CN113955162A - Air supply feedway for aircraft - Google Patents
Air supply feedway for aircraft Download PDFInfo
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- CN113955162A CN113955162A CN202111217093.XA CN202111217093A CN113955162A CN 113955162 A CN113955162 A CN 113955162A CN 202111217093 A CN202111217093 A CN 202111217093A CN 113955162 A CN113955162 A CN 113955162A
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- 239000007788 liquid Substances 0.000 claims abstract description 37
- 239000000446 fuel Substances 0.000 claims abstract description 15
- 238000004891 communication Methods 0.000 claims description 4
- 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 3
- 238000007599 discharging Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 description 6
- 230000009471 action Effects 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
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
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The application relates to the technical field of aerospace, in particular to an air supply and feeding device for an aircraft. The application provides an air feed feedway for aircraft includes: the device comprises a device body, wherein the upper end of the device body is provided with an inflation inlet and a filling port, the inflation inlet is used for filling gas, the filling port 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 port; the gas cylinders are distributed in the device body, adjacent gas cylinders are sequentially communicated, and inlets of the gas cylinders are communicated with the gas charging port; the right end of the air supply pipe is communicated with an 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 and feeding device for an aircraft.
Background
When the carrier aircraft flies outside the atmosphere, liquid fuel and gas are carried to maintain remote flight and attitude adjustment, so that a fuel storage tank and a gas cylinder are usually reserved in the aircraft, and the space envelope of equipment and a container is reduced as much as possible along with the improvement of the carrying capacity requirement of the aircraft.
The existing gas cylinder, storage tank, fuel filling pipeline and gas supply pipeline are independently arranged, when the aircraft is filled with fuel on the ground, the filling pipeline is connected to the storage tank firstly, then the fuel filling is carried out, and simultaneously, the other end of the storage tank is communicated with a gas pipe so as to be convenient for discharging the air in the storage tank; when gas filling is carried out, in order to ensure the purity of gas in the gas cylinder, the gas supply pipeline of the gas cylinder needs to be vacuumized, and then the gas cylinder is filled with high-pressure gas by the gas pipeline at the other end. The arrangement of the gas cylinder and the storage tank has the defects of large occupied space and complicated manual operation, so that a gas supply and material supply device which is compact in structure and convenient to operate is needed to meet the carrying requirement of an aircraft.
Disclosure of Invention
The embodiment of the application provides an air feed feedway for aircraft, and the device is in the same place gas cylinder, storage tank and air supply line, filling pipeline integration, has reduced equipment space, the manual operation of being convenient for.
The application provides an air feed feedway for aircraft includes:
the device comprises a device body, wherein the upper end of the device body is provided with an inflation inlet and a filling port, the inflation inlet is used for filling gas, the filling port 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 port;
the gas cylinders are distributed in the device body, adjacent gas cylinders are sequentially communicated, and inlets of the gas cylinders are communicated with the gas charging port;
the right end of the air supply pipe is communicated with an 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 also provided with a vent used for vacuumizing the gas cylinder and exhausting gas in the first storage tank and the second storage tank.
In some embodiments, the cylinder has a wall thickness of 2mm to 6 mm.
In some embodiments, the internal face of the cylinder is cylindrical.
In some embodiments, the material of the gas cylinder is a 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 passage, a second gas flow passage and a third gas flow passage are arranged in the device body, an inlet of the first gas flow passage is communicated with the vent, an inlet of the second gas flow passage is communicated with the inflation inlet, a second outlet of the second gas flow passage is communicated with an inlet of the gas cylinder, an inlet of the third gas flow passage is communicated with an outlet of the gas cylinder, and an outlet of the third gas flow passage is communicated with the right end of the gas supply pipe.
In some embodiments, a first liquid flow passage and a second liquid flow passage are arranged in the device body, an inlet of the first liquid flow passage and an inlet of the second liquid flow passage are both communicated with the filling port, an outlet of the first liquid flow passage is communicated with the first oil port, and an outlet of the second liquid flow passage is communicated with the right end of the oil pipe.
In some embodiments, the second gas flow passage, the first liquid flow passage, and the second liquid flow passage are all in communication with the first gas flow passage.
In some embodiments, a plurality of fourth gas flow passages are further disposed in the device body, and adjacent gas cylinders are communicated through the fourth gas flow passages.
The beneficial effect that technical scheme that this application provided brought includes: according to the air supply and feeding device for the aircraft, the air bottle, the air supply pipeline and the fuel filling pipeline are integrated, the structure is compact, the occupied space of equipment is small, and the reliability of the equipment is improved; when the air supply and feeding device for the aircraft is used, an installation interface of a filling pipeline is not required to be added on the aircraft, and manual operation is reduced.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
Fig. 1 is a schematic external structural view of an air supply and supply device for an aircraft according to an embodiment of the present application;
fig. 2 is a schematic internal structural diagram of an air supply and supply device for an aircraft according to an embodiment of the present application;
fig. 3 is a schematic layout of gas cylinders of the air supply and supply device for the aircraft according to the embodiment of the present application.
In the figure: 1. a device body; 11. a vent; 12. an inflation inlet; 13. a filling port; 14. a first gas flow path; 15. a second gas flow channel; 16. a third gas flow channel; 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. a gas 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 (7) a plug.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in 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 obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
The embodiment of the application provides an air feed feedway for aircraft, and the device is in the same place gas cylinder and air supply line, fuel filling pipeline are integrated, have reduced the equipment space, the manual operation of being convenient for.
Fig. 1 is a schematic diagram of the internal structure of an air supply and supply device for an aircraft according to an embodiment of the present application, and referring to fig. 1 and 2, the air supply and 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 device comprises a device body 1, wherein a vent 11, an inflation inlet 12 and a filling inlet 13 are sequentially formed in the upper end of the device body 1 from left to right, a first gas flow passage 14, a second gas flow passage 15, a third gas flow passage 16, a plurality of fourth gas flow passages 17, a first liquid flow passage 18 and a second liquid flow passage 19 are arranged in the device body 1, an inlet of the first gas flow passage 14 is communicated with the vent 11, an inlet of the second gas flow passage 15 is communicated with the inflation inlet 12, an inlet of the first liquid flow passage 18 and an inlet of the second liquid flow passage 19 are both communicated with the filling inlet 13, a first gas port 111 and a first oil port 112 are formed in the right end of the device body 1 from top to bottom, the first gas port 111 is communicated with a first outlet of the second gas flow passage 15, and the first oil port 112 is communicated with an outlet of the first liquid flow passage 18; in this embodiment, the plugs 7 are disposed at the vent 11, the inflation port 12, the filling port 13, and the first vent 111.
A plurality of gas cylinders 2 are arranged in the device body 1, the adjacent gas cylinders 2 are communicated through a fourth gas flow passage 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 marked as a1、A2、A3、A4、A5、A6、A7、A8、A9As can be seen in FIG. 3, the label is A1-A6The gas cylinders 2 are arranged in two rows and three columns, the gas cylinders 2 (A)2) With gas cylinder 2 (A)1) Gas cylinder 2 (A)3) Gas cylinder 2 (A)5) Through the fourth gas flow passage 17, the gas cylinder 2 (A)6) With gas cylinder 2 (A)3) Through the fourth gas flow passage 17, the gas cylinder 2 (A)8) With gas cylinder 2 (A)5) Through the fourth gas flow passage 17, the gas cylinder 2 (A)1) Gas cylinder 2 (A)4) Gas cylinder 2 (A)7) Gas cylinder 2 (A)9) Connected in series through a fourth gas flow passage 17, the gas cylinder 2 (A)9) Is in communication with a second outlet of the second gas channel 15, then it is possible to supply gas to the gas cylinder 2 (a) through the charging port 129) With intermediate injection of high pressure gas, cylinder 2 (A)9) The high-pressure gas in the middle flows into other gas cylinders 2, the gas cylinder 2 (A), in turn through a fourth gas flow passage 179) Is in communication with the inlet of the third gas flow channel 16; in the embodiment, the gas cylinder 2 is made of titanium alloy, the wall thickness of the gas cylinder 2 is 2mm-6mm, and the inner surface of the gas cylinder 2 is cylindrical.
The right end of the air supply pipe 3 is communicated with an outlet of the third air flow channel 16, a valve 31 is arranged on the air supply pipe 3, the valve 31 is used for adjusting air pressure and flow of air supply, the valve 31 is an electromagnetic valve or an electric explosion valve, a second air port 32 is arranged at the left end of the air supply pipe 3, and air supply is carried out on 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 storage tank 5 and the second storage tank 6 are independently arranged, an inlet of the first storage tank 5 is communicated with the first oil port 112, liquid fuel is injected into the first storage tank 5 through the first oil port 112, an inlet of the second storage tank 6 is communicated with the second oil port 41, the liquid fuel is injected into the second storage tank 6 through the second oil port 41, the first storage tank 5 and the second storage tank 6 are both communicated with the first air port 111, and gas is injected into the first storage tank 5 and the second storage tank 6 through the first air port 111.
In this embodiment, the second gas flow path 15, the first liquid flow path 18, and the second liquid flow path 19 are all connected to the first gas flow path 14, so that the gas cylinder 2 can be evacuated and excess air in the first storage tank 5 and the second storage tank 6 can be discharged through the vent 11.
The working principle of the air supply and supply device for the aircraft provided by the embodiment is as follows: when the aircraft is on the ground, before filling liquid fuel and gas, the plug 7 of the air vent 11 is opened, the gas in the gas cylinder 2, the first storage tank 5 and the second storage tank 6 is discharged in a vacuumizing mode, after the vacuumizing is finished, the plug 7 of the filling port 13 is opened, the liquid fuel is added into the filling port 13, the liquid fuel is divided into two paths, one path reaches the first oil port 112 through the first liquid flow passage 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 passage 19 and the oil pipe 4 and then flows into the second storage tank 6; when gas is filled, the plug 7 of the charging port 12 is opened, gas is injected through the charging port 12, and the gas enters the gas cylinder 2 (A) through the second gas flow passage 159) And sequentially flows into other gas cylinders 2 (a) through the fourth gas flow passage 171-A8) During flight of the aircraft, the gas in the gas cylinder 2 is supplied to the aircraft through the third gas flow passage 16 and the gas supply pipe 3 to the second gas port 32.
In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are only for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present application. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
It is noted that, in the present 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. Also, 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 an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The above description is merely exemplary of the present application and is presented to enable those skilled in the art to understand and practice the present 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 (10)
1. An air supply and supply device for an aircraft, comprising:
the device comprises a device body (1), wherein the upper end of the device body (1) is provided with an inflation inlet (12) and a filling inlet (13), the inflation inlet (12) is used for filling gas, the filling inlet (13) is used for filling liquid fuel, the right end of the device body (1) is provided with a first oil port (112), and the first oil port (112) is communicated with the filling inlet (13);
the gas cylinders (2) are arranged in the device body (1), adjacent gas cylinders (2) are sequentially communicated, and the inlets of the gas cylinders (2) are communicated with the inflating port (12);
the right end of the air supply pipe (3) is communicated with the outlet of the air bottle (2), the left end of the air supply pipe (3) is provided with a second air port (32), 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 tank (5), wherein the inlet of the first tank (5) is communicated with a first oil port (112);
and the inlet of the second storage tank (6) is communicated with the second oil port (41).
2. The air supply and feeding device for the aircraft according to claim 1, wherein the upper end of the device body (1) is further provided with a vent (11), and the vent (11) is used for vacuumizing the air bottle (2) and discharging the air in the first storage tank (5) and the second storage tank (6).
3. An air supply and supply device for aircraft according to claim 1, characterized in that the wall thickness of the cylinder (2) is between 2mm and 6 mm.
4. An air supply and supply device for aircraft according to claim 1, characterized in that the internal shape of the cylinder (2) is cylindrical.
5. An air supply and supply device for aircraft according to claim 1, characterized in that the material of the cylinder (2) is titanium alloy.
6. The air supply and feeding device for the aircraft according to claim 1, wherein the device body (1) and the air bottle (2) are integrally formed by 3D printing.
7. The air supply and feeding device for the aircraft according to claim 2, wherein 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 first gas flow passage (14) is communicated with the vent port (11), 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 air bottle (2), an inlet of the third gas flow passage (16) is communicated with an outlet of the air bottle (2), and an outlet of the third gas flow passage (16) is communicated with a right end of the air supply pipe (3).
8. The air supply and feeding device for the aircraft according to claim 7, wherein a first liquid flow passage (18) and a second liquid flow passage (19) are arranged in the device body (1), an inlet of the first liquid flow passage (18) and an inlet of the second liquid flow passage (19) are both communicated with the filling port (13), an outlet of the first liquid flow passage (18) is communicated with the first oil port (112), and an outlet of the second liquid flow passage (19) is communicated with the right end of the oil pipe (4).
9. An aircraft gas supply and supply device according to claim 8, characterised in that 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).
10. The air supply and feeding device for the aircraft according to claim 1, wherein a plurality of fourth gas flow passages (17) are further provided in the device body (1), and adjacent air bottles (2) are communicated through the fourth gas 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 true CN113955162A (en) | 2022-01-21 |
| CN113955162B 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) |
Citations (9)
| 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 |
| 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 (9)
| 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 |
| 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 |
| 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 |
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| Publication number | Publication date |
|---|---|
| CN113955162B (en) | 2024-03-12 |
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