CN102721612B - High temperature-distributed load thermal strength test device for plane structure of high-speed missile aerobat - Google Patents
High temperature-distributed load thermal strength test device for plane structure of high-speed missile aerobat Download PDFInfo
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- CN102721612B CN102721612B CN201210228870.5A CN201210228870A CN102721612B CN 102721612 B CN102721612 B CN 102721612B CN 201210228870 A CN201210228870 A CN 201210228870A CN 102721612 B CN102721612 B CN 102721612B
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Abstract
The invention discloses a high temperature-distributed load thermal strength test device for a plane structure of a high-speed missile aerobat, which comprises a plane high-temperature heating unit, a high-speed missile plane test piece, a thermostability insulation thin layer, a temperature thermocouple, a computer, a water sac loader, flexible heat insulation materials, a steel stressing plate, a hydraulic pressure actuator, a loading link rod, a ceramic frame and a force transducer, a thermal environment with a temperature above 1,000 DEG C is generated by the plane high-temperature heating unit, and a flexible heat separation is carried out between the water sac loader which can generate distributed load and a heat source. According to the thermal strength test device, uniform high-temperature distributed load is implemented to the plane structure of the high-speed missile in the thermal environment with a temperature above 1,000 DEG C, and a high temperature load test method closer to the actual stressing state is provided for a safe design of the high-speed missile structure. The device has important application values on military engineering.
Description
Technical field
The present invention relates to high-speed missile aircraft planar structure high temperature-distributed load thermal strength test device.Particularly, when simulated missile hypersonic flight thermal environment, can in guided missile planar structure, produce up to more than 1000 ℃ high thermal environments, apply distributed load simultaneously.For developing hypersonic missile and high speed aerospace flight vehicle, provide a kind of effective high temperature-distributed load Combined Trials means.
Background technology
Because the design flying speed of the aircraft such as guided missile is more and more faster, the temperature that aircraft surface is produced by Aerodynamic Heating is also more and more higher.Under exceedingly odious high thermal environment condition, the hot strength problem of high-speed aircraft material and structure becomes the key issue concerning development success or failure.This is because the high temperature that serious Aerodynamic Heating produces during high-speed flight, can significantly reduce the strength degree of hypersonic aircraft material and the load-bearing capacity of Flight Vehicle Structure, make structure generation thermal deformation, destroy the aerodynamic configuration of parts and affect the security performance of Flight Vehicle Structure.For guaranteeing the safety of high-speed aircraft, thermal shock and high temperature thermal stress damage that the material of confirmation aircraft and structure produce in the time of whether standing high-speed flight, must carry out quiet, dynamic pneumatic analog test and thermal strength test to hypersonic aircraft material and structure.Simulated flight material and the structure situation of being truly heated when high-speed flight, the impact of the variation of the high temperature mechanical property parameters such as the thermal stress of aircraft each several part, thermal deformation, structure swell increment on Vehicle Structure Strength in analytical test process.The method of testing by thermal environment simulation, come the observation analysis mechanical property of material and force-bearing situation of structure under thermal environment and mechanical environment compound action, thereby further research and analyse structure load-bearing capacity, serviceable life and safe reliability at high temperature, this work has very important practical significance for thermal protection and the safe design of missile flight device.
The parts such as the missile wing of high-speed missile aircraft, rudder face are generally planar structure, and the aerodynamic loading being subject to during flight is face distributed load.Can utilize at normal temperatures the distributed load of rubber bag with water Simulation Study On Pressure, but because the heatproof of rubber bag with water is limited, at high temperature can cause that rubber bodies is broken to make, become liquid to reveal, therefore, the hot environment Imitating distributed load at the even thousands of degree of hundreds of degree is a difficult problem.
Design flying speed due to hypersonic cruise missile has reached 6-10 Mach number at present, even has development trend faster, and this makes the temperature of aircraft surface more and more higher.The urgent hope of Missile Design department can be invented a kind of planar structure high temperature-distributed load Combined Trials method that surpasses 1000 ℃, for the safe flight of high-speed missile provides effective test design foundation.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, a kind of high-speed missile aircraft planar structure high temperature-distributed load thermal strength test device is provided, this device can make, surpassing under the high thermal environment of 1000 ℃, the heat distribution load of high-speed missile planar structure to be carried out to test simulation.
Technical solution of the present invention is: high-speed missile aircraft planar structure high temperature-distributed load thermal strength test device, comprising: base of ceramic, planar high temperature heater, high-speed missile plane testpieces, high-temperature insulation thin layer, temperature thermocouple, computing machine, water pocket loader, flexible insulant material, the afterburning flat board of steel, hydraulic pressure are made device, loaded link rod, power sensor, on described base of ceramic, lay metal flat high temperature fever tablet, high-speed missile plane testpieces is pressed on planar high temperature heater, planar high temperature heater be all covered with up and down high-temperature insulation thin layer, temperature thermocouple is placed on high-speed missile plane testpieces downside, temperature thermocouple is connected with computing machine, measure and by the temperature of computer control high-speed missile plane testpieces downside, water pocket loader is pressed on high-speed missile plane testpieces, between high-speed missile plane testpieces and water pocket loader, lay flexible insulant material, the top of water pocket loader has a steel afterburning dull and stereotyped, hydraulic pressure is made device and is exerted pressure to water pocket loader by loading the afterburning flat board of link rod and steel, by water pocket loader and flexible insulant material, high-speed missile plane testpieces is applied to uniform distributed load, hydraulic pressure is done device below strong sensor is installed, by computer measurement and control, be applied to the size of the pressure on high-speed missile plane testpieces.
Described planar high temperature heater becomes the Ping Mian rotation curved shape shown in Fig. 2 by iron, chromium or aluminum metal thin slice (the about 1.5-2mm of thickness of sheet metal) by electrosparking, after energising, can produce 1000 ℃ of above high temperature, give the lower surface heating of high-speed missile plane testpieces.
Described high-temperature insulation thin layer adopts flexible quartz fibre cloth that can resistance to 1400 ℃ of high temperature, and its thickness is 2mm.Can make planar high temperature heater and the temperature thermocouple of conduction form the isolation between strong, weak electricity, the protection weak electric signal of temperature thermocouple and the safety of computing machine.
Described water pocket loader is made by Viton that can resistance to 450 ℃ of high temperature, and inside is filled with pure water, when water pocket loader is subject to downward power load, can form the power that the is uniformly distributed load with object conformal.
Described flexible insulant material is can resistance to 1400 ℃ of flexible ceramic fibers, the heat conduction velocity making progress in order to reduce high-speed missile plane testpieces.
Four borders of described water pocket loader are provided with ceramic frame, in order to limit water pocket loader to the expansion of horizontal direction.
Principle of the present invention: along with the design flying speed of the aerospace flight vehicles such as guided missile is more and more faster, the temperature that aircraft surface is produced by Aerodynamic Heating is also more and more higher.In order to simulate the high temperature-distributed load of high-speed missile aircraft planar structure, designed the thermal environment that planar high temperature heater generates thousands of degree, planar high temperature heater can with high-speed missile plane testpieces close contact, flexible thermal isolation will be carried out between water pocket loader and thermal source simultaneously, to realize, be greater than under the high thermal environment of 1000 ℃, high-speed missile planar structure is applied to uniform high temperature distributed load, for the safe design of high-speed missile provides the hot test means that more approach actual forced status.
The present invention's beneficial effect is compared with prior art:
(1) prior art, when carrying out missile flight device planar structure distributed load strength test, adopts water pocket loader to object, to apply the power that the is uniformly distributed load of conformal.But under the thermal extremes environment of thousands of degree, the flexible water pocket loader of being made by rubber can damage by Yin Gaowen, causes leak of liquid, causes test failure.The present invention, when the high temperature heat test of carrying out thousands of degree, adopts flexible insulant material to be placed between high-speed missile plane testpieces and water pocket loader, subtracts the speed of low heat transfer, and assurance water pocket loader can be worked under safe temperature.
(2) water pocket loader uses Viton that can resistance to 450 ℃ of high temperature to make, and has improved water pocket loader safe reliability at high temperature.
(3) planar high temperature heater is engraved as the flat shape shown in Fig. 2 by iron-chromium-aluminum metal thin slice by electric spark, can produce 1000 ℃ of above high temperature after energising, gives the lower surface heating of high-speed missile plane testpieces.
(4) both sides up and down of metal flat high temperature heater; all be covered with and can be operated in 1400 ℃ of flexible high-temperature resistant heat insulating laminas under hot environment; the metal flat high temperature heater of conduction and temperature thermocouple are formed to the isolation between strong, weak electricity, protected the security of weak electric signal and the computing machine of temperature thermocouple.
(5) apparatus of the present invention are simple for structure, easy to use, for the high temperature hot strength of high-speed missile, check with safe design effective research technique is provided.There is important military engineering using value.
Accompanying drawing explanation
Fig. 1 is structure front elevational schematic of the present invention;
Fig. 2 is planar high temperature heater schematic diagram of the present invention.
Embodiment
As depicted in figs. 1 and 2, the present invention does device 10, loading link rod 11, ceramic frame 12, power sensor 13 by afterburning dull and stereotyped 9, the hydraulic pressure of base of ceramic 1, planar high temperature heater 2, high-speed missile plane testpieces 3, high-temperature insulation thin layer 4, temperature thermocouple 5, computing machine 6, water pocket loader 7, flexible insulant material 8, steel and forms.On base of ceramic 1, lay planar high temperature fever tablet 2, high-speed missile plane testpieces 3 is pressed on planar high temperature heater 2, planar high temperature heater 2 upper, all be covered with high-temperature insulation thin layer 4 below, temperature thermocouple 5 is placed on high-speed missile plane testpieces 3 downsides, temperature thermocouple 5 is connected with computing machine 6, measure and pass through the temperature of computing machine 6 control high-speed missile plane testpieces 3 downsides, water pocket loader 7 is pressed on high-speed missile plane testpieces 3, between high-speed missile plane testpieces 3 and water pocket loader 7, lay flexible insulant material 8, a steel afterburning dull and stereotyped 9 is arranged at the top of water pocket loader 7, hydraulic pressure is made device 10 and is exerted pressure to water pocket loader 7 by loading link rod 11 and steel afterburning dull and stereotyped 9, by water pocket loader 7 and 8 pairs of high-speed missile plane testpieces 3 of flexible insulant material, apply uniform distributed load, four borders of water pocket loader 7 are provided with ceramic frame 12, hydraulic pressure is done device 10 belows strong sensor 13 is installed, by computing machine 6, measure and control the size that is applied to the pressure on high-speed missile plane testpieces 3.
Midplane high temperature heater 2 of the present invention becomes the flat shape shown in Fig. 2 by iron, chromium or aluminum metal thin slice by electrosparking, can produce 1000 ℃ of above high temperature after energising, gives the lower surface heating of high-speed missile plane testpieces 3.The thickness of planar high temperature heater 2 is 1.5-2mm.
In the present invention, high-temperature insulation thin layer 4 adopts flexible quartz fibre cloth that can resistance to 1400 ℃ of high temperature, and its thickness is 2mm.Can make the planar high temperature heater 2 of conduction form electricity isolation with temperature thermocouple 5, guarantee the weak electric signal of temperature thermocouple 5 and the safety of computing machine 6.
In the present invention, water pocket loader 7 is made by Viton that can resistance to 450 ℃ of high temperature, and inside is filled with pure water, when water pocket loader 7 is subject to downward power load, can form the power that the is uniformly distributed load with object conformal.
In the present invention, flexible insulant material 8 is can resistance to 1400 ℃ of flexible ceramic fibers, the heat conduction velocity making progress in order to reduce high-speed missile plane testpieces 3.
In the present invention, four of water pocket loader 7 borders are provided with ceramic frame 12, in order to limit water pocket loader 7 to the expansion of horizontal direction.
The present invention has overcome the shortcoming of the approximate test method that in the past can only take the loading of multiple spot concentrated force under 1000 ℃ of high temperature, can realize and being greater than under the high thermal environment of 1000 ℃, the uniform high temperature distributed load of applying of high-speed missile planar structure is carried out to Re-Li Combined Trials of plane institution movement, for the safe design of high-speed missile provides the high temperature load research technique that more approaches guided missile actual forced status.This technology has important military engineering using value.
Non-elaborated part of the present invention belongs to techniques well known.
Claims (8)
1. high-speed missile aircraft planar structure high temperature-distributed load thermal strength test device, is characterized in that comprising: base of ceramic (1), planar high temperature heater (2), high-speed missile plane testpieces (3), high-temperature insulation thin layer (4), temperature thermocouple (5), computing machine (6), water pocket loader (7), flexible insulant material (8), steel afterburning dull and stereotyped (9), hydraulic pressure are made device (10), loaded link rod (11), power sensor (13), on described base of ceramic (1), lay planar high temperature heater (2), high-speed missile plane testpieces (3) is pressed on planar high temperature heater (2), planar high temperature heater (2) upper, all be covered with high-temperature insulation thin layer (4) below, temperature thermocouple (5) is placed on high-speed missile plane testpieces (3) downside, temperature thermocouple (5) is connected with computing machine (6), measure and pass through the temperature of computing machine (6) control high-speed missile plane testpieces (3) downside, water pocket loader (7) is pressed on high-speed missile plane testpieces (3), between high-speed missile plane testpieces (3) and water pocket loader (7), lay flexible insulant material (8), a steel afterburning dull and stereotyped (9) is arranged at the top of water pocket loader (7), hydraulic pressure is made device (10) and is exerted pressure to water pocket loader (7) by loading link rod (11) and steel afterburning dull and stereotyped (9), by water pocket loader (7) and flexible insulant material (8), high-speed missile plane testpieces (3) is applied to uniform distributed load, hydraulic pressure is done device (10) below strong sensor (13) is installed, power sensor (13) is connected with computing machine (6), by computing machine (6) measurement and control, be applied to the size of the pressure on high-speed missile plane testpieces (3).
2. high-speed missile aircraft planar structure high temperature-distributed load thermal strength test device according to claim 1, is characterized in that: described planar high temperature heater (2) becomes Ping Mian rotation curved shape by sheet metal by electrosparking.
3. high-speed missile aircraft planar structure high temperature-distributed load thermal strength test device according to claim 1, is characterized in that: described high-temperature insulation thin layer (4) is the flexible quartz fibre cloth of resistance to 1400 ℃ of high temperature.
4. high-speed missile aircraft planar structure high temperature-distributed load thermal strength test device according to claim 1, is characterized in that: described water pocket loader (7) is made by the Viton of resistance to 450 ℃ of high temperature, and inside is filled with pure water.
5. high-speed missile aircraft planar structure high temperature-distributed load thermal strength test device according to claim 1, is characterized in that: described flexible insulant material (8) is resistance to 1400 ℃ of flexible ceramic fibers.
6. high-speed missile aircraft planar structure high temperature-distributed load thermal strength test device according to claim 1, it is characterized in that: four borders of described water pocket loader (7) are provided with ceramic frame (12), in order to limit water pocket loader (7) to the expansion of horizontal direction.
7. high-speed missile aircraft planar structure high temperature-distributed load thermal strength test device according to claim 1, is characterized in that: the thickness of described planar high temperature heater (2) is 1.5-2mm.
8. high-speed missile aircraft planar structure high temperature-distributed load thermal strength test device according to claim 2, is characterized in that: described sheet metal is iron, chromium or aluminium.
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