CN202002747U - High-temperature measuring device for surface of nonmetal heat-proof material plane test piece of high-supersonic aircrafts - Google Patents
High-temperature measuring device for surface of nonmetal heat-proof material plane test piece of high-supersonic aircrafts Download PDFInfo
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- CN202002747U CN202002747U CN2011200691891U CN201120069189U CN202002747U CN 202002747 U CN202002747 U CN 202002747U CN 2011200691891 U CN2011200691891 U CN 2011200691891U CN 201120069189 U CN201120069189 U CN 201120069189U CN 202002747 U CN202002747 U CN 202002747U
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Abstract
The utility model relates to a high-temperature measuring device for the surface of a nonmetal heat-proof material plane test piece of high-supersonic aircrafts, which comprises a high-temperature ceramic frame, a temperature measuring thermoelectric couple, a nonmetal heat-proof material flat test piece, a silicon molybdenum infrared radiation heating pipe and a computer, wherein a circular hole is formed in the high-temperature ceramic frame; the temperature measuring thermoelectric couple sleeved with a ceramic insulation casing pipe is inserted into the circular hole in the high-temperature ceramic frame; the front part of the temperature measuring thermoelectric couple is bent to form an upward arch; the nonmetal heat-proof material flat test piece presses the high-temperature ceramic frame by dead weight to press the temperature sensing part which is welded to form a ball shape on the forefront of the temperature measuring thermoelectric couple; and the nonmetal heat-proof material plane test piece can contact the temperature sensing part at the front end of the thermoelectric couple tightly at the high-temperature environment of between 1,000 and 1,400 DEG C by adopting the double technical measures of applying predeformation and increasing prestress under the mutual effect between the downward pressure of the nonmetal heat-proof material flat test piece and the upward elastic force of the arch on the front part of the temperature measuring thermoelectric couple, so that high-temperature test results of the surface of the nonmetal heat-proof material plane test piece of the high-supersonic aircrafts such as guided missiles, space shuttles and the like are accurate and reliable.
Description
Technical field
The utility model relates to testpieces surface, the nonmetal heat insulation material of hypersonic aircraft plane high temperature measurement device, in the hot test environment of hypersonic aircrafts such as simulated missile, space shuttle, the non-metal heat-insulating material surface is measured and record in real time up to 1000 ℃-1400 ℃ high temperature dynamic change with nonmetal plane light heat-insulating material.
Background technology
Along with the development of world's space flight and aviation technology, the design rate of long-range maneuvering-vehicle is increasing substantially, the development work that developed countries such as present the United States, Russia, European Union just competitively carry out hypersonic aircraft.China is also making great efforts to carry out the research of the long-range maneuvering-vehicle of hypersonic speed of new generation, the research of pointing out the long-range maneuvering-vehicle of hypersonic speed in the project of national nature science fund project guide " relates to national security and peaceful use space; being that one of focus of space technology is competitively fought in the world at present, is the embodiment of overall national strength ".When high speed aircraft such as guided missile flew with high Mach number, " thermal boundary " problem that is caused by pneumatic heating was very serious.When flight Mach number near 4 the time, guided missile front end stagnation temperature can reach 700 ℃, with the hypersonic aircraft of 6 Mach numbers flights, the stagnation temperature in its nose of wing and antenna house tapering will be above 1200 ℃.Therefore the design of the research of high-temperature structural material and anti-heat insulation structural is the gordian technique and the core technology of the reliability design of hypersonic aircraft general safety.
When temperature will be above 1000 ℃, even if adopt refractory metal materials such as nickel base superalloy or titanium alloy, also can occur being out of shape, soften, the phenomenon of rigidity decline, have a strong impact on the aerodynamic configuration and the safe flight of high-speed aircraft.The interior temperature of instrument room that sophisticated electronics is installed does not in addition generally allow above 80 ℃, necessary design and installation thermal protection struc ture or laying heat-barrier material, to reduce the conduction of velocity of the guided missile surface inside portion of heat, therefore, Xin Yidai hypersonic vehicle generally all adopts nonmetal light materials such as carbon fibre composite, porous foam type refractory ceramics watt, resurrection glass fibre to manufacture the shell of aircraft or as anti-heat-barrier material.
When carrying out the security and Reliability Design of hypersonic aircrafts such as guided missile, need in advance the surface temperature of employed nonmetal light material to be measured, to check its heat resistance, ablation property and heat-proof quality.Because nonmetallic materials can not can be with temperature thermocouple silk direct spot welding on material surface, so generally adopt the method surface measurements temperature of bonding or crimping as metal material.If adopt bonding way, since the temperature probe of metal material and nonmetallic materials difference of thermal expansion coefficients very big, be higher than under 1000 ℃ the thermal environment, metal temperature probe and the non-metal material surface segregation phenomenon of coming unstuck often occurring, causing the inaccurate situation of surface temperature measurement.
If can guarantee that metal temperature probe and non-metal material surface are in intimate-association state all the time under hot environment, can realize the temperature survey of non-metal material surface under the hot environment on principle.But, make the temperature thermocouple front end in process of the test, remain tight contact to non-metal material surface, must make between near part of thermopair front end and the non-metal material surface big relative displacement can not be arranged, otherwise inevitable related thermopair front end temperature-sensitive portion's warpage and dislocation, particularly it will can also keep steady state (SS) under greater than 1000 ℃ hot environment, and this is to be related to crimping thermometric mode key of success and technological difficulties.
In addition, because under greater than 1000 ℃ hot environment, the testpieces surface can thermal ablation occur and heat waste is ruined, generally can not repeat the multiple high temp test to same testpieces, and the solar heat protection test specimen of high-speed aircraft is all very expensive, just surpass 50,000 U.S. dollars as U.S.'s Glenn than the solar heat protection watt monolithic cost of inferior space shuttle, so the test data that each test obtains is all very valuable.Therefore, must exploitation can write down in the elevated temperature heat process of the test situation of change of heat insulation material surface temperature at the nonmetal heat insulation material of the high-speed aircraft of reliably working under hot environment plane test specimen surface high temperature measurement device.This work has very important practical significance for the thermal protection and the security and Reliability Design of hypersonic aircrafts such as guided missile, space shuttle.
The utility model content
Technology of the present utility model is dealt with problems and is: overcome the deficiencies in the prior art, testpieces surface, the nonmetal heat insulation material of a kind of hypersonic aircraft plane high temperature measurement device is provided, this device can be accurately and is measured reliably and write down in the hypersonic aircraft heat test process, the dynamic high temperature of nonmetal heat insulation material plane testpieces surface temperature field up to 1000 ℃-1400 ℃ changes, and it is simple in structure, easy to use, checking with safety and Protection for the hot strength of hypersonic aircrafts such as guided missile, space shuttle provides reliable test basis.
Technical solution of the present utility model is: the nonmetal heat insulation material of hypersonic aircraft plane testpieces surface high temperature measurement device comprises: refractory ceramics framework, temperature thermocouple, nonmetal heat insulation material treadmill test part, adiabatic bracing frame, heating source and computing machine; The refractory ceramics framework lies on the adiabatic bracing frame, one circular hole is arranged on the refractory ceramics framework, temperature thermocouple is inserted in the circular hole, and the front portion that makes temperature thermocouple curves upwards arc, nonmetal heat insulation material treadmill test part is pressed on the refractory ceramics framework, make the refractory ceramics framework push down the thermopair front end temperature-sensitive portion that is welded into ball-point pen type of temperature thermocouple forefront, interaction between the elastic force that makes progress by downward gravity of nonmetal heat insulation material treadmill test part and temperature thermocouple front arcuate position, make that nonmetal heat insulation material treadmill test part can remain tight the contact with thermopair front end temperature-sensitive portion under 1000 ℃-1400 ℃ hot environment under hot environment, guarantee the accuracy and the reliability of temperature-measuring results; Can produce the below that is placed on nonmetal heat insulation material treadmill test part up to the silicon chrome vermillion external radiation heating source of 1600 ℃ of high temperature, heating power carries out radiation heating to the lower surface of nonmetal heat insulation material treadmill test part; The temperature thermocouple that is crimped on nonmetal heat insulation material treadmill test part lower surface is sent to computing machine with output signal by lead, and computer recording also calculates the high temperature delta data on the nonmetal heat insulation material treadmill test of guided missile, space shuttle and so on hypersonic aircraft part surface.
Refractory ceramics framework and temperature thermocouple do not adopt traditional adhering fixed mode, but the interaction between the elastic force that makes progress by downward pressure of nonmetal heat insulation material treadmill test part and temperature thermocouple front arcuate position makes that nonmetal heat insulation material treadmill test part remains tight the contact with thermopair front end temperature-sensitive portion under the hot environment.
Bad phenomenon can not appear being in contact with one another in order to ensure thermopair front end temperature-sensitive portion in the elevated temperature heat process of the test and nonmetal heat insulation material treadmill test part, before nonmetal heat insulation material treadmill test part is installed, it is bigger that the first arc displacement that the front portion of temperature thermocouple is made progress is done, make thermopair front end temperature-sensitive portion be higher than plane 5mm-6mm on the refractory ceramics framework, form an initial predeformation that makes progress, when nonmetal heat insulation material treadmill test part is pressed on the refractory ceramics framework, the displacement of 5mm-6mm will appear descending mutually in thermopair front end temperature-sensitive portion, after this 5mm-6mm distortion of thermopair front portion is forced to push back, can produce the bigger elastic force that makes progress, make the thermopair front end temperature-sensitive portion can to keep tight the contact, adopt this predeformation reinforcing method to guarantee the reliability and stability of thermometric work under 1000 ℃ of-1400 ℃ of hot environments with nonmetal heat insulation material treadmill test part surface.
Principle of work of the present utility model is: make a refractory ceramics framed structure that equates with plane test specimen boundary dimensions, this ceramic frame adopts the alumina content of 1800 ℃ of abilities to fire up to 99% corundum high-temperature ceramic materials and forms, therefore, this ceramic frame can be guaranteed steady operation under 1000 ℃ to 1400 ℃ hot environments.One circular hole is arranged in the refractory ceramics framed structure, temperature thermocouple is installed in the mesopore of refractory ceramics framed structure, the anterior upwards bow shape of temperature thermocouple.When carrying out test specimen surface, the nonmetal heat insulation material of hypersonic aircraft plane high temperature measurement, nonmetal heat insulation material plane test specimen is pressed on the refractory ceramics framed structure, produce between the bowed shape that downward pressure and thermopair front portion upwards curve by the deadweight of plane test specimen and to interact, form the tight contact between test specimen surface, nonmetal heat insulation material plane and the thermocouple temperature sensitive portion.Make thermopair front end thermometric portion at high temperature also can remain contact force upwards.When heating for test specimen surface, nonmetal heat insulation material plane according to heat flow curve or temperature curve, because the rigidity that bowed shape that warm galvanic couple front end makes progress and thermocouple wire itself have, and corundum refractory ceramics framed structure has the not yielding advantage that gets under 1800 ℃ of high temperature, even when temperature up to 1000 ℃ during to 1400 ℃, also can closely contact between test specimen surface and the thermocouple temperature sensitive portion, thermopair front end temperature-sensitive portion, perception test specimen surface temperature change is passed through computer recording rapidly, and calculate the dynamic temperature change curve on nonmetal heat insulation material test specimen surface in the heat test process.
The utility model beneficial effect compared with prior art is: because utility model has been taked temperature thermocouple is installed in the mesopore of refractory ceramics framed structure, the anterior upwards bow shape of temperature thermocouple, deadweight by the plane test specimen produces between the upwarding pressure that bowed shape that downward pressure and thermopair front portion upwards curve produces and interacts, and has guaranteed that test specimen surface, nonmetal heat insulation material plane contacts with the tight of thermocouple temperature sensitive portion.Because the temperature thermocouple support zone do not use bonding agent, avoided traditional bonding support fixation method under greater than 1000 ℃ of hot environments, the test failure that comes unglued and cause very easily appears in the temperature thermocouple support zone.In addition, because thermopair front end temperature-sensitive portion does not have adhesive linkage yet, it between test specimen surface and the thermocouple temperature sensitive portion depended on pressure rather than by bonding contact, under 1000 ℃-1400 ℃ hot environment, even because high temperature thermal deformation produces a small amount of transversal displacement, because bigger interactional prestress is arranged, can guarantee between test specimen surface and the thermocouple temperature sensitive portion it is to be in tight state of contact all the time between the two.Make measurement result more accurately, reliably.Above utility model has solved under 1000 ℃-1400 ℃ excessive temperature environment, is related to crimping thermometric mode key of success technological difficulties.In addition, need be the time, owing to there is not adhesive linkage to a large amount of testpieces thermometric of different effect of heat insulation, different-thickness, do not need to clear up adhesive spots, only need change new nonmetal heat insulation material plane test specimen, so the utility model also has simple and direct, the easy to use advantage of installation.
Description of drawings
Fig. 1 is a structure side view of the present utility model;
Fig. 2 is the perspective view of refractory ceramics framework of the present utility model;
Certain guided missile carbon fibre composite plane testpieces under 1000 ℃ high temperature the testpieces surface temperature change curve map of Fig. 3 for using the utility model to record;
Certain guided missile carbon fibre composite plane testpieces under 1400 ℃ high temperature the testpieces surface temperature change curve map of Fig. 4 for using the utility model to record.
Embodiment
As depicted in figs. 1 and 2, the utility model is made up of refractory ceramics framework 1, temperature thermocouple 2, nonmetal heat insulation material treadmill test part 6, adiabatic bracing frame 7, heating source 8 (employing can form the silicon chrome vermillion external radiation heating tube of 1600 ℃ of hot environments), lead 9 and computing machine 10.Refractory ceramics framework 1 adopts the corundum high-temperature ceramic materials of the alumina content 99% of 1800 ℃ of abilities to fire, and temperature thermocouple 2 adopts the two platinum Rhodium thermopairs of measurement range up to 1800 ℃.Refractory ceramics framework 1 is placed on the adiabatic bracing frame 7, one circular hole 5 is arranged on the refractory ceramics framework 1, the temperature thermocouple 2 that is with ceramic insulation sleeve pipe 4 is inserted in the circular hole 5 of refractory ceramics framework 1, temperature thermocouple 2 front portions curve upwards arc, nonmetal heat insulation material treadmill test part 6 is pressed on the refractory ceramics framework 1, make it push down the thermopair front end temperature-sensitive portion 3 that temperature thermocouple 2 forefronts are welded into round bead shape, interaction between the elastic force that makes progress by downward gravity of nonmetal heat insulation material treadmill test part 6 and temperature thermocouple 2 front arcuate positions makes nonmetal heat insulation material treadmill test part 6 can remain tight the contact with thermopair front end temperature-sensitive portion 3.
The diameter of the circular hole 5 in the utility model is 5mm; The front portion of temperature thermocouple 2 is to up-bow, and makes thermopair front end temperature-sensitive portion 3 be higher than the last plane 5mm-6mm of refractory ceramics framework 1, forms the upwards initial predeformation of 5mm-6mm.When nonmetal heat insulation material treadmill test part 6 is pressed on the refractory ceramics framework 1, the thermopair front end temperature-sensitive portion 3 that is fixed on temperature thermocouple 2 forefronts on the refractory ceramics framework 1 is forced to push back 5mm-6mm downwards by nonmetal heat insulation material treadmill test part 6, be that thermopair front end temperature-sensitive portion 3 is forced to depress and get back to original initial position, because the rigidity that the metal thermoelectric thermo wires has, can produce the very large elastic force that makes progress when pressure is depressed, this apply prestressed technical method guaranteed between thermopair front end temperature-sensitive portion 3 and the nonmetal heat insulation material treadmill test part 6 contact more closely and reliable.
In the pneumatic heat test process of high temperature up to 1000 ℃-1400 ℃ of hypersonic aircrafts such as simulated missile, when heating source 8 carries out radiation heating for the surface of nonmetal heat insulation material treadmill test part 6 according to the heating-up temperature curve, with the tight temperature thermocouple front end temperature-sensitive portion 3 that contacts in nonmetal heat insulation material treadmill test part 6 surfaces, detect nonmetal heat insulation material treadmill test part 6 surface temperature change, and change temperature variation into electric signal, send into computing machine 10 through lead 9 and store and calculate, the dynamic changing curve that draws nonmetal heat insulation material treadmill test part 6 surface temperatures is shown in Fig. 3 (1000 ℃ of steady temperatures) and Fig. 4 (1400 ℃ of steady temperatures).
Can see that from Fig. 3 and Fig. 4 the surface temperature of the nonmetal heat insulation material treadmill test of hypersonic aircraft part 6 rises to 1000 ℃ and 1400 ℃ of high temperature respectively in 150 seconds, heating process finishes when remaining to for 600 seconds afterwards.Can also be seen that by Fig. 3 and Fig. 4 in the whole test overall process, design temperature curve and observing and controlling temperature curve repeatability are good, tracking error is very little, and the observing and controlling temperature curve is level and smooth, does not have jitter phenomenon.Proved the utility model under 1000 ℃ of-1400 ℃ of very high temperature environments, also can measure in real time and record the dynamic change of the nonmetal heat insulation material treadmill test of hypersonic aircraft part 6 surface temperatures accurately and effectively.
The content that is not described in detail in the utility model instructions belongs to this area professional and technical personnel's known prior art.
Claims (9)
1. the nonmetal heat insulation material of hypersonic aircraft plane testpieces surface high temperature measurement device is characterized in that comprising: refractory ceramics framework (1), temperature thermocouple (2), nonmetal heat insulation material treadmill test part (6), adiabatic bracing frame (7), heating source (8) and computing machine (10); Refractory ceramics framework (1) lies on the adiabatic bracing frame (7), one circular hole (5) is arranged on the refractory ceramics framework (1), temperature thermocouple (2) is inserted in the circular hole (5), and the front portion that makes temperature thermocouple (2) curves upwards arc, nonmetal heat insulation material treadmill test part (6) is pressed on the refractory ceramics framework (1), make refractory ceramics framework (1) push down the thermopair front end temperature-sensitive portion (3) that is welded into ball-point pen type of temperature thermocouple (2) forefront, interaction between the elastic force that makes progress by downward gravity of nonmetal heat insulation material treadmill test part (6) and temperature thermocouple (2) front arcuate position, make that nonmetal heat insulation material treadmill test part (6) can remain tight the contact with thermopair front end temperature-sensitive portion (3) under 1000 ℃-1400 ℃ hot environment under hot environment, guarantee the accuracy and the reliability of temperature-measuring results; Heating source (8) is placed on the below of nonmetal heat insulation material treadmill test part (6), and heating power carries out radiation heating to the lower surface of nonmetal heat insulation material treadmill test part (6); The output signal that is crimped on the temperature thermocouple (2) of nonmetal heat insulation material treadmill test part (6) lower surface is sent to computing machine (10) by lead (9), and computing machine (10) writes down and calculate the high temperature delta data on the nonmetal heat insulation material treadmill test of guided missile, space shuttle and so on hypersonic aircraft part (6) surface.
2. testpieces surface, the nonmetal heat insulation material of hypersonic aircraft according to claim 1 plane high temperature measurement device, it is characterized in that: the diameter of described circular hole (5) is 5mm.
3. testpieces surface, the nonmetal heat insulation material of hypersonic aircraft according to claim 1 plane high temperature measurement device, it is characterized in that: described nonmetal heat insulation material treadmill test part (6) remains tight the contact with thermopair front end temperature-sensitive portion (3).
4. testpieces surface, the nonmetal heat insulation material of hypersonic aircraft according to claim 1 plane high temperature measurement device, it is characterized in that: the front portion of described temperature thermocouple (2) is to up-bow, make thermopair front end temperature-sensitive portion (3) be higher than the last plane 5mm-6mm of refractory ceramics framework (1), form initial predeformation upwards.
5. testpieces surface, the nonmetal heat insulation material of hypersonic aircraft according to claim 1 plane high temperature measurement device, it is characterized in that: the thermopair front end temperature-sensitive portion (3) that is welded into ball-point pen type of described temperature thermocouple (2) forefront is forced to depress 5mm-6mm by refractory ceramics framework (1).
6. testpieces surface, the nonmetal heat insulation material of hypersonic aircraft according to claim 1 plane high temperature measurement device, it is characterized in that: described refractory ceramics framework (1) adopts the corundum high-temperature ceramic materials of the alumina content 99% of 1800 ℃ of abilities to fire.
7. testpieces surface, the nonmetal heat insulation material of hypersonic aircraft according to claim 1 plane high temperature measurement device is characterized in that: be with ceramic insulation sleeve pipe (4) on the described temperature thermocouple (2).
8. testpieces surface, the nonmetal heat insulation material of hypersonic aircraft according to claim 1 plane high temperature measurement device, it is characterized in that: described heating source (8) adopts the silicon chrome vermillion external radiation heating tube that can form 1600 ℃ of hot environments.
9. testpieces surface, the nonmetal heat insulation material of hypersonic aircraft according to claim 1 plane high temperature measurement device, it is characterized in that: described temperature thermocouple (2) adopts the two platinum Rhodium thermopairs of measurement range up to 1800 ℃.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011200691891U CN202002747U (en) | 2011-03-16 | 2011-03-16 | High-temperature measuring device for surface of nonmetal heat-proof material plane test piece of high-supersonic aircrafts |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011200691891U CN202002747U (en) | 2011-03-16 | 2011-03-16 | High-temperature measuring device for surface of nonmetal heat-proof material plane test piece of high-supersonic aircrafts |
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| CN102183312A (en) * | 2011-03-16 | 2011-09-14 | 北京航空航天大学 | Surface high-temperature measurement device for nonmetallic heat resistant material plane test piece of hypersonic speed aircraft |
| CN102564610A (en) * | 2011-12-28 | 2012-07-11 | 哈尔滨工业大学 | Energy method-based high-temperature radiation rate measuring device of semi-transparent material and revising method for deducting background radiation |
| CN102879423A (en) * | 2012-10-09 | 2013-01-16 | 北京航空航天大学 | Single-side high-temperature testing device of hypersonic aircraft material in 1800-degree aerobic environment |
| CN103234998A (en) * | 2013-04-25 | 2013-08-07 | 哈尔滨工业大学 | High heating flux solar full-spectrum radiation heating device |
| CN103630567A (en) * | 2013-12-23 | 2014-03-12 | 哈尔滨工业大学 | Anti-background-noise sample heating system for measuring emissivity of translucent material sample |
| CN104048991A (en) * | 2014-06-16 | 2014-09-17 | 中国飞机强度研究所 | Radiant heater heat flux density transfer method |
| CN104501984A (en) * | 2014-12-15 | 2015-04-08 | 贵州黎阳航空动力有限公司 | Thermocouple temperature measurement device and temperature measurement method for brazing |
| CN104925269A (en) * | 2015-05-08 | 2015-09-23 | 湖北航天技术研究院总体设计所 | Ultrahigh-speed aircraft cabin thermal environment testing device and method |
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| CN106066342A (en) * | 2016-05-25 | 2016-11-02 | 江西洪都航空工业集团有限责任公司 | A kind of thermal protection test method for aircraft test piece level sample |
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- 2011-03-16 CN CN2011200691891U patent/CN202002747U/en not_active Expired - Lifetime
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| CN102183312B (en) * | 2011-03-16 | 2013-01-02 | 北京航空航天大学 | Surface high-temperature measurement device for nonmetallic heat resistant material plane test piece of hypersonic speed aircraft |
| CN102564610A (en) * | 2011-12-28 | 2012-07-11 | 哈尔滨工业大学 | Energy method-based high-temperature radiation rate measuring device of semi-transparent material and revising method for deducting background radiation |
| CN102879423A (en) * | 2012-10-09 | 2013-01-16 | 北京航空航天大学 | Single-side high-temperature testing device of hypersonic aircraft material in 1800-degree aerobic environment |
| CN102879423B (en) * | 2012-10-09 | 2015-01-21 | 北京航空航天大学 | Single-side high-temperature testing device of hypersonic aircraft material in 1800-degree aerobic environment |
| CN103234998A (en) * | 2013-04-25 | 2013-08-07 | 哈尔滨工业大学 | High heating flux solar full-spectrum radiation heating device |
| CN103630567A (en) * | 2013-12-23 | 2014-03-12 | 哈尔滨工业大学 | Anti-background-noise sample heating system for measuring emissivity of translucent material sample |
| CN104048991A (en) * | 2014-06-16 | 2014-09-17 | 中国飞机强度研究所 | Radiant heater heat flux density transfer method |
| CN104501984B (en) * | 2014-12-15 | 2018-04-27 | 贵州黎阳航空动力有限公司 | A kind of soldering thermocouple temperature measuring apparatus and temp measuring method |
| CN104501984A (en) * | 2014-12-15 | 2015-04-08 | 贵州黎阳航空动力有限公司 | Thermocouple temperature measurement device and temperature measurement method for brazing |
| CN104925269A (en) * | 2015-05-08 | 2015-09-23 | 湖北航天技术研究院总体设计所 | Ultrahigh-speed aircraft cabin thermal environment testing device and method |
| CN104925269B (en) * | 2015-05-08 | 2016-09-21 | 湖北航天技术研究院总体设计所 | The assay device of a kind of high hypervelocity aircraft cabin section thermal environment and method |
| US11118849B2 (en) | 2015-11-30 | 2021-09-14 | The Boeing Company | Computer aided measuring system (CAMS) temperature reporters |
| CN107016151A (en) * | 2015-11-30 | 2017-08-04 | 波音公司 | Computer Assisted Measurement System temperature reporter |
| CN107016151B (en) * | 2015-11-30 | 2022-07-08 | 波音公司 | Temperature reporter of computer-aided measuring system |
| CN105444918A (en) * | 2015-12-10 | 2016-03-30 | 中国电子科技集团公司第四十八研究所 | Temperature detecting device for aircraft |
| CN106066342A (en) * | 2016-05-25 | 2016-11-02 | 江西洪都航空工业集团有限责任公司 | A kind of thermal protection test method for aircraft test piece level sample |
| CN106312289A (en) * | 2016-10-14 | 2017-01-11 | 大连理工大学 | Ultrasonic metal welding method adopting pre-stamping deformation treatment |
| CN108344521A (en) * | 2018-03-14 | 2018-07-31 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of transient heat flow sensor |
| CN108344521B (en) * | 2018-03-14 | 2024-04-16 | 中国空气动力研究与发展中心超高速空气动力研究所 | Transient heat flow sensor |
| CN110018186A (en) * | 2019-04-04 | 2019-07-16 | 北京卫星制造厂有限公司 | A kind of lossless detection method of the integrally formed thermal protection struc ture of recoverable airship |
| CN114722543A (en) * | 2022-06-09 | 2022-07-08 | 中国飞机强度研究所 | Design method for heat reflecting screen in structural heat strength test of hypersonic aircraft |
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