CN103738502B - A kind of Aircraft Air oil-receiving device ground check interconnecting device - Google Patents
A kind of Aircraft Air oil-receiving device ground check interconnecting device Download PDFInfo
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- CN103738502B CN103738502B CN201310627100.2A CN201310627100A CN103738502B CN 103738502 B CN103738502 B CN 103738502B CN 201310627100 A CN201310627100 A CN 201310627100A CN 103738502 B CN103738502 B CN 103738502B
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- oily
- aircraft
- unlocking mechanism
- receiving device
- air oil
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- 230000006835 compression Effects 0.000 claims description 5
- 238000007906 compression Methods 0.000 claims description 5
- 239000003921 oil Substances 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 210000005056 cell body Anatomy 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 239000010729 system oil Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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Abstract
The invention belongs to aviation field, relate to a kind of Aircraft Air oil-receiving device ground check interconnecting device.Described flight refuelled system ground check interconnecting device mainly comprises aircraft pressure filling by joint (1), by oily unlocking mechanism (2), handwheel (3), compress cam mechanism (4), switching fixed body (5), described switching fixed body (5) one end is enclosed within Aircraft Air oil-receiving device, and be fixed by compressing cam mechanism (4), the other end is socketed with by oily unlocking mechanism (2), should dock with aircraft bowser by joint (1) through aircraft pressure filling by the other end of oily unlocking mechanism (2), handwheel (3) is socketed in by oily unlocking mechanism (2), and by be enclosed within by the guide ring (7) of oily unlocking mechanism cylindrical shell and circular nut (9) spacing, for advancing and locking by oily unlocking mechanism (2).The switching that the present invention can realize Aircraft Air oil-receiving device and aircraft bowser is refueled, and has the advantages such as simple structure, handled easily, connection are reliable, good airproof performance.
Description
Technical field
The invention belongs to aviation field, relate to a kind of Aircraft Air oil-receiving device ground check interconnecting device.
Background technology
The improvement type of aircraft is equipped with flight refuelled system, and ensure maintenance needs according to outfield, aircraft needs when ground is parked regularly to carry out the inspection of oil circuit patency to flight refuelled system.In order to complete the inspection of flight refuelled system oil circuit patency, need aircraft bowser to be connected with flight refuelled system, and open flight refuelled system by oily plug.But the fueling connection of aircraft bowser is specifically designed to wing lower fuel tank oil filling port and refuels, and can not directly be connected with flight refuelled system, need newly to grind transition apparatus complete transfer and open flight refuelled system be subject to oily plug.
Summary of the invention
The object of the invention is: in order to solve the problem of Aircraft Air oil-receiving device ground check, the invention provides one and can connect aircraft bowser and Aircraft Air oil-receiving device, realizing the interconnecting device of Aircraft Air oil-receiving device ground check.
Technical scheme of the present invention is: in order to solve the problems of the technologies described above, the technical scheme provided is as follows: a kind of Aircraft Air oil-receiving device ground check interconnecting device, it comprises aircraft pressure filling by joint 1, by oily unlocking mechanism 2, handwheel 3, compression cam mechanism 4, switching fixed body 5, described switching fixed body 5 one end is enclosed within Aircraft Air oil-receiving device, and be fixed by compressing cam mechanism 4, the other end is socketed with by oily unlocking mechanism 2, should dock by the other end of oily unlocking mechanism 2 through aircraft pressure filling by joint 1 with aircraft bowser.Handwheel 3 is socketed in by oily unlocking mechanism 2, and by be enclosed within by the guide ring 7 of oily unlocking mechanism cylindrical shell and circular nut 9 spacing, for advancing by oily unlocking mechanism 2 and lock.
Wherein, described switching fixed body 5 has four " L " type guide groove restriction handwheels 3 can only do straight-line motion and spin locking along " L " type guide groove on the housing of switching fixed body.
Described by oily unlocking mechanism 2 comprise cylindrical shell 6, guide ring 7, lid 8, circular nut 9, seal ring 10, cone end holding screw 11.Described guide ring 7, lid 8 are all socketed on cylindrical shell 6 outer wall, and circular nut 9 is screwed onto on 6 outer walls, and seal ring 10 is embedded on the scalene cone of cylindrical shell 6 inner chamber, and cone end holding screw 11 radial direction is screwed onto on circular nut 9.
Described compression cam mechanism 4 comprises self-control bolt 12, fly nut 13, cam 14.Thick one end, described self-control bolt 12 one end is thin, and all there is outside thread at two ends.Cam 14 top tilts, and flat segments top, middle part has slotted hole, and bottom has elongated slot, and bottom has the through hole wearing bolt.After self-control bolt 12 taper end is spirally connected through the slotted hole on cam 14 top and fly nut 13, then weld.Described cam lower lobes curve is formed by three sections of circular arcs are tangent.
Beneficial effect of the present invention is: the switching that the present invention can realize Aircraft Air oil-receiving device and aircraft bowser is refueled, there is the advantages such as simple structure, handled easily, connection are reliable, good airproof performance, and can be applied in other have on the aircraft of flight refuelled system, general, practicality good.
Accompanying drawing explanation
Fig. 1 is axonometric drawing of the present invention;
Fig. 2 is the present invention and Aircraft Air oil-receiving device docking scheme;
Fig. 3 be the present invention be subject to oily unlocking mechanism partly cut open figure;
Fig. 4 is the cutaway view that the present invention compresses cam mechanism;
Wherein, the pressure filling of 1-aircraft is by oil head, and 2-is by oily unlocking mechanism, 3-handwheel, 4-compresses cam mechanism, and 5-transfers fixed body, and 6-cylindrical shell, 7-guide ring, 8-lid, 9-circular nut, 10-seal ring, 11-cone end holding screw, 12-make bolt, 13-fly nut, 14-cam by oneself.
Detailed description of the invention
Below by detailed description of the invention, the invention will be further described:
Please refer to Fig. 1,2,3,4, Aircraft Air oil-receiving device ground check interconnecting device of the present invention comprises aircraft pressure filling by joint 1, by oily unlocking mechanism 2, handwheel 3, compression cam mechanism 4, switching fixed body 5.Described switching fixed body 5 one end is enclosed within Aircraft Air oil-receiving device, and is fixed by compressing cam mechanism 4, and the other end is socketed with by oily unlocking mechanism 2, should dock by the other end of oily unlocking mechanism 2 through aircraft pressure filling by joint 1 with aircraft bowser.Handwheel 3 is socketed in by oily unlocking mechanism 2, and by be enclosed within by the guide ring 7 of oily unlocking mechanism cylindrical shell and circular nut 9 spacing, for advancing by oily unlocking mechanism 2 and lock.
Described switching fixed body 5 has four " L " type guide groove restriction handwheels 3 can only do straight-line motion and spin locking along " L " type guide groove on the housing of switching fixed body, the length of switching fixed body 5 " L " type guide groove vertical section is Aircraft Air oil-receiving device and entirely opens stroke 32mm by oily plug, when can ensure to be pulled to the end by oily unlocking mechanism 2, Aircraft Air oil-receiving device is in full open position by oily plug.
Described by oily unlocking mechanism 2 comprise cylindrical shell 6, guide ring 7, lid 8, circular nut 9, seal ring 10, cone end holding screw 11.Described guide ring 7, lid 8 are all socketed on cylindrical shell 6 outer wall, and circular nut 9 is screwed onto on 6 outer walls, and seal ring 10 is embedded on the scalene cone of cylindrical shell 6 inner chamber, and cone end holding screw 11 is radially screwed onto on circular nut 9 and prevents circular nut 9 from getting loose.When handwheel 3 does straight-line motion along switching fixed body 5 " L " type guide groove, drive and do straight-line motion by oily unlocking mechanism 2, simultaneously, cylindrical shell 6 inner chamber scalene cone by oily unlocking mechanism 2 embedded seal ring 10 push flight refuelled system make it open by oily plug, namely realize unblanking by oil, seal ring 10 effectively can prevent from refueling when checking and occur revealing.
Described compression cam mechanism 4 comprises self-control bolt 12, fly nut 13, cam 14.Thick one end, described self-control bolt 12 one end is thin, and all there is outside thread at two ends.Cam 14 top tilts, convenient operation, and flat segments top, middle part has slotted hole, and bottom has elongated slot, and bottom has the through hole wearing bolt, and fillet curve is formed by three sections of circular arcs are tangent, thus can not interfere with flight refuelled system cell body when ensureing lower motion.Self-control bolt 12 taper end is welded after being spirally connected with fly nut 13 through the slotted hole on cam 14 top again, self-control bolt 12 welds rear composition wing bolt and is embedded in cam 14 slotted hole with fly nut 13, wing bolt can be screwed into the tapped blind hole internal fixtion cam 14 of switching fixed body 5.Cam 14 is connected with switching fixed body 5 by bolt assembly, and after connecting, cam 14 freely can rotate around bolt, when fixed body 5 of transferring is enclosed within Aircraft Air oil-receiving device, pulls lower cam 14, namely realizes being fixed.
During use, control step is as follows:
A) be enclosed within Aircraft Air oil-receiving device by switching fixed body 5, symmetry is pulled after lower cam 14 is fixed, and twists fly nut 13 and enters in the tapped blind hole of switching fixed body 5 to self-control bolt 12;
B) holding handwheel 3 promotes by oily 2 to the end of unlocking mechanism along switching fixed body 5 " L " type guide groove straight line portion, and when after the opening completely by oily plug of Aircraft Air oil-receiving device, left-hand revolution handwheel 3, namely completes and unblank and lock-bit by oil;
C) aircraft bowser is connect mouth by oil to dock with aircraft pressure oiling joint 1;
D) aircraft bowser starts to refuel the oil circuit patency checking Aircraft Air oil-receiving device.
In sum, the switching that the present invention can realize Aircraft Air oil-receiving device and aircraft bowser is refueled, there is the advantages such as simple structure, handled easily, connection are reliable, good airproof performance, and can be applied on other aircraft with Aircraft Air oil-receiving device, general, practicality good.
Claims (5)
1. an Aircraft Air oil-receiving device ground check interconnecting device, it is characterized in that: comprise aircraft pressure filling by joint (1), by oily unlocking mechanism (2), handwheel (3), compress cam mechanism (4), switching fixed body (5), described switching fixed body (5) one end is enclosed within Aircraft Air oil-receiving device, and be fixed by compressing cam mechanism (4), the other end is socketed with by oily unlocking mechanism (2), should dock with aircraft bowser by joint (1) through aircraft pressure filling by the other end of oily unlocking mechanism (2), handwheel (3) is socketed in by oily unlocking mechanism (2), and by be enclosed within by the guide ring (7) of oily unlocking mechanism cylindrical shell and circular nut (9) spacing, for advancing and locking by oily unlocking mechanism (2).
2. Aircraft Air oil-receiving device ground check interconnecting device according to claim 1, is characterized in that: switching fixed body (5) has four " L " type guide grooves restriction handwheel (3) can only do straight-line motion and spin locking along " L " type guide groove on the housing of switching fixed body.
3. Aircraft Air oil-receiving device ground check interconnecting device according to claim 1, it is characterized in that: the described oily unlocking mechanism (2) that is subject to comprises cylindrical shell (6), guide ring (7), lid (8), circular nut (9), seal ring (10), cone end holding screw (11), described guide ring (7), lid (8) is all socketed on cylindrical shell (6) outer wall, circular nut (9) is screwed onto on cylindrical shell (6) outer wall, seal ring (10) is embedded on the scalene cone of cylindrical shell (6) inner chamber, cone end holding screw (11) radial direction is screwed onto on circular nut (9).
4. Aircraft Air oil-receiving device ground check interconnecting device according to claim 1, it is characterized in that: described compression cam mechanism (4) comprises self-control bolt (12), fly nut (13), cam (14), described self-control bolt (12) one end is thick, one end is thin, and all there is outside thread at two ends; Cam (14) top tilts, and flat segments top, middle part has slotted hole, and bottom has elongated slot, and bottom has the through hole wearing bolt; After self-control bolt (12) taper end is spirally connected through the slotted hole on cam (14) top and fly nut (13), then weld.
5. Aircraft Air oil-receiving device ground check interconnecting device according to claim 4, is characterized in that: described cam lower lobes curve is formed by three sections of circular arcs are tangent.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310627100.2A CN103738502B (en) | 2013-11-27 | 2013-11-27 | A kind of Aircraft Air oil-receiving device ground check interconnecting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310627100.2A CN103738502B (en) | 2013-11-27 | 2013-11-27 | A kind of Aircraft Air oil-receiving device ground check interconnecting device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103738502A CN103738502A (en) | 2014-04-23 |
| CN103738502B true CN103738502B (en) | 2016-02-24 |
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|---|---|---|---|
| CN201310627100.2A Active CN103738502B (en) | 2013-11-27 | 2013-11-27 | A kind of Aircraft Air oil-receiving device ground check interconnecting device |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104085536A (en) * | 2014-06-17 | 2014-10-08 | 江西洪都航空工业集团有限责任公司 | Manual oiling switch |
| CN105000191B (en) * | 2015-08-14 | 2017-11-21 | 中国航空工业集团公司西安飞机设计研究所 | A kind of connectivity structure and there is its aircraft fuel tank and aircraft |
| CN108545215B (en) * | 2018-05-18 | 2023-10-03 | 沈阳飞研航空设备有限公司 | Butt joint detection equipment for aerial oil receiving probe |
| CN109734039B (en) * | 2019-01-09 | 2020-10-30 | 中冶华天工程技术有限公司 | Automatic oil filling device that catches of sintering platform truck wheel |
| CN112602677A (en) * | 2020-12-29 | 2021-04-06 | 哈尔滨工程北米科技有限公司 | Underwater suction head with detection function |
| CN113859557B (en) * | 2021-09-24 | 2023-07-21 | 成都飞机工业（集团）有限责任公司 | Residual oil discharge assisting device for aerial oil receiving pipe of airplane and application method of residual oil discharge assisting device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3059895A (en) * | 1957-05-31 | 1962-10-23 | Parker Hannifin Corp | Probe terminal assembly for in-flight re-fueling |
| US6234224B1 (en) * | 2000-03-14 | 2001-05-22 | Robert L. Schultz, Jr. | Aircraft fueling nozzle |
| WO2010084316A2 (en) * | 2009-01-21 | 2010-07-29 | Flight Refuelling Limited | A nozzle for a refuelling probe |
| CN102190086A (en) * | 2010-01-28 | 2011-09-21 | 尤洛考普特公司 | Device for filling box through gravity or under pressure |
| CN102582839A (en) * | 2011-01-05 | 2012-07-18 | 通用电气航空系统有限责任公司 | Method and system for a refueling drogue assembly |
-
2013
- 2013-11-27 CN CN201310627100.2A patent/CN103738502B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3059895A (en) * | 1957-05-31 | 1962-10-23 | Parker Hannifin Corp | Probe terminal assembly for in-flight re-fueling |
| US6234224B1 (en) * | 2000-03-14 | 2001-05-22 | Robert L. Schultz, Jr. | Aircraft fueling nozzle |
| WO2010084316A2 (en) * | 2009-01-21 | 2010-07-29 | Flight Refuelling Limited | A nozzle for a refuelling probe |
| CN102190086A (en) * | 2010-01-28 | 2011-09-21 | 尤洛考普特公司 | Device for filling box through gravity or under pressure |
| CN102582839A (en) * | 2011-01-05 | 2012-07-18 | 通用电气航空系统有限责任公司 | Method and system for a refueling drogue assembly |
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| Publication number | Publication date |
|---|---|
| CN103738502A (en) | 2014-04-23 |
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