CN100559142C - Engine room structure is pressurizeed to detect the device and method of its leakage - Google Patents
Engine room structure is pressurizeed to detect the device and method of its leakage Download PDFInfo
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- CN100559142C CN100559142C CNB2006100833082A CN200610083308A CN100559142C CN 100559142 C CN100559142 C CN 100559142C CN B2006100833082 A CNB2006100833082 A CN B2006100833082A CN 200610083308 A CN200610083308 A CN 200610083308A CN 100559142 C CN100559142 C CN 100559142C
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Abstract
The invention provides a kind of being used for pressurizes and measures the device (10) of this engine room structure (12) leakage rate engine room structure (12), and comprising: an air supply line (14) is used for forced air is supplied to this engine room structure (12) from described pressurized air source; An air supply valve (36); A pressure transducer (50) is used for this engine room structure of sensing (12) pressure inside and is used to provide representing this engine room structure (12) internal pressure signal; An air vent line (42) is used for air is discharged to this air outlet (44) from this engine room structure (12) inside; With a bleed air valve (48).An electronic control unit (ECU) that is suitable for controlling this air supply valve (36) and this bleed air valve (48) according to the signal that this pressure transducer (50) provides, thereby forced air is fed in this engine room structure (12), and afterwards air is discharged from this engine room structure (12) is inner.
Description
Technical field
[1] the present invention relates to that a kind of engine room structure that is used for aircraft pressurizes and the device and method of the leakage rate of survey aircraft engine room structure.
Background technology
[2] because the environmental pressure at aircraft flight height place is very low, and the cabin of aircraft awing remains on the pressure that increases usually, this pressure is equivalent to about 2500 meters atmospheric pressures of highly locating on the sea level.Thereby, engine room structure must be designed to bear low environmental pressure and the cabin pressure that increases between pressure reduction.In addition, the aircraft cabin structure must roughly not leaked, thereby can keep the pressure that increases in the cabin.Therefore, in the last assembling process of aircraft, must test the aircraft cabin structure, thereby: 1. there are not the leakage that produces owing to the assembling defective in the structural strength of checking pressurised cabin and 2. checkings, and it will hinder the pressurization of aircraft cabin awing.
Summary of the invention
[3] the present invention is devoted to address this problem, and a kind of device and method that is used for different type of airplanes is provided, and it makes can be reliably, accurately and automatically the aircraft cabin structure is pressurizeed, thereby helps preventing cabin leakage.
[4] in order to address the above problem, the inventive system comprises an air supply line, first end of this air supply line can be connected to pressurized air source and its second end can be connected to the aircraft cabin structure, thereby forced air is fed to the aircraft cabin structure from pressurized air source.Second end of this air supply line can be connected to the opening that is arranged in the aircraft cabin structure.For example, when carrying out leak-testing, the opening that is used for attached air supply line can be formed at a simulated aircraft cabin door that substitutes actual aircraft cabin door.
[5] be provided with the air supply valve in the air supply line, this air supply valve for example can be solenoid valve.In the closed condition of air supply valve, its fluid that interrupts between pressurized air source and the aircraft cabin structure connects, and in its open mode, the air supply valve allows forced air to be fed to the aircraft cabin structure from pressurized air source.
Device of the present invention also comprises a pressure transducer, and this pressure transducer is used for the pressure of sensing aircraft cabin inside configuration, and is used to provide the signal of representing aircraft cabin inside configuration pressure.This pressure transducer can directly be placed on the aircraft cabin inside configuration, and provides corresponding pressure signal by the equipment of being electrically connected accordingly.Yet preferably, this pressure transducer is arranged on the aircraft cabin structural outer, and for example is connected to the inside of engine room structure by flexible duct.Described device is more more firm than the device that comprises the sophisticated electronic circuit.
In addition, be provided with the air vent line, its first end can be connected to the aircraft cabin structure, and its second end can be connected to air outlet, thereby air is discharged to air outlet from engine room structure inside.Preferably, this air vent line branch is in this air supply line, make with the aircraft cabin inside configuration between connection device of needs only.This air outlet can reach in the external environment condition and can be provided with a sound absorber, thereby in the generation that when the aircraft cabin structure is discharged air, suppresses noise by air vent line and air outlet.
Be provided with a bleed air valve in the air vent line, similar with the air supply valve, this bleed air valve can be a solenoid valve.In the closed condition of this bleed air valve, its fluid that interrupts between aircraft cabin structure and the air outlet connects, and in its open mode, this bleed air valve allows air to be discharged to air outlet from the aircraft cabin structure.
The electronic control unit that is used for the leakage of hunter engine room structure in the device of the present invention is suitable for controlling air supply valve and bleed air valve according to the signal that pressure transducer provides, thereby forced air is fed in the aircraft cabin structure, reach first predetermined pressure level up to the aircraft cabin inside configuration, on first predeterminated level, keep one first predetermined amount of time with pressure with the aircraft cabin inside configuration, after this, discharge air from the aircraft cabin inside configuration.In other words, this electronic control unit control air supply valve and bleed air valve, thus forced air is fed in the aircraft cabin structure, thereby form an elevated pressure in the aircraft cabin inside configuration.Because the pressure reduction in the aircraft cabin structure, air leaks from the aircraft cabin inside configuration.Therefore in first predetermined amount of time, thereby the operator can easily check the aircraft cabin structure, distinguishes leakage harmful in the aircraft cabin structure reliably, and the defective of this leakages by the defective of each parts or when assembling causes.
In the preferred implementation of apparatus of the present invention, electronic control unit also is suitable for controlling air supply valve and bleed air valve according to the signal that pressure transducer provides, thereby after first predetermined amount of time and before the aircraft cabin inside configuration is discharged air, further forced air being fed to the aircraft cabin structure, reach second predetermined pressure level up to the aircraft cabin inside configuration.This second predetermined pressure level is higher than described first predetermined pressure level.This electronic control unit also can be suitable for controlling air supply valve and bleed air valve according to the signal that pressure transducer provides, thereby the air of aircraft cabin inside configuration is kept one second predetermined amount of time on second predetermined pressure level.Then, can utilize this second predetermined amount of time to check the aircraft cabin structure once more, thereby distinguish the less leakage that for example in first predetermined amount of time, does not pick out.
In addition, the electronic control unit of apparatus of the present invention can be suitable for controlling air supply valve and bleed air valve according to the signal that pressure transducer provides, thereby behind second predetermined amount of time, further forced air is fed in the aircraft cabin structure, reach the 3rd predetermined pressure level up to aircaft configuration inside, on the 3rd predeterminated level, keep one the 3rd predetermined amount of time with stress level with the aircraft cabin inside configuration.The 3rd predetermined pressure level is higher than described second predetermined pressure level, and preferably one be higher than the stress level that the operation of aircraft normal flight the time is applied to the structural pressure reduction of aircraft cabin.
This first, second and the 3rd time period can be the time period of predetermined fixed.Yet, when this electronic control unit also can carry out leak-testing on the aircraft cabin structure according to specific test situation---for example when aircraft cabin structure remain on time period that elevated pressure following time need prolong when checking the aircraft cabin structure---and manually change this preset time section.
Preferably, forced air is fed in the aircraft cabin structure with about 1.2 millibars/second speed, up to reaching the first about 100 millibars predetermined stress level (pressure reduction between environmental pressure and the aircraft cabin internal pressure) that increases.The stress level that is about 100 millibars can keep being about 1 minute first predetermined amount of time.This time period is enough to the leakage of distinguishing big in the aircraft cabin structure usually.After this, the pressure of aircraft cabin inside configuration increases with about 1.2 millibars/second speed, reaches the second about 400 millibars predetermined pressure level up to the aircraft cabin inside configuration.This stress level keeps being about 8 minutes second predetermined amount of time.This time period also is enough to the leakage of distinguishing less in the aircraft cabin structure usually.
When the pressure of aircraft cabin inside configuration further increases, because security reason no longer allows the operator near aircraft cabin structure to be tested.Thereby a kind of control module that apparatus of the present invention electronic control unit is preferably such: it is suitable for allowing to carry out Long-distance Control in whole test process.From the second about 400 millibars predetermined pressure level, the pressure of aircraft cabin inside configuration is increased to the 3rd about 800 millibars predetermined pressure level, wherein this pressure is increased to about 593 millibars level with about 1.2 millibars/second speed, is increased to about 800 millibars level from 593 millibars level with about 0.6 millibar/second speed again.The pressure of aircraft cabin inside configuration keeps being about 300 seconds the 3rd predetermined amount of time on the 3rd about 800 millibars predetermined pressure level.
In the preferred implementation of apparatus of the present invention, electronic control unit also is suitable for controlling air supply valve and bleed air valve according to the signal that pressure transducer provides, to discharge air from the aircraft cabin inside configuration, up to reaching the 4th predetermined pressure level, and air supply valve and bleed air valve remained on its closed condition, up to reaching the 5th predetermined pressure level.Preferably, the pressure of aircraft cabin inside configuration is reduced to the 4th about 593 millibars predetermined pressure level with about 1.2 millibars/second speed from about 800 millibars maximum pressure levels.The 4th about 593 millibars predetermined pressure level is applied to the structural pressure reduction of aircraft cabin when moving corresponding to the aircraft normal flight.The 5th predetermined pressure level for example can be about 500 millibars stress level.Because air supply valve and bleed air valve remain on its closed condition, the leakage that only reduces by the aircraft cabin structure from the pressure of the 4th predetermined pressure level to the five predetermined pressure level causes.
The electronic control unit of apparatus of the present invention preferably also can be reduced to the leakage value that the 5th predeterminated level calculates the aircraft cabin structure from the 4th predeterminated level according to the pressure of aircraft cabin inside configuration.For example, the leakage value of this calculating can be corresponding to the tangent slope that calculates between the 4th and the 5th predetermined pressure level, in the predetermined pressure level place that for example is about 556 millibars in the relation curve between time and stress level.Can compare with specified leakage value by this leakage value that electronic control unit calculates.If the difference that records between leakage value and the specified leakage value exceeds a predetermined limits, then must take suitable step to improve the leakage characteristics of aircraft cabin structure.
After the stress level of aircraft cabin inside configuration has reached the 5th predetermined pressure level, this electronic control unit can be controlled air supply valve and bleed air valve according to the signal that pressure transducer provides, discharging air with about 1.2 millibars/second speed, reach ambient pressure level once more up to the pressure of aircraft cabin inside configuration from the aircraft cabin inside configuration.
The apparatus of the present invention that are used for the leakage of hunter engine room structure also can comprise an alerting signal output device, when receiving corresponding alerting signal output order from electronic control unit, this alerting signal output device is suitable for exporting a vision and/or audible ringing signal.For example, when the stress level of aircraft cabin inside configuration reaches a predetermined pressure level, the exportable alerting signal output order of this electronic control unit.In addition, this electronic control unit also can be suitable for the stress level that will be recorded by pressure transducer during the testing airplane engine room structure and compares with the relation curve between the time with corresponding rated pressure level with the relation curve between the time.Then, if interior measured stress level of aircraft cabin structure and the difference between the corresponding rated pressure level have exceeded predetermined limit, then this electronic control unit can provide an alerting signal output order to the alerting signal output device.This electronic control unit also can be suitable for interrupt test automatically, when for example the difference between measured stress level and the corresponding rated pressure level has exceeded predetermined limit in the aircraft cabin structure, interrupts forced air and is fed to the aircraft cabin structure.
Apparatus of the present invention also can be provided with one can manually operated emergency cut-off equipment, and it allows interrupt test, and particularly any time in test is interrupted the supply to the forced air of aircraft cabin structure.
The apparatus of the present invention that are used for the leakage of hunter engine room structure also can comprise a ball valve that is arranged on the air supply line.For example, this ball valve can be arranged in the air supply line in air supply valve downstream.This ball valve is as safety equipment, even its permission also can be controlled the pressure of aircraft cabin inside configuration reliably when the air supply valve lost efficacy.
The part of air supply line and/or air supply valve and/or pressure transducer and/or bleed air valve and/or ball valve can be installed in one movably on the support.Then, the movable supporting frame that has several vitals of apparatus of the present invention can for example be placed between the different websites of final assembly line.
Being used for apparatus of the present invention that the hunter engine room structure leaks can use in the final assembling process of aircraft, the leakage in the aircraft cabin structure that assembles with detection.Yet, also can be for example in the flight line, use apparatus of the present invention to come each parts of hunter engine room structure the leakage of---for example airframe---.
According to an optional embodiment, be used to make apparatus of the present invention of pressurization of aircraft cabin structure and survey aircraft engine room structure leakage rate to comprise: an air supply line, its first end can be connected to pressurized air source and its second end can be connected to the aircraft cabin structure, thereby forced air is fed to the aircraft cabin structure from this pressurized air source; One air supply valve, it is arranged in this air supply line; One pressure transducer, it is used to respond to the pressure of aircraft cabin inside configuration and the signal of indication aircraft cabin inside configuration pressure is provided; One air vent line, its first end can be connected to the aircraft cabin structure and its second end can be connected to air outlet, thereby air is discharged to this air outlet from the aircraft cabin inside configuration; One bleed air valve, it is arranged in this air vent line; With at least one pressure program.Electronic control unit the signal that provides according to pressure transducer is provided and controls air supply valve and bleed air valve according to the setting value of this pressure program, thereby forced air is fed in the aircraft cabin structure or air is discharged from the aircraft cabin structure, thereby control the pressure of aircraft cabin inside configuration according to this pressure program.
Preferably, provide a plurality of pressure programs for different type of airplanes and different test specifications.
Preferably, this electronic control unit also is suitable for selecting, controls and/or revises (adapt) pressure program.
In addition, this electronic control unit can be suitable for providing the scheme (protocol) of a measuring process, and it includes a value of representing cabin leakage.
The inventive method that is used for the leakage of hunter engine room structure comprises the steps: forced air is fed to the aircraft cabin structure from pressurized air source via the air supply line; Respond to the pressure of this aircraft cabin inside configuration and the signal of representing aircraft cabin inside configuration pressure is provided by pressure transducer; And air is discharged to air outlet from the aircraft cabin inside configuration via the air vent line.The bleed air valve that is arranged on the air supply valve in the air supply line and is arranged in the air vent line is controlled according to the signal that pressure transducer provided by electronic control unit, thereby forced air is fed in the aircraft cabin structure, reach first predetermined pressure level up to the aircraft cabin inside configuration, the pressure of aircraft cabin inside configuration is kept one first predetermined amount of time on first predeterminated level, after this discharge air from the aircraft cabin inside configuration.
The signal controlling air supply valve that provided according to pressure transducer by electronic control unit and the step of bleed air valve can also be provided method of the present invention, thereby after first predetermined amount of time and before discharging air from the aircraft cabin inside configuration, further forced air is fed in the aircraft cabin structure, reaches second predetermined pressure level up to the aircraft cabin inside configuration.The pressure of aircraft cabin inside configuration can keep one second predetermined amount of time on second predeterminated level.Behind second predetermined amount of time, can further forced air be fed in the aircraft cabin structure, reach the 3rd predetermined pressure level up to the aircraft cabin inside configuration.The pressure of aircraft cabin inside configuration can keep one the 3rd predetermined amount of time on the 3rd predeterminated level.
Preferably, the signal controlling air supply valve that provided according to pressure transducer by electronic control unit and the step of bleed air valve also are provided the inventive method, thereby discharge air from the aircraft cabin structure, up to reaching the 4th predetermined pressure level.Air supply valve and bleed air valve can be remained on its closed condition, up to reaching the 5th predetermined pressure level.The aircraft cabin inside configuration is only caused by the leakage of aircraft cabin structure from the pressure reduction of the 4th predetermined pressure level to the five predetermined pressure level.
Being used for the inventive method that the hunter engine room structure leaks preferably also comprises by electronic control unit and reduces the step of calculating aircraft cabin structure leakage value according to the aircraft cabin inside configuration from the pressure of the 4th predetermined pressure level to the five predetermined pressure level.
According to an optional embodiment, be used to make the inventive method of pressurization of aircraft cabin structure and survey aircraft engine room structure leakage rate to comprise the steps: forced air is fed to the aircraft cabin structure from pressurized air source via the air supply line; By pressure transducer induction machine cabin structure pressure inside and the signal of representing aircraft cabin inside configuration pressure is provided; Air is discharged to air outlet from the aircraft cabin inside configuration via the air vent line; And provide a pressure program.Be arranged on the air supply valve in the air supply line and be arranged on signal that the bleed air valve in the air vent line provides according to pressure transducer by electronic control unit and the setting value in the pressure program is controlled, thereby forced air is fed in the aircraft cabin structure or discharges air, with pressure according to pressure program control aircraft cabin inside configuration from the aircraft cabin structure.
Preferably, provide a plurality of pressure programs for different type of airplanes with different test categories.
The inventive method can also comprise by electronic control unit selects, controls and/or revise a pressure program.
Preferably, the inventive method also comprises the step that a measuring process scheme is provided by electronic control unit, and this scheme includes the value of representing cabin leakage.
Description of drawings
At length explain the present invention now with reference to synoptic diagram, wherein
Fig. 1 show the present invention be used for to the device of aircraft cabin structure pressurization and survey aircraft engine room structure leakage rate and
Fig. 2 shows the pressure of aircraft cabin inside configuration in the process of the test of carrying out pressurization of aircraft cabin structure and survey aircraft engine room structure leakage rate and the relation curve between the time.
Embodiment
Among Fig. 1, be used to make the device 10 of 12 pressurizations of aircraft cabin structure and survey aircraft engine room structure 12 leakage rates to comprise air supply line 14.First end of air supply line 14 is connected to the pressurized air source (not shown in figure 1), and it is used for the pressure supply air with 6～8 crust.Being provided with first in air supply line 14 can manually operated isolation valve 16.In air supply line 14, be provided with second isolation valve 18 in first isolation valve, 16 downstreams, it is used for automatically interrupting the forced air by 14 supplies of air supply line when power fail.The filtrator 20 that be arranged in the air supply line 14, is arranged in second isolation valve, 18 downstreams is used to filter the forced air that is fed to the aircraft cabin structure, thereby avoids granule foreign to be introduced in the aircraft cabin structure.
Air supply line 14 comprises the first fixed part 14a that is connected to second portion 14b, and wherein the second portion 14b of air supply line 14 is installed on the traversing carriage 22.The second portion 14b of air supply line 14 is connected to the 3rd air supply line part 14c, and this part 14c and the first fixed part 14a are set to the form of fixed-piping similarly.Air supply line 14 comprises the 4th part 14d that is formed by flexible duct at last, and its fixing third part 14c with air supply line 14 is connected to the opening 24 that is arranged in the simulated aircraft cabin door 26.In the test that survey aircraft engine room structure 12 leaks, analog machine hatch door 26 replaces actual cabin door.
From Fig. 1 obviously as seen, the 3rd fixed part 14c branch of air supply line 14, thus extend to two different tie points 28 and 28 '.Thereby the 4th flexible duct part 14d of air supply line 14 can be connected to any tie point 28 and 28 ' of the 3rd fixed part 14c of air supply line 14.Be provided with selector valve 30 and 30 ' among the 3rd fixed part 14c of air supply line 14, optionally forced air is fed to one selected in tie point 28 and 28 '.Thereby device 10 can be used for surveying the leakage of the aircraft cabin structure of different size.
Major part 14a, the 14b of first, second of air supply line 14 and third part and 14c, valve 16,18,30 and 30 ', filtrator 20 and traversing carriage 22 are arranged in the basement of aircraft factory with saving the space.The third part 14c of air supply line 14 extends through the opening 32 that is arranged in the basement ceiling 34.
Electromagnetic air supply valve 36 is arranged among the second portion 14b of air supply line 14, and is installed on the traversing carriage 22.Air supply valve 36 allows forced air is fed to the aircraft cabin structure 12 from pressurized air source in its open mode, and regulates the pressure of the forced air that is fed to aircraft cabin structure 12.First pressure transducer 38 is used to measure in air supply line 14, be positioned at the pressure in air supply valve 36 downstreams.
Ball valve 40 is arranged among the second portion 14b of air supply line 14, be positioned at the downstream part of air supply valve 36.Ball valve 40 also is installed on the traversing carriage 22.Ball valve 40 allows forced air is fed to the aircraft cabin structure 12 from pressurized air source in its open mode.In contrast, ball valve 40 is fed to aircraft cabin structure 12 at its closed condition interruption air from pressurized air source.
Air vent line 42 is from the second portion 14b branch of air supply line 14 and extend to air outlet 44, and this air outlet 44 is opened towards outside environment.44 places are provided with sound absorber 46 at air outlet, thereby in the generation that when air is discharged in aircraft cabin structure 12 inside, suppresses noise by air outlet 44.Electromagnetic air exhaust valve 48 is arranged in the air vent line 42.Bleed air valve 48 allows air is discharged to air outlet 44 from aircraft cabin structure 12 inside in its open mode, and regulates the pressure that is discharged to the air of air outlet 44 from aircraft cabin structure 12.
Second pressure transducer 50 also is installed on the traversing carriage 22.This second pressure transducer 50 is connected to aircraft cabin structure 12 inside by flexible duct 52.This sensor 50 is used for survey aircraft engine room structure 12 pressure inside, and will represent the signal of aircraft cabin structure 12 pressure inside to offer electronic control unit ECU.
This electronic control unit ECU is arranged to away from traversing carriage 22 and aircraft cabin structure to be tested, but is suitable for coming remote control air supply valve 36, ball valve 40 and bleed air valve 48 according to the signal that is provided by second pressure transducer 50.This electronic control unit ECU comprises a display unit, and---particularly show as shown in Figure 2, by second pressure transducer 50 measured aircraft cabin structure 12 pressure inside and the relation curve between the time---is shown to the operator with test parameter.Thereby this electronic control unit ECU is also as a personal-machine interface.This electronic control unit ECU is also connected to alerting signal output device 54, and this alerting signal output device 54 is suitable for a visual alerting signal of output and an audible ringing signal when receiving a corresponding alerting signal output order from electronic control unit ECU.
In order to carry out the test of aircraft cabin structure 12 leak detections, manual unlocking first isolation valve 16.Also open second isolation valve 18 and first selector valve 30 '.Then, forced air is fed to aircraft cabin structure 12 from pressurized air source, and wherein air supply valve 36 and ball valve 40 be by electronic control unit ECU control, thereby the pressure of guaranteeing the aircraft cabin inside configuration increases with 1.2 millibars/second speed.Forced air is being fed in the process of aircraft cabin structure 12, bleed air valve 48 remains in its closed condition.
When aircraft cabin structure 12 pressure inside (pressure reduction between environmental pressure and aircraft cabin structure 12 pressure inside) when having arrived 100 millibars first predeterminated level, this electronic control unit ECU provides an alerting signal output order to alerting signal output device 54, thereby, these alerting signal output device 54 a visual alerting signal of output and audible ringing signals.High-visible from Fig. 2, suitably to control air supply valve 36, ball valve 40 and bleed air valve 48 and 100 millibars first predetermined pressure level is kept one first predetermined amount of time by electronic control unit ECU, this first predetermined amount of time is about 1 minute.In first predetermined amount of time, can check aircraft cabin structure 12, thereby can easily detect the big leakage of aircraft cabin structure 12.
Behind first predetermined amount of time, aircraft cabin structure 12 pressure inside further increase with 1.2 millibars/second speed, up to second predetermined pressure level that reaches 400 millibars.Then, an alerting signal output order offers alerting signal output device 54 by electronic control unit ECU once more, and this alerting signal output device 54 is then exported a visual alerting signal and an audible ringing signal.By suitably controlling air supply valve 36, ball valve 40 and bleed air valve 48, aircraft cabin structure 12 pressure inside keep being about 8 minutes second predetermined amount of time at 400 millibars second predeterminated level.In second predetermined amount of time, can check aircraft cabin structure 12 once more, thereby also may detect aircraft cabin structure 12 unidentified little leakage that goes out in first predetermined amount of time.
Behind second predetermined amount of time, suitably control air supply valve 36, ball valve 40 and bleed air valve 48 and increase aircraft cabin structure 12 pressure inside once more by electronic control unit, up to the stress level that reaches 593 millibars.After this, pressure is advanced the speed and is reduced to 0.6 millibar/second, reaches 800 millibars the 3rd predeterminated level up to aircraft cabin structure 12 pressure inside.800 millibars the 3rd predetermined pressure level is far above aircraft normal flight 593 millibars the pressure reduction of being about that is applied on the aircraft cabin structure 12 in service.When aircraft cabin structure 12 pressure inside reach 800 millibars the 3rd predeterminated level, electronic control unit ECU provides an alerting signal output order for once more alerting signal output device 54, and this alerting signal output device 54 is exported a visual alerting signal and an audible ringing signal then.By suitably controlling air supply valve 36, ball valve 40 and bleed air valve 48, aircraft cabin structure 12 pressure inside keep the 3rd about 300 seconds predetermined amount of time on the 3rd stress level.
Behind the 3rd predetermined amount of time, air supply valve 36, ball valve 40 and bleed air valve 48 are controlled by an electronic control unit, and make aircraft cabin structure 12 pressure inside be reduced to 593 millibars the 4th predetermined pressure level with 1.2 millibars/second speed.As above mentioned, 593 millibars the 4th predetermined pressure level is corresponding to the aircraft normal flight pressure reduction that is applied on the aircraft cabin structure 12 in service.When aircraft cabin structure 12 pressure inside reach 593 millibars the 4th predetermined pressure level, close air supply valve 36, ball valve 40 and bleed air valve 48.The mode of operation of maintaining valve 36,40,48 is reduced to 500 millibars the 5th predeterminated level up to aircraft cabin structure 12 pressure inside.Only cause from 593 millibars of pressure reductions that are reduced to 500 millibars by the leakage of aircraft cabin structure 12.
When aircraft cabin structure 12 pressure inside are reduced to 500 millibars the 5th predeterminated level, electronic control unit ECU control air supply valve 36, ball valve 40 and bleed air valve 48 make aircraft cabin structure 12 pressure inside be reduced to environmental pressure from 500 millibars the 5th predeterminated level with 1.2 millibars/second speed.
Electronic control unit ECU is by time shown in Fig. 2 and the relation curve between the pressure, calculates the tangent slope at 556 millibars of pressure places between the 4th and the 5th predetermined pressure level, thereby calculates the leakage value of aircraft cabin structure 12.The leakage value of this calculating is compared with specified leakage value.If the leakage value of this calculating and the difference between the specified leakage value do not exceed predetermined limits, think that then the leakage characteristics of aircraft cabin structure 12 is adequate.
Claims (19)
1. one kind is used for aircraft cabin structure (12) the pressurization device (10) with the leakage that detects this aircraft cabin structure (12), and it comprises:
An air supply line (14), first end of this air supply line is connected to pressurized air source, and its second end is connected to this aircraft cabin structure (12), thereby forced air is supplied to this aircraft cabin structure (12) from pressurized air source;
An air supply valve (36), it is arranged in this air supply line (14);
A pressure transducer (50), this pressure transducer are used for this aircraft cabin structure (12) pressure inside of sensing, and are used to provide the signal of representing this aircraft cabin structure (12) internal pressure;
An air vent line (42), its first end are connected to this aircraft cabin structure (12), and its second end is connected to air outlet (44), thereby air is discharged to this air outlet (44) from this aircraft cabin structure (12) inside;
A bleed air valve (48), it is arranged in this air vent line (42); With
An electronic control unit (ECU), it is suitable for controlling this air supply valve (36) and this bleed air valve (48) according to the signal that this pressure transducer (50) provides, thereby forced air is fed in this aircraft cabin structure (12), reach first predetermined pressure level up to this aircraft cabin structure (12) inside, thereby this aircraft cabin structure (12) pressure inside is kept one first predetermined amount of time on this first predeterminated level, and after this air is discharged from this aircraft cabin structure (12) is inner.
2. device as claimed in claim 1, wherein said electronic control unit (ECU) also is suitable for controlling described air supply valve (36) and described bleed air valve (48) according to the signal that described pressure transducer (50) provides, thereby behind described first predetermined amount of time, and further forced air is being fed to the described aircraft cabin structure (12) before from the inner air of discharging of described aircraft cabin structure (12), reach second predetermined pressure level up to described aircraft cabin structure (12) inside, and this aircraft cabin structure (12) pressure inside kept one second predetermined amount of time on second predetermined pressure level, and after described second predetermined amount of time, further forced air is fed in the described aircraft cabin structure (12), reach the 3rd predetermined pressure level up to described aircraft cabin structure (12) inside, and described aircraft cabin structure (12) pressure inside is kept one the 3rd predetermined amount of time on described the 3rd predetermined pressure level.
3. device as claimed in claim 1, wherein said electronic control unit (ECU) also is suitable for controlling described air supply valve (36) and described bleed air valve (48) according to the signal that described pressure transducer (50) provides, thereby from the inner air of discharging of described aircraft cabin structure (12), up to reaching the 4th predetermined pressure level, and described air supply valve (36) and described bleed air valve (48) remained on its closed condition, up to reaching the 5th predetermined pressure level.
4. device as claimed in claim 3, wherein said electronic control unit (ECU) also are suitable for being reduced to the leakage value that the 5th predeterminated level calculates described aircraft cabin structure (12) according to described aircraft cabin structure (12) pressure inside from the 4th predeterminated level.
5. as each described device in the claim 1 to 4, further comprise an alerting signal output device (54), when receiving corresponding alerting signal output order from described electronic control unit (ECU), described alerting signal output device is suitable for exporting a vision and/or audible ringing signal.
6. as each described device in the claim 1 to 4, further comprise a ball valve (40), described ball valve is arranged on the downstream that described air supply line (14) is interior, be positioned at described air supply valve (36).
7. as each described device in the claim 1 to 4, the part (14b) of wherein said air supply line (14) and/or described air supply valve (36) and/or described pressure transducer (50) and/or described bleed air valve (48) and/or described ball valve (40) are installed in one movably on the support (22).
8. one kind is used for aircraft cabin structure (12) is pressurizeed with the device (10) of the leakage that detects this aircraft cabin structure (12), and it comprises:
An air supply line (14), first end of this air supply line is connected to pressurized air source, and its second end is connected to this aircraft cabin structure (12), thereby forced air is supplied to this aircraft cabin structure (12) from pressurized air source;
An air supply valve (36), it is arranged in this air supply line (14);
A pressure transducer (50), this pressure transducer are used for this aircraft cabin structure (12) pressure inside of sensing, and are used to provide the signal of representing this aircraft cabin structure (12) internal pressure;
An air vent line (42), its first end are connected to this aircraft cabin structure (12), and its second end is connected to air outlet (44), thereby air is discharged to this air outlet (44) from this aircraft cabin structure (12) inside;
A bleed air valve (48), it is arranged in this air vent line (42);
At least one pressure program and
An electronic control unit (ECU), it the signal that provides according to this pressure transducer (50) is provided and controls this air supply valve (36) and this bleed air valve (48) according to the setting value in this pressure program, thereby forced air is fed in this aircraft cabin structure (12) or air is discharged from this aircraft cabin structure (12), thereby control this aircraft cabin structure (12) pressure inside according to this pressure program.
9. device as claimed in claim 8 wherein is provided with a plurality of pressure programs for different type of airplanes and different test specifications.
10. install as claimed in claim 8 or 9, wherein said electronic control unit (ECU) also is suitable for selecting, controls and/or revise a pressure program.
11. install as claimed in claim 8 or 9, wherein said electronic control unit (ECU) also is suitable for providing the scheme of a measuring process, it includes a value of representing cabin leakage.
12. be used for aircraft cabin structure (12) the pressurization method with the leakage that detects this aircraft cabin structure (12), it comprises the steps:
Forced air is fed to this aircraft cabin structure (12) from pressurized air source via air supply line (14);
By this aircraft cabin structure (12) pressure inside of pressure transducer (50) sensing and the signal of representing this aircraft cabin structure (12) internal pressure is provided;
Air is discharged to air outlet (44) from this aircraft cabin structure (12) is inner via air vent line (42);
The signal that provides according to this pressure transducer (50) by electronic control unit (ECU) come control setting in this air supply line (14) air supply valve (36) and be arranged on bleed air valve (48) in this air vent line (42), thereby forced air is fed in this aircraft cabin structure (12), reach first predetermined pressure level up to this aircraft cabin structure (12) inside, and this aircraft cabin structure (12) pressure inside is kept one first predetermined amount of time on first predeterminated level, and after this air is being discharged from this aircraft cabin structure (12) is inner.
13. method as claimed in claim 12, the described air supply valve of signal controlling (36) that provides according to described pressure transducer (50) by described electronic control unit (ECU) and the step of described bleed air valve (48) also are provided, thereby after described first predetermined amount of time, and further forced air is being fed to the described aircraft cabin structure (12) before from the inner air of discharging of described aircraft cabin structure (12), reach second predetermined pressure level up to described aircraft cabin structure (12) inside, described aircraft cabin structure (12) pressure inside is kept one second predetermined amount of time on second predeterminated level, behind second predetermined amount of time, further forced air is fed in the described aircraft cabin structure (12), reach the 3rd predetermined pressure level up to described aircraft cabin structure (12) inside, and described aircraft cabin structure (12) pressure inside is kept one the 3rd predetermined amount of time on the 3rd predeterminated level.
14. as claim 12 or 13 described methods, the described air supply valve of signal controlling (36) that provides according to described pressure transducer (50) by described electronic control unit (ECU) and the step of described bleed air valve (48) also are provided, thereby air is discharged from described aircraft cabin structure (12), up to reaching the 4th predetermined pressure level, described air supply valve (36) and described bleed air valve (48) are remained on its closed condition, up to reaching the 5th predetermined pressure level.
15. method as claimed in claim 14 also comprises by described electronic control unit (ECU) and reduces the step of calculating described aircraft cabin structure (12) leakage value according to the internal pressure of described aircraft cabin structure (12) from the pressure that the 4th predetermined pressure level is reduced to the 5th predetermined pressure level.
16. be used for making the method for aircraft cabin structure (12) pressurization with the leakage that detects this aircraft cabin structure (12), it may further comprise the steps:
Forced air is fed to this aircraft cabin structure (12) from pressurized air source via air supply line (14);
By this aircraft cabin structure (12) pressure inside of pressure transducer (50) sensing and the signal of representing this aircraft cabin structure (12) internal pressure is provided;
Air is discharged to air outlet (44) from this aircraft cabin structure (12) is inner via air vent line (42);
Provide a pressure program and
The signal that provides according to this pressure transducer (50) by electronic control unit (ECU) and according to the setting value in this pressure program come control setting in this air supply line (14) air supply valve (36) and be arranged on bleed air valve (48) in this air vent line (42), thereby forced air is fed in this aircraft cabin structure (12) or air is discharged from this aircraft cabin structure (12), thereby control this aircraft cabin structure (12) pressure inside according to this pressure program.
17. method as claimed in claim 16 wherein is provided with a plurality of pressure programs for different type of airplanes and different test specifications.
18., further comprise the step of selecting, control and/or revise the pressure program by described electronic control unit (ECU) as claim 16 or 17 described methods.
19. as claim 16 or 17 described methods, further comprise the step that a measuring process scheme is provided by described electronic control unit (ECU), this scheme comprises a value of representing this cabin leakage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100833082A CN100559142C (en) | 2006-05-31 | 2006-05-31 | Engine room structure is pressurizeed to detect the device and method of its leakage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100833082A CN100559142C (en) | 2006-05-31 | 2006-05-31 | Engine room structure is pressurizeed to detect the device and method of its leakage |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101082532A CN101082532A (en) | 2007-12-05 |
| CN100559142C true CN100559142C (en) | 2009-11-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNB2006100833082A Expired - Fee Related CN100559142C (en) | 2006-05-31 | 2006-05-31 | Engine room structure is pressurizeed to detect the device and method of its leakage |
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| CN (1) | CN100559142C (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101666701B (en) * | 2009-09-07 | 2012-09-05 | 安徽省芜湖仪器仪表研究所 | Device and method for detecting air leakage rate of container |
| FR2965052B1 (en) * | 2010-09-17 | 2013-07-26 | Airbus Operations Sas | DEVICE FOR REALIZING TESTS ON AT LEAST ONE FLUID NETWORK OF AN AIRCRAFT |
| CN104989702A (en) * | 2015-06-30 | 2015-10-21 | 中国人民解放军总装备部军械技术研究所 | Hydraulic testing method for radar hydraulic cylinder |
| CN112484935B (en) * | 2020-10-27 | 2023-09-19 | 潍柴动力股份有限公司 | System and method for detecting leakage of hydrogen filling of vehicle |
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| CN101082532A (en) | 2007-12-05 |
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