8. main airplane wheels 9. belts 10. indicator lamps 11. resistance.
The specific embodiment
Below in conjunction with accompanying drawing the utility model is described as follows:
The Aircraft Main wheel drive unit, comprise electrical motor, driving wheel 5, flower wheel 6, drive wheel 7 form, the part that described driving wheel 5 is electrical motor, flower wheel 6 and drive wheel 7 are coaxial captives joint side by side, electrical motor rotates and drives driving wheel 5 rotations, driving wheel 5 drives flower wheel 6, drive wheel 7 rotations by belt 9, drive wheel 7 drives the aircraft main wheel, it is characterized in that: this device also comprises AC converter 2, described electrical motor is selected alternating current dynamo 4, and AC converter 2 will be complementary with frequency, the rotating speed of alternating current dynamo 4; AC converter 2 links to each other with alternating current dynamo 4, by the rotation speed change of the speed adjustment handle 1 control alternating current dynamo 4 on the AC converter 2, and through driving wheel 5, flower wheel 6, drive wheel 7 transmissions, thus the velocity variations of realization main airplane wheel 8.
When ambient temperature is lower than-10 ℃, AC converter 2 can't work, adaptive capacity to environment for assurance device, it is wide warm nature, this device can also arrange heating module, provide electric energy by the 380V that gives AC converter 2, alternating current dynamo 4 power supplies, with indicator lamp 10, resistance 11 rear end ground connection in parallel, the other end links to each other with power supply by switch.
Described heater circuit can also arrange many groups, with the normal operation of assurance device.
For make this actuating device movability stronger, use more conveniently, the parts such as AC converter 2, alternating current dynamo 4 can also be fixed on the dolly 3.
Protection domain of the present utility model is not limited only to the disclosed technical scheme of specific embodiment part, all modes of having utilized AC converter to cooperate with alternating current dynamo, and the technical scheme that changes Aircraft Main wheel speed on ground all falls into protection domain of the present utility model.
Claims (3)
1. Aircraft Main wheel drive unit, comprise speed adjustment handle (1), electrical motor, driving wheel (5), flower wheel (6), drive wheel (7) forms, described driving wheel (5) is the part of electrical motor, flower wheel (6) is captiveed joint side by side with drive wheel (7) is coaxial, electrical motor rotates and drives driving wheel (5) rotation, driving wheel (5) drives flower wheel (6) by belt (9), drive wheel (7) rotates, drive wheel (7) drives aircraft main wheel (8), it is characterized in that: this device also comprises AC converter (2), described electrical motor is selected alternating current dynamo (4), the frequency of AC converter (2) and alternating current dynamo (4), rotating speed will be complementary; AC converter (2) links to each other with alternating current dynamo (4), rotation speed change by the control alternating current dynamo of the speed adjustment handle (1) on the AC converter (2) (4), through driving wheel (5), flower wheel (6), drive wheel (7) transmission, thus the velocity variations of realization main airplane wheel (8).
2. Aircraft Main wheel drive unit according to claim 1, it is characterized in that: can comprise heating module, the resistance (11) that comprises indicator lamp and heating, with indicator lamp (10), resistance (a 11) rear end ground connection in parallel, the other end links to each other with the 380V power supply by switch.
3. Aircraft Main wheel drive unit according to claim 1 is characterized in that: described heater circuit can also arrange many groups and be connected in parallel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205796813U CN202828102U (en) | 2011-12-23 | 2011-12-23 | Airplane main wheel drive unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205796813U CN202828102U (en) | 2011-12-23 | 2011-12-23 | Airplane main wheel drive unit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202828102U true CN202828102U (en) | 2013-03-27 |
Family
ID=47939866
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011205796813U Expired - Fee Related CN202828102U (en) | 2011-12-23 | 2011-12-23 | Airplane main wheel drive unit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202828102U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103630355A (en) * | 2013-12-18 | 2014-03-12 | 沈阳飞研航空设备有限公司 | Machine wheel rotating equipment |
| CN105716884A (en) * | 2014-11-30 | 2016-06-29 | 中航贵州飞机有限责任公司 | Airplane brake system detecting device |
| CN108106856A (en) * | 2016-11-24 | 2018-06-01 | 中航贵州飞机有限责任公司 | A kind of airplane brake system tests and analyzes device |
-
2011
- 2011-12-23 CN CN2011205796813U patent/CN202828102U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103630355A (en) * | 2013-12-18 | 2014-03-12 | 沈阳飞研航空设备有限公司 | Machine wheel rotating equipment |
| CN105716884A (en) * | 2014-11-30 | 2016-06-29 | 中航贵州飞机有限责任公司 | Airplane brake system detecting device |
| CN108106856A (en) * | 2016-11-24 | 2018-06-01 | 中航贵州飞机有限责任公司 | A kind of airplane brake system tests and analyzes device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130327 Termination date: 20161223 |