CN106248216A - A kind of big temperature difference system of large-scale deployable antenna builds and method of testing - Google Patents
A kind of big temperature difference system of large-scale deployable antenna builds and method of testing Download PDFInfo
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- CN106248216A CN106248216A CN201610616556.2A CN201610616556A CN106248216A CN 106248216 A CN106248216 A CN 106248216A CN 201610616556 A CN201610616556 A CN 201610616556A CN 106248216 A CN106248216 A CN 106248216A
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- 239000010937 tungsten Substances 0.000 description 2
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/0003—Radiation pyrometry, e.g. infrared or optical thermometry for sensing the radiant heat transfer of samples, e.g. emittance meter
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/0096—Radiation pyrometry, e.g. infrared or optical thermometry for measuring wires, electrical contacts or electronic systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
- G01R29/08—Measuring electromagnetic field characteristics
- G01R29/10—Radiation diagrams of antennas
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B6/00—Heating by electric, magnetic or electromagnetic fields
- H05B6/64—Heating using microwaves
- H05B6/72—Radiators or antennas
Abstract
The invention discloses a kind of big temperature difference system of large-scale deployable antenna to build and method of testing, including step: antenna is placed in test chamber, lamp battle array is placed on antenna side, first thermal imaging system and the second thermal imaging system are installed in lamp battle array, thermocouple is installed on antenna, first thermal imaging system and the second thermal imaging systems antenna surface temperature, demarcate antenna emissivity；Remove thermocouple, the first thermal imaging system and the second thermal imaging system local emissivity are set according to calibration result；According to gas flow rate and lamp battle array temperature, determine thermal-boundary-leyer thickness；According to thermal-boundary-leyer thickness, determine the distance of antenna and lamp battle array, test and adjust lamp battle array irradiation nonuniformity；It is cooled to the minimum temperature value of antenna；Turn on lights battle array, adjusts power and meets test requirements document to antenna surface temperature, carry out antenna function test；The present invention passes through spectrum isolation technology, integrated Infrared Heating and temp measuring system, it is achieved that antenna big temperature difference operating mode；By thermal boundary theory analysis, solve the problem that reflector temperature field is disturbed by lamp battle array.
Description
Technical field
The present invention relates to a kind of big temperature difference system of large-scale deployable antenna build and method of testing, be particularly suited for utilizing infrared
Spectrum isolation technology is theoretical with thermal boundary layer to antenna thermometric, belongs to the antenna big temperature difference wireless technical field of heating of operating mode.
Background technology
Large space deployable antenna is arranged on outside spacecraft, is affected by solar radiation and cold empty background in-orbit, sky
Line area of illumination temperature is high, and non-area of illumination temperature is low, forms big temperature gradient.Large scale structure each parts thermal deformation is caused not mated,
Large space antenna is launched the shape face after function and expansion, pointing accuracy etc. and produces material impact, and along with space development
Antenna size is increasing, and structure becomes increasingly complex, and required precision is more and more higher simultaneously, and the impact of temperature is the biggest.To this end, it is large-scale
Space development antenna high/low temperature is launched and testing experiment becomes the important tests project that antenna is developed.
In prior art, the mode for realizing the big temperature difference system in antenna element surface mainly has following 3 classes:
(1) infrared heating cage: by powering to Infrared Heating band, lifter temperature, then high-temperature heating band is to antenna spoke
Penetrate heat energy, heating antenna；Owing to heating tape radiant power is limited, it is generally used for vacuum environment, is not suitable for normal pressure convection environment；
In addition, heating cage is arranged dumb, need to arrange version for specific antenna.
(2) solar simulator: launch similar Fraunhofer lines, heating antenna by polymer/metallic lamp；But solar simulation
Device involves great expense, system complex, owing to being full spectral emissions, obvious to the greenhouse gases heats in air, is not suitable for
Atmospheric pressure environment temperature difference system.
(3) infrared lamp: the conventional infrared lamp negligible amounts used by temperature difference system, according to single infrared lamp, it is impossible to full
The actual demand of the irradiation nonuniformity of foot infrared lamp irradiation area, and traditional temperature difference system is for infrared lamp and antenna
Distance lacks accurately restriction, causes the temperature difference system stability ultimately formed relatively low.
Summary of the invention
The technology of the present invention solves problem: overcomes the deficiencies in the prior art, the invention provides a kind of large-scale expansion sky
The big temperature difference system of line builds and method of testing, by spectrum isolation technology, integrated Infrared Heating and temp measuring system, it is achieved that large-scale
Antenna big temperature difference operating mode；By thermal boundary, theoretical and analysis, solves the problem that reflector temperature field is disturbed by lamp battle array；By closing
Reason arranges lamp battle array, overcomes the defect that traditional temperature difference system stability is relatively low.
The technical solution of the present invention is:
A kind of big temperature difference system of large-scale deployable antenna builds and method of testing, comprises the steps:
The first step: launching to be placed in test chamber by antenna, lamp battle array is placed on the side of antenna, the first thermal imaging system and second
Thermal imaging system is separately mounted in lamp battle array, installs thermocouple at antenna different parts, uses the first thermal imaging system and the second thermal imaging system same
Time test antenna surface temperature, demarcate antenna different parts emissivity；
Second step: remove described thermocouple, arranges the first thermal imaging system and the second thermal imaging system according to emissivity calibration result
Local emissivity；
3rd step: according to gas flow rate in test chamber and lamp battle array temperature, determine thermal-boundary-leyer thickness δt；
4th step: according to thermal-boundary-leyer thickness δtAnd antenna launches motion requirement, determine the distance of antenna and lamp battle array, described
Distance is more than thermal-boundary-leyer thickness δt, lamp battle array is positioned at antenna and launches outside maximum space envelope, tests and adjust described distance model
Enclose the irradiation nonuniformity of interior lamp battle array irradiation area；
5th step: reduce test chamber temperature to minimum temperature value T of antennamin；
6th step: turn on lights battle array, adjusts the power of lamp battle array according to described antenna surface temperature, until antenna surface temperature is full
Foot test requirements document, carries out antenna function test.
Thermal-boundary-leyer thickness δtShould meet formula:Wherein: Pr
For Prandtl number, δ be flow-boundary-layer thickness, L be lamp battle array along the length of airflow direction, x0Suppose that leading edge, V ∞ are for examination for turbulent flow
Test indoor gas flow velocity, υ is fluid dynamic viscosity.
The radiation wavelength λ of lamp battle arrayLightIt is not more than 2.55 μm.
Lamp battle array is not less than 0.15m with the distance of antenna.
Lamp battle array uses distributed compensation formula layout, by adjusting the irradiating angle of each infrared lamp so that lamp battle array irradiation area
Irradiation nonuniformity less than 10%.
Test indoor air flow uses dry air, minimum temperature value T of antennaminIt is not less than dew point temperature.
Detection band range λ of the first thermal imaging system and the second thermal imaging systemCameraIt is 7.6～12.0 μm.
First thermal imaging system and the second thermal imaging system are symmetricly set on the both sides of lamp battle array.
First thermal imaging system and the second thermal imaging system all use thermal infrared imager, the thermometric model of the first thermal imaging system and the second thermal imaging system
Enclose the maximum temperature difference more than described antenna surface temperature.
The present invention compared with prior art provides the benefit that:
1, the present invention uses the mode of high-power lamp battle array fixed point heating under atmospheric low-temperature operating mode, it is to avoid firing equipment pair
Antenna launches process and produces interference, meets the thermometric demand of the big temperature difference system of atmospheric pressure environment antenna, effectively overcomes traditional
Infrared heating cage arranges an inflexible difficult problem.
2, the present invention is by controlling the transmitting light belt of high-power lamp battle array, effectively avoids atmospheric absorption spectroscopy, it is to avoid big
The power modulation battle array radiation heat effect to air, solves the full spectral emissions of traditional solar simulator and asks the interference in temperature field
Topic.
3, the present invention penetrates light belt, atmospheric radiation light belt by separating thermal infrared imager capture light belt with high-power lamp paroxysm,
Introduce contactless temperature-measuring method, it is achieved that accurately measuring and controlling antenna surface temperature field, reduce traditional contact
The interference to temperature field of the formula thermometric, compensate for traditional contact temperature-measuring and antenna launches the defect of function effect.
4, the present invention passes through Heat Flow Analysis, is moved by antenna outside lamp battle array hot-fluid boundary region, it is to avoid high temperature lampshade and lamp
The frame interference to antenna temperature field.
5, the temp measuring method logic smoothness of the present invention, clear thinking, reasonable in design, those skilled in the art are according to the present invention
Step test, it is possible to the surface temperature of the big temperature difference system of antenna of quick obtaining large and complex structure and temperature gradient.
6, the quantity of the present invention the first thermal imaging system and the second thermal imaging system can be arranged flexibly according to practical situation, and thermometric process is pacified
Complete reliable, the scope of application is relatively wide, and the first thermal imaging system and the second thermal imaging system are symmetricly set on the both sides of lamp battle array, optimizes operation sky
Between, alleviate the operation burden of staff.
7, the present invention the first thermal imaging system and the second thermal imaging system are conventional hardware, easy accessibility, without special, and are easy to
Maintenance and replacing, significantly reduce production cost.
8, the configuration after antenna is launched by the present invention is not particularly limited, it is adaptable to the various working environments such as low-temperature atmosphere-pressure,
Under complex working condition, still large space deployable antenna can be carried out thermometric, workable.
Accompanying drawing explanation
Fig. 1 is the flow chart of the present invention
Fig. 2 is the structure chart of the present invention
Fig. 3 is metal halide lamp spectral radiance map
Fig. 4 is Philip Halogen lamp spectrum scatter chart
Fig. 5 is that thermal-boundary-leyer thickness of the present invention is with lamp battle array temperature, the curve chart of gas flow rate change
Fig. 6 is that thermal-boundary-leyer thickness of the present invention supposes the curve chart of leading edge distance change with turbulent flow
Fig. 7 is that the present invention launches result of the test figure for the big temperature difference of large-scale antenna
Wherein: 1 test chamber；2 lamp battle arrays；3 first thermal imaging systems；4 second thermal imaging systems；5 antennas；
Detailed description of the invention
The invention will be further described with specific embodiment in explanation below in conjunction with the accompanying drawings:
As shown in Figure 1-2, a kind of big temperature difference system of large-scale deployable antenna builds and method of testing, comprises the steps:
The first step: launching to be placed in test chamber 1 by antenna 5, lamp battle array 2 is placed on the side of antenna 5, the first thermal imaging system 3
It is separately mounted in lamp battle array 2 with the second thermal imaging system 4, at antenna 5 different parts, thermocouple is installed, uses the first thermal imaging system 3 simultaneously
Testing antenna 5 surface temperature with the second thermal imaging system 4, demarcate the emissivity of antenna 5 different parts, scaling method is: with thermocouple
Test temperature is reference, revises the first thermal imaging system 3 and the second thermal imaging system 4 local emissivity, makes the first thermal imaging system 3 and the second thermal imagery
Instrument 4 test result is identical with thermocouple assay temperature, and local emissivity now is the true transmitting of antenna 5 corresponding position
Rate；
Second step: remove described thermocouple, according to emissivity calibration result, surveys at the first thermal imaging system 3 and the second thermal imaging system 4
Select antenna 5 different parts on examination software, and input demarcation emissivity, complete the first thermal imaging system 3 and local of the second thermal imaging system 4
Emissivity is arranged；
3rd step: according to gas flow rate in test chamber 1 and lamp battle array 2 temperature, determine thermal-boundary-leyer thickness δt；
4th step: according to thermal-boundary-leyer thickness δtAnd antenna 5 launches motion requirement, determine the distance of antenna 5 and lamp battle array 2,
Described distance is more than thermal-boundary-leyer thickness δt, lamp battle array 2 is positioned at antenna 5 and launches outside maximum space envelope, tests and adjust described
The irradiation nonuniformity of lamp battle array 2 irradiation area in distance range；
5th step: reduce test chamber 1 temperature to minimum temperature value T of antenna 5min；
6th step: turn on lights battle array 2, adjusts the power of lamp battle array 2 according to described antenna 5 surface temperature, until antenna 5 surface temperature
Degree meets test requirements document, carries out antenna 5 functional test.
Gas radiation has two key properties:
The composition the first, to heat radiation in air with radiation and absorbability is mainly carbon dioxide CO2And steam
H2O, other major part compositions, such as nitrogen, oxygen, hydrogen etc., for the heat radiation transparent body, do not carry out heat radiation and the most do not absorb heat
Radiation.
The second, carbon dioxide CO2With steam H2O has selectivity to radiation wavelength, only to light belt in particular range of wavelengths
Heat radiation have radiation and absorbability.Carbon dioxide CO2Main light with three sections: 2.65～2.80 μm, 4.15～
4.45 μm, 13.0～17.0 μm, steam H2The main light belt of O also have three sections: 2.55～2.84 μm, 5.60～7.60 μm,
12.0～30.0 μm.
Utilize two characteristics of more than gas radiation, selective radiation wavelength XLightThe radiating light source composition of≤2.55 μm is high-power
Lamp battle array, avoids the absorption band of carbon dioxide and steam completely, makes environmental test indoor gas temperature not by high-power lamp battle array
The impact of radiation.
Owing to tested antenna 5 surface all approximates unrestrained grey body at near-infrared and visible spectrum so that lamp battle array 2 emittance is led to
Cross product surface and be reflected into the first thermal imaging system 3 and the second thermal imaging system 4.In order to make the first thermal imaging system 3 and survey of the second thermal imaging system 4
Test result truly reflects the temperature of product surface, it is necessary to make the first thermal imaging system 3 and the second thermal imaging system 4 detect radiation wavelength away from
Lamp battle array 2 radiation spectrum, avoids carbon dioxide and steam light belt simultaneously.Therefore optional detection radiant light is with 4 sections, respectively 2.84
～4.15 μm, 4.45～5.6 μm, 7.6～12.0 μm and ＞ 30 μm.
Large-scale deployable antenna test temperature scope generally-100～+130 DEG C, according to Wien displacement law: λmT=
2.8976×10-3M K, wherein, λmRepresent that greatest irradiation Reeb is long.
Understanding, large-scale deployable antenna is greatest irradiation power wavelength X in the range of test temperaturemScope is 7.19～16.75 μm,
Preferably, detection radiation light belt λCameraIt is maximum that=7.6～12.0 μm detect antenna energy, for optimal detection spectral coverage.
Thermal-boundary-leyer thickness δtShould meet formula:Wherein: Pr
For Prandtl number, δ be flow-boundary-layer thickness, L be lamp battle array along the length of airflow direction, x0Suppose that leading edge, V ∞ are for examination for turbulent flow
Test indoor gas flow velocity, υ is fluid dynamic viscosity.
Theoretical according to hot-fluid, thermal boundary layer is the thin layer of fluid temperature (F.T.) acute variation near the surface of solids, and its thickness is δt,
It is defined according to its lip temperature t:
t-tW=99% (t∞-tW), wherein: t is fluid temperature (F.T.), t at hot-fluid boundary regionWFor lamp battle array surface temperature, t ∞
For gas temperature in test chamber.
Thermal boundary layer external fluid temperature can be approximately considered for stream body temperature t∞, i.e. the outer temperature of thermal boundary layer is not by lamp
The impact of battle array 2 temperature.For simplifying the analysis, it is assumed that lamp battle array 2 and support are a flat board, according to thermal convection principle:
In laminar flow section Rex≤5×105, thermal-boundary-leyer thicknessWherein: x is distance
The length of lamp battle array front end, lamp battle array front end represents lamp battle array one end that gas access, separating test room is nearest.
When air velocity becomes big, and laminar flow changes to turbulent flow, and thermal boundary layer is thickening.
Speed in turbulent boundary layer uses 7 power rules, it may be assumed thatWherein: y is distance lamp battle array plane
Length, u are the fluid velocity at distance lamp battle array front end x and lamp battle array plane y.
Then momentum loss thickness is:
Momentum loss thickness at turbulent flow section flat board x=L is:
Turbulent flow supposes leading edge
Critical length
Associating above formula obtains fluid boundary layer thickness under turbulent condition:
Thermal-boundary-leyer thickness:
Wherein: Prandtl number Pr and kinematic viscosity coefficient υ is all relevant to the temperature of lamp battle array 2 and gas, Pr change little, υ with
Temperature raises and raises.
In test chamber 1, air-flow uses dry air, minimum temperature value T of antenna 5minIt is not less than dew point temperature.
Lamp battle array 2 is not less than 0.15m with the distance of antenna 5.
Lamp battle array 2 uses distributed compensation formula layout, by adjusting the irradiating angle of each infrared lamp so that lamp battle array 2 irradiated region
The irradiation nonuniformity in territory is less than 10%.
First thermal imaging system 3 and the second thermal imaging system 4 are symmetricly set on the both sides of lamp battle array 2, and cover antenna 5 big temperature difference formation district
Territory, the side that the side that antenna 5 is irradiated by lamp battle array 2 and antenna 5 are not irradiated by lamp battle array 2 can form big temperature difference region.
First thermal imaging system 3 and the second thermal imaging system 4 all use thermal infrared imager, the first thermal imaging system 3 and survey of the second thermal imaging system 4
Temperature scope is more than the maximum temperature difference of described antenna surface temperature.
As shown in Figure 3-4, the exemplary spectrum distribution curve of radiating light source metal halide lamp and Halogen light has turned out: gold
Belonging to halide lamp main radiation spectrum scope is 0.35～1.75 μm, and the main radiation spectrum scope of Philip halogen tungsten lamp is 0.35
～2.5 μm, it is seen that these two kinds of lamps are satisfied by use demand, and metal halide radiation wavelength is shorter, is better than halogen tungsten lamp.
In conjunction with laminar flow and Turbulent computation formula, obtain thermal-boundary-leyer thickness with lamp battle array temperature, the Changing Pattern of gas flow rate
As seen in figs. 5-6, it can be seen that, lamp battle array 2 is the most relevant to 3 factors on the impact of antenna 5 temperature:
First, lampshade and lamp bracket temperature, temperature is the highest, and υ is the biggest, and thermal boundary layer is the thickest, affects the biggest on the temperature of antenna,
Otherwise it is the least；
Second, lamp battle array 2 and the relative position relation of antenna 5: along airflow direction, thermal boundary layer is thickening, and lamp battle array 2 is at antenna 5
Upwind side on the impact of antenna 5 temperature more than leeward；Lamp battle array 2 from antenna 5 apart from the least, from thermal boundary layer more close to,
Temperature impact is the biggest, otherwise the least；
3rd, wind speed size in test chamber 1: wind speed is the least, and thermal boundary layer is the thickest, affect the biggest, on the contrary the least.
Therefore according to wind speed in test chamber 1, adjust the distance of lamp battle array 2 and antenna 5, make antenna 5 lamp battle array 2 thermal boundary layer it
Outward, it is ensured that antenna 5 surface temperature is not affected by lamp battle array 2 temperature.
As it is shown in fig. 7, build and method of testing according to the one of the present invention big temperature difference system of large-scale deployable antenna, real
Synchronising hinge-68.6～the big temperature difference temperature gradient distribution of 27.4 DEG C and temperature field non-cpntact measurement are showed.
The operation principle of the present invention is:
In test chamber 1, it is passed through dry cold air, freezes, make environment and antenna 5 reach uniform, stable lowest temperature
Value Tmin, turn on lights battle array the 2, first thermal imaging system 3 and the second thermal imaging system 4, according to the first thermal imaging system 3 and the second thermal imaging system 4 temperature test
As a result, adjust the radiant power of lamp battle array 2, make antenna 5 irradiated area temperature reach to test high temperature requirement, thus be subject at antenna 5
Show up and non-irradiated face forms big temperature difference environment.
The content not described in detail in description of the invention is known to the skilled person technology.
Claims (9)
1. the big temperature difference system of large-scale deployable antenna builds and method of testing, it is characterised in that: comprise the steps:
The first step: launching to be placed in test chamber (1) by antenna (5), lamp battle array (2) is placed on the side of antenna (5), the first thermal imagery
Instrument (3) and the second thermal imaging system (4) are separately mounted in lamp battle array (2), install thermocouple at antenna (5) different parts, use first
Antenna (5) surface temperature tested by thermal imaging system (3) and the second thermal imaging system (4) simultaneously, demarcates the emissivity of antenna (5) different parts；
Second step: remove described thermocouple, arranges the first thermal imaging system (3) and the second thermal imaging system (4) according to emissivity calibration result
Local emissivity；
3rd step: according to test chamber (1) interior gas flow rate and lamp battle array (2) temperature, determine thermal-boundary-leyer thickness δt；
4th step: according to thermal-boundary-leyer thickness δtAnd antenna (5) launches motion requirement, determine the distance of antenna (5) and lamp battle array (2),
Described distance is more than thermal-boundary-leyer thickness δt, lamp battle array (2) is positioned at antenna (5) and launches, outside maximum space envelope, to test and adjust
The irradiation nonuniformity of lamp battle array (2) irradiation area in described distance range；
5th step: reduce test chamber (1) temperature to antenna (5) minimum temperature value Tmin；
6th step: turn on lights battle array (2), adjusts the power of lamp battle array (2) according to described antenna (5) surface temperature, until antenna (5) table
Surface temperature meets test requirements document, carries out antenna (5) functional test.
The big temperature difference system of the large-scale deployable antenna of one the most according to claim 1 builds and method of testing, it is characterised in that:
Described thermal-boundary-leyer thickness δtShould meet formula:Wherein: Pr is general
Lang Te number, δ be flow-boundary-layer thickness, L be lamp battle array along the length of airflow direction, x0Suppose that leading edge, V ∞ are test chamber for turbulent flow
Interior gas flow rate, υ are fluid dynamic viscosity.
The big temperature difference system of the large-scale deployable antenna of one the most according to claim 1 and 2 builds and method of testing, and its feature exists
In: the radiation wavelength λ of described lamp battle array (2)LightIt is not more than 2.55 μm.
The big temperature difference system of the large-scale deployable antenna of one the most according to claim 3 builds and method of testing, it is characterised in that:
Described lamp battle array (2) is not less than 0.15m with the distance of antenna (5).
The big temperature difference system of the large-scale deployable antenna of one the most according to claim 3 builds and method of testing, it is characterised in that:
Described lamp battle array (2) uses distributed compensation formula layout, by adjusting the irradiating angle of each infrared lamp so that lamp battle array (2) irradiated region
The irradiation nonuniformity in territory is less than 10%.
The big temperature difference system of the large-scale deployable antenna of one the most according to claim 3 builds and method of testing, it is characterised in that:
Described test chamber (1) interior air-flow uses dry air, antenna (5) minimum temperature value TminIt is not less than dew point temperature.
The big temperature difference system of the large-scale deployable antenna of one the most according to claim 3 builds and method of testing, it is characterised in that:
Described first thermal imaging system (3) and detection band range λ of the second thermal imaging system (4)CameraIt is 7.6～12.0 μm.
The big temperature difference system of the large-scale deployable antenna of one the most according to claim 7 builds and method of testing, it is characterised in that:
Described first thermal imaging system (3) and the second thermal imaging system (4) are symmetricly set on the both sides of lamp battle array (2).
The big temperature difference system of the large-scale deployable antenna of one the most according to claim 8 builds and method of testing, it is characterised in that:
Described first thermal imaging system (3) and the second thermal imaging system (4) all use thermal infrared imager, the first thermal imaging system (3) and the second thermal imaging system (4)
Temperature-measuring range more than the maximum temperature difference of described antenna surface temperature.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610616556.2A CN106248216B (en) | 2016-07-29 | 2016-07-29 | A kind of big temperature difference system of large size deployable antenna constructs and test method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109163831A (en) * | 2018-08-21 | 2019-01-08 | 南京中车浦镇城轨车辆有限责任公司 | A kind of ultrasonic wave residual stress measuring method |
| CN116046179A (en) * | 2022-12-05 | 2023-05-02 | 兰州空间技术物理研究所 | Non-contact temperature measurement and calibration method in plasma thruster operation environment |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5686930A (en) * | 1994-01-31 | 1997-11-11 | Brydon; Louis B. | Ultra lightweight thin membrane antenna reflector |
| US6292140B1 (en) * | 1999-11-03 | 2001-09-18 | Hypres, Inc. | Antenna for millimeter-wave imaging and bolometer employing the antenna |
| CN101806762A (en) * | 2010-05-31 | 2010-08-18 | 哈尔滨工业大学 | Method for identifying thermal defects by means of auxiliary heat source under condition of small temperature difference |
| CN102967623A (en) * | 2012-11-06 | 2013-03-13 | 上海卫星工程研究所 | Infrared lamp array heat-flow density calibration device and calibration method |
| CN103997801A (en) * | 2014-06-04 | 2014-08-20 | 北京卫星环境工程研究所 | Application of forming heating plate in space vehicle antenna thermal vacuum test |
| CN104267062A (en) * | 2014-10-22 | 2015-01-07 | 北京航空航天大学 | Method for converting cold wall heat flux into hot wall heat flux in aerodynamic heat simulating test |
| CN105328511A (en) * | 2015-11-18 | 2016-02-17 | 江苏科技大学 | Cutting online-temperature collecting method used for porous material |
| CN105606923A (en) * | 2015-12-18 | 2016-05-25 | 国网河南省电力公司电力科学研究院 | Cable current carrying limit determination method based on numerical simulation and passive wireless temperature measurement |
| CN105716723A (en) * | 2016-04-05 | 2016-06-29 | 中国计量学院 | Device and method for improving temperature measuring precision of industrial site thermal imager |
-
2016
- 2016-07-29 CN CN201610616556.2A patent/CN106248216B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5686930A (en) * | 1994-01-31 | 1997-11-11 | Brydon; Louis B. | Ultra lightweight thin membrane antenna reflector |
| US6292140B1 (en) * | 1999-11-03 | 2001-09-18 | Hypres, Inc. | Antenna for millimeter-wave imaging and bolometer employing the antenna |
| CN101806762A (en) * | 2010-05-31 | 2010-08-18 | 哈尔滨工业大学 | Method for identifying thermal defects by means of auxiliary heat source under condition of small temperature difference |
| CN102967623A (en) * | 2012-11-06 | 2013-03-13 | 上海卫星工程研究所 | Infrared lamp array heat-flow density calibration device and calibration method |
| CN103997801A (en) * | 2014-06-04 | 2014-08-20 | 北京卫星环境工程研究所 | Application of forming heating plate in space vehicle antenna thermal vacuum test |
| CN104267062A (en) * | 2014-10-22 | 2015-01-07 | 北京航空航天大学 | Method for converting cold wall heat flux into hot wall heat flux in aerodynamic heat simulating test |
| CN105328511A (en) * | 2015-11-18 | 2016-02-17 | 江苏科技大学 | Cutting online-temperature collecting method used for porous material |
| CN105606923A (en) * | 2015-12-18 | 2016-05-25 | 国网河南省电力公司电力科学研究院 | Cable current carrying limit determination method based on numerical simulation and passive wireless temperature measurement |
| CN105716723A (en) * | 2016-04-05 | 2016-06-29 | 中国计量学院 | Device and method for improving temperature measuring precision of industrial site thermal imager |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109163831A (en) * | 2018-08-21 | 2019-01-08 | 南京中车浦镇城轨车辆有限责任公司 | A kind of ultrasonic wave residual stress measuring method |
| CN109163831B (en) * | 2018-08-21 | 2020-11-13 | 南京中车浦镇城轨车辆有限责任公司 | Ultrasonic residual stress measuring method |
| CN116046179A (en) * | 2022-12-05 | 2023-05-02 | 兰州空间技术物理研究所 | Non-contact temperature measurement and calibration method in plasma thruster operation environment |
| CN116046179B (en) * | 2022-12-05 | 2024-02-20 | 兰州空间技术物理研究所 | Non-contact temperature measurement and calibration method in plasma thruster operation environment |
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