CN100585370C - Device and method for testing airplane tank system - Google Patents
Device and method for testing airplane tank system Download PDFInfo
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- CN100585370C CN100585370C CN200610083252A CN200610083252A CN100585370C CN 100585370 C CN100585370 C CN 100585370C CN 200610083252 A CN200610083252 A CN 200610083252A CN 200610083252 A CN200610083252 A CN 200610083252A CN 100585370 C CN100585370 C CN 100585370C
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- fuel
- fuel supply
- isolation valve
- airplane
- tank system
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- 238000012360 testing method Methods 0.000 title claims abstract description 65
- 238000000034 method Methods 0.000 title claims description 15
- 239000000446 fuel Substances 0.000 claims abstract description 321
- 230000004044 response Effects 0.000 claims abstract description 9
- 239000002828 fuel tank Substances 0.000 claims description 81
- 238000002955 isolation Methods 0.000 claims description 66
- 230000005540 biological transmission Effects 0.000 claims description 10
- 230000003213 activating effect Effects 0.000 claims description 4
- 239000003921 oil Substances 0.000 description 24
- 238000007599 discharging Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 206010057315 Daydreaming Diseases 0.000 description 1
- 241000282414 Homo sapiens Species 0.000 description 1
- 230000004913 activation Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000008187 granular material Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000010926 purge Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
A kind of device used in detecting the airplane oil basin includes the fuel supplying equipment and this fuel supplying equipment includes the fuel container, the fuel supplying pipe used to supply the fuel to the fuel outlet of fuel supplying equipment from the fuel container and the first isolated valve set in the fuel supplying pipe. The equipment said above also includes: the fuel delivery pipe which is used to supply the fuel to air oil basin system from the fuel outlet of fuel supplying equipment; and the second isolated valve set in the fuel delivery pipe. The electronic control unit of this equipment (ECU) suits to the first isolated valve and the second isolated valve and responses to the test reference signal supplying to the electronic control unit of the device and corresponds to breaking the fuel supply by the fuel supplying pipe and the fuel delivery by the fuel delivery pipe.
Description
Technical field
The present invention relates to be used for the equipment and the method for testing airplane tank.
Background technology
In the final assembling process of aircraft, must test to guarantee the airplane fuel tank system opertaing device normal running of---especially oil level control device---to airplane fuel tank system.In addition, whether this test is used to detect oil tank system and leaks.The test of this airplane fuel tank system relates to the fuel quantity predetermined from fuel reservoir toward the oil tank system supply.For safety factor, the equipment that is used for testing airplane tank generally includes emergency shutdown device, this emergency shutdown device can interrupt test when the safe emergency situation occurring, and this safe emergency situation for example is in a fuel tanker to be tested the superpressure situation to take place therein.In addition, control by brake hard (deadman) device usually from the fuel supply of fuel reservoir.If the operator fail (for example with constant duration or constantly) press corresponding emergency stop button (dead man ' s button) and continue from the order of accepting one's fate really of fuel reservoir fuel supplying to produce, then this urgent actuating device is used for the fuel supply of interrupts fuel reservoir immediately.
The test of airplane fuel tank system can be quite time-consuming, in some cases even reach 8 hours.Concerning the operator, it is very uncomfortable operating emergency braking apparatus so for a long time.In addition, have such risk: operating personnel are for example owing to absent minded and do not press emergency stop button mistakenly test is unexpectedly interrupted.
Summary of the invention
The present invention is directed to the problems referred to above and a kind of equipment and a kind of method are provided, it can be tested airplane fuel tank system reliably and guarantee higher security at test process simultaneously.
In order to address the above problem, the equipment that the present invention is used for testing airplane tank system comprises: fuel supply device, it comprises fuel reservoir and fuel supply pipe road, this fuel supply pipe road first end is connected to described fuel reservoir, and second end is connected to the fuel outlet of this fuel supply device, thereby is used for fuel is supplied to from fuel reservoir the fuel outlet of fuel supply device.In this fuel conduit, be provided with first isolation valve of the integral part of a formation fuel supply device.In its open mode, this first isolation valve allows fuel to be fed to the fuel outlet of fuel supply device from fuel reservoir, and in its closed condition, this first isolation valve interrupts the fuel supply of the fuel outlet from the fuel reservoir to the fuel supply device.This fuel supply device can be stationary device, but is preferably movably device, for example refuelling car.In addition, this fuel supply device can comprise a petrolift, and it is used for from the fuel reservoir transfer the fuel.
The device that is used for testing airplane tank system of the present invention also comprises fuel delivery line, this fuel delivery line is connected to the fuel outlet of fuel supply device at first end, and can be connected to airplane fuel tank system, and be used for thus fuel is sent to airplane fuel tank system from the fuel outlet of fuel supply device at second end.One second isolation valve is set in this fuel delivery line.In its open mode, this second isolation valve allows fuel to be sent to airplane fuel tank system from the fuel outlet of fuel supply device, and in its closed condition, and this second isolation valve interrupts the fuel supply from the fuel outlet of fuel supply device to airplane fuel tank system.
The electronic control unit of present device is suitable for controlling this first isolation valve and second isolation valve, with in response to providing the fuel supply interrupted respectively to the test parameter signal of electronic control unit by the fuel supply pipe road and the fuel by fuel delivery line to transmit.In other words, if electronic control unit receives corresponding test parameter signal, then this electronic control unit is controlled first and second isolation valves and is closed this first and second isolation valve, and thus respective interrupt by the fuel supply pipe road the fuel supply and the fuel by fuel delivery line transmit.Thereby first isolation valve of fuel supply device is integrated in the control circuit of electronic control unit.
Thus, at the equipment that is used for testing airplane tank system of the present invention, can save the emergency braking apparatus of the fuel supply that is used to control the interrupts fuel feeding mechanism.Therefore, this equipment is Energy and comfort to the operator.In addition, because electronic control unit responds corresponding test parameter signal and controls first and second isolation valves simultaneously, thereby correspondingly interrupt immediately by the fuel supply on fuel supply pipe road and the fuel transmission of passing through fuel delivery line, therefore in the process of carrying out the airplane fuel tank system test, overall security has obtained reinforcement.
The electronic control unit of present device also can be suitable for controlling the petrolift of fuel supply device, provides to the relevant parameter of this electronic control unit with response and stops the conveying of fuel from fuel reservoir.Yet, selectively, can petrolift be attached in the control circuit of electronic control unit yet.If first isolation valve responds from the corresponding command of electronic control unit and cuts out, and petrolift remains in operation, then the operator scheme of petrolift is changed into the lost motion operation pattern.
Preferably, for tightening security property, the present invention is used for first and second isolation valves of equipment of testing airplane tank system, and one of them is the pneumatic operation valve at least.
In a preferred embodiment, present device also comprises a pressure transducer, and it is used for the pressure in the sensing fuel tanker and the test parameter signal of the pressure in the expression airplane fuel tank system is provided.Preferably, this pressure transducer be suitable for be arranged on airplane fuel tank system on draining valve removably be connected.For example, this pressure transducer can be suitable for being removably disposed in the draining valve housing that is positioned on the airplane fuel tank system.Preferably, this pressure transducer can be connected in the exterior section of this draining valve.This draining valve is arranged on the bottom of airplane fuel tank system usually and can gets to remove condensate water from this airplane fuel tank system from the aircraft outside.By a pressure transducer is provided---this pressure transducer can be inserted in after unloading the draining valve valve body simply in the draining valve housing, and this pressure transducer can easily be installed from the aircraft outside.Thereby can save installation at the pressure transducer of interior of aircraft.Because draining valve is arranged on the minimum point of oil tank system usually, sensor is positioned at also can be quite reliably in this valve housing and accurately measure pressure in the oil tank system.
Present device can comprise a plurality of pressure transducers, and these pressure transducers are used for the pressure of each fuel tank in the sensing airplane fuel tank system, that is, and and the pressure of the wing tank of sensing aircraft, mid-fuel tank and auxiliary mid-fuel tank.These can be arranged on pressure transducer in the draining valve housing of each fuel tank will represent that the test parameter signal of the pressure in each fuel tank in the airplane fuel tank system provides to electronic control unit.
This electronic control unit can be suitable for controlling this first isolation valve and second isolation valve, correspondingly to interrupt under the situation that exceeds predetermined limit value by the pressure in the airplane fuel tank system that pressure transducer was sensed by the fuel supply on fuel supply pipe road and the fuel transmission of passing through fuel delivery line.Then, the pressure during present device has been guaranteed to be the fuel tank refuelling reliably when carrying out the airplane fuel tank system test in the airplane fuel tank system is no more than this predetermined limit value.Thus, can be able to remarkable enhancing in the overall security of carrying out test period.In addition, owing to the destruction to oil tank system and aircraft that produces that exceeds standard of fuel pressure in the airplane fuel tank system is avoided.
Present device also can comprise an overflow reservoir, and it can link to each other with airplane fuel tank system, is used to receive the fuel that overflows from airplane fuel tank system carrying out the airplane fuel tank system test period.Usually, the airplane fuel tank system opertaing device comprises the oil level control device, if it is full being used for the oil level sensing apparatus indication fuel tanker of the oil level of sensing airplane fuel tank system, its this oil level control device can be suitable for automatic interrupts fuel and be supplied to airplane fuel tank system.Carrying out the airplane fuel tank system test period, the normal running of necessary test oil level control device.Under the situation of oil level control device fault, promptly under the not interrupted situation of the fuel supply of airplane fuel tank system, although fuel tanker is full, the overflow reservoir receives the fuel that overflows from airplane fuel tank system.In addition, can carry out the overflow test,,, but still continue wittingly to the airplane fuel tank system fuel supplying although fuel tanker is full at this test period.
Be used for the equipment of testing airplane tank system in the present invention, level sensor can be set, the test parameter signal that it is used for the oil level of sensing overflow reservoir and is used for providing the oil level of expression overflow reservoir.Preferably, a plurality of overflow reservoirs are set, are used for the ccontaining fuel that overflows from each fuel tank of airplane fuel tank system.Each overflow reservoir can be provided with a level sensor, is used for the oil level of sensing overflow reservoir and the test parameter signal of representing the oil level in this overflow reservoir is provided.
Preferably, the electronic control unit of present device is suitable for controlling first isolation valve and second isolation valve, correspondingly to interrupt under the situation that exceeds preset limit by the oil level in the overflow reservoir that level sensor was sensed by the fuel supply on fuel supply pipe road and the fuel transmission of passing through fuel delivery line.In other words, in the present device,, then interrupt by the fuel supply on fuel supply pipe road and the fuel transmission of passing through fuel delivery line if the overflow reservoir has been expired.
Preferably, present device comprises that also at least one can manually operated emergency off push-button, and it provides the expression operator test parameter signal of control request when activating.This equipment can be provided with a plurality of and fuel supply device, comprise the fixing of the fuel delivery line and second isolation valve or movably test table and each overflow reservoir be associated can manually operated emergency off push-button.
The electronic control unit of present device can be suitable for controlling first isolation valve and second isolation valve, interrupts by the fuel supply on fuel supply pipe road and the fuel transmission of passing through fuel delivery line with the response test parameter signal that emergency off push-button was provided.In other words, described electronic control unit is controlled this first and second isolation valve and has manually been pressed the fuel that interrupts under the situation that is arranged on the emergency off push-button on the present device passing through the fuel supply on fuel supply pipe road and passing through fuel delivery line the operator and transmitted.
The method that the present invention is used for testing airplane tank system may further comprise the steps: from the fuel outlet fuel supplying of fuel reservoir to fuel supply device, and transmit fuel from the fuel outlet of fuel supply device to airplane fuel tank system through fuel delivery line through the fuel supply pipe road.Be arranged on first isolation valve in the fuel supply pipe road and second isolation valve that is arranged in the fuel delivery line and control, provide the fuel supply correspondingly interrupted to the test parameter signal of electronic control unit by the fuel supply pipe road and the fuel by fuel delivery line to transmit with response by electronic control unit.
Preferably, the inventive method is further comprising the steps of: the pressure in the sensing airplane fuel tank system also provides the test parameter signal of the pressure of expression in this airplane fuel tank system by pressure transducer.Preferably, first isolation valve and second isolation valve are preferably controlled by electronic control unit, correspondingly to interrupt under the situation that exceeds predetermined limit value by the pressure in the airplane fuel tank system that pressure transducer was sensed by the fuel supply on fuel supply pipe road and the fuel transmission of passing through fuel delivery line.
The method that the present invention is used for testing airplane tank system also can may further comprise the steps: sensing is used to receive the oil level of the overflow reservoir of the fuel that overflows from airplane fuel tank system, and the test parameter signal of the oil level in the expression overflow reservoir is provided by level sensor.First isolation valve and second isolation valve can be controlled by electronic control unit, correspondingly to interrupt under the situation that exceeds predetermined limit value by the oil level in the overflow reservoir that level sensor was sensed by the fuel supply on fuel supply pipe road and the fuel transmission of passing through fuel delivery line.
Preferably, the inventive method is further comprising the steps of: provide at least one can manually operated emergency off push-button, it provides the expression operator test parameter signal of control request when activating.First isolation valve and second isolation valve can be controlled by electronic control unit, correspondingly interrupt by the fuel supply on fuel supply pipe road and the fuel transmission of passing through fuel delivery line with the response test parameter signal that emergency off push-button was provided.
Followingly the present invention is described in detail with reference to accompanying drawing.
Description of drawings
Fig. 1 schematically shows a preferred implementation of the present invention that is used for testing airplane tank system.
Embodiment
The equipment 10 that is used for testing airplane tank system 12 comprises a fuel supply device 14, and the form of this fuel supply device 14 is a refuelling car that includes fuel reservoir 16.Fuel supply reservoir 16 is connected in first end on fuel supply pipe road 18.Second disconnection on fuel supply pipe road 18 is connected to the fuel outlet 20 of fuel supply device 14.
First isolation valve 22 is arranged in the fuel supply pipe road 18, and in off position, these first isolation valve, 22 interrupts fuel are fed to the fuel outlet 20 of fuel supply device 14 from fuel reservoir 16.On the contrary, in open mode, this first isolation valve 22 allows fuel to be fed to the fuel outlet 20 of fuel supply device 14 from fuel reservoir 16.The petrolift 24 that be arranged in the fuel supply pipe road 18, is positioned at first isolation valve, 22 downstreams is used for from fuel reservoir 16 transfer the fuels.
The fuel outlet 20 of fuel supply device 14 is via suitable first end that member 28 is connected in fuel delivery line 26 that is coupled.In order to carry out the test of airplane fuel tank system, second end of fuel delivery line 26 is coupled member 30 by one and is connected in airplane fuel tank system 12.First pressure gauge 32 is arranged in the fuel delivery line 26, is used for the pressure of this fuel delivery line 26 of sensing.The downstream of first pressure gauge 32 is provided with a counting assembly 34 in fuel delivery line 26, and it is used to measure flow through quality of fuel, density and the temperature of fuel delivery line 26.
The downstream of counting assembly 34 is provided with one second isolation valve 36 in this fuel delivery line 26.Be similar to first isolation valve 22, this second isolation valve 32 is pneumatically-operated valves.In its closed condition, these second isolation valve, 36 interrupts fuel are fed to airplane fuel tank system 12 from the fuel outlet 20 of fuel supply device 14, and in its open mode, this second isolation valve 36 allows fuel to be fed to airplane fuel tank system 12 from the fuel outlet 20 of fuel supply device 14.
The downstream of second isolation valve 36 is provided with a fuel supply valve 38 in fuel delivery line 26.This fuel supply valve is used to regulate the fuel flow rate by fuel delivery line 26.The downstream of fuel supply valve 38 is provided with one second pressure gauge 40 in fuel delivery line 26, is used for the pressure of the fuel delivery line 26 in sensing fuel supply valve 38 downstreams.
One overflow reservoir 42 is connected in airplane fuel tank system by an overflow passage 44, although this overflow reservoir 42 is used for still being supplied to the fuel that overflows from the airplane fuel tank system reception under the situation of airplane fuel tank system 12 at the full too much fuel of fuel tanker 12.One level sensor 46 is set, in order to oil level in the sensing overflow reservoir 42 in this overflow reservoir 42.
Pressure transducer 48 is used for the pressure in the survey aircraft oil tank system 12.This pressure transducer 48 is removably disposed in the draining valve housing that is positioned on the airplane fuel tank system 12.This draining valve is arranged on the bottom of airplane fuel tank system 12 and can gets at from the aircraft outside.Therefore, this pressure transducer 48 can be inserted in the draining valve housing after pulling down the draining valve valve body.
In addition, at fuel supply device 14, overflow reservoir 42 and comprise on the mobile test platform of fuel delivery line 26, first and second pressure gauges 32 and 40, counting assembly 34, second isolation valve 36 and fuel supply valve 38 and be provided with emergency off push-button 50,52 and 54.
Emergency off push-button 50,52 and 54 all provides the test parameter signal of an expression control request (being operator's turn-off request) to electronic control unit ECU.In addition, fuel oil level sensor 46 will represent that the test parameter signal of the oil level in the overflow reservoir offers electronic control unit ECU.At last, electronic control unit ECU receives the test parameter signal of representing the pressure the airplane fuel tank system 12 from pressure transducer 48.
The equipment 10 that is used for testing airplane tank system 12 further comprises fuel draining pipeline 56, and this fuel draining pipeline 56 is connected in airplane fuel tank system 12 by being coupled member 58.Fuel draining pipeline 56 is connected in air pipeline 59, and what this air pipeline 59 can be connected to the second end place that is positioned at fuel supply pipe road 18 is coupled member 30.For example being arranged so that like this can be recycled directly to fuel draining pipeline 56 from fuel supply pipe road 18 with fuel when the purge fuel supply line, and need not airplane fuel tank system 12 is connected between fuel conduit 18 and the fuel draining pipeline 56.One the 3rd pressure gauge 60 is arranged in the fuel draining pipeline 56, is used for measuring the fuel pressure of fuel draining pipeline 56.
Fuel is controlled by fuel draining valve 62 through the discharging of fuel draining pipeline 56 from airplane fuel tank system 12.When its closed condition, these fuel draining valve 62 interrupts fuel are from the discharging of airplane fuel tank system 12 through fuel draining pipeline 56, and when its open mode, this fuel draining valve 62 allows fuel from the discharging of airplane fuel tank system 12 through fuel draining pipeline 56.Fuel draining pipeline 56 is connected in the fuel reservoir 16 of fuel supply device 14.This makes to have nothing to do with the pump 24 of fuel supply device 14 and draws off fuel from airplane fuel tank system.Thereby, after carrying out the airplane fuel tank system test, can be other test institute via the fuel that fuel draining pipeline 56 discharged and utilize once more.
In fuel draining pipeline 56, the downstream of fuel draining valve 62 is provided with a filtrator 64.Filtrator 64 is provided with pressure reduction sensing apparatus 66, to detect obstruction or other faults of filtrator 64.Filtrator 64 is used for preventing that the granule foreign of the fuel that airplane fuel tank system is discharged is introduced in the fuel reservoir 16 of fuel supply device 14.
In order to carry out the system testing of fuel tanker, second end of fuel delivery line 26 is connected to airplane fuel tank system 12 through being coupled member 30.38 manual operations of fuel supply valve to its open mode, are fed to airplane fuel tank system 12 to allow fuel from fuel supply device 14.Then, the pump of operation fuel supply device 14 and fuel is transported to airplane fuel tank system 12 from fuel reservoir 16.
During being airplane fuel tank system 12 refuellings, the pressure in the airplane fuel tank system 12 is carried out sensing continuously by pressure transducer 48.In addition, level sensor 46 oil level in the sensing overflow reservoir 42 continuously.
When providing pressure to the signal of electronic control unit ECU indication airplane fuel tank system to surpass preset limit from pressure transducer 48, electronic control unit ECU control setting in fuel supply pipe road 18 first isolation valve 22 and be arranged on second isolation valve 36 in the fuel delivery line 26, transmit correspondingly to interrupt fuel supply by fuel supply pipe road 18 and the fuel by fuel delivery line 26 immediately.Thus, interrupted reliably to the fuel supply of airplane fuel tank system 12 from the fuel reservoir 16 of fuel supply device 14.
Similarly, if it is full to the signal of electronic control unit ECU indication overflow reservoir 42 that level sensor 46 provides, then electronic control unit ECU controls first isolation valve 22 and second isolation valve 36 and correspondingly interrupts fuel supply by fuel supply pipe road 18 and the fuel by fuel delivery line 26 transmits.
At last, if operator's manual activation emergency off push-button 50,52 and 54 one of them, then electronic control unit ECU controls first isolation valve 22 and second isolation valve 36 and correspondingly interrupts fuel supply by fuel supply pipe road 18 and the fuel by fuel delivery line 26 transmits.
In order to draw off fuel, fuel draining pipeline 56 is connected in airplane fuel tank system 12 by being coupled member 58 from airplane fuel tank system 12.After this, its device for opening is arrived in 62 manual operations of fuel draining valve, thereby fuel can discharge and introduce once more the fuel reservoir 16 of fuel supply device 14 by fuel draining pipeline 56 from airplane fuel tank system 12.
Claims (9)
1. equipment (10) that is used for testing airplane tank system (12), it comprises:
Fuel supply device (14), it comprises fuel reservoir (16), be used for fuel is supplied to the fuel supply pipe road (18) of fuel outlet (20) of fuel supply device (14) and first isolation valve (22) that is arranged on this fuel supply pipe road (18) from fuel reservoir (16);
Fuel delivery line (26) is used for fuel is sent to airplane fuel tank system (12) from the fuel outlet (20) of fuel supply device (14);
Be arranged on second isolation valve (36) in the described fuel delivery line (26); And
Electronic control unit (ECU), this electronic control unit is suitable for controlling described first isolation valve (22) and second isolation valve (36), thereby in response to providing the fuel supply correspondingly interrupted to the test parameter signal of this electronic control unit (ECU) by fuel supply pipe road (18) and the fuel by fuel delivery line (26) to transmit.
2. equipment as claimed in claim 1, wherein, described first and second isolation valves (22,36) one of them is pneumatically-operated valve at least.
3. equipment as claimed in claim 1 or 2, also comprise a pressure transducer (48), the test parameter signal that it is used for the pressure in the sensing fuel tanker (12) and the pressure in the expression airplane fuel tank system (12) is provided, wherein said electronic control unit (ECU) is suitable for controlling described first isolation valve (22) and second isolation valve (36), thereby, pressure in the airplane fuel tank system (12) that pressure transducer (48) senses exceeds under the situation of a predetermined limit value, correspondingly interrupts by the fuel supply on fuel supply pipe road (18) and the fuel transmission of passing through fuel delivery line (26).
4. equipment as claimed in claim 1 or 2 also comprises: overflow reservoir (42) is used for receiving the fuel that overflows from airplane fuel tank system (12); Level sensor (46), be used for the oil level of this overflow reservoir (42) of sensing and the test parameter signal of representing the oil level in the overflow reservoir (42) is provided, wherein said electronic control unit (ECU) is suitable for controlling described first isolation valve (22) and second isolation valve (36), thereby, oil level in the overflow reservoir (42) that level sensor (46) senses exceeds under the situation of a predetermined limit value, correspondingly interrupts by the fuel supply on fuel supply pipe road (18) and the fuel transmission of passing through fuel delivery line (26).
5. equipment as claimed in claim 1 or 2, comprise that also at least one can manually operated emergency off push-button (50,52,54), it provides the expression operator test parameter signal of control request when activating, wherein said electronic control unit (ECU) is suitable for controlling described first isolation valve (22) and second isolation valve (36), thereby respond described emergency off push-button (50,52,54) the test parameter signal that provides and correspondingly interrupt fuel supply by fuel supply pipe road (18) and the fuel by fuel delivery line (26) transmits.
6. be used for the method for testing airplane tank system (12), it may further comprise the steps:
Through fuel supply pipe road (18) from fuel outlet (20) fuel supplying of fuel reservoir (16) to fuel supply device (14);
Transmit fuel from the fuel outlet (20) of fuel supply device (14) to airplane fuel tank system (12) through fuel delivery line (26); And
By electronic control unit (ECU) control setting in fuel supply pipe road (18) first isolation valve (22) and be arranged on second isolation valve (36) in the fuel delivery line (26), thereby response provides the fuel supply correspondingly interrupted to the test parameter signal of electronic control unit (ECU) by fuel supply pipe road (18) and the fuel by fuel delivery line (26) to transmit.
7. method as claimed in claim 6, further comprising the steps of:
By the pressure in pressure transducer (48) the sensing airplane fuel tank system (12) and the test parameter signal of the pressure in the expression this airplane fuel tank system (12) is provided; And
By electronic control unit (ECU) control first isolation valve (22) and second isolation valve (36),, transmits the pressure in the airplane fuel tank system (12) that pressure transducer (48) is sensed thereby exceeding the fuel that correspondingly interrupts passing through the fuel supply on fuel supply pipe road (18) and passing through fuel delivery line (26) under the situation of predetermined limit value.
8. as claim 6 or 7 described methods, also can may further comprise the steps:
Be used for receiving the oil level of the overflow reservoir (42) of the fuel that overflows from airplane fuel tank system (12) by level sensor (46) sensing, and the test parameter signal of the oil level in the expression overflow reservoir (42) is provided; And
By electronic control unit (ECU) control first isolation valve (22) and second isolation valve (36),, transmits the oil level in the overflow reservoir (42) that level sensor (46) is sensed thereby exceeding the fuel that correspondingly interrupts passing through the fuel supply on fuel supply pipe road (18) and passing through fuel delivery line (26) under the situation of predetermined limit value.
9. as claim 6 or 7 described methods, further comprising the steps of:
Provide at least one can manually operated emergency off push-button (50,52,54), it provides the expression operator test parameter signal of control request when activating; And
By electronic control unit (ECU) control first isolation valve (22) and second isolation valve (36), thereby response emergency off push-button (50,52,54) the test parameter signal that is provided and correspondingly interrupt fuel supply by fuel supply pipe road (18) and the fuel by fuel delivery line (26) transmits.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200610083252A CN100585370C (en) | 2006-05-31 | 2006-05-31 | Device and method for testing airplane tank system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200610083252A CN100585370C (en) | 2006-05-31 | 2006-05-31 | Device and method for testing airplane tank system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101082544A CN101082544A (en) | 2007-12-05 |
| CN100585370C true CN100585370C (en) | 2010-01-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200610083252A Expired - Fee Related CN100585370C (en) | 2006-05-31 | 2006-05-31 | Device and method for testing airplane tank system |
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| Country | Link |
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| CN (1) | CN100585370C (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106089867A (en) * | 2016-06-29 | 2016-11-09 | 北华航天工业学院 | A kind of fuel tank of vehicle explosion pressure-resistant test system |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2352929Y (en) * | 1998-10-07 | 1999-12-08 | 荆门市亚科电子有限责任公司 | Instrument for measuring volum of fuel in fuel tank of automobile |
| US6131445A (en) * | 1997-10-10 | 2000-10-17 | Ford Motor Company | Fuel tank sensor assembly |
-
2006
- 2006-05-31 CN CN200610083252A patent/CN100585370C/en not_active Expired - Fee Related
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6131445A (en) * | 1997-10-10 | 2000-10-17 | Ford Motor Company | Fuel tank sensor assembly |
| CN2352929Y (en) * | 1998-10-07 | 1999-12-08 | 荆门市亚科电子有限责任公司 | Instrument for measuring volum of fuel in fuel tank of automobile |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101082544A (en) | 2007-12-05 |
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