CN107727237A - A kind of ground heat test Low Temperature Target infrared radiation measurement device and method - Google Patents
A kind of ground heat test Low Temperature Target infrared radiation measurement device and method Download PDFInfo
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- CN107727237A CN107727237A CN201710790945.1A CN201710790945A CN107727237A CN 107727237 A CN107727237 A CN 107727237A CN 201710790945 A CN201710790945 A CN 201710790945A CN 107727237 A CN107727237 A CN 107727237A
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- G—PHYSICS
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- 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
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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
- G01J5/02—Constructional details
- G01J5/0205—Mechanical elements; Supports for optical elements
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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
- G01J5/0003—Radiation pyrometry, e.g. infrared or optical thermometry for sensing the radiant heat transfer of samples, e.g. emittance meter
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Abstract
A kind of ground heat test Low Temperature Target infrared radiation measurement device and method, including measurement apparatus and control rack；Measurement apparatus includes equipment compartment agent structure, infrared optical window, closed type charging and discharging valve and interface, sealed type electric connector, temperature sensor, pressure sensor, heating plate, multilayer insulation component, thermal-control circuit, bracket, thermal infrared imager, cabin controlling system；Equipment compartment agent structure includes nacelle, protecgulum, bonnet；Infrared optical window is arranged on protecgulum, after cover installation sealed type electric connector and closed type inflation/deflation interface valve；Thermal infrared imager is arranged on the bracket in equipment compartment body, for gathering target information；Nacelle inner surface sticking heating plates；Multipoint temperature sensor, pressure sensor are arranged, and passes through the temperature in thermal-control circuit control cabinet body；Preceding exterior surface is coated using multilayer insulation component；Control system is used for below deck equipment power supply, environmental monitoring and data acquisition, and the data collected are sent into control rack.
Description
Technical field
The present invention proposes a kind of ground heat test Low Temperature Target infrared radiation measurement device and method, belong to experiment with it is low
Warm technical field of measurement and test.
Background technology
Spacecraft thermal test (thermal vacuum test, the general designation of heat balance test) is one be subjected to before Spacecraft Launch
Important ground examination.Spacecraft thermal vacuum test is in vacuum (vacuum 10-3Below Pa), cold black (environment temperature about 100K) environment
Lower progress, it is even lower that testpieces surface temperature can reach 150K ((- 123 DEG C)), traditionally typically uses thermoelectricity occasionally temperature-sensitive
The contact measurement means monitoring test part surface temperature such as resistance.In recent years, because thermal infrared imager is with not interference test part fortune
Move, can intuitively analyze the remarkable advantages such as spacecraft surface temperature field distribution, be gradually applied in spacecraft testing.In the past
During experiment application, generally thermal infrared imager is placed on outside vacuum tank, target in simulated environment surveyed by infrared window
Amount, is limited, p- less than 40 DEG C Low Temperature Targets by factors such as thermal imaging system noise, measuring route stray radiation, low temperature target-abilities
Do not possess measurement capability, the accurate measurement of less than -40 DEG C Low Temperature Targets can not be realized.Infrared thermal imaging equipment low-temperature measurement ability
Deficiency seriously constrains its further applying in spacecraft thermal test.
The content of the invention
The technical problems to be solved by the invention are：Overcome the shortcomings of existing means, there is provided a kind of ground heat test low temperature
Target Infrared Radiation measurement apparatus and method, it can realize that the non-contacting infrared of 150K (- 123 DEG C) even lower temperature objectives is special
Property measurement, and can directly be operated in heat test environment, measurement accuracy is high.
The technical scheme is that：A kind of ground heat test Low Temperature Target infrared radiation measurement device, including measurement dress
Put and control rack；The measurement apparatus includes equipment compartment agent structure, infrared optical window, closed type charging and discharging valve and connect
It is mouth, sealed type electric connector, temperature sensor, pressure sensor, heating plate, multilayer insulation component, thermal-control circuit, bracket, red
Outer thermal imaging system, cabin controlling system；The equipment compartment agent structure includes nacelle, protecgulum, bonnet；Infrared optical window is arranged on
On protecgulum, after cover installation sealed type electric connector and closed type charging and discharging valve and interface；Thermal infrared imager is arranged on equipment
On bracket in nacelle, for gathering target information；Nacelle inner surface sticking heating plates；Arrangement multi-point temp sensing in nacelle
Device, pressure sensor, and pass through the temperature in thermal-control circuit control cabinet body；Preceding exterior surface is coated using multilayer insulation component；
The nacelle controlling system is used for below deck equipment power supply, environmental monitoring and data acquisition, and the data collected are sent into control
Rack processed.
The measurement apparatus is placed in vacuum tank, and control rack is placed on outside vacuum tank.
Top and rear portion in the equipment compartment body are provided with hot-swappable fans, and install V-type deflector in air outlet.
The nacelle controlling system includes DC/DC power conversion modules, fiber optic switching module, environment acquisition module；Its
Middle DC/DC power conversion modules are used to power for thermal infrared imager and other below deck equipments；Fiber optic switching module is used for will be infrared
The picture signal of thermal imaging system is converted into optical signal and sent to out of my cabin；Environment acquisition module is used to gather temperature and pressure number in cabin
According to, and collection result is sent to out of my cabin by RS485 buses.
The equipment compartment agent structure material is 304 stainless steels, and inner and outer surfaces spraying thermal control in cabin is pitch-dark.
The closed type charging and discharging valve and interface include valve, interface and plug, and valve uses hand stop valve, charge and discharge
Gas interface uses 37 ° of spherical interfaces, and is sealed with plug.
Connected with flange between the nacelle and protecgulum and bonnet, sealed at flange-interface using aviation nitrile rubber
Circle.
The thermal infrared imager is tiltedly mounted on the bracket in equipment compartment body, and inclination angle is 13 °.
The measurement apparatus is connected with control rack by the socket through walls on vacuum tank.
A kind of method that heat test Low Temperature Target infrared radiation measurement in ground is carried out using above-mentioned measurement apparatus, step is such as
Under：
1) front opening equipment compartment protecgulum is tested, thermal infrared imager is arranged in equipment compartment, filled after installation by closed type
Deflation interface nitrogen displacement wherein air, ensure the atmospheric pressure of pressure 1~1.2 in cabin, inflation inlet is closed after 10 minutes, capping is stifled
Head prevents gas leakage；
2) airtight test is integrally carried out to equipment compartment；
3) measurement apparatus is arranged in vacuum and low temperature container, cable connection inside and outside tank is completed by plug through walls；
4) equipment compartment vivo environment temperature and pressure is monitored in real time by temperature sensor, pressure sensor when testing, and
Indoor environment temperature is controlled to setting value using heating plate, multilayer insulation component, thermal-control circuit；
5) thermal imaging system starts measurement, passes through cabin controlling system data acquisition.
The present invention compared with prior art the advantages of be：
(1) it is better than 0.8mm/m using the high section structure of airtight performance, nacelle flange face processing roughness requirements2,
Sealed at flange-interface using two seals mode, sealing ring selects O-shaped aviation nitrile rubber sealing ring.Device can be for a long time
(being not less than 30 days) is directly operated in vacuum low-temperature environment, is effectively reduced tank external pelivimetry path stray radiation to measurement
Influence, improve measurement accuracy.
(2) using the measure such as equipment compartment internal fan, deflector, inwall be pitch-dark, thermal infrared imager and nacelle heat exchange are improved
Speed, using radiation heat transfer and Active thermal control, realize thermal infrared imager optical system works temperature in the range of -60 DEG C~30 DEG C
It is settable, when controlling optical system works in low-temperature condition, thermal infrared imager system noise is effectively reduced, greatly improved low
Temperature measurement ability, 150K (- 123 DEG C) even more Low Temperature Targets can be measured, and with preferably linear.
(3) when device works, inflated with nitrogen in equipment compartment, when control changes indoor environment temperature, it effectively prevent steam
The influence to optical measurement such as condensation, corrosion.
(4) thermal infrared imager is tilted and installed by device, and the thermal imaging system optical axis and equipment compartment front end infrared window are formed necessarily
Angle, the problems such as effectively prevent the ghost of optical imagery.
(5) device has flexibly with general feature, by changing infrared window and thermal infrared imager, can be achieved outside Different Red
Wave band measures.
(6) a kind of new non-contacting infrared temp measuring method for heat test is proposed, devises a kind of Novel temperature measuring dress
Put.
Brief description of the drawings
Fig. 1 is apparatus of the present invention composition schematic diagram.
Fig. 2 is the curve that using low temperature black matrix apparatus of the present invention are carried out with radiation calibration.
Embodiment
1 operation principle
During spacecraft thermal test, thermal infrared imager observation background is heat sink for liquid nitrogen refrigerating, and temperature is generally below 100K, this
When, the background radiation that thermal infrared imager obtains turns into system for restricting essentially from own optical system, optical system stray radiation
An important factor for low-temperature measurement ability.When spacecraft target is in low temperature, mesh signal is weaker, and optical system stray radiation is drawn
The noise risen often floods echo signal, has a strong impact on system hypothermia measurement capability.In the case where detector is selected, optical system
The analysis of system stray radiation and suppression are the key technologies for realizing low-temperature measurement.
Optical system radiation includes camera lens radiation and lens barrel structure radiation.For the infrared light that cold stop efficiency is 100%
System, in system aperture angular region, only the infrared radiant energy of optical mirror plane reaches detector image planes, therefore only needs to calculate
Camera lens radiates.Illumination of the optical system heat radiation in image planes is：
Wherein, ρ0For single optical lens transmitance, εlFor camera lens emissivity, n is number of lenses.
Bring numerical computations into and obtain irradiation level of the different temperatures optical system in detector image planes and be listed in table 1：
Irradiation level of the different temperatures optical system of table 1 in detector image planes
As can be seen that noise caused by the optical system stray radiation of refrigeration measure is not taken to be far above noise of detector.
If it is desired to which optical system radiation is had no effect as matter to measurement, optical system should take refrigeration measure, operating temperature
150K should be less than.
But when engineering actually uses, the extremely low operating temperature of optical system realizes that cost is very big, therefore, further analysis
Influence of the optical system stray radiation to target measurement SNR.System bandwidth of operation minimum value during calculating optical system different temperatures,
It is listed in table 2：
The different temperatures optical system of table 2 influences on system bandwidth
As a result show, during about -20 DEG C of optical system temperature, system bandwidth minimum 50, for 130K targets, infrared system letter
Make an uproar than SNR ≈ 9, when optical system refrigeration arrives about -100 DEG C, for 130K targets, infrared system signal to noise ratio can increase to
SNR≈45。
According to the method described above, according to the actual low-temperature measurement demand of spacecraft, under the premise of ensureing enough SNR, rationally control
Optical system works temperature.
2 device schemes
As shown in figure 1, a kind of ground heat test Low Temperature Target infrared radiation measurement device, including equipment compartment structure housing,
Infrared optical window, closed type charging and discharging valve and interface, sealed type electric connector, hot-swappable fans, deflector, sealing ring, temperature
Spend sensor, pressure sensor, heating plate, multilayer insulation component, thermal-control circuit, bracket, thermal infrared imager, control is in cabin
System, nacelle controlling system, vacuum socket through walls, tank outer control rack etc.；Equipment compartment main body is sealing structure, by circular cabin
Body, protecgulum, bonnet three parts composition, infrared optical window are arranged on protecgulum, after cover installation sealed type electric connector and close
Envelope type charging and discharging valve and interface.Thermal infrared imager is tiltedly mounted in equipment compartment on bracket, and nacelle inner surface pastes heater,
Multipoint temperature sensor, pressure sensor are arranged in cabin simultaneously, front end exterior surface takes multilayer insulation component to coat, equipment compartment
Interior installation fan, and V-type heat-conducting plate is installed in air outlet, cabin controlling system is used for below deck equipment power supply, temperature control, environment
Monitoring and data acquisition.Front opening equipment compartment protecgulum is tested, thermal imaging system is arranged in equipment compartment, connect after installation by inflation/deflation
Mouthful with nitrogen displacement wherein air, the close inspection of promoting the circulation of qi of going forward side by side, device overall work is in vacuum low-temperature environment during experiment, equipment compartment
Interior environment temperature and pressure is monitored in real time by temperature sensor, pressure sensor, utilizes heating plate, multilayer insulation component, heat
Controlling circuit controls indoor environment temperature to start measurement to setting value, thermal imaging system, pass through cabin controlling system, socket through walls and cable
Deng data acquisition.
Equipment compartment structure housing material is 304 stainless steels, and surfaces externally and internally spraying thermal control in cabin is pitch-dark.
Charging and discharging valve uses hand stop valve, and inflation/deflation interface uses 37 ° of spherical interfaces, and is sealed with plug.
Equipment compartment airtight performance requires high, integral leakage requirement：Static≤10-7Pa*L/s, dynamic≤10-6Pa*L/s, equipment
Cabin flange Surface Machining roughness requirements are better than 0.8mm/m2, sealed using two seals mode at flange-interface, using O
Type aviation nitrile rubber sealing ring, be resistant to -60 DEG C of low temperature, can avoid using common fluorubber and caused by sealing ring embrittlement etc.
Phenomenon.
Bracket is used to install support thermal imaging system, 13 ° of inclination angle, passes through 5mm fiberglass heat insulating mattress and the heat-insulated installation of thermal imaging system.
Hot-swappable fans are arranged on top and each one of rear portion in equipment compartment, and fan designs V-arrangement heat-conducting plate in air outlet.
6 temperature sensors, 2 pressure sensors are laid in equipment compartment, realize that real time environment monitors, equipment compartment inwall glues
4 road heating plates are pasted, realize Active thermal control, -60 DEG C of temperature controlling range~30 DEG C.
Using air in nitrogen displacement equipment compartment before device experiment, ensure the atmospheric pressure of pressure 1~1.2 in cabin..
Equipment compartment front shroud opens infrared window, and wave band matches with thermal imaging system, replaceable.
Device realizes control, data acquisition and power supply using socket through walls outside tank.Device is using socket through walls outside tank
Control, data acquisition and power supply are realized, configures 1 socket through walls, 2 optical fiber air plugs, 1 vision signal air plug.Socket through walls
From Y27-2455ZJB4H (totally 55 points), for signal (8 tunnel), power supply (12 tunnel), thermal imaging system network interface (16), heat
As instrument synchronizing signal (8 points), and reserve 11 points.
The control rack of the outer apparatus for placing of vacuum tank, it is controllable directly to be that equipment compartment in tank provides 24V by AC/DC power modules
Power supply is flowed, is powered directly to thermal infrared imager, nacelle controlling system and heating plate, receives temperature, barometric information, it is aobvious in real time
Show, and according to for different mode, realize temperature control；Recovery photosignal is picture signal, and is acquired, stores, turning
Hair.
At the large flange of equipment compartment, take multiple tracks aviation nitrile rubber sealing ring to seal, prevent to occur wherein
The leakage of one of sealing ring.
By calculating, it is less than 10 in integral leakage-6Index, in the case of being inside pressed in work 30 days, the equipment compartment pressure loss
For 110Pa, loss amount is much smaller than 105The 5%% of Pa, i.e. 5000Pa, it disclosure satisfy that the requirement of normal pressure.
2.1 organization plan
Equipment compartment main body is sealing structure, and equipment compartment agent structure is made up of bulge, protecgulum, bonnet three parts, respectively
Part is connected by screw, and is sealed between the two by flange seal ring, it is ensured that equipment compartment seals.Weld and join in equipment compartment both sides
Axle device, it is connected by shaft coupling with the turntable above omnidirectional measurement mechanism.Equipment compartment external dimensions no more than ф 360mm ×
800mm, the infrared transparent windows that front end is ф 100mm (window wave band is 7~14 μm).Inside is ф 280mm × 550mm circle
Cylindricality, is equipped with support and guide rail, and support can remove equipment compartment by guide rail, be easy to equipment to install.Pedestal upper end places thermal imaging system,
Place nacelle controlling system in lower end.
2.1.1 guide rail bracket scheme
Dismounted for ease of equipment in equipment compartment, using guide rail bracket scheme.
Guide rail is installed on equipment ceiling board, and long waist shaped mounting hole is opened on guide rail mounting surface, is installed for guide rail, and adjustable
Save the installation site of guide rail.Bracket is the part that equipment below deck equipment is installed concentratedly, and bracket two sides are installed four sliding blocks, are used for
Bracket is matched somebody with somebody with guide rail and merges slip.Bracket leading portion sets a limiting bracket, for limiting the final position of bracket.On limiting bracket
Long waist shaped is opened, for adjusting the position of limiting bracket.
2.1.2 equipment mounting bracket
Thermal infrared imager is installed by the long waist shaped hole of bracket front end, and position is adjustable, the bottom-up installation of fastener, is used
Sunk screw, the controller with bottom installation is avoided to interfere.Controller is arranged on bracket base, and size is no more than 164X250X60
(mm).Two fans are installed on upper surface and the thermal imaging system top (blower tray on thermal imaging system top of bracket by metal plate support
Thermal imaging system is borrowed during installation from mounting hole with handles).
2.1.3 charging and discharging valve
Each 1 of charging and discharging valve, using hand stop valve.After thermal imaging system is fit into equipment compartment, while open charge and discharge
Gas stop valve, inflation inlet connect nitrogen cylinder and carry out equipment compartment nitrogen displacement (preventing that air condenses in vacuum tank).Closed after 10 minutes
Inflation inlet, and add plug to prevent gas leakage.Air inlet hand stop valve is closed afterwards and adds plug.
Inflation/deflation interface uses 37 ° of spherical interfaces, after gas displacement is carried out to its inside before equipment compartment enters container,
By silently and screw-threaded coupling, ensureing the overall sealing property of equipment compartment.
2.1.4 cable laying scheme
Bracket upper surface, region laying of the cable along equipment both sides.Bracket floor space is more loose, and cable is along bracket bottom
Face laying is fixed.Directly it can be fixed for thinner cable (such as thermistor cable, fan cable etc.) with silicon rubber, phase
To thicker cable use fixed seat again.For laying to the branch of crossing cabin plug, the surplus that must at least reserve 100mm is used for
Before bonnet docking, plug grafting operation surplus.
2.1.5 encapsulation scheme
Device requires higher for the sealing property of equipment compartment itself, and the whole leak rate requirement of sealed compartment is：When static not
More than 10-7Pa*L/s, 10 are not more than during dynamic-6Pa*L/s.At the large flange of equipment compartment, multiple-sealed circle sealing is taken, is prevented
The leakage for wherein one sealing ring that may only occur.Using special aviation nitrile rubber sealing ring, -60 DEG C low is resistant to
Temperature, can avoid using common fluorubber and caused by sealing ring embrittlement phenomena such as.By calculating, it is less than 10 in integral leakage-6Finger
Mark, in the case of being inside pressed in work 30 days, pressure loss 110Pa, loss amount is much smaller than 105The 5%% of Pa, i.e. 5000Pa,
It disclosure satisfy that the requirement of normal pressure.
2.2 electrical design
2.2.1 electrical system task and function
The task of equipment compartment electrical system is to provide power supply for thermal imaging system in itself and cabin, receives the control of rear end console
And ensure that temperature meets design objective requirement in cabin, send rear end to show indoor environment state, while be responsible for thermal imaging system in cabin
Camlink interfaces carry out opto-electronic conversion, realize the fiber optic communication with rear end console.The major function of completion has：
A)+12V (50W) controllable direct current power supply is provided for thermal infrared imager in cabin；
B) gather and show temperature data in 6 tunnel cabins；
C) gather and show barometric information in 2 tunnel cabins；
D) 4 road electric heating sheets are configured, it is real using the temperature data collected, the working condition of automatic control electrical heating piece
Temperature control function in the existing cabin regulation of temperature range (can in Local or Remote control cabinet)；
E) two DC fans are set in cabin, realize cabin inner air convection；
F) thermal infrared imager Camlink interface images data in cabin are transferred into host computer by optical fiber to store, and will figure
As data forwarding is to master control；
G) provide cabin in the electrical connection passage of other interfaces of thermal infrared imager and host computer (network interface, vision signal,
Synchronizing signal etc.).
2.2.2 system composing and working theory
It is divided into equipment below deck equipment and tank outer control cabinet two large divisions on whole system hardware.
Below deck equipment is by nacelle controlling system and other ancillary equipment (including temperature sensor, pressure sensor, wind
Fan, heating plate etc.) composition.Wherein heating plate and nacelle controlling system is powered by control rack out of my cabin.In nacelle
Control system is used to power (except heating plate) for thermal imaging system and the power supply of other below deck equipments, and the 6 tunnel temperature that will be collected in cabin
Degree, 2 road barometric informations send control rack out of my cabin to by RS485 buses, and thermal imaging system figure line data are converted into photosignal,
Control rack out of my cabin is transferred to by optical fiber.Temperature sensor, pressure sensor are used for collecting temperature, pressure data；Electrical heating
Piece is used to heat to nacelle, maintains the temperature in cabin；DC fan, air in cabin is set to form convection current, temperature is uniform.
Vacuum tank outer control rack provides 24V controllable direct current power supplies by AC/DC power modules for below deck equipment, directly to
Nacelle controlling system and heating plate power supply, reception temperature, barometric information, real-time display, and according to for different mode, reality
Existing temperature control；Recovery photosignal is picture signal, and is acquired, stores, forwards；Master control instruction can be received, realizes system
System is remotely for power-off.
2.2.3 nacelle controlling system
Nacelle controlling system include DC/DC power conversion modules, fiber optic switching module, environment acquisition module composition (for
Volume is saved, pressure sensor is integrated in nacelle controlling system).It is thermal imagery that wherein DC/DC power conversion modules, which are used for,
Instrument and the power supply of other below deck equipments are (except heating plate)；Fiber optic switching module is used to pass through the picture signal of thermal imaging system
Camlink modules are converted into optical signal；Environment acquisition module is responsible for gathering 6 tunnel temperature, 2 road barometric informations in cabin, and will collection
As a result switch board out of my cabin is sent to by RS485 buses.
(1) DC/DC power conversion modules
It is thermal imaging system, temperature sensor, pressure sensor and in-line power that DC/DC power conversion modules, which are used for,.From demand
Analysis understands that input voltage 24V, output voltage is divided into 2 kinds：12V and 5V, wherein 12V are mainly thermal imaging system power supply, and 5V is it
He powers.Wherein thermal imaging system power supply can instruct controlling switch by host computer.To meet power reguirements, DC/DC module indexs
It is it is required that as follows：
The DC/DC module index requests of table 3
| Index | 5V | 12V |
| Input voltage | 18~36V | 18~36V |
| Output voltage | 5V±0.2V | 12V±0.5V |
| Export maximum current (in the case of consideration maximum power dissipation) | 6A | 5A |
| Ripple voltage | ≤200mV | ≤200mV |
(2) fiber optic switching module
Fiber optic switching module is used to the picture signal of thermal imaging system being converted into optical signal by Camlink modules.Due to setting
Standby indoor environment temperature is harsh, and in general Camlink optical fiber conversion products are unable to reach sub-zero operating temperature.Equipment compartment
The interior CameraLink-- optical fiber transition cards for intending obtaining industrial company's development ＆ production using Sichuan thunder, the card technique index are as follows：
A) thermal imaging system end CameraLink Base, Medium, Full interface are supported；
B) maximum can support 10tap × 8bit Extended Full patterns；
C) CameraLink highest frequencies 85Mhz is supported；
D) it is transmitted (agreement can customize) using the GTP of Xilinx companies, optical fiber transmission maximum rate
3.125Gbps, it can facilitate and be interconnected with high-speed dsp processing platform；
E) view data is no-delay, in real time transmission；
F)+5V powers, Base power consumptions 5V/0.5A, Full power consumption 5V/1A；
G) maximum transmission distance：Use 50/125um multimode fibres, 250 meters of maximum transmission distance；Can using single-mode fiber
To 100Km；
H) operating temperature：- 20~60 DEG C；
I) storage temperature：- 60~85 DEG C；
J) size：109x81mm.
(3) environment acquisition module
Environment acquisition module is responsible for gathering 6 tunnel temperature, 2 road barometric informations in cabin, and collection result is passed through into RS485 buses
Send switch board out of my cabin to.Core processor MCU uses 16/32 general single chips to realize, is responsible for collection, control and leads to
Letter, it is the core of whole nacelle controlling system；RS485 serial communication modulars are by RS485 electrical level transferring chips and interface protection
Circuit is formed, and is responsible for the communications with rear end console.Main control MCU uses the 32-bit microprocessor STM32 of ST companies, possesses
Higher calculation process speed and reliability.
Environment acquisition module improves system reliability using mainboard Dual module Hot Spare mode.Environment acquisition module mainboard A,
B input interface is arranged to high-impedance state using parallel way connection sensor, the input interface of standby host mainboard according to instruction,
RS485 is communicated using mode hand in hand with host computer, and acquiescence is A modules when airliner.Under normal operating conditions, host computer passes through
RS485 buses are per second to carry out inspection to A, B module, and being switched to standby host by instruction in the case of airliner failure works.
In addition to photosignal, data transfer communications use RS485 buses, and agreement is with reference to MODBUS bus protocols.It is specific logical
Believe content such as table 4 below：
The environmental control system bus communication content of table 4
2.2.4 design for temperature sensor
Temperature sensor uses number bus formula temperature sensor chip DS18B20, can be directly by temperature number in equipment compartment
According to sending nacelle controlling system to.DS18B20 " one-wire bus " digital temperature sensor is the single line number of DALLAS productions
Word temperature sensor, measurement temperature scope is -55 DEG C~+125 DEG C, and in the range of -10~+85 DEG C, precision is ± 0.5 DEG C.It is existing
Field temperature directly being digitally transmitted with " one-wire bus ", substantially increases the anti-interference of system, is suitable for adverse circumstances
Scene temperature measurement.Each temperature sensor is picked out using lead terminal, and temperature measuring point is attached to heat-conducting glue.Temperature sensor end
And binding post is respectively provided with obvious label, and with being corresponded in software, prevent measurement result from obscuring.
2.2.5 pressure sensor design
The BMP085 movement air pressure sensor chips that baroceptor is produced using BOSCH companies.
BMP085 is a high accuracy, the pressure sensor of super low energy consumption, can be applied in a mobile device.Its performance
Brilliance, absolute precision is minimum can to reach 0.03hPa, and power consumption is extremely low, only 3 μ A.
BMP085 can pass through I using powerful 8-pin ceramic leadless chips carrying (LCC) Ultrathin packaging2C buses
Directly it is connected with various microprocessors.Nacelle controlling system casing non-tight, baroceptor is directly welded on mainboard, double
Redundancy backup.
2.2.6 the outer electrical control cubicles design of tank
Tank outer control cabinet is made up of power supply module, image processing system, environmental control module, comprehensive control module.Power supply
Module provides 24V direct current controllable direct current power supplies by AC/DC power modules for below deck equipment；Image processing system is received in cabin
Image photooptical data, and be reduced to picture signal and be acquired, store, forward, at the same also bear whole system monitoring and
Communication work, include the display control of indoor environment situation, below deck equipment is for power-off control and the communication between master control；Ring
Border control module is communicated by RS485 with the environment acquisition module in cabin, can control electricity according to Current Temperatures and desired temperature
Heating plate supplies power-off, to maintain temperature in cabin to be communicated in setting range, while with image processing workstations by RS485,
The instruction of acceptable images processing workstation, heating plate is carried out for power-off control.Comprehensive control module module is mainly responsible for will
The confession powering-off state of system is supplied to master control, can be in the confession power-off of environmental Kuznets Curves cabinet or master control control whole system.
2.2.7 image processing system
Image processing system is mainly responsible for the image data acquiring of thermal imaging system, storage.Mainly by work station, Camlink
Fiber optic switching module, Camlink capture cards etc. form.
Image processing system mainly by configure the work station of Camlink capture cards and solid state hard disc, fiber optic switching module and
Acquisition process software forms.View data caused by thermal imaging system is believed by fiber optic switching module by Camlink interface conversions for light
Number, transmitted by crossing cabin optical fiber to switch board out of my cabin, Camlink is given after being converted into Camlink signals by fiber optic switching module
After capture card collection, acquisition process software is being locally stored.
2.3 thermal control design
According to equipment compartment configuration feature and mission requirements, mainly take logical inside equipment compartment case temperature control box equipment compartment
The design that wind heat exchange is combined：
A) spraying of equipment compartment inner and outer surfaces is pitch-dark, strengthens its radiation heat transfer with inside and outside environment；
B) equipment compartment inner surface pastes electric heater, accurately controls its temperature range.
C) ventilation heat exchange in equipment compartment：
D) position being adapted in equipment compartment sets fan so that air flow in cabin, strengthens the radiating effect of thermal imaging system；
E) electric heater is pasted on thermal imaging system housing, its temperature range is adjusted.
F) equipment compartment surfaces externally and internally sprays pitch-dark, with enhanced rad heat-sinking capability；
G) 5mm fiberglass heat insulating mattress is padded between equipment compartment and internal stent and is thermally shielded installation；
H) equipment compartment front end exterior surface takes multilayer insulation thermal control component to coat, and reduces bulkhead temperature to measured target
Influence；
I) equipment compartment surface mount heater carries out temperature control.
J) fan is being set, air outlet velocity 1m/s, wind direction is with dissipating above thermal imaging system at face thermal imaging system heat sink
Hot plate is parallel, strengthens heat sink radiating；
K) fan is set at thermal imaging system rear portion, and V-arrangement heat-conducting plate is designed in air outlet, strengthens internal gas and equipment
The heat convection effect of cabin side wall.
L) true qualities anodization is taken on the surface such as support, environmental control, strengthens heat loss through radiation；
M) environmental control surface mount electric heater, its temperature levels is controlled；
N) heater is pasted in two sides of thermal imaging system, to control thermal imaging system temperature levels.
Heating resource such as table 5 needed for estimation at present, the control and data acquisition of heating circuit and observing and controlling temperature are by environment
Controller is realized.
The electrical heating resource requirement of table 5
| Sequence number | Position | Heater way | Heating power W | Pt resistance quantity |
| 1 | Equipment compartment surface | 4 | 150 | 4 |
| 2 | Thermal imaging system surface | 2 | 30 | 5 |
| 3 | Environmental control | 1 | 10 | 1 |
| It is total | 7 | 190 | 10 |
3rd, application example
In hot vacuum environment, entrance pupil mode is covered using big face source low temperature black matrix radiation calibration is carried out to the system.Mark
Determine curve such as Fig. 2.
Test result shows, for Low Temperature Target, using the 1200 microsecond times of integration, when optical system works temperature -30
DEG C when, preferable linearity measure ability is respectively provided with to 150K (- 123 DEG C) even more Low Temperature Targets.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (10)
- A kind of 1. ground heat test Low Temperature Target infrared radiation measurement device, it is characterised in that：Including measurement apparatus and control machine Cabinet；The measurement apparatus includes equipment compartment agent structure, infrared optical window, closed type charging and discharging valve and interface, closed type Electric connector, temperature sensor, pressure sensor, heating plate, multilayer insulation component, thermal-control circuit, bracket, thermal infrared imager, Cabin controlling system；The equipment compartment agent structure includes nacelle, protecgulum, bonnet；Infrared optical window is arranged on protecgulum, after Cover installation sealed type electric connector and closed type charging and discharging valve and interface；Thermal infrared imager is arranged on the support in equipment compartment body On frame, for gathering target information；Nacelle inner surface sticking heating plates；Arrangement multipoint temperature sensor, pressure sensing in nacelle Device, and pass through the temperature in thermal-control circuit control cabinet body；Preceding exterior surface is coated using multilayer insulation component；The nacelle internal control System processed is used for below deck equipment power supply, environmental monitoring and data acquisition, and the data collected are sent into control rack.
- A kind of 2. ground heat test Low Temperature Target infrared radiation measurement device according to claim 1, it is characterised in that：Institute State measurement apparatus to be placed in vacuum tank, control rack is placed on outside vacuum tank.
- A kind of 3. ground heat test Low Temperature Target infrared radiation measurement device according to claim 1, it is characterised in that： Top and rear portion in the equipment compartment body are provided with hot-swappable fans, and install V-type deflector in air outlet.
- A kind of 4. ground heat test Low Temperature Target infrared radiation measurement device according to claim 1, it is characterised in that：Institute Stating nacelle controlling system includes DC/DC power conversion modules, fiber optic switching module, environment acquisition module；Wherein DC/DC power supplys Conversion module is used to power for thermal infrared imager and other below deck equipments；Fiber optic switching module is used for the image of thermal infrared imager Signal is converted into optical signal and sent to out of my cabin；Environment acquisition module is used to gather temperature and pressure data in cabin, and will collection As a result send to out of my cabin.
- A kind of 5. ground heat test Low Temperature Target infrared radiation measurement device according to claim 1, it is characterised in that：Institute It is 304 stainless steels to state equipment compartment agent structure material, and it is pitch-dark that cabin inner and outer surfaces spray thermal control.
- A kind of 6. ground heat test Low Temperature Target infrared radiation measurement device according to claim 1, it is characterised in that：Institute Stating closed type charging and discharging valve and interface includes valve, interface and plug, and valve uses hand stop valve, and inflation/deflation interface uses 37 ° of spherical interfaces, and sealed with plug.
- A kind of 7. ground heat test Low Temperature Target infrared radiation measurement device according to claim 1, it is characterised in that：Institute State and connected between nacelle and protecgulum and bonnet with flange, aviation nitrile rubber sealing ring is used at flange-interface.
- A kind of 8. ground heat test Low Temperature Target infrared radiation measurement device according to claim 1, it is characterised in that：Institute State on the bracket that thermal infrared imager is tiltedly mounted in equipment compartment body, inclination angle is 13 °.
- A kind of 9. ground heat test Low Temperature Target infrared radiation measurement device according to claim 1, it is characterised in that：Institute Measurement apparatus is stated with control rack by the socket through walls on vacuum tank to be connected.
- 10. a kind of carry out ground heat test Low Temperature Target infrared radiation measurement using the arbitrarily described measurement apparatus of claim 1-9 Method, it is characterised in that it is as follows using step：1) front opening equipment compartment protecgulum is tested, thermal infrared imager is arranged in equipment compartment, passes through closed type inflation/deflation after installation Interface nitrogen displacement wherein air, ensure the atmospheric pressure of pressure 1~1.2 in cabin, inflation inlet is closed after 10 minutes, capping plug is prevented Leak-stopping gas；2) airtight test is integrally carried out to equipment compartment；3) measurement apparatus is arranged in vacuum and low temperature container, cable connection inside and outside tank is completed by plug through walls；4) equipment compartment vivo environment temperature and pressure is monitored in real time by temperature sensor, pressure sensor when testing, and is utilized Heating plate, multilayer insulation component, thermal-control circuit control indoor environment temperature to setting value；5) thermal imaging system starts measurement, passes through cabin controlling system data acquisition.
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| CN108986600A (en) * | 2018-07-17 | 2018-12-11 | 杭州电子科技大学 | A kind of compound thermal diaphragm cooling device of horizontal solar telescope |
| CN109357898A (en) * | 2018-09-27 | 2019-02-19 | 北京卫星环境工程研究所 | Spacecraft parts grade normal pressure heat test control system |
| CN110672556A (en) * | 2019-08-30 | 2020-01-10 | 中国科学院西安光学精密机械研究所 | Thermal control device of Doppler differential interferometer with high thermal stability |
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| CN111762456A (en) * | 2020-06-22 | 2020-10-13 | 中国科学院电工研究所 | Electrical equipment sealed cabin system with nitrogen gas directional temperature control function |
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| CN108401151A (en) * | 2018-03-26 | 2018-08-14 | 中国科学院新疆理化技术研究所 | Cmos image sensor single particle effect trial image online acquisition method |
| CN108469852A (en) * | 2018-04-24 | 2018-08-31 | 北京强度环境研究所 | Heating means |
| CN108986600A (en) * | 2018-07-17 | 2018-12-11 | 杭州电子科技大学 | A kind of compound thermal diaphragm cooling device of horizontal solar telescope |
| CN109357898A (en) * | 2018-09-27 | 2019-02-19 | 北京卫星环境工程研究所 | Spacecraft parts grade normal pressure heat test control system |
| CN110672556A (en) * | 2019-08-30 | 2020-01-10 | 中国科学院西安光学精密机械研究所 | Thermal control device of Doppler differential interferometer with high thermal stability |
| CN111006774A (en) * | 2019-12-06 | 2020-04-14 | 北京振兴计量测试研究所 | System and method for testing calibration blackbody radiation source manufactured by MEMS (micro-electromechanical systems) process |
| CN111006774B (en) * | 2019-12-06 | 2021-05-07 | 北京振兴计量测试研究所 | System and method for testing calibration blackbody radiation source manufactured by MEMS (micro-electromechanical systems) process |
| CN110954353A (en) * | 2019-12-23 | 2020-04-03 | 北京空间技术研制试验中心 | Cabin door heat sealing mechanism examination test device and method |
| CN111722345A (en) * | 2020-05-06 | 2020-09-29 | 哈尔滨新光光电科技股份有限公司 | Stray light suppression device |
| CN111762456A (en) * | 2020-06-22 | 2020-10-13 | 中国科学院电工研究所 | Electrical equipment sealed cabin system with nitrogen gas directional temperature control function |
| CN111762456B (en) * | 2020-06-22 | 2022-07-22 | 中国科学院电工研究所 | Electrical equipment sealed cabin system with nitrogen gas directional temperature control function |
| CN112284543A (en) * | 2020-09-17 | 2021-01-29 | 北京卫星制造厂有限公司 | Temperature field measurement system under thermal vacuum test environment |
| CN112284543B (en) * | 2020-09-17 | 2022-03-04 | 北京卫星制造厂有限公司 | Temperature field measurement system under thermal vacuum test environment |
| CN112857588A (en) * | 2021-03-01 | 2021-05-28 | 中国空气动力研究与发展中心超高速空气动力研究所 | Infrared thermal imaging measuring device for surface temperature of wind tunnel test model |
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