CN110531683B - Aircraft skin valve monitoring device and method - Google Patents
Aircraft skin valve monitoring device and method Download PDFInfo
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- CN110531683B CN110531683B CN201910900388.3A CN201910900388A CN110531683B CN 110531683 B CN110531683 B CN 110531683B CN 201910900388 A CN201910900388 A CN 201910900388A CN 110531683 B CN110531683 B CN 110531683B
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- 238000012806 monitoring device Methods 0.000 title claims abstract description 26
- 238000012544 monitoring process Methods 0.000 claims abstract description 44
- 238000006073 displacement reaction Methods 0.000 claims abstract description 23
- 230000008569 process Effects 0.000 claims description 43
- 238000009423 ventilation Methods 0.000 claims description 22
- 230000008676 import Effects 0.000 claims description 7
- 238000012423 maintenance Methods 0.000 abstract description 3
- 238000012937 correction Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 238000001816 cooling Methods 0.000 description 4
- 238000001514 detection method Methods 0.000 description 4
- 238000002955 isolation Methods 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
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- 230000002159 abnormal effect Effects 0.000 description 1
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- 230000007797 corrosion Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
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- 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
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- 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
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- 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
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/26—Pc applications
- G05B2219/2612—Data acquisition interface
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- Computer Networks & Wireless Communication (AREA)
- Health & Medical Sciences (AREA)
- Automation & Control Theory (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Indication Of The Valve Opening Or Closing Status (AREA)
Abstract
The invention relates to an aircraft skin valve monitoring device, which comprises a collector (21), a processor (22) and a memory (23) which are sequentially connected, wherein the collector (21) is also connected with an outlet valve angular displacement sensor (24) and an inlet valve angular displacement sensor (25), and the processor (22) comprises: the information acquisition module is used for acquiring time information of the full opening position of the outlet valve, the full closing position of the outlet valve, the half open-loop state of the outlet valve, the full opening position of the inlet valve and the full closing position of the inlet valve; the characteristic value calculation module is used for calculating the actuation time of the inlet valve and the actuation time of the outlet valve to obtain characteristic values; and the trend monitoring module is used for monitoring the characteristic value in real time and giving an alarm when the characteristic value exceeds a preset range. Compared with the prior art, the method for monitoring the failure of the valve effectively realizes the forecast of the failure of the valve by the method for monitoring the trend, and has the advantages of high accuracy, reduced running risk of the aircraft, improved maintenance work efficiency, reduced maintenance cost and the like.
Description
Technical Field
The invention relates to an airborne system and method, in particular to an aircraft skin valve monitoring device and method.
Background
The electronic cabin ventilation system mainly provides cooling for electronic cabin computer equipment, and as an important part of the electronic cabin ventilation system, the electronic cabin ventilation system of the aircraft has three working modes, namely an open-loop mode, a closed-loop mode and an intermediate mode, and the electronic cabin ventilation system works in different modes according to the environment temperature, the air-ground mode of the aircraft and the like.
Under the open loop form, the skin air inlet valve and the skin air outlet valve are completely opened, external air is sucked by the blower fan through the skin air inlet valve, and after radiating various electronic and electric equipment in the electronic cabin and the cockpit, the external air is pumped out by the exhaust fan and is discharged outside the aircraft through the skin air outlet valve.
In the closed loop mode, the skin air inlet valve and the skin air outlet valve are completely closed, the skin heat exchange isolation valve is opened, the skin heat exchange inlet bypass valve is opened when the pressure electric valve detects 1 correct pressure/air flow in the system, and the skin heat exchange outlet bypass valve is opened for reducing noise. The air circulates only internally, the circulating air is cooled via the skin heat exchange isolation flaps into the skin heat exchanger and subsequently again cools the electronic cabin equipment.
In the semi-open loop mode, the skin air inlet valve is fully closed, the skin air outlet valve is partially opened, the skin heat exchange isolation valve is opened, the skin heat exchange inlet bypass valve is opened when the pressure electric valve detects 1 correct pressure/air flow in the system, and the skin heat exchange outlet bypass valve is opened for reducing noise. After cooling the electronic cabin equipment, part of the cooling air is discharged outside the aircraft, part of the cooling air enters the skin heat exchanger through the skin heat exchange isolation valve to be cooled, and then the electronic cabin equipment is cooled again.
The skin outlet valve is positioned at the downstream of the whole electronic cabin ventilation system, if the skin outlet valve is not normally closed in the take-off stage or in the air, the normal cabin pressurization cannot be established in the cabin, and in the past three years, the skin outlet valve of the electronic cabin ventilation system of a certain aviation public crew is blocked and the like to cause abnormal events such as multiple times of return to the air for lowering and slipping back. At present, the skin valve monitoring can only be realized through an AIRMAN, the AIRMAN monitoring is in a post alarm mode, namely a mode without faults and alarms, and the pre-warning cannot be realized, so that a skin valve trend monitoring method needs to be researched and developed to realize the pre-fault prediction of the valve.
In the prior art, an electronic cabin ventilation system mounted on an aircraft is provided with a switch circuit, so that the valve can be controlled and the state information of the valve can be obtained. The shutter has three positions of full opening, partial opening and full closing, the full opening position is controlled and indicated by S1 and S2, the partial opening is controlled and indicated by S3 and S4, the full closing position is controlled and indicated by S5 and S6, S1, S3 and S5 are brake electric doors, and S2, S4 and S6 are indication electric doors. If the switching circuit is used to obtain status information of the shutters, the reliability of each electric gate is extremely important, and the electric gate generally comprises three contacts: the common terminal, the normally open contact and the normally closed contact are easy to generate electric corrosion after being used for a long time, so that the contact resistance is increased or unstable, and fault signals are easy to generate; in addition, the indication switch generally adopts a mechanical micro-switch to act based on the state of the valve, and the mechanical micro-switch often has the defects of insensitive action, unreliable work, incorrect signal indication and the like in the use process; furthermore, the risk of signal transmission delay or display faults and the like exists in the process of acquiring the state information of the valve through the electronic cabin ventilation system, so that the risk of acquiring the state information of the valve through the electronic cabin ventilation system carried on an aircraft is high, and the reliability is low.
In addition, the patent of the invention with the publication number of CN104340368B discloses a monitoring system and a method for an anti-icing valve of an aircraft wing. The monitoring system of the aircraft wing anti-icing valve comprises: a time recording device which records the time of opening or closing the anti-icing shutter; a data acquisition device which acquires the time of opening or closing the anti-icing shutter recorded by the time recording device; the message generating device generates an anti-icing valve performance message according to the time for opening or closing the anti-icing valve acquired by the data acquisition device; the anti-icing valve performance evaluation device receives the anti-icing valve performance message and evaluates the performance of the anti-icing valve according to the opening or closing time of the anti-icing valve in the anti-icing valve performance message, wherein the anti-icing valve performance message comprises the corrected opening or closing time of the anti-icing valve, and the correction formula is as follows:
Post-correction time = pre-correction time + (a (PD) +b)
Where PD represents the bleed air pressure and a and b are correction parameters.
The time for opening or closing the anti-icing valve of the monitoring system needs to be corrected based on the bleed air pressure, the complexity of the monitoring system is increased, the accuracy of the correction result depends on the correct setting of correction parameters, and factors affecting the reliability of the monitoring system are increased. In summary, the monitoring system has the defects of high complexity and low reliability.
And when the valve of the electronic cabin ventilation system not only has an open-loop form and a closed-loop form, but also has a semi-open-loop form, the monitoring system only takes the open-loop form and the closed-loop form into account, and when the electronic cabin ventilation system is monitored, false alarm is generated because of the semi-open-loop form.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide an aircraft skin valve monitoring device and method capable of alarming in advance.
The aim of the invention can be achieved by the following technical scheme:
The utility model provides an aircraft skin valve monitoring device, includes collector, treater and the memory that connects gradually, the electronic cabin ventilation system is connected to the collector, and electronic cabin ventilation system is equipped with switch circuit, can detect the skin valve and be in the time information of full open position, full close position and half open loop state, the time information of export valve full open position, export valve full close position, import valve full open position, import valve full close position and export valve half open loop state is obtained to the collector, the treater includes:
the characteristic value calculation module is used for calculating the actuation time of the inlet valve and the actuation time of the outlet valve to obtain characteristic values;
And the trend monitoring module is used for monitoring the characteristic value in real time and giving an alarm when the characteristic value exceeds a preset range.
Further, the collector and the memory are integrated in a wireless quick access recorder, which is connected to the processor.
The invention also provides an aircraft skin valve monitoring device, which comprises a collector, a processor and a memory which are sequentially connected, wherein the collector is also connected with an information acquisition module, an outlet valve full-open position sensor, an outlet valve full-closed position sensor, an inlet valve full-open position sensor and an inlet valve full-closed position sensor, the information acquisition module is connected with an electronic cabin ventilation system and is used for acquiring time information of a semi-open loop state of the outlet valve, and the processor comprises:
the characteristic value calculation module is used for calculating the actuation time of the inlet valve and the actuation time of the outlet valve to obtain characteristic values;
And the trend monitoring module is used for monitoring the characteristic value in real time and giving an alarm when the characteristic value exceeds a preset range.
Further, the outlet valve full-open position sensor, the outlet valve full-close position sensor, the inlet valve full-open position sensor and the inlet valve full-close position sensor are all photosensitive sensors.
Further, the collector and the memory are integrated in a wireless quick access recorder, which is connected to the processor.
The invention also provides an aircraft skin valve monitoring device, which comprises a collector, a processor and a memory which are connected in sequence, wherein the collector is also connected with an outlet valve angular displacement sensor and an inlet valve angular displacement sensor, and the processor comprises:
The information acquisition module is used for acquiring time information of the full opening position of the outlet valve, the full closing position of the outlet valve and the semi-open loop state of the outlet valve from data transmitted by the angular displacement sensor of the outlet valve; acquiring time information of the full opening position and the full closing position of the inlet valve from data transmitted by the inlet valve angular displacement sensor;
the time information is obtained from the angular displacement sensor, specifically, in the signal transmitted by the angular displacement sensor, the minimum angle corresponds to the full-closed position, the maximum angle corresponds to the full-closed position, the rest angles correspond to the semi-open loop state, and the corresponding time is added to obtain the time information to be obtained.
The characteristic value calculation module is used for calculating the actuation time of the inlet valve and the actuation time of the outlet valve to obtain characteristic values;
And the trend monitoring module is used for monitoring the characteristic value in real time and giving an alarm when the characteristic value exceeds a preset range.
Further, the collector and the memory are integrated in a wireless quick access recorder, which is connected to the processor.
The invention also provides an aircraft skin valve monitoring method adopting the aircraft skin valve monitoring device, which comprises the following steps:
an information acquisition step: the processor extracts time information of the full opening position of the outlet valve, the full closing position of the outlet valve, the full opening position of the inlet valve, the full closing position of the inlet valve and the semi-open loop state of the outlet valve from the data acquired by the collector in real time;
calculating a characteristic value: the processor calculates the actuation time of the inlet valve and the actuation time of the outlet valve based on the acquired time information, acquires the characteristic value and stores the characteristic value into the memory;
Trend monitoring: the processor monitors the calculated characteristic value in real time and compares the calculated characteristic value with a preset highest threshold value and a preset lowest threshold value, if the characteristic value is higher than the highest threshold value, an outlet jump alarm is sent out, if the characteristic value is lower than the lowest threshold value, an inlet jump alarm is sent out, and otherwise, no alarm is given.
Further, the characteristic values include a characteristic value of a shutter full-open to full-close process and a characteristic value of a shutter full-close to full-open process.
Further, the characteristic value calculation expression of the valve full-open to full-close process is as follows:
ΔT＝T1-T2-TFPO
T1＝TFc1-TFo1
T2＝TFc2-TFo2
Wherein DeltaT is a characteristic value, T 1 is the actuation time length from the full opening of the outlet valve to the full closing, T 2 is the actuation time length from the full opening of the inlet valve to the full closing, T FPO is the half-open loop time length from the full opening of the outlet valve to the full closing, T Fc1 is the time of full closing of the outlet valve, T Fo1 is the time of full opening of the outlet valve, T Fc2 is the time of full closing of the inlet valve, and T Fo2 is the time of full opening of the inlet valve;
the characteristic value calculation expression of the valve full-closing to full-opening process is as follows:
ΔT＝T3-T4-TFPO
T3＝TFo1-TFc1
T4＝TFo2-TFc2
Wherein T3 is the actuation time period from the full closing process to the full opening process of the outlet valve, and T4 is the actuation time period from the full closing process to the full opening process of the inlet valve.
Compared with the prior art, the invention has the following advantages:
(1) The invention utilizes the characteristics that the operating time length of each outlet valve is approximately consistent with that of each inlet valve, only a small difference exists, and the difference is constant in a reasonable interval, and obtains the operating time length of the outlet valve and the inlet valve by obtaining the time information of the full opening state of the outlet valve, the full closing state of the outlet valve, the full opening state of the inlet valve, the full closing state of the inlet valve and the semi-open state of the outlet valve, and obtains the characteristic value, and if the characteristic value exceeds the preset range, the characteristic value is the sign of the decline of the valve performance, so the invention can effectively realize the forecast before the valve failure by a trend monitoring method.
(2) The invention not only provides a monitoring device for acquiring time information through the electronic cabin ventilation system, but also provides a device for monitoring by directly acting on the valve through the photosensitive sensor or the angular displacement sensor, so that the possible way of faults is greatly reduced, and the sensor generally has the advantages of reliable performance and high detection accuracy, and has remarkable advantages compared with the monitoring through a circuit.
(3) The invention monitors the valve by arranging the sensor, and has the advantages of small occupied space, high detection accuracy and comprehensive information acquisition.
(4) And the running risk is reduced: the invention can continuously monitor the working state of the valve, can arrange the valve with declined performance in time, and reduces the return voyage caused by the failure of the valve.
(5) Work efficiency is improved, and maintenance cost is reduced: the invention only needs to count and analyze the stored data, can accurately know which valve has faults, and reduces the loss caused by misdisassembly and misjudgment.
Drawings
FIG. 1 is a schematic structural diagram of an aircraft skin flap monitoring device according to embodiment 1 of the present invention;
fig. 2 is a schematic structural diagram of an aircraft skin flap monitoring device according to embodiment 2 of the present invention;
FIG. 3 is a schematic structural diagram of an aircraft skin flap monitoring device according to embodiment 3 of the present invention;
FIG. 4 is a flow chart of the aircraft skin flap monitoring method of the present invention;
FIG. 5 is a diagram of the shutter monitoring data according to embodiment 4 of the present invention;
Fig. 6 is a schematic diagram of the valve monitoring data characteristic value analysis according to embodiment 4 of the present invention.
Detailed Description
The invention will now be described in detail with reference to the drawings and specific examples. The present embodiment is implemented on the premise of the technical scheme of the present invention, and a detailed implementation manner and a specific operation process are given, but the protection scope of the present invention is not limited to the following examples.
Example 1
As shown in fig. 1, the present embodiment is an aircraft skin valve monitoring device, applied to an a320 aircraft, where the monitoring device includes a collector 1, a processor 2 and a memory 3 that are sequentially connected, where the collector 1 is connected to an electronic cabin ventilation system, and the electronic cabin ventilation system of the a320 is composed of a blower fan, an exhaust fan, a skin air inlet valve, a skin air outlet valve, and an electronic cabin ventilation computer (AEVC), where the electronic cabin ventilation computer is provided with a switch circuit, and is capable of detecting time information that the skin valve is in a fully opened state, a fully closed state, and a half open state, and where the collector 1 obtains time information that the outlet valve is in a fully opened state, an outlet valve is in a fully closed state, an inlet valve is in a fully closed state, and an outlet valve is in a half open state.
The processor 2 includes:
the characteristic value calculation module is used for calculating the actuation time of the inlet valve and the actuation time of the outlet valve to obtain characteristic values;
And the trend monitoring module is used for monitoring the characteristic value in real time and giving an alarm when the characteristic value exceeds a preset range.
The processor 2 of the present embodiment is a CPU.
The collector 1 and the memory 3 of the present embodiment are integrated in a wireless fast access recorder which is connected to the processor 2.
Example 2
As shown in fig. 2, the present embodiment is an aircraft skin valve monitoring device, applied to an a320 aircraft, where the monitoring device includes a collector 11, a processor 12, and a memory 13, which are sequentially connected, the collector 11 is further connected with an information acquisition module 14, an outlet valve fully-open position sensor 15, an outlet valve fully-closed position sensor 16, an inlet valve fully-open position sensor 17, and an inlet valve fully-closed position sensor 18, and the information acquisition module 14 is connected with an electronic cabin ventilation system, and is used for acquiring time information of a semi-open loop state of the outlet valve.
The outlet valve full-open sensor 15 is arranged in the electronic cabin and is opposite to the full-open position of the outlet valve.
The outlet valve full-closing sensor 16 is arranged in the electronic cabin and is opposite to the full-closing position of the outlet valve.
The inlet valve full-open sensor 17 is arranged in the electronic cabin and is opposite to the full-open position of the inlet valve.
The inlet valve full-closing sensor 18 is arranged in the electronic cabin and is opposite to the full-closing position of the inlet valve.
The outlet valve full-open position sensor 15, the outlet valve full-close position sensor 16, the inlet valve full-open position sensor 17 and the inlet valve full-close position sensor 18 are photosensitive sensors, and all infrared sensors are adopted in the embodiment.
The processor 12 includes:
the characteristic value calculation module is used for calculating the actuation time of the inlet valve and the actuation time of the outlet valve to obtain characteristic values;
And the trend monitoring module is used for monitoring the characteristic value in real time and giving an alarm when the characteristic value exceeds a preset range.
The processor 2 of the present embodiment is a CPU.
The collector 11 and the memory 13 of the present embodiment are integrated in a wireless quick access recorder which is connected to the processor 12.
Example 3
As shown in fig. 3, the present embodiment is an aircraft skin valve monitoring device, applied to an a320 aircraft, where the monitoring device includes a collector 21, a processor 22 and a memory 23 connected in sequence, and the collector 21 is further connected to an outlet valve angular displacement sensor 24 and an inlet valve angular displacement sensor 25.
The outlet valve angular displacement sensor 24 is disposed on the door frame of the outlet valve, and the detection end of the outlet valve angular displacement sensor 24 is fixedly connected with the rotating shaft of the outlet valve, so that the detection end can rotate along with the rotation of the rotating shaft.
The inlet valve angular displacement sensor 25 is disposed on the door frame of the inlet valve, and the detecting end of the inlet valve angular displacement sensor 25 is fixedly connected to the rotating shaft of the inlet valve, so that the detecting end can rotate along with the rotation of the rotating shaft.
The processor 22 includes:
the information acquisition module is used for acquiring time information of the full opening position of the outlet valve, the full closing position of the outlet valve and the semi-open loop state of the outlet valve from the data transmitted by the outlet valve angular displacement sensor 24; acquiring time information of the full opening position of the inlet valve and the full closing position of the inlet valve from data transmitted by the inlet valve angular displacement sensor 25;
the time information is obtained from the angular displacement sensor, specifically, in the signal transmitted by the angular displacement sensor, the minimum angle corresponds to the full-closed position, the maximum angle corresponds to the full-closed position, the rest angles correspond to the semi-open loop state, and the corresponding time is added to obtain the time information to be obtained.
The characteristic value calculation module is used for calculating the actuation time of the inlet valve and the actuation time of the outlet valve to obtain characteristic values;
And the trend monitoring module is used for monitoring the characteristic value in real time and giving an alarm when the characteristic value exceeds a preset range.
The processor 2 of the present embodiment is a CPU.
The collector 21 and the memory 23 of the present embodiment are integrated in a wireless quick access recorder which is connected to the processor 22.
Example 4
As shown in fig. 4, the present embodiment is an aircraft skin valve monitoring method, applied to an a320 aircraft, which includes the following steps:
information acquisition step S1: the processor extracts time information of the full opening position of the outlet valve, the full closing position of the outlet valve, the full opening position of the inlet valve, the full closing position of the inlet valve and the semi-open loop state of the outlet valve from the data acquired by the collector in real time;
and a characteristic value calculating step S2: the processor calculates the actuation time of the inlet valve and the actuation time of the outlet valve based on the acquired time information, acquires the characteristic value and stores the characteristic value into the memory;
trend monitoring step S3: the processor monitors the calculated characteristic value in real time and compares the calculated characteristic value with a preset highest threshold value and a preset lowest threshold value, if the characteristic value is higher than the highest threshold value, an outlet jump alarm is sent out, if the characteristic value is lower than the lowest threshold value, an inlet jump alarm is sent out, and otherwise, no alarm is given.
The characteristic value in the characteristic value calculation step includes a characteristic value of a shutter full-open to full-close process and a characteristic value of a shutter full-close to full-open process.
The characteristic value calculation expression of the valve full-open to full-close process is as follows:
ΔT＝T1-T2-TFPO
T1＝TFc1-TFo1
T2＝TFc2-TFo2
Wherein DeltaT is a characteristic value, T 1 is the actuation time length from the full opening of the outlet valve to the full closing, T 2 is the actuation time length from the full opening of the inlet valve to the full closing, T FPO is the half-open loop time length from the full opening of the outlet valve to the full closing, T Fc1 is the time of full closing of the outlet valve, T Fo1 is the time of full opening of the outlet valve, T Fc2 is the time of full closing of the inlet valve, and T Fo2 is the time of full opening of the inlet valve.
The characteristic value calculation expression of the valve full-closing to full-opening process is as follows:
ΔT＝T3-T4-TFPO
T3＝TFo1-TFc1
T4＝TFo2-TFc2
Wherein T3 is the actuation time period from the full closing process to the full opening process of the outlet valve, and T4 is the actuation time period from the full closing process to the full opening process of the inlet valve.
As shown in fig. 5, in order to monitor the characteristic value result from the full opening to the full closing of the flap after the flap is monitored by the method for monitoring the flap of the aircraft skin according to the present invention, FO is full opening and FC is full closing.
As shown in fig. 6, the moment in the figure is an actual time period, in a monitoring process on the a320 aircraft, the set highest threshold is 4, the set lowest threshold is-4, the characteristic value shows the outlet valve jump at the 14 th moment, the outlet jump alarm is sent out, the inlet valve jump is also shown at the fifteenth moment, and the inlet jump alarm is sent out. After the aircraft lands, the alarm valve is immediately subjected to fault elimination, so that the valve fault is effectively prevented.
The foregoing describes in detail preferred embodiments of the present invention. It should be understood that numerous modifications and variations can be made in accordance with the concepts of the invention by one of ordinary skill in the art without undue burden. Therefore, all technical solutions which can be obtained by logic analysis, reasoning or limited experiments based on the prior art by the person skilled in the art according to the inventive concept shall be within the scope of protection defined by the claims.
Claims (7)
1. The utility model provides an aircraft skin valve monitoring device, includes collector (1), treater (2) and memory (3) that connect gradually, its characterized in that, electronic cabin ventilation system is connected to collector (1), time information that export valve is full open, export valve is closed the position entirely, import valve is full open, import valve is closed the position entirely and export valve is half open loop state is obtained to collector (1), treater (2) include:
the characteristic value calculation module is used for calculating the actuation time of the inlet valve and the actuation time of the outlet valve to obtain characteristic values;
The trend monitoring module is used for monitoring the characteristic value in real time and comparing the characteristic value with a preset highest threshold value and a preset lowest threshold value, if the characteristic value is higher than the highest threshold value, an outlet jump alarm is sent out, if the characteristic value is lower than the lowest threshold value, an inlet jump alarm is sent out, otherwise, no alarm is given;
the characteristic values comprise characteristic values of a valve full-open-full-close process and characteristic values of a valve full-close-full-open process, and the characteristic value calculation expression of the valve full-open-full-close process is as follows:
ΔT＝T1-T2-TFPO
T1＝TFc1-TFo1
T2＝TFc2-TFo2
Wherein DeltaT is a characteristic value, T 1 is the actuation time length from the full opening of the outlet valve to the full closing, T 2 is the actuation time length from the full opening of the inlet valve to the full closing, T FPO is the half-open loop time length from the full opening of the outlet valve to the full closing, T Fc1 is the time of full closing of the outlet valve, T Fo1 is the time of full opening of the outlet valve, T Fc2 is the time of full closing of the inlet valve, and T Fo2 is the time of full opening of the inlet valve;
the characteristic value calculation expression of the valve full-closing to full-opening process is as follows:
ΔT＝T3-T4-TFPO
T3＝TFo1-TFc1
T4＝TFo2-TFc2
Wherein T3 is the actuation time period from the full closing process to the full opening process of the outlet valve, and T4 is the actuation time period from the full closing process to the full opening process of the inlet valve.
2. Aircraft skin flap monitoring device according to claim 1, characterized in that the collector (1) and the memory (3) are integrated in a wireless quick access recorder which is connected to the processor (2).
3. The utility model provides an aircraft skin valve monitoring device, includes collector (11), treater (12) and memory (13) that connect gradually, its characterized in that, collector (11) still are connected with information acquisition module (14), export valve full open position sensor (15), export valve full close position sensor (16), import valve full open position sensor (17) and import valve full close position sensor (18), electronic cabin ventilation system is connected in information acquisition module (14) for acquire the moment information of export valve half open loop state, treater (12) include:
the characteristic value calculation module is used for calculating the actuation time of the inlet valve and the actuation time of the outlet valve to obtain characteristic values;
The trend monitoring module is used for monitoring the characteristic value in real time and comparing the characteristic value with a preset highest threshold value and a preset lowest threshold value, if the characteristic value is higher than the highest threshold value, an outlet jump alarm is sent out, if the characteristic value is lower than the lowest threshold value, an inlet jump alarm is sent out, otherwise, no alarm is given;
the characteristic values comprise characteristic values of a valve full-open-full-close process and characteristic values of a valve full-close-full-open process, and the characteristic value calculation expression of the valve full-open-full-close process is as follows:
ΔT＝T1-T2-TFPO
T1＝TFc1-TFo1
T2＝TFc2-TFo2
Wherein DeltaT is a characteristic value, T 1 is the actuation time length from the full opening of the outlet valve to the full closing, T 2 is the actuation time length from the full opening of the inlet valve to the full closing, T FPO is the half-open loop time length from the full opening of the outlet valve to the full closing, T Fc1 is the time of full closing of the outlet valve, T Fo1 is the time of full opening of the outlet valve, T Fc2 is the time of full closing of the inlet valve, and T Fo2 is the time of full opening of the inlet valve;
the characteristic value calculation expression of the valve full-closing to full-opening process is as follows:
ΔT＝T3-T4-TFPO
T3＝TFo1-TFc1
T4＝TFo2-TFc2
Wherein T3 is the actuation time period from the full closing process to the full opening process of the outlet valve, and T4 is the actuation time period from the full closing process to the full opening process of the inlet valve.
4. An aircraft skin flap monitoring device according to claim 3, characterized in that the outlet flap fully open sensor (15), the outlet flap fully closed sensor (16), the inlet flap fully open sensor (17) and the inlet flap fully closed sensor (18) are all light-sensitive sensors.
5. An aircraft skin flap monitoring device according to claim 3, characterized in that the collector (11) and the memory (13) are integrated in a wireless quick access recorder which is connected to the processor (12).
6. The utility model provides an aircraft skin valve monitoring device, includes collector (21), treater (22) and memory (23) that connect gradually, its characterized in that, collector (21) still are connected with export valve angular displacement sensor (24) and import valve angular displacement sensor (25), treater (22) include:
The information acquisition module is used for acquiring time information of the full opening position of the outlet valve, the full closing position of the outlet valve and the semi-open loop state of the outlet valve from data transmitted by the outlet valve angular displacement sensor (24); acquiring time information of the full opening position of the inlet valve and the full closing position of the inlet valve from data transmitted by an inlet valve angular displacement sensor (25);
the characteristic value calculation module is used for calculating the actuation time of the inlet valve and the actuation time of the outlet valve to obtain characteristic values;
The trend monitoring module is used for monitoring the characteristic value in real time and comparing the characteristic value with a preset highest threshold value and a preset lowest threshold value, if the characteristic value is higher than the highest threshold value, an outlet jump alarm is sent out, if the characteristic value is lower than the lowest threshold value, an inlet jump alarm is sent out, otherwise, no alarm is given;
the characteristic values comprise characteristic values of a valve full-open-full-close process and characteristic values of a valve full-close-full-open process, and the characteristic value calculation expression of the valve full-open-full-close process is as follows:
ΔT＝T1-T2-TFPO
T1＝TFc1-TFo1
T2＝TFc2-TFo2
Wherein DeltaT is a characteristic value, T 1 is the actuation time length from the full opening of the outlet valve to the full closing, T 2 is the actuation time length from the full opening of the inlet valve to the full closing, T FPO is the half-open loop time length from the full opening of the outlet valve to the full closing, T Fc1 is the time of full closing of the outlet valve, T Fo1 is the time of full opening of the outlet valve, T Fc2 is the time of full closing of the inlet valve, and T Fo2 is the time of full opening of the inlet valve;
the characteristic value calculation expression of the valve full-closing to full-opening process is as follows:
ΔT＝T3-T4-TFPO
T3＝TFo1-TFc1
T4＝TFo2-TFc2
Wherein T3 is the actuation time period from the full closing process to the full opening process of the outlet valve, and T4 is the actuation time period from the full closing process to the full opening process of the inlet valve.
7. Aircraft skin flap monitoring device according to claim 6, characterized in that the collector (21) and the memory (23) are integrated in a wireless quick access recorder which is connected to the processor (22).
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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 |
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| BR112016019211A2 (en) * | 2014-02-21 | 2017-10-17 | Taleris Global Llp | method of diagnosing a failure in an air conditioning unit of an aircraft |
| CN108163224B (en) * | 2017-11-28 | 2020-10-23 | 中国南方航空股份有限公司 | State monitoring device and method for flow control valve of civil aircraft air conditioner |
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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 |
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| Title |
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| 基于大数据建模的A320飞机电子舱蒙皮出口活门失效预测;赵红华 等;《航空维修与工程》(第第9期期);第52-56页 * |
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