CN113335550B - Airplane ground environmental control vehicle with automatic filling function - Google Patents
Airplane ground environmental control vehicle with automatic filling function Download PDFInfo
- Publication number
- CN113335550B CN113335550B CN202110826045.4A CN202110826045A CN113335550B CN 113335550 B CN113335550 B CN 113335550B CN 202110826045 A CN202110826045 A CN 202110826045A CN 113335550 B CN113335550 B CN 113335550B
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- China
- Prior art keywords
- flow
- liquid supply
- liquid
- supply pipeline
- output pump
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- 230000007613 environmental effect Effects 0.000 title claims abstract description 15
- 239000007788 liquid Substances 0.000 claims abstract description 75
- 238000001802 infusion Methods 0.000 claims abstract description 17
- 230000001105 regulatory effect Effects 0.000 claims abstract description 13
- 238000007872 degassing Methods 0.000 claims abstract description 12
- 230000003993 interaction Effects 0.000 claims abstract description 8
- 238000002955 isolation Methods 0.000 claims description 11
- 210000001503 joint Anatomy 0.000 claims description 6
- 230000002265 prevention Effects 0.000 claims description 6
- 239000012530 fluid Substances 0.000 abstract description 3
- 238000004140 cleaning Methods 0.000 abstract 1
- 125000004122 cyclic group Chemical group 0.000 abstract 1
- 239000000110 cooling liquid Substances 0.000 description 22
- 238000012423 maintenance Methods 0.000 description 5
- 239000002826 coolant Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000037452 priming Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/36—Other airport installations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B67—OPENING, CLOSING OR CLEANING BOTTLES, JARS OR SIMILAR CONTAINERS; LIQUID HANDLING
- B67D—DISPENSING, DELIVERING OR TRANSFERRING LIQUIDS, NOT OTHERWISE PROVIDED FOR
- B67D7/00—Apparatus or devices for transferring liquids from bulk storage containers or reservoirs into vehicles or into portable containers, e.g. for retail sale purposes
- B67D7/02—Apparatus or devices for transferring liquids from bulk storage containers or reservoirs into vehicles or into portable containers, e.g. for retail sale purposes for transferring liquids other than fuel or lubricants
Abstract
The invention discloses an aircraft ground environmental control vehicle with an automatic filling function, which comprises a small-flow liquid conveying system and a large-flow liquid conveying system. The liquid delivery system includes: the infusion box is connected with the output pump set, the liquid supply pipeline connected with the output pump set and the liquid supply hose connected with the liquid supply pipeline; the liquid supply pipeline is provided with a first-stage degassing filter, a second-stage precise filter and an electric flow regulating valve; the liquid supply pipeline is also provided with an automatic flow control system. The invention can realize the automatic flow regulation in a wide range through simple man-machine interaction, and simultaneously has the functions of manual fluid infusion and cyclic cleaning.
Description
Technical Field
The invention relates to the field of aircraft ground environmental control system guarantee equipment, in particular to an aircraft ground environmental control vehicle with an automatic filling function.
Background
With the development of the aviation field in China, the annular control system of the multi-type aircraft starts to comprehensively guarantee the annular control system of the aircraft in a liquid cooling mode, and the filling modes of cooling liquid of different types are gradually diversified. When different model aircraft environmental control systems need the coolant liquid to annotate, current aircraft ground guarantee equipment only can satisfy the function of annotating of a certain model, and the filling function is single, can only annotate the coolant liquid through manual mode, and the degree of universalization is low, causes the problem such as guarantee wasting of resources.
Disclosure of Invention
The invention aims to solve the problem that the existing aircraft ground ring control vehicle cannot simultaneously meet the requirements of single and diversified functions under the filling working conditions of ring control systems of different types, and provides the aircraft ground ring control vehicle with the advantages of compact structure, stable work, high degree of universalization and multiple filling functions of manual operation, automatic operation, small flow, large flow and the like.
In order to achieve the purpose, the technical scheme adopted by the invention is to design the aircraft ground environmental control vehicle with the automatic filling function, which comprises a small-flow liquid conveying system and a large-flow liquid conveying system.
The low flow liquid delivery system includes: the infusion box is connected with the small-flow output pump set, the liquid supply pipeline connected with the output pump set and the liquid supply hose connected with the liquid supply pipeline; the liquid supply hose can be pulled out to the airplane filling port electrically to be in butt joint with the airplane filling port; the liquid supply pipeline is provided with a first-stage degassing filter and a second-stage precise filter, and the filter precision is respectively 40 mu m, 10 mu m and 1 mu m; meanwhile, a backflow prevention one-way valve is also arranged; the small-flow output pump set adopts a two-stage pump series connection mode, and comprises an output pump and a booster pump;
the high flow liquid delivery system includes: the infusion box is connected with the high-flow output pump set, the liquid supply pipeline connected with the output pump set and the liquid supply hose connected with the liquid supply pipeline; the liquid supply hose can be pulled out to the airplane filling port electrically to be in butt joint with the airplane filling port; the liquid supply pipeline is provided with a first-stage degassing filter and a second-stage precise filter, the filter precision is respectively 40 mu m, 10 mu m and 1 mu m, and a backflow prevention one-way valve is also arranged; the high-flow output pump set adopts a two-stage pump series connection mode, and comprises an output pump and a booster pump.
The liquid supply pipeline is also provided with a flow automatic control system.
The automatic flow control system includes: and the man-machine interaction module is respectively connected with the isolation signal acquisition module and the isolation signal output module of the man-machine interaction.
The isolation signal acquisition module is also connected with a pressure sensor, a flow sensor and external aircraft signals.
An electric flow regulating valve is also arranged between the flow sensor and the output pump group, and the flow regulating range is respectively 2-50L/min and 50-300L/min.
A safety valve is arranged between the pressure sensor and the infusion box.
And the isolation signal output module is also connected with an output pump set driver and a flow regulating valve controller.
Compared with the prior art, the invention has the following beneficial effects:
the utility model provides an aircraft ground environmental control car with automatic filling function, it has little flow output pump package, high-flow output pump package automatic control system, can realize little flow, high-flow automatic filling through simple human-computer interaction, can compromise simultaneously that manual fluid infusion fills function and circulation washs the function.
The invention adopts a mode of switching a conventional small-flow output pump set and a large-flow output pump set, realizes the functions of automatically filling the cooling liquid with different flow rates and different pressures by regulating the speed of the output pump set and collecting signals on a flow sensor and an external machine through the flow automatic control system, and the output pump set adopts two-stage output pumps for serial backup.
Drawings
Fig. 1 is a schematic diagram of the present invention.
Detailed Description
The following describes the embodiments of the present invention further with reference to the drawings and examples. The following examples are only for more clearly illustrating the technical aspects of the present invention, and are not intended to limit the scope of the present invention.
As shown in FIG. 1, the invention provides an aircraft ground environmental control vehicle with an automatic filling function, which comprises a small-flow liquid conveying system and a large-flow liquid conveying system.
The low flow liquid delivery system includes: the infusion box is connected with the small-flow output pump set, the liquid supply pipeline connected with the output pump set and the liquid supply hose connected with the liquid supply pipeline; the liquid supply hose can be pulled out to the airplane filling port electrically to be in butt joint with the airplane filling port; the liquid supply pipeline is provided with a first-stage degassing filter and a second-stage precise filter, and the filter precision is respectively 40 mu m, 10 mu m and 1 mu m; meanwhile, a backflow prevention one-way valve is also arranged;
the high flow liquid delivery system includes: the infusion box is connected with the high-flow output pump set, the liquid supply pipeline connected with the output pump set and the liquid supply hose connected with the liquid supply pipeline; the liquid supply hose can be pulled out to the airplane filling port electrically to be in butt joint with the airplane filling port; the liquid supply pipeline is provided with a first-stage degassing filter and a second-stage precise filter, the filter precision is respectively 40 mu m, 10 mu m and 1 mu m, and the liquid supply pipeline is also provided with a backflow prevention one-way valve.
The liquid supply pipeline is also provided with an automatic flow control system; the automatic flow control system includes: the system comprises a man-machine interaction, an isolated signal acquisition module and an isolated signal output module, wherein the isolated signal acquisition module and the isolated signal output module are respectively connected with the man-machine interaction; the isolation signal acquisition module is also connected with a pressure sensor, a flow sensor and external aircraft signals; an electric flow regulating valve is also arranged between the flow sensor and the output pump set, and the flow regulating range is respectively 2-50L/min and 50-300L/min; a safety valve is arranged between the pressure sensor and the infusion box; the isolation signal output module is also connected with an output pump set driver and a flow regulating valve controller.
The aircraft ground environmental control vehicle can change the working frequency of the output pump set and the switching of the small-flow output pump set and the large-flow output pump set according to the requirements of different model parameters, and adjust the liquid supply flow and pressure. Through the analysis processing of the feed liquid flow and the pressure feedback signals, and then the electric flow regulating valve is regulated according to the analysis processing result, the flow and the pressure output by the system are accurately controlled. And connecting the filling ground joint with the aircraft liquid supply joint, and selecting a liquid filling function. The cooling liquid in the transfusion box enters the output pump set through the maintenance ball valve, and after being pressurized by the output pump set (comprising the output pump and the booster pump), the cooling liquid enters the aircraft through the flow sensor, the pressure sensor, the one-way valve, the degassing filter, the coarse filter, the fine filter, the liquid supply hose and the filling ground joint, so that the filling of the cooling liquid of the aircraft is realized.
The ground ring control vehicle of the airplane monitors the liquid level of the infusion box in real time through the liquid level sensor, and when the liquid level is too low, an alarm can be sent out and the equipment is stopped. When the liquid adding pressure of the system exceeds the rated pressure of the aircraft ground ring control vehicle, the flow automatic control system collects signals of the pressure sensor to stop the aircraft ground ring control vehicle, and the safety valve is opened to unload, so that the purposes of protecting the aircraft and the aircraft ground ring control vehicle are achieved.
The aircraft ground environmental control vehicle collects an aircraft full oil signal and an aircraft emergency signal through the isolation signal collecting module. When full oil signals or emergency signals appear in the process of filling the liquid into the aircraft, the aircraft ground environmental control vehicle can automatically stop to prevent excessive filling of the cooling liquid, so as to realize an automatic stopping function; the aircraft ground ring control liquid cooling vehicle can also set the single cooling liquid filling amount.
The cooling liquid filling mode of the aircraft environment control vehicle is divided into a large-flow filling mode, a small-flow filling mode, an automatic filling mode and a manual filling mode.
Mode one, high flow priming mode:
when the aircraft needs to be filled with the flow of 50-300L/min, the filling flow and the pressure are set according to the model requirement, the cooling liquid in the infusion box enters a large-flow output pump set through a maintenance ball valve, and the cooling liquid enters the aircraft through a flow sensor, a pressure sensor, a one-way valve, a degassing filter, a coarse filter, a fine filter, a liquid supply hose and a filling ground joint after being pressurized by the output pump set (comprising the output pump and a booster pump), and is automatically stopped according to an on-board oil filling signal, so that the large-flow filling of the cooling liquid of the aircraft is realized.
Mode two, low flow priming mode:
when the aircraft needs to be filled with the flow of 2-50L/min, the filling flow and the pressure are set according to the model requirement, the cooling liquid in the infusion box enters a small-flow output pump set through a maintenance ball valve, and the cooling liquid enters the aircraft through a flow sensor, a pressure sensor, a one-way valve, a degassing filter, a coarse filter, a fine filter, a liquid supply hose and a filling ground joint after being pressurized by the output pump set (comprising the output pump and a booster pump), and is automatically stopped according to an on-board oil filling signal, so that the small-flow filling of the cooling liquid of the aircraft is realized.
Mode three, automatic filling mode:
the filling quantity, the filling flow and the filling pressure of the cooling liquid are set according to the model requirement, the cooling liquid in the infusion box enters an output pump set (a large-flow output pump set and a small-flow output pump set are automatically switched according to the filling quantity of the cooling liquid) through a maintenance ball valve, the cooling liquid is pressurized through the output pump set (comprising the output pump and a booster pump), then enters an airplane through a flow sensor, a pressure sensor, a one-way valve, a degassing filter, a coarse filter, a fine filter, a liquid supply hose and a filling ground joint, and is automatically stopped according to an on-board oil filling signal, so that the cooling liquid of the airplane is automatically filled.
Mode four, manual fluid infusion fill mode:
when the aircraft is not full of oil signals, the aircraft ground environmental control vehicle is filled at the speed of 2L/min of liquid supply flow, the cooling liquid in the liquid conveying box enters a small-flow output pump set through a maintenance ball valve, and the cooling liquid is pressurized through the output pump set (comprising the output pump and a booster pump) and then enters the aircraft through a flow sensor, a pressure sensor, a one-way valve, a degassing filter, a coarse filter, a fine filter, a liquid supply hose and a filling ground joint, so that manual liquid filling of the aircraft cooling liquid is realized.
Therefore, on the basis of guaranteeing the aircraft environmental control system, a plurality of modes for filling the aircraft are added, and the filling function requirements of different aircraft types can be effectively and reliably met.
The foregoing is merely a preferred embodiment of the present invention, and it should be noted that modifications could be made by those skilled in the art without departing from the technical principles of the present invention, and such modifications should also be considered as being within the scope of the present invention.
Claims (5)
1. The utility model provides an aircraft ground environmental control car with automatic filling function, includes low discharge liquid conveying system and high-flow liquid conveying system, its characterized in that: the low flow liquid delivery system includes: the infusion box is connected with the small-flow output pump set, the liquid supply pipeline connected with the output pump set and the liquid supply hose connected with the liquid supply pipeline; the liquid supply hose can be pulled out to the airplane filling port electrically to be in butt joint with the airplane filling port; the liquid supply pipeline is provided with a first-stage degassing filter and a second-stage precise filter, and the filter precision is respectively 40 mu m, 10 mu m and 1 mu m; meanwhile, a backflow prevention one-way valve is also arranged;
the high flow liquid delivery system includes: the infusion box is connected with the high-flow output pump set, the liquid supply pipeline connected with the output pump set and the liquid supply hose connected with the liquid supply pipeline; the liquid supply hose can be pulled out to the airplane filling port electrically to be in butt joint with the airplane filling port; the liquid supply pipeline is provided with a first-stage degassing filter and a second-stage precise filter, the filter precision is respectively 40 mu m, 10 mu m and 1 mu m, and a backflow prevention one-way valve is also arranged;
the liquid supply pipeline is also provided with an automatic flow control system;
the automatic flow control system comprises: and the man-machine interaction module is respectively connected with the isolation signal acquisition module and the isolation signal output module of the man-machine interaction.
2. An aircraft ground pilot vehicle with automatic fueling capability as set forth in claim 1 wherein: the isolation signal acquisition module is also connected with a pressure sensor, a flow sensor and external aircraft signals.
3. An aircraft ground pilot vehicle with automatic fueling capability as set forth in claim 2 wherein: an electric flow regulating valve is also arranged between the flow sensor and the output pump group, and the flow regulating range is respectively 2-50L/min and 50-300L/min.
4. An aircraft ground pilot vehicle with automatic fueling capability as set forth in claim 3 wherein: a safety valve is arranged between the pressure sensor and the infusion box.
5. An aircraft ground pilot vehicle with automatic fueling capability as set forth in claim 4 wherein: and the isolation signal output module is also connected with an output pump set driver and a flow regulating valve controller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110826045.4A CN113335550B (en) | 2021-07-21 | 2021-07-21 | Airplane ground environmental control vehicle with automatic filling function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110826045.4A CN113335550B (en) | 2021-07-21 | 2021-07-21 | Airplane ground environmental control vehicle with automatic filling function |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113335550A CN113335550A (en) | 2021-09-03 |
| CN113335550B true CN113335550B (en) | 2024-04-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110826045.4A Active CN113335550B (en) | 2021-07-21 | 2021-07-21 | Airplane ground environmental control vehicle with automatic filling function |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114408207A (en) * | 2022-01-10 | 2022-04-29 | 沈阳航达机载设备有限公司 | Aircraft ground liquid cooling equipment with automatic vacuumizing function |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3111968A (en) * | 1960-07-11 | 1963-11-26 | Richard T Headrick | Apparatus for transporting fluids |
| US4371096A (en) * | 1979-04-16 | 1983-02-01 | Nordson Corporation | Control apparatus for pressurized gas/liquid systems |
| CN101486381A (en) * | 2009-02-26 | 2009-07-22 | 中国人民解放军空军济南航空四站装备修理厂 | Airplane ground liquid cooling vehicle |
| CN106184809A (en) * | 2016-08-31 | 2016-12-07 | 飞瑞航空科技（江苏）有限公司 | A kind of plant protection unmanned plane medicinal liquid automatic filling unit |
| CN210484259U (en) * | 2019-05-06 | 2020-05-08 | 沈阳航达机载设备有限公司 | Hydraulic oil supply system capable of being switched in opening and closing mode |
-
2021
- 2021-07-21 CN CN202110826045.4A patent/CN113335550B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3111968A (en) * | 1960-07-11 | 1963-11-26 | Richard T Headrick | Apparatus for transporting fluids |
| US4371096A (en) * | 1979-04-16 | 1983-02-01 | Nordson Corporation | Control apparatus for pressurized gas/liquid systems |
| CN101486381A (en) * | 2009-02-26 | 2009-07-22 | 中国人民解放军空军济南航空四站装备修理厂 | Airplane ground liquid cooling vehicle |
| CN106184809A (en) * | 2016-08-31 | 2016-12-07 | 飞瑞航空科技（江苏）有限公司 | A kind of plant protection unmanned plane medicinal liquid automatic filling unit |
| CN210484259U (en) * | 2019-05-06 | 2020-05-08 | 沈阳航达机载设备有限公司 | Hydraulic oil supply system capable of being switched in opening and closing mode |
Non-Patent Citations (1)
| Title |
|---|
| 航空地面空调液冷综合保障车研制;李旭;吴勇川;胡方亮;雷金果;张永亮;;装甲兵工程学院学报(第05期);全文 * |
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| CN113335550A (en) | 2021-09-03 |
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