CN109115473A - A kind of aircraft fuel system oil pump testing device - Google Patents
A kind of aircraft fuel system oil pump testing device Download PDFInfo
- Publication number
- CN109115473A CN109115473A CN201710480324.3A CN201710480324A CN109115473A CN 109115473 A CN109115473 A CN 109115473A CN 201710480324 A CN201710480324 A CN 201710480324A CN 109115473 A CN109115473 A CN 109115473A
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- CN
- China
- Prior art keywords
- oil pump
- fuel tank
- circulation line
- sensor
- aircraft
- 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.)
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Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0428—Safety, monitoring
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/26—Pc applications
- G05B2219/2604—Test of external equipment
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/26—Pc applications
- G05B2219/2612—Data acquisition interface
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
A kind of aircraft fuel system oil pump testing device, including fuel tank, oil filler, fuel tank ventilation valve, circulation line, circulation line exhaust valve, temperature sensor, flow sensor, pressure sensor, electronics oily filter, tested oil pump, liquid level sensor, data collector, host, test cabinet and operation display, oil filler is arranged on fuel tank top, fuel tank ventilation valve is arranged in top of oil-tank, circulation line one end connect the other end with fuel tank top and connect with tested oil pump, tested oil pump is mounted on fuel tank right side, and circulation line exhaust valve is arranged at the top of circulation line.The oil pump testing device structure is simple, easy to operate, automatically records test data, monitors operation of oil pump state in real time.Also, aircraft oil pump test flow in process, pressure, the stability of temperature are preferably ensured, ensure that test result, it is ensured that the qualified supply of aircraft oil pump improves test efficiency.
Description
Technical field
The present invention relates to aircraft fuel system oil pump performance the field of test technology, and in particular to a kind of aircraft fuel system oil
Pump test device.
Background technique
Aircraft fuel system is an important component of entire aircraft, it mainly stores a certain number of aircrafts and flies
The required fuel oil of row safety, and guarantee that fuel oil is safely and reliably delivered to aircraft engine by aircraft, to guarantee that engine is normal
Work, provides power needed for aircraft flight.Aircraft fuel system mainly has improvement aircraft refuelling condition and shortens refueling time, increases
Volume read-out is to extend the purpose of the airborne period of aircraft.And in aircraft fuel system aircraft oil pump be more crucial component it
One, it is to provide the power producer of fuel oil to engine, it is different according to engine oil supply situation, provided by aircraft oil pump
Uninterrupted is also different.The quality of aircraft oil pump performance directly affects the normal work of flight fuel system, also directly affects
The flight safety of aircraft.It needs to carry out it performance index verification before the installation of aircraft oil pump, aircraft oil pump performance indicators are tested
Card means are by aircraft oil pump testing device to aircraft oil pump progressive energy index test.Currently, aircraft fuel system oil pump tries
Experiment device mainly includes test fuel tank, circulation line, flow sensor, pressure sensor, temperature sensor etc., will need to test
In the aircraft oil pump of verifying is mounted in test fuel tank, by allowing its work to the power supply of aircraft oil pump, aircraft oil pump mentions for fuel oil
For power, circulate fuel oil by circulation management and test fuel tank, by flow sensor, the pressure sensing in circulation management
Device, temperature sensor test the flow of flow fuel oil, pressure, temperature, judge whether aircraft oil pump performance meets with this
It is required that.But fuel oil oil liquid has air to be mixed into following bad pipeline cyclic process, it is unstable fuel oil oil circulation occur, so that
Flow sensor, pressure sensor, the analog value of temperature sensor measurement are unstable, affect the normal survey of aircraft oil pump performance
Examination.Also, the voltage and current situation of operation of oil pump can not be detected, so that cannot judge whether oil pump meets installation and require.
Summary of the invention
In order to solve the above technical problems, the present invention provides a kind of stable testing airplanes to pump performance, it is ensured that aircraft oil
Pump testing is gone on smoothly, and guarantees the aircraft fuel system oil pump testing device of aircraft oil pump qualification supply.
A kind of aircraft fuel system oil pump testing device, including fuel tank, oil filler, fuel tank ventilation valve, circulation line, circulation
Pipeline exhaust valve, temperature sensor, flow sensor, pressure sensor, electronics oily filter, tested oil pump, liquid level sensor, data
Collector, host, test cabinet and operation display, oil filler setting are arranged in fuel tank top, fuel tank ventilation valve on fuel tank top
Portion, circulation line one end connect the other end with fuel tank top and connect with tested oil pump, and tested oil pump is mounted on fuel tank right side, follows
Endless tube road exhaust valve is arranged at the top of circulation line, and electronics oily filter is arranged in circulation line and is located at tested oil pump out of the mouth
Place, pressure sensor are arranged in circulation line and are located at electronics oily filter rear, and flow sensor is arranged in circulation line simultaneously
Positioned at pressure sensor rear, temperature sensor is arranged in circulation line and is located at flow sensor rear, liquid level sensor
It is vertically arranged in fuel tank, test cabinet is placed on fuel tank side, and the setting of operation display on test cabinet front, adopt by data
Storage and host are arranged in test cabinet, temperature sensor, flow sensor, pressure sensor, electronics oily filter, tested oil pump
It is connect by conducting wire with data collector with liquid level sensor, data collector and operation display are connected by conducting wire and host
It connects.
Further, which further includes Current Voltage tester, Current Voltage tester
It is arranged in test cabinet, Current Voltage tester is connect by conducting wire with the circuit of tested oil pump and data collector.
Further, which further includes gas concentration detection sensor, gas concentration inspection
Sensor is surveyed to be arranged in fuel tank internal upper part.
It is that the oil pump testing device structure is simple by the advantageous effects that the technological means present invention obtains, operation
It is convenient, test data is automatically recorded, monitors operation of oil pump state in real time.Also, aircraft oil pump test process is preferably ensured
Middle flow, pressure, the stability of temperature, ensure that test result, it is ensured that the qualified supply of aircraft oil pump improves test effect
Rate.
Detailed description of the invention
Fig. 1 is the structural diagram of the present invention.
Fig. 2 is logic diagram of the invention.
In figure: 1, fuel tank；2, oil filler；3, fuel tank ventilation valve；4, circulation line；5, circulation line exhaust valve；6, warm
Spend sensor；7, flow sensor；8, pressure sensor；9, electronics oily filter；10, it is tested oil pump；11, liquid level sensor；12, number
According to collector；13, host；14, Current Voltage tester；15, test cabinet；16, display is operated；17, gas concentration detects
Sensor.
Specific embodiment
The principle and features of the present invention will be described below with reference to the accompanying drawings, and example is served only for explaining invention, not
For limiting the scope of the invention.
A kind of aircraft fuel system oil pump testing device, including fuel tank 1, oil filler 2, fuel tank ventilation valve 3, circulation line 4,
Circulation line exhaust valve 5, temperature sensor 6, flow sensor 7, pressure sensor 8, electronics oily filter 9, tested oil pump 10, liquid level
Sensor 11, data collector 12, host 13, test cabinet 15 and operation display 16, oil filler 2 are arranged on 1 top of fuel tank,
The setting of fuel tank ventilation valve 3 is at 1 top of fuel tank, and 4 one end of circulation line connect the other end with 1 top of fuel tank and tested oil pump 10 connects
It connects, tested oil pump 10 is mounted on 1 right side of fuel tank, and the setting of circulation line exhaust valve 5 is set in 4 top of circulation line, electronics oily filter 9
Tested 10 oil outlet of oil pump is set in circulation line 4 and is located at, pressure sensor 8 is arranged in circulation line 4 and is located at electricity
Seed oil filters 9 rears, and flow sensor 7 is arranged in circulation line 4 and is located at 8 rear of pressure sensor, and temperature sensor 6 is arranged
In circulation line 4 and it is located at 7 rear of flow sensor, liquid level sensor 11 is vertically arranged in fuel tank 1, and test cabinet 15 is put
It sets in 1 side of fuel tank, operates display 16 and be arranged on 15 front of test cabinet, data collector 12 and the setting of host 13 are being surveyed
In test-run a machine cabinet 15, temperature sensor 6, flow sensor 7, pressure sensor 8, electronics oily filter 9, tested oil pump 10 and level sensing
Device 11 is connect by conducting wire with data collector 12, and data collector 12 and operation display 16 are connected by conducting wire and host 13
It connects.
To make judge whether its Current Voltage is qualified, it is ensured that quilt with the Current Voltage tested when tested oil pump 10 works
Survey the reliability of oil pump 10.The aircraft fuel system oil pump testing device further includes Current Voltage tester 14, and Current Voltage is surveyed
It tries device 14 to be arranged in test cabinet 15, Current Voltage tester 14 is acquired by the circuit and data of conducting wire and tested oil pump 10
Device 12 connects.
Fuel oil test danger is larger, to shift to an earlier date pre- blast protection, improves the safety of test, it is ensured that test is gone on smoothly.It should
Aircraft fuel system oil pump testing device further includes gas concentration detection sensor 17, and the setting of gas concentration detection sensor 17 exists
1 internal upper part of fuel tank.Gas concentration detection sensor 17 monitors surrounding oil molecule content, prevents fuel molecule too high levels and causes
Security risk.
Operation display 16 is mainly used to test products and setting data, shows detection parameters.Host 13 is entirely to control
The maincenter of system completes acquisition data processing and control.Data collector 12 by various sensors acquire come signal, by institute
There is signal to be converted to the digital signal that computer can identify.
Tested oil pump 10 is mounted on 1 right side of fuel tank, then 4 lower end of circulation line is connected to the outlet of tested oil pump 10
Place issues starting test instructions by operation display 16, at this point, tested oil pump 10 starts to work, the logical circulation line 4 of oil is in oil
It is recycled in case, electronics oily filter 9 detects the cleannes of oil at this time, and flow sensor 7 detects the uninterrupted of pump oil, pressure sensor
8 detection fuel pump outlet oil pressure, temperature sensor 6 detect oil temperature in circulation line 4, and liquid level sensor 11 detects oil mass in fuel tank 1,
Data collector 12 is transmitted signals to, the signal after conversion is sent to host 13 and handled by data collector 12, main
Machine 13 will treated that signal is sent to that operation display 16 is shown, completes test process.
Above-mentioned technical proposal only embodies the optimal technical scheme of technical solution of the present invention, those skilled in the art
The principle of the present invention is embodied to some variations that some of them part may be made, belongs to the scope of protection of the present invention it
It is interior.
Claims (3)
1. a kind of aircraft fuel system oil pump testing device, it is characterised in that: the aircraft fuel system oil pump testing device packet
Include fuel tank (1), oil filler (2), fuel tank ventilation valve (3), circulation line (4), circulation line exhaust valve (5), temperature sensor
(6), flow sensor (7), pressure sensor (8), electronics oily filter (9), tested oil pump (10), liquid level sensor (11), data
Collector (12), host (13), test cabinet (15) and operation display (16), the oil filler (2) are arranged on fuel tank (1)
Portion, at the top of fuel tank (1), described circulation line (4) one end is connect separately with fuel tank (1) top for fuel tank ventilation valve (3) setting
One end is connect with tested oil pump (10), and tested oil pump (10) are mounted on fuel tank (1) right side, the circulation line exhaust valve (5)
At the top of circulation line (4), electronics oily filter (9) setting goes out in circulation line (4) and positioned at tested oil pump (10) for setting
Oil port, pressure sensor (8) setting is in circulation line (4) and is located at electronics oily filter (9) rear, the flow sensing
Device (7) setting is in circulation line (4) and is located at pressure sensor (8) rear, and the temperature sensor (6) is arranged in circulation pipe
In road (4) and it is located at flow sensor (7) rear, the liquid level sensor (11) is vertically arranged in fuel tank (1), the test
Cabinet (15) is placed on fuel tank (1) side, and the operation display (16) is arranged on test cabinet (15) front, the data
Collector (12) and host (13) setting are in test cabinet (15), the temperature sensor (6), flow sensor (7), pressure
Sensor (8), electronics oily filter (9), tested oil pump (10) and liquid level sensor (11) are connected by conducting wire and data collector (12)
It connects, the data collector (12) and operation display (16) are connect by conducting wire with host (13).
2. aircraft fuel system oil pump testing device according to claim 1, it is characterised in that: the aircraft fuel system
Oil pump testing device further includes Current Voltage tester (14), and the Current Voltage tester (14) is arranged in test cabinet (15)
Interior, the Current Voltage tester (14) is connect by conducting wire with the circuit of tested oil pump (10) and data collector (12).
3. aircraft fuel system oil pump testing device according to claim 1 or 2, it is characterised in that: the aircraft fuel oil
System oil pump testing device further includes gas concentration detection sensor (17), and gas concentration detection sensor (17) setting exists
Fuel tank (1) internal upper part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710480324.3A CN109115473A (en) | 2017-06-22 | 2017-06-22 | A kind of aircraft fuel system oil pump testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710480324.3A CN109115473A (en) | 2017-06-22 | 2017-06-22 | A kind of aircraft fuel system oil pump testing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109115473A true CN109115473A (en) | 2019-01-01 |
Family
ID=64732667
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710480324.3A Pending CN109115473A (en) | 2017-06-22 | 2017-06-22 | A kind of aircraft fuel system oil pump testing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109115473A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN113236544A (en) * | 2021-04-25 | 2021-08-10 | 成都成航车辆仪表有限责任公司 | Function detection device for fuel booster pump of airplane |
| CN114427527A (en) * | 2021-12-20 | 2022-05-03 | 上海工程技术大学 | Testing device for aircraft fuel supply pump and fuel oil testing system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2168097Y (en) * | 1993-01-07 | 1994-06-08 | 北京铁道工程机电技术研究所 | Automatic testing jig for detection of oil pump motor set |
| CN205087161U (en) * | 2015-10-30 | 2016-03-16 | 黑龙江省科学院自动化研究所 | Movable aircraft fuel oil system test device |
| CN106742010A (en) * | 2015-11-24 | 2017-05-31 | 中航贵州飞机有限责任公司 | A kind of aircraft fuel system cleaning Vehicle |
| CN108105079A (en) * | 2016-11-24 | 2018-06-01 | 中航贵州飞机有限责任公司 | A kind of oil pump testing device |
-
2017
- 2017-06-22 CN CN201710480324.3A patent/CN109115473A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2168097Y (en) * | 1993-01-07 | 1994-06-08 | 北京铁道工程机电技术研究所 | Automatic testing jig for detection of oil pump motor set |
| CN205087161U (en) * | 2015-10-30 | 2016-03-16 | 黑龙江省科学院自动化研究所 | Movable aircraft fuel oil system test device |
| CN106742010A (en) * | 2015-11-24 | 2017-05-31 | 中航贵州飞机有限责任公司 | A kind of aircraft fuel system cleaning Vehicle |
| CN108105079A (en) * | 2016-11-24 | 2018-06-01 | 中航贵州飞机有限责任公司 | A kind of oil pump testing device |
Non-Patent Citations (1)
| Title |
|---|
| 王炜等: "综合油泵试验台的设计与实现", 《机电一体化》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN113236544A (en) * | 2021-04-25 | 2021-08-10 | 成都成航车辆仪表有限责任公司 | Function detection device for fuel booster pump of airplane |
| CN114427527A (en) * | 2021-12-20 | 2022-05-03 | 上海工程技术大学 | Testing device for aircraft fuel supply pump and fuel oil testing system |
| CN114427527B (en) * | 2021-12-20 | 2023-07-04 | 上海工程技术大学 | Testing device for aircraft fuel feed pump and fuel testing system |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190101 |