CN209506130U - Aircraft airborne hydraulic oil pump protective cover sealing experimental facility - Google Patents
Aircraft airborne hydraulic oil pump protective cover sealing experimental facility Download PDFInfo
- Publication number
- CN209506130U CN209506130U CN201822241832.9U CN201822241832U CN209506130U CN 209506130 U CN209506130 U CN 209506130U CN 201822241832 U CN201822241832 U CN 201822241832U CN 209506130 U CN209506130 U CN 209506130U
- Authority
- CN
- China
- Prior art keywords
- protective cover
- hydraulic oil
- oil pump
- flange
- compression ring
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000001681 protective effect Effects 0.000 title claims abstract description 52
- 239000010720 hydraulic oil Substances 0.000 title claims abstract description 18
- 238000007789 sealing Methods 0.000 title claims abstract description 18
- 230000006835 compression Effects 0.000 claims abstract description 26
- 238000007906 compression Methods 0.000 claims abstract description 26
- 238000002474 experimental method Methods 0.000 description 6
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 239000004411 aluminium Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- NMFHJNAPXOMSRX-PUPDPRJKSA-N [(1r)-3-(3,4-dimethoxyphenyl)-1-[3-(2-morpholin-4-ylethoxy)phenyl]propyl] (2s)-1-[(2s)-2-(3,4,5-trimethoxyphenyl)butanoyl]piperidine-2-carboxylate Chemical compound C([C@@H](OC(=O)[C@@H]1CCCCN1C(=O)[C@@H](CC)C=1C=C(OC)C(OC)=C(OC)C=1)C=1C=C(OCCN2CCOCC2)C=CC=1)CC1=CC=C(OC)C(OC)=C1 NMFHJNAPXOMSRX-PUPDPRJKSA-N 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Landscapes
- Gasket Seals (AREA)
Abstract
The utility model discloses a kind of aircraft airborne hydraulic oil pump protective cover sealing experimental facilities; including compression ring, cover board and inlet suction port; the compression ring be sheathed on the flange on protective cover and with protective cover against; the cover board be set to protective cover open end and with the flange of protective cover against; multiple groups fastening assembly is equipped between the compression ring and cover board; circumferentially along the flange, the inlet suction port is installed on the cover board fastening assembly described in multiple groups.The utility model has many advantages, such as that structure is simple, reliable, easy to use.
Description
Technical field
The utility model relates to aircraft airborne equipment more particularly to a kind of aircraft airborne hydraulic oil pump protective cover sealing experiments
Device.
Background technique
Airborne hydraulic Oil pump electrical machinery protective cover is as shown in attached drawing one, and generally tubular is open at one end, closed at one end, opening
Periphery flanged pin is held, it is needed since tensile elongation is big by repeatedly stretching repeatedly by aviation aluminium sheet aluminium L4M drawing and forming
Molding.Therefore it can inevitably be mingled with substandard products, especially end face seal face in product, be easy corrugation, requirement is not achieved.Furthermore
Since use environment is severe, need to bear corresponding larger value of oil liquid pressure, aviation components are usually that small lot is raw in addition
It produces, requirement high reliablity, before the installation of each part, needs to do various tests to corresponding part.Hydraulic oil pump motor
Protective cover need to carry out the leakproofness experiment for being more than or equal to 3 times using pressure, due to its specific shape, need to design a set of experiment
Sealing device is sealed experiment.
Utility model content
The technical problems to be solved in the utility model be overcome the deficiencies of the prior art and provide a kind of structure it is simple, it is reliable,
Aircraft airborne hydraulic oil pump protective cover sealing experimental facility easy to use.
In order to solve the above technical problems, the utility model uses following technical scheme:
A kind of aircraft airborne hydraulic oil pump protective cover sealing experimental facility, including compression ring, cover board and inlet suction port,
The compression ring be sheathed on the flange on protective cover and with protective cover against, the cover board be set to protective cover open end and with guarantor
The flange of shield is against being equipped with multiple groups fastening assembly, fastening assembly described in multiple groups is along described convex between the compression ring and cover board
Circumferentially, the inlet suction port is installed on the cover board edge.
As a further improvement of the above technical scheme: the convex extended into protective cover is equipped in the middle part of the cover board
Portion.
As a further improvement of the above technical scheme: the compression ring is equipped with flexible pad close to the side of the flange
Ring.
As a further improvement of the above technical scheme: the flexibility gasket ring is rubber pad ring.
Compared with the prior art, the advantages of the utility model are: aircraft airborne hydraulic oil pump disclosed by the utility model
Protective cover sealing experimental facility is arranged compression ring using the open end of cover plate for sealing protective cover on protective cover, and compression ring utilizes
The included flange in protective cover open end as positioning, cover board connect with compression ring by multiple groups fastening assembly it is integral, thus reality
Existing fixation of the cover board on protective cover, more evenly, easy damaged, inlet suction port are not set on cover board stress flange, Ke Yitong everywhere
It crosses inlet suction port and is passed through gas in protective cover, and then the leakproofness of protective cover is tested, after the completion of experiment, first unscrew tight
Gu component removes cover board, then compression ring is removed from protective cover, overall structure is simple, reliable, easy to use.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of aircraft airborne hydraulic oil pump protective cover.
Fig. 2 is the structural schematic diagram of the utility model aircraft airborne hydraulic oil pump protective cover sealing experimental facility.
Each label indicates in figure: 1, protective cover；11, flange；2, compression ring；3, cover board；31, positioning convex portion；4, fastening group
Part；5, inlet suction port；6, flexible gasket ring.
Specific embodiment
The utility model is described in further detail below in conjunction with Figure of description and specific embodiment.
Fig. 2 shows a kind of embodiments of the utility model aircraft airborne hydraulic oil pump protective cover sealing experimental facility, originally
The aircraft airborne hydraulic oil pump protective cover sealing experimental facility of embodiment, including compression ring 2, cover board 3 and intake and exhaust connector 5,
Compression ring 2 be sheathed on protective cover 1 and with the flange of protective cover 1 11 against, cover board 3 be set to protective cover 1 open end and with guarantor
The flange 11 of shield 1 is against equipped with multiple groups fastening assembly 4 between compression ring 2 and cover board 3, multiple groups fastening assembly 4 is along flange 11
Circumferentially, intake and exhaust connector 5 is installed on cover board 3.
The aircraft airborne hydraulic oil pump protective cover sealing experimental facility, the open end using 3 sealing protective 1 of cover board are (attached
It is lower end in figure), compression ring 2 is arranged on protective cover 1, the flange 11 that compression ring 2 is carried using 1 open end of protective cover is as fixed
Position, cover board 3 and compression ring 2 pass through multiple groups fastening assembly 4 (such as can be matched fillister head screw, locking nut and gasket)
It connects integral, to realize fixation of the cover board 3 on protective cover 1, biggish air pressure can be born, stress is more equal everywhere for flange 11
Even, easy damaged, inlet suction port 5 are not set on cover board 3, gas can be passed through in protective cover 1 by inlet suction port 5, and then right
The leakproofness of protective cover 1 is tested, and after the completion of experiment, first unscrews fastening assembly 4, cover board 3 is removed, then by compression ring 2 from
It is removed on protective cover 1, overall structure is simple, reliable, easy to use.
Further, in this embodiment being equipped with the positioning convex portion 31 extended into protective cover 1 in the middle part of cover board 3, it is convenient for cover board
3 positioning is assembled.
Further, in this embodiment compression ring 2 is equipped with flexible pad close to the side (being downside in attached drawing 2) of flange 11
Ring 6.Due to having knuckle between flange 11 and protective cover 1, by the way that flexible gasket ring 6 is arranged, compression ring 2 is on the one hand avoided
It is directly contacted with 11 upper surface of flange, on the other hand flexible gasket ring 6 can be preferably bonded with knuckle, compression ring 2, cover board
3 stability on protective cover 1 is more preferable.
As a preferred technical solution, in the present embodiment, flexible gasket ring 6 uses rubber pad ring.
Although the utility model has been disclosed with preferred embodiment as above, it is not intended to limit the utility model.It is any
Those skilled in the art, in the case where not departing from technical solutions of the utility model range, all using the disclosure above
Technology contents many possible changes and modifications are made to technical solutions of the utility model, or be revised as the equivalent of equivalent variations
Embodiment.Therefore, all contents without departing from technical solutions of the utility model, according to the utility model technical spirit to the above reality
Any simple modifications, equivalents, and modifications that example is done are applied, should all be fallen in the range of technical solutions of the utility model protection.
Claims (4)
1. a kind of aircraft airborne hydraulic oil pump protective cover sealing experimental facility, it is characterised in that: including compression ring (2), cover board
(3) and inlet suction port (5), the compression ring (2) are sheathed on protective cover (1) and support with the flange (11) of protective cover (1)
It leans on, the cover board (3) is set to the open end of protective cover (1) and with the flange (11) of protective cover (1) against the compression ring (2)
Be equipped with multiple groups fastening assembly (4) between cover board (3), fastening assembly (4) described in multiple groups along the flange (11) circumferentially,
The inlet suction port (5) is installed on the cover board (3).
2. aircraft airborne hydraulic oil pump protective cover sealing experimental facility according to claim 1, it is characterised in that: the lid
The positioning convex portion (31) extended into protective cover (1) is equipped in the middle part of plate (3).
3. aircraft airborne hydraulic oil pump protective cover sealing experimental facility according to claim 1 or 2, it is characterised in that: institute
It states compression ring (2) and is equipped with flexible gasket ring (6) close to the side of the flange (11).
4. aircraft airborne hydraulic oil pump protective cover sealing experimental facility according to claim 3, it is characterised in that: described soft
Property gasket ring (6) be rubber pad ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822241832.9U CN209506130U (en) | 2018-12-28 | 2018-12-28 | Aircraft airborne hydraulic oil pump protective cover sealing experimental facility |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822241832.9U CN209506130U (en) | 2018-12-28 | 2018-12-28 | Aircraft airborne hydraulic oil pump protective cover sealing experimental facility |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209506130U true CN209506130U (en) | 2019-10-18 |
Family
ID=68198293
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822241832.9U Active CN209506130U (en) | 2018-12-28 | 2018-12-28 | Aircraft airborne hydraulic oil pump protective cover sealing experimental facility |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209506130U (en) |
-
2018
- 2018-12-28 CN CN201822241832.9U patent/CN209506130U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |