CN215293408U - Wear-resisting sealing device of aircraft buffer - Google Patents
Wear-resisting sealing device of aircraft buffer Download PDFInfo
- Publication number
- CN215293408U CN215293408U CN202120842535.9U CN202120842535U CN215293408U CN 215293408 U CN215293408 U CN 215293408U CN 202120842535 U CN202120842535 U CN 202120842535U CN 215293408 U CN215293408 U CN 215293408U
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- Prior art keywords
- buffer
- outer cylinder
- piston rod
- piston
- ring
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Abstract
The utility model belongs to wear-resisting structural design technique, concretely relates to wear-resisting sealing device of aircraft buffer. The sealing device includes: the buffer device comprises a buffer outer cylinder (1), a piston rod (2) and a piston ring (3), wherein the piston rod (2) is arranged in the buffer outer cylinder (1) and can move relative to the buffer outer cylinder (1), and the piston ring (3) is arranged between the buffer outer cylinder (1) and the piston rod (2). The utility model discloses an add the piston ring between buffer urceolus and piston rod, can effectively protect the safety of buffer structure spare, promote the life of buffer structure spare.
Description
Technical Field
The utility model belongs to wear-resisting structural design technique, concretely relates to wear-resisting sealing device of aircraft buffer.
Background
The bumper is one of the most important parts in the landing gear of the airplane, and mainly has the functions of absorbing impact energy during landing and taxiing, reducing the load applied to the airplane body to an acceptable degree, quickly attenuating vibration and improving the cabin vibration noise environment by using the bumper. The currently used buffer is generally composed of a metal sleeve and a piston rod, and the following problems can be caused in the use process:
1) relative sliding friction exists between the sleeve and the piston rod, and the sleeve and the piston rod are damaged;
2) the long-term contact between the sleeve and the piston rod can cause gap deviation and influence the design;
3) metal chips can be generated during friction between the sleeve and the piston rod, and the metal chips fall into hydraulic oil to pollute the hydraulic oil.
SUMMERY OF THE UTILITY MODEL
Utility model purpose: the wear-resistant sealing device for the airplane buffer is provided to solve the problem of relative sliding friction between a sleeve of the airplane buffer and a piston rod.
The technical scheme is as follows:
in a first method aspect, there is provided an aircraft bumper abradable seal, comprising: the damper comprises a damper outer cylinder 1, a piston rod 2 and a piston ring 3, wherein the piston rod 2 is arranged in the damper outer cylinder 1 and can move relative to the damper outer cylinder 1, and the piston ring 3 is arranged between the damper outer cylinder 1 and the piston rod 2.
Further, a first annular groove is provided on the outer wall of the piston rod 2 near the piston head, and the piston ring 3 is disposed in the first annular groove.
Further, the piston ring 3 is a band-shaped ring structure.
Further, the buffer device further comprises a retaining ring 4, a second annular groove is formed in the inner wall, close to the end, of the buffer outer cylinder 1, and the retaining ring 4 is arranged in the second annular groove.
Further, the cross section of the retainer ring is T-shaped, wherein a rod portion of the retainer ring is disposed in the second annular groove.
Furthermore, the piston ring 3 is a phenolic cotton cloth laminated tube formed by resin dipping cotton cloth and hot pressing and curing of a layering.
Further, the retainer ring 4 is a modified polytetrafluoroethylene retainer ring.
Has the advantages that:
the utility model discloses an expansion ring, contour machining is convenient, long service life. The laminated tube used for the piston ring has high compression strength, high hardness, friction resistance and excellent oil resistance, can effectively reduce the relative friction between the outer cylinder and the piston rod of the buffer when applied to the structure of the aircraft buffer, protects the metal materials of the outer cylinder and the piston rod, can effectively protect the safety of the structural member of the buffer, and prolongs the service life of the structural member of the buffer.
Drawings
Fig. 1 is a schematic structural view of a piston ring according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of an aircraft bumper wear seal according to an embodiment of the present invention.
Wherein, bumper urceolus 1, piston rod 2, piston ring 3, retaining ring 4.
Detailed Description
First, as shown in fig. 1, the piston ring for the aircraft bumper can be a phenolic cotton cloth laminated tube, has high compression strength, high hardness, friction resistance, excellent oil resistance and the like, and can effectively reduce the relative friction between the outer cylinder and the piston rod of the bumper after being applied to the aircraft bumper, and protect the metal materials of the outer cylinder and the piston rod and the hydraulic oil used in the bumper.
As shown in fig. 2, the wear-resistant sealing device for the aircraft buffer of the present invention comprises a buffer outer cylinder 1, a piston rod 2 and a piston ring 3, wherein the piston rod 2 is disposed in the buffer outer cylinder 1 and can move relative to the buffer outer cylinder 1, and the piston ring 3 is disposed between the buffer outer cylinder 1 and the piston rod 2. By adding the piston ring 3, the device has high compression strength, high hardness, friction resistance and excellent oil resistance. An annular groove is arranged on the outer wall of the piston rod 2 close to the piston head, and the piston ring 3 is arranged in the annular groove. The piston ring 3 is in a belt-shaped annular structure.
Further, a retaining ring 4 can be further included, an annular groove is arranged on the inner wall of the buffer outer cylinder 1 close to the end, and the retaining ring 4 is arranged in the annular groove. The cross section of the retainer ring can be T-shaped. The retainer ring 4 is a modified polytetrafluoroethylene retainer ring.
The phenolic cotton cloth laminated tube is formed by resin-impregnated reinforced material (cotton cloth) and hot-pressed and solidified by layering. The compressive strength in the direction parallel to the cloth layer is not lower than 210MPa, and the compressive strength in the direction perpendicular to the cloth layer is not lower than 330 MPa. The hardness of the phenolic cotton cloth laminated pipe is not lower than 420MPa in Brinell hardness. The coefficient of friction in the steady state is not more than 0.3. The piston ring is soaked in 10# or 15# hydraulic oil for a long time, and the compression strength of the piston ring is kept above 90%.
Claims (7)
1. An aircraft bumper wear seal, comprising: the buffer device comprises a buffer outer cylinder (1), a piston rod (2) and a piston ring (3), wherein the piston rod (2) is arranged in the buffer outer cylinder (1) and can move relative to the buffer outer cylinder (1), and the piston ring (3) is arranged between the buffer outer cylinder (1) and the piston rod (2).
2. A device according to claim 1, characterised in that the piston rod (2) is provided with a first annular groove in its outer wall close to the piston head, in which first annular groove the piston ring (3) is arranged.
3. Device according to claim 2, characterized in that the piston ring (3) is of a belt-shaped ring-like construction.
4. A device according to claim 3, characterized by a collar (4), a second annular groove being provided on the inner wall of the damper outer cylinder (1) near the end, said collar (4) being provided in said second annular groove.
5. The apparatus of claim 4, wherein the retainer ring is T-shaped in cross-section with a stem portion of the retainer ring disposed in the second annular groove.
6. The device according to claim 1, characterized in that the piston ring (3) is a phenolic cotton cloth laminated tube formed by resin impregnation of cotton cloth and hot pressing and curing of the laid layers.
7. Device according to claim 1, characterized in that the collar (4) is a modified polytetrafluoroethylene collar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120842535.9U CN215293408U (en) | 2021-04-22 | 2021-04-22 | Wear-resisting sealing device of aircraft buffer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120842535.9U CN215293408U (en) | 2021-04-22 | 2021-04-22 | Wear-resisting sealing device of aircraft buffer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215293408U true CN215293408U (en) | 2021-12-24 |
Family
ID=79537705
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120842535.9U Active CN215293408U (en) | 2021-04-22 | 2021-04-22 | Wear-resisting sealing device of aircraft buffer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215293408U (en) |
-
2021
- 2021-04-22 CN CN202120842535.9U patent/CN215293408U/en active Active
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