CN201566839U - Balancing technique configuration for fuel quantity of multiple aeroplanes - Google Patents
Balancing technique configuration for fuel quantity of multiple aeroplanes Download PDFInfo
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- CN201566839U CN201566839U CN 200920351231 CN200920351231U CN201566839U CN 201566839 U CN201566839 U CN 201566839U CN 200920351231 CN200920351231 CN 200920351231 CN 200920351231 U CN200920351231 U CN 200920351231U CN 201566839 U CN201566839 U CN 201566839U
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Abstract
The utility model relates to a balancing technique configuration for fuel quantity of multiple aeroplanes, including two oil tanks arranged on a left airfoil, two oil tanks arranged on a right airfoil, four oil tanks are connected to four corresponding engines respectively, characterized in that an AC oil transferring pump of each oil tank is connected with the engine through a check valve, an oil quantity balance valve and a fire-proof cock, in addition, the oil transferring pumps connected with the four engines are connected by a pipeline, and fire-proof cocks are arranged there between. Compared with the present technology, the beneficial effects of the utility model are that the utility model has automatic and artificial control modes which is convenient to be operated by pilots; the utility model has guise compensation and is capable of balancing oil quantity automatically by flying attitude; each control signal and oil quantity data presentation is visual and convenient to observe.
Description
Technical field
The utility model is multiple aircraft fuel oil oil mass balancing technique configuration, belongs to the technical field of structures of product, is used for four and sends out between the different corresponding fuel tank groups of aircraft and the oil mass balance between the left and right wing tank group.
Background technology
At present, the manual control that traditional multiple aircraft fuel system oil mass balance adopts is to be made of coupling cock and oil mass balance control switch, it is the oil feed pump of closing the more side fuel tank group of oil mass by manual connection coupling cock and oil mass balance cock, give the principle of work of all engine oils by opposite side wing tank group, reach the oil mass balance, its shortcoming is: the work load that has 1. increased the aviator; 2. balance will be reset oil pump after finishing; 3. do not introduce attitude and temperature compensating; If 4. in equilibrium process, the oil feed pump fault of work can make aircraft fuel system enter the gravity feed state, influences normally finishing of aircraft task.
Summary of the invention
The utility model designs at above-mentioned problems of the prior art just provides a kind of multiple aircraft fuel oil oil mass balancing technique configuration, its objective is to realize between the corresponding fuel tank group of different driving engines or oil mass balanced arrangement between the wing of the left and right sides.
The objective of the invention is to realize by following technical measures:
The configuration of the multiple aircraft fuel oil oil mass of this kind balancing technique, each two fuel tank that comprises left and right wing, four fuel tanks correspondence respectively are connected to four driving engines, it is characterized in that: the interchange fuel transfer pump in each fuel tank passes through check valve, oil mass balance valve, fule shut-off valve and is connected with driving engine, in addition, the oil transportation channel that has a pipeline will connect four driving engines links together, between the fiery switch of setting up defences.
The configuration of multiple aircraft fuel oil oil mass balancing technique mainly by the fuel measurement computing machine, add oil consumption controller, fuel-quantity transducer, temperature sensor, oil mass balance valve, coupling cock, oil pump, pressure signal device and EICAS telltale and constitute.Fuel-quantity transducer and temperature sensor send to the fuel oil temperature measured and oil mass after the fuel measurement computing machine handles, and are demonstrating the un-balance oil amount value between each single fuel tank fuel quantity, each engine oil tank group oil mass, left and right sides wing tank oil mass, the complete total oil mass of machine and adjacent engine oil tank group and the outage of left and right sides wing tank on the EICAS telltale; In addition, send the working state signal of oil pump, oil mass balance valve and coupling cock by pressure signal device and micro-switch and on the EICAS telltale, show.Awing, after oil mass data that fuel measurement computing machine basis collects and flight attitude data are carried out the logic operation judgement, send control command to adding the oil consumption controller, by the mode of operation that adds oil consumption controller automatic guidance oil mass balance valve and coupling cock, realize the function of automatic oil mass balance; If the automatic guidance disabler can also show according to EICAS, control oil mass balance valve and coupling cock by the hand control switch that is provided with on the operating console, realize manual oil mass balance control function.
Description of drawings
Fig. 1 is the structural representation of the utility model device
The specific embodiment
Below with reference to drawings and Examples the utility model is further described:
The configuration of the multiple aircraft fuel oil oil mass of this kind balancing technique, each two fuel tank 7 that comprises left and right wing, four fuel tanks 7 correspondence respectively are connected to four driving engines 8, it is characterized in that: the interchange fuel transfer pump 1 in each fuel tank 7 passes through check valve 3, oil mass balance valve 4, fule shut-off valve 6 and is connected with driving engine 8, in addition, the oil transportation channel that has a pipeline 9 will connect four driving engines 8 links together, between the fiery switch 6 of setting up defences.
Its working process is:
1. measure the oil mass data of each fuel tank group by fuel quantity meas urement system, and send the data to the fuel measurement computing machine;
2. send the aircraft flight attitude data to the fuel measurement computing machine;
3. carry out logic determines after receiving outage and aircraft flight attitude data;
4. if the oil mass equilibrium conditions that satisfies outage and flight attitude simultaneously then to the actuating unit sending controling instruction, is connected coupling cock and oil mass balance valve, realize the oil mass equilibrium function, and after the oil mass balance finishes, disconnect oil mass balance valve and coupling cock; Otherwise do not carry out the oil mass balance.
During four aircraft fuel oil oil masses of this type self-equalizing, aircraft fuel system is in automatic oil consumption mode, when the outage between the corresponding fuel tank group of adjacent driving engine during greater than specified value, the fuel measurement computing machine carries out logic operation according to receiving the flight attitude data, if satisfy the oil mass equilibrium conditions, then send control command to adding the oil consumption controller, automatically connect coupling cock between the less driving engine of oil mass cooresponding oil mass balance valve and the adjacent driving engine by adding the oil consumption controller, begin the fuel oil of the more engine oil tank group of fuel consumption this moment; When outage during less than specified value, the oil mass balance finishes, and disconnects oil mass balance valve, closes coupling cock, recovers the normal fuel injection mode.In like manner, when the outage of left and right wing during greater than specified value, the fuel measurement computing machine carries out logic operation according to the flight attitude data that receive, if satisfy the oil mass equilibrium conditions, then send control command to adding the oil consumption controller, automatically connect two cooresponding oil mass balances of driving engine of the less side wing of oil mass valve and complete three fuel oil coupling cocks of machine by adding the oil consumption controller, begin the fuel oil of the more side wing of fuel consumption this moment; When outage during less than specified value, the oil mass balance finishes, and disconnects oil mass balance valve, closes coupling cock, recovers the normal fuel injection mode.
For example the oil mass of 1 hair oil case group is more than 2, and satisfy the oil mass equilibrium conditions, oil consumption select switch " man-auto " on the operating console is placed on " automatically " position at this moment, the fuel measurement computing machine sends control command to adding the oil consumption controller, the controller automatic guidance is connected " 1-2 " coupling cock 6 and 2 between sending out and is sent out oil mass balance valve 4 cooresponding, oil mass balance between beginning 1 and 2, promptly 1 and 2 consumes 1 fuel oil of sending out the fuel tank group corresponding simultaneously; When satisfying oil mass balance termination condition, the controller automatic guidance disconnects 2 and sends out oil mass balance valve 4 cooresponding, and closes 1-2 " coupling cock 6 between sending out, recover normal fuel injection, the oil mass balance control principle between other adjacent driving engine is the same.If the oil mass of left wing tank group is more than the right wing tank group and satisfy the oil mass equilibrium conditions, oil consumption select switch " man-auto " on the operating console is placed on " automatically " position at this moment, the fuel measurement computing machine sends control command to adding the oil consumption controller, the controller automatic guidance connect " 1-2 ", " L-R ", " 3-4 " between sending out coupling cock 6 and 3 and 4 send out oil mass balance valve 4 cooresponding, begin the oil mass balance between left and right wing fuel tank group, promptly four driving engines consume the fuel oil of the corresponding fuel tank group of two driving engines of left wing simultaneously; When satisfying oil mass balance termination condition, the controller automatic guidance disconnects 3 and 4 sends out oil mass balance valve 4 cooresponding, and closes above-mentioned 3 coupling cocks, the recovery normal fuel injection.
The same automatic guidance of manual control principle.The driving compartment operating console is provided with the cabinet switch of annexes such as fuel oil system oil mass balance valve, coupling cock, oil pump.Show the working signal of each control signal of fuel oil system, grouping fuel tank and total oil mass, outage (un-balance oil amount value), oil mass balance valve and coupling cock on the EICAS fuel oil picture.
At present, be used for four aircraft fuel systems of certain type, through actual use checking, multiple aircraft oil mass balancing technique configuration is advanced, and system operation is simple, dependable performance, and it is vivid, directly perceived to show, and effect is obvious.Therefore, this technical configuration can be at 6,8 even more promote the use of on the multiengined aeroplane.
Beneficial effect
Compared with prior art, the beneficial effects of the utility model are:
1. have automatic and artificial two kinds of control modes, be convenient to pilot operator;
2. have the attitude compensation, automatically carry out the oil mass balance by flight attitude;
3. each control signal and oil mass data show image, directly perceived, are convenient to observe.
Claims (1)
1. multiple aircraft fuel oil oil mass balancing technique configuration, each two fuel tank (7) that comprises left and right wing, four fuel tanks (7) correspondence respectively are connected to four driving engines (8), it is characterized in that: the interchange fuel transfer pump (1) in each fuel tank (7) passes through check valve (3), oil mass balance valve (4), fule shut-off valve (6) and is connected with driving engine (8), in addition, the oil transportation channel that has a pipeline (9) will connect four driving engines (8) links together, between the fiery switch (6) of setting up defences.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200920351231 CN201566839U (en) | 2009-12-30 | 2009-12-30 | Balancing technique configuration for fuel quantity of multiple aeroplanes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200920351231 CN201566839U (en) | 2009-12-30 | 2009-12-30 | Balancing technique configuration for fuel quantity of multiple aeroplanes |
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| CN201566839U true CN201566839U (en) | 2010-09-01 |
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| CN 200920351231 Expired - Fee Related CN201566839U (en) | 2009-12-30 | 2009-12-30 | Balancing technique configuration for fuel quantity of multiple aeroplanes |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104494835A (en) * | 2014-12-04 | 2015-04-08 | 江西洪都航空工业集团有限责任公司 | Balanced oil transportation system of symmetric oil tanks |
| CN105599908A (en) * | 2014-10-28 | 2016-05-25 | 中国航空工业集团公司西安飞机设计研究所 | Universal ventilation system for aircraft wing oil tanks |
| CN106697308A (en) * | 2016-12-15 | 2017-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Fuel oil transferring method for large airplane |
| CN108100227A (en) * | 2017-11-22 | 2018-06-01 | 中国航空工业集团公司西安飞机设计研究所 | A kind of wing tank calculation of pressure method for considering rib and influencing |
| CN109484657A (en) * | 2018-03-16 | 2019-03-19 | 陕西飞机工业（集团）有限公司 | A kind of automatic oil mass balance system of multiengined aeroplane |
| CN111907641A (en) * | 2020-02-25 | 2020-11-10 | 青岛海洋地质研究所 | Method and device for controlling oil tank of multi-hull ship and multi-hull ship |
| CN112816133A (en) * | 2020-12-29 | 2021-05-18 | 中国航空工业集团公司西安飞机设计研究所 | High-safety active gravity center control system and method |
| WO2021118391A1 (en) * | 2019-12-12 | 2021-06-17 | Общество С Ограниченной Ответственностью "Окб Авиарешения" | Multicopter-type pilotless aircraft |
-
2009
- 2009-12-30 CN CN 200920351231 patent/CN201566839U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105599908A (en) * | 2014-10-28 | 2016-05-25 | 中国航空工业集团公司西安飞机设计研究所 | Universal ventilation system for aircraft wing oil tanks |
| CN104494835A (en) * | 2014-12-04 | 2015-04-08 | 江西洪都航空工业集团有限责任公司 | Balanced oil transportation system of symmetric oil tanks |
| CN106697308A (en) * | 2016-12-15 | 2017-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Fuel oil transferring method for large airplane |
| CN108100227A (en) * | 2017-11-22 | 2018-06-01 | 中国航空工业集团公司西安飞机设计研究所 | A kind of wing tank calculation of pressure method for considering rib and influencing |
| CN108100227B (en) * | 2017-11-22 | 2021-01-08 | 中国航空工业集团公司西安飞机设计研究所 | Wing oil tank pressure calculation method considering wing rib influence |
| CN109484657A (en) * | 2018-03-16 | 2019-03-19 | 陕西飞机工业（集团）有限公司 | A kind of automatic oil mass balance system of multiengined aeroplane |
| WO2021118391A1 (en) * | 2019-12-12 | 2021-06-17 | Общество С Ограниченной Ответственностью "Окб Авиарешения" | Multicopter-type pilotless aircraft |
| CN111907641A (en) * | 2020-02-25 | 2020-11-10 | 青岛海洋地质研究所 | Method and device for controlling oil tank of multi-hull ship and multi-hull ship |
| CN112816133A (en) * | 2020-12-29 | 2021-05-18 | 中国航空工业集团公司西安飞机设计研究所 | High-safety active gravity center control system and method |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100901 Termination date: 20181230 |