CN204301824U - A kind of aircraft oil scale in situ detection device - Google Patents
A kind of aircraft oil scale in situ detection device Download PDFInfo
- Publication number
- CN204301824U CN204301824U CN201520008806.5U CN201520008806U CN204301824U CN 204301824 U CN204301824 U CN 204301824U CN 201520008806 U CN201520008806 U CN 201520008806U CN 204301824 U CN204301824 U CN 204301824U
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- oil
- stop valve
- aircraft
- detection device
- car body
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Abstract
A kind of aircraft oil scale in situ detection device, it relates to a kind of fuel level gauge checkout gear.The purpose of this utility model can only dismantle oil meter detect to solve aircraft oil scale detection check of the prior art, detects data comprehensive, the problem that detection efficiency is low.Measurement Trunk Line one end of the present utility model connects oil filler, the other end connects oil-out, measure on Trunk Line and the first stop valve is installed successively, second stop valve, temperature sensor, hydraulic pump, main filter, pressure sensor and flowmeter, the first measurement looped pipeline line is connected between the output of oil filler and the second stop valve, first measures looped pipeline line is provided with the 3rd stop valve, be connected to the second measurement looped pipeline line between the output of the second stop valve and the input of main filter, second measures looped pipeline line is provided with the 4th stop valve.The utility model achieves and can detect without the need to dismounting the function that aircraft fuel system instrument just can reach measurement object.
Description
Technical field
The utility model relates to fuel level gauge checkout gear, is specifically related to a kind of aircraft oil scale in situ detection device, belongs to Fuel On Board fuel level gauge detection technique field.
Background technology
The Fuel On Board fuel level gauge of current domestic air mail circle does not have special original position calibration equipment, and fuel level gauge pointing accuracy mainly relies on the output quantity of ground refueling equipment to contrast.Because fuel tank is not regular shape, fuel-quantity transducer and indicator directly can not do the degree of accuracy verification of oil mass instruction during operation, generally only do electric property (electric current, resistance and inductance or electric capacity) and detect.For checking that Fuel Oil Remaining indicates whether accurately, and minimum oily plane emergency warning lamp, the highest oily plane emergency warning lamp whether accurately ignite, the verification of original position oil mass must be carried out.Especially, after replacing fuel tank, sensor or fuel level gauge, must verify the accuracy of fuel level gauge instruction.And oil meter must be dismantled during prior art detection check, just can carry out.
Summary of the invention
The purpose of this utility model can only dismantle oil meter detect to solve aircraft oil scale detection check of the prior art, detects data comprehensive, the problem that detection efficiency is low.
The technical solution of the utility model is: a kind of aircraft oil scale in situ detection device, comprise oil filler, measure working connection pipe, data processing section, control panel and oil-out, described data processing section comprises PLC control chip, control panel comprises touch display screen, described measurement working connection pipe one end connects oil filler, the other end connects oil-out, measure on working connection pipe and the first stop valve is installed successively, second stop valve, temperature sensor, hydraulic pump, main filter, pressure sensor and flowmeter, the first measurement auxiliary oil circuit pipe is connected between the output of described oil filler and the second stop valve, first measures auxiliary oil circuit pipe is provided with the 3rd stop valve, the second measurement auxiliary oil circuit pipe is connected between the output of the second stop valve and the input of main filter, second measures auxiliary oil circuit pipe is provided with the 4th stop valve, the data output end of described temperature sensor, pressure sensor and flowmeter connects with the data receiver of the PLC control chip of data processing section respectively, control output end connecting fluid press pump, the first stop valve, the second stop valve, the 3rd stop valve and the 4th stop valve respectively of PLC control chip, PLC control chip is set up bi-directional data with control panel by data bus connection and is connected.
Be provided with secondary filter between described first stop valve and the second stop valve, prefiltration can be carried out by the fuel oil in oil-way pipe, preventing from impacting testing result because having impurity in fuel oil.
Be provided with memory cell in described touch display screen, buffer memory can be carried out to data, make man-machine interaction more smooth.
Described aircraft oil meter original position calibration equipment is placed in car body, described car body upper end is provided with top cover and manipulation case, the sidewall of car body is provided with side door, the rear end of car body is provided with pushing hands, the lower end of car body is provided with wheel and oil-out, the side of described top cover is provided with side cover, side cover is connected by folding and top cover, the upper end of top cover is provided with oil-in, described oil-in is connected by oil-way pipe and oil filler, oil-out is connected by oil-way pipe and fuel outlet, control panel is placed in manipulation case, adopt cart structure, make device operating position more flexible, body layout is convenient in use carry out operational maintenance and maintenance in the future.
Described top cover adopts the sidewall of hinge structure and car body to connect, and top cover can be made to turn over and turn 90 degrees, be convenient to safeguard internal duct and circuit.
Described wheel is provided with brake gear, flexible operation safety, prevents the automatic moving because of car body from causing the accident.
The sidewall of described top cover is provided with louvre, and the temperature in maintenance car body, within safety value scope, provides safety guarantee.
The lower end of car body is provided with external power supply case, prevents the fuel oil hydrocarbons contact in electric spark and car body from causing the accident.
The utility model compared with prior art has following effect: 1. the utility model combines with sensor testing techniques using by the automatic control technology of PLC control chip as core, related data is gathered by controlling unit, the data collected are passed to touch display screen by data communication interface, touch display screen shows test data in real time, and compare with the indicated value shown by the fuel system instrument on aircraft, whether qualified to judge the performance parameter of aircraft fuel system instrument.The parameter that whole automation equipment can detect comprises flow, total oil mass, oil temperature, aircraft remain oil and minimum oil, the highest oil warning etc., achieve while fueling a plane, aircraft fuel system instrument can be detected without the need to dismounting and just can reach the function measuring object.Carried out detection through scene to aircraft oil scale in situ detection device to try out, result shows:
This device is solid and reliable, and crosslinked relation is correct; Accurate measurement, meets design accuracy requirement; With tank service truck, aircraft carries out crosslinked test, and can verify aircraft fuel oil fuel level gauge, check results meets design requirement, and improves the efficiency of aircraft maintenance, greatly reduces maintenance cost.
2. the utility model adopts PLC control and touch display screen as man-machine data interaction, and the programming of this touch display screen is simple, and burning is easy, easy to operate, has the features such as low-power consumption, cheapness, stable performance.
3. the utility model can be selected working method by touch display screen and detect data display mode, and can automatically switch.And have both have freely carry out fuel oil oiling, oil pumping and filtering function.
Accompanying drawing explanation
Fig. 1 is overall structure schematic diagram of the present utility model;
Fig. 2 is the utility model car body front view;
Fig. 3 is the left view of the utility model car body.
In figure 1, first stop valve, 2, second stop valve, 3, 3rd stop valve, 4, 4th stop valve, 5, secondary filter, 6, temperature sensor, 7, hydraulic pump, 8, pressure sensor, 9, main filter, 10, flowmeter, 11, measure working connection pipe, 12, first measures auxiliary oil circuit pipe, 13, second measures auxiliary oil circuit pipe, 14, oil filler, 15, oil-out, 16, data processing section, 17, control panel, 20, car body, 21, top cover, 22, manipulation case, 23, side door, 24, pushing hands, 25, wheel, 26, fuel outlet, 27, side cover, 28, hinge, 29, oil-in, 30, louvre, 31, oil gun, 32, power supply box, 33, oil way flexible pipe frame, 34, oil way flexible pipe, 35, danger button.
Detailed description of the invention
Accompanying drawings detailed description of the invention of the present utility model, a kind of aircraft oil scale in situ detection device of present embodiment, comprise oil filler 14, measure working connection pipe 11, data processing section 16, control panel 17 and oil-out 15, described data processing section 16 comprises PLC control chip, control panel 17 comprises touch display screen, described measurement working connection pipe 11 one end connects oil filler 14, the other end connects oil-out 15, measure on working connection pipe 11 and first stop valve 1 is installed successively, second stop valve 2, temperature sensor 6, hydraulic pump 7, main filter 9, pressure sensor 8 and flowmeter 10, be connected to the first measurement auxiliary oil circuit pipe 12 between described oil filler 14 and the output of the second stop valve 2, first measures auxiliary oil circuit pipe 12 is provided with the 3rd stop valve 3, the second measurement auxiliary oil circuit pipe 13 is connected between the output of the second stop valve 2 and the input of main filter 9, second measures auxiliary oil circuit pipe 13 is provided with the 4th stop valve 4, the data output end of described temperature sensor 6, pressure sensor 8 and flowmeter 10 connects with the data receiver of the PLC control chip of data processing section 16 respectively, the control output end of PLC control chip respectively connecting fluid press pump 7, first stop valve 1, second stop valve 2, the 3rd stop valve 3 and the 4th stop valve 4, PLC control chip is set up bi-directional data with control panel 17 by data bus connection and is connected.
Secondary filter 5 is provided with between described first stop valve 1 and the second stop valve 2.
Memory cell is provided with in described touch display screen.
Described aircraft oil meter original position calibration equipment is placed in car body 20, described car body 20 upper end is provided with top cover 21 and manipulation case 22, the lower end of car body 20 is provided with wheel 25 and fuel outlet 26, the sidewall of car body 20 is provided with side door 23, the side of car body 20 is provided with oil way flexible pipe frame 33, the opposite side of car body 20 is provided with pushing hands 24, the side of described top cover 21 is provided with side cover 27, side cover 27 is connected by hinge 28 and top cover 21, the upper end of top cover 21 is provided with oil-in 29, described oil-in 29 is connected by oil-way pipe and oil filler 14, oil-out 15 is connected by oil-way pipe and fuel outlet 26, control panel 17 is placed in manipulation case 22.Fuel outlet 26 connects oil gun 31 by oil way flexible pipe 34, and oil way flexible pipe 34 dish is placed on oil way flexible pipe frame 33.
Described top cover 21 adopts the sidewall of hinge structure and car body 20 to connect.
Described wheel 25 is provided with brake gear.
The sidewall of described top cover 21 is provided with louvre 30 and danger button 35.
The lower end of car body 20 is provided with external power supply case 32.
Car body 20 is equipped with accessory case, the included maintenance tool of accessory case and annex; Consider fireproof needs, go-cart is provided with extinguisher device.And in each significant points mark explanation in Chinese and diagram.Consider fireproof requirement simultaneously, take equipment body earthing mode.
The PLC control chip that present embodiment adopts is siemens PLC CN, and the flowmeter 10 of employing is the high precision flow of domestic production, and its precision is 0.2%, can meet technical requirement like this, cost-saved again; Hydraulic pump 7 selects the fuel oil that aircraft is installed to transfer pump, and its pressure, flow etc. all can meet the demands.
Auxiliary oil circuit pipe 12, second measurement auxiliary oil circuit pipe 13 measured by measurement working connection pipe 11, first and oil way flexible pipe 34 all adopts stainless steel and petrochemical industry specialty hose construction, anti-oxidant, corrosion-resistant, and has the earth connection of antistatic in flexible pipe.
Present embodiment measures auxiliary oil circuit pipe 12 by control survey working connection pipe 11, first and the second unit measured on auxiliary oil circuit pipe 13 gathers related data, the data collected are passed to touch display screen by data communication interface, touch display screen shows test data in real time, and compare with the indicated value shown by the fuel system instrument on aircraft, whether qualified to judge the performance parameter of aircraft fuel system instrument.
Measurement comprises two kinds of measurement patterns:
Oil car verification: the first stop valve 1, second stop valve 2, the 4th stop valve 4 are opened, and the 3rd stop valve 3 is closed.Fuel oil from tank service truck through: after oil filler 14 → the first stop valve 1 → secondary filter 5 → the second stop valve the 2 → four stop valve 4 → main filter 9 → flowmeter 10 → oil-out 14 → oil way flexible pipe 34 → oil gun 31, enter helicopter fuel tank.
Self-checking: the 3rd stop valve 3 is opened, the first stop valve 1, second stop valve 2, the 3rd stop valve 4 are closed.Fluid from by oil pumping source through: after oil filler the 14 → three stop valve 3 → hydraulic pump 7 → main filter 9 → flowmeter 10 → oil-out 14 → oil way flexible pipe 34 → oil gun 31, target approach fuel tank.
Claims (8)
1. an aircraft oil scale in situ detection device, comprise oil filler (14), measure working connection pipe (11), data processing section (16), control panel (17) and oil-out (15), it is characterized in that: described data processing section (16) comprises PLC control chip, control panel (17) comprises touch display screen, described measurement working connection pipe (11) one end connects oil filler (14), the other end connects oil-out (15), measure on working connection pipe (11) and the first stop valve (1) is installed successively, second stop valve (2), temperature sensor (6), hydraulic pump (7), main filter (9), pressure sensor (8) and flowmeter (10), the first measurement auxiliary oil circuit pipe (12) is connected between the output of described oil filler (14) and the second stop valve (2), first measures auxiliary oil circuit pipe (12) is provided with the 3rd stop valve (3), the second measurement auxiliary oil circuit pipe (13) is connected between the output of the second stop valve (2) and the input of main filter (9), second measures auxiliary oil circuit pipe (13) is provided with the 4th stop valve (4), the data output end of described temperature sensor (6), pressure sensor (8) and flowmeter (10) connects with the data receiver of the PLC control chip of data processing section (16) respectively, control output end connecting fluid press pump (7), the first stop valve (1), the second stop valve (2), the 3rd stop valve (3) and the 4th stop valve (4) respectively of PLC control chip, PLC control chip is set up bi-directional data with control panel (17) by data bus connection and is connected.
2. a kind of aircraft oil scale in situ detection device according to claim 1, is characterized in that: be provided with secondary filter (5) between described first stop valve (1) and the second stop valve (2).
3. a kind of aircraft oil scale in situ detection device according to claim 2, is characterized in that: be provided with memory cell in described touch display screen.
4. a kind of aircraft oil scale in situ detection device according to claim 3, it is characterized in that: described aircraft oil meter original position calibration equipment is placed in car body (20), described car body (20) upper end is provided with top cover (21) and manipulation case (22), the lower end of car body (20) is provided with wheel (25) and fuel outlet (26), the sidewall of car body (20) is provided with side door (23), the rear end of car body (20) is provided with pushing hands (24), the side of described top cover (21) is provided with side cover (27), side cover (27) is connected by hinge (28) and top cover (21), the upper end of top cover (21) is provided with oil-in (29), described oil-in (29) is connected by oil-way pipe and oil filler (14), oil-out (15) is connected by oil-way pipe and fuel outlet (26), control panel (17) is placed in manipulation case (22).
5. a kind of aircraft oil scale in situ detection device according to claim 4, is characterized in that: described top cover (21) adopts hinge structure to connect with the sidewall of car body (20).
6. a kind of aircraft oil scale in situ detection device according to claim 5, is characterized in that: described wheel (25) is provided with brake gear.
7. a kind of aircraft oil scale in situ detection device according to claim 6, is characterized in that: the sidewall of described top cover (21) is provided with louvre (30).
8. a kind of aircraft oil scale in situ detection device according to claim 7, is characterized in that: the lower end of car body (20) is provided with external power supply case (32).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520008806.5U CN204301824U (en) | 2015-01-08 | 2015-01-08 | A kind of aircraft oil scale in situ detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520008806.5U CN204301824U (en) | 2015-01-08 | 2015-01-08 | A kind of aircraft oil scale in situ detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204301824U true CN204301824U (en) | 2015-04-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520008806.5U Expired - Fee Related CN204301824U (en) | 2015-01-08 | 2015-01-08 | A kind of aircraft oil scale in situ detection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204301824U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105004408A (en) * | 2015-06-05 | 2015-10-28 | 哈尔滨飞机工业集团有限责任公司 | Calibration method for helicopter fuel oil indication system |
| CN105383709A (en) * | 2015-10-30 | 2016-03-09 | 黑龙江省科学院自动化研究所 | Movable airplane fuel system testing device and control method thereof |
| CN106347703A (en) * | 2016-11-28 | 2017-01-25 | 中航通飞华南飞机工业有限公司 | Large-scale airplane fuel oil system test device |
| CN110455377A (en) * | 2019-07-23 | 2019-11-15 | 东风柳州汽车有限公司 | Fuel vehicle course continuation mileage display matching rack and test method |
| CN110920914A (en) * | 2019-12-06 | 2020-03-27 | 南京航空航天大学 | Comprehensive thermal management and regulation system for airplane |
| CN113091858A (en) * | 2021-03-18 | 2021-07-09 | 中国人民解放军海军航空大学青岛校区 | In-situ calibration device for lubricating oil mass |
| CN113232874A (en) * | 2021-06-11 | 2021-08-10 | 江西洪都航空工业集团有限责任公司 | Automatic control device for aircraft pressure refueling |
| CN113310554A (en) * | 2021-05-28 | 2021-08-27 | 长沙航空职业技术学院 | Comprehensive test device and method for aircraft fuel consumption meter |
-
2015
- 2015-01-08 CN CN201520008806.5U patent/CN204301824U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105004408A (en) * | 2015-06-05 | 2015-10-28 | 哈尔滨飞机工业集团有限责任公司 | Calibration method for helicopter fuel oil indication system |
| CN105383709A (en) * | 2015-10-30 | 2016-03-09 | 黑龙江省科学院自动化研究所 | Movable airplane fuel system testing device and control method thereof |
| CN106347703A (en) * | 2016-11-28 | 2017-01-25 | 中航通飞华南飞机工业有限公司 | Large-scale airplane fuel oil system test device |
| CN106347703B (en) * | 2016-11-28 | 2019-01-15 | 中航通飞华南飞机工业有限公司 | Large aircraft fuel system experimental rig |
| CN110455377A (en) * | 2019-07-23 | 2019-11-15 | 东风柳州汽车有限公司 | Fuel vehicle course continuation mileage display matching rack and test method |
| CN110920914A (en) * | 2019-12-06 | 2020-03-27 | 南京航空航天大学 | Comprehensive thermal management and regulation system for airplane |
| CN113091858A (en) * | 2021-03-18 | 2021-07-09 | 中国人民解放军海军航空大学青岛校区 | In-situ calibration device for lubricating oil mass |
| CN113310554A (en) * | 2021-05-28 | 2021-08-27 | 长沙航空职业技术学院 | Comprehensive test device and method for aircraft fuel consumption meter |
| CN113232874A (en) * | 2021-06-11 | 2021-08-10 | 江西洪都航空工业集团有限责任公司 | Automatic control device for aircraft pressure refueling |
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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 |
Granted publication date: 20150429 Termination date: 20160108 |