CN208383289U - It is double to spread out solar wing vibration measurement device - Google Patents
It is double to spread out solar wing vibration measurement device Download PDFInfo
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- CN208383289U CN208383289U CN201820975898.8U CN201820975898U CN208383289U CN 208383289 U CN208383289 U CN 208383289U CN 201820975898 U CN201820975898 U CN 201820975898U CN 208383289 U CN208383289 U CN 208383289U
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Abstract
The utility model discloses a kind of pair to spread out solar wing vibration measurement device, described device spreads out solar wing including double, vibrational excitation mechanism and vibration detection mechanism, vibrational excitation mechanism spreads out solar wing with pair and connect, for motivating double solar wings that spread out to generate vibration, vibration detection mechanism includes two groups of binocular vision systems and two truss, it is arranged in parallel before and after two truss, two groups of binocular vision systems and two truss correspond, and every group of binocular vision system is arranged on corresponding truss, two groups of binocular vision systems for detect it is double spread out solar wing before, the vibration detection index point region of rear upper surface.The utility model is by two groups of binocular vision system settings on two front and back truss disposed in parallel, it is detected using vibration detection index point region of two groups of binocular vision systems to double front and rear portions upper surfaces for spreading out solar wing, non-contact measurement can be carried out to double solar wings that spread out, obtain double spreading out the more accurate vibration information of solar wing.
Description
Technical field
The utility model relates to a kind of vibration measurement device, especially a kind of pairs to spread out solar wing vibration measurement device, belong to
In vibration measurement field.
Background technique
In recent years, the complexity for the task that spacecraft is undertaken is continuously increased, and requirement of the people to its structure is higher and higher,
On the one hand it requires to improve bearing capacity, on the one hand requires the gross mass for reducing structure, therefore, spacecraft is towards Low rigidity, flexibility
Change, the trend development of enlargement, the big flexible big feature for becoming modern spacecraft.Flexible structure is widely present in spacecraft
In, such as the solar energy sailboard structure of satellite or space work station, space flight wing, space station flexible mechanical arm, large-scale paraboloid day
Line etc., from its structure feature, the spacecraft with flexible structure can be divided into three classes: all kinds of large-scale flexible accessory class boats of Rigid Base band
Its device, Rigid Base band large size composite flexible structure accessory class spacecraft, Grazing condition structure class spacecraft.These flexible structures
Space scale is bigger, up to tens meters of even rice up to a hundred, production of small using density, Low rigidity materials, has large deflection, non-
Linearly, small damping, modal frequency be low and the physical characteristics such as intensive.
Currently, the most of of output are accounted for by the monocrystalline silicon of substrate and polysilicon solar cell of glass hard material,
But the high energy consumption due to itself manufacturing process keeps the cost of electricity-generating of this kind of battery higher with high vacuum condition, and it is easy
Broken, bad and the features such as being bent, limits certain applications.Thin-film solar cells belongs to solar battery of new generation, presses
Hard substrate and flexible substrate two major classes can be divided into according to the type of substrate.Flexible substrate film solar battery refers in flexible material
The thin-film solar cells of upper production.The research of new inorganic and organic solar material, the spy of novel solar battery structure
Rope, roll-to-roll print production technique and ink jet printing provide possibility to reduce flexible thin-film solar cell cost.
Non-contact measurement compares traditional sensor contact measurement and has many good qualities.Non-contact measurement will not influence
The dynamic property of measurand, will not because of influencing its normal work on testee additional mass, to measurand without
Damage and strong antijamming capability.But the precision of non-contact measurement is generally lower than contact type measurement.Non-contact measurement is
A kind of simple and effective vibration measuring method, common are the methods of laser vibration measurer, laser sensor, binocular vision system,
In, the binocular vision system vibration measuring method that is made of two high speed cameras with image procossing and analytical technology mature,
Increasingly become a kind of simple and convenient vibration measuring method with very high use value.High speed camera measurement vibration is a kind of multiple spot
Measurement method, compared to the method for some spot measurements, high speed camera measurement vibration is measuring the Mode variation of multiple points
When with very big advantage, as long as the resolution ratio of high speed camera and filming frequency are sufficiently high, the range of shooting is sufficiently large, only need
To make several upper mark points inside tested range, it can inside a range the multiple points of precise measurement vibration, obtain
The modal information of multiple points is taken, finally, binocular vision system can decouple the multi-modes of the vibration of testee, it can
Complicated multi-modes to be reduced to the superposition of multiple first-order modals, show the information of vibration is more intuitive.
Utility model content
Purpose of the utility model is to solve the defects of the above-mentioned prior art, provide a kind of pair and spread out solar wing vibration
Two groups of binocular vision system settings on two front and back truss disposed in parallel, are utilized two groups pairs by dynamic measuring device, the device
Mesh vision system detects the vibration detection index point region of double front and rear portions upper surfaces for spreading out solar wing, can be to double
It spreads out solar wing and carries out non-contact measurement, obtain double spreading out the more accurate vibration information of solar wing.
The purpose of this utility model can be reached by adopting the following technical scheme that:
It is double to spread out solar wing vibration measurement device, including it is double spread out solar wing, vibrational excitation mechanism and vibration detection mechanism,
The vibrational excitation mechanism spreads out solar wing with pair and connect, for motivating double solar wings that spread out to generate vibration, the vibration detection
Mechanism includes two groups of binocular vision systems and two truss, is arranged in parallel before and after described two truss, two groups of binocular visions
System and two truss correspond, and every group of binocular vision system is arranged on corresponding truss, two groups of binocular vision systems
For detecting the vibration detection index point region of double front and rear portions upper surfaces for spreading out solar wing.
Further, it includes coiling unfolded part, English truss, fixation member, uncoiling portion that described pair, which spreads out solar wing,
Part and two panels solar battery thin film, the coiling unfolded part are arranged in the middle part of fixation member, and the one of the English truss
End is connect with coiling unfolded part, and the other end of English truss and the middle part of unwinding mem-ber connect, two panels solar battery thin
Film is symmetricly set on the right and left of English truss, and the both ends of two panels solar battery thin film respectively with fixation member, uncoiling
The middle part of component connection, the vibrational excitation mechanism and unwinding mem-ber connects.
Further, described device further includes support platform and ground backing plate, and described pair spreads out solar wing and support platform
Surface keeping parallelism relationship, the fixation member is fixed in support platform by two vertical square bars, described two truss
It is fixed on the inside of support platform by corner fittings respectively, the unwinding mem-ber is fixed on the backing plate of ground by two vertical square bars.
Further, the support platform includes substrate and four support legs, and the fixation member passes through two vertical bars
It is fixed on the upper surface of substrate, described two truss pass through corner fittings respectively and are fixed on the inside of substrate, four support legs and base
The lower surface of plate is fixedly connected.
Further, every group of binocular vision system includes two high speed cameras, a laser, a guide rail, three cunnings
Block and two holders, the guide rail are fixed on corresponding truss, and three sliding blocks are slidably arranged on guide rail, and described two
High speed camera, two holders and two of them sliding block are to correspond, and every high speed camera is arranged on corresponding holder, often
A holder is fixed on corresponding sliding block, and the laser is fixed on another sliding block, and is located between two high speed cameras；
Wherein in one group of binocular vision system, the double front medial locations for spreading out solar wing of emission port alignment of laser,
For vibration detection index point to be projected double front upper surfaces for spreading out solar wing, the double pavings of the alignment lens of two high speed cameras
Open the vibration detection index point region of the front upper surface of solar wing；
In another group of binocular vision system, the double rear portion middle positions for spreading out solar wing of emission port alignment of laser are used
In vibration detection index point is projected double rear upper surfaces for spreading out solar wing, the alignment lens of two high speed cameras are double to be spread out
The vibration detection index point region of the rear upper surface of solar wing.
Further, in every group of binocular vision system, the horizontal distance between two high speed cameras is 400mm, and
The camera lens of two high speed cameras and double the distance between solar wing upper surfaces that spread out are 800mm~1000mm.
Further, each truss includes a horizon bar and two vertical bars, and the both ends of the horizon bar are respectively with two
One end of root vertical bar connects, and the other end of two vertical bars is fixed.
Further, the vibrational excitation mechanism includes vibration excitor and signal processing module, and the vibration excitor is spread out with double
Solar wing connection, the signal processing module are connect with vibration excitor.
Further, the signal processing module includes signal generator and power amplifier, the signal generator, function
Rate amplifier and vibration excitor are sequentially connected.
The utility model have compared with the existing technology it is following the utility model has the advantages that
1, the utility model uses two groups of binocular vision systems, and two groups of binocular vision system settings are flat two front and backs
On the truss of row setting, vibration is generated by the double solar wings that spread out of vibrational excitation mechanism incitation, in the premise without additive effect
Under contactless vibration measurement is carried out to double solar wings that spread out, what thus measurement obtained double spreads out solar wing vibration information precision phase
To higher.
2, fixation member is fixed in support platform by the utility model by two vertical square bars, and perpendicular by two
Unwinding mem-ber is fixed on the backing plate of ground by histogram bar, so that solar battery thin film is in the state of tensioning, to make double pavings
Solar wing is opened to stablize in gravitational field.
3, two truss are passed through corner fittings respectively and are fixed on the inside of support platform by the utility model, by the pine for controlling corner fittings
Tightly, the distance between the horizon bar of adjustable truss and support platform surface adjust the height of truss, so as to adjust binocular
The shooting height of vision system.
4, two groups of binocular vision systems of the utility model are respectively provided with two high speed cameras and a laser, and laser can
With by vibration detection index point project it is double spread out solar wing upper surface, two high speed cameras can shoot double spread out on solar wing
The vibration detection index point region on surface, by three sliding blocks on moving guide rail, adjustable two high speed cameras and one
The horizontal position of laser, to change the positional relationship between two high speed cameras, every high speed camera is arranged corresponding
On holder, spread out too to realize multimetering due to double by the angle that holder can change high speed camera and shoot surface
The volume of the positive wing is larger, is detected using multimetering mode to double solar wings that spread out, and can spread out the more of solar wing to double
The vibration of rank modal coupling is decoupled, the accurate double Vibration Conditions for spreading out solar wing of reduction.
5, the binocular vision system that the utility model uses can be with horizontal displacement, can also be with vertical displacement, and can adjust
The shooting angle of whole high speed camera, the calibration and different shape and size of double vibrations for spreading out solar wing for being conducive to camera are surveyed
Amount obtains more accurate double vibration characteristics for spreading out solar wing.
Detailed description of the invention
Fig. 1 is that the double of the utility model embodiment 1 spread out solar wing vibration measurement device general structure schematic diagram.
Fig. 2 is double front views for spreading out solar wing vibration measurement device of the utility model embodiment 1.
Fig. 3 is double top views for spreading out solar wing vibration measurement device of the utility model embodiment 1.
Fig. 4 is double right views for spreading out solar wing vibration measurement device of the utility model embodiment 1.
Fig. 5 is the schematic diagram of wherein one group of binocular vision system of the vibration detection mechanism of the utility model embodiment 1.
Wherein, 1- coiling unfolded part, 2- English truss, 3- fixation member, 4- unwinding mem-ber, the first solar-electricity of 5-
Pond film, the second solar battery thin film of 6-, 7- support platform, 701- substrate, 702- support leg, the ground 8- backing plate, 9- first
Vertical square bar, the vertical square bar of 10- second, 11- vibration excitor, 12- signal generator, 13- power amplifier, 14- mandril, the purlin 15-
Frame, the first high speed camera of 16-, the second high speed camera of 17-, 18- laser, 19- guide rail, the first sliding block of 20-, the second sliding block of 21-,
22- third sliding block, the first holder of 23-, the second holder of 24-, 25- computer.
Specific embodiment
The present invention will be further described in detail with reference to the embodiments and the accompanying drawings, but the implementation of the utility model
Mode is without being limited thereto.
Embodiment 1:
As shown in Figure 1 to 4, it present embodiments provides a kind of pair and spreads out solar wing vibration measurement device, which includes
Double to spread out solar wing, vibrational excitation mechanism and vibration detection mechanism, the dotted line in Fig. 1 indicates the pass of the line between each equipment
System, direction arrow show the direction of transfer for detecting and controlling signal stream.
Double solar wing that spreads out is flexible structure comprising coiling unfolded part 1, English truss 2, fixation member 3,
Unwinding mem-ber 4, the first solar battery thin film 5 and the second solar battery thin film 6, fixation member 3 and unwinding mem-ber 4 are made respectively
For double front and rear ends for spreading out solar wing, the setting of coiling unfolded part 1 is in 3 middle part of fixation member, one end of English truss 2
It is connect with coiling unfolded part 1, the other end of English truss 2 is connect with the middle part of unwinding mem-ber 4, the first solar battery thin
Film 5 and the second solar battery thin film 6 are symmetricly set on the right and left of English truss 2, and the two of the first solar battery thin film 5
It holds and is connect respectively with the left part of the left part of fixation member 3, unwinding mem-ber 4, the both ends of the second solar battery thin film 6 are respectively and solid
Determine the right part connection of the right part, unwinding mem-ber 4 of component 3.
Double solar wings that spread out are in gravitational field, and since the rigidity of English truss 2 is inadequate, in order to stablize, support is double to be spread out too
Double solar wing vibration measurement devices that spread out of the positive wing, the present embodiment further include support platform 7 and ground backing plate 8, double to spread out the sun
The surface keeping parallelism relationship of the wing and support platform 7, fixation member 3 are fixed on support platform 7 by two first vertical square bars 9
On, unwinding mem-ber 4 is fixed on ground backing plate 8 by two second vertical square bars 10, specifically, first passes through screw-nut for two
One end of the vertical square bar 9 of root first is fixed in support platform 7, and by screw-nut by two second vertical square bars 10
One end is fixed on ground backing plate 8, then passes through two right angle supporting plates for the other end and fixed part of two first vertical square bars 9
Part 3 is fixedly connected, and is fixed the other end of two second vertical square bars 10 and unwinding mem-ber 4 by two right angle supporting plates and connected
It connects, solar wing is spread out so that support is double, so that the first solar battery thin film 5 and the second solar battery thin film 6 are in tensioning
State.
Further, the support platform 7 includes substrate 701 and support leg 702, and fixation member 3 is perpendicular by two first
Straight-bar 9 is fixed on the upper surface of substrate 701, and four support legs 702 are fixedly connected with the lower surface of substrate 701, both can be improved
Support platform 7 support it is double spread out the stability of solar wing, and the material of support platform 7 can be saved, reduce the system of support platform 7
Make cost.
In the present embodiment, support platform 7 is assembled by the aluminum profile that three kinds of length are respectively 2000mm, 1400mm, 500mm
It forms, substrate 701 is one piece of 2120mm × 1520mm × 8mm stainless steel plate, and substrate 701 is connect by screw with profile, type
Each junction of material has angle bar to fix；Double full-sizes for spreading out solar wing are 2870mm × 1150mm, 2 He of English truss
For fixation member 3 by aluminium as material, the first solar battery thin film 5 and the second solar battery thin film 6 are amorphous silicon battery
Film；Plastic material stick can be selected in unwinding mem-ber 4, has certain elasticity.
The vibrational excitation mechanism is for motivating double solar wings that spread out to generate vibration comprising signal processing module and exciting
Device 11, signal processing module include signal generator 12 and power amplifier 13, signal generator 12, power amplifier 13 and are swashed
Vibration device 11 is sequentially connected, and the vibration excitor 11 of the present embodiment is fixed on ground backing plate 8, and passes through mandril 14 and unwinding mem-ber 4
Middle part connection, signal generator issue vibration signal, and vibration excitor is sent to after the amplification of power amplifier 13, and vibration excitor 11 receives
Vibration is generated after signal, unwinding mem-ber 4 is driven by mandril 14, to motivate double solar wings that spread out to generate vibration, is sent out by changing
Raw signal generates different vibrations to detect and double spread out vibration characteristics of the solar wing under different vibrational excitations.
In the present embodiment, vibration excitor 11 selects the vibration excitor of the model JZK-50 of U.S. GST company production, vibration excitor
11 maximum exciting force is 500N, and peak swing is ± 12.5mm, and peak acceleration 55g, maximum input current is 30Arms,
Frequency range is DC-2k, and outer dimension is Ф 240mm × 345mm, and the way of output is that power is transmitted by mandril 14 to unwinding mem-ber 4
On；Power amplifier of the power amplifier 13 using the model 50WD1000 of U.S. AR company, working frequency DC-
1000MHz。
The vibration detection mechanism includes two groups of binocular vision systems and two truss 15, and two 15 front and backs of truss are set in parallel
It sets, two groups of binocular vision systems and two truss 15 correspond, and every group of binocular vision system is arranged in corresponding truss 15
On, that is to say, that two groups of binocular vision systems are respectively one group of front binocular vision system and rear set binocular vision system,
Before one group of front binocular vision system is for detecting the first solar battery thin film 5 and 6 upper surface of the second solar battery thin film
The vibration detection index point region in portion, rear set binocular vision system is for detecting the first solar battery thin film 5 and second
The vibration detection index point region at 6 upper surface rear portion of solar battery thin film.
Further, each truss 15 is made of aluminum profile comprising a horizon bar and two vertical bars, horizon bar
Both ends are connect with one end of two vertical bars respectively, and the other end of two vertical bars is fixed on the inside of support platform 7, specifically
Ground, the both ends of horizon bar pass through corner fittings respectively and connect with one end of two vertical bars, and the other end of two vertical bars passes through respectively
Corner fittings is fixed on the inside of substrate 701 of support platform 7, by the elastic of control corner fittings, the horizon bar of adjustable truss 15 with
The distance between 701 upper surface of substrate of support platform 7 adjusts the height of truss 15, so as to adjust binocular vision system
Shooting height.
As shown in fig. 1~fig. 5, every group of binocular vision system includes the first high speed camera 16, the second high speed camera 17, laser
Device 18, guide rail 19, the first sliding block 20, the second sliding block 21, third sliding block 22, the first holder 23 and the second holder 24, guide rail 19 are solid
It being scheduled on the horizon bar of corresponding truss 15, the first sliding block 20, the second sliding block 21 and third sliding block 22 are slidably arranged on guide rail 19,
That is the first sliding block 20, the second sliding block 21 and third sliding block 22 can move on rails 19, and third sliding block 22 is located at first and slides
Between block 20 and the second sliding block 21, the first high speed camera 16 is arranged on the first holder 23, and the setting of the second high speed camera 17 is the
On two holders 24, the first holder 23 is fixed on the first sliding block 20, and the second holder 24 is fixed on the second sliding block 21, laser 18
It is fixed on third sliding block 22, and between the first high speed camera 16 and the second high speed camera 17, passes through mobile first sliding block
20, the second sliding block 21 and third sliding block 22, the water of adjustable first high speed camera 16, the second high speed camera 17 and laser 18
Prosposition is set, to change the positional relationship between the first high speed camera 16 and the second high speed camera 17, by adjusting the first holder
23 and second holder 24, thus it is possible to vary the angle of the first high speed camera 16 and the second high speed camera 17 and shooting surface meets each
Double vibration detection needs for spreading out solar wing of kind shape size；The position of high speed camera should make it is double spread out solar wing it is static when inspection
It surveys end face and is located substantially at high speed camera visual field middle position, it is double to spread out solar wing always when spreading out solar wing vibration so that guarantee is double
In field range in high speed camera, guarantee the continuity of measurement, the optical axis of high speed camera and solar battery thin film
Face is vertical, and high speed camera front is enabled to shoot its solar battery thin film surface；The laser of two groups of binocular vision systems
Vibration detection index point is projected solar battery thin film upper surface by 18, generates the identical rectangular lattice of spacing, vibration detection
Indicate that size, spacing, color and the focal length of the point of dot matrix are adjustable, can satisfy different size of detection body and not TongAn
Fill the vibration detection requirement under height, and laser 18 can long time continuous working do not generate light decay phenomenon, and have relatively strong
At line effect, also possess anti-seismic performance, can be reduced double spread out influences brought by solar wings vibration, two groups of binocular vision systems
Captured image splices because identifying, so former and later two laser dot-matrixes generated of the laser 18 of two groups of binocular vision systems
Color shape must have any different, and be conducive to more accurate image recognition and splicing.
Further, before in one group of binocular vision system, before the emission port alignment pair of laser 18 spreads out solar wing
Portion middle position, the vibration detection mark of the 5 upper surface front of the first solar battery thin film of alignment lens of the first high speed camera 16
Will point region, the vibration detection mark of the 6 upper surface front of the second solar battery thin film of alignment lens of the second high speed camera 17
Point region；In rear set binocular vision system, the double rear portion middle positions for spreading out solar wing of emission port alignment of laser 18,
The vibration detection index point region at the 5 upper surface rear portion of the first solar battery thin film of alignment lens of the first high speed camera 16, the
The vibration detection index point region at the 6 upper surface rear portion of the second solar battery thin film of alignment lens of two high speed cameras 17；Two groups
First high speed camera 16 of binocular vision system and the image transmitting of the second high speed camera 17 shooting are into computer 25.
Further, the water in every group of binocular vision system, between the first high speed camera 16 and the second high speed camera 17
Flat distance is 400mm, and the distance between the camera lens of the first high speed camera 16 and 5 upper surface of the first solar battery thin film are
800mm~1000mm, the distance between the camera lens of the second high speed camera 17 and 6 upper surface of the second solar battery thin film are also
800mm~1000mm.
In the present embodiment, the first high speed camera 16 and the second high speed camera 17 select wound connection in Wuhan to reach the limited public affairs of science and technology
The high speed camera of the model Memrecam HX-3E of department, possesses 5,000,000 pixels, and under the full resolution frame speed up to 2000
Frame/second, frame speed assigns 9220 frames/second up to 4670 frames/second, 1,000,000 pixels under full HD pixel, inside saves as 64GB, operating temperature
Range is 0-40 degrees Celsius, and weight is about 5.9 kilograms, and the power supply needed is 100-240VAC-1.5A, 50-60Hz；Laser 18
Select the model ZLM100MTX650-16GD laser of Shenzhen Zhong Lai scientific & technical corporation, optical maser wavelength 650nm, output power
For 100mW, operating current≤180mA, supply voltage DC2.8-5.2V, facular model, dot matrix, optical lens: lenticular lenses (Germany
Import).
The present embodiment additionally provides a kind of pair and spreads out solar wing vibration measurement method, and this method is realized based on above-mentioned apparatus,
The following steps are included:
Step 1: the laser 18 of two groups of binocular vision systems spreads out solar wing transmitting laser against double, by vibration detection
Index point projects the front and rear portions upper surface of the first solar battery thin film 5 and the second solar battery thin film 6；
Step 2: signal generator 12 issues vibration signal, vibration excitor 11 is sent to after the amplification of power amplifier 13；
Step 3: vibration excitor 11 is transmitted in power to unwinding mem-ber 4 by mandril 14, it is different that excitation pair spreads out solar wing generation
The vibration of frequency；
Step 4: it is double spread out solar wing vibration during, by the first high speed camera 16 of two groups of binocular vision systems
High frequency shooting is synchronized to the vibration detection index point region of the front and rear portions upper surface of the first solar battery thin film 5, and
Vibration by the second high speed camera 17 of two groups of binocular vision systems to the front and rear portions upper surface of the second solar battery thin film 6
Detection index point region synchronizes high frequency shooting；
Step 5: computer 25 reads first high speed camera 16 of two groups of binocular vision systems and the second high speed camera 17 is clapped
The image taken the photograph, by Zhang Zhengyou calibration method to the first high speed camera 16 and the second high speed camera 17 of two groups of binocular vision systems
It is demarcated, extracts the coordinate of image spot feature calculation laser point, be further processed to obtain double vibration letters for spreading out solar wing
Breath, and visualization processing is carried out, result is presented over the display.
In conclusion the utility model uses two groups of binocular vision systems, two groups of binocular vision systems are arranged two
On a front and back truss disposed in parallel, vibration is generated by the double solar wings that spread out of vibrational excitation mechanism incitation, without additional effect
Contactless vibration measurement is carried out to double solar wings that spread out under the premise of answering, double solar wings that spread out that thus measurement obtains vibrate letter
It is relatively high to cease precision.
The above, only the utility model patent preferred embodiment, but the protection scope of the utility model patent is simultaneously
Not limited to this, anyone skilled in the art is in the range disclosed in the utility model patent, according to this
Technical solution and its utility model design of utility model patent are subject to equivalent substitution or change, belong to the utility model patent
Protection scope.
Claims (9)
1. pair spreading out solar wing vibration measurement device, it is characterised in that: spread out solar wing, vibrational excitation mechanism and vibration including double
Testing agency, the vibrational excitation mechanism spread out solar wing with pair and connect, described for motivating double solar wings that spread out to generate vibration
Vibration detection mechanism includes two groups of binocular vision systems and two truss, is arranged in parallel before and after described two truss, described two groups
Binocular vision system and two truss correspond, and every group of binocular vision system is arranged on corresponding truss, two groups of binoculars
Vision system is used to detect the vibration detection index point region of double front and rear portions upper surfaces for spreading out solar wing.
2. according to claim 1 pair spreads out solar wing vibration measurement device, it is characterised in that: described pair spreads out solar wing
Including coiling unfolded part, English truss, fixation member, unwinding mem-ber and two panels solar battery thin film, the coiling
Unfolded part is arranged in the middle part of fixation member, and one end of the English truss is connect with coiling unfolded part, English truss
The connection of the middle part of the other end and unwinding mem-ber, two panels solar battery thin film are symmetricly set on the right and left of English truss, and
The both ends of two panels solar battery thin film are connect with fixation member, unwinding mem-ber respectively, the vibrational excitation mechanism and uncoiling portion
The middle part of part connects.
3. according to claim 2 pair spreads out solar wing vibration measurement device, it is characterised in that: described device further includes branch
Platform and ground backing plate, double surface keeping parallelism relationships for spreading out solar wing and support platform are supportted, the fixation member is led to
It crosses two vertical square bars to be fixed in support platform, described two truss pass through corner fittings respectively and are fixed on the inside of support platform, institute
Unwinding mem-ber is stated to be fixed on the backing plate of ground by two vertical square bars.
4. double solar wing vibration measurement device is spread out according to claim 3, it is characterised in that: the support platform includes
Substrate and four support legs, the fixation member are fixed on the upper surface of substrate, described two truss point by two vertical bars
It is not fixed on the inside of substrate by corner fittings, four support legs are fixedly connected with the lower surface of substrate.
5. according to claim 1-4 pair spreads out solar wing vibration measurement device, it is characterised in that: every group of binocular
Vision system includes that two high speed cameras, a laser, a guide rail, three sliding blocks and two holders, the guide rail are fixed
On corresponding truss, three sliding blocks are slidably arranged on guide rail, two high speed cameras, two holders and wherein two
A sliding block is to correspond, and every high speed camera is arranged on corresponding holder, and each holder is fixed on corresponding sliding block,
The laser is fixed on another sliding block, and is located between two high speed cameras；
Wherein in one group of binocular vision system, the double front medial locations for spreading out solar wing of emission port alignment of laser are used for
Vibration detection index point is projected into double front upper surfaces for spreading out solar wing, the alignment lens of two high speed cameras are double to be spread out too
The vibration detection index point region of the front upper surface of the positive wing；
In another group of binocular vision system, the double rear portion middle positions for spreading out solar wing of emission port alignment of laser, being used for will
Vibration detection index point projects double rear upper surfaces for spreading out solar wing, and the alignment lens of two high speed cameras are double to spread out the sun
The vibration detection index point region of the rear upper surface of the wing.
6. according to claim 5 pair spreads out solar wing vibration measurement device, it is characterised in that: every group of binocular vision
In system, the horizontal distance between two high speed cameras is 400mm, and the camera lens of two high speed cameras is spread out on solar wing with double
The distance between surface is 800mm~1000mm.
7. according to claim 1-4 pair spreads out solar wing vibration measurement device, it is characterised in that: each truss
Including a horizon bar and two vertical bars, the both ends of the horizon bar are connect with one end of two vertical bars respectively, and two perpendicular
The other end of straight-bar is fixed.
8. according to claim 1-4 pair spreads out solar wing vibration measurement device, it is characterised in that: the vibration
Excitation mechanism includes vibration excitor and signal processing module, and the vibration excitor spreads out solar wing with pair and connect, the signal processing mould
Block is connect with vibration excitor.
9. according to claim 8 pair spreads out solar wing vibration measurement device, it is characterised in that: the signal processing module
Including signal generator and power amplifier, the signal generator, power amplifier and vibration excitor are sequentially connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201820975898.8U CN208383289U (en) | 2018-06-25 | 2018-06-25 | It is double to spread out solar wing vibration measurement device |
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| CN201820975898.8U CN208383289U (en) | 2018-06-25 | 2018-06-25 | It is double to spread out solar wing vibration measurement device |
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| CN208383289U true CN208383289U (en) | 2019-01-15 |
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| CN201820975898.8U Expired - Fee Related CN208383289U (en) | 2018-06-25 | 2018-06-25 | It is double to spread out solar wing vibration measurement device |
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| CN (1) | CN208383289U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108709625A (en) * | 2018-06-25 | 2018-10-26 | 华南理工大学 | It is double to spread out solar wing vibration measurement device and method |
| CN112444365A (en) * | 2020-11-30 | 2021-03-05 | 哈尔滨工业大学 | Satellite solar wing substrate unfolding low-frequency modal testing method based on force hammer swing method and laser Doppler method |
-
2018
- 2018-06-25 CN CN201820975898.8U patent/CN208383289U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108709625A (en) * | 2018-06-25 | 2018-10-26 | 华南理工大学 | It is double to spread out solar wing vibration measurement device and method |
| CN108709625B (en) * | 2018-06-25 | 2024-01-30 | 华南理工大学 | Double-spreading solar wing vibration measuring device and method |
| CN112444365A (en) * | 2020-11-30 | 2021-03-05 | 哈尔滨工业大学 | Satellite solar wing substrate unfolding low-frequency modal testing method based on force hammer swing method and laser Doppler method |
| CN112444365B (en) * | 2020-11-30 | 2023-08-29 | 哈尔滨工业大学 | Satellite solar wing substrate unfolding low-frequency mode testing method |
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