CN105775111B - The buffer structure of airplane wheel - Google Patents
The buffer structure of airplane wheel Download PDFInfo
- Publication number
- CN105775111B CN105775111B CN201610330392.7A CN201610330392A CN105775111B CN 105775111 B CN105775111 B CN 105775111B CN 201610330392 A CN201610330392 A CN 201610330392A CN 105775111 B CN105775111 B CN 105775111B
- Authority
- CN
- China
- Prior art keywords
- hydraulic cylinder
- buffering hydraulic
- buffer
- surge chamber
- buffer gear
- 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.)
- Expired - Fee Related
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
- B64C25/36—Arrangements or adaptations of wheels, tyres or axles in general
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Tires In General (AREA)
- Vehicle Body Suspensions (AREA)
Abstract
The present invention provides a kind of buffer structure for the airplane wheel that can cut down on ground to the huge recoil strength of wheel in aircraft landing, including supporting plate, the wheel of connection corresponding with support shaft, in addition to the first buffer gear, the second buffer gear for being longitudinally disposed at below the supporting plate；The lower end of second buffer gear is connected with the support shaft, and one end and the support shaft of first buffer gear are hinged, and the other end of first buffer gear is articulated with the supporting plate at the second buffer gear rear；And first buffer gear, the second buffer gear, the triangle structure of supporting plate three；The buffer structure of the design can be provided for wheel and safely and effectively protected, and huge recoil strength that can be effectively by ground to wheel is eliminated, and provided and safely and effectively ensured for the safe landing of aircraft.
Description
Technical field
The present invention relates to aircraft technology field, more particularly to a kind of buffer structure of airplane wheel.
Background technology
Aircraft, especially for passenger plane, heavy freighter for, the fuselage weight of its aircraft is larger, and in aircraft landing,
The wheel of its aircraft is contacted with ground first, and the moment contacted in airplane wheel with ground, and its ground is huge to wheel one
Recoil strength, and this recoil strength will cause fatal harm if do not overcome to aircraft, and such a phenomenon is more bright on transporter
It is aobvious, particularly when transporter is dropped on off-gauge machine road, particularly need to avoid.
The content of the invention
It is an object of the invention to overcome the deficiencies in the prior art, the real needs of adaptation are there is provided one kind in aircraft landing
The buffer structure for the airplane wheel that ground can be cut down to the huge recoil strength of wheel.
In order to realize the purpose of the present invention, the technical solution adopted in the present invention is：
Design a kind of buffer structure of airplane wheel, including supporting plate, the wheel of connection corresponding with support shaft, in addition to
One buffer gear, the second buffer gear being longitudinally disposed at below the supporting plate；The lower end of second buffer gear and institute
Support shaft connection is stated, one end and the support shaft of first buffer gear are hinged, the other end of first buffer gear
In the supporting plate for being articulated with the second buffer gear rear；And first buffer gear, the second buffer gear, supporting plate three's structure
Triangularity structure.
Further, first buffer gear includes the first pipe fitting, is provided with the middle part of first inside pipe fitting
First dividing plate, and first pipe fitting by first dividing plate by the cavity in first pipe fitting be divided into the first surge chamber,
Second surge chamber；The first buffering hydraulic cylinder is provided with first surge chamber；The cylinder body of first buffering hydraulic cylinder and institute
Supporting plate is stated to be hinged；The telescopic shaft top pressure of first buffering hydraulic cylinder is on the first dividing plate inside first surge chamber；
Further, the second buffering hydraulic cylinder is provided with second surge chamber, and in second surge chamber
First pressure sensor is additionally provided with first dividing plate, the cylinder body top pressure of second buffering hydraulic cylinder is sensed in the first pressure
On device, end and the support shaft of the telescopic shaft of second buffering hydraulic cylinder are hinged, and second buffering hydraulic cylinder
The normality of telescopic shaft is stretching state.
Further, the normality of the telescopic shaft of first buffering hydraulic cylinder is stretching state.
Further, the first buffer spring is also cased with the telescopic shaft of first buffering hydraulic cylinder, described first delays
The lower end for rushing spring is withstood on first dividing plate.
Further, second buffer gear includes the second pipe fitting, is provided with the middle part of second inside pipe fitting
Second partition, and second pipe fitting by the second partition by the cavity in second pipe fitting be divided into the 3rd surge chamber,
4th surge chamber；The 3rd buffering hydraulic cylinder is provided with the 3rd surge chamber；The cylinder body of 3rd buffering hydraulic cylinder and institute
Supporting plate is stated to be hinged；The telescopic shaft top pressure of 3rd buffering hydraulic cylinder is on the second partition inside the 3rd surge chamber；
Further, the 4th buffering hydraulic cylinder is provided with the 4th surge chamber, and in the 4th surge chamber
Second pressure sensor is additionally provided with second partition, the cylinder body top pressure of the 4th buffering hydraulic cylinder is sensed in the second pressure
On；The normality of the telescopic shaft of 4th buffering hydraulic cylinder is stretching state, and the telescopic shaft of the 4th buffering hydraulic cylinder
End is hinged with the support shaft.
Further, the telescopic shaft normality of the 3rd buffering hydraulic cylinder is stretching state.
Further, the second buffer spring is also cased with the telescopic shaft of the 3rd buffering hydraulic cylinder, described second delays
The lower end for rushing spring is withstood on the second partition.
Further, in addition to controller, the first pressure sensor, second pressure sensor with the controller
Connection, in addition to the first magnetic valve, the second magnetic valve, the 3rd magnetic valve, the 4th magnetic valve being connected with the controller, it is described
First buffering hydraulic cylinder, the second buffering hydraulic cylinder, the 3rd buffering hydraulic cylinder, the 4th buffering hydraulic cylinder pass through the first electromagnetism respectively
Valve, the second magnetic valve, the 3rd magnetic valve, the 4th magnetic valve are connected with oil pump.
The beneficial effects of the present invention are：
The buffer structure of the design can be provided for wheel and safely and effectively protected, can be effectively by ground to wheel
Huge recoil strength is cut down, and provides and safely and effectively ensures for the safe landing of aircraft.
Brief description of the drawings
Fig. 1 is primary structure schematic diagram of the invention；
Fig. 2 is cross-sectional view of the invention；
In figure：1. supporting plate；2. the second pipe fitting；3. the first pipe fitting；4. the 3rd buffering hydraulic cylinder；5. the first buffering hydraulic
Cylinder；6. the 4th buffering hydraulic cylinder；7. the second buffering hydraulic cylinder；8. the pin joint of the 3rd buffering hydraulic cylinder and supporting plate；9. first
The cylinder body of buffering hydraulic cylinder and the pin joint of supporting plate；10. the telescopic shaft of the 4th buffering hydraulic cylinder；11. the second buffering hydraulic cylinder
Telescopic shaft；12. support shaft；13. wheel；14. second partition；15. the first dividing plate；17. the telescopic shaft of the 3rd buffering hydraulic cylinder；
18. the telescopic shaft of the first buffering hydraulic cylinder；19. the second buffer spring；20. the first buffer spring；21. second pressure sensor；
22. first pressure sensor.
Embodiment
The present invention is further described with reference to the accompanying drawings and examples：
Embodiment 1：A kind of buffer structure of airplane wheel, referring to Fig. 1, Fig. 2；Including supporting plate 1, corresponding with support shaft 12
The wheel 13 of connection, in addition to the first buffer gear, the second buffer gear for being longitudinally disposed at the lower section of supporting plate 1；It is described
The lower end of second buffer gear is connected with the support shaft 12, and one end of first buffer gear is cut with scissors with the support shaft 12
Connect, the other end of first buffer gear is articulated with the supporting plate 1 at the second buffer gear rear；And first buffer
Structure, the second buffer gear, the triangle structure of the three of supporting plate 1.
Specifically, above-described first buffer gear includes the first pipe fitting 3, the middle part inside first pipe fitting 3
The first dividing plate 15 is provided with, and the cavity in first pipe fitting 3 is divided into by first pipe fitting 3 by first dividing plate 15
First surge chamber, the second surge chamber；The first buffering hydraulic cylinder 5 is provided with first surge chamber；First buffering hydraulic
The cylinder body of cylinder 5 is hinged with the supporting plate 1；The top pressure of telescopic shaft 18 of first buffering hydraulic cylinder is in first surge chamber
On first dividing plate 15 in portion；The second buffering hydraulic cylinder 7 is provided with second surge chamber, and in second surge chamber
First pressure sensor 22 is additionally provided with first dividing plate 15, the cylinder body top pressure of second buffering hydraulic cylinder 7 is in the described first pressure
On force snesor 22, the end of the telescopic shaft 11 of second buffering hydraulic cylinder is hinged with the support shaft 12, and described second
The normality of the telescopic shaft 11 of buffering hydraulic cylinder is stretching state.
Further, the normality of the telescopic shaft 18 of above-described first buffering hydraulic cylinder is stretching state, described the
Also it is cased with the first buffer spring 20 on the telescopic shaft 18 of one buffering hydraulic cylinder, the lower end of first buffer spring 20 withstands on described
On first dividing plate 15.
Specifically, above-described second buffer gear includes the second pipe fitting 2, the middle part inside second pipe fitting 2
Second partition 14 is provided with, and the cavity in second pipe fitting is divided into by second pipe fitting 2 by the second partition 14
3rd surge chamber, the 4th surge chamber；The 3rd buffering hydraulic cylinder 4 is provided with the 3rd surge chamber；3rd buffering hydraulic
The cylinder body of cylinder 4 is hinged with the supporting plate 1；The top pressure of telescopic shaft 17 of 3rd buffering hydraulic cylinder is in the 3rd surge chamber
On the second partition 14 in portion；The 4th buffering hydraulic cylinder 6 is provided with the 4th surge chamber, and in the 4th surge chamber
Second pressure sensor 21 is additionally provided with second partition 14, the cylinder body top pressure of the 4th buffering hydraulic cylinder 6 is in the described second pressure
In power sensing 21；The normality of the telescopic shaft 10 of 4th buffering hydraulic cylinder is stretching state, and the 4th buffering hydraulic cylinder
The end of telescopic shaft 10 be hinged with the support shaft 12.
Specifically, the normality of telescopic shaft 17 of above-described 3rd buffering hydraulic cylinder is stretching state, it is slow the described 3rd
The second buffer spring 19 is also cased with the telescopic shaft 17 of fliud flushing cylinder pressure, the lower end of second buffer spring 19 withstands on described second
On dividing plate 14.Further, in addition to controller, the first pressure sensor, second pressure sensor with the control
Device is connected, in addition to the first magnetic valve, the second magnetic valve, the 3rd magnetic valve, the 4th magnetic valve, institute being connected with the controller
The first buffering hydraulic cylinder, the second buffering hydraulic cylinder, the 3rd buffering hydraulic cylinder, the 4th buffering hydraulic cylinder are stated respectively by the first electromagnetism
Valve, the second magnetic valve, the 3rd magnetic valve, the 4th magnetic valve are connected with oil pump.
The design is operationally：Aircraft left direction into Fig. 1 advances, and its airplane wheel with ground when contacting, its ground
Face and fuselage give wheel one pressure, and then its 3rd buffering hydraulic cylinder, the 4th buffering hydraulic cylinder play main cushioning effect,
And its airplane wheel can also be moved to the right in the process, hereafter its first buffering hydraulic cylinder, the second buffering hydraulic cylinder
Secondary cushioning effect is played, and in this buffering course, if its first pressure sensor, second pressure sensor are detected
Pressure it is excessive, its controller will control corresponding first magnetic valve, the second magnetic valve, the 3rd magnetic valve, the 4th magnetic valve will
First buffering hydraulic cylinder, the second buffering hydraulic cylinder, the 3rd buffering hydraulic cylinder, the 4th buffering hydraulic cylinder carry out pressure release, then entered again
Row punching press base, realizes local retraction, the stretching of telescopic shaft repeatedly on buffering hydraulic cylinder, and the reciprocal frequent operation of this process
Cushioning effect can be achieved；And its first buffer spring and the second buffer spring also will be helpful to cushioning effect in above process.
What embodiments of the invention were announced is preferred embodiment, but is not limited thereto, the ordinary skill people of this area
Member, easily according to above-described embodiment, understands the spirit of the present invention, and makes different amplifications and change, but as long as not departing from this
The spirit of invention, all within the scope of the present invention.
Claims (7)
1. a kind of buffer structure of airplane wheel, including supporting plate, the wheel of connection corresponding with support shaft, it is characterised in that：Also
Including the first buffer gear, the second buffer gear being longitudinally disposed at below the supporting plate；Under second buffer gear
End is connected with the support shaft, and one end and the support shaft of first buffer gear are hinged, first buffer gear
The other end is articulated with the supporting plate at the second buffer gear rear；And first buffer gear, the second buffer gear, supporting plate
The triangle structure of three；First buffer gear includes the first pipe fitting, is set at the middle part of first inside pipe fitting
There is the first dividing plate, and the cavity in first pipe fitting is divided into the first buffering by first pipe fitting by first dividing plate
Room, the second surge chamber；The first buffering hydraulic cylinder is provided with first surge chamber；The cylinder body of first buffering hydraulic cylinder with
The supporting plate is hinged；First dividing plate of the telescopic shaft top pressure of first buffering hydraulic cylinder inside first surge chamber
On；
It is provided with the second buffering hydraulic cylinder, and the first dividing plate in second surge chamber and also sets in second surge chamber
There is first pressure sensor, the cylinder body top pressure of second buffering hydraulic cylinder is on the first pressure sensor, described second
The end of the telescopic shaft of buffering hydraulic cylinder is hinged with the support shaft, and the normality of the telescopic shaft of second buffering hydraulic cylinder is
Stretching state.
2. the buffer structure of airplane wheel as claimed in claim 1, it is characterised in that：First buffering hydraulic cylinder it is flexible
The normality of axle is stretching state.
3. the buffer structure of airplane wheel as claimed in claim 2, it is characterised in that：In stretching for first buffering hydraulic cylinder
The first buffer spring is also cased with contracting axle, the lower end of first buffer spring is withstood on first dividing plate.
4. the buffer structure of airplane wheel as claimed in claim 1, it is characterised in that：Second buffer gear includes second
Pipe fitting, is provided with second partition in the middle part of second inside pipe fitting, and second pipe fitting will by the second partition
Cavity in second pipe fitting is divided into the 3rd surge chamber, the 4th surge chamber；Provided with the 3rd buffering in the 3rd surge chamber
Hydraulic cylinder；The cylinder body of 3rd buffering hydraulic cylinder is hinged with the supporting plate；The telescopic shaft top of 3rd buffering hydraulic cylinder
It is pressed on the second partition inside the 3rd surge chamber；
It is provided with the 4th buffering hydraulic cylinder, and second partition in the 4th surge chamber and also sets in the 4th surge chamber
There is second pressure sensor, the cylinder body top pressure of the 4th buffering hydraulic cylinder is in second pressure sensing；Described 4th delays
The normality of the telescopic shaft of fliud flushing cylinder pressure is stretching state, and end and the support of the telescopic shaft of the 4th buffering hydraulic cylinder
Axle is hinged.
5. the buffer structure of airplane wheel as claimed in claim 4, it is characterised in that：3rd buffering hydraulic cylinder it is flexible
Axle normality is stretching state.
6. the buffer structure of airplane wheel as claimed in claim 5, it is characterised in that：In stretching for the 3rd buffering hydraulic cylinder
The second buffer spring is also cased with contracting axle, the lower end of second buffer spring is withstood on the second partition.
7. the buffer structure of airplane wheel as claimed in claim 6, it is characterised in that：Also include controller, first pressure
Force snesor, second pressure sensor are connected with the controller, in addition to be connected with the controller the first magnetic valve,
Second magnetic valve, the 3rd magnetic valve, the 4th magnetic valve, first buffering hydraulic cylinder, the second buffering hydraulic cylinder, the 3rd buffer solution
Cylinder pressure, the 4th buffering hydraulic cylinder pass through the first magnetic valve, the second magnetic valve, the 3rd magnetic valve, the 4th magnetic valve and oil pump respectively
Connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610330392.7A CN105775111B (en) | 2016-05-13 | 2016-05-13 | The buffer structure of airplane wheel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610330392.7A CN105775111B (en) | 2016-05-13 | 2016-05-13 | The buffer structure of airplane wheel |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105775111A CN105775111A (en) | 2016-07-20 |
| CN105775111B true CN105775111B (en) | 2017-11-07 |
Family
ID=56379057
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610330392.7A Expired - Fee Related CN105775111B (en) | 2016-05-13 | 2016-05-13 | The buffer structure of airplane wheel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105775111B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108860607A (en) * | 2018-06-19 | 2018-11-23 | 智飞智能装备科技东台有限公司 | It is a kind of from steady wind resistance unmanned plane |
| CN109502015B (en) * | 2018-12-23 | 2021-11-16 | 江苏润翔软件技术有限公司 | Undercarriage damping structure for near space solar unmanned aerial vehicle |
| GB2611099A (en) | 2021-09-28 | 2023-03-29 | Airbus Operations Ltd | Landing gear stay |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE328744C (en) * | 1918-04-16 | 1920-11-04 | Eisenfuehr & Co G M B H | Aircraft chassis suspension |
| US3510093A (en) * | 1965-10-19 | 1970-05-05 | John Michael Frankovich | Landing gear for airplanes |
| CN202360664U (en) * | 2011-11-03 | 2012-08-01 | 浙江庆源车业部件有限公司 | Oil pressure damping buffer |
| CN202783777U (en) * | 2012-08-24 | 2013-03-13 | 董韬 | Unmanned aerial vehicle undercarriage |
| CN204822065U (en) * | 2015-07-28 | 2015-12-02 | 河南大诚通用航空科技有限公司 | Unmanned aerial vehicle's undercarriage |
-
2016
- 2016-05-13 CN CN201610330392.7A patent/CN105775111B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN105775111A (en) | 2016-07-20 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190709 Address after: 211151 Ganquanhu Community, Hengxi Street, Jiangning District, Nanjing City, Jiangsu Province Patentee after: NANJING RUYI AVIATION MACHINERY EQUIPMENT CO.,LTD. Address before: 214153 Wuxi Business Vocational and Technical College, No. 809 Qianhu Highway, Huishan District, Wuxi City, Jiangsu Province Patentee before: Wuxi Institute of Commerce |
|
| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171107 |
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| CF01 | Termination of patent right due to non-payment of annual fee |