CN103969137A - Thermal shock joint experiment device for nanometer thermal insulation material in extreme high-temperature environment - Google Patents
Thermal shock joint experiment device for nanometer thermal insulation material in extreme high-temperature environment Download PDFInfo
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Abstract
The invention provides a thermal shock joint experiment device for a nanometer thermal insulation material in extreme high-temperature environment. The thermal shock joint experiment device comprises a nanometer thermal insulation material test piece of a hypersonic flight vehicle, a primary thermal insulation platform, a precious-metal platinum rhodium pressing sheet, a double platinum rhodium temperature sensor, a hollow ceramic rod, a semicircular clamp, a stretched spring, a secondary-stage thermal insulation platform, a shock table body, an excitation platform, a water cooling channel, an infrared radiation heat source array, a high-power regulator, a fixed electrode, a connecting support, a light thermal insulation material, a shock table drive controller, a ceramic tube and a high-temperature-resistant soft mat. The experiment device can realize the experimental measurement for the anti-shock performance of the nanometer thermal insulation material of the hypersonic flight vehicle in the extreme high-temperature environment being 1500 DEG C, provides important experimental bases for the bearing capability, the thermal insulation performance and the safe and reliable design of the novel nanometer thermal insulation material used by hypersonic remote motor flight vehicles in the extreme high-temperature environment, and has an important engineering application value for development of the hypersonic flight vehicle.
Description
Technical field
The present invention relates under a kind of thermal extremes environment the nanometer heat insulation material heat Collaborative experiment device that shakes, particularly this experimental provision can be realized the experiment test of hypersonic aircraft nanometer heat insulation material shock resistance under the thermal extremes environment up to 1500 DEG C, and load-bearing capacity, anti-heat-proof quality and the security and Reliability Design of the novel nano heat-barrier material using for hypersonic long-range maneuvering-vehicle under thermal extremes environment provides important evidence.
Background technology
Hypersonic aircraft can be realized the remote arrival fast in the whole world, implements effective high-altitude high speed prominent anti-, completes quick precision strike.Owing to having extremely important application value in army and national security is had to great strategic importance, hypersonic aircraft has become the focus of the each main spacefaring nation research in the world.The flying speed of hypersonic aircraft is very fast, generally more than velocity of sound (is greater than 5 Mach) at 5 times, the hypersonic aircraft HTV-2 of U.S. Department of Defense's research and development, and its flight Mach number is up to 22; Russia at present reaches 14 the sky and space plane with super " territorial sky " striking capabilities putting forth effort research and development Mach number; Ministry of National Defence of France has also carried out the development effort of the hypersonic motor-driven aircraft of Mach 2 ship 12; The design rate of the hypersonic aircraft SHEFEX II of the national space flight of Germany center development is up to 12 Mach.In addition, Britain, Japan and other countries have also all been carried out the research about hypersonic aircraft technology.Due to the speed of hypersonic aircraft and increasing substantially of flight time, the thermal environment problem being produced by Aerodynamic Heating when High Mach number flight becomes very harsh.In the time that High Mach number flies, the temperature of some key position of hypersonic aircraft, up to 1500 DEG C, has even exceeded 1500 DEG C as the local temperature of air intake duct and some attitude controlling position.Therefore the ground experiment under thermal extremes environment is very important to the safe design of hypersonic aircraft.
Some position of long-range hypersonic aircraft is not only among exceedingly odious hot environment, and its high-temperature duration even will reach thousands of seconds.Because hypersonic aircraft inside is provided with accurate electronic equipment and warhead etc., its temperature does not allow to exceed 80 DEG C.For weight reduction, the thermal protection space of hypersonic aircraft is very little.Therefore must develop and install high efficiency heat insulation material or thermal protection structure, to reduce the conduction of velocity of the hypersonic aircraft surface inside portion of heat, ensure the safety of internal unit.The requirement of thermally protective materials and structure is: lightweight, thickness is little, the anti-thermal efficiency is high, common heat insulation material is difficult to meet the demands, and adopting in recent years novel nano-material is the important research direction that meets the anti-heat insulation demand of hypersonic aircraft.
Although the heat-proof quality of nanometer heat insulation material is superior, but owing to there being a large amount of minute apertures, loosely organized, the ability of opposing vibration is relatively low, therefore how to solve and under high temperature and strong vibration environment, can use reliably problem extremely important in ground in the anti-heat-barrier material of nanometer not high intensity.Some thermal protection structure, in order to improve heat insulation usefulness, is made (as shown in Figure 1) by the different material of multilayer or unitized construction, and serious safety problem very easily appears in sandwich construction and Complex Assembled Structure.Because long-range hypersonic aircraft is among long high temperature and high vibration environment, fierce shake can cause that heat insulation material or thermal protection structure occur crackle, misplace, peel off or come off, and causes serious heat to reveal and even causes fatal security incident.For example, U.S.'s the Space Shuttle Columbia is because an external tank protective materials comes off, cause wing front end thermal protection system to occur slight crack, gas very hot when space shuttle is reentried enters wing from slight crack, cause the fusing of wing inner structure, finally cause full machine blast to be disintegrated, loss is very heavy.The hypersonic aircraft HTV-2 of US military development, while taking a flight test for the second time, peeling off appears in thermally protective materials, and Aerodynamic Heating parameter exceedes two orders of magnitude of design objective, finally causes test failure.Therefore in order to ensure the safe reliability of long-range hypersonic aircraft, must carry out heat under the high-temperature vibrating condition associating ground demonstration test of shaking to heat insulation material, thermal protection struc ture, thermal extremes and the combinational environment of strong vibration in simulation hypersonic aircraft High Mach number flight course, check heat insulation material and anti-vibration ability, anti-effect of heat insulation and stability and the reliability of structure under hot environment by the heat Combined Trials method of shaking.This work has very important meaning for safe design and the reliability assessment of hypersonic aircraft.
But, not yet have at present and can be under the thermal extremes environment up to 1500 DEG C can carry out the shake device of Combined Trials test of heat to the shock resistance of nanometer heat insulation material.In order to confirm the anti-heat-barrier material of hypersonic aircraft and the structure reliability under severe high temperature strong vibration combinational environment, ensure the safety of distance flight, the development departments of hypersonic aircraft has proposed active demand for the resistance to shock test of nanometer heat insulation material under the combinational environment that shakes up to 1500 DEG C of heat at present, therefore, under thermal extremes environment, nanometer heat insulation material heat is shaken that the development of Collaborative experiment device not only has important engineering background and is a challenging research topic.
Summary of the invention
The technical problem to be solved in the present invention is: overcome the deficiencies in the prior art, the nanometer heat insulation material heat Collaborative experiment device that shakes is provided under a kind of thermal extremes environment, can complete and have a large amount of minute apertures, loosely organized nano-material surface is up to the reliable temperature survey at the temperature of 1500 DEG C and under strong vibration condition, reaches the shake object of Collaborative experiment of heat.And can be under the exceedingly odious hot environment up to 1500 DEG C carry out heat isolation and heat protection to the expensive excitational equipment with rubber seal parts, ensure vibration excitational equipment can be within the time that reaches thousands of seconds trouble free service continuously.Load-bearing capacity, anti-heat-proof quality and the safe design of the novel nano heat-barrier material using for hypersonic long-range maneuvering-vehicle under thermal extremes environment provides reliable basis.
The technical scheme that the present invention solves the problems of the technologies described above employing is: the nanometer heat insulation material heat Collaborative experiment device that shakes under a kind of thermal extremes environment, comprise: hypersonic aircraft nanometer heat insulation material testpieces, one-level insulation platform of heat, noble metal platinum rhodium compressing tablet, double platinum rhodium temperature sensor, hollow ceramic bar, semicircle clip, back-moving spring, secondary insulation platform of heat, vibration stage body, excitation platform, water-cooling channel, infrared radiation thermal source array, Great Power Adjuster, fixed electorde, connecting rack, light heat-insulating material, shaking table driving governor, ceramic pipe and high-temperature flexible mat, described hypersonic aircraft nanometer heat insulation material testpieces is fixed on one-level insulation platform of heat, noble metal platinum rhodium compressing tablet is pressed on thermometric double platinum rhodium temperature sensor, and the hollow ceramic bar of installing by four right-angled intersections is tightly crimped on the front end of double platinum rhodium temperature sensor on nanometer heat insulation material testpieces, by the end position of four hollow refractory ceramics bars, be fixed on secondary insulation platform of heat by semicircle clip and back-moving spring, when heat is shaken Combined Trials, the temperature sensing end of double platinum rhodium temperature sensor is owing to being pressed downwards by noble metal platinum rhodium compressing tablet, therefore can be synchronized with the movement up and down with the vibration of secondary insulation platform of heat, make the leading section potential energy of double platinum rhodium temperature sensor enough under high strength random vibration, keep close contact with nanometer heat insulation material testpieces all the time, double platinum rhodium temperature sensor can be measured the surface temperature of the nanometer heat insulation material testpieces under 1500 DEG C of high temperature strong vibration combinational environments reliably.
Further, described test unit has one-level insulation platform of heat and secondary insulation platform of heat, one-level insulation platform of heat and secondary insulation platform of heat are all horizontally fixed on the excitation platform of vibration stage body, and the provision for thermal insulation of two-stage combined-type water cold type carrys out reliable heat isolation guaranteed price costliness and that be easy to the vibratory equipment damaging.
Further, the inside Jia Gong You rotation shape water-cooling channel of described one-level insulation platform of heat and secondary insulation platform of heat, the heat Combined Trials Shi rotation shape water-cooling channel inside that shakes is flow through chilled water one-level insulation platform of heat and secondary insulation platform of heat is lowered the temperature.
Further, described infrared radiation heating array is lifted on nanometer heat insulation material testpieces by fixed electorde and connecting rack, between infrared radiation thermal source array and vibration stage body and excitation platform, there is no hard coupling part, while making to test, infrared radiation thermal source array keeps stationary state, has avoided fragile infrared radiation thermal source array because the random vibration of high strength up and down of excitation platform is shattered.
Further, on two one metal wires of described double platinum rhodium temperature sensor, be installed with thin ceramic tubes, make between tinsel and tinsel and noble metal platinum rhodium compressing tablet between mutually insulated, prevent from occurring short circuit phenomenon between tinsel double platinum rhodium temperature sensor and noble metal platinum rhodium compressing tablet.
Further, the end position of described four hollow ceramic bars is provided with 8 back-moving springs altogether, in order to absorb vibratory impulse energy.
Further, right-angled intersection place of described four hollow refractory ceramics bars, is all placed with thickness and is the high-temperature flexible mat of 3-4mm as buffering transition member, impact energy when absorbing vibration.
Further, the Elema that described infrared radiation heating array is 1500 DEG C by operating limit temperature is arranged in parallel and forms.
Further, the top of the surrounding of described nanometer heat insulation material testpieces and infrared radiation thermal source array and light heat-insulating material is around all installed, the heat while preventing 1500 DEG C of hot tests is revealed.
Principle of the present invention is:
Infrared radiation thermal source array is installed above nanometer heat insulation material testpieces, by connecting Great Power Adjuster power supply, the upper surface of nanometer heat insulation material testpieces is heated.Infrared radiation heating array is lifted on nanometer heat insulation material testpieces by fixed electorde and connecting rack, between infrared radiation thermal source array and vibration stage body and excitation platform, there is no hard coupling part, when test, infrared radiation thermal source array will keep stationary state, has therefore avoided fragile infrared radiation thermal source array to be shattered due to the high-intensity oscillation of excitation platform.The top of the surrounding of nanometer heat insulation material testpieces and infrared radiation thermal source array and light heat-insulating material, the heat leak while preventing 1500 DEG C of hot tests are around all installed.Shaking table driving governor drives excitation platform to move up and down according to the vibrational waveform setting and intensity in test, the nanometer heat insulation material testpieces being fixed on one-level insulation platform of heat is carried out to vibrational excitation, to realize hypersonic aircraft nanometer heat insulation material shock resistance experiment test under the thermal extremes environment of temperature up to 1500 DEG C.
Because double platinum rhodium temperature sensor is the thermopair of being made up of two elongated tinsels, shape is elongated and soft, and under high-intensity vibration, the upper and lower whipping of meeting, causes damage.Therefore not only use one can resistance to 1500 DEG C of high temperature noble metal platinum rhodium compressing tablet be pressed in the thermometric end of double platinum rhodium temperature sensor, also use another piece noble metal platinum rhodium compressing tablet to be pressed near of the root of double platinum rhodium temperature sensor, being pressed on nanometer heat insulation material testpieces double platinum rhodium temperature sensor by four hollow ceramic bars, when test, double platinum rhodium temperature sensor can keep synchronous vibration with nanometer heat insulation material testpieces under high-intensity oscillation, while having avoided test, the shake of double platinum rhodium temperature sensor damages, ensure the reliability of thermometric when Long Time Thermal shakes test.
Because double platinum rhodium temperature sensor and noble metal platinum rhodium compressing tablet are conductive metallic material, for avoiding producing short circuit between double platinum rhodium temperature sensor and noble metal platinum rhodium compressing tablet, prevent from occurring short circuit phenomenon between two one metal wires of double platinum rhodium temperature sensor simultaneously, on two one metal wires of described double platinum rhodium temperature sensor, be all installed with thin ceramic tubes, make between tinsel and tinsel and noble metal platinum rhodium compressing tablet between insulate.
Solid refractory ceramics bar structure elongated under high-temperature vibrating environment easily ruptures, therefore the hollow ceramic bar that adopts four intersections of hollow structure to install is tightly crimped on the front end of double platinum rhodium temperature sensor on nanometer heat insulation material testpieces, because ceramic bar is hollow, the free expansion space, inside and outside border of hollow ceramic bar is large, and the anti-fracture characteristics under high thermal environment is better than solid construction.Between four hollow refractory ceramics bars, there are four point of crossing, owing to can producing the hard contact of rigid material between four hollow refractory ceramics bars, easily fracture under strong vibration, therefore in right-angled intersection place of four hollow refractory ceramics bars, all be placed with thickness and be the high-temperature flexible mat of 3-4mm as buffering transition member, impact energy when absorbing vibration.The end position of other four hollow ceramic bars is equipped with back-moving spring and connects with secondary insulation platform of heat, also can absorb vibratory impulse energy, the employing of described two-stage vibration reducing measure, the rupture failure of the hollow refractory ceramics bar of rigidity while having avoided strong vibration.
For this test unit want can be under the thermal extremes environment up to 1500 DEG C that exceedes most metals material melting point trouble free service, design and manufacture of the present invention two-stage water-cooled insulation platform of heat vibratory equipment expensive and that be easy to damage carried out to heat isolate.One-level insulation platform of heat and secondary insulation platform of heat inside are all processed with rotation shape water-cooling channel as shown in Fig. 2, and this design connects water-cooling channel compared with linear pattern, have advantages of lightweight, heat-insulating efficiency is high.Due to being installed, insulation platform of heat can produce additional mass, the maximum effective push of excitational equipment will be lowered, therefore distance is designed littlely in the planar dimension with the closer one-level insulation platform of heat of nanometer heat insulation material testpieces of high-temperature region, be mainly used in 1500 DEG C of high thermal regions in hot environment middle part to realize heat isolation.Because the planar dimension of one-level insulation platform of heat designs littlely, its additional mass is also relatively little, also less on the impact of excitational equipment thrust.The planar dimension of secondary insulation platform of heat is relatively large, can cover whole excitation platform completely, and the second heat thermal extremes environment in test being carried out by the larger secondary insulation platform of heat of planar dimension is isolated, and has guaranteed the safe reliability of vibration excitational equipment.The nanometer heat insulation material heat Collaborative experiment device that shakes under above-mentioned thermal extremes environment, load-bearing capacity, anti-heat-proof quality and the safe design of the novel nano heat-barrier material using for hypersonic long-range maneuvering-vehicle under thermal extremes environment provides reliable experimental basis, has important engineering using value.
The present invention's beneficial effect is compared with prior art:
(1) the present invention uses the noble metal platinum rhodium compressing tablet of heatproof up to 1800 DEG C to push down the thermometric end of thermometric double platinum rhodium temperature sensor, the hollow ceramic bar of installing by four right-angled intersections is crimped on the front end of double platinum rhodium temperature sensor on nanometer heat insulation material testpieces, ensured in experimentation double platinum rhodium temperature sensor all the time can with nanometer heat insulation material testpieces surface close contact and thermometric reliability.And use back-moving spring that the two ends of hollow refractory ceramics bar are fixed, back-moving spring is apparatus with shock absorbing effectively; High-temperature flexible mat is installed as buffering transition member at the point of crossing place of four hollow ceramic bars, is prevented from making rigid ceramic bar to produce hard contact point.Owing to having adopted the damping technology measure of above-mentioned two-stage absorption vibratory impulse energy, avoid the rupture failure of the hollow refractory ceramics bar of rigidity of the lower four right-angled intersections installation of high temperature strong vibration combinational environment.For make test unit can be under the thermal extremes environment up to 1500 DEG C that exceedes most metals material melting point trouble free service, design and manufacture two-stage water-cooled insulation platform of heat vibratory equipment expensive and that be easy to damage is carried out to heat isolation, guaranteed to vibrate the safe reliability of excitational equipment.The present invention can measure reliably surface temperature, effect of heat insulation and the shock resistance of the more open nanometer heat insulation material testpieces of structure under 1500 DEG C of severe high temperature strong vibration combinational environments, load-bearing capacity, anti-insulative properties and the safe design of the novel nano heat-barrier material using for hypersonic long-range maneuvering-vehicle under thermal extremes environment provides reliable test basis, and the development of hypersonic aircraft is had to important engineering using value.
(2) because double platinum rhodium temperature sensor is the thermopair of being made up of two elongated tinsels, shape is elongated and soft, and under high-intensity random oscilation, the upper and lower whipping of meeting, causes damage.Therefore the present invention not only use one can resistance to 1500 DEG C of high temperature noble metal platinum rhodium compressing tablet be pressed in the thermometric end of double platinum rhodium temperature sensor, also use another piece noble metal platinum rhodium compressing tablet to be pressed near the root of double platinum rhodium temperature sensor, by four hollow ceramic bars, double platinum rhodium temperature sensor is pressed on nanometer heat insulation material testpieces, when test, the entirety of double platinum rhodium temperature sensor can keep being synchronized with the movement with nanometer heat insulation material testpieces under high-intensity oscillation, while having avoided test, the shake of double platinum rhodium temperature sensor damages, ensure the Long Time Thermal thermometric reliability in Combined Trials of shaking.
(3), because solid refractory ceramics bar structure easily ruptures under high-temperature vibrating environment, the hollow ceramic bar that therefore adopts four right-angled intersections of hollow structure to install is crimped on the front end of double platinum rhodium temperature sensor on nanometer heat insulation material testpieces.Because use the ceramic bar structure of hollow, the inside and outside free expansion space of bar is large, and the anti-fracture characteristics under thermal extremes environment is better, not easy fracture.
(4) between the hollow refractory ceramics bar due to four right-angled intersections installations, there are four contact points, therefore there will be the hard contact region of rigidity between ceramic bar, under strong vibration, easily occur crack conditions.The present invention is in right-angled intersection place of four hollow refractory ceramics bars, is all placed with thickness and is the high-temperature flexible mat of 3-4mm as buffering transition material, impact energy when absorbing vibration.In addition, the end position of four hollow ceramic bars is all provided with eight back-moving springs, also can absorb vibratory impulse energy, the employing of two-stage vibration reducing measure, the rupture failure of the hollow refractory ceramics bar of rigidity while having avoided strong vibration.
(5) design and manufacture of the present invention two-stage combined-type water cold type insulation platform of heat expensive vibratory equipment is carried out to heat isolation.Because insulation platform of heat can produce additional mass, effective push on excitational equipment has impact, therefore the planar dimension of the nanometer heat insulation material testpieces closer one-level insulation platform of heat of distance in high-temperature region designs littlely, be mainly used in the middle part high-temperature area of 1500 DEG C of thermal environments to realize heat isolation, because the planar dimension of one-level insulation platform of heat is less, its additional mass is also relatively little, also less on the impact of excitational equipment thrust.The planar dimension of secondary insulation platform of heat is relatively large, can cover whole excitation platform completely, second heat thermal extremes environment in test being carried out by the larger secondary insulation platform of heat of planar dimension is isolated, and has guaranteed the safe reliability of the vibration excitational equipment more fragile for thermal environment.
(6) the inside equal Jia Gong You rotation shape water-cooling channel of one-level insulation platform of heat and secondary insulation platform of heat, this design connects water-cooling channel compared with linear pattern, have lightweight, the advantage that heat-insulating efficiency is high.
(7) apparatus of the present invention are simple for structure, for load-bearing capacity, anti-heat-proof quality and the safe design of novel nano heat-barrier material under the combinational environment up to 1500 DEG C of thermal extremes and strong vibration provides important experimental test means.
Brief description of the drawings
Fig. 1 is hypersonic aircraft nanometer heat insulation material schematic diagram;
Fig. 2 is structural representation of the present invention;
Fig. 3 is the insulation platform of heat inner structure schematic diagram of Han You rotation shape water-cooling channel of the present invention.
Embodiment
Further illustrate the present invention below in conjunction with accompanying drawing and embodiment.
As shown in Figures 2 and 3, the present invention is made up of with high-temperature flexible mat 19 hypersonic aircraft nanometer heat insulation material testpieces 1, one-level insulation platform of heat 2, noble metal platinum rhodium compressing tablet 3, double platinum rhodium temperature sensor 4, hollow ceramic bar 5, semicircle clip 6, back-moving spring 7, secondary insulation platform of heat 8, vibration stage body 9, excitation platform 10, water-cooling channel 11, infrared radiation thermal source array 12, Great Power Adjuster 13, fixed electorde 14, connecting rack 15, light heat-insulating material 16, shaking table driving governor 17, ceramic pipe 18.Hypersonic aircraft nanometer heat insulation material testpieces 1 is fixed on one-level insulation platform of heat 2, noble metal platinum rhodium compressing tablet 3 is pressed in to the thermometric end of thermometric double platinum rhodium temperature sensor 4, and the hollow ceramic bar 5 of installing by four right-angled intersections is tightly crimped on the front end of double platinum rhodium temperature sensor 4 on nanometer heat insulation material testpieces 1, by semicircle clip 6 and back-moving spring 7, the end of four hollow refractory ceramics bars 5 is fixed on secondary insulation platform of heat 8, when heat is shaken Combined Trials, the temperature sensing end of double platinum rhodium temperature sensor 4 is owing to being pressed downwards by noble metal platinum rhodium compressing tablet 3, therefore can be synchronized with the movement up and down with the vibration of secondary insulation platform of heat 8, make the leading section potential energy of double platinum rhodium temperature sensor 4 enough under high strength random vibration condition, keep close contact with nanometer heat insulation material testpieces 1 all the time, thereby make double platinum rhodium temperature sensor 4 can measure reliably the surface temperature of the nanometer heat insulation material testpieces 1 under 1500 DEG C of high temperature and strong vibration combinational environment.One-level insulation platform of heat 2 and secondary insulation platform of heat 8 are all horizontally fixed on the excitation platform 10 of vibration stage body 9; the inside Jia Gong You rotation shape water-cooling channel 11 of one-level insulation platform of heat 2 and secondary insulation platform of heat 8; in the time that shaking test, heat isolates hot environment by mobile chilled water; can carry out heat isolation and heat protection to the parts such as rubber closure and excitation moving-coil that very easily damage due to high temperature below excitation platform 10, to reach the object that can ensure the expensive long-time safe and reliable work of vibration excitational equipment under the thermal extremes environment up to 1500 DEG C.Infrared radiation thermal source array 12 is installed above nanometer heat insulation material testpieces 1, powers by connecting Great Power Adjuster 13, the upper surface of nanometer heat insulation material testpieces 1 is heated.Infrared radiation heating array 12 is lifted on the top of nanometer heat insulation material testpieces 1 by fixed electorde 14 and connecting rack 15, between infrared radiation thermal source array 12 and excitation platform 10, there is no hard coupling part, when test, infrared radiation thermal source array 12 will keep stationary state, has therefore avoided fragile infrared radiation thermal source array 12 because the random vibration of high strength up and down of excitation platform 10 is damaged.The top of the surrounding of nanometer heat insulation material testpieces 1 and infrared radiation thermal source array 12 and light heat-insulating material 16 is around all installed, the heat while preventing 1500 DEG C of hot tests is revealed.In experiment, shaking table driving governor 17 drives excitation platform 10 to move up and down according to the vibrational waveform setting and intensity, and the nanometer heat insulation material testpieces 1 being fixed on one-level insulation platform of heat 2 is carried out to vibrational excitation.
Because double platinum rhodium temperature sensor 4 is thermopairs of being made up of two elongated tinsels, shape is elongated and soft, and under high-intensity vibration, the upper and lower whipping of meeting, very easily causes damage.Therefore not only use one can resistance to 1500 DEG C of high temperature noble metal platinum rhodium compressing tablet 3 be pressed in the thermometric end of double platinum rhodium temperature sensor 4, also use another piece noble metal platinum rhodium compressing tablet 3 to be pressed near of the root of double platinum rhodium temperature sensor 4, the hollow ceramic bar 5 of installing by four right-angled intersections is pressed on double platinum rhodium temperature sensor 4 on nanometer heat insulation material testpieces 1, when test, double platinum rhodium temperature sensor 4 can keep synchronous vibration with nanometer heat insulation material testpieces 1 under high-intensity oscillation, avoid the shake of double platinum rhodium temperature sensor 4 in experimentation to damage, ensure the Long Time Thermal thermometric reliability of Collaborative experiment of shaking.
Because double platinum rhodium temperature sensor 4 and noble metal platinum rhodium compressing tablet 3 are conductive metallic material, between double platinum rhodium temperature sensor 4 and noble metal platinum rhodium compressing tablet 3, produce short circuit, prevent from occurring short circuit phenomenon between two one metal wires of double platinum rhodium temperature sensor 4 simultaneously, on two one metal wires of double platinum rhodium temperature sensor 4, be all installed with thin ceramic tubes 18, make between tinsel and tinsel and noble metal platinum rhodium compressing tablet 3 between insulation.
Because solid refractory ceramics bar structure elongated under high-temperature vibrating environment easily ruptures, therefore the hollow ceramic bar 5 that adopts four intersections of hollow structure to install is tightly crimped on the front end of double platinum rhodium temperature sensor 4 on nanometer heat insulation material testpieces 1, because the free expansion space, inside and outside border of hollow ceramic bar is large, the anti-fracture characteristics under high thermal environment is better than solid construction.Between four hollow refractory ceramics bars 5, there are four point of crossing, firmly contact owing to can producing rigidity between four hollow refractory ceramics bars 5, under strong vibration, easily there is crack conditions, therefore in right-angled intersection place of four hollow refractory ceramics bars 5, all being placed with thickness is the high-temperature flexible mat 19 conduct buffering transition member of 3-4mm, impact energy while vibration to absorb.The end position of other four hollow ceramic bars 5 is provided with altogether root back-moving spring 7 and connects with secondary insulation platform of heat 8, in order to absorb vibratory impulse energy, and the employing of above two-stage vibration reducing measure, the rupture failure of the hollow refractory ceramics bar 5 of rigidity while having avoided strong vibration.
For this test unit want can be under 1500 DEG C of thermal extremes environment that exceed most metals material melting point trouble free service.Design and manufacture of the present invention two-stage water-cooled insulation platform of heat to expensive and be easy to damage vibratory equipment carry out heat isolate.One-level insulation platform of heat 2 is all processed with rotation shape water-cooling channel 11 as shown in Fig. 3 with the inside of secondary insulation platform of heat 8, and this design connects water-cooling channel compared with simple linear pattern, have advantages of lightweight, heat-insulating efficiency is high.Due to being installed, insulation platform of heat can produce additional mass, effective push to excitational equipment has certain influence, therefore closer apart from nanometer heat insulation material testpieces 1, the planar dimension of the one-level insulation platform of heat 2 in high-temperature region designs smallerly, is mainly used in the central region of 1500 DEG C of hot environments to realize heat isolation.Because the planar dimension of one-level insulation platform of heat 2 designs littlely, its additional mass is also relatively little, also less on the impact of excitational equipment thrust.The planar dimension of secondary insulation platform of heat 8 is relatively large, can cover whole excitation platform 10 completely, second heat thermal extremes environment in experiment being carried out by the larger secondary insulation platform of heat 8 of planar dimension is isolated, and has guaranteed the safe reliability of the vibration excitational equipment more fragile to thermal environment.The nanometer heat insulation material heat Collaborative experiment device that shakes under above-mentioned thermal extremes environment, the novel nano heat-barrier material using for hypersonic long-range maneuvering-vehicle provides reliable basis at shake up to the heat of 1500 DEG C load-bearing capacity under combinational environment, anti-heat-proof quality and safe design, has important engineering using value.
Non-elaborated part of the present invention belongs to techniques well known.
Claims (9)
1. the nanometer heat insulation material heat Collaborative experiment device that shakes under a thermal extremes environment, it is characterized in that comprising: hypersonic aircraft nanometer heat insulation material testpieces (1), one-level insulation platform of heat (2), noble metal platinum rhodium compressing tablet (3), double platinum rhodium temperature sensor (4), hollow ceramic bar (5), semicircle clip (6), back-moving spring (7), secondary insulation platform of heat (8), vibration stage body (9), excitation platform (10), water-cooling channel (11), infrared radiation thermal source array (12), Great Power Adjuster (13), fixed electorde (14), connecting rack (15), light heat-insulating material (16), shaking table driving governor (17), ceramic pipe (18) and high-temperature flexible mat (19), described hypersonic aircraft nanometer heat insulation material testpieces (1) is fixed on one-level insulation platform of heat (2), noble metal platinum rhodium compressing tablet (3) is pressed on the thermometric end of thermometric double platinum rhodium temperature sensor (4), and hollow ceramic bar (5) being tightly crimped on nanometer heat insulation material testpieces (1) double platinum rhodium temperature sensor (4) of installing by four right-angled intersections, by the end position of four hollow refractory ceramics bars (5), be fixed on secondary insulation platform of heat (8) by semicircle clip (6) and back-moving spring (7), when heat is shaken Combined Trials, the temperature sensing end of double platinum rhodium temperature sensor (4) is pressed downwards by noble metal platinum rhodium compressing tablet (3), can be synchronized with the movement up and down with the vibration of secondary insulation platform of heat (8), make the front end position of double platinum rhodium temperature sensor (4) keep close contact with nanometer heat insulation material testpieces (1) all the time under high strength random vibration, make double platinum rhodium temperature sensor (4) can under 1500 DEG C of high temperature strong vibration combinational environments, measure reliably the surface temperature of more fragile nanometer heat insulation material testpieces (1).
2. the nanometer heat insulation material heat Collaborative experiment device that shakes under a kind of thermal extremes environment according to claim 1, it is characterized in that: described test unit has one-level insulation platform of heat (2) and secondary insulation platform of heat (8), it is upper that one-level insulation platform of heat (2) and secondary insulation platform of heat (8) are all horizontally fixed on the excitation platform (10) of vibration stage body (9), and the provision for thermal insulation of two-stage combined-type water cold type carrys out reliable heat isolation guaranteed price costliness and that be easy to the vibratory equipment damaging.
3. the nanometer heat insulation material heat Collaborative experiment device that shakes under a kind of thermal extremes environment according to claim 1, it is characterized in that: the inside Jia Gong You rotation shape water-cooling channel (11) of described one-level insulation platform of heat (2) and secondary insulation platform of heat (8), heat Combined Trials Shi rotation shape water-cooling channel (11) inside that shakes is flow through chilled water one-level insulation platform of heat (2) and secondary insulation platform of heat (8) are lowered the temperature.
4. the nanometer heat insulation material heat Collaborative experiment device that shakes under a kind of thermal extremes environment according to claim 1, it is characterized in that: described infrared radiation heating array (12) is lifted on nanometer heat insulation material testpieces (1) by fixed electorde (14) and connecting rack (15), between infrared radiation thermal source array (12) and vibration stage body (9) and excitation platform (10), there is no hard coupling part, while making to test, infrared radiation thermal source array (12) keeps stationary state, avoid fragile infrared radiation thermal source array (12) because the random vibration of high strength up and down of excitation platform (10) is shattered.
5. the nanometer heat insulation material heat Collaborative experiment device that shakes under a kind of thermal extremes environment according to claim 1, it is characterized in that: on two one metal wires of described double platinum rhodium temperature sensor (4), be installed with thin ceramic tubes (18), make between tinsel and tinsel and noble metal platinum rhodium compressing tablet (3) between mutually insulated, prevent from occurring short circuit phenomenon between tinsel double platinum rhodium temperature sensor (4) and noble metal platinum rhodium compressing tablet (3).
6. the nanometer heat insulation material heat Collaborative experiment device that shakes under a kind of thermal extremes environment according to claim 1, it is characterized in that: the end position of described four hollow ceramic bars (5) is provided with 8 back-moving springs (7) altogether, in order to absorb vibratory impulse energy.
7. the nanometer heat insulation material heat Collaborative experiment device that shakes under a kind of thermal extremes environment according to claim 1, it is characterized in that: right-angled intersection place of described four hollow refractory ceramics bars (5), all being placed with thickness is high-temperature flexible mat (19) the conduct buffering transition member of 3-4mm, impact energy while vibration in order to absorb.
8. the nanometer heat insulation material heat Collaborative experiment device that shakes under a kind of thermal extremes environment according to claim 1, is characterized in that: the Elema that described infrared radiation heating array (12) is 1500 DEG C by operating limit temperature is arranged in parallel and forms.
9. the nanometer heat insulation material heat Collaborative experiment device that shakes under a kind of thermal extremes environment according to claim 1, it is characterized in that: the top of the surrounding of described nanometer heat insulation material testpieces (1) and infrared radiation thermal source array (12) and light heat-insulating material (16) is around all installed, the heat while preventing 1500 DEG C of hot tests is revealed.
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| CN112525452A (en) * | 2020-11-06 | 2021-03-19 | 北京强度环境研究所 | High-temperature-resistant excitation measurement integrated test device |
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| CN108168856A (en) * | 2017-11-30 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of load combined experimental rig of heat |
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| CN110274871A (en) * | 2019-07-02 | 2019-09-24 | 北京航空航天大学 | Lightweight heat insulation material heat/vibration coupling test test device under 1700 DEG C of thermal extremes environment of one kind |
| CN110274871B (en) * | 2019-07-02 | 2020-04-21 | 北京航空航天大学 | Testing device for heat/vibration coupling test of light heat-proof material in extremely high temperature environment |
| CN112525452A (en) * | 2020-11-06 | 2021-03-19 | 北京强度环境研究所 | High-temperature-resistant excitation measurement integrated test device |
| CN112649170A (en) * | 2020-12-04 | 2021-04-13 | 中国航天空气动力技术研究院 | Compound heat-proof structure in electric arc wind tunnel test cabin |
| CN113358458A (en) * | 2021-06-03 | 2021-09-07 | 重庆大学 | End plate for compression test suitable for members with different sections |
| CN114309656A (en) * | 2021-12-28 | 2022-04-12 | 北京星航机电装备有限公司 | Powder cleaning method for additive manufacturing complex titanium alloy wing rudder part |
| CN114309656B (en) * | 2021-12-28 | 2023-11-07 | 北京星航机电装备有限公司 | Powder cleaning method for additive manufacturing of complex titanium alloy wing rudder part |
| CN117571242A (en) * | 2024-01-15 | 2024-02-20 | 南京航空航天大学 | High-temperature vibration mode test device for variable-section carbon fiber resin matrix composite |
| CN117571242B (en) * | 2024-01-15 | 2024-04-02 | 南京航空航天大学 | High-temperature vibration mode test device for variable-section carbon fiber resin matrix composite |
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