CN109612755A - A kind of strain measurement system and application thereof for space environmental simulation - Google Patents
A kind of strain measurement system and application thereof for space environmental simulation Download PDFInfo
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- CN109612755A CN109612755A CN201811512703.7A CN201811512703A CN109612755A CN 109612755 A CN109612755 A CN 109612755A CN 201811512703 A CN201811512703 A CN 201811512703A CN 109612755 A CN109612755 A CN 109612755A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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- G01M99/002—Thermal testing
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Abstract
The strain measurement system and application thereof that the invention discloses a kind of for space environmental simulation, which includes: for the Work container of space environmental simulation, element under test is placed in the Work container；The strain transducer being fixed on element under test；First data transmission line in Work container is set；The second data line outside Work container is set；And the signal receiving device being connect with the second data line；Wherein, first data transmission line is connect with the second data line.Strain measurement system provided by the invention, the working environment of Work container can be set according to different environmental requirements, the strain signal of element under test is obtained through strain transducer, it can strained situation of the whole record element under test in space environmental simulation change procedure, it can be achieved to any element under test and with the strain acquirement of a piece of element under test different location, it can be used for the strain testing under space environment such as solar cell, solar battery array substrate, had a good application prospect.
Description
Technical field
The present invention relates to a kind of strain detection testing devices, and in particular to a kind of strain measurement system for space environmental simulation
And application thereof.
Background technique
Environment and the energy are the two large problems of 21 century facing mankind.How to be developed more on the basis of rationally utilizing environment
Multiple-energy-source has become the challenge that the whole mankind faces jointly.In recent decades, the development and utilization of new energy are gradually connect by the mankind
By and use, make full use of solar energy source that can effectively solve the problems, such as the lack of energy of facing mankind.
Currently, solar cell is navigating because of the incident photon-to-electron conversion efficiency of its superelevation, stable working time and lighter weight
Good application has been obtained in it and great civil engineering.There are many solar cell is successfully applied to space flight both at home and abroad
Aircraft, satellite, airship and the example of space station.Solar wing is the energy source of satellite, i.e. solar energy sailboard, is a kind of receipts
Collect solar device, be usually applied to the energy supply of satellite, spaceship, it can also be used to be mounted at the top of eco-friendly car.It is logical
Often, it is made of in space using solar wing thousands of solar cells being pasted on lightweight rigidity or flexible base board.According to
Specific shape is made in the electricity consumption of satellite or space station and composite request, will be collected into space environment using photovoltage effectiveness
The energy of sunlight is converted to electric energy.
However, the aerospace craft solar wing run in space, which will receive severe space environment, to be influenced.According to information,
Vacuum degree is high in space, and space temperature difference is very big, in geostationary orbit aircraft towards the one side of the sun
Surface temperature up to 100 DEG C or more, and away from the sun one side surface temperature then at -80 DEG C or less.Aerospace craft exists
The 5-10 year being on active service in space tens of thousands of can pass through secondaryly high-temperature area and low-temperature region, and solar wing can undergo tens of thousands of height
The test of true temp impact, and solar cell can then be subjected to especially severe space environment shadow during high/low temperature alternation
It rings.
Therefore, deformation of the solar cell being accurately characterized on solar wing under the influence of being subjected to space adverse circumstances, can
Help researcher effectively grasps and controls solar battery array under space environment deformation, reduction because of temperature alternating caused by too
Rupture caused by positive electricity pond thermal stress is concentrated, guarantees normal in the power of orbit aerocraft, effectively improves China's aerospace craft
Reliability.However, there is no relevant researchs for the strain to solar battery array under the influence of space environment both at home and abroad at present, to too
The characterization of stress variation of the positive cell array under space environment is also without the method for corresponding ripeness standard.
Summary of the invention
To solve the above problems, the purpose of the present invention is to provide a kind of strain testing systems under space environmental simulation
System.
In order to achieve the above object, the present invention provides a kind of strain measurement system for space environmental simulation, packets
Contain:
For the Work container of space environmental simulation, element under test is placed in the Work container；
The strain transducer being fixed on the element under test；
First data transmission line in the Work container is set；
The second data line outside the Work container is set；And
The signal receiving device being connect with the second data line；
Wherein, the first data transmission line is connect with the second data line；By in Work container and working
The connection of data line outside container is, it can be achieved that vacuum degree in Work container and temperature controlled guarantee.
Preferably, the test macro includes: the heating device for heating up to Work container.
Preferably, Work container selection air dry oven, heating in vacuum case, vacuum coating equipment and the thermal vacuum heating
Any one in tank.
Preferably, the element under test includes solar cell, solar battery array substrate and solar cell and sun electricity
It is more than any one in the adhesive between the battle array substrate of pond.
Preferably, the strain transducer selects strain ga(u)ge.
Preferably, the data line is space conducting wire, high temperature resistant wire or plain conductor.
Preferably, the signal receiving device is digital strainometer, installs in the computer equipment and oscillograph of software
Any one.
Preferably, second data line is received by the third data line and signal of signal receiving device
Device connection.
The present invention also provides a kind of purposes according to the above-mentioned strain measurement system for space environmental simulation, the surveys
Test system is for characterizing strain of the element under test under various space environments.
Preferably, the space environment is simulation space environment, high temperature low pressure vacuum, low temperature are applied to Work container
The alternate combinations of low pressure vacuum or both environment, wherein the high temperature is 30 DEG C -400 DEG C, and the low temperature is -300
℃-30℃；The vacuum degree of the low pressure vacuum is less than 104Pa, the humidity of the space environmental simulation be less than
50%.The present invention applies space environmental simulation to the element under test in Work container, it can be achieved that approximation to space adverse circumstances
Simulation, space environmental simulation, shows element under test and the consistent strain effects of space environment to greatest extent.Therefore, it utilizes
Method provided by the invention can the deformation that is occurred of element under test effectively under simulation and reduction space environment.
The working environment of Work container can be arranged in strain measurement system provided by the invention according to different environmental requirements,
Element under test is placed in the working environment of simulation, the strain signal tested through strain transducer, by being separately positioned on work
First data transmission line and the second data line inside and outside container, send signal receiving device for the strain signal, this is
Structure of uniting is simple, reusable, at low cost, can strain of the whole record element under test in space environmental simulation change procedure
Situation is realized to any element under test and with the strain acquirement of a piece of element under test different location, is particularly suitable for sun electricity
The stress under space environment of binder between pond, solar battery array substrate and solar cell and solar battery array substrate
Test, has a good application prospect.
Detailed description of the invention
Fig. 1 is a kind of structural schematic diagram of strain measurement system for space environmental simulation of the invention.
Fig. 2 is to be obtained in the embodiment of the present invention 5 using strain testing method of the solar cell under space environmental simulation
Solar cell strain curve.
Specific embodiment
Below in conjunction with drawings and examples, the following further describes the technical solution of the present invention.
It is as shown in Figure 1 a kind of strain measurement system for space environmental simulation of the invention, it includes:
For the Work container 10 of space environmental simulation, element under test 1 is placed in the Work container 10；
The strain transducer 20 being fixed on the element under test；
First data transmission line 30 in the Work container 10 is set；
The second data line 40 outside the Work container 10 is set；And
The signal receiving device 50 being connect with the second data line；
Wherein, the first data transmission line 30 is connect with the second data line 40.
Second data line 40 is received by the third data line 60 and signal of signal receiving device and is filled
Set 50 connections.
The Work container 10 selects in air dry oven, heating in vacuum case, vacuum coating equipment and thermal vacuum heating tank
Any one.
The element under test 1 includes solar cell, solar battery array substrate and solar cell and solar battery array base
It is more than any one in the binder between plate.
The solar cell includes crystal-silicon solar cell, silicon-based thin film solar cell, compound film solar cell, has
Machine thin film solar cell or group Ⅲ-Ⅴ compound semiconductor solar cell；The silicon-based thin film solar cell includes amorphous silicon
Solar cell, flexible silicon-based thin film solar cell and more piece laminated silicon-base film solar cell；The compound film sun
Battery includes CIGS thin-film solar cell and cadmium telluride film solar cells, and the organic film solar cell includes dye
Material sensitization solar cell, perovskite solar cell, copper-zinc-tin-sulfur solar cell and artificial gold solar cell, III-V race
Compound semiconductor solar cell includes unijunction gallium arsenide solar cell, multijunction gallium arsenide solar cell and fexible film GaAs
Solar cell.The solar battery array substrate is rigid solar cell array substrate or flexible solar cell array substrate；Described
Rigid solar cell array substrate include rigid aluminum honeycomb substrate, rigid aluminium sheet, rigid Polymethacrylimide (PMI) substrate,
Rigid NOMEX honeycomb substrate, the flexible base board include pet substrate and PI substrate.The binder is one component room temperature
Sulphurated siliastic or double component room temperature vulcanization silicon rubber.
Strain transducer can be selected from the sensor of strain transducer field routine specification, but need meet with
Lower requirement: (1) selected strain transducer will not react or degrade under space environmental simulation.(2) selected to answer
Become sensor needs to use under certain high and low temperature environment and vacuum environment.(3) selected strain transducer does not need again
By processing (such as soldering and insulation processing).Preferably, the strain transducer is high/low temperature specific use sensing
Strain ga(u)ge may be selected in device.The strain transducer with a thickness of 0.01-0.5mm, preferably 0.05mm；Width is 3-
8mm, preferably 4mm；Length is 7-15mm, preferably 9mm.
The data line is space conducting wire, high temperature resistant wire or plain conductor.
The signal receiving device is digital strainometer, installs the computer equipment of software and any one in oscillograph
Kind.
In some preferred embodiments, the test macro also includes: the heating dress for heating up to Work container 10
Set 70.
Test macro of the invention can apply Work container for characterizing strain of the element under test under various space environments
Increasing temperature the alternate combinations of low pressure vacuum, low-temperature and low-pressure vacuum or both environment, wherein high temperature is 30 DEG C -400 DEG C,
Preferably 30 DEG C -150 DEG C；Low temperature is -300 DEG C -30 DEG C, preferably -135 DEG C -30 DEG C；The vacuum degree of low pressure vacuum be less than
104Pa, preferably less than 10Pa, further preferably less than 10-3；The humidity of the space environmental simulation is less than 50%.
The number of the alternate combinations circulation is 1.5-100 times, preferably 1.5-6.5 times.
Strain testing method provided by the invention under space environmental simulation the following steps are included:
Step 1, strain transducer and element under test are pasted by adhesive, finger pressure makes strain transducer and member to be measured
There is no bubble presence between part, the two is equably pasted together by adhesive thickness；
Step 2, the first data transmission line in the Work container of strain transducer and space environmental simulation is connected；
Step 3, the second data line outside Work container is connect with signal receiving device；
Step 4, first data transmission line and the second data line are connected, and debugs signal；
Step 5, space environmental simulation is applied to element under test by Work container, acquires element under test under the environment and generates
Strain.
Adhesive described in step 1 can be selected from the material of adhesive field routine specification, but be needed full
Foot is claimed below: (1) selected adhesive will not react with strain transducer or element under test surface.(2) selected
Adhesive needs used under certain high temperature, low temperature environment and vacuum environment.Preferably, selected adhesive is silicon rubber
Glue, intermediate-temperature glue, high-temperature plastic or high temperature setting glue, preferably intermediate-temperature glue.The silicon rubber is bi-component silicon rubber
Glue or one-component silicone rubber.The use temperature of silicon rubber is -200 DEG C -+200 DEG C.The solidification temperature of the high temperature setting glue is
50-300 DEG C, preferably 120 DEG C, the tolerable temperature of the high-temperature plastic are 80-400 DEG C, preferably 160 DEG C.The adhesive
Dosage be 20ul-200ul, preferably 50ul.
The connection type of the data line is conducting wire winding, manual soldering, boxing or electric resistance welding.Conducting wire is wound
Finger mutually winds the data line in the extraction wire and Work container of strain transducer.Manual soldering, which refers to, passes strain
Data line in the extraction wire and Work container of sensor welds together manually.Boxing refers to the number in Work container
A bit of according to transmission line is wound on strain transducer lead-out wire, will be welded at winding using manual soldering later.Electric resistance welding
Refer to and is welded together strain transducer extraction wire and data line in Work container in the way of resistance welding.
The first data transmission line is to connect the data line at both ends with the connection of the second data line, specific to connect
Mode includes following four:
First data transmission line and the second data line are connected respectively to the ring flange being mounted on Work container wall
On conducting wire stamen.
First data transmission line and the second data line make collection line interface respectively, and two collection line interfaces are by installing
Ring flange on Work container wall is connected.
First data transmission line is connected with the second data line one-to-one correspondence to be placed in Work container, and the second data pass
Defeated line is drawn by the gastight channels on Work container wall.
First data transmission line, which is connected with the second data line by collection line interface, to be placed in Work container, the second number
It is drawn according to transmission line by the gastight channels on Work container wall.
The debugging signal include whether measurement circuit is connected, whether test curve has signal or test curve whether just
Often.Signal is debugged according to strain acquirement field conventional method and judges that signal is normal.If test curve normally if show to survey
Examination curve has signal and measurement circuit is connected.Preferably, should include a piece of temperature-compensating plate in all test foil gauges,
The setting of the temperature-compensating plate only needs to be separately provided in software.It is further preferred that the temperature-compensating plate should be pasted onto
On special material, such as aluminium sheet, steel plate, plastic plate, glass plate or marble slab, ground is further preferably selected, the temperature-compensating plate
The material Ying Yuqi self compensation coefficient of stickup is consistent, preferably steel plate.
The shape of the solar cell is that circle, rectangle, square, one end have the rectangle of unfilled corner, one end to have unfilled corner
The shape of square or other unlisted but required test deformation.
The size of the solar cell is length: 2mm-30cm；Wide: 2mm-30cm or diameter 2mm-30cm or other are not
The shape of test deformation list but required.
The solar cell is with a thickness of 1um-50mm.
The shape of the solar battery array substrate be circle, rectangle, square, centre have circular hole or other unlisted
But the shape of required test deformation.The size of the solar battery array substrate is length: 5cm-500cm；It is wide: 1cm-400cm.Institute
The solar battery array substrate thickness stated is 1mm-200mm.
The dosage of the adhesive is 20ul-200ul.
The size of the strain transducer is length: 7mm-15mm；It is wide: 2mm-8mm.
Acquisition device used in the strain that acquisition element under test generates is to be mounted with the computer of specified acquisition software or show
Wave device.
Embodiment 1
A kind of strain measurement system under space environmental simulation is present embodiments provided to exist for testing solar battery
Strain testing method under space environmental simulation, specifically includes the following steps:
(1) strain transducer and solar cell are pasted using adhesive, specifically:
Solar cell is silicon-based thin film solar cell, and strain transducer is strain ga(u)ge, and adhesive is high-temperature plastic.It will
Adhesive is evenly coated in the back side of strain transducer, and the position of the solar cell to be pasted of strain transducer alignment uses
Sensor is fixed on solar cell paste position by finger pressure, is kept for finger pressure 2 minutes, curing time 24 hours.
(2) data line in the work tank of strain transducer and space environmental simulation after stickup is connected, specifically
Are as follows:
A, the data line in work tank vacuum coating equipment is made.
Data line required in vacuum coating equipment is all concentrated and is welded on collection line interface.The collection line interface
For electric connector.
B, using the welding method of manual soldering, by the data in the both ends conducting wire of every a piece of strain transducer and coating machine
Transmission line is connected.
(3) data line of the data line outside work tank and signal receiving device connects, specifically:
A, the data line outside vacuum coating equipment is made.
Data line required outside vacuum coating equipment is all concentrated and is welded on collection line interface.The line concentration connects
Mouth is electric connector.
B, using the welding method of manual soldering, by the other end of the data transmission line and signal receiving device outside coating machine
Data line is connected.
(4) it is connect in work tank with the outer data line of tank, and debugs signal, specifically:
It is connected with external data line by collecting line interface inside vacuum coating equipment, the collection line interface is 65 stars
Electric connector, the flange that the interior data line with outside tank of tank passes through electric connector respectively and is mounted on vacuum coating equipment tank skin
Disk is connected.
After the completion of connection, the computer for being mounted with test software is opened, debugs route, whether observation route is connected or surveys
Whether normal try curve.
(5) space environmental simulation is applied to solar cell, acquires the strain that solar cell generates under the environment, specifically:
The space environmental simulation of application is vacuum 10-3Pa after applying 30 minutes, continues to keep the continuous state vacuumized, this
When to vacuum coating equipment apply high temperature, realized by the heating tube inside coating machine, heating rate be 10 DEG C/min, be heated to
120 minutes are kept the temperature after 200 DEG C, heating device is closed later, is cooled to room temperature with coating machine.It is adopted using test computer whole process
Collect strain value.
Embodiment 2
A kind of strain measurement system under space environmental simulation is present embodiments provided to exist for testing solar battery
Strain testing method under space environmental simulation, specifically includes the following steps:
(1) strain transducer and solar cell are pasted using adhesive, specifically:
Solar cell is multijunction gallium arsenide solar cell, and strain transducer is strain ga(u)ge, and adhesive is silicon rubber.It will
Adhesive is evenly coated in the back side of strain transducer, and the position of the solar cell to be pasted of strain transducer alignment uses
Sensor is fixed on solar cell paste position by finger pressure, is kept for finger pressure 1 minute, curing time 36 hours.
(2) data line in the thermal vacuum tank of strain transducer and space environmental simulation after stickup is connected, tool
Body are as follows:
A, the data line in thermal vacuum tank is connected.
Data line required in thermal vacuum tank is all concentrated and is welded on the conducting wire stamen of tank skin inner flange.
B, using the welding method of manual soldering, by the number in the both ends conducting wire of every a piece of strain transducer and thermal vacuum tank
It is connected according to transmission line.
(3) data line of the data line outside thermal vacuum tank and signal receiving device connects, specifically:
A, the data line outside thermal vacuum tank is connected.
Data line required outside thermal vacuum tank is all concentrated and is welded on the conducting wire stamen of tank skin outward flange disk.
B, using the welding method of electric resistance welding, the data of data line and signal receiving device outside thermal vacuum tank are passed
Defeated line is connected.
(4) it is connect in thermal vacuum tank with the outer data line of tank, and debugs signal, specifically:
It connect inside thermal vacuum with external data line and is connected by the line stamen of the ring flange on tank skin, the method
The line stamen of blue disk is 55 star electric connectors.
After the completion of connection, the computer for being mounted with test software is opened, debugs route, whether observation route is connected or surveys
Whether normal try curve.
(5) space environmental simulation is applied to solar cell, acquires the strain that solar cell generates under the environment, specifically:
The space environmental simulation of application is vacuum 10-4Pa after applying 120 minutes, continues to keep the continuous state vacuumized, this
When to thermal vacuum tank apply high temperature, realized by the infrared heating pipe inside thermal vacuum tank, heating rate be 6 DEG C/min, add
Heat is to keeping the temperature 30 minutes after 180 DEG C.Cooling device is opened later, it is cooling using liquid nitrogen cooling, -90 are cooled to after 90 minutes
℃.Heat preservation starts to warm up after 30 minutes, keeps the temperature 30 minutes after rising to 180 DEG C.Heating device is closed later, it is cooling with thermal vacuum tank
To room temperature.Use the strain value of test computer whole process acquisition solar cell.
Embodiment 3
A kind of strain measurement system under space environmental simulation is present embodiments provided to exist for testing solar battery
Strain testing method under space environmental simulation, specifically includes the following steps:
(1) strain transducer and solar cell are pasted using adhesive, specifically:
Solar cell is unijunction gallium arsenide solar cell, and strain transducer is strain ga(u)ge, and adhesive is normal temperature cure
Glue.Adhesive is evenly coated in the back side of strain transducer, strain transducer is aligned to the position of the solar cell to be pasted,
Sensor is fixed on solar cell paste position using finger pressure, is kept for finger pressure 2 minutes, curing time 36 hours.
(2) data line in the vacuum coating equipment of strain transducer and space environmental simulation after stickup is connected,
Specifically:
A, the data line in vacuum coating equipment is made.
Data line required in vacuum coating equipment is all concentrated and is welded in tank on electric connector.
B, using the welding method of electric resistance welding, the data in the both ends conducting wire of every a piece of strain transducer and coating machine are passed
Defeated line is connected.
(3) data line of the data line outside vacuum coating equipment and signal receiving device connects, specifically:
A, the data line outside vacuum coating equipment is connected.
Data line required outside vacuum coating equipment is all concentrated and is welded on tank male electrical connector.
B, using the welding method of electric resistance welding, by the other end of the data line outside coating machine and signal receiving device
Data line is connected.
(4) it is connect in work tank with the outer data line of tank, and debugs signal, specifically:
It connect inside vacuum coating equipment with external data line and is connected by electrical connector interface, the electrical connection
Device is 65 star interface electric connectors.Air-tight interfaces are installed by the tapping reserved in vacuum coating equipment wall, the outer cable of tank passes through
The air-tight interfaces are drawn and are attached outside tank with signal receiving device.
After the completion of connection, the oscillograph that test uses is opened, debugs route, whether observation route is connected or tests song
Whether line is normal.
(5) space environmental simulation is applied to solar cell, acquires the strain that solar cell generates under the environment, specifically:
The space environmental simulation of application is vacuum 10-3Pa after applying 120 minutes, continues the state for keeping vacuumizing, at this time
High temperature is applied to vacuum coating equipment, is realized by the heating tube inside coating machine, heating rate is 6 DEG C/min, is heated to 180
30 minutes are kept the temperature after DEG C, heating device is closed later, is cooled to room temperature with coating machine.It is acquired using test scope whole process
The strain value of solar cell.
Embodiment 4
A kind of strain measurement system under space environmental simulation is present embodiments provided to exist for testing solar battery
Strain testing method under space environmental simulation, specifically includes the following steps:
(1) strain transducer and solar cell are pasted using adhesive, specifically:
Solar cell is multijunction gallium arsenide solar cell, and strain transducer is strain ga(u)ge, and adhesive is normal temperature cure
Glue.Adhesive is evenly coated in the back side of strain transducer, strain transducer is aligned to the position of the solar cell to be pasted,
Sensor is fixed on solar cell paste position using finger pressure, is kept for finger pressure 1 minute, curing time 24 hours.
(2) data line in the thermal vacuum tank of strain transducer and space environmental simulation after stickup is connected, tool
Body are as follows:
A, the data line in thermal vacuum tank is made.
One end of data line required in thermal vacuum tank is all concentrated and is welded in tank on electric connector.
B, using the welding method of manual soldering, by the number in the both ends conducting wire of every a piece of strain transducer and thermal vacuum tank
It is connected according to the transmission line other end.
(3) data line of the data line outside thermal vacuum tank and signal receiving device connects, specifically:
A, the data line outside thermal vacuum tank is connected.
Data line required outside thermal vacuum tank is all concentrated and is welded on tank male electrical connector.
B, using the welding method of manual soldering, the other end of the data line outside thermal vacuum tank and signal is received and filled
The data line set is connected, and packet insulating tape carries out insulation.
(4) it is connect in thermal vacuum tank with the outer data line of tank, and debugs signal, specifically:
It connect inside thermal vacuum tank with external data line and is connected by electrical connector interface, the electric connector
For 65 star interface electric connectors.Pass through electric connector respectively with the data line outside tank in tank and is mounted on thermal vacuum tank tank skin
On ring flange be connected.
After the completion of connection, the computer that test uses is opened, debugs route, observation route whether is connected or test curve
It is whether normal.
(5) space environmental simulation is applied to solar cell, acquires the strain that solar cell generates under the environment, specifically:
The space environmental simulation of application is vacuum 10-4Pa after applying 120 minutes, continues to keep the continuous state vacuumized, this
When to thermal vacuum tank apply high temperature, realized by the lamp array inside thermal vacuum tank, heating rate be 8 DEG C/min, be heated to 130
60 minutes are kept the temperature after DEG C.Cooling device is opened later, it is cooling using liquid nitrogen cooling, -120 DEG C are cooled to after 180 minutes.It protects
Temperature starts to warm up after sixty minutes, according to heating mode and heat preserving mode consistent with the above, carries out 6 high temperature and low temperature altogether
Circulation keeps the temperature 60 minutes after being continuously heating to 130 DEG C at the end of the last one recycles low-temperature insulation.Heating device is closed later,
It is cooled to room temperature with thermal vacuum tank.Use the strain value of test computer whole process acquisition solar cell.
Embodiment 5
A kind of strain measurement system under space environmental simulation is present embodiments provided to exist for testing solar battery
Strain testing method under space environmental simulation, specifically includes the following steps:
(1) strain transducer and solar cell are pasted using adhesive, specifically:
Solar cell is multijunction gallium arsenide solar cell, and strain transducer is strain ga(u)ge, and adhesive is normal temperature cure
Glue.Adhesive is evenly coated in the back side of strain transducer, strain transducer is aligned to the position of the solar cell to be pasted,
Sensor is fixed on solar cell paste position using finger pressure, is kept for finger pressure 2 minutes, curing time 24 hours.
(2) data line in the thermal vacuum tank of strain transducer and space environmental simulation after stickup is connected, tool
Body are as follows:
A, the data line in thermal vacuum tank is made
One end of data line required in thermal vacuum tank is all concentrated and is welded in tank on electric connector.
B, using the welding method of manual soldering, by the number in the both ends conducting wire of every a piece of strain transducer and thermal vacuum tank
It is connected according to the transmission line other end.
(3) data line of the data line outside thermal vacuum tank and signal receiving device connects, specifically:
A, the data line outside thermal vacuum tank is connected.
Data line required outside thermal vacuum tank is all concentrated and is welded on tank male electrical connector.
B, using the welding method of manual soldering, the other end of the data line outside thermal vacuum tank and signal is received and filled
The data line set is connected, and packet insulating tape carries out insulation.
(4) it is connect in thermal vacuum tank with the outer data line of tank, and debugs signal, specifically:
It connect inside thermal vacuum tank with external data line and is connected by electrical connector interface, the electric connector
For 65 star interface electric connectors.Pass through electric connector respectively with the data line outside tank in tank and is mounted on thermal vacuum tank tank skin
On ring flange be connected.
After the completion of connection, the computer that test uses is opened, debugs route, observation route whether is connected or test curve
It is whether normal.
(5) space environmental simulation is applied to solar cell, acquires the strain that solar cell generates under the environment, specifically:
The space environmental simulation of application is vacuum 10-3Pa after applying 240 minutes, continues to keep the continuous state vacuumized, this
When to thermal vacuum tank apply high temperature, realized by the lamp array inside thermal vacuum tank, heating rate be 7 DEG C/min, be heated to 135
120 minutes are kept the temperature after DEG C.Cooling device is opened later, it is cooling using liquid nitrogen cooling, it is cooled to -123 DEG C and keeps the temperature 120 points
Clock starts to warm up later, and according to heating mode and heat preserving mode consistent with the above, 120 points are kept the temperature after being continuously heating to 135 DEG C
Clock.Heating device is closed later, is cooled to room temperature with thermal vacuum tank.Use the strain of test computer whole process acquisition solar cell
Value, does strain curve figure as shown in Fig. 2, the curve has recorded solar cell in 1.5 vacuum high/low temperature cyclic processes in real time
The strain variation of generation.
Embodiment 6
A kind of strain measurement system under space environmental simulation is present embodiments provided to exist for testing solar battery
Strain testing method under space environmental simulation, specifically includes the following steps:
(1) strain transducer and solar cell are pasted using adhesive, specifically:
Solar cell is perovskite solar cell, and strain transducer is strain ga(u)ge, and adhesive is high temperature setting glue.It is logical
The operation for crossing " first gluing is pasted again in solar battery surface " pastes strain transducer and solar cell, i.e., adhesive is uniform
Ground is coated in the surface of the solar cell to be pasted, and adhesive is made uniformly thinly to cover one layer of surface in institute's paste position,
The area of adhesive coating is equal to the area of strain transducer.By the position of the solar cell to be pasted of strain transducer alignment
It sets, sensor is fixed on solar cell paste position using finger pressure, is kept for finger pressure 2 minutes.High-temperature pressurizing solidification is carried out later,
It is specially pressed using mold to foil gauge, pressure pressure is 20Kg, and pressure temperature is 120 DEG C, and pressure is complete after 48 hours
At solidification.
(2) data line in the vacuum tank of strain transducer and space environmental simulation after stickup is connected, specifically
Are as follows:
A, the data line in thermal vacuum tank is made.
One end of data line required in thermal vacuum tank is all concentrated and is welded in tank on electric connector, it is described
Electric connector is 55 star interface electric connectors.
B, using the welding method of electric resistance welding, by the data in the both ends conducting wire of every a piece of strain transducer and thermal vacuum tank
The transmission line other end is connected.
(3) data line of the data line outside vacuum tank and signal receiving device connects, specifically:
A, the data line outside thermal vacuum tank is connected
Data line required outside thermal vacuum tank is all concentrated and is welded on tank male electrical connector.
B, using the welding method of electric resistance welding, by the other end and signal receiving device of the data line outside thermal vacuum tank
Data line be connected, and packet insulating tape carries out insulation.
(4) it is connect in work tank with the outer data line of tank, and debugs signal, specifically:
It connect inside thermal vacuum tank with external data line and is connected by electrical connector interface, the electric connector
For 55 star interface electric connectors.Pass through electric connector respectively with the data line outside tank in tank and is mounted on thermal vacuum tank tank skin
On ring flange be connected.
After the completion of connection, the computer that test uses is opened, debugs route, observation route whether is connected or test curve
It is whether normal.
(5) space environmental simulation is applied to solar cell, acquires the strain that solar cell generates under the environment, specifically:
The space environmental simulation of application is vacuum 10-4Pa applies and continues to keep the continuous state vacuumized after twenty minutes, this
When to thermal vacuum tank apply high temperature, realized by the infrared lamp arrays inside thermal vacuum tank, heating rate be 5 DEG C/min, heating
To keeping the temperature 20 minutes after 120 DEG C.Cooling device is opened later, it is cooling using liquid nitrogen cooling, -130 are cooled to after 240 minutes
℃.Heat preservation starts to warm up after twenty minutes, according to heating mode and heat preserving mode consistent with the above, carry out altogether 3 high temperature with
The circulation of low temperature keeps the temperature 20 minutes after being continuously heating to 120 DEG C at the end of the last one recycles low-temperature insulation.It closes and adds later
Thermal, thermal vacuum tank are cooled to room temperature.Use the strain value of test computer whole process acquisition solar cell.
Embodiment 7
A kind of strain measurement system under space environmental simulation is present embodiments provided for testing solar battery battle array
Strain testing method of the substrate under space environmental simulation, specifically includes the following steps:
(1) using adhesive by strain transducer and solar battery array substrate sticking, specifically:
Solar battery array substrate is rigid aluminum honeycomb substrate, and strain transducer is strain ga(u)ge, and adhesive is solid for room temperature
Change glue.Make strain transducer and solar battery array substrate sticking by the operation of " first gluing is pasted again in strain transducer ".Tool
Body are as follows: adhesive is equably coated in the back side of strain transducer, adhesive is made uniformly thinly to cover one layer in strain sensing
The back side of device；By the position of the solar battery array substrate to be pasted of strain transducer alignment, sensor is fixed using finger pressure
In solar battery array substrate sticking position, kept for finger pressure 2 minutes, curing time 24 hours.
(2) data line in the heating in vacuum case of strain transducer and space environmental simulation after stickup is connected,
Specifically:
A, the data line in heating in vacuum case is made
Data line required in heating in vacuum case is all concentrated and is welded in case on electric connector.
It b, will be in the both ends conducting wire of every a piece of strain transducer and heating in vacuum case using the welding method of manual soldering
Data line is connected.
(3) data line of the data line outside heating in vacuum case and signal receiving device connects, specifically:
A, the data line outside heating in vacuum case is connected.
Data line required outside heating in vacuum case is all concentrated and is welded on case male electrical connector.
B, using the welding method of manual soldering, the other end of the data line outside heating in vacuum case and signal are received
The data line of device is connected.
(4) it is connect in heating in vacuum case with the outer data line of case, and debugs signal, specifically:
It connect inside heating in vacuum case with external data line and is connected by electrical connector interface, the electrical connection
Device is 65 star interface electric connectors.Air-tight interfaces are installed by the tapping reserved in heating in vacuum case tank wall, the outer cable of tank is logical
It crosses outside air-tight interfaces extraction tank and is attached with signal receiving device.
After the completion of connection, the computer that test uses is opened, debugs route, observation route whether is connected or test curve
It is whether normal.
(5) space environmental simulation is applied to solar battery array substrate, acquires what solar battery array substrate under the environment generated
Strain, specifically:
The space environmental simulation of application is vacuum 10Pa, after applying 120 minutes, continues the state for keeping vacuumizing, at this time
High temperature is applied to heating in vacuum case, is realized by the heating muff inside heating in vacuum case, heating rate is 4 DEG C/min, is added
Heat is closed heating component later, is cooled to room temperature with heating in vacuum case to keeping the temperature 120 minutes after 180 DEG C.It is complete using test computer
The strain value of journey acquisition solar battery array substrate.
Embodiment 8
A kind of strain measurement system under space environmental simulation is present embodiments provided to exist for testing solar battery
Strain testing method under space environmental simulation, specifically includes the following steps:
(1) strain transducer and solar cell are pasted using adhesive, specifically:
Solar cell is dye-sensitized solar cells, and strain transducer is strain ga(u)ge, and adhesive is high temperature setting glue.
The operation of " first gluing is pasted again in strain transducer " pastes strain transducer and solar cell, specifically: adhesive is equal
It is coated in the back side of strain transducer evenly, adhesive is made uniformly thinly to cover one layer of back side in strain transducer；It will strain
Sensor is fixed on solar cell paste position using finger pressure by the position of the solar cell to be pasted of sensor alignment, is protected
Hold finger pressure 1 minute.High-temperature pressurizing solidification is carried out later, is specially pressed using mold to foil gauge, and pressure pressure is
40Kg, pressure temperature are 90 DEG C, and pressure completes solidification after 72 hours.
(2) data line in the work tank of strain transducer and space environmental simulation after stickup is connected, specifically
Are as follows:
A, the data line in thermal vacuum tank is made
One end of data line required in thermal vacuum tank is all concentrated and is welded in tank on electric connector, it is described
Electric connector is 65 star interface electric connectors.
B, using the welding method of manual soldering, by the number in the both ends conducting wire of every a piece of strain transducer and thermal vacuum tank
It is connected according to the transmission line other end.
(3) data line of the data line outside thermal vacuum tank and signal receiving device connects, specifically:
A, the data line outside thermal vacuum tank is connected.
Data line required outside thermal vacuum tank is all concentrated and is welded on tank male electrical connector.
B, using the welding method of manual soldering, the other end of the data line outside thermal vacuum tank and signal is received and filled
The data line set is connected, and packet insulating tape carries out insulation.
(4) it is connect in work tank with the outer data line of tank, and debugs signal, specifically:
It connect inside thermal vacuum tank with external data line and is connected by electrical connector interface, the electric connector
For 65 star interface electric connectors.Pass through electric connector respectively with the data line outside tank in tank and is mounted on thermal vacuum tank tank skin
On air-tight interfaces channel be connected.
After the completion of connection, the computer that test uses is opened, debugs route, observation route whether is connected or test curve
It is whether normal.
(5) space environmental simulation is applied to solar cell, acquires the strain that solar cell generates under the environment, specifically:
The space environmental simulation of application is vacuum 10-4Pa after applying 30 minutes, continues to keep the continuous state vacuumized, this
When to thermal vacuum tank apply high temperature, realized by the lamp array inside thermal vacuum tank, heating rate be 2 DEG C/min, be heated to 95
30 minutes are kept the temperature after DEG C.Cooling device is opened later, it is cooling using liquid nitrogen cooling, -130 DEG C are cooled to after 240 minutes.It protects
Temperature starts to warm up after 30 minutes, according to heating mode and heat preserving mode consistent with the above, carries out 4 high temperature and low temperature altogether
Circulation keeps the temperature 20 minutes after being continuously heating to 95 DEG C at the end of the last one recycles low-temperature insulation.Heating device is closed later,
Thermal vacuum tank is cooled to room temperature.Use the strain value of test computer whole process acquisition solar cell.
Embodiment 9
A kind of strain measurement system under space environmental simulation is present embodiments provided to exist for testing solar battery
Strain testing method under space environmental simulation, specifically includes the following steps:
(1) strain transducer and solar cell are pasted using adhesive, specifically:
Solar cell is perovskite solar cell, and strain transducer is strain ga(u)ge, and adhesive is high-temperature plastic.Pass through
The operation of " first gluing is pasted again in solar battery surface " pastes strain transducer and solar cell, i.e., equably by adhesive
It is coated in the surface of the solar cell to be pasted, adhesive is made uniformly thinly to cover one layer of surface in institute's paste position, glue
The area of glutinous agent coating is equal to the area of strain transducer.Strain transducer is aligned to the position of the solar cell to be pasted,
Sensor is fixed on solar cell paste position using finger pressure, is kept for finger pressure 2 minutes.After normal temperature and pressure solidifies 48 hours later
Complete solidification.
(2) data line in the heating in vacuum case of strain transducer and space environmental simulation after stickup is connected,
Specifically:
A, the data line in heating in vacuum case is made
Data line required in heating in vacuum case is all concentrated and is welded in case on electric connector.
B, using the welding method of electric resistance welding, by the number in the both ends conducting wire of every a piece of strain transducer and heating in vacuum case
It is connected according to transmission line.
(3) data line of the data line outside heating in vacuum case and signal receiving device connects, specifically:
A, the data line outside vacuum coating equipment is connected.
Data line required outside heating in vacuum case is all concentrated and is welded on case male electrical connector.
B, using the welding method of electric resistance welding, the other end of the data line outside heating in vacuum case and signal is received and filled
The data line set is connected.
(4) it is connect in heating in vacuum case with the outer data line of case, and debugs signal, specifically:
It connect inside heating in vacuum case with external data line and is connected by electrical connector interface, the electrical connection
Device is 55 star interface electric connectors.Cable outside tank and cable in tank are electrically connected by ring flange on heating in vacuum case tank wall
Device is connect to be attached.
After the completion of connection, the oscillograph that test uses is opened, debugs route, whether observation route is connected or tests song
Whether line is normal.
(5) space environmental simulation is applied to solar cell, acquires the strain that solar cell generates under the environment, specifically:
The space environmental simulation of application is vacuum 5Pa, after applying 120 minutes, continues the state for keeping vacuumizing, right at this time
Heating in vacuum case applies high temperature, is realized by the heating muff inside heating in vacuum case, and heating rate is 2 DEG C/min, heating
To keeping the temperature 60 minutes after 100 DEG C, heating component is closed later, heating in vacuum case is cooled to room temperature.Use test scope
The strain value of whole process acquisition solar cell.
Embodiment 10
Present embodiments provide a kind of strain measurement system under space environmental simulation for testing solar battery with
Strain testing method of the binder (binder to be measured) under space environmental simulation between solar battery array substrate, specifically includes
Following steps:
(1) strain transducer and binder to be measured are pasted, specifically:
Binder between solar cell and solar battery array substrate is double component room temperature vulcanization silicon rubber, strain transducer
For strain ga(u)ge, adhesive is normal temperature cure glue.Strain is passed by the operation of " first gluing is pasted again in strain transducer "
Sensor and binder to be measured are pasted.Specifically: adhesive is equably coated in the back side of strain transducer, keeps adhesive uniformly thin
Unfertile land covers one layer of back side in strain transducer；By the position of the binder to be measured to be pasted of strain transducer alignment, make
Sensor is fixed on binder to be measured with finger pressure, is kept for finger pressure 1 minute, curing time 120 hours.
(2) data line in the work tank of strain transducer and space environmental simulation after stickup is connected, specifically
Are as follows:
Using boxing and the united welding method of manual soldering, the both ends conducting wire of every a piece of strain transducer is done with air blast
Data line in dry case is connected.
(3) data line of the data line outside work tank and signal receiving device connects, specifically:
Using boxing and the united welding method of manual soldering, by one end of the data line outside air dry oven and letter
The data line of number reception device is connected.
(4) it is connect in work tank with the outer data line of tank, and debugs signal, specifically:
Connect with external data line inside air dry oven pass through craft soldering directly by tank with the number outside tank
According to transmission wire bonding completion, air-tight interfaces are installed by the tapping reserved in air dry oven tank wall, the outer cable of tank is by being somebody's turn to do
Air-tight interfaces are drawn outside tank.
After the completion of connection, the computer for being mounted with test software is opened, debugs route, whether observation route is connected or surveys
Whether normal try curve.
(5) space environmental simulation is applied to binder to be measured, acquires the strain that binder to be measured generates under the environment, specifically
Are as follows:
High temperature is applied to air dry oven, is realized by the heating muff inside air dry oven, heating rate 6
DEG C/min, 120 minutes are kept the temperature after being heated to 150 DEG C, heating component is closed later, is cooled to room temperature with air dry oven.
Using being mounted with that the computer whole process of test software acquires the strain value of binder to be measured.
Embodiment 11
A kind of strain measurement system under space environmental simulation is present embodiments provided to exist for testing solar battery
Strain testing method under space environmental simulation, specifically includes the following steps:
(1) strain transducer and solar cell are pasted using adhesive, specifically:
Solar cell is perovskite solar cell, and strain transducer is strain ga(u)ge, and adhesive is normal temperature cure glue.It will
Adhesive is evenly coated in the back side of strain transducer, and the position of the solar cell to be pasted of strain transducer alignment uses
Sensor is fixed on solar cell paste position by finger pressure, is kept for finger pressure 1 minute, curing time 24 hours.
(2) data line in the work tank of strain transducer and space environmental simulation after stickup is connected, specifically
Are as follows:
Using the welding method of electric resistance welding, the data in the both ends conducting wire of every a piece of strain transducer and coating machine are transmitted
Line is connected.
(3) data line of the data line outside vacuum coating equipment and signal receiving device connects, specifically:
Using the welding method of electric resistance welding, by one end of the data line outside vacuum coating equipment and signal receiving device
Data line is connected.
(4) it is connect in vacuum coating equipment with the outer data line of machine, and debugs signal, specifically:
It is connect inside vacuum coating equipment with external data line and completion is directly welded by manual soldering method, passed through
Air-tight interfaces are installed in the tapping that vacuum coating equipment machine wall is reserved, the outer cable of coating machine is drawn outside tank by the air-tight interfaces.
After the completion of connection, the computer for being mounted with test software is opened, debugs route, whether observation route is connected or surveys
Whether normal try curve.
(5) space environmental simulation is applied to solar cell, acquires the strain that solar cell generates under the environment, specifically:
The space environmental simulation of application is vacuum 10-3Pa after applying 30 minutes, continues the state for keeping vacuumizing, at this time
High temperature is applied to vacuum coating equipment, is realized by the heating muff inside vacuum coating equipment, heating rate is 10 DEG C/min, is added
Heat is closed heating component later, is cooled to room temperature with vacuum coating equipment to keeping the temperature 120 minutes after 110 DEG C.Shown using test
The strain value of wave device whole process acquisition solar cell.
The present invention mainly uses two big measures to guarantee that acquisition strain value is reliable.
Firstly, the strain transducer used is the high temperature resistant strain transducer of special strain transducer producer production,
Actual use temperature range is strict controlled in working range specified in its specification.
Secondly, can all be arranged sufficiently to exclude influence of the environmental factor to the self-deformation of foil gauge in each test
A piece of foil gauge (element under test) is used as temperature-compensating plate, to eliminate foil gauge self-deformation bring error.
The strain value for acquiring above-mentioned solar cell is mainly that react solar cell suffered under space environmental simulation
Strain stress situation, according to this strained situation, in conjunction with the mechanical stress limiting value of solar cell, so that it may find out solar cell and exist
Biggish section is strained under space environmental simulation, finds out the time zone that cell piece fragmentation easily occurs, and guidance technology personnel formulate
Corresponding design or technological measure reduce solar cell strain suffered under space environmental simulation, improve solar cell piece
The reliability of product.
By the palm evidence of the strain information to solar cell under space environmental simulation, it is equally applicable to space travel
In device because directly space environment do this test difficulty it is too big, can only by solar cell apply space environmental simulation, it is right
Collected solar cell strain data can preferably reflect aerospace craft solar cell institute in space environmental simulation
The ess-strain being subject to can then help Scientific Research Workers ahead of time to sun electricity for the space environment of large strain occurs
The improvement of technique or design is made in pond, to reduce strain value, reduces the number of tiles of solar cell, guarantees that the safety of spacecraft can
It leans on.
It is discussed in detail although the contents of the present invention have passed through above preferred embodiment, but it should be appreciated that above-mentioned
Description is not considered as limitation of the present invention.After those skilled in the art have read above content, for of the invention
A variety of modifications and substitutions all will be apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (10)
1. a kind of strain measurement system for space environmental simulation, which is characterized in that the test macro includes:
For the Work container of space environmental simulation, element under test is placed in the Work container；
The strain transducer being fixed on the element under test；
First data transmission line in the Work container is set；
The second data line outside the Work container is set；And
The signal receiving device being connect with the second data line；
Wherein, the first data transmission line is connect with the second data line.
2. being used for the strain measurement system of space environmental simulation as described in claim 1, which is characterized in that the test macro packet
Contain: the heating device for heating up to Work container.
3. being used for the strain measurement system of space environmental simulation as described in claim 1, which is characterized in that the work is held
Device selects any one in air dry oven, heating in vacuum case, vacuum coating equipment and thermal vacuum heating tank.
4. being used for the strain measurement system of space environmental simulation as described in claim 1, which is characterized in that the member to be measured
Part is comprising any in the adhesive between solar cell, solar battery array substrate and solar cell and solar battery array substrate
More than one.
5. being used for the strain measurement system of space environmental simulation as described in claim 1, which is characterized in that the strain sensing
Device selects strain ga(u)ge.
6. being used for the strain measurement system of space environmental simulation as described in claim 1, which is characterized in that the data pass
Defeated line is space conducting wire, high temperature resistant wire or plain conductor.
7. being used for the strain measurement system of space environmental simulation as described in claim 1, which is characterized in that the signal connects
Receiving apparatus is digital strainometer, the computer equipment for installing software and any one in oscillograph.
8. being used for the strain measurement system of space environmental simulation as described in claim 1, which is characterized in that second number
It is connect by the third data line of signal receiving device with signal receiving device according to transmission line.
9. a kind of use described in any one of -8 for the strain measurement system of space environmental simulation according to claim 1
On the way, which is characterized in that the test macro is for characterizing strain of the element under test under various space environments.
10. the purposes for the strain measurement system of space environmental simulation as claimed in claim 9, which is characterized in that described
Space environment be simulation space environment, to Work container apply high temperature low pressure vacuum, low-temperature and low-pressure vacuum or both
The alternate combinations of environment, wherein the high temperature is 30 DEG C -400 DEG C, and the low temperature is -300 DEG C -30 DEG C；The low gas
The vacuum degree for pressing vacuum is less than 104Pa, the humidity of the space environmental simulation are less than 50%.
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