CN201672853U - Infrared radiation hot-fluid density reinforcing means used in missile high temperature pneumatic heat simulation test - Google Patents
Infrared radiation hot-fluid density reinforcing means used in missile high temperature pneumatic heat simulation test Download PDFInfo
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- CN201672853U CN201672853U CN201020221452XU CN201020221452U CN201672853U CN 201672853 U CN201672853 U CN 201672853U CN 201020221452X U CN201020221452X U CN 201020221452XU CN 201020221452 U CN201020221452 U CN 201020221452U CN 201672853 U CN201672853 U CN 201672853U
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Abstract
An infrared radiation hot-fluid density reinforcing means used in missile high temperature pneumatic heat simulation test comprises a quartz lamp heating array, a blower fan, a frequency conversion speed regulator, quartz glass air-flow isolation plates, a high temperature radiation test member, a water cooling box, a hot-fluid sensor, a temperature sensor and a computer; a unidirectional air-flow guiding isolation channel is composed of the quartz glass air-flow isolation plates; the motor of the blower fan drives diversion fan leaves to rotate in high speed to generate a unidirectional strong air-flow; in the pneumatic heat test for simulating the high temperature transient of missile hypersonic speed flight, the strong air-flow flows across the surface of the quartz lamp heating array in the isolation channel to reduce the temperature to below the softening temperature of the quartz glass. In the utility model, in the heat strength test, the density of the hot-fluid received by the surface of the missile high temperature radiation test member exceeds the limit of 1MW/m2 before air-cooling; and the instant hot-fluid density achieves 2MW/m2; and the utility model provides a more effective dynamic heat radiation high temperature test means for developing hypersonic speed missile.
Description
Technical field
The utility model relates to infrared radiation heat flow density reinforcement device for high temperature pneumatic thermal simulating test of missile.Particularly when the pneumatic heating environment of simulated missile hypersonic flight test, this experimental rig is increased to 2Mw/m2 with the instantaneous radiation heat flow density.For developmental flight speed faster hypersonic missile effective hot test means are provided.
Background technology
Needs for prominent anti-, anti-ballistic, aspect such as the high-altitude is scouted at a high speed, the flying speed of aircraft such as guided missile is more and more faster, the flight Mach Mach number of air defence missile and air-air guided missile has surpassed 6 Mach numbers, the transient heat flow density in missile wing leading edge and guided missile front end antenna house tapering is up to more than the 1.2Mw/m2, and stagnation temperature will be above 1200 ℃.The serious high temperature that pneumatic heating produced can reduce the strength degree of material and the bearing capacity of Flight Vehicle Structure, makes structure produce thermal deformation, destroys the aerodynamic configuration of parts and influences the safe flight of aircraft.For guaranteeing the safety of high-speed aircraft, thermal shock and elevated temperature heat stress rupture that the material of affirmation aircraft and structure are produced in the time of whether standing high-speed flight must carry out pneumatic analog test and thermal strength test to high-speed flight modulator material and structure.Simulated flight material and the structure heating status when high-speed flight, the mechanical property of observation analysis material under thermal environment and mechanical environment effect and the force-bearing situation of structure, thereby further research and analyse structure bearing capacity at high temperature, this work has very important practical significance for the thermal protection of missile flight device with the safety design.
The method of pneumatic thermal modeling test generally has " non-convection type " and " convection type " two classes.
Because the wind tunnel test of representative " convection type ", the experimentation cost under the high temperature and high speed condition are very expensive, the expense of each test is minimum to need hundreds of thousands yuan, needs at most more than millions of units.Therefore, the relatively low pneumatic thermal modeling test technology of representative " non-convection type " quartz heater infra-red radiation of experimentation cost comprises that countries such as the U.S., Russia, Germany, Israel and China are existing all in use.
The outer wall of quartz heater adopts the infrared permeable line, and the hot mastication temperature is 1600 ℃ a quartz glass.Because when test, heater had a segment distance with heated guided missile hyperthermia radiation testpieces (guided missile hyperthermia radiation testpieces is made by ceramic and carbon fibre composite usually), to be higher than heated testpieces surface temperature as the temperature of the heater of pyrotoxin.Therefore, when the distance heater has 50-100mm testpieces surface temperature far away to reach 1100 ℃, will cause that the vacuum sealing of quartz heater leaks, and then the tungsten system of causing filament high-temperature oxydation burn near 1600 ℃ of the softening temperatures of quartz glass as the heater table surface temperature of thermal source.The general quartz heater infra-red radiation thermal source heating guided missile hyperthermia radiation testpieces that uses, its heat flow density is less than 1Mw/m2.
At present because its design flying speed of high-speed missile reaches 6-8 Mach number even higher.The heat flow density of missile wing leading edge and point stationary point portion all can surpass 1.2Mw/m2.Guided missile design department wishes that very the heat flow density of the infra-red radiation that the guided missile test part is accepted in the pneumatic heat test of guided missile high temperature can further improve.Design the pneumatic heat test infra-red radiation of a kind of guided missile high temperature heat flow density intensifier for this reason.Make it heat flow density of infra-red radiation surpass 1Mw/m2 when the high-speed aircraft thermal strength test, transient heat flow density reaches 2Mw/m2.For the flying speed development of hypersonic missile faster provides necessary research technique.
The utility model content
Technology of the present utility model is dealt with problems and is: overcome the deficiencies in the prior art, a kind of infrared radiation heat flow density reinforcement device for high temperature pneumatic thermal simulating test of missile is provided, this device can make the radiant heat flux density of existing quartz heater infrared radiant heat experimental rig be improved, for carry out flying speed faster the pneumatic hot thermal modeling test of hypersonic missile provide radiant heat flux stronger research technique.
Technical solution of the present utility model is: infrared radiation heat flow density reinforcement device for high temperature pneumatic thermal simulating test of missile comprises: quartz lamp heating electrodes, blower fan, variable-frequency governor, quartz glass air-flow division board, hyperthermia radiation testpieces, adiabatic framework, water-cooled case, heat flow transducer, temperature sensor and computer; Described quartz lamp heating electrodes is positioned at by four transparent quartz glass air-flow division boards forms one-way gas flow guiding channel isolation, channel isolation makes high velocity air can not directly be diffused into the surface of hyperthermia radiation testpieces, but the high temp, infrared radiation light that the quartz lamp heating electrodes sends can pass transparent quartz glass air-flow division board and shine directly on the surface of hyperthermia radiation testpieces, when the surface that makes the hyperthermia radiation testpieces can absorb high-intensity infra-red radiation hot-fluid, the influence on the surface of the diffusion couple hyperthermia radiation testpieces of isolation high velocity air; Both sides at quartz glass air-flow division board are equipped with the water-cooled case, are welded with paired cooling-water duct on the water-cooled case, and water-cooled case and cooling-water duct form mobile cooling water peripheral passage; Adiabatic framework is installed around the hyperthermia radiation testpieces; Near the hyperthermia radiation testpieces heat flow transducer is installed, the heating surface of the front end of heat flow transducer and hyperthermia radiation testpieces is on the same vertical plane; On the rear surface of hyperthermia radiation testpieces temperature sensor is installed, heat flow transducer is connected with computer by lead with temperature sensor, two sensors are sent into Computer Storage after gathering the temperature data of radiant heat flux in the pneumatic thermal modeling test process of guided missile high temperature and reflection hyperthermia radiation testpieces back side effect of heat insulation, use for subsequent treatment; Blower fan is positioned at the lower end of quartz lamp heating electrodes, and be installed in support that ground is connected on; The infra-red radiation light that the quartz lamp heating electrodes sends shines the hyperthermia radiation testpieces of guided missile, the suffered dynamic pneumatic heating environments of parts surface such as bullet, body and missile wing during the simulated missile high-speed flight, the motor drives water conservancy diversion flabellum of blower fan rotates at a high speed, form air-flow upwards, high velocity air flows through the outer surface of quartz lamp heating electrodes, take away the heat on part quartz lamp surface, make the temperature on quartz lamp heating electrodes surface drop to quartz glass following 1400 ℃ of softening temperature, the quartz lamp heating electrodes can continue trouble free service.
Described device has also been installed variable-frequency governor, described variable-frequency governor carries out stepless time adjustment to the motor of blower fan, can be during test according to the power of residing hot-fluid environment in the missile flight process, adjust and control the wind speed and the flow that flow through quartz lamp heating electrodes outer surface easily, the temperature that does not make quartz lamp heating electrodes outer surface is brought into play the hyperthermia radiation efficient of quartz lamp heating electrodes as much as possible owing to wind speed falls lowly excessively too greatly.
Described quartz lamp heating electrodes is double quartz lamp heating electrodes, the staggered arrangement of two row's quartz lamp heating electrodes, the infra-red radiation light that next row's quartz lamp heating electrodes is sent just in time passes between the slit of front one row's quartz lamp heating electrodes, and the staggered mode of laying of double quartz lamp heating electrodes has strengthened the radiant heat flux density of irradiated guided missile test part front surface greatly.
The surperficial painted black of described hyperthermia radiation testpieces absorbs the radiant heat flux that the quartz lamp heating electrodes sends to greatest extent.
Described blower fan is installed on the U type support that is connected with ground, and there is the above distance of 50cm on the lower surface of blower fan and ground, form open space environment, guarantees that blower fan air intake path is smooth and easy.
The water-cooled case surface of the relative side of described hyperthermia radiation testpieces is polished into mirror reflection surface, the quartz lamp heating electrodes can be reflexed to the front surface of hyperthermia radiation testpieces to the IR of the other side radiation of hyperthermia radiation testpieces, improve the radiation efficiency of quartz lamp heating electrodes.
Principle of the present utility model: because the flying speed of aircraft such as guided missile is more and more faster, harsh experimental enviroment condition has surpassed the limit of the pneumatic thermal infrared radiation experimental rig of being made up of quartz lamp heater of guided missile high temperature of present use.In order to improve the thermal radiation capability of quartz lamp heater, designed by resistant to elevated temperatures, and the quartz glass air-flow division board that can see through IR is formed one-way gas flow guiding channel isolation, and the motor drives water conservancy diversion flabellum by blower fan rotates at a high speed and forms unidirectional air blast.Make air blast flow through the surface of the quartz lamp heating electrodes in the channel isolation, will be reduced to the softening temperature of quartz glass as the quartz lamp surface temperature of thermal source below 1600 ℃.Utilize quartz glass air-flow division board can see through the characteristic of IR simultaneously, the intense radiation IR that the quartz lamp heating electrodes is sent can shine directly on the hyperthermia radiation testpieces by transparent quartz glass air-flow division board.Because the obstruct of quartz glass air-flow division board, the surface that high velocity air can not be diffused into the hyperthermia radiation testpieces produces dynamic disturbance to it.This technology makes quartz lamp heat run device can give off the stronger IR of heat flow density and is not burnt, and thermal radiation capability has surpassed original operating limit.The heat flow density that guided missile hyperthermia radiation testpieces surface receives during thermal strength test surpasses the restriction do not carry out the 1Mw/m2 when air-cooled, and transient heat flow density can reach 2Mw/m2.For developmental flight speed faster hypersonic missile the effectively dynamic heat radiation research technique of high temperature is provided more.
The utility model beneficial effect compared with prior art is:
(1) in the pneumatic heat test of high temperature transient state of simulated missile hypersonic flight, designed by four transparent high temperature resistant quartz glass air-flow division boards and formed air-flow guiding channel isolation, the motor drives water conservancy diversion flabellum by blower fan rotates the formation air blast at a high speed.Unidirectional air blast flows through the surface of the quartz lamp heating electrodes that is in the channel isolation, takes away the heat on part quartz lamp surface, and the temperature on quartz lamp heating electrodes surface is descended.Because of the hot mastication temperature of quartz glass is 1600 ℃, as long as adjust the rotating speed and the ventilation of motor by variable-frequency governor, when making the temperature on quartz lamp heating electrodes surface drop to below 1400 ℃, the quartz lamp heating electrodes is operate as normal safely just.Form the unidirectional flow-guiding channel that prevents the air-flow diffusion by four quartz glass air-flow division boards, make high velocity air can not directly be diffused into the surface of hyperthermia radiation testpieces, shine directly on the surface of hyperthermia radiation testpieces but the high temp, infrared radiation light that the quartz lamp heating electrodes sends can pass transparent quartz glass air-flow division board.When the surface that makes the hyperthermia radiation testpieces can absorb high-intensity infra-red radiation hot-fluid, isolated the influence on surface of the diffusion couple hyperthermia radiation testpieces of high velocity air again.Therefore, as long as the temperature on quartz lamp heating electrodes surface is dropped to by high velocity air below the hot mastication temperature of quartz glass, the quartz lamp heating electrodes just can be by promoting on the surface that high supply voltage gives off more hot-fluid arrival hyperthermia radiation testpieces.The surperficial painted black of hyperthermia radiation testpieces absorbs the radiant heat flux that the quartz lamp heating electrodes sends to greatest extent.This technology makes the radianting capacity of quartz lamp heating electrodes surpass original operating limit, can give off the stronger IR of heat flow density, the radiant heat flux density that the surface of hyperthermia radiation testpieces receives when the high-speed aircraft thermal strength test has surpassed the restriction of not carrying out the 1Mw/m2 when air-cooled, and transient heat flow density can reach 2Mw/m2.For developmental flight speed faster hypersonic missile effectively dynamic high temperature heat radiation research technique is provided more.
(2) increase as much as possible for the transient state irradiation heat flow density that makes guided missile radiation test part front surface, design and installation double quartz lamp heating electrodes, the staggered arrangement of two row's quartz lamp heating electrodes, the infra-red radiation light that next row's quartz lamp heating electrodes is sent just in time passes between the slit of front one row's quartz lamp heating electrodes, double quartz lamp heating electrodes staggered laid mode and increased significantly compared with single its heating efficiency of heating electrodes mode of routine, strengthened the radiant heat flux density of irradiated guided missile test part front surface greatly.
(3) because the outer wall of quartz heater adopts the infrared permeable line, the hot mastication temperature is 1600 ℃ a quartz glass.But as long as therefore make the temperature of quartz heater outer surface be lower than 1400 ℃ of just trouble free services in the test.The utility model has been installed variable-frequency governor, and the motor of blower fan is carried out stepless time adjustment, can adjust and control the wind speed and the ventilation that flow through quartz lamp heating electrodes outer surface easily according to the power of residing hot-fluid environment in the missile flight process during test.The hyperthermia radiation efficient of quartz lamp heating electrodes is brought into play and improved to the temperature that does not make the quartz heater outer surface as much as possible owing to wind speed falls lowly excessively too greatly.
(4) the utility model apparatus structure is succinct, and is easy to use, and checking with the safety design for the high temperature hot strength of hypersonic vehicles such as guided missile provides radianting capacity stronger ground experiment means.Has important military engineering using value.
Description of drawings
Fig. 1 is a structural representation of the present utility model;
Fig. 2 is a structure schematic top plan view of the present utility model.
The specific embodiment
As depicted in figs. 1 and 2, the utility model is made up of with computer 10 quartz lamp heating electrodes 1, blower fan 2, variable-frequency governor 3, quartz glass air-flow division board 4, hyperthermia radiation testpieces 5, adiabatic framework 6, water-cooled case 7, heat flow transducer 8, temperature sensor 9.Quartz lamp heating electrodes 1 is fixedly connected with the electrode of quartz lamp by the good flat copper bar of electric conductivity, form the dense arrangement plane body of a horizontal positioned, quartz lamp heating electrodes 1 is placed in the one-way gas flow guiding channel isolation of being made up of four transparent quartz glass air-flow division boards 4, the infra-red radiation light that quartz lamp heating electrodes 1 sends shines on the hyperthermia radiation testpieces 5 of guided missile, the suffered dynamic pneumatic heating environments of parts surface such as bullet, body or missile wing during the simulated missile high-speed flight.Blower fan 2 is positioned at the lower end of quartz lamp heating electrodes 1, and the motor 11 of blower fan 2 drives water conservancy diversion flabellum 12 rotation at a high speed, forms air-flow upwards.When high velocity air flows through quartz lamp heating electrodes 1, take away the heat on part quartz lamp surface, the temperature on quartz lamp heating electrodes 1 surface is descended.Because of the hot mastication temperature of quartz glass is 1600 ℃, as long as adjust the rotating speed and the ventilation of motor 11 by variable-frequency governor 3, when making the temperature on quartz lamp heating electrodes 1 surface drop to below 1400 ℃, quartz lamp heating electrodes 1 is operate as normal safely just.Form the air-flow area of isolation that prevents the air-flow diffusion by four quartz glass air-flow division boards 4, form unidirectional flow-guiding channel, make high velocity air can not directly be diffused into the surface of hyperthermia radiation testpieces 5, shine directly on the surface of hyperthermia radiation testpieces 5 but the high temp, infrared radiation light that quartz lamp heating electrodes 1 sends can pass transparent quartz glass air-flow division board 4.When the surface that makes hyperthermia radiation testpieces 5 can absorb high-intensity infra-red radiation hot-fluid, isolated the influence on surface of the diffusion couple hyperthermia radiation testpieces 5 of high velocity air again.The surperficial painted black of hyperthermia radiation testpieces 5 absorbs the hot-fluid that quartz lamp heating electrodes 1 sends to greatest extent.Therefore, as long as the temperature on quartz lamp heating electrodes 1 surface is dropped to below the hot mastication temperature of quartz glass by high velocity air, quartz lamp heating electrodes 1 just can give off on the surface that more hot-fluid arrives hyperthermia radiation testpieces 5 by promoting high supply voltage, has improved the ability of the pneumatic heat test device of guided missile high temperature radiant heat flux.For carry out flying speed faster the pneumatic hot thermal modeling test of hypersonic missile ground high temperature important research technique is provided.
In a word, infrared radiation heat flow density reinforcement device for high temperature pneumatic thermal simulating test of missile, by four transparent softening temperatures is that 1600 ℃ high temperature resistant quartz glass air-flow division board 4 is formed one-way gas flow guiding channel isolation, the motor 11 by blower fan 2 drive water conservancy diversion flabellums 12 at a high speed rotation form unidirectional air blast.In the pneumatic thermal shock test of high temperature transient state of simulated missile hypersonic flight, unidirectional air blast high velocity stream is crossed the surface of the quartz lamp heating electrodes 1 that is in the channel isolation, its surface temperature is reduced under the softening temperature of quartz lamp, utilize the transparent logical photosensitiveness of quartz glass air-flow division board 4 simultaneously, the intense radiation IR that quartz lamp heating electrodes 1 is sent can shine directly on the hyperthermia radiation testpieces 5 by transparent quartz glass air-flow division board 4.Because the obstruct of quartz glass air-flow division board 4, the surface that high velocity air can not be diffused into hyperthermia radiation testpieces 5 exerts an influence to it.The utility model makes the radianting capacity of quartz lamp heating electrodes 1 surpass original operating limit, can give off the bigger IR of heat flow density, the radiant heat flux density that the surface 5 of hyperthermia radiation testpieces receives when the high-speed aircraft thermal strength test has surpassed the restriction of not carrying out when air-cooled of the highest 1Mw/m2, and transient heat flow density can reach 2Mw/m2.For developmental flight speed faster hypersonic missile effective dynamic high temperature research technique is provided.Has important military engineering using value.
The utility model does not elaborate part and belongs to techniques well known.
Claims (6)
1. infrared radiation heat flow density reinforcement device for high temperature pneumatic thermal simulating test of missile is characterized in that comprising: quartz lamp heating electrodes (1), blower fan (2), variable-frequency governor (3), quartz glass air-flow division board (4), hyperthermia radiation testpieces (5), adiabatic framework (6), water-cooled case (7), heat flow transducer (8), temperature sensor (9) and computer (10); Described quartz lamp heating electrodes (1) is positioned at by four transparent quartz glass air-flow division boards (4) forms one-way gas flow guiding channel isolation; In the both sides of quartz glass air-flow division board (4) water-cooled case (7) is installed, is welded with paired cooling-water duct (13) on the water-cooled case (7), water-cooled case (7) and cooling-water duct (13) form the cooling water peripheral passage of flowing; Adiabatic framework (6) is installed around the hyperthermia radiation testpieces (5); Near the hyperthermia radiation testpieces (5) heat flow transducer (8) is installed, the heating surface of the front end of heat flow transducer (8) and hyperthermia radiation testpieces (5) is on the same vertical plane; Temperature sensor (9) is installed on the rear surface of hyperthermia radiation testpieces (5), heat flow transducer (8) is connected with computer (10) by lead with temperature sensor (9), and two sensors are sent into computer (10) after gathering the temperature data of radiant heat flux in the pneumatic thermal modeling test process of guided missile high temperature and reflection hyperthermia radiation testpieces (5) back side effect of heat insulation; Blower fan (2) is positioned at the lower end of quartz lamp heating electrodes (1), and is installed on the support (15) that is connected with ground.
2. guided missile High Temperature Gas dynamic simulated heat test infra-red radiation heat flow density intensifier according to claim 1, it is characterized in that: described device has also been installed variable-frequency governor (3), and described variable-frequency governor (3) carries out stepless time adjustment to the motor (11) of blower fan (2).
3. guided missile High Temperature Gas dynamic simulated heat test infra-red radiation heat flow density intensifier according to claim 1, it is characterized in that: described quartz lamp heating electrodes (1) is double quartz lamp heating electrodes, two row's quartz lamp heating electrodes (1) are staggered to be settled, and the infra-red radiation light that next row's quartz lamp heating electrodes (1) is sent just in time passes between the slit of front one row's quartz lamp heating electrodes (1).
4. guided missile High Temperature Gas dynamic simulated heat test infra-red radiation heat flow density intensifier according to claim 1 is characterized in that: the surperficial painted black of described hyperthermia radiation testpieces (5).
5. guided missile High Temperature Gas dynamic simulated heat test infra-red radiation heat flow density intensifier according to claim 1, it is characterized in that: described blower fan (2) is installed on the U type support (15) that is connected with ground, there is the above distance of 50cm on the lower surface of blower fan (2) and ground, and type becomes open space environment.
6. guided missile High Temperature Gas dynamic simulated heat test infra-red radiation heat flow density intensifier according to claim 1, it is characterized in that: water-cooled case (7) surface of the relative side of described hyperthermia radiation testpieces (5) is polished into mirror reflection surface (14), quartz lamp heating electrodes (1) is reflexed to the front surface of hyperthermia radiation testpieces (5) to the IR of the other side radiation of hyperthermia radiation testpieces (5).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201020221452XU CN201672853U (en) | 2010-06-02 | 2010-06-02 | Infrared radiation hot-fluid density reinforcing means used in missile high temperature pneumatic heat simulation test |
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| CN201020221452XU CN201672853U (en) | 2010-06-02 | 2010-06-02 | Infrared radiation hot-fluid density reinforcing means used in missile high temperature pneumatic heat simulation test |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101907422A (en) * | 2010-06-02 | 2010-12-08 | 北京航空航天大学 | Infrared radiation heat flow density reinforcement device for high temperature pneumatic thermal simulating test of missile |
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2010
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101907422A (en) * | 2010-06-02 | 2010-12-08 | 北京航空航天大学 | Infrared radiation heat flow density reinforcement device for high temperature pneumatic thermal simulating test of missile |
| CN101907422B (en) * | 2010-06-02 | 2012-09-26 | 北京航空航天大学 | Infrared radiation heat flow density reinforcement device for high temperature pneumatic thermal simulating test of missile |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20101215 Termination date: 20110602 |