CN106697270A - Air vehicle bi-directional damping method - Google Patents
Air vehicle bi-directional damping method Download PDFInfo
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- CN106697270A CN106697270A CN201510787126.2A CN201510787126A CN106697270A CN 106697270 A CN106697270 A CN 106697270A CN 201510787126 A CN201510787126 A CN 201510787126A CN 106697270 A CN106697270 A CN 106697270A
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- inner barrel
- damping
- cylinder body
- outer cylinder
- floating piston
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Abstract
The invention discloses an air vehicle bi-directional damping method. According to the air vehicle bi-directional damping method, two dampers acts at the same time; for each damper, an oil hydraulic space is filled with oil liquid, under external extrusion force, an internal cylinder body performs compression movement in relative to an external cylinder body, and the oil liquid passes through a damping hole on a damping body; when the oil liquid enters into a slow pressing space, a floating piston is pushed to press a spring; when external force disappears, the floating piston is pushed by the spring, and the oil liquid in the slow pressing space is pushed into the oil hydraulic space via a one-way valve and the damping hole, the oil liquid in the oil hydraulic space is used for pushing the internal cylinder body to perform stretching movement in relative to the external cylinder body. Equipment of the air vehicle bi-directional damping method is composed of two connected dampers, relatively long stroke is provided, and excellent damping effect is achieved.
Description
Technical field
The present invention relates to aircraft field, more particularly to a kind of shock-dampening method 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 damper.If shock absorber design is unreasonable, will cause that aircraft bears bigger load, cause airplane design weight to improve.If damper breaks down, aircraft hard landing will be caused, airframe structure is destroyed, or even fatal crass occurs.
Existing damper 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 damper will significantly weaken, and damper 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 aircraft bidirectional damping method.
The purpose of the present invention is achieved through the following technical solutions：
Aircraft bidirectional damping method, using equipment as described below：The equipment includes two dampers of interconnection, and damper includes 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；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, and also including the check valve being arranged on damping body, check valve is outwards turned on by inner barrel；Two outer cylinder body blind ends of damper are connected with each other；
Specific method is as follows：
Two dampers are acted simultaneously, and fluid is full of in oil pressure space, and when being extruded by external force, inner barrel does compression motion relative to outer cylinder body, and fluid can now produce damping so as to absorb portion of energy during aircraft landing by the damping hole on damping body；
After fluid enters slow pressure space, floating piston compression spring, further energy absorption 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 by check valve and damping hole, and the fluid in oil pressure space promotes inner barrel, inner barrel is done stretching exercise relative to outer cylinder body, so realize the return of damper.
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 damper will significantly weaken and damper cannot return problem.
Equipment of the invention is interconnected to constitute using two dampers, there is provided stroke more long, so as to possess more preferable damping effect.
Further, sealed using 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 bottom of the inner barrel 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. equipment of the invention is interconnected to constitute using two dampers, there is provided stroke more long, so as to possess more preferable damping effect；
3. seal support part is set, it is to avoid the oil liquid leakage in outer cylinder body；
4. 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 the structural representation of damper in the present 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- 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, aircraft bidirectional damping method, using equipment as described below：The equipment includes two dampers of interconnection, and damper includes 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；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, and also including the check valve 12 being arranged on damping body 4, check valve 12 is outwards turned on by inner barrel 1；Two blind ends of the outer cylinder body of damper 2 are connected with each other.
Specific method is：
Two dampers are acted simultaneously, and fluid is full of in oil pressure space 7, and when being extruded by external force, inner barrel 1 does compression motion relative to outer cylinder body 2, and fluid is by the damping hole 6 on damping body 4；
After fluid enters slow pressure space 8, the compression spring 5 of floating piston 3 is 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 by check valve 12 and damping hole 6, 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.
The present invention substitutes the air in inner barrel 1 using spring 5, it is to avoid air leakage cause the buffering effect of damper will significantly weaken and damper cannot return problem.
Check valve 12 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 is interconnected to constitute using two dampers, there is provided stroke more long, so as to possess more preferable damping effect.
Embodiment 2：
As shown in figure 1, the present embodiment is on the basis of embodiment 1, sealed using seal support part 9 between the bottom interior surface of the outer cylinder body 2 and the outer surface of the inner barrel 1
Seal support part 8 is set, it is to avoid the oil liquid leakage in outer cylinder body 2.
Embodiment 3：
As shown in figure 1, the present embodiment is on the basis of embodiment 2, the seal support part 9 is connected by bearing pin 10 with the outer cylinder body 2.
Embodiment 4：
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 4：
As shown in figure 1, the present embodiment is on the basis of above-mentioned any one embodiment, the bottom of the inner barrel 1 is provided with connector 11.
Connector 11 is used to for the present invention to be fixed on undercarriage.
Claims (6)
1. aircraft bidirectional damping method, it is characterised in that：
Using equipment as described below：
The equipment includes two dampers of interconnection, and damper includes 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；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 including being arranged at damping body（4）On check valve（12）, check valve（12）By inner barrel（1）Outwards conducting；Two outer cylinder bodies of damper（2）Blind end is connected with each other.
2. specific method is：
Two dampers are acted simultaneously, oil pressure space（7）In be full of fluid, when being extruded by external force, inner barrel（1）Relative to outer cylinder body（2）Compression motion is done, fluid passes through damping body（4）On damping hole（6）；
Fluid enters slow pressure space（8）Afterwards, floating piston is promoted（3）Compression spring（5）；
After external force disappearance, spring（5）Promote floating piston（3）, floating piston（3）By slow pressure space（8）In fluid pass through check valve（12）And damping hole（6）Push back oil pressure space（7）, oil pressure space（7）In fluid promote inner barrel（1）, make inner barrel（1）Relative to outer cylinder body（2）Do stretching exercise.
3. aircraft bidirectional damping method 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 used between outer surface（9）Sealed.
4. aircraft bidirectional damping method according to claim 2, it is characterised in that：
The seal support part（9）By bearing pin（10）With the outer cylinder body（2）Connection.
5. aircraft bidirectional damping method according to claim 1, it is characterised in that：
The damping hole（6）It is opened in the damping body（4）Center.
6. the aircraft bidirectional damping method according to any one in claim 1 ~ 4, it is characterised in that：
The inner barrel（1）Bottom be provided with connector（11）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510787126.2A CN106697270A (en) | 2015-11-16 | 2015-11-16 | Air vehicle bi-directional damping method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510787126.2A CN106697270A (en) | 2015-11-16 | 2015-11-16 | Air vehicle bi-directional damping method |
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| Publication Number | Publication Date |
|---|---|
| CN106697270A true CN106697270A (en) | 2017-05-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510787126.2A Pending CN106697270A (en) | 2015-11-16 | 2015-11-16 | Air vehicle bi-directional damping method |
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| CN (1) | CN106697270A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109700518B (en) * | 2019-01-29 | 2021-11-09 | 南方医科大学南方医院 | Intramedullary bone extension auxiliary device |
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- 2015-11-16 CN CN201510787126.2A patent/CN106697270A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109700518B (en) * | 2019-01-29 | 2021-11-09 | 南方医科大学南方医院 | Intramedullary bone extension auxiliary device |
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| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170524 |