CN203753416U - Aircraft wing fuel tank pressure refueling control device - Google Patents
Aircraft wing fuel tank pressure refueling control device Download PDFInfo
- Publication number
- CN203753416U CN203753416U CN201420134194.XU CN201420134194U CN203753416U CN 203753416 U CN203753416 U CN 203753416U CN 201420134194 U CN201420134194 U CN 201420134194U CN 203753416 U CN203753416 U CN 203753416U
- Authority
- CN
- China
- Prior art keywords
- master cock
- electromagnetic valve
- back contact
- break back
- indicator lamp
- 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.)
- Expired - Fee Related
Links
Abstract
The utility model belongs to the technology of aircraft wing fuel tank pressure refueling and relates to improvement of an aircraft wing fuel tank pressure refueling control device. The aircraft wing fuel tank pressure refueling control device is characterized in that the second stationary contact K1c of a right control switch K1 is connected in series with a right full tank indicator light (4) and then connected with the closing signal input end (3b) of a right electromagnetic valve (3), and the first stationary contact K1b of the right control switch K1 is in an idle state; the second stationary contact K2c of a left control switch K2 is connected in series with a left full tank indicator light (10) and then connected with the closing signal input end (8b) of a left electromagnetic valve (8), and the first stationary contact K2b of the left control switch K2 is in the idle state. The aircraft wing fuel tank pressure refueling control device can guarantee that, when the right control switch K1 and the left control switch K2 are cut off, the right electromagnetic valve (3) and the left electromagnetic valve (8) can be in a power-off state, so that the potential risk of fuel flushing of a left tank and a right tank can be totally avoided.
Description
Technical field
The utility model belongs to aircraft wing tank pressure and adds oil tech, relates to the improvement to aircraft wing tank pressure refueling control device.
Background technology
The theory structure of current aircraft wing tank pressure filling control setup is referring to Fig. 1.It connects mouth 1 by nearside tank refueling control device, offside tank refueling control device and self-styled oiling and forms.Offside tank refueling control device is comprised of right master cock K1, offside tank 2, right electromagnetic valve 3, right full oily indicator lamp 4 and right oiling indicator lamp 5.Self-styled oiling connects mouth 1 and is communicated with the first import and export 3d of right electromagnetic valve 3 by pipeline, and second of right electromagnetic valve 3 is imported and exported 3e and is communicated with offside tank 2 by pipeline.Right master cock K1 is single-pole triple-throw hand switch, the moving contact K1a of right master cock K1 is connected with aircraft bus-bar 6 by wire, the 3rd break back contact K1d that right master cock K1 is positioned at the left side is connected after right oiling indicator lamp 5 and is connected with the connection signal input end 3c of right electromagnetic valve 3 by wire, the ground terminal ground connection of right electromagnetic valve 3, on control panel, there is " opening " sign the right master cock K1 position that is positioned at the 3rd break back contact K1d on the left side; The second break back contact K1c of right master cock K1 in the middle of being positioned at is vacant, on control panel, there is "off" sign the position of the second break back contact K1c of right master cock K1 in the middle of being positioned at; The first break back contact K1b that right master cock K1 is positioned at the right connect after right full oily indicator lamp 4 and is connected with the closing signal input end 3b of right electromagnetic valve 3 by wire, on control panel, the position of the first break back contact K1b of right master cock K1 on the right of being positioned at has " closing " to identify.Nearside tank refueling control device is comprised of left master cock K2, nearside tank 7, left electromagnetic valve 8, left full oily indicator lamp 9 and left oiling indicator lamp 10.Self-styled oiling connects mouth 1 and is communicated with the first import and export 8d of left electromagnetic valve 8 by pipeline, second of left self-styled electromagnetic valve 8 is imported and exported 8e and is communicated with nearside tank 7 by pipeline, left master cock K2 is single-pole triple-throw hand switch, the moving contact K2a of left master cock K2 is connected with aircraft bus-bar 6 by wire, the 3rd break back contact K2d that left master cock K2 is positioned at the left side is connected after left oiling indicator lamp 9 and is connected with the connection signal input end 8c of left electromagnetic valve 8 by wire, the ground terminal ground connection of left electromagnetic valve 8, on control panel, there is " opening " sign the position that left master cock K2 is positioned at the 3rd break back contact K2d on the left side, the second break back contact K2c of left master cock K2 in the middle of being positioned at is vacant, on control panel, there is "off" sign the position of the second break back contact K2c of left master cock K2 in the middle of being positioned at, the first break back contact K2b that left master cock K2 is positioned at the right connect after left full oily indicator lamp 10 and is connected with the closing signal input end 8b of left electromagnetic valve 8 by wire, on control panel, the position of the first break back contact K2b of left master cock K2 on the right of being positioned at has " closing " to identify.The shortcoming of this device is: the potential faults that has left and right fuel tank string oil.Its reason is: when doing full machine airtight test, operator need to be placed in " opening " position by right master cock K1 and left master cock K2, after test, right master cock K1 and left master cock K2 first must be placed in to " closing " position, and then be placed in " cut-out " position, the right electromagnetic valve 3 of guarantee and left electromagnetic valve 8 are in closed condition, if directly right master cock K1 and left master cock K2 are switched to " cut-out " position from " opening " position, right electromagnetic valve 3 and left electromagnetic valve 8 are likely still in open mode, left and right fuel tank is communicated with, cause the oily fault of string.In addition, if the right master cock K1 of someone maloperation and left master cock K2, after right master cock K1 and left master cock K2 are stirred several times repeatedly, be easy to forget from which direction and toggle it to open position, if toggle it to disconnection from opening, so right electromagnetic valve 3 and left electromagnetic valve 8 just do not closed, and fuel tank will be gone here and there oil.
Summary of the invention
The purpose of this utility model is: propose a kind of improved aircraft wing tank pressure refueling control device, to guarantee when right master cock K1 and left master cock K2 are placed in " cut-out " position, right electromagnetic valve 3 and left electromagnetic valve 8, in closed condition, are stopped the potential faults of left and right fuel tank string oil.
The technical solution of the utility model is: a kind of aircraft wing tank pressure refueling control device, and it connects mouth 1 by nearside tank refueling control device, offside tank refueling control device and self-styled oiling and forms, offside tank refueling control device is by right master cock K1, offside tank 2, right electromagnetic valve 3, right full oily indicator lamp 4 and right oiling indicator lamp 5 form, self-styled oiling connects mouth 1 and is communicated with the first import and export 3d of right electromagnetic valve 3 by pipeline, second of right electromagnetic valve 3 is imported and exported 3e and is communicated with offside tank 2 by pipeline, right master cock K1 is single-pole triple-throw hand switch, the moving contact K1a of right master cock K1 is connected with aircraft bus-bar 6 by wire, the 3rd break back contact K1d that right master cock K1 is positioned at the left side is connected after right oiling indicator lamp 5 and is connected with the connection signal input end 3c of right electromagnetic valve 3 by wire, the ground terminal ground connection of right electromagnetic valve 3, on control panel, there is " opening " sign the position that right master cock K1 is positioned at the 3rd break back contact K1d on the left side, nearside tank refueling control device is by left master cock K2, nearside tank 7, left electromagnetic valve 8, left full oily indicator lamp 9 and left oiling indicator lamp 10 form, self-styled oiling connects mouth 1 and is communicated with the first import and export 8d of left electromagnetic valve 8 by pipeline, second of left self-styled electromagnetic valve 8 is imported and exported 8e and is communicated with nearside tank 7 by pipeline, left master cock K2 is single-pole triple-throw hand switch, the moving contact K2a of left master cock K2 is connected with aircraft bus-bar 6 by wire, the 3rd break back contact K2d that left master cock K2 is positioned at the left side is connected after left oiling indicator lamp 9 and is connected with the connection signal input end 8c of left electromagnetic valve 8 by wire, the ground terminal ground connection of left electromagnetic valve 8, on control panel, there is " opening " sign the position that left master cock K2 is positioned at the 3rd break back contact K2d on the left side, it is characterized in that: the second break back contact K1c in the middle of right master cock K1 is positioned at connects by wire, and right full oily indicator lamp 4 is rear to be connected with the closing signal input end 3b of right electromagnetic valve 3, on control panel, there is " closing " sign the position of the second break back contact K1c of right master cock K1 in the middle of being positioned at, it is vacant that right master cock K1 is positioned at the first break back contact K1b on the right, on control panel, there is "off" sign the right master cock K1 position of the first break back contact K1b that is positioned at the right, the second break back contact K2c in the middle of left master cock K2 is positioned at connects by wire, and left full oily indicator lamp 10 is rear to be connected with the closing signal input end 8b of left electromagnetic valve 8, on control panel, there is " closing " sign the position of the second break back contact K2c of left master cock K2 in the middle of being positioned at, it is vacant that left master cock K2 is positioned at the first break back contact K2b on the right, on control panel, there is "off" sign the left master cock K2 position of the first break back contact K2b that is positioned at the right.
The utility model has the advantages that: proposed a kind of improved aircraft wing tank pressure refueling control device, can guarantee when right master cock K1 and left master cock K2 are placed in " cut-out " position, right electromagnetic valve 3 and left electromagnetic valve 8, in closed condition, have been stopped the potential faults of left and right fuel tank string oil.
Accompanying drawing explanation
Fig. 1.The theory structure schematic diagram of current aircraft wing tank pressure filling control setup.
Fig. 2 is theory structure schematic diagram of the present utility model.
The specific embodiment
Below the utility model is described in further details.Referring to Fig. 2, a kind of aircraft wing tank pressure refueling control device, it connects mouth 1 by nearside tank refueling control device, offside tank refueling control device and self-styled oiling and forms, offside tank refueling control device is by right master cock K1, offside tank 2, right electromagnetic valve 3, right full oily indicator lamp 4 and right oiling indicator lamp 5 form, self-styled oiling connects mouth 1 and is communicated with the first import and export 3d of right electromagnetic valve 3 by pipeline, second of right electromagnetic valve 3 is imported and exported 3e and is communicated with offside tank 2 by pipeline, right master cock K1 is single-pole triple-throw hand switch, the moving contact K1a of right master cock K1 is connected with aircraft bus-bar 6 by wire, the 3rd break back contact K1d that right master cock K1 is positioned at the left side is connected after right oiling indicator lamp 5 and is connected with the connection signal input end 3c of right electromagnetic valve 3 by wire, the ground terminal ground connection of right electromagnetic valve 3, on control panel, there is " opening " sign the position that right master cock K1 is positioned at the 3rd break back contact K1d on the left side, nearside tank refueling control device is by left master cock K2, nearside tank 7, left electromagnetic valve 8, left full oily indicator lamp 9 and left oiling indicator lamp 10 form, self-styled oiling connects mouth 1 and is communicated with the first import and export 8d of left electromagnetic valve 8 by pipeline, second of left self-styled electromagnetic valve 8 is imported and exported 8e and is communicated with nearside tank 7 by pipeline, left master cock K2 is single-pole triple-throw hand switch, the moving contact K2a of left master cock K2 is connected with aircraft bus-bar 6 by wire, the 3rd break back contact K2d that left master cock K2 is positioned at the left side is connected after left oiling indicator lamp 9 and is connected with the connection signal input end 8c of left electromagnetic valve 8 by wire, the ground terminal ground connection of left electromagnetic valve 8, on control panel, there is " opening " sign the position that left master cock K2 is positioned at the 3rd break back contact K2d on the left side, it is characterized in that: the second break back contact K1c in the middle of right master cock K1 is positioned at connects by wire, and right full oily indicator lamp 4 is rear to be connected with the closing signal input end 3b of right electromagnetic valve 3, on control panel, there is " closing " sign the position of the second break back contact K1c of right master cock K1 in the middle of being positioned at, it is vacant that right master cock K1 is positioned at the first break back contact K1b on the right, on control panel, there is "off" sign the right master cock K1 position of the first break back contact K1b that is positioned at the right, the second break back contact K2c in the middle of left master cock K2 is positioned at connects by wire, and left full oily indicator lamp 10 is rear to be connected with the closing signal input end 8b of left electromagnetic valve 8, on control panel, there is " closing " sign the position of the second break back contact K2c of left master cock K2 in the middle of being positioned at, it is vacant that left master cock K2 is positioned at the first break back contact K2b on the right, on control panel, there is "off" sign the left master cock K2 position of the first break back contact K2b that is positioned at the right.
Principle of work of the present utility model is: at present, the control logic of right master cock K1 and left master cock K2 is from left to right " close → disconnect → open ", when the interjacent open position of master cock, cannot guarantee " to open " from the left side and toggle it to "off" or toggle it to "off" left from " the closing " on the right to the right.When master cock, really from the left side, " open " while toggling it to "off" to the right, just there will be the fault of left and right fuel tank string oil.The utility model has changed the wiring order of left master cock K2 and right master cock K1, makes control logic from left to right become " open → close → disconnect ".When master cock is in open position, must process close this position, thereby while having guaranteed that master cock is in open position, right electromagnetic valve 3 and left electromagnetic valve 8, in closed condition, have thoroughly been eliminated the potential faults of left and right fuel tank string oil.
Claims (1)
1. an aircraft wing tank pressure refueling control device, it connects mouth (1) by nearside tank refueling control device, offside tank refueling control device and self-styled oiling and forms, offside tank refueling control device is by right master cock K1, offside tank (2), right electromagnetic valve (3), right full oily indicator lamp (4) and right oiling indicator lamp (5) form, self-styled oiling connects mouth (1) and is communicated with the first import and export (3d) of right electromagnetic valve (3) by pipeline, second of right electromagnetic valve (3) is imported and exported (3e) and is communicated with offside tank (2) by pipeline, right master cock K1 is single-pole triple-throw hand switch, the moving contact K1a of right master cock K1 is connected with aircraft bus-bar (6) by wire, the 3rd break back contact K1d that right master cock K1 is positioned at the left side is connected after right oiling indicator lamp (5) and is connected with the connection signal input end (3c) of right electromagnetic valve (3) by wire, the ground terminal ground connection of right electromagnetic valve (3), on control panel, there is " opening " sign the position that right master cock K1 is positioned at the 3rd break back contact K1d on the left side, nearside tank refueling control device is by left master cock K2, nearside tank (7), left electromagnetic valve (8), left full oily indicator lamp (9) and left oiling indicator lamp (10) form, self-styled oiling connects mouth (1) and is communicated with the first import and export (8d) of left electromagnetic valve (8) by pipeline, second of left self-styled electromagnetic valve (8) is imported and exported (8e) and is communicated with nearside tank (7) by pipeline, left master cock K2 is single-pole triple-throw hand switch, the moving contact K2a of left master cock K2 is connected with aircraft bus-bar (6) by wire, the 3rd break back contact K2d that left master cock K2 is positioned at the left side is connected after left oiling indicator lamp (9) and is connected with the connection signal input end (8c) of left electromagnetic valve (8) by wire, the ground terminal ground connection of left electromagnetic valve (8), on control panel, there is " opening " sign the position that left master cock K2 is positioned at the 3rd break back contact K2d on the left side, it is characterized in that: the second break back contact K1c in the middle of right master cock K1 is positioned at connects by wire, and right full oily indicator lamp (4) is rear to be connected with the closing signal input end (3b) of right electromagnetic valve (3), on control panel, there is " closing " sign the position of the second break back contact K1c of right master cock K1 in the middle of being positioned at, it is vacant that right master cock K1 is positioned at the first break back contact K1b on the right, on control panel, there is "off" sign the right master cock K1 position of the first break back contact K1b that is positioned at the right, the second break back contact K2c in the middle of left master cock K2 is positioned at connects by wire, and left full oily indicator lamp (10) is rear to be connected with the closing signal input end (8b) of left electromagnetic valve (8), on control panel, there is " closing " sign the position of the second break back contact K2c of left master cock K2 in the middle of being positioned at, it is vacant that left master cock K2 is positioned at the first break back contact K2b on the right, on control panel, there is "off" sign the left master cock K2 position of the first break back contact K2b that is positioned at the right.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420134194.XU CN203753416U (en) | 2014-03-24 | 2014-03-24 | Aircraft wing fuel tank pressure refueling control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420134194.XU CN203753416U (en) | 2014-03-24 | 2014-03-24 | Aircraft wing fuel tank pressure refueling control device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203753416U true CN203753416U (en) | 2014-08-06 |
Family
ID=51248718
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420134194.XU Expired - Fee Related CN203753416U (en) | 2014-03-24 | 2014-03-24 | Aircraft wing fuel tank pressure refueling control device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203753416U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105045172A (en) * | 2015-06-29 | 2015-11-11 | 中国航空工业集团公司西安飞机设计研究所 | Switch control circuit, control system possessing same and airplane |
| CN105059555A (en) * | 2015-08-14 | 2015-11-18 | 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 |
-
2014
- 2014-03-24 CN CN201420134194.XU patent/CN203753416U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105045172A (en) * | 2015-06-29 | 2015-11-11 | 中国航空工业集团公司西安飞机设计研究所 | Switch control circuit, control system possessing same and airplane |
| CN105059555A (en) * | 2015-08-14 | 2015-11-18 | 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 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203344750U (en) | High voltage interlocking system of electric vehicle | |
| CN203753416U (en) | Aircraft wing fuel tank pressure refueling control device | |
| CN204678019U (en) | A kind of Lubrication Control System of multiple-channel output | |
| CN104155887B (en) | Multifunctional fault-signal simulating device | |
| CN204065311U (en) | The aobvious device of switch behaviour of monitoring switch control loop template | |
| CN202711060U (en) | Coal mining machine simulation testing stand electric control system | |
| CN202256650U (en) | Multifunctional electric power meter testing desk | |
| CN101787947B (en) | Automobile spray emulator endurance test device | |
| CN202109068U (en) | Valve way control circuit of gas cooker | |
| CN103545910A (en) | Dual-power-supply control circuit | |
| CN203570277U (en) | Oil field well opening liquid flow direction indicating device | |
| CN201561855U (en) | Complete vehicle analogue signal wiring device for experimental platform | |
| CN204024879U (en) | A kind of oil-way system and excavator | |
| CN202600031U (en) | High-voltage line power loss alarm system | |
| CN202948269U (en) | Loosening machine control system | |
| CN203310585U (en) | Hydraulic normally-closed prefill valve testing device | |
| CN202794460U (en) | Hall proximity switch failure detector | |
| CN202850086U (en) | Excavator integrated control unit | |
| CN104345243A (en) | Electrical performance check tester for fuel system | |
| CN206237131U (en) | Battery connection automatic identification device | |
| CN201858417U (en) | Gas valve device | |
| CN105300698A (en) | Method for eliminating ground test start faults of turbofan engine | |
| CN204167216U (en) | The many driving switch of a kind of automobile | |
| CN203859399U (en) | High-voltage power distribution box of hybrid power system | |
| CN203157726U (en) | Automobile double power takeoff interlock circuit structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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: 20140806 Termination date: 20170324 |