CN105372290A - Aircraft ground thermal simulation test apparatus capable of rapidly cooling - Google Patents
Aircraft ground thermal simulation test apparatus capable of rapidly cooling Download PDFInfo
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- CN105372290A CN105372290A CN201510820839.4A CN201510820839A CN105372290A CN 105372290 A CN105372290 A CN 105372290A CN 201510820839 A CN201510820839 A CN 201510820839A CN 105372290 A CN105372290 A CN 105372290A
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- 238000001816 cooling Methods 0.000 title claims abstract description 184
- 238000012360 testing method Methods 0.000 title claims abstract description 101
- 238000004088 simulation Methods 0.000 title abstract description 27
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims abstract description 164
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 126
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 83
- 239000007788 liquid Substances 0.000 claims abstract description 77
- 238000000034 method Methods 0.000 claims abstract description 19
- 230000005855 radiation Effects 0.000 claims description 46
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 27
- 238000006243 chemical reaction Methods 0.000 claims description 20
- 230000001105 regulatory effect Effects 0.000 claims description 18
- 239000000498 cooling water Substances 0.000 claims description 17
- 229910052751 metal Inorganic materials 0.000 claims description 17
- 239000002184 metal Substances 0.000 claims description 17
- 239000000463 material Substances 0.000 claims description 14
- 238000009792 diffusion process Methods 0.000 claims description 13
- 230000001276 controlling effect Effects 0.000 claims description 9
- 239000013535 sea water Substances 0.000 claims description 9
- 239000007921 spray Substances 0.000 claims description 9
- 230000000694 effects Effects 0.000 claims description 8
- 230000001960 triggered effect Effects 0.000 claims description 6
- 239000000945 filler Substances 0.000 claims description 5
- 239000007789 gas Substances 0.000 claims description 4
- JEGUKCSWCFPDGT-UHFFFAOYSA-N h2o hydrate Chemical compound O.O JEGUKCSWCFPDGT-UHFFFAOYSA-N 0.000 claims description 4
- 238000005507 spraying Methods 0.000 claims description 4
- 238000009827 uniform distribution Methods 0.000 claims description 4
- 238000012856 packing Methods 0.000 claims description 3
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 abstract description 16
- 238000010998 test method Methods 0.000 abstract description 6
- 239000003570 air Substances 0.000 description 122
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 238000001914 filtration Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 229910001220 stainless steel Inorganic materials 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical group [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 230000000593 degrading effect Effects 0.000 description 1
- 238000009795 derivation Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 206010022000 influenza Diseases 0.000 description 1
- 230000036244 malformation Effects 0.000 description 1
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- 230000003020 moisturizing effect Effects 0.000 description 1
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- 229910052755 nonmetal Inorganic materials 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
- G01N25/20—Investigating or analyzing materials by the use of thermal means by investigating the development of heat, i.e. calorimetry, e.g. by measuring specific heat, by measuring thermal conductivity
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- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The invention discloses an aircraft ground thermal simulation test apparatus capable of rapidly cooling. The aircraft ground thermal simulation test apparatus comprises an air compressing system (A), a water/liquid nitrogen supply system (B), a first test piece heating-cooling test platform (C), a second test piece heating-cooling test platform (D), and a data acquisition and control system (E). The aircraft ground thermal simulation test apparatus can effectively integrate the heating and cooling systems of an aircraft, test piece position can be exchanged between a heating end and a cooling end on the heating-cooling test platform through a linear slide rail, after the test piece reaches a predetermined temperature, the test piece moves along the track and triggers a stroke switch so that a cooling working medium is released, rapid starting for cooling is realized, heating and cooling simulation test processes can be effectively connected; urgent demand for exploitation of novel high-speed aircrafts and guarantee of flight safety can be satisfied, and a ground thermal simulation test method can be improved.
Description
Technical field
The invention belongs to high-speed aircraft thermal simulation technical field, relate to a kind of can the aircraft ground thermal modeling test device of fast cooling.
Background technology
The lifting of high-speed aircraft (especially hypersonic vehicle) flying speed be degrading aircraft faced by thermal environment, violent Aerodynamic Heating can be produced in its flight course, body surface temperature can rise to over 1000 DEG C under the effect of Aerodynamic Heating, and because of factor impacts such as aircraft down in flight course, high temperature surface may experience the process of a fast cooling.The fast cooling on high temperature surface can cause that thermal stress is excessive, seal failure, malformation and destruction, the safety of aircraft and normal flight are caused and have a strong impact on.For some parts and material, need the process at its fast cooling of ground simulation, observe the concrete situation of change of material and parts and detect its reliability by thermal modeling test.
In order to reduce experimentation cost, avoid flight test and wind tunnel test, the thermal modeling test device on ground becomes the necessary means that numerous high-speed aircraft carries out detecting, by testpieces surface apply required for heat flow density, can at ground accurate reproduction associated materials and parts being heated and temperature variations in flight course.
But, thermal modeling test device mostly is Aerodynamic Heating process simulation both at home and abroad at present, as using infrared radiation heater or graphite heater as thermal source, simulate pneumatic heat hot stream, test material and the specific performance of parts under Aerodynamic Heating effect, cannot meet the testing requirements of temperature-fall period simulation, in document, also rare similar cooling analogue means is reported.How cooling simulation realizes, how simulate with heating process and be connected, and these problems all can affect the development& testing of new high-speed aircraft.
For this reason, build the fast cooling ground level heat simulation test device that can meet the requirement of high-speed aircraft thermal modeling test, being the active demand of developing new high-speed aircraft, ensureing its flight safety, is also the important means improving ground level heat simulation experiment method.
Summary of the invention
The problem that the present invention solves be to provide a kind of can the aircraft ground thermal modeling test device of fast cooling, meet the fast cooling demand of different size, different materials testpieces, and different rate of temperature fall can be provided.
The present invention is achieved through the following technical solutions:
Can the aircraft ground thermal modeling test device of fast cooling, this device comprises compressed air system, water/liquid nitrogen supply system, the first testpieces heating-pull-down test platform, the second testpieces heating-pull-down test platform and Data Acquisition and Conversion System (DACS);
Described compressed air system heats-pull-down test platform to the first testpieces, the second testpieces heating-pull-down test platform provides pressurized air as temperature-reducing medium, the valve that setting data data acquisition and controlling system is controlled on the pipeline that it provides temperature-reducing medium;
Described water/liquid nitrogen supply system to the second testpieces heat-pull-down test platform provides water/liquid nitrogen as temperature-reducing medium, the valve that setting data data acquisition and controlling system is controlled on the pipeline that it provides temperature-reducing medium;
The first described testpieces heating-pull-down test platform, the second testpieces heating-pull-down test platform are respectively equipped with the track that infrared radiation heater, the cooling device receiving temperature-reducing medium and heating-cooling position are changed, track is provided with testpieces pedestal; Testpieces is placed on testpieces pedestal and moves can change at fire end and colling end with it, the travel switch starting temperature-reducing medium release is also provided with in the outside in cooling hot junction, trigger travel switch when pedestal moves to colling end, travel switch is opened, and temperature-reducing medium enters into cooling device.
Described compressed air system comprises piston type air compressor, its air out is connected with oil-water separator, be connected with gas-holder by filtrator, the outlet of gas-holder is connected with the first diffuser, pressurized air after preliminary diffusion enters air passage through flowmeter and air cooling opening and closing solenoid valve, air passage heats with the first testpieces-pull-down test system in be connected as the array jetting cooling module of cooling device, pressurized air produces array jetting in array jetting cooling module after further diffusion and rectification.
Described oil-water separator, by being connected with the second gas-holder with the first gas-holder respectively after three grades of accurate filters, the pipeline between accurate filter and gas-holder is also provided with the first stop valve; Oil-water separator is also connected with gas-holder by the pipeline being provided with the second stop valve; Control the first stop valve, pressurized air directly can be sent into gas-holder by the opening and closing of the second stop valve under plugged filter operating mode;
The upstream of the first described gas-holder, downstream pipe are also respectively equipped with the 3rd stop valve, the 4th stop valve, the switching of single/two gas-holder can be realized.
Described air cooling opening and closing solenoid valve connects the travel switch that can trigger, and is discharged in array jetting cooling module after it is triggered by the pressurized air in gas-holder; Described air passage comprises 4 passage controlled subregion cooling metal hose and for single channel cooling metal hose, 4 passage controlled subregion cooling flexible pipe is also respectively equipped with electric control valve, this electric control valve is by the control of data acquistion and control system, air mass flow is regulated, and then controls temperature-fall period; The flow signal of collection is sent to Data Acquisition and Conversion System (DACS) by described flowmeter.
Described array jetting cooling module comprises in the middle part of array jetting cooling module top, array jetting cooling module and array jetting cooling module bottom;
Described array jetting cooling module top is diffuser, comprises oral area and flaring passage, is provided with flow distributor at oral area, be also provided with monolithic porous, be folded with porous packing between monolithic porous in flaring passage); Described oral area number and single channel air passage or 4 channel air branch roads match;
Be rectification section in the middle part of described array jetting cooling module, in the passage in the middle part of array jetting cooling module, be provided with honeycomb;
Described array jetting cooling module bottom is the nozzle array of release medium, and nozzle is arranged in array at nozzle plate.
After pressurized air enters array jetting cooling module, pressurized air through flow distributor be uniformly distributed on module xsect and in flaring passage diffusion, the noise that its flow process produces is absorbed by the metal porous filling material be clipped between monolithic porous; Carry out rectification to air in the middle part of array jetting cooling module, air flows when flowing through honeycomb steadily and flow direction is consistent; The nozzle array of array jetting cooling module bottom is replaceable;
Described water/liquid nitrogen system comprises supercharging liquid nitrogen container and supercharging water tank, and described supercharging liquid nitrogen container enters water/liquid nitrogen/air delivery pipe through cryogenic flow gauge and stream selective cut-off valve;
The upper end of supercharging water tank be provided with filler and be connected with from supercharging liquid nitrogen container add gas port, lower end is provided with water delivering orifice, and water delivering orifice is connected with water/liquid nitrogen/air delivery pipe through filter, flowmeter branch road, stream selective cut-off valve;
The pressurized air of compressed air system enters into water/liquid nitrogen/air delivery pipe by air compressor by stream selective cut-off valve;
Water/liquid nitrogen/air delivery pipe is provided with travel switch, is connected with the nozzle as cooling device through water/liquid nitrogen/air opening and closing solenoid valve.
Described enters water/liquid nitrogen/air delivery pipe from the liquid nitrogen of supercharging liquid nitrogen container through cryogenic flow gauge and stream selective cut-off valve;
Water in supercharging water tank is under the pressure effect of nitrogen cylinder, enter after different flowmeter branch roads through filter and send into water/liquid nitrogen/air delivery pipe, supercharging water tank export pipeline is also provided with variable valve, regulates discharge when water jet cooling and water spray cooling;
Open the stream selective cut-off valve on different pipelines, make a kind of working medium in water/liquid nitrogen/air enter water/liquid nitrogen/air delivery pipe; Water/liquid nitrogen/air opening and closing solenoid valve is triggered when testpieces arrives below nozzle, and water/liquid nitrogen/air to be discharged by nozzle as heat eliminating medium and starts cooling fast; Described nozzle is straight tube-like nozzle or atomizer, produces jet or spraying.
Described testpieces pedestal is water-cooled base, and water-cooled base is installed water-cooled base in orbit by slide block and moved between infrared radiation heater and cooling device;
Described infrared radiation heater comprises the housing and the reflecting surface that are spliced to form well heater by water-cooling channel, water-cooling channel two ends arrange cooling water outlet and inlet respectively, infrared radiation fluorescent tube is arranged on infrared radiation heater by fluorescent tube fixing metal sheet, and is connected with the bus-bar of power supply; Infrared radiation heater is also connected with the SCR Intelligent power regulating eqiupment of controller power or autocoupling type pressure regulator;
Water tank is connected respectively by the cooling water outlet and inlet of the pipeline with infrared radiation heater that are provided with cooling sea water regulating valve, the cooling water outlet and inlet of testpieces pedestal, and regulates the discharge entered wherein; Between the cooling water outlet and inlet of infrared radiation heater, be also provided with cooled water distributor at cooling sea water regulating valve, cooled water distributor is by water yield uniform distribution between the water-cooling channel of infrared radiation heater; Also be provided with float and float switch watch-dog in water tank, float switch signal is sent into Data Acquisition and Conversion System (DACS) by float switch watch-dog, reports to the police respectively when low level and a high position.
Described data acquistion and control system (E) comprises data collecting instrument, switch board, PLC, control module and computing machine, wherein control module adopts PLC and touch-screen to form, wherein PLC can Real-time Collection testpieces surface temperature sensor temperature data and control the aperture of the electric control valve on temperature-reducing medium pipeline, and then the flow controlling temperature-reducing medium is to regulate rate of temperature fall;
Touch-screen is as controling parameters inputting interface and can show in real time, preserve temperature data from PLC, test specimen surface temperature situation of change in the controlled subregion temperature-fall period of display in real time;
Temperature, pressure and data on flows in data collecting instrument acquisition test process, and can show data and store;
Switch board is provided with multi-way switch and display lamp, can power for each instrument, PLC and touch-screen, the cooling water outlet temperature display of simultaneously piston type air compressor start and stop, the display of chilled water water level, testpieces pedestal and infrared radiation heater is all integrated in this switch board.
Compared with prior art, the present invention has following useful technique effect:
1) the present invention effectively incorporates heating and the cooling system of aircraft, heating-pull-down test platform realizes the conversion of testpieces position between fire end and colling end by line slide rail, after testpieces reaches predetermined temperature, trigger travel switch along rail moving cooling working medium is discharged, realize the quick startup of cooling, effectively can be connected heating and cooling simulation test procedure; The new high-speed aircraft of exploitation can be met, ensure the active demand of its flight safety, perfect ground level heat simulation experiment method;
2) the present invention adopts internal water cooling passage for large-size infrared radiation heater in heating process, can prevent its temperature distortion, ensures the Long-Time Service under hot conditions;
3) the present invention have employed the mode of segmentation diffusion as during cooling working medium, the air of supply needed for process of the test providing pressurized air, and have employed array jetting cooling module and produce uniform air-spray;
4) the heat eliminating medium supply system in the present invention can realize supply and the switching of pressurized air, water and liquid nitrogen, and can meet the pull-down test demand of different size, different materials testpieces;
5) hardware of control system of the present invention have employed PLC and touch-screen, can realize controlling the PID of large scale testpieces temperature-fall period, and temperature data also can show in real time and store.
Accompanying drawing explanation
Fig. 1 is fast cooling ground level heat simulation test device structural representation of the present invention;
Fig. 2 is the structural representation of array jetting cooling module of the present invention;
Fig. 3 is the structural representation of infrared radiation heater of the present invention;
Fig. 4 is controling parameters input and the monitoring interface of the touch-screen of data acquistion and control system of the present invention;
Fig. 5 is the data summarization of the touch-screen of data acquistion and control system of the present invention and derivation interface;
Fig. 6 is type testing curve of the present invention (400mm × 400mm × 8mm large-scale titanium alloy testpieces array air-spray pull-down test, pressure of storage tank 0.8MPa, nozzle quantity 16 × 16, nozzle height 5cm, 9 measuring points are in the distribution of testpieces surface uniform);
In figure: A-compressed air system, B-water and liquid nitrogen system, C-first testpieces heating-pull-down test platform, D-second testpieces heating-pull-down test platform, E-Data Acquisition and Conversion System (DACS), 1-piston type air compressor, 2-oil-water separator, 3-P level air strainer, 4-Q level air strainer, 5-S level air strainer, 6-first gas-holder (can close), 7-second gas-holder (often opening), 8-first diffuser, 9-is from supercharging liquid nitrogen container, 10-nitrogen cylinder, 11-supercharging water tank, 12-filtrator, the controlled cooling air passage of 13-4 passage subregion, 14-single channel cooling air passage, 15-array jetting cooling module, 16-water tank, 17-first testpieces pedestal, 18-cooled water distributor, 19-stainless steel flexible hose, 20-first infrared radiation heater, 21-first track, 22-first slide block, 23-water/liquid nitrogen/air delivery pipe, 24-nozzle, 25-second slide block, 26-second track, 27-second infrared radiation heater, 28-second testpieces pedestal, 29, 30-air feed stop valve, 31-first stop valve, 32-second stop valve, 33-the 3rd stop valve, 34-the 4th stop valve, 35-air cooling opening and closing solenoid valve, 36, 37, 38, 39-electric control valve, 40, 41, 42, 43, 44-stream selective cut-off valve, 45-liquid nitrogen conveying stop valve, 46-nitrogen cylinder reduction valve, 47-filler stop valve, 48-filler, 49-air pressure balance stop valve, 50-flow control valve, 51-cryogenic flow gauge 52, 53, 54, 55-flowmeter, 56-water/liquid nitrogen/air opening and closing solenoid valve, 57, 58-cooling sea water regulating valve, 59-SCR Intelligent power regulating eqiupment, 60-autotransformer, 61-draining valve, 62, 63-travel switch, 64-array jetting cooling module top, in the middle part of 65-array jetting cooling module, 66-array jetting cooling module bottom, 67-flow distributor, 68-monolithic porous, the metal porous filling material of 69-, 70-honeycomb, 71-nozzle plate, 72-nozzle, 73-bus-bar, 74-hanger, 75-water-cooling channel, 76-fluorescent tube fixing metal sheet, 77-infrared radiation fluorescent tube, 78-passage bridge button, 79-export data button, 80-data window, 81-data window, 82-chart area, 83-parameter adjustment window, 84-shift knob, 85-data form.
Embodiment
The present invention is the new demand in order to adapt to ground level heat simulation test, a kind of test unit that can carry out fast cooling process simulation is provided, simulate with heating to being connected cooling simulation, meet the fast cooling demand of different size, different materials testpieces, and different rate of temperature fall can be provided, realize the controlled subregion cooling of large scale testpieces.Below in conjunction with specific embodiment, the present invention is described in further detail, and the explanation of the invention is not limited.
See Fig. 1, can the aircraft ground thermal modeling test device of fast cooling, this device comprises compressed air system A, water/liquid nitrogen supply system B, the first testpieces heating-pull-down test platform C, the second testpieces heating-pull-down test platform D and Data Acquisition and Conversion System (DACS) E;
Described compressed air system A heats-pull-down test platform C to the first testpieces, the second testpieces heating-pull-down test platform D provides pressurized air as temperature-reducing medium, the pipeline that it provides temperature-reducing medium is arranged by the controlled valve of Data Acquisition and Conversion System (DACS) E;
Described water/liquid nitrogen supply system B to the second testpieces heat-pull-down test platform D provides water/liquid nitrogen as temperature-reducing medium, the pipeline that it provides temperature-reducing medium arranged by the controlled valve of Data Acquisition and Conversion System (DACS) E;
The first described testpieces heating-pull-down test platform C, the second testpieces heating-pull-down test platform D are respectively equipped with the track that infrared radiation heater 27, the cooling device receiving temperature-reducing medium and heating-cooling position are changed, track is provided with testpieces pedestal 17; Testpieces is placed on testpieces pedestal and moves can change at fire end and colling end with it, the travel switch starting temperature-reducing medium release is also provided with in the outside in cooling hot junction, when rail moving triggers travel switch to during colling end, travel switch is opened, and temperature-reducing medium enters into cooling device.
Wherein, wherein compressed air system A, water and liquid nitrogen system B for cooling simulation cooling working medium is provided, first testpieces heating-pull-down test platform C, the second testpieces heating-pull-down test platform D realize the heating-temperature-fall period of testpieces, and Data Acquisition and Conversion System (DACS) E acquisition test process data also can control controlled subregion cooling simulation test.
The open ended maximum testpieces of first testpieces heating-pull-down test platform C is of a size of 600mm × 600mm, and maximum heating power is 54kW.The open ended maximum testpieces of second testpieces heating-pull-down test platform D is of a size of 200mm × 200mm, and maximum heating power is 22kW.
Described compressed air system A comprises piston type air compressor 1, its air out is connected with oil-water separator 2, be connected with gas-holder by filtrator, the outlet of gas-holder is connected with the first diffuser 8, pressurized air after preliminary diffusion enters air passage through flowmeter 55 and air cooling opening and closing solenoid valve 35, air passage heats with the first testpieces-pull-down test system C in be connected as the array jetting cooling module 15 of cooling device, pressurized air produces array jetting in array jetting cooling module 15 after further diffusion and rectification.
Described oil-water separator 2, by being connected with the second gas-holder 7 with the first gas-holder 6 respectively after three grades of accurate filters, the pipeline between accurate filter and gas-holder is also provided with the first stop valve 31; Oil-water separator 2 is also connected with gas-holder by the pipeline being provided with the second stop valve 32; Pressurized air directly can be sent into gas-holder by the opening and closing controlling the first stop valve 31, second stop valve 32 under plugged filter operating mode;
The upstream of the first described gas-holder 6, downstream pipe are also respectively equipped with the 3rd stop valve 33, the 4th stop valve 34, the switching of single/two gas-holder can be realized.
Described air cooling opening and closing solenoid valve 35 controls by travel switch 62, is discharged in array jetting cooling module 15 after it is triggered by the pressurized air in gas-holder; Described air passage comprises 4 passage controlled subregion cooling metal hose and for single channel cooling metal hose, 4 passage controlled subregion cooling flexible pipe is also respectively equipped with electric control valve, this electric control valve is by the control of data acquistion and control system E, air mass flow is regulated, and then controls temperature-fall period; The flow signal of collection is sent to Data Acquisition and Conversion System (DACS) E by described flowmeter 55.
Concrete, piston type air compressor 1 indoor environment air-breathing produces pressurized air, pressurized air carries out coarse filtration through oil-water separator 2, three grades of accurate filters (3-P level air strainer, 4-Q level air strainer, 5-S level air strainer) are filtered further to pressurized air, and filter passage stop valve (31-first stop valve, 32-second stop valve) can by accurate filter short circuit under more renew cartridge or blocking operating mode; Pressurized air after filtration sends into gas-holder (6-first gas-holder (can close), 7-second gas-holder (often opening)) through pipeline, first gas-holder 6 can rely on gas-holder stop valve (33,34) to disconnect, and meets the operating condition of test requirement that gas consumption is few; The outlet of gas-holder connects air diffuser 8, and pressurized air can preliminary diffusion in flaring passage; Air cooling opening and closing solenoid valve 35 is closed under the control of travel switch 62 connects air flow circuit, and flowmeter 55 can measure the real-time traffic of air; Flange and single channel are lowered the temperature and to be connected with air passage 14 (metal hose), composition single channel cooling air flue, on flange, closure plate is installed during the 4 controlled cooling of passage subregion, electric control valve (36,37,38,39) connects the controlled cooling air passage 13 of 4 passage subregion respectively and forms 4 air flues, can for different cooling area provides different air mass flows under Data Acquisition and Conversion System (DACS) E effect.
See Fig. 2, described array jetting cooling module 15 to comprise in the middle part of array jetting cooling module top 64, array jetting cooling module 65 and array jetting cooling module bottom 66;
Described array jetting cooling module top 64 is diffuser, comprises oral area and flaring passage, is provided with flow distributor 67 at oral area, be also provided with monolithic porous 68 in flaring passage, be folded with porous packing 69 between monolithic porous 68; Described oral area number and single channel air passage or 4 channel air branch roads match;
In the middle part of described array jetting cooling module, 65 is rectification section, in the middle part of array jetting cooling module 65 passage in be provided with honeycomb 70;
Described array jetting cooling module bottom 66 is the nozzle array of release medium, and nozzle 72 is arranged in array at nozzle plate 71.
After pressurized air enters array jetting cooling module 15, pressurized air through flow distributor 67 be uniformly distributed on module xsect and in flaring passage diffusion, its flow process produce noise absorbed by the metal porous filling material 69 be clipped between monolithic porous 68; In the middle part of array jetting cooling module, 65 pairs of air carry out rectification, and air flows when flowing through honeycomb 70 steadily and flow direction is consistent; The nozzle array of array jetting cooling module bottom 66 is replaceable;
Concrete, array jetting cooling module top 64 is for pressurized air diffusion, pressurized air through flow distributor 67 be uniformly distributed on module xsect and in flaring passage diffusion, its flow process produce noise absorbed by the metal porous filling material 69 be clipped between monolithic porous 68; In the middle part of array jetting cooling module, rectification is carried out to air, air flow when flowing through honeycomb 70 can more steadily and flow direction consistance improve; 66-array jetting cooling module bottom is nozzle array, and nozzle 72 is formed by Drilling operation on nozzle plate 71; Module material is 304 stainless steels, relies on bolt to connect between three parts; Array jetting cooling module bottom 66 can be changed according to the requirement of different tests operating mode to nozzle array; The structure of 4 channel array fluidics modules is identical with single channel module, difference is that 4 entrances and flaring passage are arranged at the top of 4 channel modules, middle part and bottom are divided into 4 uniform square ducts, and top and middle part weld together, and arrange rubber blanket and seal 4 passages between middle part and bottom.
Described water/liquid nitrogen system B comprises supercharging liquid nitrogen container 9 and supercharging water tank 11, and described supercharging liquid nitrogen container 9 enters water/liquid nitrogen/air delivery pipe through cryogenic flow gauge 51 and stream selective cut-off valve;
The upper end of supercharging water tank 11 be provided with filler and be connected with from supercharging liquid nitrogen container 9 add gas port, lower end is provided with water delivering orifice, and water delivering orifice is connected with water/liquid nitrogen/air delivery pipe through filter 12, flowmeter branch road, stream selective cut-off valve;
The pressurized air of compressed air system A enters into water/liquid nitrogen/air delivery pipe by air compressor by stream selective cut-off valve;
Water/liquid nitrogen/air delivery pipe is provided with formation switch, is connected with the nozzle as cooling device through water/liquid nitrogen/air opening and closing solenoid valve.
Described enters water/liquid nitrogen/air delivery pipe from the liquid nitrogen of supercharging liquid nitrogen container 9 through cryogenic flow gauge 51 and stream selective cut-off valve,
Water in supercharging water tank 11 is under the pressure effect of nitrogen cylinder 10, enter after different flowmeter branch roads through filter 12 and send into water/liquid nitrogen/air delivery pipe, supercharging water tank 11 export pipeline is also provided with variable valve 50, regulates discharge when water jet cooling and water spray cooling;
Open the stream selective cut-off valve on different pipelines, make a kind of working medium in water/liquid nitrogen/air enter water/liquid nitrogen/air delivery pipe; Water/liquid nitrogen/air opening and closing solenoid valve is triggered when testpieces arrives below nozzle 24, and water/liquid nitrogen/air to be discharged by nozzle 24 as heat eliminating medium and starts cooling fast; Described nozzle 24 is straight tube-like nozzle or atomizer, produces jet or spraying.
Concrete, liquid nitrogen can be driven to enter stream from supercharging liquid nitrogen container 9, supercharging water tank 11 relies on the pressure-driven water of nitrogen cylinder 10 to enter stream, in addition, pressurized air from compressed air system A also enters this system, solenoid valve and follow-up stream is shared with water and liquid nitrogen, the switching of different working medium is realized by the opening and closing of stream selective cut-off valve 40,41,42,43,44: as opened stream selective cut-off valve 41 during liquid nitrogen injection pull-down test, opens stream selective cut-off valve 42,43,44 respectively when water jet falls or temperature of spraying tests according to discharge; The stream of water is equipped with the normal operation that filtrator 12 prevents impurity effect valve opening and closing and flowmeter, flow control valve 50 can carry out minute adjustment to discharge, because water spray cooling and water jet different operating mode down-off of lowering the temperature change greatly, the flowmeter 52,53,54 of different range is set; Water/liquid nitrogen/air opening and closing solenoid valve is connected to hand switch, can open temperature-fall period by quick manual when testpieces moves to below nozzle.
Nozzle 24 is atomizer when water spray cools, and is straight pipe type nozzle when air, water and liquid nitrogen injection are lowered the temperature; Water-cooling channel is not established in testpieces pedestal and infrared radiation heater inside, only filling fire resisting material, and the power of infrared radiation heater is realized by autotransformer 60 manual adjustments heating voltage.
Described testpieces pedestal 17 is water-cooled base, and water-cooled base is installed water-cooled base in orbit by slide block and moved between infrared radiation heater 20 and cooling device;
See Fig. 3, described infrared radiation heater 20 comprises the housing and the reflecting surface that are spliced to form well heater by water-cooling channel 75, water-cooling channel 75 two ends arrange cooling water outlet and inlet respectively, infrared radiation fluorescent tube 77 is arranged on infrared radiation heater 20 by fluorescent tube fixing metal sheet 76, and is connected with the bus-bar 73 of power supply; Infrared radiation heater 20 is also connected with the SCR Intelligent power regulating eqiupment 59 of controller power or autocoupling type pressure regulator;
Water tank 16 is connected with the cooling water outlet and inlet of infrared radiation heater 20, the cooling water outlet and inlet of water-cooled base respectively by the pipeline being provided with cooling sea water regulating valve, and regulates the discharge entered wherein; Between the cooling water outlet and inlet of infrared radiation heater 20, be also provided with cooled water distributor 18 at cooling sea water regulating valve, cooled water distributor 18 is by water yield uniform distribution between the water-cooling channel 75 of infrared radiation heater 20; Also be provided with float and float switch watch-dog in water tank 16, float switch signal is sent into Data Acquisition and Conversion System (DACS) E by float switch watch-dog, reports to the police respectively when low level and a high position.
Concrete, bus-bar is copper, it can be lamp tube power supply, whole well heater is fixed on aluminum hanger, the water-cooling channel 75 of rectangle is spliced to form housing and the reflecting surface of well heater, passage two ends arrange cooling water outlet and inlet respectively, and infrared radiation fluorescent tube 77 is installed on the heaters by fluorescent tube fixing metal sheet 76.SCR Intelligent power regulating eqiupment 59 controls the power of infrared radiation heater 20, testpieces is placed on testpieces pedestal 17, be heated to moving to below array jetting cooling module after fixed temperature in orbit through infrared radiation heater 20, travel switch is closed simultaneously connects solenoid valve, starts temperature-fall period; Cooling sea water regulating valve 57,58 regulates the discharge entering testpieces pedestal 17 and infrared radiation heater in process of the test, cooled water distributor 18 is by water yield uniform distribution between 8 passages of infrared radiation heater 20, to reduce to cause temperature different because each water-cooling channel water yield is different, prevent heater texturing; Water level in water tank 16 is monitored by its inner float switch installed, and float switch signal sends into Data Acquisition and Conversion System (DACS) E, realizes low level and the warning of high-order bright light.
See Fig. 4,5, described data acquistion and control system E comprises data collecting instrument, switch board, control module and computing machine, wherein control module adopts PLC and touch-screen to form, PLC can Real-time Collection testpieces surface temperature sensor temperature data and control the aperture of the electric control valve on temperature-reducing medium pipeline, and then the flow controlling temperature-reducing medium is to regulate rate of temperature fall;
Touch-screen is as controling parameters inputting interface and can show in real time, preserve temperature data from PLC, test specimen surface temperature situation of change in the controlled subregion temperature-fall period of display in real time;
Temperature, pressure and data on flows in data collecting instrument acquisition test process, and can logarithm according to the show and store;
Switch board is provided with multi-way switch and display lamp, can power for each instrument, PLC and touch-screen, the cooling water outlet temperature display of simultaneously piston type air compressor start and stop, the display of chilled water water level, testpieces pedestal and infrared radiation heater is all integrated in this switch board.
Concrete, temperature, pressure and data on flows in data collecting instrument acquisition test process, and can undertaken showing and storing data by display interface; Switch board is provided with multi-way switch and display lamp, can power for each instrument, PLC and touch-screen, in addition, the cooling water outlet temperature display of piston type air compressor 1 start and stop, the display of chilled water water level, testpieces pedestal 17 and infrared radiation heater 20 is all integrated in this switch board; PLC controls the aperture of electric control valve 36,37,38,39 in temperature-fall period in real time according to given control law as controller, can realize same testpieces surface zones of different and complete test according to different temperature lowering curves; The control program of PLC can be uploaded and amendment, and its controling parameters can adjust in touch-screen, and in addition, touch-screen also can be monitored real time temperature curve and show, and realize storage and the derivative of data, the touch screen interface of establishment as shown in Figure 4 and Figure 5.Passage bridge button 78 can realize the switching at different control channel interface, export data button 79 can switch to data summarization as shown in Figure 5 and derive interface, data window 80 shows real time temperature data, data window 81 shows given temperature data, all can show in real time at chart area 82 to fixed temperature and real time temperature curve, controling parameters inputs from parameter adjustment window 83, shift knob 84 can the start and stop of control PLC, Fig. 5 data summarization is free and temperature data with the institute of deriving in interface display control procedure, and can realize statistical conversion.
Above-mentioned can the concrete test procedure of aircraft ground thermal modeling test device when testing of fast cooling as follows:
1) large scale testpieces single channel array jetting cooling simulation test step: place testpieces, at testpieces surface-welding (metalwork) or stickup (to nonmetal parts) thermopair, start Data Acquisition and Conversion System (DACS) (E), open and start piston type air compressor 1 to gas-holder inflation, opening/closing or regulate each valve in compressed air system A; Open the cooling sea water regulating valve 57,58 in the first testpieces heating-pull-down test platform C, treadmill test part to be placed on testpieces pedestal and to move to below infrared radiation heater, regulates SCR Intelligent power regulating eqiupment 59 to open heating process; Testpieces is heated to after predetermined temperature below nigration part pedestal to array jetting cooling module, and trigger travel switch 62, air cooling opening and closing solenoid valve is opened and started simulation test procedure of lowering the temperature.
2) large scale testpieces hyperchannel controlled subregion cooling simulation test step: set correlation parameter according to test duration, each channel targets temperature lowering curve in Data Acquisition and Conversion System (DACS) E, closure plate installed by control flange, change multichannel array fluidics module, all the other test procedures are with single channel array jetting cooling simulation test.
3) small size testpieces water spray, liquid nitrogen injection, one-jet air-spray cool simulation test: be respectively from supercharging liquid nitrogen container 9 supercharging according to selected working medium, be supercharging water tank 11 moisturizing pressurization or start piston type air compressor 1, open corresponding stream valve, the aperture of adjust flux variable valve 50; Start Data Acquisition and Conversion System (DACS) E, be placed in by testpieces on testpieces pedestal, be heated to move to below nozzle after predetermined temperature through infrared radiation heater, trigger travel switch 63, water/liquid nitrogen/air solenoid valve is opened and is started simulation test procedure of lowering the temperature.
Be illustrated in figure 6 type testing curve of the present invention (400mm × 400mm × 8mm large-scale titanium alloy testpieces, pressure of storage tank 0.8MPa, nozzle quantity 16 × 16, nozzle height 5cm, 9 measuring points are in the distribution of testpieces surface uniform), wherein horizontal ordinate is the time, and ordinate is temperature, a figure left side is temperature ramps, and the figure right side is fast cooling section; The demand for heat that can meet testpieces in temperature-rise period can being seen, the cooling demand of testpieces can be met by fast cooling when lowering the temperature.
The embodiment more than provided realizes the present invention's preferably example, the invention is not restricted to above-described embodiment.Any nonessential interpolation that those skilled in the art makes according to the technical characteristic of technical solution of the present invention, replacement, all belong to protection scope of the present invention.
Claims (10)
1. one kind can the aircraft ground thermal modeling test device of fast cooling, it is characterized in that, this device comprises compressed air system (A), water/liquid nitrogen supply system (B), the first testpieces heating-pull-down test platform (C), the second testpieces heating-pull-down test platform (D) and Data Acquisition and Conversion System (DACS) (E);
Described compressed air system (A) provides pressurized air as temperature-reducing medium to the first testpieces heating-pull-down test platform (C), the second testpieces heating-pull-down test platform (D), the valve that setting data data acquisition and controlling system (E) is controlled on the pipeline that it provides temperature-reducing medium;
Described water/liquid nitrogen supply system (B) provides water/liquid nitrogen as temperature-reducing medium to the second testpieces heating-pull-down test platform (D), the valve that setting data data acquisition and controlling system (E) is controlled on the pipeline that it provides temperature-reducing medium;
The first described testpieces heating-pull-down test platform (C), the second testpieces heating-pull-down test platform (D) are respectively equipped with the track that infrared radiation heater (27), the cooling device receiving temperature-reducing medium and heating-cooling position are changed, track is provided with testpieces pedestal; Testpieces is placed on testpieces pedestal and moves can change at fire end and colling end with it, the travel switch starting temperature-reducing medium release is also provided with in the outside in cooling hot junction, trigger travel switch when pedestal moves to colling end, travel switch is opened, and temperature-reducing medium enters into cooling device.
2. as claimed in claim 1 can the aircraft ground thermal modeling test device of fast cooling, it is characterized in that, described compressed air system (A) comprises piston type air compressor (1), its air out is connected with oil-water separator (2), be connected with gas-holder by filtrator, the outlet of gas-holder is connected with the first diffuser (8), pressurized air after preliminary diffusion enters air passage through flowmeter (55) and air cooling opening and closing solenoid valve (35), air passage heats with the first testpieces-pull-down test system (C) in be connected as the array jetting cooling module (15) of cooling device, pressurized air produces array jetting in array jetting cooling module (15) after further diffusion and rectification.
3. as claimed in claim 2 can the aircraft ground thermal modeling test device of fast cooling, it is characterized in that, described oil-water separator (2), by being connected with the second gas-holder (7) with the first gas-holder (6) respectively after three grades of accurate filters, the pipeline between accurate filter and gas-holder is also provided with the first stop valve (31); Oil-water separator (2) is also connected with gas-holder by the pipeline being provided with the second stop valve (32); Control the first stop valve (31), pressurized air directly can be sent into gas-holder by the opening and closing of the second stop valve (32) under plugged filter operating mode;
The upstream of described the first gas-holder (6), downstream pipe are also respectively equipped with the 3rd stop valve (33), the 4th stop valve (34), the switching of single/two gas-holder can be realized.
4. as claimed in claim 2 can the aircraft ground thermal modeling test device of fast cooling, it is characterized in that, described air cooling opening and closing solenoid valve (35) is the travel switch that can trigger, and is discharged into by the pressurized air in gas-holder in array jetting cooling module (15) after it is triggered; Described air passage comprises 4 passage controlled subregion cooling metal hose and for single channel cooling metal hose, 4 passage controlled subregion cooling flexible pipe is also respectively equipped with electric control valve, this electric control valve is by the control of data acquistion and control system (E), air mass flow is regulated, and then controls temperature-fall period; The flow signal of collection is sent to Data Acquisition and Conversion System (DACS) (E) by described flowmeter (55).
5. as described in claim 2 or 4 can the aircraft ground thermal modeling test device of fast cooling, it is characterized in that, described array jetting cooling module (15) comprises (65) and array jetting cooling module bottom (66) in the middle part of array jetting cooling module top (64), array jetting cooling module;
Described array jetting cooling module top (64) is diffuser, comprise oral area and flaring passage, flow distributor (67) is provided with at oral area, also be provided with monolithic porous (68) in flaring passage, between monolithic porous (68), be folded with porous packing (69); Described oral area number and single channel air passage or 4 channel air branch roads match;
In the middle part of described array jetting cooling module, (65) are rectification section, in the middle part of array jetting cooling module (65) passage in be provided with honeycomb (70);
The nozzle array that described array jetting cooling module bottom (66) is release medium, nozzle (72) is arranged in array in nozzle plate (71).
6. as claimed in claim 5 can the aircraft ground thermal modeling test device of fast cooling, it is characterized in that, after pressurized air enters array jetting cooling module (15), pressurized air through flow distributor (67) be uniformly distributed on module xsect and in flaring passage diffusion, the noise that its flow process produces is absorbed by the metal porous filling material (69) that is clipped between monolithic porous (68); In the middle part of array jetting cooling module, (65) carry out rectification to air; The nozzle array of array jetting cooling module bottom (66) is replaceable.
7. as claimed in claim 1 can the aircraft ground thermal modeling test device of fast cooling, it is characterized in that, described water/liquid nitrogen system (B) comprises supercharging liquid nitrogen container (9) and supercharging water tank (11), and described supercharging liquid nitrogen container (9) enters water/liquid nitrogen/air delivery pipe through cryogenic flow gauge (51) and stream selective cut-off valve;
The upper end of supercharging water tank (11) be provided with filler and be connected with from supercharging liquid nitrogen container (9) add gas port, lower end is provided with water delivering orifice, and water delivering orifice is connected with water/liquid nitrogen/air delivery pipe through filter (12), flowmeter branch road, stream selective cut-off valve;
The pressurized air of compressed air system (A) enters into water/liquid nitrogen/air delivery pipe by air compressor by stream selective cut-off valve;
Water/liquid nitrogen/air delivery pipe is provided with travel switch, is connected with the nozzle as cooling device through water/liquid nitrogen/air opening and closing solenoid valve.
8. as claimed in claim 7 can the aircraft ground thermal modeling test device of fast cooling, it is characterized in that, described enters water/liquid nitrogen/air delivery pipe from the liquid nitrogen of supercharging liquid nitrogen container (9) through cryogenic flow gauge (51) and stream selective cut-off valve
Water in supercharging water tank (11) is under the pressure effect of nitrogen cylinder (10), enter after different flowmeter branch roads through filter (12) and send into water/liquid nitrogen/air delivery pipe, supercharging water tank (11) export pipeline is also provided with variable valve (50), regulates discharge when water jet cooling and water spray cooling;
Open the stream selective cut-off valve on different pipelines, make a kind of working medium in water/liquid nitrogen/air enter water/liquid nitrogen/air delivery pipe; Water/liquid nitrogen/air opening and closing solenoid valve is triggered when testpieces arrives nozzle (24) below, and water/liquid nitrogen/air starts cooling as heat eliminating medium fast by nozzle (24) release; Described nozzle (24) is straight tube-like nozzle or atomizer, produces jet or spraying.
9. as claimed in claim 1 can the aircraft ground thermal modeling test device of fast cooling, it is characterized in that, described testpieces pedestal (17) is water-cooled base, and water-cooled base is installed water-cooled base in orbit by slide block and moved between infrared radiation heater (20) and cooling device;
Described infrared radiation heater (20) comprises the housing and the reflecting surface that are spliced to form well heater by water-cooling channel (75), water-cooling channel (75) two ends arrange cooling water outlet and inlet respectively, infrared radiation fluorescent tube (77) is arranged on infrared radiation heater (20) by fluorescent tube fixing metal sheet (76), and is connected with the bus-bar (73) of power supply; Infrared radiation heater (20) is also connected with the SCR Intelligent power regulating eqiupment (59) of controller power;
Water tank (16) is connected respectively by the cooling water outlet and inlet of pipeline with infrared radiation heater (20) being provided with cooling sea water regulating valve, the cooling water outlet and inlet of testpieces pedestal, and regulates the discharge entered wherein; Between cooling sea water regulating valve and the cooling water outlet and inlet of infrared radiation heater (20), be also provided with cooled water distributor (18), cooled water distributor (18) is by water yield uniform distribution between the water-cooling channel (75) of infrared radiation heater (20); Also be provided with float and float switch watch-dog in water tank (16), float switch signal is sent into Data Acquisition and Conversion System (DACS) (E) by float switch watch-dog, reports to the police respectively when low level and a high position.
10. as claimed in claim 1 can the aircraft ground thermal modeling test device of fast cooling, it is characterized in that, described data acquistion and control system (E) comprises data collecting instrument, switch board, control module and computing machine, wherein control module adopts PLC and touch-screen to form, wherein PLC can Real-time Collection testpieces surface temperature sensor temperature data and control the aperture of the electric control valve on temperature-reducing medium pipeline, and then the flow controlling temperature-reducing medium is to regulate rate of temperature fall;
Touch-screen is as controling parameters inputting interface and can show in real time, preserve temperature data from PLC, test specimen surface temperature situation of change in the controlled subregion temperature-fall period of display in real time;
Temperature, pressure and data on flows in data collecting instrument acquisition test process, and can show data and store;
Switch board is provided with multi-way switch and display lamp, can power for each instrument, PLC and touch-screen, the cooling water outlet temperature of simultaneously piston type air compressor (1) start and stop, chilled water water-level alarm, testpieces pedestal (17) and infrared radiation heater (20) shows and is all integrated in this switch board.
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| CN106769133A (en) * | 2016-12-02 | 2017-05-31 | 哈尔滨工业大学 | A kind of the atomized water spray pilot system and its application method of test flight device hot junction portion structure part thermal shock resistance |
| CN107639461A (en) * | 2017-09-25 | 2018-01-30 | 东莞安默琳机械制造技术有限公司 | Automatic liquid nitrogen combined mist cooling system |
| CN107855825A (en) * | 2017-09-25 | 2018-03-30 | 东莞安默琳机械制造技术有限公司 | Automatic liquid nitrogen combined mist cooling means |
| CN110136772A (en) * | 2019-04-08 | 2019-08-16 | 北京强度环境研究所 | A kind of low pressure heat test large scale structure inside active cooling device |
| CN110160894A (en) * | 2018-04-16 | 2019-08-23 | 北京机电工程研究所 | Scragging system |
| CN111089744A (en) * | 2019-10-25 | 2020-05-01 | 西安航天动力试验技术研究所 | Movable thermal environment device for ground heat insulation prevention test of aerospace craft |
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| CN112817345A (en) * | 2020-12-28 | 2021-05-18 | 中国航空工业集团公司沈阳飞机设计研究所 | Skin temperature control method and system |
| CN113933235A (en) * | 2021-12-16 | 2022-01-14 | 中国飞机强度研究所 | Method for measuring temperature of aircraft skin in solar radiation simulation test |
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| CN106769133A (en) * | 2016-12-02 | 2017-05-31 | 哈尔滨工业大学 | A kind of the atomized water spray pilot system and its application method of test flight device hot junction portion structure part thermal shock resistance |
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| CN110136772A (en) * | 2019-04-08 | 2019-08-16 | 北京强度环境研究所 | A kind of low pressure heat test large scale structure inside active cooling device |
| CN111829680A (en) * | 2019-04-23 | 2020-10-27 | 北京振兴计量测试研究所 | Surface pyrometry method |
| CN111089744A (en) * | 2019-10-25 | 2020-05-01 | 西安航天动力试验技术研究所 | Movable thermal environment device for ground heat insulation prevention test of aerospace craft |
| CN111089744B (en) * | 2019-10-25 | 2022-03-11 | 西安航天动力试验技术研究所 | Movable thermal environment device for ground heat insulation prevention test of aerospace craft |
| CN112817345A (en) * | 2020-12-28 | 2021-05-18 | 中国航空工业集团公司沈阳飞机设计研究所 | Skin temperature control method and system |
| CN113933235A (en) * | 2021-12-16 | 2022-01-14 | 中国飞机强度研究所 | Method for measuring temperature of aircraft skin in solar radiation simulation test |
| CN113933235B (en) * | 2021-12-16 | 2022-02-25 | 中国飞机强度研究所 | Method for measuring temperature of aircraft skin in solar radiation simulation test |
| CN114509232A (en) * | 2022-01-20 | 2022-05-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Modular hole wall device for wind tunnel test |
| CN114509232B (en) * | 2022-01-20 | 2023-08-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Hole wall device for modularized wind tunnel test |
| CN114815931A (en) * | 2022-06-23 | 2022-07-29 | 中国飞机强度研究所 | Method for controlling thermal test temperature of aircraft component in extremely high temperature environment |
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