CN113955162B - Air supply and feeding device for aircraft - Google Patents
Air supply and feeding device for aircraft Download PDFInfo
- Publication number
- CN113955162B CN113955162B CN202111217093.XA CN202111217093A CN113955162B CN 113955162 B CN113955162 B CN 113955162B CN 202111217093 A CN202111217093 A CN 202111217093A CN 113955162 B CN113955162 B CN 113955162B
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- communicated
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- port
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- 239000007788 liquid Substances 0.000 claims abstract description 37
- 239000000446 fuel Substances 0.000 claims abstract description 14
- 238000010146 3D printing Methods 0.000 claims description 3
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 2
- 238000000034 method Methods 0.000 description 6
- 238000004891 communication Methods 0.000 description 4
- 239000000945 filler Substances 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G5/00—Ground equipment for vehicles, e.g. starting towers, fuelling arrangements
Abstract
The application relates to the technical field of aerospace, in particular to an air supply device for an aircraft. The application provides an aircraft is with air feed device includes: the device comprises a device body, wherein the upper end of the device body is provided with an inflation inlet and a filling opening, the inflation inlet is used for filling gas, the filling opening is used for filling liquid fuel, the right end of the device body is provided with a first oil port, and the first oil port is communicated with the filling opening; the gas cylinders are arranged in the device body, adjacent gas cylinders are sequentially communicated, and an inlet of each gas cylinder is communicated with the charging port; the right end of the air supply pipe is communicated with the outlet of the air bottle, and the left end of the air supply pipe is provided with a second air port through which air is supplied to the aircraft; the right end of the oil pipe is communicated with the filling port, and the left end of the oil pipe is provided with a second oil port; the inlet of the first storage tank is communicated with the first oil port; and the inlet of the second storage tank is communicated with the second oil port.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to an air supply device for an aircraft.
Background
When the carrier aircraft flies outside the atmosphere, liquid fuel and gas are required to be carried to maintain long-distance flight and attitude adjustment, so that a fuel storage tank and a gas bottle are usually placed in a reserved space on the aircraft, and the space envelope of equipment and a container is reduced as much as possible along with the increase of the requirements on the carrying capacity of the aircraft.
When the aircraft is filled with fuel on the ground, the filling pipeline is connected into the storage tank and then filled with fuel, and meanwhile, the other end of the storage tank is communicated with an air pipe so as to facilitate the air in the storage tank to be discharged; when gas filling is carried out, in order to ensure the purity of the gas in the gas cylinder, the gas supply pipeline of the gas cylinder is vacuumized, and then the gas cylinder is filled with high-pressure gas at the other end by using the gas pipeline. The arrangement of the air bottle and the storage box has the defects of large occupied space and complicated manual operation, so that the air supply and feeding device which has a compact structure and is convenient to operate is necessary to meet the carrying requirement of the aircraft.
Disclosure of Invention
The embodiment of the application provides an air feed device for aircraft, the device is in the same place gas cylinder, storage tank and air feed pipeline, filling pipeline integration, has reduced the equipment space, the manual operation of being convenient for.
The application provides an aircraft is with air feed device, include:
the device comprises a device body, wherein the upper end of the device body is provided with an inflation inlet and a filling opening, the inflation inlet is used for filling gas, the filling opening is used for filling liquid fuel, the right end of the device body is provided with a first oil port, and the first oil port is communicated with the filling opening;
the gas cylinders are arranged in the device body, adjacent gas cylinders are sequentially communicated, and an inlet of each gas cylinder is communicated with the charging port;
the right end of the air supply pipe is communicated with the outlet of the air bottle, and the left end of the air supply pipe is provided with a second air port through which air is supplied to the aircraft;
the right end of the oil pipe is communicated with the filling port, and the left end of the oil pipe is provided with a second oil port;
the inlet of the first storage tank is communicated with the first oil port;
and the inlet of the second storage tank is communicated with the second oil port.
In some embodiments, the upper end of the device body is further provided with a vent, and the vent is used for vacuumizing the gas cylinder and exhausting the gas in the first storage tank and the second storage tank.
In some embodiments, the gas cylinder has a wall thickness of 2mm-6mm.
In some embodiments, the inner shape of the cylinder is cylindrical.
In some embodiments, the gas cylinder is made of titanium alloy.
In some embodiments, the device body and the gas cylinder are integrally formed by 3D printing.
In some embodiments, a first gas flow channel, a second gas flow channel and a third gas flow channel are arranged in the device body, an inlet of the first gas flow channel is communicated with the air vent, an inlet of the second gas flow channel is communicated with the air charging port, a second outlet of the second gas flow channel is communicated with an inlet of the gas cylinder, an inlet of the third gas flow channel is communicated with an outlet of the gas cylinder, and an outlet of the third gas flow channel is communicated with the right end of the gas supply pipe.
In some embodiments, a first liquid flow channel and a second liquid flow channel are arranged in the device body, the inlet of the first liquid flow channel and the inlet of the second liquid flow channel are both communicated with the filling port, the outlet of the first liquid flow channel is communicated with the first oil port, and the outlet of the second liquid flow channel is communicated with the right end of the oil pipe.
In some embodiments, the second gas flow channel, the first liquid flow channel, and the second liquid flow channel are all in communication with the first gas flow channel.
In some embodiments, a plurality of fourth gas channels are further disposed in the device body, and adjacent gas cylinders are communicated through the fourth gas channels.
The beneficial effects that technical scheme that this application provided brought include: the air supply device for the aircraft integrates the air cylinder, the air supply pipeline and the fuel filling pipeline together, has compact structure and small occupied space of equipment, and improves the reliability of the equipment; when the aircraft air supply feeding device is used, the installation interface of the filling pipeline is not required to be increased on the aircraft, and manual operation is reduced.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic view of an external structure of an air supply device for an aircraft according to an embodiment of the present application;
fig. 2 is a schematic diagram of an internal structure of an air supply device for an aircraft according to an embodiment of the present disclosure;
fig. 3 is a schematic layout view of a gas cylinder of a gas supply device for an aircraft according to an embodiment of the present application.
In the figure: 1. a device body; 11. a vent; 12. an inflation inlet; 13. a filler neck; 14. a first gas flow passage; 15. a second gas flow path; 16. a third gas flow path; 17. a fourth gas flow path; 18. a first liquid flow path; 19. a second liquid flow path; 111. a first gas port; 112. a first oil port; 2. a gas cylinder; 3. an air supply pipe; 31. a valve; 32. a second gas port; 4. an oil pipe; 41. a second oil port; 5. a first tank; 6. a second tank; 7. and (5) plugging.
Detailed Description
For the purposes of making the objects, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is apparent that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present application based on the embodiments herein.
The embodiment of the application provides an air feed device for aircraft, the device is in the same place gas cylinder and air feed pipeline, fuel filling pipeline integration, has reduced the equipment space, the manual operation of being convenient for.
Fig. 1 is a schematic view showing an internal structure of an air supply device for an aircraft according to an embodiment of the present application, and referring to fig. 1 and 2, the air supply device includes a device body 1, a plurality of air cylinders 2, an air supply pipe 3, an oil pipe 4, a first tank 5, and a second tank 6.
The upper end of the device body 1 is sequentially provided with a vent 11, an inflation inlet 12 and a filling opening 13 from left to right, the device body 1 is internally provided with a first gas flow channel 14, a second gas flow channel 15, a third gas flow channel 16, a plurality of fourth gas flow channels 17, a first liquid flow channel 18 and a second liquid flow channel 19, the inlet of the first gas flow channel 14 is communicated with the vent 11, the inlet of the second gas flow channel 15 is communicated with the inflation inlet 12, the inlet of the first liquid flow channel 18 and the inlet of the second liquid flow channel 19 are both communicated with the filling opening 13, the right end of the device body 1 is provided with a first gas port 111 and a first oil port 112 from top to bottom, the first gas port 111 is communicated with the first outlet of the second gas flow channel 15, and the first oil port 112 is communicated with the outlet of the first liquid flow channel 18; in this embodiment, the vent 11, the inflation inlet 12, the filler inlet 13, and the first air inlet 111 are all provided with plugs 7.
A plurality of gas cylinders 2 are arranged in the device body 1, adjacent gas cylinders 2 are communicated through a fourth gas flow channel 17, and the device body 1 and the gas cylinders 2 are integrally formed through 3D printing.
Referring to fig. 3, in the present embodiment, the number of the gas cylinders 2 is nine, and the nine gas cylinders 2 are respectively denoted as a 1 、A 2 、A 3 、A 4 、A 5 、A 6 、A 7 、A 8 、A 9 As can be seen from fig. 3, marked a 1 -A 6 Are arranged in two rows and three columns, and the gas cylinders 2 (a 2 ) With a gas cylinder 2 (A) 1 ) Gas cylinder 2 (A) 3 ) Gas cylinder 2 (A) 5 ) Is communicated with the fourth gas flow passage 17, and the gas cylinder 2 (a 6 ) With a gas cylinder 2 (A) 3 ) Is communicated with the fourth gas flow passage 17, and the gas cylinder 2 (a 8 ) With a gas cylinder 2 (A) 5 ) Is communicated with the fourth gas flow passage 17, and the gas cylinder 2 (a 1 ) Gas cylinder 2 (A) 4 ) Gas cylinder 2 (A) 7 ) Gas cylinder 2 (A) 9 ) Is communicated in sequence through the fourth gas flow passage 17, and the gas cylinder 2 (a 9 ) Is communicated with the second outlet of the second gas flow path 15, and can be supplied to the gas cylinder 2 (a through the charging port 12 9 ) Middle pouringInto which high-pressure gas is introduced, gas cylinder 2 (A 9 ) The high-pressure gas in (1) flows into the other gas cylinders 2 in sequence through the fourth gas flow passage 17, and the gas cylinders 2 (a 9 ) Is in communication with the inlet of the third gas flow passage 16; in the embodiment, the material of the gas cylinder 2 is titanium alloy, the wall thickness of the gas cylinder 2 is 2mm-6mm, and the inner shape surface of the gas cylinder 2 is cylindrical.
The right end of the air supply pipe 3 is communicated with the outlet of the third air flow passage 16, a valve 31 is arranged on the air supply pipe 3, the valve 31 is used for adjusting the air pressure and flow of air supply, an electromagnetic valve or an electric explosion valve is selected as the valve 31, a second air port 32 is arranged at the left end of the air supply pipe 3, and air is supplied to the aircraft through the second air port 32.
The right end of the oil pipe 4 is communicated with the outlet of the second liquid flow passage 19, and the left end of the oil pipe 4 is provided with a second oil port 41.
The first tank 5 and the second tank 6 are independently arranged, the inlet of the first tank 5 is communicated with the first oil port 112, liquid fuel is injected into the first tank 5 through the first oil port 112, the inlet of the second tank 6 is communicated with the second oil port 41, liquid fuel is injected into the second tank 6 through the second oil port 41, the first tank 5 and the second tank 6 are communicated with the first air port 111, and air is injected into the first tank 5 and the second tank 6 through the first air port 111.
In this embodiment, the second gas flow channel 15, the first liquid flow channel 18 and the second liquid flow channel 19 are all in communication with the first gas flow channel 14, so that the air bottle 2 can be vacuumized through the air vent 11 and the redundant air in the first storage tank 5 and the second storage tank 6 can be discharged.
The air feed device for aircraft that this embodiment provided theory of operation does: when the aircraft is on the ground, before filling liquid fuel and gas, firstly opening the plug 7 of the vent 11, vacuumizing to discharge gas in the gas cylinder 2, the first storage tank 5 and the second storage tank 6, after vacuumizing, opening the plug 7 of the filling port 13, adding the liquid fuel into the filling port 13, wherein the liquid fuel is divided into two paths, one path reaches the first oil port 112 through the first liquid flow channel 18 and then flows into the first storage tank 5, and the other path reaches the second oil port 41 through the second liquid flow channel 19 and the oil pipe 4 and then flows into the second storage tank 6; when gas filling is carried out, the plug 7 of the gas filling port 12 is opened byThe gas is injected into the gas charging port 12 and enters the gas cylinder 2 (a through the second gas flow passage 15 9 ) And sequentially flows into the other cylinders 2 (a 1 -A 8 ) During the flight of the aircraft, the gas in the gas cylinder 2 reaches the second gas port 32 via the third gas flow channel 16 and the gas supply pipe 3 to supply gas to the aircraft.
In the description of the present application, it should be noted that the azimuth or positional relationship indicated by the terms "upper", "lower", etc. are based on the azimuth or positional relationship shown in the drawings, and are merely for convenience of description of the present application and simplification of the description, and are not indicative or implying that the apparatus or element in question must have a specific azimuth, be configured and operated in a specific azimuth, and thus should not be construed as limiting the present application. Unless specifically stated or limited otherwise, the terms "mounted," "connected," and "coupled" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art as the case may be.
It should be noted that in this application, relational terms such as "first" and "second" and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
The foregoing is merely a specific embodiment of the application to enable one skilled in the art to understand or practice the application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (6)
1. An air supply and feed device for an aircraft, comprising:
the device comprises a device body (1), wherein an inflation inlet (12) and a filling opening (13) are formed in the upper end of the device body (1), the inflation inlet (12) is used for filling gas, the filling opening (13) is used for filling liquid fuel, a first oil port (112) is formed in the right end of the device body (1), and the first oil port (112) is communicated with the filling opening (13);
the gas cylinders (2) are arranged in the device body (1), adjacent gas cylinders (2) are sequentially communicated, and an inlet of each gas cylinder (2) is communicated with the inflation inlet (12);
the right end of the air supply pipe (3) is communicated with an outlet of the air bottle (2), a second air port (32) is arranged at the left end of the air supply pipe (3), and air is supplied to the aircraft through the second air port (32);
the right end of the oil pipe (4) is communicated with the filling port (13), and the left end of the oil pipe (4) is provided with a second oil port (41);
a first storage tank (5), wherein an inlet of the first storage tank (5) is communicated with a first oil port (112);
a second storage tank (6), wherein an inlet of the second storage tank (6) is communicated with a second oil port (41);
a first gas flow passage (14), a second gas flow passage (15) and a third gas flow passage (16) are arranged in the device body (1), an inlet of the second gas flow passage (15) is communicated with the charging port (12), a second outlet of the second gas flow passage (15) is communicated with an inlet of the gas cylinder (2), an inlet of the third gas flow passage (16) is communicated with an outlet of the gas cylinder (2), and an outlet of the third gas flow passage (16) is communicated with the right end of the gas supply pipe (3);
a first liquid flow channel (18) and a second liquid flow channel (19) are arranged in the device body (1), an inlet of the first liquid flow channel (18) and an inlet of the second liquid flow channel (19) are both communicated with the filling port (13), an outlet of the first liquid flow channel (18) is communicated with the first oil port (112), and an outlet of the second liquid flow channel (19) is communicated with the right end of the oil pipe (4);
the upper end of the device body (1) is also provided with a vent (11), and the vent (11) is used for vacuumizing the gas cylinder (2) and exhausting gas in the first storage tank (5) and the second storage tank (6);
the device body (1) and the air bottle (2) are integrally formed through 3D printing;
the second gas flow passage (15), the first liquid flow passage (18) and the second liquid flow passage (19) are all communicated with the first gas flow passage (14).
2. Air supply and supply device for aircraft according to claim 1, characterized in that the wall thickness of the gas cylinder (2) is 2-6 mm.
3. Air supply and supply device for aircraft according to claim 1, characterized in that the inner shape of the cylinder (2) is cylindrical.
4. Air supply and supply device for aircraft according to claim 1, characterized in that the material of the gas cylinder (2) is titanium alloy.
5. The air supply and supply device for the aircraft according to claim 1, wherein a first air flow passage (14) is arranged in the device body (1), and an inlet of the first air flow passage (14) is communicated with the air vent (11).
6. The air supply and feeding device for the aircraft according to claim 1, wherein a plurality of fourth air flow passages (17) are further arranged in the device body (1), and adjacent air cylinders (2) are communicated through the fourth air flow passages (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111217093.XA CN113955162B (en) | 2021-10-19 | 2021-10-19 | Air supply and feeding device for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111217093.XA CN113955162B (en) | 2021-10-19 | 2021-10-19 | Air supply and feeding device for aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113955162A CN113955162A (en) | 2022-01-21 |
| CN113955162B true CN113955162B (en) | 2024-03-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111217093.XA Active CN113955162B (en) | 2021-10-19 | 2021-10-19 | Air supply and feeding device for aircraft |
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| Country | Link |
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| CN (1) | CN113955162B (en) |
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| RU2440918C1 (en) * | 2010-07-15 | 2012-01-27 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Spaceship high-pressure gas cylinder filling system and method of its operation |
| CN205168481U (en) * | 2015-11-06 | 2016-04-20 | 山东东大工程机械有限公司 | Gas cylinder composite set and highway rail hydraulic haulage car |
| KR20190101781A (en) * | 2018-02-23 | 2019-09-02 | 서미영 | Drone using cng as a fuel |
| CN111928104A (en) * | 2020-10-09 | 2020-11-13 | 北京星际荣耀空间科技有限公司 | Liquid oxymethane rocket supercharging device and liquid oxymethane rocket |
| CN112879809A (en) * | 2021-01-11 | 2021-06-01 | 江苏深蓝航天有限公司 | Propellant transfer integrated cabin and propellant filling system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20210171223A1 (en) * | 2017-06-15 | 2021-06-10 | University Of Vermont And State Agricultural College | Propulsion Systems Utilizing Gas Generated Via An Exothermically Decomposable Chemical Blowing Agent, and Spacecraft Incorporating Same |
-
2021
- 2021-10-19 CN CN202111217093.XA patent/CN113955162B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5562130A (en) * | 1995-03-16 | 1996-10-08 | Olin Corporation | Hazardous chemical transfer module |
| US6360730B1 (en) * | 1996-03-18 | 2002-03-26 | Fuel Dynamics | Inert loading jet fuel |
| CN2894736Y (en) * | 2006-03-22 | 2007-05-02 | 湖南煤矿安全装备有限公司 | Isolated compressed oxygen self-rescuer |
| RU2440918C1 (en) * | 2010-07-15 | 2012-01-27 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Spaceship high-pressure gas cylinder filling system and method of its operation |
| CN205168481U (en) * | 2015-11-06 | 2016-04-20 | 山东东大工程机械有限公司 | Gas cylinder composite set and highway rail hydraulic haulage car |
| KR20190101781A (en) * | 2018-02-23 | 2019-09-02 | 서미영 | Drone using cng as a fuel |
| CN111928104A (en) * | 2020-10-09 | 2020-11-13 | 北京星际荣耀空间科技有限公司 | Liquid oxymethane rocket supercharging device and liquid oxymethane rocket |
| CN112879809A (en) * | 2021-01-11 | 2021-06-01 | 江苏深蓝航天有限公司 | Propellant transfer integrated cabin and propellant filling system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113955162A (en) | 2022-01-21 |
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