CN102721612A - 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
- Publication number
- CN102721612A CN102721612A CN2012102288705A CN201210228870A CN102721612A CN 102721612 A CN102721612 A CN 102721612A CN 2012102288705 A CN2012102288705 A CN 2012102288705A CN 201210228870 A CN201210228870 A CN 201210228870A CN 102721612 A CN102721612 A CN 102721612A
- Authority
- CN
- China
- Prior art keywords
- high temperature
- speed missile
- temperature
- distributed load
- plane
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
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 the hypersonic flight thermal environment of simulated missile, can apply distributed load simultaneously producing up to the elevated temperature heat environment more than 1000 ℃ on the guided missile planar structure.For developing hypersonic guided missile and high speed aerospace flight vehicle a kind of effective high temperature-distributed load Combined Trials means are provided.
Background technology
Because the design flying speed of aircraft such as guided missile is more and more faster, aircraft surface is also increasingly high by the temperature that pneumatic heating produces.Under exceedingly odious elevated temperature heat environmental baseline, the hot strength problem of high-speed flight modulator material and structure becomes the key issue concerning the development success or failure.This is because the serious high temperature that pneumatic heating produced 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 produce thermal deformation, destroy the aerodynamic configuration of parts and influence the security performance of Flight Vehicle Structure.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 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 mechanical behavior under high temperature parameters such as the thermal stress of aircraft each several part, thermal deformation, structure swell increment is to the influence of Flight Vehicle Structure intensity in the analytical test process.Method through 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 the thermal protection and the Safety Design of missile flight device.
Parts such as the missile wing of high-speed missile aircraft, rudder face are generally planar structure, and the aerodynamic loading that receives during flight is the face distributed load.Can utilize rubber bag with water pressurization simulation distribution load at normal temperatures; 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 simulation distributed load is a difficult problem under the hot environment of hundreds of degree even thousands of degree.
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 makes that the temperature of aircraft surface is increasingly high.The urgent hope of guided 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: the deficiency that overcomes 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 and surpass under 1000 ℃ the elevated temperature heat environment, to the simulation that makes an experiment of the heat distribution load of high-speed missile planar structure.
Technical solution of the present invention 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, force transducer; On said base of ceramic, lay metal flat high temperature heating sheet; High-speed missile plane testpieces is pressed on the planar high temperature heater; The planar high temperature heater all be covered with the high-temperature insulation thin layer up and down, temperature thermocouple is placed on high-speed missile plane testpieces downside, temperature thermocouple is connected with computing machine; Measure and the temperature through 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, lays flexible insulant material, and the top of water pocket loader has a steel afterburning dull and stereotyped; Hydraulic pressure is made device and is exerted pressure through loading the afterburning dull and stereotyped water pocket loader of giving of link rod and steel; Through water pocket loader and flexible insulant material high-speed missile plane testpieces is applied uniform distributed load, hydraulic pressure is done the device below force transducer is installed, and is applied to the size of the pressure on the testpieces of high-speed missile plane through computer measurement and control.
Said planar high temperature heater becomes Ping Mian rotation curved shape shown in Figure 2 by iron, chromium or aluminum metal thin slice (the about 1.5-2mm of the thickness of sheet metal) through electrosparking; Can produce the high temperature more than 1000 ℃ after the energising, give the lower surface heating of high-speed missile plane testpieces.
Said 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 and the temperature thermocouple of conduction form the isolation between the strong, weak electricity, the weak electric signal of protection temperature thermocouple and the safety of computing machine.
Said water pocket loader is processed by Viton that can anti-450 ℃ of high temperature, and inside is filled with pure water, when the water pocket loader receives downward power load, can form the even distributed force load with the object conformal.
Said flexible insulant material is can anti-1400 ℃ of flexible ceramic fibers, in order to reduce the heat conduction velocity that high-speed missile plane testpieces makes progress.
Four borders of said water pocket loader are equipped with ceramic frame, in order to the expansion of restriction water pocket loader to horizontal direction.
Principle of the present invention: along with the design flying speed of aerospace flight vehicles such as guided missile is more and more faster, aircraft surface is also increasingly high by the temperature that pneumatic 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 closely contact with high-speed missile plane testpieces; Isolate carrying out flexible thermal between water pocket loader and the thermal source simultaneously; To be implemented in, the high-speed missile planar structure is applied uniform high temperature distributed load, for the Safety Design of high-speed missile provides more the hot test means near actual forced status greater than under 1000 ℃ the elevated temperature heat environment.
The present invention's 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 processed by rubber can damage by Yin Gaowen, causes leak of liquid, causes test failure.When the present invention tests in the elevated temperature heat of carrying out thousands of degree, adopt flexible insulant material to be placed between high-speed missile plane testpieces and the water pocket loader, lower the speed that heat is transmitted, assurance water pocket loader can be worked under safe temperature.
(2) the water pocket loader use can anti-450 ℃ of high temperature Viton process, 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 through 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) both sides up and down of metal flat high temperature heater; All be covered with the flexible high-temperature insulation thin layer that can be operated under 1400 ℃ of hot environments; Metal flat high temperature heater and temperature thermocouple to conduction form the isolation between the strong, weak electricity, have protected the security of the weak electric signal and the computing machine of temperature thermocouple.
(5) apparatus of the present invention are simple for structure, and are easy to use, and checking with Safety Design for the high temperature hot strength of high-speed missile provides effective research technique.Having the important military practical applications is worth.
Description of drawings
Fig. 1 is a structure front elevational schematic of the present invention;
Fig. 2 is a planar high temperature heater synoptic 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, force transducer 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.Lay planar high temperature heating sheet 2 on the base of ceramic 1; High-speed missile plane testpieces 3 is pressed on the planar high temperature heater 2; The above and below of planar high temperature heater 2 all is covered with high-temperature insulation thin layer 4; Temperature thermocouple 5 is placed on high-speed missile plane testpieces 3 downsides, and temperature thermocouple 5 is connected with computing machine 6, measures and pass through the temperature of computing machine 6 control 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 reinforcing flat board 9 is arranged at the top of water pocket loader 7, and hydraulic pressure is made device 10 and exerted pressure to water pocket loader 7 with the afterburning flat board 9 of steel through loading link rod 11; Apply uniform distributed load through 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, and hydraulic pressure is done device 10 belows force transducer 13 is installed, and are applied to the size of the pressure on the high-speed missile plane testpieces 3 through computing machine 6 measurements and control.
Midplane high temperature heater 2 of the present invention becomes flat shape shown in Figure 2 by iron, chromium or aluminum metal thin slice through electrosparking, can produce the high temperature more than 1000 ℃ after the 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.
Among the present invention 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, guarantee the weak electric signal of temperature thermocouple 5 and the safety of computing machine 6 with temperature thermocouple 5.
Water pocket loader 7 is processed by Viton that can anti-450 ℃ of high temperature among the present invention, and inside is filled with pure water, when water pocket loader 7 receives downward power load, can form the even distributed force load with the object conformal.
Flexible insulant material 8 is can anti-1400 ℃ of flexible ceramic fibers among the present invention, in order to reduce the heat conduction velocity that high-speed missile plane testpieces 3 makes progress.
Four of water pocket loader 7 borders are equipped with ceramic frame 12 among the present invention, in order to the expansion of restriction water pocket loader 7 to horizontal direction.
The present invention has overcome the shortcoming of the approximate test method that in the past under 1000 ℃ of high temperature, can only take the loading of multiple spot concentrated force; Can be implemented in greater than under 1000 ℃ the elevated temperature heat environment; Re-Li the Combined Trials of plane institution movement is carried out in the uniform high temperature distributed load of applying of high-speed missile planar structure, for the Safety Design of high-speed missile provides more the high temperature load research technique near the guided missile actual forced status.This technology has the important military practical applications and is worth.
The present invention does not set forth part in detail 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), force transducer (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 said base of ceramic (1); High-speed missile plane testpieces (3) is pressed on the planar high temperature heater (2); The above and below of planar high temperature heater (2) 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 pass through the temperature of computing machine (6) control 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), lays 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 for water pocket loader (7) through loading link rod (11) and steel afterburning dull and stereotyped (9), through water pocket loader (7) and flexible insulant material (8) high-speed missile plane testpieces (3) is applied uniform distributed load, and hydraulic pressure is done device (10) below force transducer (13) is installed; Force transducer (13) is connected with computing machine (6), is applied to the size of the pressure on the high-speed missile plane testpieces (3) through 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 is characterized in that: said planar high temperature heater (2) becomes Ping Mian rotation curved shape by sheet metal through 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 said 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: said water pocket loader (7) is processed 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 is characterized in that: said 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 said water pocket loader (7) are equipped with ceramic frame (12), in order to the expansion of restriction water pocket loader (7) to horizontal direction.
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 said 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: said sheet metal is iron, chromium or aluminium.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210228870.5A CN102721612B (en) | 2012-07-03 | 2012-07-03 | High temperature-distributed load thermal strength test device for plane structure of high-speed missile aerobat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210228870.5A CN102721612B (en) | 2012-07-03 | 2012-07-03 | High temperature-distributed load thermal strength test device for plane structure of high-speed missile aerobat |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102721612A true CN102721612A (en) | 2012-10-10 |
| CN102721612B CN102721612B (en) | 2014-01-29 |
Family
ID=46947437
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210228870.5A Expired - Fee Related CN102721612B (en) | 2012-07-03 | 2012-07-03 | High temperature-distributed load thermal strength test device for plane structure of high-speed missile aerobat |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102721612B (en) |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103018096A (en) * | 2012-12-10 | 2013-04-03 | 中国飞机强度研究所 | Coordination applying device and method for transient uniform distribution of thermal and mechanical loads |
| RU2517790C1 (en) * | 2012-12-18 | 2014-05-27 | Открытое акционерное общество "Обнинское научно-производственное предприятие "Технология" | Application of heat stress to rocket cowls of nonmetals |
| CN103867712A (en) * | 2012-12-10 | 2014-06-18 | 中国飞机强度研究所 | Metal foil high temperature sealing method |
| CN104697862A (en) * | 2013-12-06 | 2015-06-10 | 中国飞机强度研究所 | Thermo-mechanical coupling loading method for thermal strength tests |
| CN104913918A (en) * | 2015-06-12 | 2015-09-16 | 中国人民解放军理工大学 | Pseudo-static test device |
| CN105241757A (en) * | 2015-09-18 | 2016-01-13 | 中国科学院武汉岩土力学研究所 | Uniform load mechanism, three dimensional slope model test load apparatus and three dimensional slope model test load method |
| RU2677487C1 (en) * | 2018-02-02 | 2019-01-17 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Method for heat loading of rocket fairings made of nonmetals |
| CN109613052A (en) * | 2018-11-12 | 2019-04-12 | 南京航空航天大学 | A kind of hot loading device of structural test |
| RU2696939C1 (en) * | 2018-09-20 | 2019-08-07 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Method for thermal loading of rocket fairings |
| RU2697410C1 (en) * | 2018-10-01 | 2019-08-14 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Ceramic shells testing method |
| CN110261232A (en) * | 2019-06-26 | 2019-09-20 | 哈尔滨工程大学 | Composite material flat plate mechanical mechanics property test device peculiar to vessel |
| CN110525686A (en) * | 2019-09-18 | 2019-12-03 | 西北工业大学 | The experimental rig of aerothermodynamic Combined Trials |
| CN111103199A (en) * | 2019-11-29 | 2020-05-05 | 南京航空航天大学 | High-temperature flexible loading device |
| RU2720738C1 (en) * | 2019-09-12 | 2020-05-13 | Акционерное общество «Обнинское научно-производственное предприятие «Технология» им. А.Г.Ромашина» | Method of controlling heating during thermal testing of ceramic fairings |
| CN112461678A (en) * | 2020-11-23 | 2021-03-09 | 北京空间机电研究所 | Spacecraft thin-wall structure thermal strength test device and test method |
| CN112730091A (en) * | 2020-12-23 | 2021-04-30 | 北京机电工程研究所 | Force and heat integrated test loading device and test method for test piece |
| CN113879559A (en) * | 2021-10-12 | 2022-01-04 | 北京机电工程研究所 | Aircraft skin static force loading device and skin dynamic strength test method |
| RU2775689C1 (en) * | 2021-04-13 | 2022-07-06 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г.Ромашина" | Method for thermal testing of rocket fairings |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2654320C1 (en) * | 2017-05-30 | 2018-05-17 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Method for testing the strength of the fairings made of brittle materials |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101187611A (en) * | 2007-11-08 | 2008-05-28 | 武汉科技大学 | Heating device for determining non-metal material high temperature compressive strength |
| 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 |
| CN102262099A (en) * | 2011-04-15 | 2011-11-30 | 北京航空航天大学 | 1400-DEG C high-temperature thermal-mechanical coupling test device for aerofoil structure of hypersonic vehicle |
| CN202693430U (en) * | 2012-07-03 | 2013-01-23 | 北京航空航天大学 | High temperature distributed load heat strength test device for plane structure of high-speed missile aircraft |
-
2012
- 2012-07-03 CN CN201210228870.5A patent/CN102721612B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101187611A (en) * | 2007-11-08 | 2008-05-28 | 武汉科技大学 | Heating device for determining non-metal material high temperature compressive strength |
| 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 |
| CN102262099A (en) * | 2011-04-15 | 2011-11-30 | 北京航空航天大学 | 1400-DEG C high-temperature thermal-mechanical coupling test device for aerofoil structure of hypersonic vehicle |
| CN202693430U (en) * | 2012-07-03 | 2013-01-23 | 北京航空航天大学 | High temperature distributed load heat strength test device for plane structure of high-speed missile aircraft |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103867712A (en) * | 2012-12-10 | 2014-06-18 | 中国飞机强度研究所 | Metal foil high temperature sealing method |
| CN103867712B (en) * | 2012-12-10 | 2016-12-07 | 中国飞机强度研究所 | A kind of metal forming elevated-temperature seal method |
| CN103018096A (en) * | 2012-12-10 | 2013-04-03 | 中国飞机强度研究所 | Coordination applying device and method for transient uniform distribution of thermal and mechanical loads |
| RU2517790C1 (en) * | 2012-12-18 | 2014-05-27 | Открытое акционерное общество "Обнинское научно-производственное предприятие "Технология" | Application of heat stress to rocket cowls of nonmetals |
| CN104697862A (en) * | 2013-12-06 | 2015-06-10 | 中国飞机强度研究所 | Thermo-mechanical coupling loading method for thermal strength tests |
| CN104913918A (en) * | 2015-06-12 | 2015-09-16 | 中国人民解放军理工大学 | Pseudo-static test device |
| CN105241757A (en) * | 2015-09-18 | 2016-01-13 | 中国科学院武汉岩土力学研究所 | Uniform load mechanism, three dimensional slope model test load apparatus and three dimensional slope model test load method |
| RU2677487C1 (en) * | 2018-02-02 | 2019-01-17 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Method for heat loading of rocket fairings made of nonmetals |
| RU2696939C1 (en) * | 2018-09-20 | 2019-08-07 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Method for thermal loading of rocket fairings |
| RU2697410C1 (en) * | 2018-10-01 | 2019-08-14 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Ceramic shells testing method |
| CN109613052A (en) * | 2018-11-12 | 2019-04-12 | 南京航空航天大学 | A kind of hot loading device of structural test |
| CN109613052B (en) * | 2018-11-12 | 2022-02-08 | 南京航空航天大学 | Heat loading device for structural test |
| CN110261232A (en) * | 2019-06-26 | 2019-09-20 | 哈尔滨工程大学 | Composite material flat plate mechanical mechanics property test device peculiar to vessel |
| RU2720738C1 (en) * | 2019-09-12 | 2020-05-13 | Акционерное общество «Обнинское научно-производственное предприятие «Технология» им. А.Г.Ромашина» | Method of controlling heating during thermal testing of ceramic fairings |
| CN110525686A (en) * | 2019-09-18 | 2019-12-03 | 西北工业大学 | The experimental rig of aerothermodynamic Combined Trials |
| CN110525686B (en) * | 2019-09-18 | 2022-12-27 | 西北工业大学 | Testing device for pneumatic-thermal combined test |
| CN111103199A (en) * | 2019-11-29 | 2020-05-05 | 南京航空航天大学 | High-temperature flexible loading device |
| CN112461678A (en) * | 2020-11-23 | 2021-03-09 | 北京空间机电研究所 | Spacecraft thin-wall structure thermal strength test device and test method |
| CN112730091A (en) * | 2020-12-23 | 2021-04-30 | 北京机电工程研究所 | Force and heat integrated test loading device and test method for test piece |
| RU2775689C1 (en) * | 2021-04-13 | 2022-07-06 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г.Ромашина" | Method for thermal testing of rocket fairings |
| CN113879559A (en) * | 2021-10-12 | 2022-01-04 | 北京机电工程研究所 | Aircraft skin static force loading device and skin dynamic strength test method |
| CN113879559B (en) * | 2021-10-12 | 2023-08-15 | 北京机电工程研究所 | Aircraft skin static force loading device and skin dynamic strength test method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102721612B (en) | 2014-01-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102721612B (en) | High temperature-distributed load thermal strength test device for plane structure of high-speed missile aerobat | |
| CN202693430U (en) | High temperature distributed load heat strength test device for plane structure of high-speed missile aircraft | |
| Meola et al. | Infrared thermography to evaluate impact damage in glass/epoxy with manufacturing defects | |
| Muñoz et al. | Modeling lightning impact thermo-mechanical damage on composite materials | |
| Foster et al. | Understanding how arc attachment behaviour influences the prediction of composite specimen thermal loading during an artificial lightning strike test | |
| Suzuki et al. | Impact-damage visualization in CFRP by resistive heating: Development of a new detection method for indentations caused by impact loads | |
| Zhang et al. | Bending behavior of lightweight C/SiC pyramidal lattice core sandwich panels | |
| Minak et al. | Influence of diameter and boundary conditions on low velocity impact response of CFRP circular laminated plates | |
| Hu et al. | Effects of exposure time and intensity on the shot peen forming characteristics of Ti/CFRP laminates | |
| Park et al. | A study on low velocity impact damage evaluation and repair technique of small aircraft composite structure | |
| Liu et al. | A damage threshold prediction model of CFRP panel by hail impact based on delamination mechanism | |
| Grigoriou et al. | Influence of ply stacking pattern on the structural properties of quasi-isotropic carbon-epoxy laminates in fire | |
| CN103542997A (en) | Method for dynamically testing rudder system on basis of high-enthalpy wind tunnel force/heat environment | |
| Foster et al. | Modelling of mechanical failure due to constrained thermal expansion at the lightning arc attachment point in carbon fibre epoxy composite material | |
| Gaikwad | Axi-symmetric thermoelastic stress analysis of a thin circular plate due to heat generation | |
| Damghani et al. | Using laminate hybridisation (CFRP-GFRP) and shaped CFRP plies to increase plate post-buckling strain to failure under shear loading | |
| Yin et al. | Experimental and numerical simulation analysis of typical carbon woven fabric/epoxy laminates subjected to lightning strike | |
| Navarro et al. | Semi-continuous approach for the study of impacts on woven composite laminates: Modeling interlaminar behavior with a specific interface element | |
| Ramakrishnan et al. | A new method for the study of parabolic impact of foam-core sandwich panels | |
| Minak et al. | Low-velocity impact on laminates | |
| Zhang et al. | Experiment and analysis of composite reinforced panel’s limit load capacity under axial compression | |
| Cope et al. | Design of the composite spar-wingskin joint | |
| Daikh et al. | Buckling and bending of coated FG graphene-reinforced composite plates and shells | |
| Mitryaikin et al. | The study of strength of composites under impact | |
| Liu et al. | The damage investigation of wedge-shaped electromagnetic riveting structure of cfrp/aluminium alloy |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140129 Termination date: 20140703 |
|
| EXPY | Termination of patent right or utility model |