CN104527987A - Airplane main oil tank pressure-maintaining vent system - Google Patents
Airplane main oil tank pressure-maintaining vent system Download PDFInfo
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- CN104527987A CN104527987A CN201510009220.5A CN201510009220A CN104527987A CN 104527987 A CN104527987 A CN 104527987A CN 201510009220 A CN201510009220 A CN 201510009220A CN 104527987 A CN104527987 A CN 104527987A
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Abstract
The invention belongs to airplane fuel oil supply technologies, and relates to improvement of an airplane main oil tank pressure-maintaining vent system. The improved airplane main oil tank pressure-maintaining vent system is characterized in that a left ventilation connecting nozzle connecting pipe (2), a first communication pipe (3), a four-way part (23) and a static pressure transducer (24) are arranged in a main oil tank connecting nozzle communication pipeline, and an electromagnetic valve (11), a second ventilation pipe (16), a second tee joint (17), a fifth hoop (18), a third hose (19), a sixth hoop (20), a third ventilation pipe (21), a vacuum valve (22), a fourth ventilation pipe (25) and a vent hole (26) are arranged in a ventilation pipeline. By means of the improved airplane main oil tank pressure-maintaining vent system, the high-altitude oil supply performance of an oil tank is improved, and the ceiling of an airplane is further improved.
Description
Technical field
The invention belongs to aircraft fuel oil supply technology, relate to the improvement to aircraft main oil tank blow and vent system.
Background technology
Aircraft main oil tank fuel oil blow and vent system makes fuel tanker be communicated with air, and when in fuel tank, fuel oil is consumed, blow and vent system supplements air in trend fuel tank, prevents producing negative pressure in fuel tank and is taken out flat, ensures that fuel charger can from fuel tank oil suction, to driving engine continuous oil supply.In fuel oil blow and vent system, fuel tank ventilating joint is used for fuel tank and is connected with vent line, is arranged on fuel tank vertex when aircraft cruises as far as possible.Fuel tank ventilating joint, can have multiple, and each joint is communicated with tank vent, at fuel tank with under the various attitudes vibration of aircraft, fuel tank can be made to have at least a ventilating joint to be communicated with ambient atmosphere by vent.Aircraft vent is positioned at the end of vent line, and be installed on inside aircraft skin, mouth communicates with air outwardly.The vent line be connected with aircraft vent should, higher than vent, prevent rainwater from entering vent line.Vent is provided with ventilation barrier, and air grid is made up of boring aluminium sheet, and the size in hole should be able to stop larger dirt to enter vent line, and on air grid, effective ventilation area should ensure that fuel oil system normally works.The structure of the main oil tank pressurize blow and vent system of certain type unmanned plane existing is see Fig. 1, it connects mouth connecting pipeline by main oil tank and vent line forms, and main oil tank connects that mouth connecting pipeline connects mouth 1 by left ventilation, left ventilation connects clip 4, first flexible pipe 5, second clip 6, second communicating pipe 7 mouth communicating pipe 28, first, right ventilation connects mouth connection pipe 8, right ventilation connects mouth 9 and the first threeway 10 forms.The right-hand member that left ventilation connects mouth communicating pipe 28 connects mouth 1 with left ventilation and is communicated with, the left end that left ventilation connects mouth communicating pipe 28 is communicated with by the right-hand member of the first clip 4 with the first flexible pipe 5, the left end of the first flexible pipe 5 is communicated with the right-hand member of the second communicating pipe 7 by the second clip 6, the left end of the second communicating pipe 7 is communicated with the 3rd port one 0c of the first threeway 10, right ventilation connects mouth 9 and is communicated with the lower end that right ventilation connects mouth connection pipe 8, and the first port 10a of upper end and the first threeway 10 that right ventilation connects mouth connection pipe 8 is communicated with.Vent line is made up of the first breather pipe 12, the 3rd clip 13, second flexible pipe 14, the 4th clip 15, vent connection pipe 27 and the vent 26 be fixed on aircraft skin.The left end of the first breather pipe 12 is communicated with the second port one 0b of the first threeway 10, the right-hand member of the first breather pipe 12 is communicated with the left end of the second flexible pipe 14 by the 3rd clip 13, and the right-hand member of the second flexible pipe 14 is communicated with the left end of vent connection pipe 27 by the 4th clip 15.The shortcoming of this structure is: fuel tank is directly communicated with ambient atmosphere, to fuel tank pressurize, can not make high-altitude oil supply performance restriction, cause the flying height of aircraft limited, be generally no more than 7500m.
Summary of the invention
The object of the invention is: the aircraft main oil tank pressurize blow and vent system proposing a kind of improvement, to improve the high-altitude oil supply performance of fuel tank, and then improve the ceiling of aircraft.
Technical scheme of the present invention is: a kind of aircraft main oil tank pressurize blow and vent system, connect mouth connecting pipeline by main oil tank and vent line forms, main oil tank connects mouth connecting pipeline and comprises that left ventilation connects mouth 1, first clip 4, first flexible pipe 5, second 6, second communicating pipe 7 of hoop, right ventilation connects mouth connection pipe 8, right ventilation connects mouth 9 and the first threeway 10; The left end of the first flexible pipe 5 is communicated with the right-hand member of the second communicating pipe 7 by the second clip 6, the left end of the second communicating pipe 7 is communicated with the 3rd port one 0c of the first threeway 10, right ventilation connects mouth 9 and is communicated with the lower end that right ventilation connects mouth connection pipe 8, and the first port 10a of upper end and the first threeway 10 that right ventilation connects mouth connection pipe 8 is communicated with; The right-hand member that vent line comprises the first breather pipe 12, the 3rd clip 13, second flexible pipe 14, the 4th clip 15 and is fixed on vent 26, first breather pipe 12 on aircraft skin is communicated with the left end of the second flexible pipe 14 by the 3rd clip 13; It is characterized in that:
Main oil tank connects in mouth connecting pipeline also has left ventilation to connect mouth connection pipe 2, first communicating pipe 3, a four-way 23 and static pressure transducer 24, the lower end that left ventilation connects mouth connection pipe 2 connects mouth 1 with left ventilation and is communicated with, first port 23a of upper end and four-way 23 that left ventilation connects mouth connection pipe 2 is communicated with, the right-hand member of the first communicating pipe 3 is communicated with the second port 23b of four-way 23, the left end of the first communicating pipe 3 is communicated with the right-hand member of the first flexible pipe 5 by the first clip 4, and the 4th port 23d of four-way 23 is communicated with the pressure-sensitive mouth of static pressure transducer 24;
The threeway 17 of electromagnetic valve 11, second breather pipe 16, second, the 5th clip 18, the 3rd flexible pipe 19, the 6th clip 20, the 3rd breather pipe 21, vacuum valve 22, the 4th breather pipe 25 and vent 26 is also had in vent line, second port one 0b of the first threeway 10 is communicated with the first port of electromagnetic valve 11, second port of electromagnetic valve 11 is communicated with the left end of the first breather pipe 12, the right-hand member of the second flexible pipe 14 is communicated with the left end of the second breather pipe 16 by the 4th clip 15, the right-hand member of the second breather pipe 16 is communicated with the first port 17a of the second threeway 17, second port one 7b of the second threeway 17 is communicated with the left end of the 4th breather pipe 25, the right-hand member of the 4th breather pipe 25 is communicated with vent 26, 3rd port one 7c of the second threeway 17 is communicated with the upper end of the 3rd flexible pipe 19 by the 5th clip 18, the lower end of the 3rd flexible pipe 19 is communicated with the left end of the 3rd breather pipe 21 by the 6th clip 20, the right-hand member of the 3rd breather pipe 21 is communicated with the admission port of vacuum valve 22, the air extractor duct of vacuum valve 22 is communicated with the 3rd port 23c of four-way 23.
Advantage of the present invention is: the aircraft main oil tank pressurize blow and vent system proposing a kind of improvement, improves the high-altitude oil supply performance of fuel tank, and then improve the ceiling of aircraft.One embodiment of the present of invention, prove through test, solve a high-level performance difficult problem for unmanned plane open type fuel tank vent system fuel feeding more than 7600 meters, namely in fuel tank natural aspirate situation, utilize fuel oil pressurize blow and vent system, airplane ceiling can be brought up to more than 8200 meters.
Accompanying drawing explanation
Fig. 1 is the structural representation of the main oil tank pressurize blow and vent system of certain type unmanned plane existing.
Fig. 2 is structural representation of the present invention.
Detailed description of the invention
Below the present invention is described in further details.See Fig. 2, a kind of aircraft main oil tank pressurize blow and vent system, connect mouth connecting pipeline by main oil tank and vent line forms, main oil tank connects mouth connecting pipeline and comprises that left ventilation connects mouth 1, first clip 4, first flexible pipe 5, second 6, second communicating pipe 7 of hoop, right ventilation connects mouth connection pipe 8, right ventilation connects mouth 9 and the first threeway 10; The left end of the first flexible pipe 5 is communicated with the right-hand member of the second communicating pipe 7 by the second clip 6, the left end of the second communicating pipe 7 is communicated with the 3rd port one 0c of the first threeway 10, right ventilation connects mouth 9 and is communicated with the lower end that right ventilation connects mouth connection pipe 8, and the first port 10a of upper end and the first threeway 10 that right ventilation connects mouth connection pipe 8 is communicated with; The right-hand member that vent line comprises the first breather pipe 12, the 3rd clip 13, second flexible pipe 14, the 4th clip 15 and is fixed on vent 26, first breather pipe 12 on aircraft skin is communicated with the left end of the second flexible pipe 14 by the 3rd clip 13; It is characterized in that:
Main oil tank connects in mouth connecting pipeline also has left ventilation to connect mouth connection pipe 2, first communicating pipe 3, a four-way 23 and static pressure transducer 24, the lower end that left ventilation connects mouth connection pipe 2 connects mouth 1 with left ventilation and is communicated with, first port 23a of upper end and four-way 23 that left ventilation connects mouth connection pipe 2 is communicated with, the right-hand member of the first communicating pipe 3 is communicated with the second port 23b of four-way 23, the left end of the first communicating pipe 3 is communicated with the right-hand member of the first flexible pipe 5 by the first clip 4, and the 4th port 23d of four-way 23 is communicated with the pressure-sensitive mouth of static pressure transducer 24;
The threeway 17 of electromagnetic valve 11, second breather pipe 16, second, the 5th clip 18, the 3rd flexible pipe 19, the 6th clip 20, the 3rd breather pipe 21, vacuum valve 22, the 4th breather pipe 25 and vent 26 is also had in vent line, second port one 0b of the first threeway 10 is communicated with the first port of electromagnetic valve 11, second port of electromagnetic valve 11 is communicated with the left end of the first breather pipe 12, the right-hand member of the second flexible pipe 14 is communicated with the left end of the second breather pipe 16 by the 4th clip 15, the right-hand member of the second breather pipe 16 is communicated with the first port 17a of the second threeway 17, second port one 7b of the second threeway 17 is communicated with the left end of the 4th breather pipe 25, the right-hand member of the 4th breather pipe 25 is communicated with vent 26, 3rd port one 7c of the second threeway 17 is communicated with the upper end of the 3rd flexible pipe 19 by the 5th clip 18, the lower end of the 3rd flexible pipe 19 is communicated with the left end of the 3rd breather pipe 21 by the 6th clip 20, the right-hand member of the 3rd breather pipe 21 is communicated with the admission port of vacuum valve 22, the air extractor duct of vacuum valve 22 is communicated with the 3rd port 23c of four-way 23.
Principle of work of the present invention is: aircraft reaches normal ceiling, and flight a period of time fuel oil consumption is to after a certain amount of, and now to account for whole fuel tanker volume comparatively large in tank-level upper air space, and engine operation oil consumption is little, and fuel tank internal gas pressure declines slow.When aircraft flies to the usual ceiling of 7600m, close vent line by electromagnetic valve 11, make fuel tank and atmospheric isolation, now, fuel oil system can not affect by external atmospheric pressure, continues normally to work a period of time.During this period of time, aircraft can continue to climb from normal ceiling.
One embodiment of the present of invention, the electromagnetic valve of employing, static pressure transducer and vacuum valve are goods shelf products.This embodiment is tested on certain type unmanned plane, and airplane ceiling brings up to more than 8200 meters from 7600 meters.
Claims (1)
1. an aircraft main oil tank pressurize blow and vent system, connect mouth connecting pipeline by main oil tank and vent line forms, main oil tank connects mouth connecting pipeline and comprises that left ventilation connects mouth (1), the first clip (4), the first flexible pipe (5), the second hoop (6), the second communicating pipe (7), right ventilation connects mouth connection pipe (8), right ventilation connects mouth (9) and the first threeway (10); The left end of the first flexible pipe (5) is communicated with the right-hand member of the second communicating pipe (7) by the second clip (6), the left end of the second communicating pipe (7) is communicated with the 3rd port (10c) of the first threeway (10), right ventilation connects mouth (9) and is communicated with the lower end that right ventilation connects mouth connection pipe (8), and first port (10a) of upper end and the first threeway (10) that right ventilation connects mouth connection pipe (8) is communicated with; The vent (26) that vent line comprises the first breather pipe (12), the 3rd clip (13), the second flexible pipe (14), the 4th clip (15) and is fixed on aircraft skin, the right-hand member of the first breather pipe (12) is communicated with the left end of the second flexible pipe (14) by the 3rd clip (13); It is characterized in that:
Main oil tank connects in mouth connecting pipeline also has left ventilation to connect mouth connection pipe (2), first communicating pipe (3), a four-way (23) and a static pressure transducer (24), the lower end that left ventilation connects mouth connection pipe (2) connects mouth (1) with left ventilation and is communicated with, first port (23a) of upper end and four-way (23) that left ventilation connects mouth connection pipe (2) is communicated with, the right-hand member of the first communicating pipe (3) is communicated with second port (23b) of four-way (23), the left end of the first communicating pipe (3) is communicated with the right-hand member of the first flexible pipe (5) by the first clip (4), 4th port (23d) of four-way (23) is communicated with the pressure-sensitive mouth of static pressure transducer (24),
Electromagnetic valve (11), the second breather pipe (16), the second threeway (17), the 5th clip (18), the 3rd flexible pipe (19), the 6th clip (20), the 3rd breather pipe (21), vacuum valve (22), the 4th breather pipe (25) and vent (26) is also had in vent line; second port (10b) of the first threeway (10) is communicated with the first port of electromagnetic valve (11), second port of electromagnetic valve (11) is communicated with the left end of the first breather pipe (12), the right-hand member of the second flexible pipe (14) is communicated with the left end of the second breather pipe (16) by the 4th clip (15), the right-hand member of the second breather pipe (16) is communicated with first port (17a) of the second threeway (17), second port (17b) of the second threeway (17) is communicated with the left end of the 4th breather pipe (25), the right-hand member of the 4th breather pipe (25) is communicated with vent (26), 3rd port (17c) of the second threeway (17) is communicated with by the upper end of the 5th clip (18) with the 3rd flexible pipe (19), the lower end of the 3rd flexible pipe (19) is communicated with the left end of the 3rd breather pipe (21) by the 6th clip (20), the right-hand member of the 3rd breather pipe (21) is communicated with the admission port of vacuum valve (22), the air extractor duct of vacuum valve (22) is communicated with the 3rd port (23c) of four-way (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510009220.5A CN104527987B (en) | 2015-01-07 | 2015-01-07 | A kind of aircraft main fuel tank pressurize aerating system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510009220.5A CN104527987B (en) | 2015-01-07 | 2015-01-07 | A kind of aircraft main fuel tank pressurize aerating system |
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| CN104527987A true CN104527987A (en) | 2015-04-22 |
| CN104527987B CN104527987B (en) | 2016-06-22 |
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| CN201510009220.5A Active CN104527987B (en) | 2015-01-07 | 2015-01-07 | A kind of aircraft main fuel tank pressurize aerating system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107745826A (en) * | 2017-09-12 | 2018-03-02 | 陕西飞机工业（集团）有限公司 | The more fuel tank vent system string oil test measuring methods of aircraft |
| EP3960635A1 (en) | 2020-08-31 | 2022-03-02 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | An aircraft with a fuel storage system |
| CN116353836A (en) * | 2023-04-19 | 2023-06-30 | 南京儒一航空机械装备有限公司 | Pressure maintaining oil tank for aircraft |
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| JPH11268695A (en) * | 1998-03-23 | 1999-10-05 | Tech Res & Dev Inst Of Japan Def Agency | Liquid fuel tank for navigation body |
| CN201086827Y (en) * | 2007-08-03 | 2008-07-16 | 西安大地测绘工程有限责任公司 | Anti-bubble fuel tank |
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| US20120025026A1 (en) * | 2010-07-29 | 2012-02-02 | Airbus Operations Limited | Venting gas from a tank |
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Patent Citations (5)
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| JPH11268695A (en) * | 1998-03-23 | 1999-10-05 | Tech Res & Dev Inst Of Japan Def Agency | Liquid fuel tank for navigation body |
| CN201086827Y (en) * | 2007-08-03 | 2008-07-16 | 西安大地测绘工程有限责任公司 | Anti-bubble fuel tank |
| CN101870365A (en) * | 2010-05-13 | 2010-10-27 | 哈尔滨飞机工业集团有限责任公司 | Pilot control overflowing system for airplane pressure fuel filling |
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Non-Patent Citations (1)
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107745826A (en) * | 2017-09-12 | 2018-03-02 | 陕西飞机工业（集团）有限公司 | The more fuel tank vent system string oil test measuring methods of aircraft |
| EP3960635A1 (en) | 2020-08-31 | 2022-03-02 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | An aircraft with a fuel storage system |
| EP3964444A1 (en) | 2020-08-31 | 2022-03-09 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | An aircraft with a fuel storage system |
| CN116353836A (en) * | 2023-04-19 | 2023-06-30 | 南京儒一航空机械装备有限公司 | Pressure maintaining oil tank for aircraft |
| CN116353836B (en) * | 2023-04-19 | 2023-09-29 | 南京儒一航空机械装备有限公司 | Pressure maintaining oil tank for aircraft |
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| CN104527987B (en) | 2016-06-22 |
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