CN108177797A - A kind of aircraft high temperature conduit gas leak detection device and its detection method - Google Patents
A kind of aircraft high temperature conduit gas leak detection device and its detection method Download PDFInfo
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- CN108177797A CN108177797A CN201711459943.0A CN201711459943A CN108177797A CN 108177797 A CN108177797 A CN 108177797A CN 201711459943 A CN201711459943 A CN 201711459943A CN 108177797 A CN108177797 A CN 108177797A
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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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Abstract
The invention discloses a kind of aircraft high temperature conduit gas leak detection device and its detection methods, and including sensor interface, sensor interface connects multiple sensor modules, and sensor module is arranged on aircraft high temperature conduit connector position；Sensor module connection signal conditioner；Signal conditioner connects controller by the first communication interface；Controller connects the engine instruction of aircraft and unit warning system by the second communication interface, and the state of controller itself, each signal conditioner and each sensor module is sent to engine instruction and unit warning system；Controller also connects the centralized alarm system of aircraft by being crosslinked interface, and the level signal for representing high temperature conduit gas leakage is sent to centralized alarm system.The gas leakage of aircraft high temperature conduit is detected using this method, detection is safe and reliable, and measures precisely, and corresponding speed is fast.
Description
Technical field
The invention belongs to aircraft environmental control system high temperature conduit gas leakage detection technique fields；More particularly to a kind of aircraft height
Warm pipeline gas leak detection device and its detection method；For detect each pipeline of aircraft environmental control system in different flight attitudes, no
With whether leaking air or alert at pipe joint under the influence of environment.
Background technology
The air-flow that aircraft engine generates need to flow through multiple pipelines on aircraft, due to aircraft flight environment complexity, by winged
The factors such as row posture, speed, acceleration, vibration, impact, air-flow, temperature, pressure, electromagnetic interference influence, in pipe joint
Place is also easy to produce gas leak phenomenon.And the gas temperature of engine discharge is high, it, can be to pipeline once gas leakage, which occurs, sprays aircraft pipeline
The other equipment generation of surrounding seriously affects, especially huge on communication lines influences various on machine, can influence flight safety.And
In flight course, pilot can not understand pipeline gas leakage situation in time, can if Intensive Flying is carried out when pipeline gas leakage
There are huge security risk, therefore it is necessary to allow pilot that can understand aircraft pipeline state in time in flight course.
Aircraft high temperature conduit gas leakage detection technique early has an application and development in external air force, domestic traditional method only according to
It is close to affixed head screw etc. and flies preceding status checkout to ensure that pipeline connection is reliable, but can only accomplish pre-incident survey, sky can not be coped with
The leakage problem generated in middle complexity flight course, so as to understand the real-time status of aircraft pipeline, can not ensure flight.
The state of aircraft pipeline in flight course can not accurately, be timely understood for current Domestic Aircraft, it is proposed that one
Kind can detect in real time and the detection method of feedback pipe joint information, solve pilot can not be learnt in flight course it is winged
The problem of whether machine pipeline works normally further ensures the flight safety of aircraft.
Invention content
The present invention provides a kind of aircraft high temperature conduit gas leak detection device and its detection method, using this method to flying
The gas leakage of row device high temperature conduit detects, and detection is safe and reliable, and measures precisely, and corresponding speed is fast.
The technical scheme is that：A kind of aircraft high temperature conduit gas leak detection device, sensor interface, sensor connect
Mouth connects multiple sensor modules, and sensor module is arranged on aircraft high temperature conduit connector position；Sensor module connection letter
Number conditioner；Signal conditioner connects controller by the first communication interface；Controller is connected by the second communication interface and flown
The engine instruction of device and unit warning system, and send each sensor module to engine instruction and unit warning system
State；Controller also connects the centralized alarm system of aircraft by being crosslinked interface, and sends table to centralized alarm system
Show the level signal of high temperature conduit gas leakage；First communication interface is the communication chip of signal conditioner and the communication chip of controller
Between internal communications interface；Device indicates second communication interface with engine in order to control and the crosslinked outside of unit warning system leads to
Believe interface.
Further, the features of the present invention also characterized in that：
Plurality of sensor module is connect with a signal conditioner, and signal conditioner have it is multiple.
Wherein sensor module is temperature sensors of high precision.
Wherein the signal of sensor module is passed to signal conditioner by sensor interface, and signal conditioner is by the way that this is believed
Number be amplified, filter, A/D conversions, digital filtering and data processing.
Wherein data are sent to controller by signal conditioner by ARINC429 bus modes by the first communication interface.
Another technical solution of the present invention is that a kind of aircraft high temperature conduit leak detection method includes the following steps：
Step S1, sensor module collect the temperature change signal in respective line, and obtain the sensor module
Locate pipe joint status signal, and the signal is conveyed to corresponding signal conditioner, signal conditioner puts signal
Greatly, after filtering, A/D conversions, digital filtering and data processing, controller is sent a signal to；
Step S2, controller reads the signal that signal conditioner is sent, and obtains the working condition of signal conditioner, so
It is sent to the engine instruction of aircraft and unit warning system afterwards；Controller is also by signal conditioner and the shape of sensor module
State signal is sent to the centralized alarm system of aircraft；
Step S3, engine instruction and unit warning system will distinguish normal signal and spectral artifacts, spectral artifacts
It is divided into as fault-signal or alarm signal, and fault-signal processing and alarm is carried out respectively to spectral artifacts.
Further, the features of the present invention also characterized in that：
It is further included in wherein step S1 and sensor module is detected, if not in the event of failure, sensor module acquires it
The status information of installation place pipeline, and it is sent to signal conditioner；If faulty, fault message is recorded.
Controller detects signal conditioner in wherein step S2, normal in signal conditioner, and controller is read
Data in signal conditioner, and the centralized alarm system for aircraft being sent to after storage；Signal conditioner is improper
In the case of, controller records its fault message, and reads the data in signal conditioner, while by data and fault message
It is sent to the centralized alarm system of aircraft simultaneously.
Engine instruction and unit warning system first determine whether the signal received is failure letter in wherein step S3
Number, if fault-signal, then carry out fault-signal processing, and handling failure；If not fault-signal then judges whether it is announcement
Alert signal, if alarm signal, is then alerted；If not alarm signal then judges it for normal signal.
Compared with prior art, the beneficial effects of the invention are as follows：The device is based on aircraft high temperature conduit air leakage detection system
It realizes, according to aircraft model and the difference of internal structure of aircraft, sensor is set in the junction of the pipeline of aircraft
Component, and sensor module is connected with corresponding signal conditioner, and signal conditioner is connect with controller, is measured precisely,
Real-time is high, and reliance security is high, and good environmental adaptability, anti-electromagnetic interference capability is strong, and reaction that can be promptly and accurately is flown
The variation of device working condition of aircraft pipeline in flight course；Controller can realize the total of summed signal conditioner output
Line signal judges itself working condition of each signal conditioner (normal/abnormal), judges that controller itself working condition is (normal/different
Often).
Further, the amplification, filtering, A/D for realizing sensor module output signal using signal conditioner are converted, from
And judge that each sensor working condition of itself is normal or abnormal, so as to judge whether the state of each pipe joint is normal
Or gas leakage.
Further, ARINC429 buses as defined in inner high speed spi bus, exterior I CD and customized are utilized
ARINC429 buses, can be by each sensor itself working condition, each aircraft pipe joint state, each signal
The operating state data of conditioner working condition and controller is timely, is accurately transmitted to EICAS.
Further, if there is pipeline gas leakage, other than the ARINC429 communication frames of periodic communication, list will also be passed through
Only cable output high level signal to centralized alarm system is alerted, it is ensured that flight safety.
Description of the drawings
Fig. 1 is the structural diagram of the present invention；
Fig. 2 is conditioner testing process schematic diagram in the present invention；
Fig. 3 is the control flow schematic diagram of controller in the present invention；
Fig. 4 is the flow diagram alerted in the present invention.
Specific embodiment
Technical scheme of the present invention is further illustrated in the following with reference to the drawings and specific embodiments.
The present invention provides a kind of aircraft high temperature conduit gas leak detection device, as shown in Figure 1, being placed on including several
Sensor module at aircraft high temperature conduit jointing, sensor module are temperature sensors of high precision；With sensor module
Several corresponding signal conditioners, plurality of sensor module correspond to a signal conditioner；With multiple signal conditioners
It is crosslinked and simultaneously with EICAS (engine indicates and unit warning system) crosslinked controller on aircraft, works as sensor module
When experiencing temperature change, the variable quantity of temperature is changed into electric signal and is conveyed to corresponding signal conditioner, signal conditioner
By amplifying, filtering, send a signal to controller after A/D conversions, digital filtering and data processing, controller is by each signal
After the signal and its working condition of conditioner summarize, EICAS is finally sent data to.Wherein entire detecting system and outside
EICAS crosslinkings using ICD files (control interface file), it is specified that ARINC429 bus communication protocols, controller and signal tune
It manages between device using customized ARINC429 bus communication protocols, inside controller between MCU and communication chip and signal
Spi bus communication mode is used inside conditioner between MCU and communication chip.
Specifically, as shown in Figure 1, EXI-IN1 is the detection device sensor interface, it is used for transmission the letter of sensor module
Number to signal conditioner, signal tune is realized using 1 mode of the signal conditioner with multiple sensor component to save volume
Reason, the electric signal that when interface prevailing transmission sensor module collected temperature change generates.One signal conditioner can
Multiple signals into line asynchronous are improved, conditioning can be synchronized between unlike signal conditioner.To upper in signal conditioner
The electric signal for stating temperature change is amplified, filters, A/D conversions, digital filtering and data processing；Simultaneously using spi bus
One byte represents the working condition of respective sensor component to be normal or improper, while uses a word of spi bus
It is normal or gas leakage that section, which represents high temperature conduit connector status that the sensor module is installed, each signal conditioner by itself
Crosslinked all the sensors component all acquires finish after, ARINC429 bus communication chips are sent in a manner of spi bus.
INI-OUT1 is the first communication interface, and the first communication structure (is sent out for the ARINC429 communication chips of signal conditioner
Send) internal communication configuration between controller ARINC429 communication chips (reception), use customized ARINC429 total
Line communication protocol, the data that controller sends all signal conditioners received, including sensor module working condition and height
Warm pipe joint state, at the same the data received are verified and judge all signal conditioners working condition (it is normal or
It is abnormal), BIT self-tests then are carried out to itself, judge itself working condition (normal or abnormal), while by all of above information
Communication frame as defined in ICD files is encapsulated as, wherein all information include sensor module working condition, high temperature conduit nipple
State, the working condition of all signal conditioners and its own working condition, it is crosslinked with EICAS to be then forwarded to controller
On ARINC429 communication chips.
EXI-OUT2 is the second communication interface, is controller and the crosslinked external communication interface of centralized alarm system, when winged
When machine high temperature conduit leaks air, a high level VCC signal will be individually sent to airplane centralized warning system, so as to apparent
Prompt the state of pilot's aircraft pipeline.
A kind of aircraft high temperature conduit leak detection method of the present invention, leads to sensor module including signal conditioner
The alarm processing of communication process and centralized alarm system between letter process, controller and EICAS.
Specifically as shown in Fig. 2, signal conditioner is to the communication process of sensor module：First to signal conditioner
And multiple sensor modules connected to it are initialized, then signal conditioner checks multiple biographies of corresponding connection
Whether sensor component is normal.If sensor module is normal, which carries out the acquisition of temperature variation data and place
Reason obtains electric signal and is sent to signal conditioner connected to it；If sensor module is improper, signal conditioner records simultaneously
Obtain the position of the sensor module and the high temperature conduit junction of its installation.Signal conditioner passes through original defeated to sensor
Go out signal be amplified, filter, after A/D conversions, digital filtering and data processing, obtain data letter in above-mentioned two situations
Breath, and it is sent to controller.
As shown in figure 3, the communication process between controller and EICAS is：Controller first checks for connected to it multiple
Whether signal conditioner is promising normal.If signal conditioner is normal condition, controller receives signal condition transmission
Data information；If the signal conditioner is abnormal, the fault message of the signal conditioner is recorded.Controller receives above-mentioned two
The data information obtained in kind situation, and the data frame format of ICD documentation requirements is packaged into, all data are sent to
EICAS systems.
As shown in figure 4, when there are during spectral artifacts, failure will be generated or warning information, flow are：To from signal tune
The data that reason device receives are traversed, and determine whether that fault-signal (is believed including signal conditioner faults itself one by one first
Number and the fault-signal of sensor that is connect with the signal conditioner), if fault-signal, then in the data sent to EICAS
The data bit for representing the failure part is set as " failure " state in frame；Then determine whether alarm signal (including institute one by one
Have the gas leakage alarm signal that sensor occurs), if alarm signal, then the biography will be represented in the data frame sent to EICAS
The data bit of sensor is set as " gas leakage alarm " state；Finally determine whether normal signal (when the signal both non-faulting one by one
Signal, also as normal signal during non-leak alarm signal), it, then will in the data frame sent to EICAS if normal signal
Corresponding data bit is set as " normal " state.
Claims (9)
1. a kind of aircraft high temperature conduit gas leak detection device, which is characterized in that including sensor interface, sensor interface connection
Multiple sensor modules, sensor module are arranged on aircraft high temperature conduit connector position；Sensor module connection signal improves
Device；Signal conditioner connects controller by the first communication interface；Controller connects the hair of aircraft by the second communication interface
Motivation indicates and unit warning system, and the shape of each sensor module is sent to engine instruction and unit warning system
State；Controller also connects the centralized alarm system of aircraft by being crosslinked interface, and is sent to centralized alarm system and represent high
The level signal of warm pipeline gas leakage；
Intercommunication of first communication interface between the communication chip of signal conditioner and the communication chip of controller connects
Mouthful；
Device and engine indicate and the crosslinked external communication interface of unit warning system second communication interface in order to control.
2. aircraft high temperature conduit gas leak detection device according to claim 1, which is characterized in that the multiple sensor
Component is connect with a signal conditioner, and signal conditioner have it is multiple.
3. aircraft high temperature conduit gas leak detection device according to claim 1, which is characterized in that the sensor module
For temperature sensors of high precision.
4. the aircraft high temperature conduit gas leak detection device according to claim 1-3 any one, which is characterized in that described
The signal of sensor module is passed to signal conditioner by sensor interface, signal conditioner by the way that the signal is amplified,
Filtering, A/D conversions, digital filtering and data processing.
5. aircraft high temperature conduit gas leak detection device according to claim 4, which is characterized in that the signal conditioner
Data are sent to by controller by the first communication interface by ARINC429 bus modes.
6. a kind of aircraft high temperature conduit leak detection method, which is characterized in that include the following steps：
Step S1, sensor module collect the temperature change signal in respective line, and obtain managing at the sensor module
Pipeline connector status signal, and the signal is conveyed to corresponding signal conditioner, signal conditioner is amplified signal, filters
After wave, A/D conversions, digital filtering and data processing, controller is sent a signal to；
Step S2, controller reads the data in signal conditioner, and obtains the working condition of signal conditioner, then sends
To the engine instruction of aircraft and unit warning system；Controller also by high temperature conduit connector, whether send out by the status signal of gas leakage
Give the centralized alarm system of aircraft；
The signal distinguishing normal signal or spectral artifacts that step S3, engine instruction and unit warning system will receive, it is non-
Normal signal divides into fault-signal or alarm signal again, and carries out fault-signal processing and alarm respectively to spectral artifacts.
7. aircraft high temperature conduit leak detection method according to claim 6, which is characterized in that in the step S1 also
Including being detected to sensor module, if not in the event of failure, sensor module acquires the status information of its installation place pipeline, and
And it is sent to signal conditioner；If faulty, fault message is recorded.
8. aircraft high temperature conduit leak detection method according to claim 6, which is characterized in that controlled in the step S2
Device processed detects signal conditioner, normal in signal conditioner, and controller reads the data in signal conditioner, and
The centralized alarm system of aircraft will be sent to after storage；Signal conditioner in the case that improper, controller record its therefore
Hinder information, and read the data in signal conditioner, while data and fault message are sent to the concentration of aircraft simultaneously
Warning system.
9. aircraft high temperature conduit leak detection method according to claim 6, which is characterized in that sent out in the step S3
Motivation indicates and unit warning system first determines whether the signal received is fault-signal, if fault-signal, then carries out
Fault-signal processing, and handling failure；If not fault-signal then judges whether it is alarm signal, if alarm signal, then
It is alerted；If not alarm signal then judges it for normal signal.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711459943.0A CN108177797A (en) | 2017-12-28 | 2017-12-28 | A kind of aircraft high temperature conduit gas leak detection device and its detection method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711459943.0A CN108177797A (en) | 2017-12-28 | 2017-12-28 | A kind of aircraft high temperature conduit gas leak detection device and its detection method |
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2017
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| DE102008025952B3 (en) * | 2008-05-30 | 2009-08-06 | Airbus Deutschland Gmbh | Aircraft line system, has sensor wire with two electrical conductors, and insulator insulating one electrical conductor from other electrical conductor and comprising electrical resistor that is varied based on temperature |
| CN205003823U (en) * | 2015-08-10 | 2016-01-27 | 海诚建筑设计院(上海)有限公司 | Multi -functional gaseous leak detection evacuates system based on thing networking |
| CN205247554U (en) * | 2015-12-21 | 2016-05-18 | 无锡圣敏传感科技股份有限公司 | Air tubular line type heat fire detector that can real -time supervision pipeline trouble |
| CN206161214U (en) * | 2016-10-26 | 2017-05-10 | 中航电测仪器股份有限公司 | Satellite loop aerial branch measuring force device for system |
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Application publication date: 20180619 |