CN110274871A - Lightweight heat insulation material heat/vibration coupling test test device under 1700 DEG C of thermal extremes environment of one kind - Google Patents
Lightweight heat insulation material heat/vibration coupling test test device under 1700 DEG C of thermal extremes environment of one kind Download PDFInfo
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- CN110274871A CN110274871A CN201910587523.3A CN201910587523A CN110274871A CN 110274871 A CN110274871 A CN 110274871A CN 201910587523 A CN201910587523 A CN 201910587523A CN 110274871 A CN110274871 A CN 110274871A
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- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
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Abstract
The present invention provides lightweight heat insulation material heat/vibration coupling test test device under 1700 DEG C of thermal extremes environment of one kind, including lightening fire resistant heat-barrier material testpieces, tungsten cover, refractory metal bolt, insulation platform of heat, double platinum rhodium temperature sensor, high-temperature ceramic, industrial control computer, high temperature inorganic glue barrier coat and double platinum rhodium silk.The device can be realized shock resistance experimental test of the hypersonic aircraft light heat-insulating material under 1700 DEG C of thermal extremes environment, and the antivibration kinetic force, anti-heat-proof quality and the security and Reliability Design that are low-density efficient and light weight heat-barrier material used in long-range hypersonic aircraft under hyperthermal environments provide important evidence.There is important engineering application value to the development of hypersonic aircraft.
Description
Technical field
The invention belongs to Material Testing Technology fields, are related to lightweight heat insulation material under 1700 DEG C of thermal extremes environment of one kind
Heat/vibration coupling test test device, especially device can be realized hypersonic aircraft light heat-insulating material at 1700 DEG C
Shock resistance experimental test under thermal extremes environment is low-density lightweight heat-proof used in hypersonic long-range vehicle
Antivibration kinetic force, anti-heat-proof quality and security and Reliability Design of the material under hyperthermal environments provide important evidence.
Background technique
Hypersonic aircraft can be realized it is global remote quickly reach, it is prominent anti-to implement effective high-altitude high speed, completes
Quick precision strike.Due to there is great strategic importance to national security, at present with extremely important application value in army
Hypersonic aircraft has become the research hotspot of each main spacefaring nation in the world.
The Aerodynamic Heating of high speed makes hypersonic aircraft face extremely harsh thermal boundary environment, some key positions
Temperature be up to 1700 DEG C, and the duration is up to hundreds of seconds even thousands of seconds.Due to being installed inside hypersonic aircraft
There are the components such as electronic instrument, control system and warhead, temperature requirement is within tens degree in cabin, therefore, it is necessary to using light
Matter high efficiency heat insulation material makes thermal protection structure, to guarantee the safety of internal unit.
The lightening fire resistant heat-barrier material of efficient low heat conductivity has zirconia material, porous ceramics and nano material etc., though
These right hot heat insulation materials have light weight, the good advantage of thermal protective performance.But due to there are a large amount of subtle holes in material,
Loosely organized, the ability for resisting vibration is relatively low.Long-range hypersonic aircraft is in prolonged high temperature and high vibration coupling
In cyclization border, violent shake will lead to that lightweight heat insulation material or thermal protection structure are cracked, misplace, remove or fall off, and make
Even cause fatal safety accident at serious heat leakage.The hypersonic aircraft HTV-2 of US military development, in high horse
When conspicuous number is taken a flight test, there is vibration removing in thermally protective materials, and aerodynamic heating parameter is more than two orders of magnitude of design objective, and test is caused to be lost
It loses.U.S.'s the Space Shuttle Columbia causes wing nose since external tank protective materials falls off under strong vibration
There is slight crack in thermal protection system, and high-temperature gas enters wing from slight crack, and explosion is caused to be disintegrated, seven astronaut's death, loss
It is extremely heavy.Therefore in order to guarantee the security reliability of long-range hypersonic aircraft, it is necessary to heat insulation material, thermal protection struc ture into
Heat/vibration coupling ground validation test under the conditions of row high-temperature vibrating, is simulated in hypersonic aircraft High Mach number flight course
Thermal extremes and strong vibration combinational environment, examine heat insulation material and structure in high temperature ring by heat/vibration coupling test method
Antivibration kinetic force, anti-heat insulation and stability and reliability under border.Peace of this work for hypersonic aircraft
Full design and reliability assessment have particularly important meaning.
But there has been no can be to hypersonic aircraft solar heat protection under up to 1700 DEG C of thermal extremes environment at present
The freedom from vibration of material can be carried out heat/vibration coupling test test device.In order to confirm hypersonic aircraft heat insulation material with
Reliability of the structure under severe high temperature strong vibration combinational environment, guarantees distance flight safety, and hypersonic aircraft is ground
Department processed proposes urgent need for being up to the resistance to shock test of heat insulation material under 1700 DEG C of heat vibration coupling environment, therefore,
The development of hypersonic aircraft heat-barrier material heat/vibration coupling test test device, which is one, under thermal extremes environment has challenge
Property project, and have extremely important military engineering application value.
Summary of the invention
The technical problem to be solved by the present invention is overcoming the deficiencies of the prior art and provide a kind of 1700 DEG C of thermal extremes rings
Lightweight heat insulation material heat/vibration coupling test test device, especially device is able to solve porous low-density lightweight heat-proof under border
For material in the case where strong vibration couples environment with thermal extremes, bulk material surface temperature is difficult to the problem of accurate measurement and control, real
Existing shock resistance experimental test of the hypersonic aircraft light heat-insulating material under 1700 DEG C of thermal extremes environment.It is superb
Antivibration kinetic force, anti-thermal insulation under low density porous light heat-insulating material hyperthermal environments used in velocity of sound long-range vehicle
The acquisition of energy and the security and Reliability Design of thermal protection struc ture provide important evidence.
The present invention solve above-mentioned technical problem the technical solution adopted is that: lightweight is anti-under a kind of 1700 DEG C of thermal extremes environment
Hot material heat/vibration coupling test test device includes: lightening fire resistant heat-barrier material testpieces, tungsten cover, refractory metal
Bolt, insulation platform of heat, double platinum rhodium temperature sensor, high-temperature ceramic, industrial control computer, high temperature inorganic glue barrier coat, flexibility
Ceramic fibre heat insulation felt, shake table drive control device, exciting stage body, shaking platform, Si-Mo rod heating electrodes, refractory ceramics frame,
Refractory ceramics thermal insulation board A, refractory ceramics thermal insulation board B, diathermanous square hole and double platinum rhodium silk；The lightening fire resistant heat-barrier material test
The size of part and the inner space of tungsten cover are fitted close, and are compressed and be installed among tungsten cover.Pass through refractory metal
Tungsten cover is fastened on the middle part of insulation platform of heat by bolt.By Plasma Welding mode by the thermometric of double platinum rhodium temperature sensor
End is welded on the upper surface centre of tungsten cover.It is set with and is resistant on two one metal wires of double platinum rhodium temperature sensor
1800 DEG C of alumina refractory ceramics pipe outer.In addition, the high temperature noble metal double platinum rhodium silk that several sections are resistant to 1800 DEG C is pressed
The both ends of double platinum rhodium silk are welded on tungsten cover on high-temperature ceramic, and through ion soldering method, so that double platinum rhodium temperature
Degree sensor is further fastened on the upper surface of tungsten cover, and the cold end of double platinum rhodium temperature sensor is connected to industry control calculating
Machine, the temperature signal that industrial control computer is measured according to double platinum rhodium temperature sensor is on the tungsten cover under heat/vibration coupling environment
Surface temperature is measured and is controlled.Although the fusing point of tungsten is very about 3380 DEG C high, tungsten will appear at high temperature
Oxidation removing.To prevent tungsten cover surface from occurring oxidation removing under 1700 DEG C of thermal extremes aerobic environments, in tungsten cover
Upper surface coat high temperature inorganic glue barrier coat, so that tungsten cover with air insulated, is blocked the oxidation on its surface at high temperature
Behavior.The present invention can carry out the upper surface temperature of tungsten cover in the case where 1700 DEG C of exceedingly odious high-temperature vibratings couple environment
Dynamic measures and control.
Further, the double platinum rhodium silk that the number segment is resistant to 1800 DEG C of high temperature is pressed on high-temperature ceramic, double
The both ends of platinum-rhodium wire are fused by plasma welding method in the upper surface of tungsten cover, are consolidated to double platinum rhodium temperature sensor
It is fixed；It is adhesively fixed in addition, being coated between double platinum rhodium temperature sensor and tungsten cover and being resistant to the inorganic glues of 1700 DEG C of high temperature.
Pass through compound reinforcement fixed form, it is ensured that under 1700 DEG C of thermal extremes and vibration coupling environment, double platinum rhodium temperature sensor with
Tungsten cover will not separate, and guarantee heat/vibration coupling test success.
Further, the tungsten cover thinner thickness is 3mm-4mm.Since metal material thermal conductivity is high, it is thermally conductive very
Fastly, the inner and outer surfaces temperature that the thin tungsten of 3mm-4mm covers on very short time internal heating surface just can reach unanimously.Therefore work as
When heat source heats tungsten cover, lightening fire resistant heat-barrier material testpieces heating surface temperature hysteresis effect is very small, substantially
It is identical as tungsten cover hot-face temperature.The present invention is by carrying out temperature to high temperature resistant, thermally conductive fast, high-intensitive tungsten cover surface
Control, and lightening fire resistant heat-barrier material testpieces is pressed among tungsten cover, it efficiently solves under strong vibration environment,
Loose lightening fire resistant heat-barrier material testpieces surface temperature is difficult to determining problem, is successfully realized 1700 DEG C of hot environments
Under, the heat/vibration coupling of the hypersonic aircraft lightening fire resistant heat-barrier material of surface porosity very low to thermal coefficient and density
Experimental test.
Further, the main ingredient of the high temperature inorganic glue barrier coat coated in tungsten cover upper surface is oxidation
Aluminium and silicate, high temperature inorganic glue barrier coat can contact of the barrier metal tungsten cover with air, prevent in 1700 DEG C of high temperature rings
There is high-temperature oxydation removing in tungsten cover under border.
Further, the surrounding of the tungsten cover be equipped be resistant to the flexible ceramic fibers of 1700 DEG C of high temperature every
The heating surface of hot felt, flexible ceramic fibers heat insulation felt is concordant with the upper surface of tungsten cover.Flexible ceramic fibers heat insulation felt reduces
The heat transfer on tungsten cover periphery.Flexible ceramic fibers heat insulation felt can be such that the peripheral temperature of high-temperature metal bolt is reduced to simultaneously
High-temperature metal bolt safe working temperature is hereinafter, ensure that the safety that can only operate in 1000 DEG C of high-temperature metal bolts below
And reliability.
Further, the Si-Mo rod heating electrodes are fixed on the refractory ceramics frame of insulation, are had on refractory ceramics frame
The equidistant circular hole of one row, Si-Mo rod heating electrodes are horizontal positioned, are inserted into the circular hole of refractory ceramics frame.Industrial control computer control
The voltage at Si-Mo rod heating electrodes both ends is made and adjusts, Si-Mo rod heating electrodes generate up to 1700 DEG C of the hot ring of thermal extremes
Border.
Further, the upper and lower part of the Si-Mo rod heating electrodes is mounted on refractory ceramics thermal insulation board, prevents heat source from producing
Raw high temperature is to external leakage.The middle part of that block refractory ceramics thermal insulation board between Si-Mo rod heating electrodes and tungsten cover
There is a square diathermanous square hole, the high temperature that Si-Mo rod heating electrodes generate is radiated to the table of tungsten cover by diathermanous square hole
Face, the lightening fire resistant heat-barrier material testpieces being fastened in tungsten cover to clamping heat.
Further, the shake table drive control device issues high-power random vibration signal, and driving is in exciting stage body
The shaking platform on top vibrates up and down, and carries out high temperature ring to the lightening fire resistant heat-barrier material testpieces being installed in tungsten cover
Shock resistance is tested under border.The isolation platform of metal is horizontally fixed on shaking platform, and the inside of insulation platform of heat is machined with
Rotation shape water-cooling channel, rotation shape water-cooling channel inside stream supercooled water cools down to insulation platform of heat when Gao Wenre/vibration coupling test,
Insulation platform of heat ensure that expensive and easily damaged vibratory equipment being capable of reliable work for a long time under 1700 DEG C of high temperature
Make.
Further, the double platinum rhodium temperature sensor be can in 1800 DEG C of high-temperature oxidation environments reliably working your gold
Belong to platinum rhodium material, the diameter of the wire of double platinum rhodium temperature sensor is 0.6-1.0mm.
The principle of the present invention is as follows:
Environment is coupled with thermal extremes in strong vibration to solve the porous low-density light heat-insulating material of hypersonic aircraft
Under, bulk material surface temperature is difficult to the problem of accurate measurement and control, realizes hypersonic aircraft low-density heat-barrier material
Shock resistance experimental test under 1700 DEG C of thermal extremes environment.Lightening fire resistant heat-barrier material testpieces is installed on resistance to
In the tungsten cover of high temperature, and the thermometric end of high temperature double platinum rhodium temperature sensor is welded on tungsten by plasma welding connection
The middle part of the upper surface of cover.Tungsten cover is fastened on insulation platform of heat by high-temperature metal bolt.Double platinum rhodium temperature in order to prevent
Degree sensor falls off under strong vibration and leads to test failure, and the double platinum rhodium silk that several sections are resistant to 1800 DEG C of high temperature is pressed on equipped with oxygen
On the double platinum rhodium temperature sensor for changing aluminium high-temperature insulation ceramic tube, the both ends of double platinum rhodium silk are fused by plasma welding method
In the upper surface of tungsten cover, double platinum rhodium temperature transducer is fixed；In addition, double platinum rhodium temperature sensor and tungsten cover
Between be coated with and be resistant to the inorganic glues of 1700 DEG C of high temperature and be adhesively fixed.Pass through a variety of compound fixed forms, it is ensured that at 1700 DEG C
Under thermal extremes and vibration coupling environment, double platinum rhodium temperature sensor will not be separated with tungsten cover, it is ensured that heat/vibration coupling test
Success.Since 3380 DEG C of fusing point of tungstens will appear oxidation peeling under high temperature aerobic environment, in tungsten
The surface of cover coats high temperature inorganic glue barrier coat, and tungsten cover is made with air insulated, to block the oxidation on its surface at high temperature
Behavior guarantees double platinum rhodium temperature transducer being reliably fixed on tungsten cover under thermal extremes.Tungsten cover is designed to compare
It is relatively thin, it is 3-4mm thick, the inner and outer surfaces temperature for making tungsten cover on very short time internal heating surface just reaches unanimously, so that gently
(tungsten cover can not be set the surface temperature basic synchronization of the hot-face temperature of quality high-temperature heat-barrier material testpieces and tungsten cover
That sets is too thin, to guarantee the rigidity of tungsten cover at high temperature).The insulation platform of heat of Nei Bu You rotation shape water-cooling channel is established simultaneously,
When high warm/vibration coupling test, rotation shape water-cooling channel inside stream supercooled water cools down to metallic insulation platform, by high temperature plus
Hot-zone is isolated with vibratory equipment, ensure that expensive and easily damaged vibratory equipment at high temperature can be reliable for a long time
Work.The present invention realizes shock resistance of the hypersonic aircraft light heat-insulating material under 1700 DEG C of thermal extremes environment
Experimental test is the antivibration under low density porous light heat-insulating material hyperthermal environments used in hypersonic long-range vehicle
The security and Reliability Design of kinetic force, the acquisition of anti-heat-proof quality and thermal protection struc ture provides important evidence, has important work
Journey application value.
Compared with the prior art, the invention has the advantages that:
(1) hypersonic aircraft is in extremely harsh thermal environment, and the temperature of certain key positions may be up to 1700
DEG C, the duration is up to hundreds of seconds even thousands of seconds.Therefore hypersonic aircraft must use low heat conductivity, low-density and prevent
The high lightening fire resistant heat-barrier material of the thermal efficiency carries out thermal protection.But as zirconium oxide resistant to high temperature, porous ceramics and nanometer material
There are a large amount of fine holes in the light heat-insulating materials such as material, loosely organized, when carrying out high temperature strong vibration coupling test, temperature sensing
The thermometric end of device will appear shake, can not stablize and be fixed on for a long time the surface of lightening fire resistant heat-barrier material, therefore
The measurement and control that high temperature strong vibration couples the surface temperature of lightening fire resistant heat-barrier material under environment becomes heat/vibration coupling test
The most key problem of success.Current existing method has that " nanometer heat insulation material heat is shaken under a kind of thermal extremes environment
Collaborative experiment device " (patent of invention ZL201410222420.4).This invention is pushed down thermometric using noble metal platinum rhodium tabletting and is used
The thermometric end of double platinum rhodium temperature sensor, the hollow ceramic bar installed by four right-angled intersections is by double platinum rhodium temperature sensor
Front end be crimped on nanometer heat insulation material testpieces, come during guarantee test double platinum rhodium temperature sensor can with nanometer every
The reliable measurements of hot material testpieces intimate surface contact and surface temperature.It finds in actual use, which is shaking
Dynamic power spectral density is highly effective when being not very big.But under 1700 DEG C of thermal extremes, elongated ceramic bar it is strong
Degree can be declined, and when the size of testpieces and bigger oscillation power spectrum density, strong high temperature random vibration can make
The middle part of longer ceramic bar generates a degree of dynamic deformation, prevent the thermometric end of temperature sensor is from resistance to lightweight
The surface of high temperature insulating material keeps being in close contact, between lightening fire resistant heat-barrier material surface and the thermometric end of temperature sensor
There is gap, causes the accuracy and reliability of the surface temperature measurement of lightening fire resistant heat-barrier material to decline, especially work as height
When the time of vibration of power spectral density is long, the problem is just more serious.Therefore, it is necessary to be innovated, try to solve
Hypersonic aircraft lightening fire resistant heat-barrier material heat/vibration coupling test under the conditions of long-time high temperature, high power spectrum density
In low-density light heat-insulating material surface temperature measurement problem.
It is very high in view of the fusing point of tungsten metal, up to 3380 DEG C, and metal material thermal conductivity is good.Therefore the present invention will
Lightening fire resistant heat-barrier material testpieces is fastened in tungsten cover resistant to high temperature, make the surface of lightening fire resistant heat-barrier material with
The problem of measurement and control lightening fire resistant heat-barrier material surface temperature is transformed into survey by tungsten cover intimate surface contact
The problem of amount is with control tungsten cover surface temperature.It must be 3mm-4mm than relatively thin by tungsten cover thickness design.And metal material
Expect that thermal conductivity is high, it is thermally conductive quickly, the thin tungsten of 3mm-4mm covers on the inner and outer surfaces temperature of very short time internal heating surface just
It can reach consistent.Therefore when heat source heats tungsten cover, lightening fire resistant heat-barrier material testpieces heating surface temperature hysteresis
It is very small, it is substantially synchronous with tungsten cover hot-face temperature.
(2) in order to make the thermometric end of temperature sensor high-temperature vibrating test in always can be with the upper surface of tungsten cover
It links together.The present invention using crimping, does not pass through high-temperature plasma welding method for the survey of metallic temperature sensor
Warm end is directly welded in the upper surface of tungsten cover, is integrally formed the two, to guarantee the stabilization of the upper surface thermometric of tungsten cover
Property and accuracy.In addition, the double platinum rhodium silk that several segments are resistant to 1800 DEG C of high temperature is pressed on the high temperature being sleeved on double platinum rhodium silk
On ceramic tube, the both ends of double platinum rhodium silk are passed through into the welding of plasma welding connection in the upper surface of tungsten cover, so that temperature passes
Sensor is securely fixed on tungsten cover, still further, the coating between double platinum rhodium temperature sensor and tungsten cover
The inorganic glue for being resistant to 1700 DEG C of high temperature is adhesively fixed to temperature sensor.Pass through MULTIPLE COMPOSITE fixing means, it is ensured that
Under 1700 DEG C of thermal extremes and vibration coupling environment, double platinum rhodium temperature sensor will not be separated with tungsten cover.
(3) although the fusing point of tungsten is very about 3380 DEG C high, tungsten will appear serious under 1700 DEG C of high temperature
Aoxidize peeling.To prevent tungsten cover surface from occurring oxidation removing under thermal extremes oxidation environment, so that tungsten cover
Intensity decline, the thermometric end for even resulting in temperature sensor falls off.Tungsten cover surface coat inorganic glue resistant to high temperature every
From coating, tungsten cover surface is made, with air exclusion, to block the oxidation behavior on its surface under 1700 DEG C of high temperature.
(4) inner space of the size of lightening fire resistant heat-barrier material testpieces and tungsten cover is fitted close, and is pressed on
In tungsten cover, tungsten cover is fastened on to the middle part of insulation platform of heat by refractory metal bolt.In the surrounding of tungsten cover
The flexible ceramic fibers heat insulation felt that can be resistant to 1700 DEG C of high temperature, the heating surface and metal of the flexible ceramic fibers heat insulation felt are installed
The upper surface of tungsten cover is concordant.Flexible ceramic fibers heat insulation felt reduces the heat transfer on tungsten cover periphery.Meanwhile flexible ceramic is fine
Dimension heat insulation felt makes the peripheral temperature of high-temperature metal bolt be reduced to 1000 DEG C hereinafter, ensure that can only operate in 1000 DEG C below
The safety and reliability of high-temperature metal bolt.
(5) high-temperature metal insulation platform of heat is fixed on shaking platform, the inside Jia Gong You rotation shape water cooling of insulation platform of heat is logical
Road, rotation shape water-cooling channel inside stream supercooled water cools down to the isolation platform of rigidity when Gao Wenre/vibration coupling test, water cooling
Metallic insulation platform under environment ensure that expensive and easily damaged vibratory equipment under 1700 DEG C of high temperature for a long time
Reliably working.
(6) apparatus of the present invention are simple for structure, good reliability, and lightweight heat insulation material heat under 1700 DEG C of thermal extremes environment is made to shake
Coupling test can be realized successfully, be low density porous light heat-insulating material superhigh temperature used in hypersonic long-range vehicle
Antivibration kinetic force, the acquisition of anti-heat-proof quality and the security and Reliability Design of thermal protection struc ture under environment provide important examination
Test method for testing, and there is important military engineering application value.
Detailed description of the invention
Fig. 1 is hypersonic aircraft lightening fire resistant heat-barrier material testpieces schematic diagram.
Fig. 2 is schematic structural diagram of testing device of the invention.
Fig. 3 is the power spectral density schematic diagram of vibration signal.
Fig. 4 is that hypersonic aircraft lightening fire resistant heat-barrier material testpieces height warms/shake the forward and backward surface of coupling test
The contrast schematic diagram of form.
Specific embodiment
With reference to the accompanying drawing and specific embodiment further illustrates the present invention.
As depicted in figs. 1 and 2, lightweight heat insulation material heat/vibration under a kind of 1700 DEG C of thermal extremes environment provided by the invention
Experiment test device includes: lightening fire resistant heat-barrier material testpieces 1, tungsten cover 2, refractory metal bolt 3, insulation platform of heat
4, double platinum rhodium temperature sensor 5, high-temperature ceramic 6, industrial control computer 7, high temperature inorganic glue barrier coat 8, flexible ceramic fibers
Heat insulation felt 9, shake table drive control device 10, exciting stage body 11, shaking platform 12, Si-Mo rod heating electrodes 13, refractory ceramics frame
14, refractory ceramics thermal insulation board A15, refractory ceramics thermal insulation board B16, diathermanous square hole 17 and double platinum rhodium silk 18.Heat-proof quality is excellent,
But the hypersonic aircraft lightening fire resistant heat-barrier material testpieces 1 that density is low, intensity is not high is placed on insulation platform of heat, and tight
Gu four sides of tungsten cover 2 are fixed in insulation platform of heat 4 by refractory metal bolt 3 in the tungsten cover 2 of box-like
Portion.In order to which the surface temperature to tungsten cover 2 controls, your gold that can will effectively work in 1800 DEG C of high temperature aerobic environments
The thermometric end for belonging to material double platinum rhodium temperature sensor 5 is directly welded in the upper surface of tungsten cover 2 by plasma welding connection
At the heart.In order to insulate, alumina high temperature ceramic tube 6 is set on two one metal wires of double platinum rhodium temperature sensor 5.By number segment
Double platinum rhodium silk 18 is pressed on high-temperature ceramic 6, and the both ends of double platinum rhodium silk 18 are welded on tungsten by plasma welding method
The upper surface of cover 2, further fixes double platinum rhodium temperature sensor 5；In addition, double platinum rhodium temperature sensor 5 and metal
It is coated with the inorganic glue for being resistant to 1700 DEG C of high temperature between tungsten cover 2, double platinum rhodium temperature sensor 5 is fastened on metal after inorganic adhesive curing
The surface of tungsten cover 2.Pass through a variety of compound fixed forms, it is ensured that under 1700 DEG C of thermal extremes and vibration coupling environment, double platinum rhodium
Temperature sensor 5 will not be separated with tungsten cover 2, be guaranteed under high temperature strong vibration environment, hypersonic aircraft lightweight solar heat protection
The successful progress of material heat/vibration coupling test.
The good rigidity of metal tungsten structure, must be than relatively thin by the thickness design of tungsten cover 2, only 3mm-4mm.Due to metal
Material thermal conductivity is high, it is thermally conductive quickly, in a short period of time, the inner and outer surfaces temperature of heating surface just can reach tungsten cover 2
Unanimously.Therefore when heat source heats tungsten cover 2, the hot-surface temperature of lightening fire resistant heat-barrier material testpieces 1 is substantially
It is identical as 2 hot-face temperature of tungsten cover.Present invention efficiently solves under strong vibration environment, loose lightening fire resistant is heat-insulated
The problem of 1 surface temperature of testing of materials part extremely difficult measurement, it is embedded into metal essentially by by lightening fire resistant heat-barrier material 1
The method of tungsten cover 2 is obtained thermal coefficient and density is very low by the measurement to 2 surface temperature of tungsten cover, surface porosity it is superb
The surface temperature of velocity of sound aircraft lightening fire resistant heat-barrier material 1, to realize lightweight solar heat protection material under 1700 DEG C of thermal extremes environment
Material heat/vibration coupling test solves critical issue.
Double platinum rhodium temperature sensor 5 is connected to industrial control computer 7, industrial control computer 7 is according to double platinum rhodium temperature sensor 5
1 upper surface of tungsten cover 2 and lightening fire resistant heat-barrier material testpieces that the temperature signal measured shakes under coupling environment to heat
Temperature is controlled.Although the fusing point of tungsten is very high, about 3380 DEG C, oxidation stripping can occur quickly in tungsten at high temperature
From.To prevent 2 surface of tungsten cover from occurring oxidation removing under 1700 DEG C of thermal extremes oxidation environments, in the upper of tungsten cover 2
Surface coats high temperature inorganic glue barrier coat 8, and tungsten cover 2 is made with air insulated, to block the oxidation row on its surface at high temperature
To guarantee the safety of tungsten cover 2 at high temperature, preventing the double platinum rhodium temperature sensor 5 for being welded on 2 upper surface of tungsten cover de-
It falls.
Though the fusing point due to tungsten is high, more crisp；The fusing point of metal molybdenum is also relatively high (2600 DEG C), but intensity is low,
Therefore the highest tungsten of fusing point and metal molybdenum are not suitable for the stress fastener of production bolt etc.Current high-temperature metal spiral shell
Bolt 3 can only operate in 1000 DEG C or less.Therefore the flexible ceramic that can be resistant to 1700 DEG C of high temperature is installed in the surrounding of tungsten cover 2
The heating surface of Fibrous insulation 9, flexible ceramic fibers heat insulation felt 9 is concordant with the upper surface of tungsten cover 2.Flexible ceramic fibers every
Hot felt 9 reduces the thermal diffusion on 2 periphery of tungsten cover, meanwhile, flexible ceramic fibers heat insulation felt 9 can make high-temperature metal bolt 3
Peripheral temperature be reduced to 1000 DEG C hereinafter, ensure that can only operate in 1000 DEG C of high-temperature metal bolts 3 below safety and
Reliability.
The i.e. high-power random vibration signal of autopower spectral density as shown in Figure 3 is issued by shake table drive control device 10,
Driving in 11 top of exciting stage body shaking platform 12 vibrate up and down, to the lightening fire resistant being installed in tungsten cover 2 every
Hot material testpieces 1 carries out shock resistance under hot environment and tests.
Heat source is made of Si-Mo rod heating electrodes 13, and Si-Mo rod heating electrodes 13 are horizontal positioned, and the both ends of Si-Mo rod are consolidated
It is scheduled on the refractory ceramics frame 14 of insulation, there is the equidistant circular hole of a row on refractory ceramics frame 14, Si-Mo rod heating electrodes 13 are inserted
Enter into the circular hole of refractory ceramics frame 14.Industrial control computer 7 controls and adjusts the voltage at 13 both ends of Si-Mo rod heating electrodes, makes silicon
Molybdenum bar heating electrodes 13 become the heating source of temperature-controllable, can generate 1700 DEG C of thermal extremes thermal environment.Si-Mo rod heating
The upper and lower part of array 13 is provided with refractory ceramics thermal insulation board A15 and B16, to prevent high temperature when test to external leakage.It is described
Refractory ceramics thermal insulation board A15 and B16 be fixedly mounted on refractory ceramics frame 14.In Si-Mo rod heating electrodes 13 and tungsten
There is a square diathermanous square hole 17 in the middle part of refractory ceramics thermal insulation board B16 between cover 2, Si-Mo rod heating electrodes 13 generate
High temperature be radiated to the surface of tungsten cover 2 by diathermanous square hole 17, it is heat-insulated to the lightening fire resistant being installed in tungsten cover 2
Testing of materials part 1 is heated.
Since the price is very expensive for vibratory equipment, itself does not have thermal protection function.In order in 1700 DEG C of thermal extremes rings
Vibratory equipment is protected under border, has designed and produced a hollow metal isolation platform 4, it is flat to be horizontally fixed on vibration
On platform 12, the inside of insulation platform of heat 4 adds work to have rotation shape water-cooling channel, rotation shape water-cooling channel inside stream supercooling when high warm vibration examination is tested
But water cools down to the insulation platform of heat 4 of rigidity, and water-cooled insulation platform of heat 4 ensure that expensive and easily damaged vibration is set
It is standby can under 1700 DEG C of high temperature reliably working.
Temperature sensor be it is a kind of can in 1800 DEG C of high-temperature oxidation environments reliably working noble metal double platinum rhodium temperature
Sensor, due to work in thermal extremes strong vibration environment, the diameter of the wire of double platinum rhodium temperature sensor 5 cannot be taken
Must be too thin, otherwise it is easy to produce fatigue at high temperature fracture.In addition, the diameter of the wire of double platinum rhodium temperature sensor 5 can not mistake
Slightly, its excessively thick thermometric thermo-lag is big, and dynamic response is bad.Therefore, the wire of double platinum rhodium temperature sensor 5 is set in the present invention
Diameter be 0.6-1.0mm.
Fig. 4 is that hypersonic aircraft lightening fire resistant heat-barrier material testpieces is forward and backward in Gao Wenre/vibration coupling test
Contrast schematic diagram, as seen from the figure by after high warm/vibration coupling test, lightening fire resistant heat-barrier material testpieces 1 occurs
Apparent through-wall crack.The appearance of crackle can reduce structural strength, and heat leakage increases, and can cause safety accident.Therefore needs pair
The material improves.Lightweight heat insulation material heat/vibration coupling test test under 1700 DEG C of thermal extremes environment provided by the invention
Device is antivibration of the low-density efficient and light weight heat-barrier material under thermal extremes environment used in long-range hypersonic aircraft
Kinetic force detection and security and Reliability Design provide important evidence.There is important reality to the development of hypersonic aircraft
Border application value.
Non-elaborated part of the present invention belongs to techniques well known.
Claims (6)
1. lightweight heat insulation material heat/vibration coupling test test device under a kind of 1700 DEG C of thermal extremes environment, it is characterised in that: institute
The test device stated include lightening fire resistant heat-barrier material testpieces (1), tungsten cover (2), refractory metal bolt (3), every
Hot platform (4), double platinum rhodium temperature sensor (5), high-temperature ceramic (6), industrial control computer (7), high temperature inorganic glue barrier coat
(8) and double platinum rhodium silk (18)；The lightening fire resistant heat-barrier material testpieces (1) is installed in tungsten cover (2), passes through resistance to height
Tungsten cover (2) is fastened on the middle part of insulation platform of heat (4) by warm metal bolts (3)；By the thermometric of double platinum rhodium temperature sensor (5)
End is welded on the central part of the upper surface of tungsten cover (2) by plasma welding connection；Two of double platinum rhodium temperature sensor (5)
High-temperature ceramic (6) are set on wire；By several sections can double platinum rhodium silk (18) resistant to high temperature be pressed in high-temperature ceramic (6)
On, the both ends of double platinum rhodium silk (18) are welded on tungsten cover (2), so that double platinum rhodium temperature sensor (5) is fastened to metal
The upper surface of tungsten cover (2), the cold end of double platinum rhodium temperature sensor (5) are connected to industrial control computer (7), industrial control computer (7) root
The temperature signal measured according to double platinum rhodium temperature sensor (5) to tungsten cover (2) the upper surface temperature under heat/vibration coupling environment into
Row detects and controls；It is coated with high temperature inorganic glue barrier coat (8) in the upper surface of tungsten cover (2), tungsten cover (2) is made to exist
With air exclusion under high temperature, the oxidation behavior on its surface is blocked.
2. lightweight heat insulation material heat/vibration coupling test is surveyed under a kind of 1700 DEG C of thermal extremes environment according to claim 1
Trial assembly is set, it is characterised in that: the test device further includes shake table drive control device (10), exciting stage body (11), vibration
Platform (12), Si-Mo rod heating electrodes (13), refractory ceramics frame (14), refractory ceramics thermal insulation board A (15), refractory ceramics thermal insulation board
B (16) and diathermanous square hole (17)；The Si-Mo rod heating electrodes (13) are fixed on the refractory ceramics frame (14) of insulation, high
There is the equidistant circular hole of a row on warm ceramic frame (14), Si-Mo rod heating electrodes (13) are horizontal positioned, are inserted into refractory ceramics frame
(14) in circular hole；Industrial control computer (7) controls and adjusts the voltage at Si-Mo rod heating electrodes (13) both ends, heats Si-Mo rod
Array (13) becomes the heating source of temperature-controllable, generates 1700 DEG C of thermal extremes thermal environment；Si-Mo rod heating electrodes (13)
Upper and lower part is equipped with refractory ceramics thermal insulation board A (15) and B (16) respectively；In Si-Mo rod heating electrodes (13) and tungsten cover
(2) there are a square diathermanous square hole (17), Si-Mo rod heating electrodes in the refractory ceramics thermal insulation board B (16) between, middle part
(13) high temperature generated is radiated to the surfaces of tungsten cover (2) by diathermanous square hole (17), to being installed in tungsten cover (2)
Lightening fire resistant heat-barrier material testpieces (1) is heated；High-power random vibration is issued by shake table drive control device (10)
Signal, driving is moved up and down in the shaking platform (12) on exciting stage body (11) top, light in tungsten cover (2) to being installed on
Quality high-temperature heat-barrier material testpieces (1) carries out shock resistance under hot environment and tests.
3. lightweight heat insulation material heat/vibration coupling test is surveyed under a kind of 1700 DEG C of thermal extremes environment according to claim 1
Trial assembly is set, it is characterised in that: the insulation platform of heat (4) is horizontally fixed on shaking platform (12), insulation platform of heat (4)
Inside plus work have rotation shape water-cooling channel (11), flow through in rotation shape water-cooling channel when height warms vibration test in insulation platform of heat (4) cold
But water cools down to metallic insulation platform (4).
4. lightweight heat insulation material heat/vibration coupling test is surveyed under a kind of 1700 DEG C of thermal extremes environment according to claim 1
Trial assembly is set, it is characterised in that: is equipped with flexible ceramic fibers heat insulation felt (9) in the surrounding of tungsten cover (2), the flexible ceramic is fine
The heating surface for tieing up heat insulation felt (9) is concordant with the upper surface of tungsten cover (2)；Flexible ceramic fibers heat insulation felt (9) not only reduces
The heat transfer on tungsten cover (2) periphery, meanwhile, flexible ceramic fibers heat insulation felt (9) makes the periphery temperature of refractory metal bolt (3)
Degree is reduced to 1000 DEG C hereinafter, ensure that the safety that can only operate in 1000 DEG C of high-temperature metal bolts (3) below and reliable
Property.
5. lightweight heat insulation material heat/vibration coupling test is surveyed under a kind of 1700 DEG C of thermal extremes environment according to claim 1
Trial assembly is set, it is characterised in that: tungsten cover (2) with a thickness of 3mm-4mm thickness；When heat source heats tungsten cover (2), lightweight
High temperature resistant heat insulation material testpieces (1) heating surface temperature is equal with the temperature of tungsten cover (2) heating surface.
6. lightweight heat insulation material heat/vibration coupling test is surveyed under a kind of 1700 DEG C of thermal extremes environment according to claim 1
Trial assembly is set, it is characterised in that: the diameter of the wire of double platinum rhodium temperature sensor (5) is 0.6-1.0mm.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112444369A (en) * | 2020-12-21 | 2021-03-05 | 中国航天空气动力技术研究院 | Pneumatic heat-vibration combined test device for flat model with adjustable attack angle |
| CN112577687A (en) * | 2020-12-28 | 2021-03-30 | 中国航天空气动力技术研究院 | Pneumatic heat-vibration combined test device for small wing rudder structure |
| CN112858381A (en) * | 2020-12-31 | 2021-05-28 | 中国建筑材料科学研究总院有限公司 | Heat insulation performance test device and test method for heat insulation material for high-speed aircraft engine |
| CN113352248A (en) * | 2021-06-02 | 2021-09-07 | 西南交通大学 | Non-conductive ceramic thermal shock test equipment anchor clamps |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102483010A (en) * | 2009-07-10 | 2012-05-30 | 埃塔里姆有限公司 | Stirling cycle transducer for converting between thermal energy and mechanical energy |
| CN103969137A (en) * | 2014-05-23 | 2014-08-06 | 北京航空航天大学 | Thermal shock joint experiment device for nanometer thermal insulation material in extreme high-temperature environment |
| CN104133933A (en) * | 2014-05-29 | 2014-11-05 | 温州职业技术学院 | Pneumatic elastic mechanical characteristic analytical method of hypersonic speed aircraft in thermal environment |
| CN203965263U (en) * | 2014-05-23 | 2014-11-26 | 北京航空航天大学 | The nanometer heat insulation material heat Collaborative experiment device that shakes under a kind of thermal extremes environment |
| CN108255781A (en) * | 2018-01-04 | 2018-07-06 | 北京环境特性研究所 | A kind of hypersonic target surface dynamic temperature modeling method |
-
2019
- 2019-07-02 CN CN201910587523.3A patent/CN110274871B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102483010A (en) * | 2009-07-10 | 2012-05-30 | 埃塔里姆有限公司 | Stirling cycle transducer for converting between thermal energy and mechanical energy |
| CN103969137A (en) * | 2014-05-23 | 2014-08-06 | 北京航空航天大学 | Thermal shock joint experiment device for nanometer thermal insulation material in extreme high-temperature environment |
| CN203965263U (en) * | 2014-05-23 | 2014-11-26 | 北京航空航天大学 | The nanometer heat insulation material heat Collaborative experiment device that shakes under a kind of thermal extremes environment |
| CN104133933A (en) * | 2014-05-29 | 2014-11-05 | 温州职业技术学院 | Pneumatic elastic mechanical characteristic analytical method of hypersonic speed aircraft in thermal environment |
| CN108255781A (en) * | 2018-01-04 | 2018-07-06 | 北京环境特性研究所 | A kind of hypersonic target surface dynamic temperature modeling method |
Non-Patent Citations (2)
| Title |
|---|
| 吴大方 等: "1500℃高温氧化环境下C/SiC复合材料结构的热/力联合试验", 《复合材料学报》 * |
| 吴大方 等: "1700℃有氧环境下高超声速飞行器轻质防热材料隔热性能试验研究", 《航天器环境工程》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112444369A (en) * | 2020-12-21 | 2021-03-05 | 中国航天空气动力技术研究院 | Pneumatic heat-vibration combined test device for flat model with adjustable attack angle |
| CN112577687A (en) * | 2020-12-28 | 2021-03-30 | 中国航天空气动力技术研究院 | Pneumatic heat-vibration combined test device for small wing rudder structure |
| CN112858381A (en) * | 2020-12-31 | 2021-05-28 | 中国建筑材料科学研究总院有限公司 | Heat insulation performance test device and test method for heat insulation material for high-speed aircraft engine |
| CN112858381B (en) * | 2020-12-31 | 2023-03-24 | 中国建筑材料科学研究总院有限公司 | Heat insulation performance test device and test method for heat insulation material for high-speed aircraft engine |
| CN113352248A (en) * | 2021-06-02 | 2021-09-07 | 西南交通大学 | Non-conductive ceramic thermal shock test equipment anchor clamps |
| CN113352248B (en) * | 2021-06-02 | 2023-03-10 | 西南交通大学 | Non-conductive ceramic thermal shock test equipment anchor clamps |
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