CN105015793A - Aircraft refueling system and aircraft comprising same - Google Patents
Aircraft refueling system and aircraft comprising same Download PDFInfo
- Publication number
- CN105015793A CN105015793A CN201510501505.0A CN201510501505A CN105015793A CN 105015793 A CN105015793 A CN 105015793A CN 201510501505 A CN201510501505 A CN 201510501505A CN 105015793 A CN105015793 A CN 105015793A
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- China
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- aircraft
- shutoff valve
- fuel tank
- pipeline
- refuelling system
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Abstract
The invention discloses an aircraft refueling system and an aircraft comprising the same. The aircraft refueling system comprises a refueling connector (1) and an oil tank assembly (3) connected with the refueling connector (1) through a pipeline (2), and further comprises a stop valve (4) arranged in the pipeline (2) between the refueling connector (1) and the oil tank assembly (3), and the stop valve (4) is electrically connected with a refueling control panel and controlled by the refueling control panel. The stop valve (4) is used for switching on or off the pipeline (2). In the aircraft refueling system, the stop valve is arranged in the pipeline between the refueling connector and the oil tank assembly, electrically connected with the refueling control panel, controlled by the refueling control panel and used for switching on or off the pipeline. Control is achieved through the stop valve, the problem that the number of components of the aircraft refueling system is large is solved, and compared with the prior art, control is easy, and the weight is small.
Description
Technical field
The present invention relates to technical field of aerospace, particularly relate to a kind of aircraft refuelling system and there is its aircraft.
Background technology
In prior art, aircraft refuelling system has more specific of components and parts, thus brings trouble point many, controls complicated, the shortcomings such as weight is large.
Therefore, wish a kind of technical scheme to overcome or at least alleviate at least one above-mentioned defect of prior art.
Summary of the invention
The object of the present invention is to provide a kind of aircraft refuelling system to overcome or at least alleviate at least one above-mentioned defect of prior art.
For achieving the above object, the invention provides a kind of aircraft refuelling system.The fuel tank assembly that described aircraft refuelling system is comprised fueling connection and is connected by pipeline with described fueling connection, described aircraft refuelling system comprises further: shutoff valve, described shutoff valve is arranged in the pipeline between described fueling connection and described fuel tank assembly, and described shutoff valve and refueling control panel Electricity Federation, control by described refueling control panel; Described shutoff valve is used for pipeline described in break-make.
Preferably, described shutoff valve is electromagnetic shut-off valve.
Preferably, described shutoff valve is electronic shutoff valve.
Preferably, described shutoff valve is ball valve.
Preferably, described fuel tank assembly comprises multiple fuel tank with partition, described pipeline comprises many branch lines, every bar branch line stretches to a described fuel tank, every bar branch line is provided with a check valve, described check valve is configured such that oil from described fueling connection to each described fuel tank direction flowing.
Preferably, described in every bar, the end of branch line is provided with diffusing opening, for limiting the flow velocity of the oil through described diffusing opening.
Present invention also offers a kind of aircraft, described aircraft comprises aircraft refuelling system as above.
In aircraft refuelling system in the present invention, shutoff valve is arranged in the pipeline between fueling connection and fuel tank assembly, and shutoff valve and refueling control panel Electricity Federation, control by refueling control panel; Shutoff valve is used for break-make pipeline.The present invention is controlled by shutoff valve, decreases the problem that aircraft refuelling system components and parts are more, and relative to prior art, it controls simple, and weight is relatively little.
Accompanying drawing explanation
Fig. 1 is the structural representation of aircraft refuelling system according to an embodiment of the invention.
Reference numeral:
| 1 | Fueling connection | 31 | Fuel tank |
| 2 | Pipeline | 21 | Branch line |
| 3 | Fuel tank assembly | 22 | Check valve |
| 4 | Shutoff valve | 23 | Diffusing opening |
Detailed description of the invention
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention.
Aircraft refuelling system of the present invention comprises fueling connection, fuel tank assembly and shutoff valve, wherein, fueling connection is connected by pipeline with fuel tank assembly, and shutoff valve is arranged in the pipeline between fueling connection and fuel tank assembly, and shutoff valve and refueling control panel Electricity Federation, control by refueling control panel; Shutoff valve is used for pipeline described in break-make.
In aircraft refuelling system in the present invention, shutoff valve is arranged in the pipeline between fueling connection and fuel tank assembly, and shutoff valve and refueling control panel Electricity Federation, control by refueling control panel; Shutoff valve is used for break-make pipeline.The present invention is controlled by shutoff valve, decreases the problem that aircraft refuelling system components and parts are more, and relative to prior art, it controls simple, and weight is relatively little.
Fig. 1 is the structural representation of aircraft refuelling system according to an embodiment of the invention.
Aircraft refuelling system as shown in Figure 1 comprises fueling connection 1, pipeline 2, fuel tank assembly 3, shutoff valve 4.Wherein, fueling connection 1 connects fuel tank assembly 3 by pipeline 2, and shutoff valve 4 is arranged in the pipeline 2 between fueling connection 1 and fuel tank assembly 3, and shutoff valve 4 and refueling control panel (not shown) Electricity Federation, control by refueling control panel; Shutoff valve 4 is for break-make pipeline 2.Namely operator controls the unlatching of shutoff valve with closed by control panel.
In the present embodiment, shutoff valve 4 is electromagnetic shut-off valve.Namely in the present embodiment, electromagnetic control is passed through.
Be understandable that, shutoff valve can also select other modes, namely can also select the shutoff valve of other kinds.Such as, in an alternative embodiment, shutoff valve is electronic shutoff valve, now, adopts Electronic control mode to control.
Advantageously, in the present embodiment, shutoff valve 4 is ball valve.Be understandable that, shutoff valve can also adopt the valve of other configurations.Such as, needle-valve etc.
Fuel tank assembly 3 comprises multiple fuel tank 31 with partition, pipeline 2 comprises many branch lines 21, every bar branch line 21 stretches to a fuel tank 31, in the present embodiment, except last fuel tank (in Fig. 1 offside tank), every bar branch line 21 is provided with a check valve 22, check valve 22 is configured such that oil flows to each fuel tank direction from fueling connection.
Be understandable that, in another alternative, last fuel tank (i.e. the last fuel tank flowed into of oil) is provided with check valve.
It should be noted that, in this application, pipeline 2 refers to the pipeline of each fuel tank 31 connected in fueling connection 1 and fuel tank assembly 3, and the pipeline not only comprised between fuel tank assembly 3 and shutoff valve 4.
In the present embodiment, the quantity of fuel tank 31 is 4.Be understandable that, the quantity of fuel tank 31 can set as required.Such as, the quantity of fuel tank be 1,2, three or more.
Advantageously, in the present embodiment, the end of every bar branch line 21 is provided with diffusing opening 23, for limiting the flow velocity of the oil through diffusing opening 23.Like this, can ensure that oil enters fuel tank according to the flow velocity preset, thus prevent the oil in fuel tank from producing shock wave.
Present invention also offers a kind of aircraft, described aircraft comprises aircraft refuelling system as above.
Finally it is to be noted: above embodiment only in order to technical scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (7)
1. an aircraft refuelling system, the fuel tank assembly (3) that described aircraft refuelling system is comprised fueling connection (1) and is connected by pipeline (2) with described fueling connection (1), it is characterized in that, described aircraft refuelling system comprises further:
Shutoff valve (4), described shutoff valve (4) is arranged in the pipeline (2) between described fueling connection (1) and described fuel tank assembly (3), and described shutoff valve (4) and refueling control panel Electricity Federation, control by described refueling control panel; Described shutoff valve (4) is for pipeline described in break-make (2).
2. aircraft refuelling system as claimed in claim 1, it is characterized in that, described shutoff valve (4) is electromagnetic shut-off valve.
3. aircraft refuelling system as claimed in claim 1, it is characterized in that, described shutoff valve (4) is electronic shutoff valve.
4. as the aircraft refuelling system in claims 1 to 3 as described in any one, it is characterized in that, described shutoff valve (4) is ball valve.
5. aircraft refuelling system as claimed in claim 1, it is characterized in that, described fuel tank assembly (3) comprises multiple fuel tank (31) with partition, described pipeline (2) comprises many branch lines (21), every bar branch line (21) stretches to a described fuel tank (31), every bar branch line (21) is provided with a check valve (22), described check valve (22) is configured such that oil from described fueling connection (1) to each described fuel tank direction flowing.
6. aircraft refuelling system as claimed in claim 5, it is characterized in that, described in every bar, the end of branch line (21) is provided with diffusing opening (23), for the flow velocity of restriction through the oil of described diffusing opening (23).
7. an aircraft, is characterized in that, described aircraft comprises as the aircraft refuelling system in claim 1 to 6 as described in any one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510501505.0A CN105015793A (en) | 2015-08-14 | 2015-08-14 | Aircraft refueling system and aircraft comprising same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510501505.0A CN105015793A (en) | 2015-08-14 | 2015-08-14 | Aircraft refueling system and aircraft comprising same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105015793A true CN105015793A (en) | 2015-11-04 |
Family
ID=54406185
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510501505.0A Pending CN105015793A (en) | 2015-08-14 | 2015-08-14 | Aircraft refueling system and aircraft comprising same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105015793A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292511A (en) * | 2015-11-26 | 2016-02-03 | 中国航空工业集团公司西安飞机设计研究所 | Refueling manifold system and aircraft pressure refueling assembly with same and aircraft |
| CN111907641A (en) * | 2020-02-25 | 2020-11-10 | 青岛海洋地质研究所 | Method and device for controlling oil tank of multi-hull ship and multi-hull ship |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110042520A1 (en) * | 2008-02-07 | 2011-02-24 | Airbus Operations Gmbh | Aircraft Tank System, Refueling Unit And Method For Refueling An Aircraft |
| CN202624642U (en) * | 2011-12-14 | 2012-12-26 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Airplane pressure refueling header pipe integrating device |
| CN103038133A (en) * | 2010-07-29 | 2013-04-10 | 空中客车运营有限公司 | A refuel control system and method of refuelling |
| CN103043222A (en) * | 2011-10-11 | 2013-04-17 | 通用电气公司 | System for wireless refueling of an aircraft |
| CN103630338A (en) * | 2012-08-28 | 2014-03-12 | 哈尔滨飞机工业集团有限责任公司 | Ground test structure of pressure refueling system |
-
2015
- 2015-08-14 CN CN201510501505.0A patent/CN105015793A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110042520A1 (en) * | 2008-02-07 | 2011-02-24 | Airbus Operations Gmbh | Aircraft Tank System, Refueling Unit And Method For Refueling An Aircraft |
| CN103038133A (en) * | 2010-07-29 | 2013-04-10 | 空中客车运营有限公司 | A refuel control system and method of refuelling |
| CN103043222A (en) * | 2011-10-11 | 2013-04-17 | 通用电气公司 | System for wireless refueling of an aircraft |
| CN202624642U (en) * | 2011-12-14 | 2012-12-26 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Airplane pressure refueling header pipe integrating device |
| CN103630338A (en) * | 2012-08-28 | 2014-03-12 | 哈尔滨飞机工业集团有限责任公司 | Ground test structure of pressure refueling system |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292511A (en) * | 2015-11-26 | 2016-02-03 | 中国航空工业集团公司西安飞机设计研究所 | Refueling manifold system and aircraft pressure refueling assembly with same and aircraft |
| CN105292511B (en) * | 2015-11-26 | 2017-06-16 | 中国航空工业集团公司西安飞机设计研究所 | A kind of oiling manifold system and the aircraft with it pressure filling assembly and aircraft |
| CN111907641A (en) * | 2020-02-25 | 2020-11-10 | 青岛海洋地质研究所 | Method and device for controlling oil tank of multi-hull ship and multi-hull ship |
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Application publication date: 20151104 |