CN210218993U - Ground service joint of airplane hydraulic system - Google Patents
Ground service joint of airplane hydraulic system Download PDFInfo
- Publication number
- CN210218993U CN210218993U CN201920766997.XU CN201920766997U CN210218993U CN 210218993 U CN210218993 U CN 210218993U CN 201920766997 U CN201920766997 U CN 201920766997U CN 210218993 U CN210218993 U CN 210218993U
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- telescopic sleeve
- connecting core
- hydraulic system
- outer side
- ground service
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Abstract
A ground service joint of an aircraft hydraulic system comprises a connecting core, a mandril, a threaded sleeve and a telescopic sleeve, wherein one end of the outer side of the mandril is connected with the inner side of the connecting core through threads, and the other end of the outer side of the mandril is in transition fit with the telescopic sleeve; a spring is arranged between the tail of the telescopic sleeve and the inner hole wall of the connecting core and is sleeved on the ejector rod; an oil outlet is formed in the side wall of one end of the ejector rod and is surrounded by the telescopic sleeve in a surrounding mode; one end of the threaded sleeve is in transition fit with the connecting core, and an internal thread is arranged on the inner wall of the through hole at the other end of the threaded sleeve. Compared with the prior art, the utility model discloses an aircraft hydraulic system ground service connects, simple structure, connection core and swivel nut adopt screw thread and outside pipeline high-speed joint, and connected mode is convenient, and the spare part of whole joint makes conveniently moreover, has practiced thrift the cost of enterprise greatly.
Description
Technical Field
The utility model relates to an aircraft accessory field specifically indicates an aircraft hydraulic system ground service connects.
Background
The hydraulic ground service connector is a quick-release connector for refueling the airplane, is generally purchased from an external manufacturer, has a complex structure and is inconvenient to operate, and particularly, the connector imported from abroad cannot be matched with domestic refueling equipment in the actual use process due to the difference in technical standards; moreover, the price of the purchased connectors is not good, and the connectors are a heavy burden for some airplane maintenance enterprises.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to above-mentioned prior art not enough, and provide an aircraft hydraulic system ground service joint.
In order to solve the technical problem, the utility model discloses a technical scheme is:
a ground service joint of an aircraft hydraulic system comprises a connecting core, a mandril, a threaded sleeve and a telescopic sleeve, wherein one end of the outer side of the mandril is connected with the inner side of the connecting core through threads, and the other end of the outer side of the mandril is in transition fit with the telescopic sleeve; a spring is arranged between the tail of the telescopic sleeve and the inner hole wall of the connecting core and is sleeved on the ejector rod; an oil outlet is formed in the side wall of one end of the ejector rod and is surrounded by the telescopic sleeve in a surrounding mode; one end of the threaded sleeve is in transition fit with the connecting core, and an internal thread is arranged on the inner wall of the through hole at the other end of the threaded sleeve.
Furthermore, the end face of the ejector rod at the oil outlet side is of a closed structure, and an inclined boss is integrally processed on the outer side of the end face of the ejector rod; a circle of conical groove is processed on the inner hole wall of one end of the telescopic sleeve; the telescopic sleeve is clamped with the inclined boss on the end face of the ejector rod through the tapered groove.
Furthermore, an extension block is integrally processed on the outer side of the telescopic sleeve.
Furthermore, an installation thread is machined on the outer side of one end of the connecting core.
Furthermore, annular grooves are formed in the inner walls of the connecting core and the threaded sleeve, and sealing rings are connected in the annular grooves.
Compared with the prior art, the utility model discloses an aircraft hydraulic system ground service connects, simple structure, connection core and swivel nut adopt screw thread and outside pipeline high-speed joint, and connected mode is convenient, and the spare part of whole joint makes conveniently moreover, has practiced thrift the cost of enterprise greatly.
Drawings
Fig. 1 is a schematic structural diagram of the present invention;
the oil-out device comprises a connecting core 1, a connecting core 2, an ejector rod 3, a threaded sleeve 4, a telescopic sleeve 5, a spring 6, a sealing ring 11, an upper shoulder 12, a lower shoulder 13, a mounting thread 21, an oil outlet 41 and an extension block.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.
As shown in fig. 1, the ground service joint of the aircraft hydraulic system comprises a connecting core 1, a mandril 2, a thread insert 3 and a telescopic sleeve 4, wherein an external thread of M30 is processed at one end of the outer side of the mandril 2, an internal thread of M30 is processed in an inner hole of the connecting core 1, an upper shoulder 11 and a lower shoulder 12 are integrally processed on the inner wall of the connecting core 1 at two sides of the internal thread, the mandril 2 is installed with the connecting core 1 through the thread of the outer side M30, and after the installation is in place, the end part of the mandril 2 is limited through the upper shoulder 11.
The other end of the ejector rod 2 is of a closed structure, and the telescopic sleeve 4 is connected to the outer side of the ejector rod 2 in a sliding manner; an inclined boss is integrally processed on the outer side of the closed end of the ejector rod 2, a circle of conical groove is processed on the inner hole wall at one end of the telescopic sleeve 4, and when the telescopic sleeve 4 slides to the closed end of the ejector rod 2, the telescopic sleeve is clamped and limited with the inclined boss on the end face of the ejector rod through the conical groove; a spring 5 is arranged between the tail part of the telescopic sleeve 4 and a lower convex shoulder 12 of the connecting core 1, and the spring 5 is sleeved on the ejector rod 2; an oil outlet 21 is formed in the side wall of one end of the ejector rod 2, and the oil outlet 21 is surrounded by the telescopic sleeve 4 in a non-working state to prevent oil leakage; one end of the screw sleeve 3 is in transition fit with the connecting core 1, and an M60 internal thread connected with an external pipeline is processed on the inner wall of the through hole at the other end.
In this embodiment, the oil outlet 21 is arranged at an angle of 60 degrees with the horizontal axis, and with such arrangement, on one hand, the oil outlet speed is increased, and on the other hand, after the oil filling is completed, the service joint is generally stored in a hanging manner, and the oil outlet 21 at an oblique angle facilitates oil return.
In this embodiment, an extension block 41 is integrally formed on the outer side of the telescopic sleeve 4, and the extension block 41 is used for jacking the telescopic sleeve 4 open when the service joint is connected with an external oil pipe; an M36 mounting thread 13 is machined on the outer side of one end of the connecting core, and the mounting thread 13 is used for being connected with an oil inlet pipeline; annular grooves are formed in the inner walls of the connecting core 1 and the threaded sleeve 3, and a sealing ring 6 is connected in each annular groove.
The present invention is not limited to the above-described embodiments, and those skilled in the art can make modifications or changes without departing from the spirit of the present invention.
Claims (5)
1. The utility model provides an aircraft hydraulic system ground service connects which characterized in that: the connecting rod comprises a connecting core, a push rod, a threaded sleeve and a telescopic sleeve, wherein one end of the outer side of the push rod is connected with the inner side of the connecting core through threads, and the other end of the outer side of the push rod is in transition fit with the telescopic sleeve; a spring is arranged between the tail of the telescopic sleeve and the inner hole wall of the connecting core and is sleeved on the ejector rod; an oil outlet is formed in the side wall of one end of the ejector rod and is surrounded by the telescopic sleeve in a surrounding mode; one end of the threaded sleeve is in transition fit with the connecting core, and an internal thread is arranged on the inner wall of the through hole at the other end of the threaded sleeve.
2. An aircraft hydraulic system ground service coupling as claimed in claim 1, wherein: the end face of the ejector rod on the oil outlet side is of a closed structure, and an inclined boss is integrally processed on the outer side of the end face of the ejector rod; a circle of conical groove is processed on the inner hole wall of one end of the telescopic sleeve; the telescopic sleeve is clamped with the inclined boss on the end face of the ejector rod through the tapered groove.
3. An aircraft hydraulic system ground service coupling as claimed in claim 1, wherein: an extension block is integrally processed on the outer side of the telescopic sleeve.
4. An aircraft hydraulic system ground service coupling as claimed in claim 1, wherein: and a mounting thread is processed on the outer side of one end of the connecting core.
5. An aircraft hydraulic system ground service coupling as claimed in claim 1, wherein: annular grooves are processed on the inner walls of the connecting core and the threaded sleeve, and sealing rings are connected in the annular grooves.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920766997.XU CN210218993U (en) | 2019-05-27 | 2019-05-27 | Ground service joint of airplane hydraulic system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920766997.XU CN210218993U (en) | 2019-05-27 | 2019-05-27 | Ground service joint of airplane hydraulic system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210218993U true CN210218993U (en) | 2020-03-31 |
Family
ID=69927755
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920766997.XU Active CN210218993U (en) | 2019-05-27 | 2019-05-27 | Ground service joint of airplane hydraulic system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210218993U (en) |
-
2019
- 2019-05-27 CN CN201920766997.XU patent/CN210218993U/en active Active
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