CN101916108A - Automation device for use in civil aircraft environment control system function test - Google Patents
Automation device for use in civil aircraft environment control system function test Download PDFInfo
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Abstract
The invention relates to an automation device for use in a civil aircraft environment control system function test, which belongs to the technical field of aircraft manufacturing. The automation device comprises an air source processing component, an electric air heating furnace, an air heating furnace controller, a main pipeline system, a pneumatic valve control component, a metal hose component, a wireless sensing communication module, a programmable logic controller (PLC) control module and an upper machine monitoring computer. In the invention, an aircraft pressure cabin and air conditioner pipeline leakage amount test, a cabin pressure regulating system test, a cabin air temperature regulating system function test and an anti-ice system function test are carried out by using an on-spot air source of an aircraft assembly plant in place of an engine or an auxiliary power unit (APU) unit, so that a plurality of test items in the aircraft environment control function test can be completed, and the requirements of aircraft mass production on the quality and efficiency improvement on the environment control function test in a final assembly process are met.
Description
Technical field
What the present invention relates to is the device in a kind of aircraft manufacturing technology field, specifically is a kind of automation equipment that is used for civil aircraft environment control system function test.
Background technology
Plane environmental control system is mainly used in air themperature and pressure in aircraft cockpit and the driving cabin is carried out regulating and controlling, the limit that restriction pipeline feed air temperature and pressure are requiring, guarantee to have certain temperature, pressure, air velocity, humidity and air cleanliness etc. in driving cabin, the passenger cabin, with the operate as normal that satisfies occupant on the machine, the necessary condition of life.Can plane environmental control system operate as normal be directly connected to aircraft flight safety, occupant's life security and the comfortableness of taking and have influence on other flying quality of aircraft as modern civil aviation aircraft or military combat aircraft important component part.
In the aircraft general assembly (GA) stage, must finish the function test of plane environmental control system by uphole equipment, to guarantee the flight safety of aircraft in flight course.Civil aircraft has very strict demand to the serviceability of flight environment of vehicle control system, and the pilot project that comprises has pressure cabin and the test of air-conditioning duct leakage rate, cockpit pressure regulating system test, cabin air humidity control system function test and anti-icing system function test.
At present, domestic plane environmental control system function test is continued to use traditional testing equipment and test method basically.Civil aircraft need be finished a plurality of pilot projects of environmental control system in the general assembly (GA) stage, traditional plane environmental control system function test method needs many cover testing equipments, the equipment bulky complex, basically the mode of armrest wage adjustment joint is operated, and measuring equipment mostly is the instrument of pointer-type or mercury pillar; The air-tight test of plane environmental control system adopts pressure decline method more, and process of the test length consuming time, measuring accuracy are subjected to the influence of external environment bigger, and control accuracy and reliability are low.By above analysis as seen, promote the quality and the efficient of aircraft general assembly environmental control system test, the environmental control system functional test should realize the digitizing of measuring equipment and the robotization of process of the test.
Find through retrieval prior art, in the paper " aircraft environmental control system Auto-Test System " that people such as Zheng Bao deliver, propose to be used for the Function detection of plane environmental control system by the aircraft environmental control system Auto-Test System that industrial computer and interface model are formed on " the 3rd academic annual meeting of Chinese aeronautics meeting aviation electrical engineering " [1999:228-232].This test macro is by multichannel resistance self-checking device, the temperature measurement signal in the simulated aircraft environmental control system and the voltage signal of electronic valve, can operate as normal by the equipment in the signal testing environmental control system that changes simulation, but this test macro can't be finished the test of air-conditioning duct and passenger cabin leakage rate.
Summary of the invention
The present invention is directed to the prior art above shortcomings, a kind of automation equipment that is used for civil aircraft environment control system function test is provided, utilize the on-the-spot source of the gas of aircraft assembly plant to replace engine or APU source of the gas to carry out aircraft pressure cabin and the test of air-conditioning duct leakage rate, cockpit pressure regulating system test, cabin air humidity control system function test and anti-icing system function test, can finish a plurality of pilot projects in the test of aircraft central control function, satisfy aircraft and criticize the demand of production environmental control system function test quality and improved efficiency in total process of assembling.
The present invention is achieved by the following technical solutions, the present invention includes: the source of the gas processing components, the air heat electric furnace, the air heat furnace controller, the main line system, the pneumatic valve Control Component, the metal hose assembly, the wireless sensing communication module, PLC control module and upper monitoring computing machine, wherein: the source of the gas processing components is connected with the air heat electric furnace, the air heat electric furnace is connected with the main line system, the air heat furnace controller is connected with air-heating furnace and transmits the signal that control air heat furnace temperature is exported, the main line system is connected with the pneumatic valve Control Component, the pneumatic control valve of pneumatic valve Control Component transmission and air pressure control signal in the main line system, metal hose assembly one end is connected with the main line system, the other end is connected with aircraft ring control test interface, wireless sensing communication module transmitting terminal is connected with the metal hose assembly and transmits aircraft ring control test interface air measured parameter data information, the PLC control module is connected with wireless sensing communication module receiving end and receives the data message that the wireless sensing communication module transmits, the PLC control module links to each other with the source of the gas processing components and transmits the switching information of source of the gas processing components operation valve, the PLC control module is connected with the air heat furnace controller and transmits the control and the monitoring information of air-heating furnace, the PLC control module is connected with the pneumatic control valve module and transmits the control and the status information of operation valve, the PLC control module is connected with the main line system and transmits the control and the metrical information of operation valve and sensor, and the upper monitoring computing machine is connected with the PLC control module and transmits man-machine exchange message.
Described source of the gas processing components is carried out oil and water separation and filtration, purification to the plant source that enters system pipeline, this source of the gas processing components comprises: two manually operated control valves, an oil-water separator, two accurate filters, three electromagnetic water discharging valves and a pneumatic ball valve, wherein: the source of the gas air inlet pipeline is divided into two branch roads by two manually operated control valves, one of them branch road is connected with oil-water separator and two accurate filters successively, oil-water separator is in inlet end, be connected with pneumatic ball valve after the endpiece parallel connection of another branch road and two described accurate filters, three electromagnetic water discharging valves join with the lower end of oil-water separator and two accurate filters respectively, and pneumatic ball valve is connected with the PLC control module respectively with solenoid valve and transmits the switch state signal and the control signal of pneumatic ball valve and solenoid valve.
Described air-heating furnace is used for the air that enters heating furnace is heated, the input end of this air-heating furnace is connected with the output channel of source of the gas processing components, the output terminal of air-heating furnace is installed a temperature sensor, temperature sensor is connected with the air heat furnace controller and transmits air-heating furnace outlet air temperature measuring-signal, and the air heat furnace controller is connected with air-heating furnace and transmits the control signal of heating power.
Described main line system is to air pressure in the aircraft environmental control system function test, the primary structure part of flow regulation, this main line system comprises: four manually operated control valves, four pneumatic flowrate variable valve, a pneumatic pressure-release valve, four pneumatic ball valves, a solenoid valve, two straight pipe type air strainers, an air silencer, two temperature sensors, a pressure transducer and three tapered mass flowmeters of V, wherein: the input end of main line system is divided into cold-air duct and hot-air duct, cold-air duct is connected with the output channel of source of the gas processing components, hot-air duct is connected with air-heating furnace, be provided with a pressure transducer on the cold-air duct successively, a manually operated control valve, a pneumatic flowrate variable valve and a pneumatic pressure-release valve, pressure transducer is connected with the PLC control module and transmits the interior air pressure of cold-air duct, be provided with a temperature sensor on the hot-air duct successively, a manually operated control valve, a pneumatic flowrate variable valve, a manually operated control valve and a pneumatic flowrate variable valve, temperature sensor is connected with the air heat furnace controller and transmits air-heating furnace outlet air temperature measuring-signal, be connected a bypass branch road between temperature sensor on the described hot-air duct and first manually operated control valve, connect a manually operated control valve on the bypass branch road, the by-pass line output terminal connects an air silencer, be connected by a branch road between first pneumatic flowrate variable valve output terminal on pneumatic flowrate variable valve output terminal and the hot-air duct on the described cold-air duct, after the pipeline of second pneumatic flowrate variable valve output terminal is connected on the pipeline of pneumatic pressure-release valve output terminal and the hot-air duct on the cold-air duct, mode by parallel connection is divided into 2 "; 4 " 6 " three path pipelines; a pneumatic ball valve and the tapered mass flowmeter of V respectively are installed on three path pipelines; pneumatic ball valve is connected with the PLC control module and transmits the switch state signal and the control signal of pneumatic ball valve; the tapered mass flowmeter of V be connected with the PLC control module and transmission pipeline in the detection signal of air mass flow; it is a path pipeline that three the tapered mass flowmeter endpiece of V pipelines converge; this section path pipeline is provided with a temperature sensor, this temperature sensor be connected with the PLC control module and transfer conduit in the measuring-signal of air themperature, pipeline after the temperature sensor is divided into three path pipelines by parallel way, article two, respectively connect a straight pipe type air strainer on the path pipeline, pneumatic flowrate variable valve of connection on another path pipeline, pneumatic flowrate variable valve output terminal pipeline is connected on the bypass bypass line that air silencer is installed simultaneously, the output terminal pipeline of a straight pipe type air strainer connects an air pressure safety valve, be connected a solenoid valve between another straight pipe type air strainer and the pneumatic flowrate variable valve, solenoid valve is connected with the PLC control module and transmits the switch state signal and the control signal of solenoid valve.Connect a pneumatic ball valve on the pipeline of air pressure safety valve endpiece, pneumatic ball valve is connected with the PLC control module and transmits the switch state signal and the control signal of pneumatic ball valve, and the pipeline of pneumatic ball valve endpiece is connected to aircraft ring control test interface by the metal hose assembly.
Described pneumatic control valve module comprises: an air strainer, an accurate reduction valve, three electric Proportion valves and three solenoid valves, wherein: the inlet end pipeline of air strainer is connected to the inlet end of cold-air duct in the main line system, the endpiece of air strainer connects accurate reduction valve, accurate reduction valve endpiece three pneumatic lines that are connected in parallel connect an electric Proportion valve and solenoid valve successively on every pneumatic line road.Article one, pneumatic line electromagnetic valve outlet end is divided into two branch roads, is connected respectively to the pneumatic flowrate variable valve on the cold-air duct and first pneumatic flowrate variable valve on the hot-air duct in the main line system; Second pneumatic line electromagnetic valve outlet end is connected on the pneumatic pressure-release valve in the main line system; Article three, Pneumatic pipe electromagnetic valve outlet end is divided into two branch roads, is connected respectively to second pneumatic flowrate variable valve on the hot-air duct and the pneumatic flowrate variable valve that is in parallel with the straight pipe type air strainer in the main line system.Three solenoid valves are connected respectively at the PLC control module with three electric Proportion valves and transmit the status signal and control model of valve.The output pressure of the input electrical signal may command electric Proportion valve by regulating electric Proportion valve, and then the aperture of control pneumatic pressure-release valve or pneumatic flowrate variable valve, thereby reach the purpose of controlling pneumatic pressure-release valve output pressure or pneumatic flowrate variable valve delivery rate.Solenoid valve between connection electric Proportion valve and the Pneumatic valve is used to control the break-make or the switching of pneumatic control circuit.
Described metal hose assembly is connected with the cabin interface that is connected main line system and the control of aircraft ring test, the test air enters interior of aircraft by aircraft connecting pipe assembly by main pneumatic line system, and temperature and pressure measurement interface is installed on the jointing of metal hose assembly and aircraft cabin interface.
Described wireless sensing communication module comprises: wireless sensing transmitting terminal and wireless sensing receiving end, wherein: the wireless sensing transmitting terminal is integrated temperature and pressure survey sensor, integrated survey sensor has the temperature, pressure survey interface and the cabin internal pressure that are connected to the metal hose joint place to measure interface, measured value is sent to the wireless sensing receiving terminal by the wireless sensing transmitting terminal, and the wireless sensing receiving terminal is sent to the measurement data that receives in the communication module of PLC control module again.
Electrically-controlled valve parts, measurement component and radio receiving terminal in described PLC control module connection air-heating furnace and Heating Furnace Control device, the system pipeline, the control program that moves among the PLC are realized entering the adjusting control of air parameter in the pipeline.The upper monitoring computing machine connects the PLC control module, is used for starting, stops, the closing test flow process, shows pilot system duty, parameter in real time, and finishes the file of test figure and the printing of test findings.
The present invention carries out work in the following manner:
The source of the gas processing components is used to finish oil and water separation, the filtration, purification that system pipeline is inserted source of the gas.Cleaned air passes enters air-heating furnace and realizes that Fast Heating heats up, and the Heating Furnace Control device is controlled the heating power of air-heating furnace, realizes the adjusting control to air-heating furnace delivery air temperature.The main line system is made of gas path pipe, operation valve and survey sensor, and survey sensor in the main line system and operation valve are finished the measurement of gas parameter in the pipeline and regulated control.The pneumatic valve Control Component connects pneumatic pressure-release valve and the pneumatic flow control valve in the main line system, for it provides the input air pressure signal of regulating and controlling amount.The metal hose assembly is used to connect main Pneumatic pipe and aircraft cabin interface.The wireless sensing communication module is temperature, the pressure measuring value of aircraft cabin porch, and the pressure of engine room inside, pressurising speed measurement value feedback send to the PLC control module.Opertaing device and measuring equipment in the PLC control module connected system, and constitute the PLC control system of central control function test with the upper monitoring computing machine, realize the sequential control of experiment process and the monitoring of system state.
Oil-water separator and accurate filter are used for the filtration, purification of big flow plant source, guarantee to enter the air cleanliness of system pipeline; Pneumatic ball valve is used for opening or closing source of the gas entering follow-up pipeline; Before pneumatic ball valve was opened, solenoid valve was discharged the ponding in oil-water separator and the accurate filter by discharging water.
Adopt the high-temperature hot air source of the gas to replace engine or APU source of the gas in cabin air adjustment in the aircraft environmental control system function test and the anti-icing system test, the air that requires on the engineering to enter the aircraft cabin pipeline is rapidly heated, and can stablize control to the temperature of test air.Because various valve arrangements are subjected to the restriction of its environment for use temperature in the pilot system pipeline, the atmosphere temperature rising in the system pipeline can not surpass the upper limit that equipment bears.The experiment automatized device of aircraft central control function of the present invention is controlled the temperature in air heat outlet of still and aircraft connecting pipe assembly exit respectively.Before hot-air entered the aircraft cabin pipeline, the pipeline to pilot system carried out preheating earlier, and the hot-air pipeline pneumatic flowrate variable valve in the pilot system pipeline is in full-gear at this moment, and cooled-air line pneumatic flowrate variable valve is in the complete shut-down state.The air-heating furnace temperature controller is according to the output power of the feedback regulation pressure regulation power controller of air heat heater outlet temperature, the outlet temperature of air-heating furnace is stabilized in the preset temperature range, can guarantees that the temperature rise of system pipeline can not surpass the upper limit of the serviceability temperature of various operation valves in the pipe system.In the preparatory stage of passenger cabin air temperature modification and anti-icing system test, can carry out preheating to the pilot system pipeline, hot-air is discharged by the pneumatic flowrate variable valve on the bypass line, and system pipeline can be rapidly heated.After test is ready to complete, open the path that connects the aircraft cabin pipeline, hot-air enters the aircraft cabin pipeline by the metal hose assembly.At this moment, the PLC control module, the input pressure signal size of regulating pneumatic flowrate variable valve on hot-air pipeline and the cooled-air line according to the Temperature Feedback of aircraft cabin porch, ratio realization that hot-air mixes with cold air is controlled and the purpose of stable aircraft cabin porch air themperature by changing.
After some pilot projects of finishing aircraft environmental control system function test, by switching the break-make of flow measurement branch road in the main line system, promptly open the flow measurement path that is used for next pilot project, close other flow measurement path, can finish all items of environmental control system function test at former test station, and needn't test station to other by mobile aircraft, improved the efficient of test.
This device can be realized functions such as the automatic collection, transmission, processing record, dynamic monitoring control, historgraphic data recording, test findings output print of real-time information in the environmental control system function test, realize the robotization of central control function process of the test control, effectively improved the operation and management level of measuring accuracy and central control function testing equipment.
Adopt the experiment automatized device of aircraft central control function of the present invention with respect to traditional central control function research technique, have following advantage: 1. the environmental control system function test relates to a plurality of pilot projects, traditional test method needs many complete equipments just can finish all environmental control system function test projects, as cockpit pressure exerciser, tightness test platform, ground breakout box etc., automation equipment of the present invention can be finished the project of all environmental control system function tests; 2. device electricity consumption heating source of the gas of the present invention replaces the hot gas source of aircraft engine or APU, in the serviceable life of having improved engine or APU effectively, reduces the noise of test site, the potential safety hazard of having avoided engine or APU ground run to bring simultaneously; 3. traditional testing equipment adopts manually-operated mode, and the measuring equipment of test parameters mainly is the instrument of pointer-type or mercury pillar and arranges and disperse that process of the test needs many people to coordinate; The operating process of this device is presented on the host computer in the parameter set of all measuring equipments by programmed control, and testing crew greatly reduces, and has effectively improved test efficiency; 4. this automation equipment is to the mass rate detection method that is based on the tapered flowmeter of V of bubble-tight pilot project employing, system pipeline adopts the branch road of different latus rectums to be used for the pilot project of different flow scope with further raising accuracy of detection, detect with respect to traditional pressure decline method, precision improves more than three times, and the time of air-tight test is reduced by half; 5. traditional test method needs testing crew by visual instrument, and the mode of hand-kept writes down the data of process of the test and test findings, and this device can be finished the historical data file of test automatically and print with test findings.
Description of drawings
Fig. 1 is a structural representation of the present invention.
Fig. 2 is the pipe system structural drawing;
Among the figure: pipe system by the double dot dash line shown in the figure be divided into four zones, upper left for source of the gas processing components, lower-left be air-heating furnace, upper right for pneumatic control valve module, bottom right be the main system pipeline.
Embodiment
Below embodiments of the invention are elaborated, present embodiment is being to implement under the prerequisite with the technical solution of the present invention, provided detailed embodiment and concrete operating process, but protection scope of the present invention is not limited to following embodiment.
As shown in Figure 1, present embodiment comprises: source of the gas processing components 1, air heat electric furnace 2, air heat furnace controller 3, main line system 4, pneumatic valve Control Component 5, aircraft connecting pipe assembly 6, aircraft 7, wireless sensing communication module 8, PLC control module 9 and upper monitoring computing machine 10, wherein: source of the gas processing components 1 is connected with air heat electric furnace 2, air heat electric furnace 2 is connected with main line system 4, air heat furnace controller 3 is connected with air-heating furnace 2 and transmits the signal that control air-heating furnace 2 temperature are exported, main line system 4 is connected with pneumatic valve Control Component 5, the pneumatic control valve of pneumatic valve Control Component 5 transmission and air pressure control signals in the main line system 4, metal hose assembly 6 one ends are connected with main line system 4, the other end is connected with the ring control test interface of aircraft 7, wireless sensing communication module 8 transmitting terminals are connected with metal hose assembly 6 and transmit the ring control test interface air measured parameter data information of aircraft 7, PLC control module 9 is connected with wireless sensing communication module 8 receiving ends and receives the data message that wireless sensing communication module 8 transmits, PLC control module 9 links to each other with source of the gas processing components 1 and transmits the switching information of source of the gas processing components 1 operation valve, PLC control module 9 is connected with air heat furnace controller 3 and transmits the control and the monitoring information of air-heating furnace 2, PLC control module 9 is connected with pneumatic control valve module 5 and transmits the control and the status information of operation valve, PLC control module 9 is connected with main line system 4 and transmits the control and the metrical information of operation valve and sensor, and upper monitoring computing machine 10 is connected with PLC control module 9 and transmits man-machine exchange message.
The plant source pipeline links to each other with source of the gas processing components 1, after source of the gas enters system pipeline, at first finishes the filtration, purification that system pipeline is inserted source of the gas by source of the gas processing components 1.Cleaned air passes enters and realizes in the air-heating furnace 2 that Fast Heating heats up, and the heating power of 3 pairs of air-heating furnaces 2 of Heating Furnace Control device carries out regulating and controlling, realizes the temperature control to the heat outputting air.Main line system 4 is made of gas path pipe, operation valve and survey sensor, and survey sensor in the main line system 4 and valve are finished the measurement of gas parameter in the pipeline and regulated control.Pneumatic pressure-release valve and pneumatic flow control valve that pneumatic valve Control Component 5 connects in the main line system 4 are for it provides controlled pressure.Metal hose assembly 6 is used to connect the cabin interface of main Pneumatic pipe 4 and flight test vehicle 7.Wireless sensing communication module 8 is porch, cabin air themperature, the pressure measuring value of flight test vehicle 7, and the pressure of engine room inside, pressurising speed measurement value feedback send to PLC control module 9.Other measuring equipment and control panel are used for the measurement of test parameters and the automatic control of process of the test in 9 while of the PLC control module connected system pipeline.The operation valve that PLC control module 9 connects in the source of the gas processing components 1 is used to control the break-make of access source of the gas and the control that discharges water of filtrator; Connect the hot air temperature that air heat furnace controller 3 is used to control the output of air-heating furnace 2; Connect operation valve and measuring equipment in the main line system 4, process control that is used to test and parameter measurement; Connect solenoid valve and electric Proportion valve in the pneumatic valve Control Component 5, by the action of pneumatic control valve and pneumatic pressure-release valve in the electric Proportion valve control main line system 4; PLC control module 9 is connected with upper monitoring computing machine 10, constitutes the automatic control system of central control function test, and upper monitoring computing machine 10 is realized the sequential control of experiment process and the Monitoring and Controlling of system state as the monitor terminal of test.
As shown in Figure 2, described pipe system according to separately the part function can be divided into four zones, shown in double dot dash line among the figure, wherein upper left is the source of the gas processing components, the lower-left is an air-heating furnace, upper right is the pneumatic valve Control Component, the bottom right is the main system pipeline.Manually operated control valve 12,13,22,23,24,27 among the figure is mainly used in the channel check of pipe system self, all keeps the on off state of acquiescence in system's use, and wherein valve 12,22 is in acquiescence complete shut-down state; Valve 13,23,27 is in the acquiescence full-gear.What Pneumatic pressure safety valve 40 was set is that the aircraft air condition pipeline is allowed the maximum pressure that bears.37 pairs of air of ducted accurate straight filter enter before the aircraft cabin inside filtration, purification once more.Filtrator 51 is used for purifying the air that enters pneumatic valve Control Component 5, and accurate reduction valve 50 is the input pressure that electric Proportion valve 45,46,49 is set the work source of the gas.The input pressure signal of pneumatic flowrate variable valve 25,26 is provided by electric Proportion valve 49 in the pipe system, the break-make of solenoid valve 48 control air pressure signals; The input air pressure signal of pneumatic flowrate variable valve 29,38 is provided by electric Proportion valve 45, and solenoid valve 44 is used to switch the path of air pressure signal.Pneumatic flowrate variable valve 25,29,38 is " normally closed ", opens gradually with the increase of input air pressure signal; Pneumatic flowrate variable valve 26 is " often opening ", closes gradually with the increase of input air pressure signal.The input air pressure signal of pneumatic pressure-release valve 28 is provided by electric Proportion valve 46, the break-make of solenoid valve 48 control air pressure signals, and the valve port opening of pneumatic pressure-release valve 28 increases with the increase of input air pressure, is used for the adjusting to main line system output stream amount and pressure.Pressure transducer 20 is used to measure the bleed pressure value, and temperature sensor 21 is used for the temperature that air conditioning test is measured the air heat outlet of still, and temperature sensor 36 is used for measuring the pre-heating temperature of air conditioning test pipeline.
Below in conjunction with the embodiment of description of drawings present embodiment patented technology scheme, provide detailed embodiment and concrete operating process.
1, aircraft air condition pipeline leakage check test
The leak test of aircraft air condition pipeline is the main contents of aircraft general assembly function test Center Vent tube road leak check, the gas-tight test pressure that is characterized in pipeline is bigger, be generally 45PSI, and the leakage rate of pipeline is less, to the measurement requirement precision height of leakage rate, measuring error requirement≤± 0.5%.The amount of leakage of air-conditioning duct changes with the variation of charge pressure, and the precision of voltage regulation of traditional tightness test platform is relatively poor, employing be the measuring method of volumetric flow rate, the fluctuation of test pressure and environment temperature can cause measuring accuracy to produce bigger error.The pipeline leakage quantity measuring method that automation equipment adopted of present embodiment is the mass rate method, can be automatically to pipeline inflation carrying out voltage stabilizing control, and the measuring accuracy of leakage rate greatly improves.The operating process of aircraft air condition pipeline leakage check test in the present embodiment is described below in conjunction with Fig. 1 and Fig. 2.
1) metal hose assembly 6 is inserted aircraft cabin air-conditioning duct interface, after test preliminary work is finished, start the automation equipment system program, select aircraft air condition pipeline earial drainage check test program by upper monitoring computing machine 10.Plant source enters source of the gas processing components 1 by pipeline access port 11, and system opens the electromagnetic water discharging valve 16 of oil mist separator 14, accurate filter 15 belows automatically, by the outlet 17 that discharges water ponding is discharged, and closes electromagnetic water discharging valve 16 after discharging water three minutes.
2) open pneumatic ball valve 18,30,41 automatically, the path of system pipeline is opened, and the source of the gas air enters the system pipeline of test unit.Add electrothermal stove group 19 in this test and do not work on power, but the test air passes through from electric furnace.At this moment, electric Proportion valve 45,49 no air pressure signal outputs, pneumatic flowrate variable valve 25,29 is in closed condition, pneumatic flowrate variable valve 26 standard-sized sheets, electric Proportion valve 46 is according to the pressure feedback input air pressure signal of aircraft cabin pipeline porch, regulate the aperture of pneumatic pressure-release valve 28, the test air flows to pneumatic pressure-release valve 28 by pneumatic flowrate variable valve 26 in the pipeline.
3) the test air in the pipeline is exported through pneumatic pressure-release valve 28 pressure regulation, 2 " pneumatic ball valve on the pipeline 30 is shown in an open position; 4 " pneumatic ball valve 31 and 6 on the pipeline " pneumatic ball valve 32 on the pipeline is closed; the air of circulation enters 2 " pipeline, the test air mass flow is by 2, and " the tapered mass flowmeter 33 of V is measured.
4) this moment, pneumatic flowrate variable valve 38 was in the closed position with bypass solenoid valve 39, pneumatic ball valve 41 is in full-gear, the test air is by 2, and " pipeline flows out; through straight filter 34 and pneumatic ball valve 41, by exporting the air-conditioning duct that the 42 metal hose assemblies 6 that join enter aircraft cabin with main line.
5) PLC control module 9 is according to the pressure of the aircraft air condition pipeline inlet of wireless sensing communication module 8 feedbacks, regulate the output pressure size (solenoid valve 47 is in conduction position) of control electric Proportion valve 46, regulate the aperture of control pneumatic pressure-release valve 28, the pressure stability that makes the aircraft air condition pipeline is in the goal pressure scope.
6) this moment 2, " it was leakage rate under the goal pressure in charge pressure that the flow that the tapered mass flowmeter of the V of pipeline 33 shows is the aircraft air condition pipeline.If find that leakage rate exceeds standard, then by stopping test in the upper monitoring computing machine 10, with electric Proportion valve 46 output pressure zero setting, pneumatic pressure-release valve 28 is closed, and open bypass solenoid valve 29 gases at high pressure of aircraft air condition pipeline are discharged by air silencer 43, by testing crew the aircraft air condition pipeline is overhauled troubleshooting then.
7) after troubleshooting is finished, repeat above-mentioned 4 by upper monitoring computing machine 10) to 6) process, the leakage rate that detects until test reaches engine request.After the stand the test, can withdraw from test routine by upper monitoring computing machine 10, close the pneumatic ball valve 18 of source of the gas end successively, with electric Proportion valve 46 output pressure zero setting, close solenoid valve 47, close pneumatic pressure-release valve 28, open bypass solenoid valve 29, after the gases at high pressure of aircraft air condition pipeline were discharged, bypass solenoid valve 29 was closed with pneumatic ball valve 41.
8) measurement data of process of the test is filed by upper monitoring computing machine 10 records, and can print test findings this moment by upper monitoring computing machine 10.
2, the function test of aircraft pressure cabin
The function test of aircraft pressure cabin mainly contains pilot projects such as the leak test, the test of passenger cabin voltage regulation function, exhaust valve functional check of pressure cabin.The pressure limit of the function test of aircraft pressure cabin is 4.0～8.5PSI, and pressure controlled accuracy requirement is higher, and the passenger cabin leakage rate is than big many of the amount of leakage of air-conditioning duct.What traditional aircraft cockpit tightness test was adopted is pressure decline method, promptly charge into the gas of certain pressure to aircraft cabin, make pressure keep stopping air feed after a period of time, observe air pressure feedback instrument, record pressure drops to the time of a certain particular value, judges by the step-down time whether the passenger cabin impermeability is qualified.The measuring accuracy of this method is poor, and is consuming time longer.In addition, traditional aeration test platform or tightness test device mostly are manual operations, and the inflation rate of test is difficult to accurate control, and the cockpit pressure of test is difficult to stablize, and operability is relatively poor.The operating process of aircraft pressure cabin function test in the present embodiment is described below in conjunction with Fig. 1 and Fig. 2.
1) metal hose assembly 6 is inserted aircraft pressure cabin interface, after test preliminary work is finished,, select aircraft pressure cabin Functional Test Procedure by upper monitoring computing machine 10 start-up system programs.Plant source enters source of the gas processing components 1 by pipeline access port 11.
2) open pneumatic ball valve 18,31,41 automatically, the path of system pipeline is opened, and the source of the gas air enters system pipeline.Add electrothermal stove group 19 in this test and do not work on power, but the test air in the pipeline passes through from electric furnace.At this moment, electric Proportion valve 45,49 no air pressure signal outputs, pneumatic flowrate variable valve 25,29 is in closed condition, pneumatic flowrate variable valve 26 standard-sized sheets, electric Proportion valve 46 is according to the pressure feedback input air pressure signal of aircraft cabin pipeline porch, regulate the aperture of pneumatic pressure-release valve 28, the test air in the pipeline flows to pneumatic pressure-release valve 28 by pneumatic flowrate variable valve 26, and exports after pressure regulation.
3) after the test air in the pipeline flowed out from pneumatic pressure-release valve 28, the pneumatic ball valve 32 on 2 " pneumatic ball valve 30 and 6 on the pipeline " pipeline was closed.4 " pneumatic ball valve on the pipeline 31 is opened, and the test air enters 4, and the tapered mass flowmeter 33 of " pipeline, the test air mass flow of circulation is by 4 " V is measured.
4) this moment, pneumatic flowrate variable valve 38 was in the closed position with bypass solenoid valve 39, pneumatic ball valve 41 is in full-gear, the test air is by 4, and " pipeline flows out; through straight filter 37 and pneumatic ball valve 41, by exporting the air-conditioning duct that the 42 metal hose assemblies 6 that join enter aircraft cabin with main line.
5) PLC control module 9 is according to the pressure of the aircraft air condition pipeline inlet of wireless sensing communication module 8 feedbacks, the aperture of coming pneumatic pressure-release valve 28 by the output pressure size (solenoid valve 47 is in conduction position) of regulating control electric Proportion valve 46, inflate in aircraft cockpit with the rate of pressure rise of test program regulation and to boost, reach predetermined value and stablize until cockpit pressure.
6) this moment is by 4, and " the tapered mass flowmeter of the V of pipeline 34 shows flows judge whether the leakage of aircraft pressure cabin exceeds standard, whether operate as normal and passenger cabin voltage regulation function be normal for exhaust valve.If find that the leakage of aircraft pressure cabin exceeds standard or the passenger cabin voltage regulation function is unusual, then by stopping test in the upper monitoring computing machine 10, with electric Proportion valve 46 output pressure zero setting, pneumatic pressure-release valve 28 is closed, PLC control module 9 is controlled the aperture (this moment, solenoid valve 44 was opened) of electric Proportion valves 45 output pressure Signal Regulation pneumatic flowrate variable valve 38 simultaneously, overbottom pressure air in the aircraft pressure cabin is discharged by air silencer 43 by the rate of pressure reduction of test program requirement, by testing crew aircraft pressure cabin or passenger cabin voltage regulation function equipment are overhauled troubleshooting then.
7) after troubleshooting is finished, repeat above-mentioned 4 by upper monitoring computing machine 10) to 6) process, reach engine request until every function test of pressure cabin.After the stand the test, can withdraw from test routine by upper monitoring computing machine 10, close the pneumatic ball valve 18 of source of the gas end successively, with electric Proportion valve 46 output pressure zero setting, close solenoid valve 47, pneumatic pressure-release valve 28 is closed, the aperture of electric Proportion valve 45 output pressure Signal Regulation pneumatic flowrate variable valve 38 (this moment, solenoid valve 44 was opened), aircraft pressure cabin overbottom pressure air is discharged by the rate of pressure reduction of test program requirement, then with electric Proportion valve 45 output pressure zero setting, close solenoid valve 44, pneumatic flowrate variable valve 38 cuts out, again pneumatic ball valve 41 is closed.
8) measurement data of process of the test is filed by upper monitoring computing machine 10 records, and can print test findings this moment by upper monitoring computing machine 10.
3, aircraft air-conditioning system and deicing system function test
The characteristics of aircraft air-conditioning system and deicing system function test be the temperature of test air up to 150～170 ℃, and air mass flow is big, the air that testing requirements enters aircraft air-conditioning system and the deicing system pipeline predetermined temperature that is rapidly heated.At present, the air-conditioning system of domestic middle-size and small-size aircraft and deicing system function test all are to provide the hot gas source by aircraft engine or APU, the test noise is big and have a potential safety hazard, the supply difficult parameters in hot gas source is with quantification simultaneously, the fault of engine or APU self can cause the reliability of aircraft central control function test to reduce, even can't finish.The operating process of aircraft air-conditioning system and deicing system function test in the present embodiment is described below in conjunction with Fig. 1 and Fig. 2.
1) metal hose assembly 6 is inserted aircraft cabin air-conditioning duct interface, after test preliminary work is finished,, select aircraft pressure cabin Functional Test Procedure by upper monitoring computing machine 10 start-up system programs.Plant source enters source of the gas processing components 1 by pipeline access port 11.
2) open pneumatic ball valve 18,32 automatically, the output pressure (this moment solenoid valve 44 open) of PLC control module 9 by regulating electromagnetic proportional valve 45 makes pneumatic flowrate variable valve place 38 be in fully open position; PLC control module 9 is according to 6, and " the flow feedback of V awl mass flowmeter 34; by the output pressure (this moment, solenoid valve 47 was opened) of regulating electromagnetic proportional valve 46; adjust the aperture of pneumatic pressure-release valve 28 makes air mass flow in the pipe system reach the flow value of pipeline preheating requirement.
3) this moment, PLC control module 9 heated the test air that adds 19 pairs of circulations of electrothermal stove group by air heat furnace controller 3.Air heat furnace controller 3 is according to the size of the electric furnace outlet temperature feedback adjusting heating power of temperature transmitter 21, make and add electrothermal stove group 19 outlet temperatures and be stabilized in about 350 ℃, can guarantee the equipment operate as normal in the temperature range that can bear in the pipeline like this, and system pipeline is rapidly heated.PLC control module 9 is according to temperature transmitter 36, regulate the output pressure (this moment, solenoid valve 48 was opened) of electric Proportion valve 49, go to control the aperture size of pneumatic flowrate variable valve 25,26, thereby the blending ratio of cold air and hot-air in the change pipeline remains in the scope of setting the preheat temperature of system pipeline.Preheated air is flowed out by pneumatic flowrate variable valve 38, discharges outdoor by air silencer 43.
4) after the instruction that receives aircraft cabin pulpit testing crew, system program is opened pneumatic ball valve 41, and the aperture of pneumatic flowrate variable valve 38 is adjusted to 25% of standard-sized sheet degree, and the hot-air in the pipeline enters aircraft air condition and deicing system pipeline.If the valve of aircraft air condition and deicing system pipeline is closed suddenly, air in the system pipeline will be got rid of from pneumatic flowrate variable valve 38, it is that the air mass flow in the pipeline is not less than the minimum definite value of electric furnace heating when guaranteeing to add 19 work of electrothermal stove group that the aperture of pneumatic flowrate variable valve 38 is adjusted to 25% of standard-sized sheet degree.
5) this moment, PLC control module 9 was according to the force value at the aircraft cabin pipe interface place of wireless sensing communication module 8 feedbacks, regulate the output pressure of electric Proportion valve 48, the aperture size of control pneumatic pressure-release valve 28 makes the pressure stability at aircraft cabin pipe interface place in the scope that test program requires; PLC control module 9 is according to the temperature value at the aircraft cabin pipe interface place of wireless sensing communication module 8 feedbacks simultaneously, regulate the output pressure of electric Proportion valve 49, the aperture size of control pneumatic flowrate variable valve 25,26, thereby the blending ratio of cold air and hot-air in the change pipeline, the temperature stabilization that makes aircraft cabin pipe interface place is in the claimed range of test program.
6) if find the fault of aircraft air-conditioning system and deicing system in the process of the test, then close pneumatic ball valve 41, simultaneously pneumatic flowrate variable valve 38 is all opened, keep pipe system to be in preheat mode by upper monitoring computing machine 10.
7) after troubleshooting is finished, repeat above-mentioned 5 by upper monitoring computing machine 10) to 7) process, reach engine request until every function test of aircraft air-conditioning system and deicing system.After the stand the test, can withdraw from test routine by upper monitoring computing machine 10, system program is at first closed and is added electrothermal stove group 19, circulation of air in the maintenance pipeline is after three minutes, close the pneumatic ball valve 18 of source of the gas end successively, with electric Proportion valve 46 output pressure zero setting, close solenoid valve 47, pneumatic pressure-release valve 28 is closed; With electric Proportion valve 49 output pressure zero setting, close solenoid valve 48; With electric Proportion valve 45 output pressure zero setting, close solenoid valve 44, pneumatic flowrate variable valve 38 cuts out, again pneumatic ball valve 41 is closed.
8) measurement data of process of the test is filed by upper monitoring computing machine 10 records, and can print test findings this moment by upper monitoring computing machine 10.
The experiment automatized device of the described aircraft central control function of present embodiment comprehensively adopts PLC technology, automatic control technology, wireless sensing acquisition technique, realizes the multiparameter centralized control of central control function test.Adopted the air heat electric furnace in the experiment automatized device main line system of present embodiment, the test source of the gas of normal temperature to 200 ℃ can be provided, the main line system design flow measurement pipeline of different latus rectums of three parallel connections, can measure the air mass flow of 0～5000kg/h wide range scope, thereby can finish above-mentioned three class aircraft environmental control system function test projects, and existing experimental technique needs many cover specialized equipments just can finish above-mentioned environmental control system function test project, with respect to existing testing equipment, the experiment automatized device of present embodiment can make the whole efficiency of central control function test improve more than the twice.The device main line system of present embodiment adopts the flow measurement pipeline of different latus rectums, the application quality discharge method detects the impermeability of aircraft cockpit and system pipeline, accuracy of detection can reach ± and 0.5%, the pressure decline method precision wider with respect to present application improves more than three times, and the time of air-tight test is reduced by half.The experiment automatized device of present embodiment adopts the pneumatic flowrate variable valve in pneumatic valve Control Component and the main pneumatic line, the control structure that pneumatic pressure-release valve constitutes, possess the function of test gas being carried out simultaneously temperature adjustment and pressure regulation, existing aircraft central control function testing equipment does not possess this function.
Claims (8)
1. automation equipment that is used for civil aircraft environment control system function test, it is characterized in that, comprise: the source of the gas processing components, the air heat electric furnace, the air heat furnace controller, the main line system, the pneumatic valve Control Component, the metal hose assembly, the wireless sensing communication module, PLC control module and upper monitoring computing machine, wherein: the source of the gas processing components is connected with the air heat electric furnace, the air heat electric furnace is connected with the main line system, the air heat furnace controller is connected with air-heating furnace and transmits the signal that control air heat furnace temperature is exported, the main line system is connected with the pneumatic valve Control Component, the pneumatic control valve of pneumatic valve Control Component transmission and air pressure control signal in the main line system, metal hose assembly one end is connected with the main line system, the other end is connected with aircraft ring control test interface, wireless sensing communication module transmitting terminal is connected with the metal hose assembly and transmits aircraft ring control test interface air measured parameter data information, the PLC control module is connected with wireless sensing communication module receiving end and receives the data message that the wireless sensing communication module transmits, the PLC control module links to each other with the source of the gas processing components and transmits the switching information of source of the gas processing components operation valve, the PLC control module is connected with the air heat furnace controller and transmits the control and the monitoring information of air-heating furnace, the PLC control module is connected with the pneumatic control valve module and transmits the control and the status information of operation valve, the PLC control module is connected with the main line system and transmits the control and the metrical information of operation valve and sensor, and the upper monitoring computing machine is connected with the PLC control module and transmits man-machine exchange message.
2. the automation equipment that is used for civil aircraft environment control system function test according to claim 1, it is characterized in that, described source of the gas processing components is carried out oil and water separation and filtration, purification to the plant source that enters system pipeline, this source of the gas processing components comprises: two manually operated control valves, an oil-water separator, two accurate filters, three electromagnetic water discharging valves and a pneumatic ball valve, wherein: the source of the gas air inlet pipeline is divided into two branch roads by two manually operated control valves, one of them branch road is connected with oil-water separator and two accurate filters successively, oil-water separator is in inlet end, be connected with pneumatic ball valve after the endpiece parallel connection of another branch road and two described accurate filters, three electromagnetic water discharging valves join with the lower end of oil-water separator and two accurate filters respectively, and pneumatic ball valve is connected with the PLC control module respectively with solenoid valve and transmits the switch state signal and the control signal of pneumatic ball valve and solenoid valve.
3. the automation equipment that is used for civil aircraft environment control system function test according to claim 1, it is characterized in that, described air-heating furnace is used for the air that enters heating furnace is heated, the input end of this air-heating furnace is connected with the output channel of source of the gas processing components, the output terminal of air-heating furnace is installed a temperature sensor, temperature sensor is connected with the air heat furnace controller and transmits air-heating furnace outlet air temperature measuring-signal, and the air heat furnace controller is connected with air-heating furnace and transmits the control signal of heating power.
4. the automation equipment that is used for civil aircraft environment control system function test according to claim 1, it is characterized in that, described main line system is to air pressure in the aircraft environmental control system function test, the primary structure part of flow regulation, this main line system comprises: four manually operated control valves, four pneumatic flowrate variable valve, a pneumatic pressure-release valve, four pneumatic ball valves, a solenoid valve, two straight pipe type air strainers, an air silencer, two temperature sensors, a pressure transducer and three tapered mass flowmeters of V, wherein: the input end of main line system is divided into cold-air duct and hot-air duct, cold-air duct is connected with the output channel of source of the gas processing components, hot-air duct is connected with air-heating furnace, be provided with a pressure transducer on the cold-air duct successively, a manually operated control valve, a pneumatic flowrate variable valve and a pneumatic pressure-release valve, pressure transducer is connected with the PLC control module and transmits the interior air pressure of cold-air duct, be provided with a temperature sensor on the hot-air duct successively, a manually operated control valve, a pneumatic flowrate variable valve, a manually operated control valve and a pneumatic flowrate variable valve, temperature sensor is connected with the air heat furnace controller and transmits air-heating furnace outlet air temperature measuring-signal, be connected a bypass branch road between temperature sensor on the described hot-air duct and first manually operated control valve, connect a manually operated control valve on the bypass branch road, the by-pass line output terminal connects an air silencer, be connected by a branch road between first pneumatic flowrate variable valve output terminal on pneumatic flowrate variable valve output terminal and the hot-air duct on the described cold-air duct, after the pipeline of second pneumatic flowrate variable valve output terminal is connected on the pipeline of pneumatic pressure-release valve output terminal and the hot-air duct on the cold-air duct, mode by parallel connection is divided into 2 "; 4 " 6 " three path pipelines; a pneumatic ball valve and the tapered mass flowmeter of V respectively are installed on three path pipelines; pneumatic ball valve is connected with the PLC control module and transmits the switch state signal and the control signal of pneumatic ball valve; the tapered mass flowmeter of V be connected with the PLC control module and transmission pipeline in the detection signal of air mass flow; it is a path pipeline that three the tapered mass flowmeter endpiece of V pipelines converge; this section path pipeline is provided with a temperature sensor, this temperature sensor be connected with the PLC control module and transfer conduit in the measuring-signal of air themperature, pipeline after the temperature sensor is divided into three path pipelines by parallel way, article two, respectively connect a straight pipe type air strainer on the path pipeline, pneumatic flowrate variable valve of connection on another path pipeline, pneumatic flowrate variable valve output terminal pipeline is connected on the bypass bypass line that air silencer is installed simultaneously, the output terminal pipeline of a straight pipe type air strainer connects an air pressure safety valve, be connected a solenoid valve between another straight pipe type air strainer and the pneumatic flowrate variable valve, solenoid valve is connected with the PLC control module and transmits the switch state signal and the control signal of solenoid valve, connect a pneumatic ball valve on the pipeline of air pressure safety valve endpiece, pneumatic ball valve is connected with the PLC control module and transmits the switch state signal and the control signal of pneumatic ball valve, and the pipeline of pneumatic ball valve endpiece is connected to aircraft ring control test interface by the metal hose assembly.
5. the automation equipment that is used for civil aircraft environment control system function test according to claim 1, it is characterized in that, described pneumatic control valve module comprises: an air strainer, an accurate reduction valve, three electric Proportion valves and three solenoid valves, wherein: the inlet end pipeline of air strainer is connected to the inlet end of cold-air duct in the main line system, the endpiece of air strainer connects accurate reduction valve, accurate reduction valve endpiece three pneumatic lines that are connected in parallel, connect an electric Proportion valve and solenoid valve on every pneumatic line road successively, article one, pneumatic line electromagnetic valve outlet end is divided into two branch roads, is connected respectively to the pneumatic flowrate variable valve on the cold-air duct and first pneumatic flowrate variable valve on the hot-air duct in the main line system; Second pneumatic line electromagnetic valve outlet end is connected on the pneumatic pressure-release valve in the main line system; Article three, Pneumatic pipe electromagnetic valve outlet end is divided into two branch roads, be connected respectively to second pneumatic flowrate variable valve on the hot-air duct and the pneumatic flowrate variable valve that is in parallel with the straight pipe type air strainer in the main line system, three solenoid valves are connected respectively at the PLC control module with three electric Proportion valves and transmit the status signal and control model of valve, the output pressure of the input electrical signal may command electric Proportion valve by regulating electric Proportion valve, and then the aperture of control pneumatic pressure-release valve or pneumatic flowrate variable valve, thereby reach the purpose of control pneumatic pressure-release valve output pressure or pneumatic flowrate variable valve delivery rate, the solenoid valve between connection electric Proportion valve and the Pneumatic valve is used to control the break-make or the switching of pneumatic control circuit.
6. the automation equipment that is used for civil aircraft environment control system function test according to claim 1, it is characterized in that, described metal hose assembly is connected with the cabin interface that is connected main line system and the control of aircraft ring test, the test air enters interior of aircraft by aircraft connecting pipe assembly by main pneumatic line system, and temperature and pressure measurement interface is installed on the jointing of metal hose assembly and aircraft cabin interface.
7. the automation equipment that is used for civil aircraft environment control system function test according to claim 1, it is characterized in that, described wireless sensing communication module comprises: wireless sensing transmitting terminal and wireless sensing receiving end, wherein: the wireless sensing transmitting terminal is integrated temperature and pressure survey sensor, integrated survey sensor has the temperature that is connected to the metal hose joint place, pressure survey interface and cabin internal pressure are measured interface, measured value is sent to the wireless sensing receiving terminal by the wireless sensing transmitting terminal, and the wireless sensing receiving terminal is sent to the measurement data that receives in the communication module of PLC control module again.
8. the automation equipment that is used for civil aircraft environment control system function test according to claim 1, it is characterized in that, described PLC control module connects air-heating furnace and Heating Furnace Control device, electrically-controlled valve parts in the system pipeline, measurement component and radio receiving terminal, the control program that moves among the PLC is realized entering the adjusting control of air parameter in the pipeline, the upper monitoring computing machine connects the PLC control module, be used for starting, in stop, the closing test flow process, show the pilot system duty in real time, parameter, and finish the file of test figure and the printing of test findings.
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101162159A (en) * | 2006-10-13 | 2008-04-16 | 沈阳航天新光集团有限公司 | Method for designing pilotless aircraft ground observing and controlling system |
-
2010
- 2010-08-31 CN CN2010102678675A patent/CN101916108B/en not_active Expired - Fee Related
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101162159A (en) * | 2006-10-13 | 2008-04-16 | 沈阳航天新光集团有限公司 | Method for designing pilotless aircraft ground observing and controlling system |
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| CN101916108B (en) | 2012-07-04 |
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