CN104494835B - A kind of symmetrical fuel tank equilibrium fuel transfer system - Google Patents
A kind of symmetrical fuel tank equilibrium fuel transfer system Download PDFInfo
- Publication number
- CN104494835B CN104494835B CN201410722797.6A CN201410722797A CN104494835B CN 104494835 B CN104494835 B CN 104494835B CN 201410722797 A CN201410722797 A CN 201410722797A CN 104494835 B CN104494835 B CN 104494835B
- Authority
- CN
- China
- Prior art keywords
- fuel tank
- oil transportation
- oil
- fuel
- selector valve
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Abstract
A kind of symmetrical fuel tank equilibrium fuel transfer system, selects switch, fuel oil to control box, oil transportation selector valve and pipeline road including port wing fuel tank, starboard wing fuel tank, oil transportation；Wherein, port wing fuel tank is provided with left fuel-quantity transducer, starboard wing fuel tank is provided with right fuel-quantity transducer, and port wing fuel tank is connected by pipeline road with starboard wing fuel tank, and on pipeline road, it is provided with oil transportation selector valve, and oil transportation selector valve controls box with fuel oil respectively, electromotor is connected, left fuel-quantity transducer, right fuel-quantity transducer control box with fuel oil and are connected, and oil transportation simultaneously selects switch to be connected with oil transportation selector valve.The present invention selects switch to combine by automatically controlled oil transportation selector valve with manual oil transportation, accurately to realize the alternately oil transportation to port wing fuel tank, starboard wing fuel tank, avoid the occurrence of symmetrical fuel tank and oil transportation uneven phenomenon easily occurs in oil transportation process, it is effectively increased the control and stability of aircraft, extends the service life of aircraft.
Description
Technical field
The present invention relates to aviation machine and control technical field, particularly relate to a kind of symmetrical fuel tank equilibrium fuel transfer system.
Background technology
Fuel tank on aircraft is symmetric, but when flight owing to being affected by oil pump performance difference and air maneuver, easily there is oil transportation uneven phenomenon in oil transportation process in symmetrical fuel tank, and then the control and stability affecting aircraft to even result in aircraft out of control, not only aircraft flight is worked the mischief, and the fuel oil parts of the unbalanced fragile aircraft of oil transportation, in the service life to a certain degree shortening aircraft.Therefore, the oil transportation how realizing symmetrical fuel tank is balanced, and oil mass is accurate, has become as the technical problem that those skilled in the art are urgently to be resolved hurrily.
Summary of the invention
Technical problem solved by the invention is in that to provide a kind of symmetrical fuel tank equilibrium fuel transfer system, to solve the shortcoming in above-mentioned background technology.
Technical problem solved by the invention realizes by the following technical solutions:
A kind of symmetrical fuel tank equilibrium fuel transfer system, selects switch, fuel oil to control box, oil transportation selector valve and pipeline road including port wing fuel tank, starboard wing fuel tank, oil transportation；Wherein, port wing fuel tank is provided with left fuel-quantity transducer, starboard wing fuel tank is provided with right fuel-quantity transducer, and port wing fuel tank is connected by pipeline road with starboard wing fuel tank, and on pipeline road, it is provided with oil transportation selector valve, and oil transportation selector valve controls box with fuel oil respectively, electromotor is connected, left fuel-quantity transducer, right fuel-quantity transducer control box with fuel oil and are connected, and oil transportation simultaneously selects switch to be connected with oil transportation selector valve.
In the present invention, oil transportation selector valve includes rotating toucher, cable socket, erection support, port wing fuel tank inlet, starboard wing fuel tank inlet, oil transportation outlet, switching valve and housing, wherein, rotate toucher and be arranged on housing side, housing bottom is provided with erection support, cable socket is arranged on housing, oil transportation outlet and switching valve it is provided with in the middle of housing, and port wing fuel tank inlet and starboard wing fuel tank inlet are separately positioned on housing two ends, it is used for connecting port wing fuel tank, starboard wing fuel tank.
In the present invention, the switch selecting switch for connecting oil transportation it is provided with in oil transportation selector valve, when aircraft makes automatic control mode lose efficacy because of the system failure, pilot can enter MANUAL CONTROL mode, starts oil transportation and selects on-off control port wing fuel tank and starboard wing fuel tank to replace oil transportation.
In the present invention, it is provided with Zener diode in oil transportation selector valve.
In the present invention, it is additionally provided with temperature sensor in oil transportation selector valve.
In the present invention, it is provided that both of which weighing apparatus oil transportation pattern:
(1) automatic control mode
Aircraft sliding, take off, when landing, fuel oil controls box and sends conversion oil transportation signal to oil transportation selector valve every 12s～17s, the oil transportation selector valve situation of change according to different stitch input positive voltages, drive and rotate the change of the toucher sense of current, and act on switching valve on make it rotate, thus turning on/off the oil circuit of port wing fuel tank inlet, starboard wing fuel tank inlet and oil transportation outlet, it is achieved the alternately oil transportation to port wing fuel tank, starboard wing fuel tank.
Aircraft is when cruising condition, fuel oil controls box and sends conversion oil transportation signal to electronic oil transportation selector valve every 1min～3min, the oil transportation selector valve situation of change according to different stitch input positive voltages, drive and rotate the change of the toucher sense of current, and act on switching valve on make it rotate, thus turning on/off the oil circuit of port wing fuel tank inlet, starboard wing fuel tank inlet and oil transportation outlet, it is achieved the alternately oil transportation to port wing fuel tank, starboard wing fuel tank.
(2) MANUAL CONTROL mode
When aircraft makes automatic control mode lose efficacy because of the system failure, pilot can enter MANUAL CONTROL mode, starts oil transportation and selects on-off control port wing fuel tank, starboard wing fuel tank to carry out alternately oil transportation.
When slight unbalanced state occurs in aircraft, the outage that namely left fuel-quantity transducer, right fuel-quantity transducer are measured reaches 66lbs(30kg) time, fuel oil controls box and sends the unbalanced signal of oil mass, and alarm prompt pilot enters MANUAL CONTROL mode；The oil mass that pilot shows according to instrument, switch is selected by regulation manually operation oil transportation, oil transportation select switch be allocated to " left side " or " right side " position, control the oil circuit of oil transportation selector valve on/off port wing fuel tank inlet, starboard wing fuel tank inlet and oil transportation outlet, until port wing fuel tank, starboard wing fuel tank fuel quantity difference return in prescribed limit.
Beneficial effect: the present invention selects switch to combine by automatically controlled oil transportation selector valve with manual oil transportation, accurately to realize the alternately oil transportation to port wing fuel tank, starboard wing fuel tank, avoid the occurrence of symmetrical fuel tank and oil transportation uneven phenomenon easily occurs in oil transportation process, it is effectively increased the control and stability of aircraft, extends the service life of aircraft.
Accompanying drawing explanation
Fig. 1 is the structural representation of presently preferred embodiments of the present invention.
Fig. 2 is the oil transportation selector valve structural representation in presently preferred embodiments of the present invention.
Fig. 3 is the port wing fuel tank inlet wiring diagram in an open position in presently preferred embodiments of the present invention.
Detailed description of the invention
For the technological means making the present invention realize, creation characteristic, reach purpose and effect and be easy to understand, below in conjunction with being specifically illustrating, the present invention is expanded on further.
Referring to a kind of symmetrical fuel tank equilibrium fuel transfer system of Fig. 1, switch 5, fuel oil is selected to control box 6, oil transportation selector valve 7, electromotor 8 and pipeline road 9 including port wing fuel tank 1, starboard wing fuel tank 2, left fuel-quantity transducer 3, right fuel-quantity transducer 4, oil transportation；Wherein, port wing fuel tank 1 is provided with left fuel-quantity transducer 3, starboard wing fuel tank 2 is provided with right fuel-quantity transducer 4, and port wing fuel tank 1 is connected by pipeline road 9 with starboard wing fuel tank 2, and on pipeline road 9, it is provided with oil transportation selector valve 7, and oil transportation selector valve 7 controls box 6 with fuel oil respectively, electromotor 8 is connected, left fuel-quantity transducer 3 and right fuel-quantity transducer 4 access fuel oil and control box 6, and oil transportation simultaneously selects switch 5 to be connected with oil transportation selector valve 7.
In the present embodiment, oil transportation selector valve 7 includes rotating toucher 10, cable socket 11, erection support 12, port wing fuel tank inlet 13, starboard wing fuel tank inlet 14, oil transportation outlet 15, switching valve 16 and housing 17, shown in Figure 2, rotate toucher 10 and be arranged on housing 17 side, housing bottom is provided with erection support 12, cable socket 11 is arranged on housing 17, oil transportation outlet 15 and switching valve 16 it is provided with in the middle of housing 17, and port wing fuel tank inlet 13 and starboard wing fuel tank inlet 14 are separately positioned on housing 17 two ends, for connecting port wing fuel tank 1, starboard wing fuel tank 2.
In the present embodiment, it is provided that both of which weighing apparatus oil transportation pattern:
(1) automatic control mode
Aircraft sliding, take off, when landing, fuel oil controls box 6 and sends conversion oil transportation signal to oil transportation selector valve 7 every 15s, the oil transportation selector valve 7 situation of change according to different stitch input positive voltages, drive and rotate the change of toucher 10 sense of current, promote the electromagnetic force direction change that solenoid produces, and act on switching valve 16 on make it rotate, thus turning on/off the oil circuit of port wing fuel tank inlet 13, starboard wing fuel tank inlet 14 and oil transportation outlet 15, it is achieved the alternately oil transportation to port wing fuel tank 1, starboard wing fuel tank 2.
Aircraft is when cruising condition, fuel oil controls box 6 and sends conversion oil transportation signal to electronic oil transportation selector valve 7 every 1min, the oil transportation selector valve 7 situation of change according to different stitch input positive voltages, drive and rotate the change of toucher 10 sense of current, promote the electromagnetic force direction change that solenoid produces, and act on switching valve 16 on make it rotate, thus turning on/off the oil circuit of port wing fuel tank inlet 13, starboard wing fuel tank inlet 14 and oil transportation outlet 15, it is achieved the alternately oil transportation to port wing fuel tank 1, starboard wing fuel tank 2.
(2) MANUAL CONTROL mode
When aircraft makes automatic control mode lose efficacy because of the system failure, pilot can enter MANUAL CONTROL mode, starts oil transportation and selects switch 5 control port wing fuel tank 1, starboard wing fuel tank 2 to carry out alternately oil transportation.
When slight unbalanced state occurs in aircraft, namely the outage that left fuel-quantity transducer 3, right fuel-quantity transducer 4 are measured reaches 66lbs(30kg) time, fuel oil controls box 6 and sends the unbalanced signal of oil mass, promote primary attention lamp in passenger cabin that glittering alarm occurs, occurring red text " fuel oil is uneven " alarm in comprehensive warning display box, prompting pilot enters MANUAL CONTROL mode simultaneously；The oil mass that pilot shows according to instrument, switch 5 is selected by regulation manually operation oil transportation, switch 5 is selected to be allocated to " left side " or " right side " position oil transportation, control oil transportation selector valve 7 and turn on/off the oil circuit of port wing fuel tank inlet 13, starboard wing fuel tank inlet 14 and oil transportation outlet 15, until port wing fuel tank 1, starboard wing fuel tank 2 oil mass difference return in prescribed limit.
In the present embodiment, shown in Figure 3, port wing fuel tank inlet 13 is in an open position, rotate toucher 10 in parallel with Zener diode 18, and respectively be used for being connected that oil transportation selects the switch 19 of switch 5, temperature sensor 20 connects, switch 19 is for when aircraft makes automatic control mode lose efficacy because of the system failure, and pilot can enter MANUAL CONTROL mode, starts oil transportation and selects switch 5 control port wing fuel tank 1 and starboard wing fuel tank 2 alternately oil transportation；Oil transportation selector valve 7 working method is as follows:
When stitch 1 passes into positive voltage, port wing fuel tank inlet 13 and oil transportation outlet 15 connection, starboard wing fuel tank inlet 14 and oil transportation outlet 15 cut-out, fuel oil flows to oil transportation outlet 15 from port wing fuel tank inlet 13, and stitch 7 exports the position signalling that port wing fuel tank inlet 13 is connected；When stitch 3 passes into positive voltage, starboard wing fuel tank inlet 14 and oil transportation outlet 15 connection, port wing fuel tank inlet 13 and oil transportation outlet 15 cut-out, fuel oil flows to oil transportation outlet 15 from starboard wing fuel tank inlet 14, stitch 9 exports the position signalling that starboard wing fuel tank inlet 14 is connected, thus equilibrium completes fuel tank oil transportation；Stitch 8 output outlet indication signal.
The ultimate principle of the present invention and principal character and advantages of the present invention have more than been shown and described.Skilled person will appreciate that of the industry; the present invention is not restricted to the described embodiments; described in above-described embodiment and description is that principles of the invention is described; without departing from the spirit and scope of the present invention; the present invention also has various changes and modifications, and these changes and improvements both fall within the claimed scope of the invention.Claimed scope is defined by appending claims and equivalent thereof.
Claims (5)
1. a symmetrical fuel tank equilibrium fuel transfer system, selects switch, fuel oil to control box, oil transportation selector valve and pipeline road including port wing fuel tank, starboard wing fuel tank, oil transportation；It is characterized in that, port wing fuel tank is provided with left fuel-quantity transducer, starboard wing fuel tank is provided with right fuel-quantity transducer, and port wing fuel tank is connected by pipeline road with starboard wing fuel tank, and on pipeline road, it is provided with oil transportation selector valve, and oil transportation selector valve controls box with fuel oil respectively, electromotor is connected, left fuel-quantity transducer, right fuel-quantity transducer control box with fuel oil and are connected, and oil transportation simultaneously selects switch to be connected with oil transportation selector valve；Oil transportation selector valve includes rotating toucher, cable socket, erection support, port wing fuel tank inlet, starboard wing fuel tank inlet, oil transportation outlet, switching valve and housing, wherein, rotate toucher and be arranged on housing side, housing bottom is provided with erection support, cable socket is arranged on housing, it is provided with oil transportation outlet and switching valve in the middle of housing, and port wing fuel tank inlet and starboard wing fuel tank inlet are separately positioned on housing two ends.
2. a kind of symmetrical fuel tank equilibrium fuel transfer system according to claim 1, it is characterised in that be provided with the switch selecting switch for connecting oil transportation in oil transportation selector valve.
3. a kind of symmetrical fuel tank equilibrium fuel transfer system according to claim 1, it is characterised in that be provided with Zener diode in oil transportation selector valve.
4. a kind of symmetrical fuel tank equilibrium fuel transfer system according to claim 1, it is characterised in that be additionally provided with temperature sensor in oil transportation selector valve.
5. a kind of symmetrical fuel tank equilibrium fuel transfer system according to claim 1, it is characterised in that provide both of which weighing apparatus oil transportation pattern specific as follows:
(1) automatic control mode
Aircraft sliding, take off, when landing, fuel oil controls box and sends conversion oil transportation signal to oil transportation selector valve every 12s～17s, the oil transportation selector valve situation of change according to different stitch input positive voltages, drive and rotate the change of the toucher sense of current, and act on switching valve on make it rotate, thus turning on/off the oil circuit of port wing fuel tank inlet, starboard wing fuel tank inlet and oil transportation outlet, it is achieved the alternately oil transportation to port wing fuel tank, starboard wing fuel tank；
Aircraft is when cruising condition, fuel oil controls box and sends conversion oil transportation signal to electronic oil transportation selector valve every 1min～3min, the oil transportation selector valve situation of change according to different stitch input positive voltages, drive and rotate the change of the toucher sense of current, and act on switching valve on make it rotate, thus turning on/off the oil circuit of port wing fuel tank inlet, starboard wing fuel tank inlet and oil transportation outlet, it is achieved the alternately oil transportation to port wing fuel tank, starboard wing fuel tank；
(2) MANUAL CONTROL mode
When aircraft makes automatic control mode lose efficacy because of the system failure, pilot can enter MANUAL CONTROL mode, starts oil transportation and selects on-off control port wing fuel tank, starboard wing fuel tank to carry out alternately oil transportation；
When slight unbalanced state occurs in aircraft, when the outage that namely left fuel-quantity transducer, right fuel-quantity transducer are measured reaches 66lbs, fuel oil controls box and sends the unbalanced signal of oil mass, and alarm prompt pilot enters MANUAL CONTROL mode；The oil mass that pilot shows according to instrument, switch is selected by regulation manually operation oil transportation, stir oil transportation and select switch, control the oil circuit of oil transportation selector valve on/off port wing fuel tank inlet, starboard wing fuel tank inlet and oil transportation outlet, until port wing fuel tank, starboard wing fuel tank fuel quantity difference return in prescribed limit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410722797.6A CN104494835B (en) | 2014-12-04 | 2014-12-04 | A kind of symmetrical fuel tank equilibrium fuel transfer system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410722797.6A CN104494835B (en) | 2014-12-04 | 2014-12-04 | A kind of symmetrical fuel tank equilibrium fuel transfer system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104494835A CN104494835A (en) | 2015-04-08 |
| CN104494835B true CN104494835B (en) | 2016-06-29 |
Family
ID=52936321
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410722797.6A Active CN104494835B (en) | 2014-12-04 | 2014-12-04 | A kind of symmetrical fuel tank equilibrium fuel transfer system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104494835B (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105059555B (en) * | 2015-08-14 | 2017-04-19 | 中国航空工业集团公司西安飞机设计研究所 | Oil tank assembly oil leading devices and airplane with same |
| CN106741982B (en) * | 2015-11-24 | 2019-10-25 | 中航贵州飞机有限责任公司 | Fuselage fuel cell fuel delivery device |
| 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 |
| CN109808901A (en) * | 2019-01-28 | 2019-05-28 | 陕西智翔航空科技发展有限公司 | Aircraft oil channel structures |
| CN111137462A (en) * | 2019-12-30 | 2020-05-12 | 航天时代飞鸿技术有限公司 | Large-scale freight unmanned aerial vehicle fuel system and control method thereof |
| CN112208779B (en) * | 2020-10-10 | 2023-06-02 | 江西洪都航空工业集团有限责任公司 | Dual-redundancy aircraft fuel oil allowance measurement system |
| CN112644721B (en) * | 2020-12-23 | 2022-06-03 | 河北利翔航空科技有限公司 | Aircraft oil supply and delivery system and control method thereof |
| CN112550738A (en) * | 2020-12-25 | 2021-03-26 | 武汉航空仪表有限责任公司 | Pressure-regulated proportional oil delivery system and method |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0518576D0 (en) * | 2005-09-12 | 2005-10-19 | Airbus Uk Ltd | Improvements in and relating to aircraft wings and fuel tanks |
| CN201566839U (en) * | 2009-12-30 | 2010-09-01 | 陕西飞机工业（集团）有限公司 | Balancing technique configuration for fuel quantity of multiple aeroplanes |
| CN201696152U (en) * | 2010-04-09 | 2011-01-05 | 江西洪都航空工业集团有限责任公司 | Airplane fuel proportional oil-wasted control system |
| US8381779B1 (en) * | 2011-10-11 | 2013-02-26 | General Electric Company | System for wireless refueling of an aircraft |
-
2014
- 2014-12-04 CN CN201410722797.6A patent/CN104494835B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN104494835A (en) | 2015-04-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104494835B (en) | A kind of symmetrical fuel tank equilibrium fuel transfer system | |
| CN101916108B (en) | Automation device for use in civil aircraft environment control system function test | |
| CN103038133A (en) | A refuel control system and method of refuelling | |
| CN201566839U (en) | Balancing technique configuration for fuel quantity of multiple aeroplanes | |
| JP5061247B2 (en) | Test equipment for testing additional central tank (ACT) systems in aircraft | |
| CN202057493U (en) | Oil source apparatus for detection of fuel oil system of engine | |
| CN105588693A (en) | Bleed air duct leak system real-time fault detection | |
| CN103226367B (en) | Airspeed head heating system | |
| CN109253131A (en) | Governor valve test macro and test method | |
| CN203705175U (en) | Oil supply device for test and fuel oil test system with oil supply device | |
| CN205103014U (en) | A detection circuitry for flow control valve among aircraft environmental control system | |
| CN103076067A (en) | Full-automatic online calibrating device and calibrating method for vehicle-mounted large-aperture flow meter and calibrating method | |
| CN214471509U (en) | Impact endurance test circuit, device and test box of pressure sensor | |
| CN201696152U (en) | Airplane fuel proportional oil-wasted control system | |
| CN202358844U (en) | Liquid control handle of crane and crane | |
| CN205446096U (en) | Electron fan with rotational speed instruction function | |
| CN109969410A (en) | A kind of fuel tanker oil controller | |
| CN208026461U (en) | A kind of governor test system | |
| CN207297917U (en) | A kind of adjustable hydraulic pressure valve arrangement | |
| CN203111511U (en) | Cabin flow control device under different back pressure structures | |
| CN202126902U (en) | Resistance device with adjustable digital quantity | |
| CN112078807A (en) | Control system and method for reversing solenoid valve of aircraft fuel system | |
| CN105000189A (en) | Spilled oil recovery system for ventilation tank of large aircraft inverted dihedral wing fuel system | |
| CN209123366U (en) | Paste the dry production system of resin | |
| CN108082532A (en) | A kind of type aircraft pneumatic element integrated test system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170516 Address after: 330024 South flying point, hi tech Industrial Development Zone, Jiangxi, Nanchang Patentee after: Jiangxi Hongdu Aviation Industry Limited by Share Ltd Address before: 330000 Jiangxi city in Nanchang Province, the new bridge box 460 box 5001 Patentee before: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. |