CN110531683A - Aircraft skin valve monitoring device and method - Google Patents
Aircraft skin valve monitoring device and method Download PDFInfo
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- CN110531683A CN110531683A CN201910900388.3A CN201910900388A CN110531683A CN 110531683 A CN110531683 A CN 110531683A CN 201910900388 A CN201910900388 A CN 201910900388A CN 110531683 A CN110531683 A CN 110531683A
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- 238000000034 method Methods 0.000 title claims abstract description 48
- 238000012806 monitoring device Methods 0.000 title claims abstract description 27
- 238000012544 monitoring process Methods 0.000 claims abstract description 47
- 238000006073 displacement reaction Methods 0.000 claims abstract description 23
- 230000008569 process Effects 0.000 claims description 28
- 230000008676 import Effects 0.000 claims description 8
- 238000004364 calculation method Methods 0.000 claims description 6
- 230000008901 benefit Effects 0.000 abstract description 5
- 238000012423 maintenance Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 6
- 238000001816 cooling Methods 0.000 description 5
- 238000012360 testing method Methods 0.000 description 4
- 238000004458 analytical method Methods 0.000 description 3
- 238000002955 isolation Methods 0.000 description 3
- 238000012937 correction Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000284 extract Substances 0.000 description 2
- 238000000605 extraction Methods 0.000 description 2
- 238000009423 ventilation Methods 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 238000013475 authorization Methods 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
- 238000013024 troubleshooting Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- 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
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- G—PHYSICS
- G08—SIGNALLING
- G08B—SIGNALLING OR CALLING SYSTEMS; ORDER TELEGRAPHS; ALARM SYSTEMS
- G08B21/00—Alarms responsive to a single specified undesired or abnormal condition and not otherwise provided for
- G08B21/18—Status alarms
- G08B21/187—Machine fault alarms
-
- G—PHYSICS
- G08—SIGNALLING
- G08C—TRANSMISSION SYSTEMS FOR MEASURED VALUES, CONTROL OR SIMILAR SIGNALS
- G08C17/00—Arrangements for transmitting signals characterised by the use of a wireless electrical link
- G08C17/02—Arrangements for transmitting signals characterised by the use of a wireless electrical link using a radio link
-
- 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
Abstract
The present invention relates to a kind of aircraft skin valve monitoring devices, including sequentially connected collector (21), processor (22) and memory (23), collector (21) is also connected with outlet valve angular displacement sensor (24) and inlet valve angular displacement sensor (25), processor (22) includes: data obtaining module, information at the time of for obtaining outlet valve standard-sized sheet position, the full off-position of outlet valve, the half-open ring status of outlet valve, inlet valve standard-sized sheet position and inlet valve full off-position；Characteristic value calculating module obtains characteristic value for calculating inlet valve actuation duration and outlet valve actuation duration；Trend monitoring module is alarmed for monitoring characteristic value in real time when characteristic value is more than preset range.Compared with prior art, the present invention is by the method for trend monitoring, and the forecast before having effectively achieved valve failure has many advantages, such as that accuracy is high, reduces aircraft operation risk, improves the working efficiency of maintenance and reduce maintenance cost.
Description
Technical field
The present invention relates to airborne system and methods, more particularly, to a kind of aircraft skin valve monitoring device and method.
Background technique
The main electron cabin computer equipment offer cooling of electronic compartment ventilating system, one as electronic compartment ventilating system
Important component, aircraft electronic cabin ventilating system there are three types of working morphology, respectively open loop form, closed loop form and intermediary,
According to environment temperature and aircraft air-ground form etc., electronic compartment ventilating operation is in different forms.
Under open loop form, covering air intlet valve and outlet valve are fully opened, and outside air passes through covering air
Inlet valve is sucked by blower fan, after being all kinds of electronic electric equipments heat dissipations of electronic compartment, cockpit, then is extracted out by extraction fan, is passed through
Covering air outlet slit valve is discharged to outside machine.
Under closed loop form, covering air intlet valve and outlet valve are completely closed, and covering heat exchange Isolation Valve is beaten
It opens, covering heat exchange import bypass flap opening when pressure electric switch detects 1 correct pressure/air-flow in system, in order to
Noise covering heat exchange outlet bypass flap is reduced to open.Air only inside recycle, circulation air via covering heat exchange every
Enter in covering heat exchanger from valve and is cooled, it is then cooling for electronics chamber device again.
Under semi-loop form, covering air intlet valve is completely closed, and covering air outlet slit valve partially opens, covering heat
Exchange Isolation Valve opening, covering heat exchange import bypass flap detect 1 correct pressure/gas in system in pressure electric switch
It opens when stream, is opened to reduce noise covering heat exchange outlet bypass flap.Cooling air is portion after electronics chamber device is cooling
Divide outside discharge machine, partially enter in covering heat exchanger via covering heat exchange Isolation Valve and be cooled, is then again electronics
Chamber device is cooling.
Covering outlet valve is in the downstream of entire electronic compartment ventilating system, such as could not normally close in takeoff phase or in the air
It closes, it will cause main cabin that can not establish normal CAB PRFS, in past three year, certain airline's fleet electronic compartment ventilating system is covered
Skin exports the failures such as valve card resistance, and a lot of make a return voyage is caused to make preparation for dropping, and the abnormal event such as slides back to.It at present can only to the monitoring of covering valve
It is realized by AIRMAN, AIRMAN monitoring is the mode that post-event alarm mode i.e. failsafe is not alarmed, and be can not achieve in advance pre-
It is alert, need to research and develop a kind of covering valve trend monitoring method thus to realize the forecast before valve failure.
Trend monitoring is carried out to covering valve and needs to obtain valve status information, in the prior art, is carried on aircraft
Electronic compartment ventilating system is equipped with switching circuit, can be controlled valve and can be obtained the status information of valve.Valve has had
Open, partially open entirely, completely closing three positions, fully open position is controlled by S1 and S2 and is indicated, partially open by
S3 and S4 is controlled and is indicated, fully closed position controls by S5 and S6 and indicated, S1, S3 and S5 are braking electric switch, S2, S4
It is instruction electric switch with S6.If obtaining the status information of valve using the switching circuit, the reliability of each electric switch is of crucial importance,
Electric switch generally comprises three contacts: common end, normally opened contact and normally-closed contact, these three contacts are easy to produce electric corruption using long
Erosion is easy to cause the generation of fault-signal so that contact resistance becomes larger or unstable；Also, instruction electric switch generally uses machinery
Formula microswitch is based on valve state and is acted, and often appearance movement is ineffective in use for mechanical microswitch
The defects of quick, work unreliable, signal designation mistake；Furthermore it obtains valve status information by electronic compartment ventilating system also to deposit
In the risks such as signal transmission delay or display failure, therefore, work is obtained by electronic compartment ventilating system by what is carried on aircraft
Risk existing for the status information of door is more, and reliability is low.
In addition, the patent of invention that Authorization Notice No. is CN104340368B discloses a kind of prison of anti-icing valve of aircraft wing
Control system and method.The monitoring system of the anti-icing valve of a kind of aircraft wing, comprising: time recording device records anti-icing
The time that valve opens or closes；Data acquisition facility, obtain the time recording device record anti-icing valve opening or
The time of closing；Message generating means, it is the time that anti-icing valve opens or closes according to acquired in data acquisition facility, raw
At anti-icing valve performance message；Anti-icing valve capability evaluating device receives the anti-icing valve performance message, according to anti-icing work
Anti-icing valve in door performance message opens or closes the time, assesses the performance of the anti-icing valve, wherein the anti-icing valve
Performance message includes that the revised anti-icing valve opens or closes the time, and wherein correction formula is as follows:
Time+(a* (PD)+b) before time=amendment after amendment
Wherein, PD indicates bleed air pressure, and a and b are corrected parameters.
The time that the anti-icing valve of the monitoring system opens or closes needs to be modified based on bleed air pressure, increases monitoring
The complexity of system, and the accuracy of correction result depends on the correct setting of corrected parameter, and increasing influences the monitoring system
The factor for reliability of uniting.To sum up, which haves the defects that complexity height and reliability are low.
And when there is only open loop forms and closed loop form for the valve of electronic compartment ventilating system, there is also half-open annulars
State, above-mentioned monitoring system is only counted and open loop form and closed loop form, when monitoring above-mentioned electronic compartment ventilating system, will because of its half
Open loop form generates wrong report.
Summary of the invention
It is an object of the present invention to overcome the above-mentioned drawbacks of the prior art and provide the aircrafts that can be alarmed in advance
Covering valve monitoring device and method.
The purpose of the present invention can be achieved through the following technical solutions:
A kind of aircraft skin valve monitoring device, including sequentially connected collector, processor and memory, the acquisition
Device connect electronic compartment ventilating system, electronic compartment ventilating system be equipped with switching circuit, can detect covering valve be in standard-sized sheet position,
Information at the time of full off-position and half-open ring status, the collector obtain outlet valve standard-sized sheet position, the full off-position of outlet valve, into
Information at the time of mouthful valve standard-sized sheet position, the full off-position of inlet valve and outlet valve half-open ring status, the processor include:
Characteristic value calculating module obtains characteristic value for calculating inlet valve actuation duration and outlet valve actuation duration；
Trend monitoring module is alarmed for monitoring characteristic value in real time when characteristic value is more than preset range.
Further, the collector and memory are integrated in wireless quick access recorder, quickly access that this is wireless
Logger connects processor.
The present invention also provides a kind of aircraft skin valve monitoring device, including sequentially connected collector, processor and deposit
Reservoir, the collector are also connected with the full off-position sensing of data obtaining module, outlet valve standard-sized sheet level sensor, outlet valve
Device, inlet valve standard-sized sheet level sensor and the full off-position sensor of inlet valve, the data obtaining module connection electronic compartment ventilation
System, information at the time of for obtaining outlet valve half-open ring status, the processor include:
Characteristic value calculating module obtains characteristic value for calculating inlet valve actuation duration and outlet valve actuation duration；
Trend monitoring module is alarmed for monitoring characteristic value in real time when characteristic value is more than preset range.
Further, the outlet valve standard-sized sheet level sensor, the full off-position sensor of outlet valve, inlet valve standard-sized sheet position
Sensor and the full off-position sensor of inlet valve are photosensitive sensor.
Further, the collector and memory are integrated in wireless quick access recorder, quickly access that this is wireless
Logger connects processor.
The present invention also provides a kind of aircraft skin valve monitoring device, including sequentially connected collector, processor and deposit
Reservoir, the collector are also connected with outlet valve angular displacement sensor and inlet valve angular displacement sensor, the processor
Include:
Data obtaining module, for obtaining outlet valve standard-sized sheet from the data that outlet valve angular displacement sensor transmits
Information at the time of position, the full off-position of outlet valve and outlet valve half-open ring status；It is transmitted from inlet valve angular displacement sensor
Information at the time of obtaining inlet valve standard-sized sheet position and the full off-position of inlet valve in data；
From angular displacement sensor acquisition time information specifically, in the signal that angular displacement sensor transmits, the smallest angle
Corresponding full off-position, maximum angle correspond to full off-position, remaining angle corresponds to half-open ring status, and at the time of be separately added into corresponding i.e.
Information at the time of obtaining to be obtained.
Characteristic value calculating module obtains characteristic value for calculating inlet valve actuation duration and outlet valve actuation duration；
Trend monitoring module is alarmed for monitoring characteristic value in real time when characteristic value is more than preset range.
Further, the collector and memory are integrated in wireless quick access recorder, quickly access that this is wireless
Logger connects processor.
The present invention also provides a kind of aircraft skin valve monitoring method using above-mentioned aircraft skin valve monitoring device, packets
Include following steps:
Information acquiring step: processor extracts outlet valve standard-sized sheet position from the data that collector obtains in real time, outlet is lived
Information at the time of door Quan Guanwei, inlet valve standard-sized sheet position, the full off-position of inlet valve and outlet valve half-open ring status；
Characteristic value calculates step: information at the time of processor is based on obtaining, and calculates inlet valve actuation duration and outlet is lived
Door actuation duration obtains characteristic value, and stores into memory；
Trend monitoring step: processor monitors calculated characteristic value in real time, and with the highest threshold value that pre-sets and minimum
Threshold comparison, characteristic value is higher than highest threshold value if it exists, then issues outlet jump alarm, characteristic value is lower than minimum threshold if it exists
Value then issues import jump alarm, does not otherwise alarm.
Further, the characteristic value includes that valve standard-sized sheet is closed entirely to the full characteristic value for closing process and valve to standard-sized sheet process
Characteristic value.
Further, characteristic value calculation expression of the valve standard-sized sheet to full pass process are as follows:
Δ T=T1-T2-TFPO
T1=TFc1-TFo1
T2=TFc2-TFo2
In formula, Δ T is characterized value, T1For outlet valve standard-sized sheet to the full actuation duration for closing process, T2For inlet valve standard-sized sheet
To the full actuation duration for closing process, TFPOFor in outlet valve standard-sized sheet to the full semi-loop duration for closing process, TFc1To export valve
At the time of full pass, TFo1At the time of to export valve standard-sized sheet, TFc2At the time of being closed entirely for inlet valve, TFo2For inlet valve standard-sized sheet
At the time of；
The valve closes the characteristic value calculation expression to standard-sized sheet process entirely are as follows:
Δ T=T3-T4-TFPO
T3=TFo1-TFc1
T4=TFo2-TFc2
In formula, T3 is to export valve to close the actuation duration for arriving standard-sized sheet process entirely, and T4 is that inlet valve is closed entirely to standard-sized sheet process
Actuation duration.
Compared with prior art, the invention has the following advantages that
(1) present invention is substantially uniform using each outlet valve and inlet valve actuation duration, there is only small difference,
And the difference is constant the reasonable section the characteristics of, passes through and obtains outlet valve standard-sized sheet position, the full off-position of outlet valve, import
Information at the time of valve standard-sized sheet position, the full off-position of inlet valve and outlet valve half-open ring status, seeks outlet valve and import is living
Door actuation duration, and ask poor, characteristic value is obtained, is that valve performance fails if this feature value exceeds preset range
Sign, therefore the present invention can forecast by the method for trend monitoring, before having effectively achieved valve failure.
(2) present invention provides not only the monitoring device that time information is obtained by electronic compartment ventilating system, is also provided with
By photosensitive sensor or angular displacement sensor, the device that valve is monitored is directly acted on, failure is greatly reduced may
The approach of generation, and sensor generally has reliable performance, the high advantage of accuracy in detection is supervised compared to by circuit
Control has significant advantage.
(3) present invention is monitored valve by placement sensor, has and occupies little space, and accuracy in detection is high, letter
Breath obtains comprehensive advantage.
(4) reduce operation risk: the present invention can continue monitoring valve working condition, can the valve to performance degradation pacify in time
Row reduces and makes a return voyage caused by valve failure.
(5) working efficiency is improved, reduce maintenance cost: the present invention only need to carry out statistics and analysis, energy to the data of storage
Accurately know which valve breaks down, loss caused by erroneous judgement part is accidentally torn in reduction open.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of 1 aircraft skin valve monitoring device of the embodiment of the present invention；
Fig. 2 is the structural schematic diagram of 2 aircraft skin valve monitoring device of the embodiment of the present invention；
Fig. 3 is the structural schematic diagram of 3 aircraft skin valve monitoring device of the embodiment of the present invention；
Fig. 4 is the flow diagram of aircraft skin valve monitoring method of the present invention；
Fig. 5 is the valve monitoring data schematic diagram of the embodiment of the present invention 4；
Fig. 6 is the schematic diagram that the embodiment of the present invention 4 carries out valve monitoring data Eigenvalues analysis.
Specific embodiment
The present invention is described in detail with specific embodiment below in conjunction with the accompanying drawings.The present embodiment is with technical solution of the present invention
Premised on implemented, the detailed implementation method and specific operation process are given, but protection scope of the present invention is not limited to
Following embodiments.
Embodiment 1
As shown in Figure 1, the present embodiment is a kind of aircraft skin valve monitoring device, apply on A320 aircraft, the monitoring
Device includes sequentially connected collector 1, processor 2 and memory 3, and collector 1 connects electronic compartment ventilating system, the electricity of A320
Sub- cabin ventilating system is calculated by blower fan, extraction fan, covering air intlet valve, covering air outlet slit valve, electronic compartment ventilation
The main components such as machine (AEVC) composition, electronic compartment divulge information computer equipped with switching circuit, can detect covering valve and be in complete
Information at the time of open position, Quan Guanwei and half-open ring status, collector 1 obtain outlet valve standard-sized sheet position, the full off-position of outlet valve,
Information at the time of inlet valve standard-sized sheet position, the full off-position of inlet valve and outlet valve half-open ring status.
Processor 2 includes:
Characteristic value calculating module obtains characteristic value for calculating inlet valve actuation duration and outlet valve actuation duration；
Trend monitoring module is alarmed for monitoring characteristic value in real time when characteristic value is more than preset range.
The present embodiment processor 2 is a kind of CPU.
The present embodiment collector 1 and memory 3 are integrated in wireless quick access recorder, this is wireless quickly to access record
Device connects processor 2.
Embodiment 2
As shown in Fig. 2, the present embodiment is a kind of aircraft skin valve monitoring device, apply on A320 aircraft, the monitoring
Device includes sequentially connected collector 11, processor 12 and memory 13, and the collector 11 is also connected with acquisition of information mould
Block 14, outlet valve standard-sized sheet level sensor 15, the full off-position sensor 16 of outlet valve, inlet valve standard-sized sheet level sensor 17 and into
The mouth full off-position sensor 18 of valve, data obtaining module 14 connect electronic compartment ventilating system, for obtaining outlet valve semi-loop
Information at the time of state.
It exports valve standard-sized sheet level sensor 15 to be arranged in electronic compartment, face exports the standard-sized sheet position of valve.
It exports the full off-position sensor 16 of valve to be arranged in electronic compartment, face exports the full off-position of valve.
Inlet valve standard-sized sheet level sensor 17 is arranged in electronic compartment, the standard-sized sheet position of face inlet valve.
The full off-position sensor 18 of inlet valve is arranged in electronic compartment, the full off-position of face inlet valve.
Export valve standard-sized sheet level sensor 15, the full off-position sensor 16 of outlet valve, inlet valve standard-sized sheet level sensor 17
It is photosensitive sensor with the full off-position sensor 18 of inlet valve, the present embodiment is all made of infrared sensor.
Processor 12 includes:
Characteristic value calculating module obtains characteristic value for calculating inlet valve actuation duration and outlet valve actuation duration；
Trend monitoring module is alarmed for monitoring characteristic value in real time when characteristic value is more than preset range.
The present embodiment processor 2 is a kind of CPU.
The present embodiment collector 11 and memory 13 are integrated in wireless quick access recorder, this is wireless quickly to access note
It records device and connects processor 12.
Embodiment 3
As shown in figure 3, the present embodiment is a kind of aircraft skin valve monitoring device, apply on A320 aircraft, the monitoring
Device includes sequentially connected collector 21, processor 22 and memory 23, and collector 21 is also connected with outlet valve angular displacement
Sensor 24 and inlet valve angular displacement sensor 25.
Outlet valve angular displacement sensor 24 is arranged on the doorframe of outlet valve, outlet valve angular displacement sensor 24
Test side is fixedly connected with the rotary shaft of outlet valve, and test side is rotated with the rotation of rotary shaft.
Inlet valve angular displacement sensor 25 is arranged on the doorframe of inlet valve, inlet valve angular displacement sensor 25
Test side is fixedly connected with the rotary shaft of inlet valve, and test side is rotated with the rotation of rotary shaft.
Processor 22 includes:
Data obtaining module, for obtaining outlet valve standard-sized sheet from the data that outlet valve angular displacement sensor 24 transmits
Information at the time of position, the full off-position of outlet valve and outlet valve half-open ring status；It is transmitted from inlet valve angular displacement sensor 25
Data in information at the time of obtain inlet valve standard-sized sheet position and inlet valve full off-position；
From angular displacement sensor acquisition time information specifically, in the signal that angular displacement sensor transmits, the smallest angle
Corresponding full off-position, maximum angle correspond to full off-position, remaining angle corresponds to half-open ring status, and at the time of be separately added into corresponding i.e.
Information at the time of obtaining to be obtained.
Characteristic value calculating module obtains characteristic value for calculating inlet valve actuation duration and outlet valve actuation duration；
Trend monitoring module is alarmed for monitoring characteristic value in real time when characteristic value is more than preset range.
The present embodiment processor 2 is a kind of CPU.
The present embodiment collector 21 and memory 23 are integrated in wireless quick access recorder, this is wireless quickly to access note
It records device and connects processor 22.
Embodiment 4
As shown in figure 4, the present embodiment is a kind of aircraft skin valve monitoring method, apply on A320 aircraft, the monitoring
Method the following steps are included:
Information acquiring step S1: processor extracts outlet valve standard-sized sheet position, outlet from the data that collector obtains in real time
Information at the time of the full off-position of valve, inlet valve standard-sized sheet position, the full off-position of inlet valve and outlet valve half-open ring status；
Characteristic value calculates step S2: information at the time of processor is based on obtaining calculates inlet valve actuation duration and outlet
Valve actuation duration obtains characteristic value, and stores into memory；
Trend monitoring step S3: processor monitors calculated characteristic value in real time, and with the highest threshold value pre-seted and most
Low threshold comparison, characteristic value is higher than highest threshold value if it exists, then issues outlet jump alarm, characteristic value is lower than minimum threshold if it exists
Value then issues import jump alarm, does not otherwise alarm.
It includes that valve standard-sized sheet is closed entirely to the full characteristic value for closing process and valve to complete that characteristic value, which calculates the characteristic value in step,
The characteristic value of open procedure.
Characteristic value calculation expression of the valve standard-sized sheet to full pass process are as follows:
Δ T=T1-T2-TFPO
T1=TFc1-TFo1
T2=TFc2-TFo2
In formula, Δ T is characterized value, T1For outlet valve standard-sized sheet to the full actuation duration for closing process, T2For inlet valve standard-sized sheet
To the full actuation duration for closing process, TFPOFor in outlet valve standard-sized sheet to the full semi-loop duration for closing process, TFc1To export valve
At the time of full pass, TFo1At the time of to export valve standard-sized sheet, TFc2At the time of being closed entirely for inlet valve, TFo2For inlet valve standard-sized sheet
At the time of.
Valve closes the characteristic value calculation expression to standard-sized sheet process entirely are as follows:
Δ T=T3-T4-TFPO
T3=TFo1-TFc1
T4=TFo2-TFc2
In formula, T3 is to export valve to close the actuation duration for arriving standard-sized sheet process entirely, and T4 is that inlet valve is closed entirely to standard-sized sheet process
Actuation duration.
As shown in figure 5, to be monitored using aircraft skin valve monitoring method of the present invention to A320 aircraft skin valve
For valve standard-sized sheet to the full characteristic value for closing process as a result, the FO in figure is standard-sized sheet, FC is complete closes afterwards.
As shown in fig. 6, be an actual period at the time of in figure, during the primary monitoring on A320 aircraft,
For the highest threshold value set as 4, lowest threshold is -4, and characteristic value the jump of outlet valve occurs the 14th moment, has issued out
Mouth jump alarm, and there is inlet valve jump the 15th moment, have issued import jump alarm.It is landed in aircraft
Afterwards, troubleshooting has been carried out to the valve alarmed immediately, has effectively prevented the generation of valve failure.
The preferred embodiment of the present invention has been described in detail above.It should be appreciated that those skilled in the art without
It needs creative work according to the present invention can conceive and makes many modifications and variations.Therefore, all technologies in the art
Personnel are available by logical analysis, reasoning, or a limited experiment on the basis of existing technology under this invention's idea
Technical solution, all should be within the scope of protection determined by the claims.
Claims (10)
1. a kind of aircraft skin valve monitoring device, including sequentially connected collector (1), processor (2) and memory (3),
It is characterized in that, the collector (1) connects electronic compartment ventilating system, the collector (1) obtains outlet valve standard-sized sheet position, goes out
Information at the time of the full off-position of mouthful valve, inlet valve standard-sized sheet position, the full off-position of inlet valve and outlet valve half-open ring status, it is described
Processor (2) includes:
Characteristic value calculating module obtains characteristic value for calculating inlet valve actuation duration and outlet valve actuation duration；
Trend monitoring module is alarmed for monitoring characteristic value in real time when characteristic value is more than preset range.
2. a kind of aircraft skin valve monitoring device according to claim 1, which is characterized in that the collector (1) and
Memory (3) is integrated in wireless quick access recorder, quick access recorder connection processor (2) that this is wireless.
3. a kind of aircraft skin valve monitoring device, including sequentially connected collector (11), processor (12) and memory
(13), which is characterized in that the collector (11) is also connected with data obtaining module (14), outlet valve standard-sized sheet level sensor
(15), the full off-position sensor (16) of outlet valve, inlet valve standard-sized sheet level sensor (17) and the full off-position sensor of inlet valve
(18), the data obtaining module (14) connects electronic compartment ventilating system, at the time of for obtaining outlet valve half-open ring status
Information, the processor (12) include:
Characteristic value calculating module obtains characteristic value for calculating inlet valve actuation duration and outlet valve actuation duration；
Trend monitoring module is alarmed for monitoring characteristic value in real time when characteristic value is more than preset range.
4. a kind of aircraft skin valve monitoring device according to claim 3, which is characterized in that the outlet valve standard-sized sheet
Level sensor (15), the full off-position sensor (16) of outlet valve, inlet valve standard-sized sheet level sensor (17) and inlet valve close entirely
Level sensor (18) is photosensitive sensor.
5. a kind of aircraft skin valve monitoring device according to claim 3, which is characterized in that the collector (11) and
Memory (13) is integrated in wireless quick access recorder, quick access recorder connection processor (12) that this is wireless.
6. a kind of aircraft skin valve monitoring device, including sequentially connected collector (21), processor (22) and memory
(23), which is characterized in that the collector (21) is also connected with outlet valve angular displacement sensor (24) and inlet valve angle position
Displacement sensor (25), the processor (22) include:
Data obtaining module, for obtaining outlet valve standard-sized sheet from the data that outlet valve angular displacement sensor (24) is transmitted
Information at the time of position, the full off-position of outlet valve and outlet valve half-open ring status；It is passed from inlet valve angular displacement sensor (25)
Information at the time of obtaining inlet valve standard-sized sheet position and the full off-position of inlet valve in defeated data；
Characteristic value calculating module obtains characteristic value for calculating inlet valve actuation duration and outlet valve actuation duration；
Trend monitoring module is alarmed for monitoring characteristic value in real time when characteristic value is more than preset range.
7. a kind of aircraft skin valve monitoring device according to claim 6, which is characterized in that the collector (21) and
Memory (23) is integrated in wireless quick access recorder, quick access recorder connection processor (22) that this is wireless.
8. it is a kind of using claim 1 or 3 or the aircraft skin valve monitoring method of the 6 aircraft skin valve monitoring devices,
Characterized by comprising the following steps:
Information acquiring step: processor extracted from the data that collector obtains in real time outlet valve standard-sized sheet position, outlet valve it is complete
Information at the time of off-position, inlet valve standard-sized sheet position, the full off-position of inlet valve and outlet valve half-open ring status；
Characteristic value calculates step: information at the time of processor is based on obtaining, and calculates inlet valve actuation duration and outlet valve is made
Dynamic duration obtains characteristic value, and stores into memory；
Trend monitoring step: processor monitors calculated characteristic value in real time, and with the highest threshold value and lowest threshold that pre-set
Comparison, characteristic value is higher than highest threshold value if it exists, then issues outlet jump alarm, characteristic value is lower than lowest threshold if it exists, then
Import jump alarm is issued, is not otherwise alarmed.
9. a kind of aircraft skin valve monitoring method according to claim 8, which is characterized in that the characteristic value includes living
Door standard-sized sheet closes the characteristic value to standard-sized sheet process to the full characteristic value for closing process and valve entirely.
10. a kind of aircraft skin valve monitoring method according to claim 9, which is characterized in that the valve standard-sized sheet arrives
The full characteristic value calculation expression for closing process are as follows:
Δ T=T1-T2-TFPO
T1=TFc1-TFo1
T2=TFc2-TFo2
In formula, Δ T is characterized value, T1For outlet valve standard-sized sheet to the full actuation duration for closing process, T2It is inlet valve standard-sized sheet to entirely
The actuation duration of pass process, TFPOFor in outlet valve standard-sized sheet to the full semi-loop duration for closing process, TFc1It is closed entirely for outlet valve
At the time of, TFo1At the time of to export valve standard-sized sheet, TFc2At the time of being closed entirely for inlet valve, TFo2For inlet valve standard-sized sheet when
It carves；
The valve closes the characteristic value calculation expression to standard-sized sheet process entirely are as follows:
Δ T=T3-T4-TFPO
T3=TFo1-TFc1
T4=TFo2-TFc2
In formula, T3 is to export valve to close the actuation duration for arriving standard-sized sheet process entirely, and T4 is that inlet valve closes the work for arriving standard-sized sheet process entirely
Dynamic duration.
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| CN201910900388.3A CN110531683A (en) | 2019-09-23 | 2019-09-23 | Aircraft skin valve monitoring device and method |
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| CN104340368A (en) * | 2013-07-24 | 2015-02-11 | 中国国际航空股份有限公司 | Aircraft wing anti-icing valve monitoring system and method |
| US20170060125A1 (en) * | 2014-02-21 | 2017-03-02 | Taleris Global Llp | Method for diagnosing a fault in an air-conditioning pack of an aircraft |
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