CN106704467A - Impact buffering device - Google Patents
Impact buffering device Download PDFInfo
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- CN106704467A CN106704467A CN201510787129.6A CN201510787129A CN106704467A CN 106704467 A CN106704467 A CN 106704467A CN 201510787129 A CN201510787129 A CN 201510787129A CN 106704467 A CN106704467 A CN 106704467A
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- inner barrel
- spring
- outer cylinder
- cylinder body
- damping
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Abstract
The invention discloses an impact buffering device. The impact buffering device comprises an inner barrel, an outer barrel, a floating piston, a damping body, a spring and a one-way valve, the upper end of the outer barrel is closed, the lower end of the outer barrel is opened, the upper end of the inner barrel is opened, and the lower end of the inner barrel is closed. The floating piston and the spring are arranged in the inner barrel; one end of the spring is connected with the floating piston, and the other end of the spring is connected with the inner surface of the bottom of the inner barrel; the spring is externally wrapped by an elastic rubber column, and the diameter of the elastic rubber column is smaller than the inner diameter of the inner barrel; the damping body is arranged on the top of the inner barrel, and the damping body is provided with a damping hole; and the inner barrel is arranged in the outer barrel in a sliding manner. An oil pressure space is formed by space between the top end of the inner barrel and the top end of the outer barrel. A pressure slowing space is formed by space between the floating piston in the inner barrel and the damping body. According to the impact buffering device, the elastic rubber column wrapping the spring is arranged, so that the spring is prevented from being excessively compressed, and the reliability of the impact buffering device is further improved.
Description
Technical field
The present invention relates to aircraft field, more particularly to a kind of buffer unit for aircraft landing gear.
Background technology
Undercarriage is the special arrangement for taking off landing.During aircraft landing, always with certain speed impacts ground, undercarriage bears and slows down this shock, so as to mitigate the stand under load of aircraft.The critical component that undercarriage slows down this bump stroke is exactly buffer unit.If buffer unit design is unreasonable, will cause that aircraft bears bigger load, cause airplane design weight to improve.If buffer unit breaks down, aircraft hard landing will be caused, airframe structure is destroyed, or even fatal crass occurs.
Existing buffer unit uses air-fuel mixture formula structure, and it is the disadvantage is that, air cavity is susceptible to leakage.Once air cavity is leaked, the buffering effect of buffer unit will significantly weaken, and buffer unit cannot return.Weaker buffering effect will be in aircraft landing, and undercarriage disappears with ground first time collision rift.
The content of the invention
It is to overcome the deficiencies in the prior art that the purpose of the present invention is, there is provided a kind of relief means.
The purpose of the present invention is achieved through the following technical solutions：
Relief means, including inner barrel, outer cylinder body, floating piston, damping body and spring；Outer cylinder body upper end closed, outer cylinder body lower end opens, and inner barrel upper end opens, inner barrel lower end closed；Floating piston and spring are arranged in inner barrel, and one end of spring is connected with floating piston, and the other end of spring is connected with the bottom interior surface of inner barrel；Spring outer wrapping elastic rubber column, the internal diameter of the diameter less than inner barrel of elastic rubber column；Damping body is arranged at the top of inner barrel, and damping hole is offered on damping body；Inner barrel is slideably positioned in outer cylinder body, and the space between inner barrel top and outer cylinder body top constitutes oil pressure space；Space in inner barrel between floating piston and damping body constitutes slow pressure space；Also include the check valve being arranged on damping body, check valve is outwards turned on by inner barrel.
Fluid is full of in oil pressure space, when being extruded by external force, inner barrel does compression motion relative to outer cylinder body, fluid can now produce damping so as to absorb partial capability during aircraft landing by the damping hole on damping body.After fluid enters slow pressure space, floating piston compression spring, further absorbability are promoted.After external force disappearance, spring promotes floating piston, floating piston that the fluid in slow pressure space is pushed back into oil pressure space, and the fluid in oil pressure space promotes inner barrel, inner barrel is done stretching exercise relative to outer cylinder body, so realizes the return of buffer unit.
Check valve is set so that the fluid in slow pressure space can faster be pushed back oil pressure space, realize returning quickly.
The present invention substitutes the air in inner barrel using spring, it is to avoid air leakage cause the buffering effect of buffer unit will significantly weaken and buffer unit cannot return problem.
Spring is easily damaged in excess compression, and the elastic rubber column of parcel spring is set for this, prevents spring to be overly compressed, and further improves reliability of the invention.
Further, the periphery of the elastic rubber column offers spiral type groove.
Spiral type groove is set, makes elastic rubber column be easier to be compressed, it is to avoid elastic rubber column is impacted to shock-absorbing capacity of the invention.
Further, the cross section of the spiral type groove is triangle.
The cross section of spiral type groove is triangle, further makes elastic rubber column be easier to be compressed.
Further, it is provided with seal support part between the outer cylinder body bottom interior surface and the inner cylinder external surface.
Seal support part is set, it is to avoid the oil liquid leakage in outer cylinder body.
Further, the seal support part is connected by bearing pin with the outer cylinder body.
Further, the damping hole is opened in the center of the damping body.
Further, the top of the bottom of the inner barrel and the outer cylinder body is provided with connector.
Connector is used to for the present invention to be fixed on undercarriage.
In sum, the advantages of the present invention are：
1. the present invention substitutes the air in inner barrel using spring, it is to avoid air leakage cause the buffering effect of damper will significantly weaken and damper cannot return problem；
2. the elastic rubber column of parcel spring is set, prevents spring to be overly compressed, further improve reliability of the invention；
3. spiral type groove is set, makes elastic rubber column be easier to be compressed, it is to avoid elastic rubber column is impacted to shock-absorbing capacity of the invention；
4. the cross section of spiral type groove is triangle, further makes elastic rubber column be easier to be compressed；
5. seal support part is set, it is to avoid the oil liquid leakage in outer cylinder body；
6. check valve is set so that the fluid in slow pressure space can faster be pushed back oil pressure space, realize returning quickly.
Brief description of the drawings
In order to illustrate more clearly of embodiments of the invention, the accompanying drawing to be used needed for the description embodiment of the present invention will be briefly described below.It will be apparent that drawings in the following description are only some embodiments described in the present invention, for a person skilled in the art, without creative efforts, other accompanying drawings can also be obtained according to following accompanying drawing.
Fig. 1 is structural representation of the invention；
The wherein corresponding parts title of reference is as follows：
1- inner barrels, 2- outer cylinder bodies, 3- floating pistons, 4- damping bodies, 5- springs, 6- damping holes, 7- oil pressure space, the slow pressure spaces of 8-, 9- seal support parts, 10- bearing pins, 11- connectors, 12- elastic rubber columns, 13- spiral grooves, 14- check valves.
Specific embodiment
In order that those skilled in the art more fully understands the present invention, clear, complete description is carried out to the technical scheme in the embodiment of the present invention below in conjunction with the accompanying drawing in the embodiment of the present invention.It will be apparent that embodiment described below is only the part in the embodiment of the present invention, rather than whole.Based on the embodiment that the present invention is recorded, other all embodiments that those skilled in the art obtain without creative efforts, in the scope of protection of the invention.
Embodiment 1：
As shown in figure 1, relief means, including inner barrel 1, outer cylinder body 2, floating piston 3, damping body 4 and spring 5；The upper end closed of outer cylinder body 2, the lower end of outer cylinder body 2 opens, and the upper end of inner barrel 1 opens, the lower end closed of inner barrel 1；Floating piston 3 and spring 5 are arranged in inner barrel 1, and one end of spring 5 is connected with floating piston 3, and the other end of spring 5 is connected with the bottom interior surface of inner barrel 1；The outer wrapping elastic rubber column 12 of spring 5, the internal diameter of the diameter less than inner barrel 1 of elastic rubber column 12；Damping body 4 is arranged at the top of inner barrel 1, and damping hole 6 is offered on damping body 4；Inner barrel 1 is slideably positioned in outer cylinder body 2, and the space between the top of inner barrel 1 and the top of outer cylinder body 2 constitutes oil pressure space 7；Space in inner barrel 1 between floating piston 3 and damping body 4 constitutes slow pressure space 8；Also include the check valve 14 being arranged on damping body 4, check valve 14 is outwards turned on by inner barrel 1.
Fluid is full of in oil pressure space 7, when being extruded by external force, inner barrel 1 does compression motion relative to outer cylinder body 2, fluid can now produce damping so as to absorb partial capability during aircraft landing by the damping hole 6 on damping body 4.After fluid enters slow pressure space 8, the compression spring 5 of floating piston 3, further absorbability are promoted.After external force disappearance, spring 5 promotes floating piston 3, floating piston 3 that the fluid in slow pressure space 8 is pushed back into oil pressure space 7, and the fluid in oil pressure space 7 promotes inner barrel 1, inner barrel 1 is done stretching exercise relative to outer cylinder body 2, so realize the return of buffer unit.
Check valve 14 is set so that the fluid in slow pressure space 8 can faster be pushed back oil pressure space 7, realize returning quickly.
The present invention substitutes the air in inner barrel 1 using spring 5, it is to avoid air leakage cause the buffering effect of buffer unit will significantly weaken and buffer unit cannot return problem.
Spring 5 is easily damaged in excess compression, and the elastic rubber column 12 of parcel spring 5 is set for this, prevents spring 5 to be overly compressed, and further improves reliability of the invention.
Embodiment 2：
As shown in figure 1, the present embodiment is on the basis of embodiment 1, the periphery of the elastic rubber column 12 offers spiral type groove 13.
Spiral type groove 13 is set, makes elastic rubber column 12 be easier to be compressed, it is to avoid elastic rubber column 12 is impacted to shock-absorbing capacity of the invention.
Embodiment 3：
As shown in figure 1, the present embodiment is on the basis of embodiment 2, the cross section of the spiral type groove 13 is triangle.
The cross section of spiral type groove 13 is triangle, further makes elastic rubber column 12 be easier to be compressed.
Embodiment 4：
As shown in figure 1, the present embodiment is on the basis of above-mentioned any one embodiment, seal support part 9 is provided between the bottom interior surface of the outer cylinder body 2 and the outer surface of the inner barrel 1.
Seal support part 9 is set, it is to avoid the oil liquid leakage in outer cylinder body 2.
Embodiment 5：
As shown in figure 1, the present embodiment is on the basis of embodiment 4, the seal support part 9 is connected by bearing pin 10 with the outer cylinder body 2.
Embodiment 6：
As shown in figure 1, the present embodiment is on the basis of above-mentioned any one embodiment, the damping hole 6 is opened in the center of the damping body 4.
Embodiment 7：
As shown in figure 1, the present embodiment is on the basis of above-mentioned any one embodiment, the top of the bottom of the inner barrel 1 and the outer cylinder body 2 is provided with connector 11.
Connector 11 is used to for the present invention to be fixed on undercarriage.
Claims (7)
1. relief means, it is characterised in that：
Including inner barrel（1）, outer cylinder body（2）, floating piston（3）, damping body（4）And spring（5）；
Outer cylinder body（2）Upper end closed, outer cylinder body（2）Lower end opens, inner barrel（1）Upper end opens, inner barrel（1）Lower end closed；
Floating piston（3）And spring（5）It is arranged at inner barrel（1）It is interior, spring（5）One end and floating piston（3）Connection, spring（5）The other end and inner barrel（1）Bottom interior surface connection；
Spring（5）Outer wrapping elastic rubber column（12）, elastic rubber column（12）Diameter be less than inner barrel（1）Internal diameter；
Damping body（4）It is arranged at inner barrel（1）Top, damping body（4）On offer damping hole（6）；
Inner barrel（1）It is slideably positioned in outer cylinder body（2）In, inner barrel（1）Top and outer cylinder body（2）Space between top constitutes oil pressure space（7）；
Inner barrel（1）Interior floating piston（3）With damping body（4）Between space constitute slow pressure space（8）；
Also include being arranged at damping body（4）On check valve（14）, check valve（14）By inner barrel（1）Outwards conducting.
2. relief means according to claim 1, it is characterised in that：
The elastic rubber column（12）Periphery offer spiral type groove（13）.
3. relief means according to claim 2, it is characterised in that：
The spiral type groove（13）Cross section be triangle.
4. relief means according to claim 1, it is characterised in that：
The outer cylinder body（2）Bottom interior surface and the inner barrel（1）Seal support part is provided between outer surface（9）.
5. relief means according to claim 4, it is characterised in that：
The seal support part（9）By bearing pin（10）With the outer cylinder body（2）Connection.
6. relief means according to claim 1, it is characterised in that：
The damping hole（6）It is opened in the damping body（4）Center.
7. relief means according to any one in claim 1 ~ 6, it is characterised in that：
The inner barrel（1）Bottom and the outer cylinder body（2）Top be provided with connector（11）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510787129.6A CN106704467A (en) | 2015-11-16 | 2015-11-16 | Impact buffering device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510787129.6A CN106704467A (en) | 2015-11-16 | 2015-11-16 | Impact buffering device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106704467A true CN106704467A (en) | 2017-05-24 |
Family
ID=58930637
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510787129.6A Pending CN106704467A (en) | 2015-11-16 | 2015-11-16 | Impact buffering device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106704467A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110901922A (en) * | 2019-12-06 | 2020-03-24 | 湖南浩天翼航空技术有限公司 | Plant protection unmanned aerial vehicle of multiplicable heavy burden |
-
2015
- 2015-11-16 CN CN201510787129.6A patent/CN106704467A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110901922A (en) * | 2019-12-06 | 2020-03-24 | 湖南浩天翼航空技术有限公司 | Plant protection unmanned aerial vehicle of multiplicable heavy burden |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170524 |
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| WD01 | Invention patent application deemed withdrawn after publication |