CN202693430U - High temperature distributed load heat strength test device for plane structure of high-speed missile aircraft - Google Patents
High temperature distributed load heat strength test device for plane structure of high-speed missile aircraft Download PDFInfo
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- CN202693430U CN202693430U CN 201220320152 CN201220320152U CN202693430U CN 202693430 U CN202693430 U CN 202693430U CN 201220320152 CN201220320152 CN 201220320152 CN 201220320152 U CN201220320152 U CN 201220320152U CN 202693430 U CN202693430 U CN 202693430U
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Abstract
A high temperature distributed load heat strength test device for a plane structure of a high-speed missile aircraft comprises a plane high temperature heating body, a high-speed missile plane testing piece, a high temperature resistance insulation lamina, a temperature thermocouple, a computer, a water sac loader, flexible thermal insulation materials, a steel stress application flat plate, a hydraulic actuator, a loading link rod, a ceramic framework and a force sensor. The plane high temperature heating body can create a thermal environment of thousands of DEG C to conduct flexible thermal insulation between the water sac loader generating distributed loads and a heat source. The high temperature distributed load heat strength test device for the plane structure of the high-speed missile aircraft can create the thermal environment of higher than 1,000 DEG C, exerts uniform high temperature distributed loads on the plane structure of a high-speed missile, provides a high temperature distributed load test method which is more approximate to an actual stress state for a safety design of a high-speed missile structure, and has significant military engineering application value.
Description
Technical field
The utility model 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 produce up to the high thermal environment more than 1000 ℃ in the guided missile planar structure, apply simultaneously distributed load.Provide a kind of effective high temperature-distributed load Combined Trials means for developing hypersonic missile and high speed aerospace flight vehicle.
Background technology
Because the design flying speed of the aircraft such as guided missile is more and more faster, aircraft surface is also more and more higher by the temperature that Aerodynamic Heating produces.Under exceedingly odious high thermal environment condition, the hot strength problem of high-speed aircraft material and structure becomes the key issue concerning the 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 the 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 affirmation 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 truly being heated when high-speed flight, the variation of the high temperature mechanical property parameters such as the thermal stress of aircraft each several part, thermal deformation, structure swell increment is on the impact of Vehicle Structure Strength in the analytical test process.Method by the thermal environment simulation test, come the mechanical property of observation analysis material under thermal environment and mechanical environment compound action and the force-bearing situation of structure, 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 that is subject to during flight is the 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, can cause at high temperature that rubber bodies is broken to make, become liquid to reveal, therefore, the hot environment Imitating distributed load at hundreds of degree even thousands of degree is a difficult problem.
Design flying speed owing to hypersonic cruise missile has reached the 6-10 Mach number at present, even faster development trend is arranged, and this is so that the temperature of aircraft surface is more and more higher.The urgent hope of Missile Design department can create 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.
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 high-speed missile aircraft planar structure high temperature-distributed load thermal strength test device is provided, this device can make surpassing under 1000 ℃ the high thermal environment, and the heat distribution load of high-speed missile planar structure is carried out test simulation.
Technical solution of the present utility model is: high-speed missile aircraft planar structure high temperature-distributed load thermal strength test device comprises: 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, are loaded link rod and power sensor; Lay metal flat high temperature heater at described base of ceramic, high-speed missile plane testpieces is pressed on the planar high temperature heater, the planar high temperature heater all be covered with up and down the 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 the temperature by computer control high-speed missile plane testpieces downside, the water pocket loader is pressed on the testpieces of high-speed missile plane, 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 the 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 uniform distributed load, hydraulic pressure is done the device below strong sensor is installed, and is applied to the size of the pressure on the testpieces of high-speed missile plane by computer measurement and control.
Described planar high temperature heater becomes Ping Mian rotation curved shape by iron, chromium or aluminum metal thin slice (the about 1.5-2mm of the thickness of sheet metal) by electrosparking, can produce the high temperature more than 1000 ℃ after the energising, gives the lower surface heating of high-speed missile plane testpieces.
Described high-temperature insulation thin layer adopt can anti-1400 ℃ of high temperature flexible quartz fibre cloth, its thickness is 2mm.Can make the planar high temperature heater of conduction and the isolation between the temperature thermocouple formation strong, weak electricity, the weak electric signal of protection temperature thermocouple and the safety of computing machine.
Described water pocket loader is made by Viton that can anti-450 ℃ of high temperature, and inside is filled with pure water, when the water pocket loader is subject to downward power load, can form the even distributed force load with the object conformal.
Described flexible insulant material is can anti-1400 ℃ of flexible ceramic fibers, the heat conduction velocity that makes progress in order to reduce high-speed missile plane testpieces.
Four borders of described water pocket loader are equipped with ceramic frame, in order to limit the water pocket loader to the expansion of horizontal direction.
Principle of the present utility model: along with the design flying speed of the aerospace flight vehicles such as guided missile is more and more faster, aircraft surface is also more and more higher by the temperature that Aerodynamic Heating produces.In order to simulate the high temperature-distributed load of high-speed missile aircraft planar structure, designed the thermal environment that the planar high temperature heater generates thousands of degree, the planar high temperature heater can with high-speed missile plane testpieces close contact, the flexible thermal isolation will be carried out simultaneously between water pocket loader and the thermal source, to realize under greater than 1000 ℃ high thermal environment, the high-speed missile planar structure is applied uniform high temperature distributed load, for the safe design of high-speed missile provides more hot test means near actual forced status.
The utility model beneficial effect compared with prior art is:
(1) prior art adopts the water pocket loader to apply the even distributed force load of conformal to object when carrying out missile flight device planar structure distributed load strength test.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 utility model adopts flexible insulant material to be placed between high-speed missile plane testpieces and the water pocket loader when the high temperature heat test of carrying out thousands of degree, lowers the speed that heat is transmitted, and assurance water pocket loader can be worked under safe temperature.
(2) the water pocket loader use can anti-450 ℃ of high temperature Viton make, improved water pocket loader safe reliability at high temperature.
(3) the planar high temperature heater is engraved as flat shape shown in Figure 2 by the iron-chromium-aluminum metal thin slice by electric spark, can produce the high temperature more than 1000 ℃ after the energising, gives the lower surface heating of high-speed missile plane testpieces.
(4) the up and down both sides of metal flat high temperature heater; all be covered with and be operated in 1400 ℃ of flexible high-temperature resistant heat insulating laminas under the hot environment; to the metal flat high temperature heater of conduction and the isolation between the temperature thermocouple formation strong, weak electricity, protected the security of weak electric signal and the computing machine of temperature thermocouple.
(5) the utility model apparatus structure is succinct, and is easy to use, and checking with safe design for the high temperature hot strength of high-speed missile provides effective research technique.Has important military engineering using value.
Description of drawings
Fig. 1 is structure front elevational schematic of the present utility model;
Fig. 2 is planar high temperature heater schematic diagram of the present utility model.
Embodiment
As depicted in figs. 1 and 2, the utility model is done 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 is formed.Lay planar high temperature heater 2 on the base of ceramic 1, high-speed missile plane testpieces 3 is pressed on the planar high temperature heater 2, planar high temperature heater 2 upper, the below all is covered with high-temperature insulation thin layer 4, temperature thermocouple 5 is placed on high-speed missile plane testpieces 3 downsides, temperature thermocouple 5 is connected with computing machine 6, measure and control by computing machine 6 temperature of high-speed missile plane testpieces 3 downsides, water pocket loader 7 is pressed on the 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 the afterburning flat board 9 of link rod 11 and steel, apply uniform distributed load by water pocket loader 7 and 8 pairs of high-speed missile planes of flexible insulant material testpieces 3, four borders of water pocket loader 7 are equipped with ceramic frame 12, hydraulic pressure is done device 10 belows strong sensor 13 is installed, and measures and control the size that is applied to the pressure on the high-speed missile plane testpieces 3 by computing machine 6.
The utility model midplane high temperature heater 2 becomes flat shape shown in Figure 2 by iron, chromium or aluminum metal thin slice (the about 1.5-2mm of the thickness of sheet metal) by electrosparking, can produce the high temperature more than 1000 ℃ after the energising, give 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 utility model high-temperature insulation thin layer 4 adopt can anti-1400 ℃ of high temperature flexible quartz fibre cloth, its thickness is 2mm.Can make the planar high temperature heater 2 of conduction form the electricity isolation with temperature thermocouple 5, guarantee the weak electric signal of temperature thermocouple 5 and the safety of computing machine 6.
Flexible insulant material 8 is can anti-1400 ℃ of flexible ceramic fibers in the utility model, the heat conduction velocity that makes progress in order to reduce high-speed missile plane testpieces 3.
Four of water pocket loader 7 borders are equipped with ceramic frame 12 in the utility model, in order to limit water pocket loader 7 to the expansion of horizontal direction.
The utility model 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 under greater than 1000 ℃ high thermal environment, the Re of plane institution movement-Li Combined Trials is carried out in the uniform high temperature distributed load of applying of high-speed missile planar structure, for the safe design of high-speed missile provides more high temperature load research technique near the guided missile actual forced status.This technology has important military engineering using value.
The utility model does not elaborate part and 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: made device (10), loaded link rod (11) and power sensor (13) by 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; Lay planar high temperature heater (2) on the described base of ceramic (1), high-speed missile plane testpieces (3) is pressed on the planar high temperature heater (2), planar high temperature heater (2) upper, the below all is covered with high-temperature insulation thin layer (4), temperature thermocouple (5) is placed on high-speed missile plane testpieces (3) downside, temperature thermocouple (5) is connected with computing machine (6), measure and control by computing machine (6) temperature of high-speed missile plane testpieces (3) downside, water pocket loader (7) is pressed on the 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 uniform distributed load, hydraulic pressure is done device (10) below strong sensor (13) is installed, power sensor (13) is connected with computing machine (6), is applied to the size of the pressure on the high-speed missile plane testpieces (3) by computing machine (6) measurement and control.
2. high-speed missile aircraft planar structure high temperature according to claim 1-distributed load thermal strength test device, it 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 according to claim 1-distributed load thermal strength test device is characterized in that: the flexible quartz fibre cloth of the anti-1400 ℃ of high temperature of described high-temperature insulation thin layer (4).
4. high-speed missile aircraft planar structure high temperature according to claim 1-distributed load thermal strength test device, it is characterized in that: described water pocket loader (7) is made by the Viton of anti-450 ℃ of high temperature, and inside is filled with pure water.
5. high-speed missile aircraft planar structure high temperature according to claim 1-distributed load thermal strength test device, it is characterized in that: described flexible insulant material (8) is anti-1400 ℃ of flexible ceramic fibers.
6. high-speed missile aircraft planar structure high temperature according to claim 1-distributed load thermal strength test device, it is characterized in that: four borders of described water pocket loader (7) are equipped with ceramic frame (12).
7. high-speed missile aircraft planar structure high temperature according to claim 1-distributed load thermal strength test device, it 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 according to claim 2-distributed load thermal strength test device, it is characterized in that: described sheet metal is iron, chromium or aluminium.
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| CN 201220320152 CN202693430U (en) | 2012-07-03 | 2012-07-03 | High temperature distributed load heat strength test device for plane structure of high-speed missile aircraft |
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| CN 201220320152 CN202693430U (en) | 2012-07-03 | 2012-07-03 | High temperature distributed load heat strength test device for plane structure of high-speed missile aircraft |
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|---|---|---|---|---|
| CN102721612A (en) * | 2012-07-03 | 2012-10-10 | 北京航空航天大学 | High temperature-distributed load thermal strength test device for plane structure of high-speed missile aerobat |
| CN104569046A (en) * | 2015-01-15 | 2015-04-29 | 中国建筑材料科学研究总院 | Ultra-high temperature heat-insulating property testing device and method |
| RU2583353C1 (en) * | 2015-02-24 | 2016-05-10 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Method for thermal loading of rocket cowls made of nonmetals |
| RU172094U1 (en) * | 2017-03-31 | 2017-06-28 | Федеральное государственное бюджетное учреждение науки Объединённый институт высоких температур Российской академии наук (ОИВТ РАН) | DEVICE FOR MODELING NON-STATIONARY TEMPERATURE FIELD IN ELEMENTS OF STRUCTURES OF ROCKET TECHNOLOGY UNDER THE INFLUENCE OF POWERFUL HEAT FLOWS |
| RU172098U1 (en) * | 2016-12-26 | 2017-06-28 | Федеральное государственное бюджетное учреждение науки Объединённый институт высоких температур Российской академии наук (ОИВТ РАН) | DEVICE FOR MODELING NON-STATIONARY TEMPERATURE FIELD IN ELEMENTS OF STRUCTURES OF ROCKET TECHNOLOGY UNDER THE INFLUENCE OF POWERFUL HEAT FLOWS |
| RU2637176C1 (en) * | 2017-02-27 | 2017-11-30 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Method of test of rocket fairings of nonmetallic materials |
| RU2670725C1 (en) * | 2017-12-06 | 2018-10-24 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Method of thermal loading of fairings of flying apparatuses made of nonmetals |
| CN108918582A (en) * | 2018-07-05 | 2018-11-30 | 北京强度环境研究所 | A kind of hot external pressure test system and method for aircraft cargo tank structure |
| RU2686528C1 (en) * | 2018-04-02 | 2019-04-29 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Method of thermal loading of non-metallic elements of aircraft structures |
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| RU2758414C1 (en) * | 2020-12-10 | 2021-10-28 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Московский авиационный институт (национальный исследовательский университет)" | Apparatus for determining complex of thermophysical characteristics of composite materials |
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-
2012
- 2012-07-03 CN CN 201220320152 patent/CN202693430U/en not_active Withdrawn - After Issue
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| CN102721612A (en) * | 2012-07-03 | 2012-10-10 | 北京航空航天大学 | High temperature-distributed load thermal strength test device for plane structure of high-speed missile aerobat |
| CN102721612B (en) * | 2012-07-03 | 2014-01-29 | 北京航空航天大学 | High temperature-distributed load thermal strength test device for plane structure of high-speed missile aerobat |
| CN104569046A (en) * | 2015-01-15 | 2015-04-29 | 中国建筑材料科学研究总院 | Ultra-high temperature heat-insulating property testing device and method |
| CN104569046B (en) * | 2015-01-15 | 2017-07-14 | 中国建筑材料科学研究总院 | Superhigh temperature Heat-Insulation Test device and test method |
| RU2583353C1 (en) * | 2015-02-24 | 2016-05-10 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Method for thermal loading of rocket cowls made of nonmetals |
| RU172098U1 (en) * | 2016-12-26 | 2017-06-28 | Федеральное государственное бюджетное учреждение науки Объединённый институт высоких температур Российской академии наук (ОИВТ РАН) | DEVICE FOR MODELING NON-STATIONARY TEMPERATURE FIELD IN ELEMENTS OF STRUCTURES OF ROCKET TECHNOLOGY UNDER THE INFLUENCE OF POWERFUL HEAT FLOWS |
| RU2637176C1 (en) * | 2017-02-27 | 2017-11-30 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Method of test of rocket fairings of nonmetallic materials |
| RU172094U1 (en) * | 2017-03-31 | 2017-06-28 | Федеральное государственное бюджетное учреждение науки Объединённый институт высоких температур Российской академии наук (ОИВТ РАН) | DEVICE FOR MODELING NON-STATIONARY TEMPERATURE FIELD IN ELEMENTS OF STRUCTURES OF ROCKET TECHNOLOGY UNDER THE INFLUENCE OF POWERFUL HEAT FLOWS |
| RU2670725C1 (en) * | 2017-12-06 | 2018-10-24 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Method of thermal loading of fairings of flying apparatuses made of nonmetals |
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| CN108918582A (en) * | 2018-07-05 | 2018-11-30 | 北京强度环境研究所 | A kind of hot external pressure test system and method for aircraft cargo tank structure |
| CN110411769A (en) * | 2019-07-19 | 2019-11-05 | 北京空天技术研究所 | A kind of hot certification test device of structure adjusted with pretightning force |
| CN110411769B (en) * | 2019-07-19 | 2020-12-04 | 北京空天技术研究所 | Structural thermal examination test device with pretightening force adjustment function |
| RU2758414C1 (en) * | 2020-12-10 | 2021-10-28 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Московский авиационный институт (национальный исследовательский университет)" | Apparatus for determining complex of thermophysical characteristics of composite materials |
| RU2758414C9 (en) * | 2020-12-10 | 2022-02-03 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Московский авиационный институт (национальный исследовательский университет)" | Apparatus for determining complex of thermophysical characteristics of composite materials |
| RU2786793C1 (en) * | 2021-12-09 | 2022-12-26 | Акционерное общество "Научно-производственная корпорация " Уралвагонзавод" имени Ф.Э. Дзержинского" | Method for determining and evaluating the thermal strength of core or molding sands and a complex for its implementation |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20130123 Effective date of abandoning: 20140129 |
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| RGAV | Abandon patent right to avoid regrant |