CN108709625B - Double-spreading solar wing vibration measuring device and method - Google Patents
Double-spreading solar wing vibration measuring device and method Download PDFInfo
- Publication number
- CN108709625B CN108709625B CN201810658122.8A CN201810658122A CN108709625B CN 108709625 B CN108709625 B CN 108709625B CN 201810658122 A CN201810658122 A CN 201810658122A CN 108709625 B CN108709625 B CN 108709625B
- Authority
- CN
- China
- Prior art keywords
- double
- vibration
- solar wing
- spread
- binocular vision
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 19
- 238000001514 detection method Methods 0.000 claims abstract description 41
- 230000007246 mechanism Effects 0.000 claims abstract description 22
- 238000005259 measurement Methods 0.000 claims abstract description 21
- 230000005284 excitation Effects 0.000 claims abstract description 15
- 230000007480 spreading Effects 0.000 claims description 13
- 238000012545 processing Methods 0.000 claims description 12
- 230000008569 process Effects 0.000 claims description 5
- 238000012800 visualization Methods 0.000 claims description 3
- 239000000284 extract Substances 0.000 claims description 2
- 230000001360 synchronised effect Effects 0.000 claims description 2
- 239000010408 film Substances 0.000 description 35
- 239000000758 substrate Substances 0.000 description 9
- 239000000463 material Substances 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 4
- 239000010409 thin film Substances 0.000 description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 229910052782 aluminium Inorganic materials 0.000 description 3
- 230000002730 additional effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000691 measurement method Methods 0.000 description 2
- 230000003287 optical effect Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 229910021417 amorphous silicon Inorganic materials 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000007641 inkjet printing Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 235000000396 iron Nutrition 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910021421 monocrystalline silicon Inorganic materials 0.000 description 1
- 229910021420 polycrystalline silicon Inorganic materials 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000007639 printing Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H9/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by using radiation-sensitive means, e.g. optical means
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
Abstract
The invention discloses a double-spread solar wing vibration measuring device and a method, wherein the device comprises double-spread solar wings, a vibration excitation mechanism and a vibration detection mechanism, the vibration excitation mechanism is connected with the double-spread solar wings and is used for exciting the double-spread solar wings to vibrate, the vibration detection mechanism comprises two groups of binocular vision systems and two trusses, the two trusses are arranged in parallel front and back, the two groups of binocular vision systems are in one-to-one correspondence with the two trusses, each group of binocular vision systems is arranged on the corresponding truss, and the two groups of binocular vision systems are used for detecting vibration detection mark point areas on the upper surfaces of the front and back parts of the double-spread solar wings. According to the invention, the two groups of binocular vision systems are arranged on the two trusses which are arranged in parallel front and back, and the vibration detection mark point areas on the upper surfaces of the front part and the rear part of the double-spread solar wing are detected by using the two groups of binocular vision systems, so that the non-contact measurement can be carried out on the double-spread solar wing, and the accurate vibration information of the double-spread solar wing can be obtained.
Description
Technical Field
The invention relates to a vibration measuring device, in particular to a double-spread solar wing vibration measuring device and a double-spread solar wing vibration measuring method, and belongs to the field of vibration measurement.
Background
In recent years, the complexity of the task borne by the spacecraft is continuously increased, the requirements of people on the structure are higher and higher, on one hand, the requirements of improving the bearing capacity and on the other hand, the requirements of reducing the total mass of the structure are required, so that the spacecraft is developed towards the trend of low rigidity, flexibility and large size, and the large flexibility becomes a great characteristic of the modern spacecraft. The flexible structure is widely used in spacecrafts, such as solar sailboard structures of satellites or space workstations, spaceship wings, space station flexible mechanical arms, large parabolic antennas and the like, and from the structural characteristics of the flexible structure, the spacecrafts with the flexible structure can be divided into three types: various large flexible accessory type spacecrafts with a central rigid body, various large composite flexible structure accessory type spacecrafts with a central rigid body and all flexible structure type spacecrafts with a central rigid body. The flexible structures have larger space dimensions, which can reach tens of meters or hundreds of meters, are made of materials with small density and low rigidity, and have the physical characteristics of large deflection, nonlinearity, small damping, low modal frequency, dense modal frequency and the like.
Currently, monocrystalline silicon and polycrystalline silicon solar cells using glass hard materials as substrates account for most of the production capacity, but the high energy consumption and high vacuum conditions in the manufacturing process of the solar cells lead to higher power generation cost of the solar cells, and the characteristics of easy breakage, poor bending and the like limit certain application occasions. Thin film solar cells belong to a new generation of solar cells, and can be classified into two major categories, namely a hard substrate and a flexible substrate, according to the types of substrates. The flexible substrate thin film solar cell refers to a thin film solar cell fabricated on a flexible material. Research on new inorganic and organic solar materials, exploration of new solar cell structures, roll-to-roll printing production process and inkjet printing offer the possibility of reducing the cost of flexible thin film solar cells.
Non-contact measurements offer many advantages over conventional sensor contact measurements. The non-contact measurement does not affect the dynamic performance of the measured object, the normal work of the measured object is not affected by adding mass to the measured object, the measured object is not damaged, and the anti-interference capability is strong. However, the accuracy of non-contact measurements is generally lower than that of contact measurements. The non-contact measurement is a simple and effective vibration measuring method, and common methods include a laser vibration meter, a laser sensor, a binocular vision system and the like, wherein the vibration measuring method of the binocular vision system consisting of two high-speed cameras is more and more a simple and convenient vibration measuring method with high use value along with the development of image processing and analysis technologies. The high-speed camera is used for measuring vibration, compared with a plurality of single-point measuring methods, the high-speed camera is used for measuring vibration, when the mode of a plurality of points is changed, the high-speed camera has great advantages, as long as the resolution and the shooting frequency of the high-speed camera are high enough, the shooting range is large enough, only a plurality of mark points are needed to be made in the detected range, the vibration of the plurality of points can be accurately measured in one range, the mode information of the plurality of points is obtained, finally, the binocular vision system can decouple the multi-order mode of the vibration of the detected object, the complex multi-order mode can be simplified into superposition of a plurality of first-order modes, and the vibration information is more intuitively displayed.
Disclosure of Invention
The invention aims to solve the defects in the prior art, and provides a double-spread solar wing vibration measuring device.
Another object of the present invention is to provide a method for measuring vibration of a double-spread solar wing based on the above device.
The aim of the invention can be achieved by adopting the following technical scheme:
the double-spreading solar wing vibration measuring device comprises double-spreading solar wings, a vibration excitation mechanism and a vibration detection mechanism, wherein the vibration excitation mechanism is connected with the double-spreading solar wings and used for exciting the double-spreading solar wings to vibrate, the vibration detection mechanism comprises two groups of binocular vision systems and two trusses, the two trusses are arranged in a front-back parallel mode, the two groups of binocular vision systems correspond to the two trusses one to one, each group of binocular vision systems are arranged on the corresponding trusses, and the two groups of binocular vision systems are used for detecting vibration detection mark point areas on the upper surfaces of the front part and the rear part of the double-spreading solar wings.
Further, the double-spread solar wing comprises a coiled spreading component, a triangular truss, a fixing component, a spreading component and two solar cell films, wherein the coiled spreading component is arranged in the middle of the fixing component, one end of the triangular truss is connected with the coiled spreading component, the other end of the triangular truss is connected with the middle of the spreading component, the two solar cell films are symmetrically arranged on the left side and the right side of the triangular truss, the two ends of the two solar cell films are respectively connected with the fixing component and the spreading component, and the vibration excitation mechanism is connected with the middle of the spreading component.
Further, the device still includes supporting platform and ground backing plate, the surface that two sun wings and supporting platform are spread out keeps parallel relation, fixed part passes through two vertical square poles to be fixed on supporting platform, two trusses are fixed in supporting platform inboard through the corner fittings respectively, the part of opening a book is fixed on ground backing plate through two vertical square poles.
Further, the supporting platform comprises a base plate and four supporting feet, the fixing part is fixed on the upper surface of the base plate through two vertical rods, the two trusses are respectively fixed on the inner side of the base plate through corner pieces, and the four supporting feet are fixedly connected with the lower surface of the base plate.
Further, each group of binocular vision system comprises two high-speed cameras, a laser, a guide rail, three sliding blocks and two cloud platforms, wherein the guide rail is fixed on a corresponding truss, the three sliding blocks are arranged on the guide rail in a sliding manner, the two high-speed cameras, the two cloud platforms and the two sliding blocks are in one-to-one correspondence, each high-speed camera is arranged on the corresponding cloud platform, each cloud platform is fixed on the corresponding sliding block, and the laser is fixed on the other sliding block and is positioned between the two high-speed cameras;
in one group of binocular vision systems, the emitting port of the laser is aligned to the middle position of the front part of the double-spread solar wing and is used for projecting vibration detection mark points to the upper surface of the front part of the double-spread solar wing, and the lenses of the two high-speed cameras are aligned to the vibration detection mark point areas of the upper surface of the front part of the double-spread solar wing;
in another group of binocular vision systems, the emitting port of the laser is aligned to the middle position of the rear part of the double-spread solar wing, and is used for projecting the vibration detection mark point to the upper surface of the rear part of the double-spread solar wing, and the lenses of the two high-speed cameras are aligned to the vibration detection mark point area of the upper surface of the rear part of the double-spread solar wing.
Further, in each group of binocular vision system, the horizontal distance between the two high-speed cameras is 400mm, and the distance between the lenses of the two high-speed cameras and the upper surface of the double-spread solar wing is 800-1000 mm.
Further, each truss comprises a horizontal rod and two vertical rods, two ends of the horizontal rod are respectively connected with one ends of the two vertical rods, and the other ends of the two vertical rods are fixed.
Further, the vibration excitation mechanism comprises a vibration exciter and a signal processing module, the vibration exciter is connected with the double-spread solar wing, and the signal processing module is connected with the vibration exciter.
Further, the signal processing module comprises a signal generator and a power amplifier, and the signal generator, the power amplifier and the vibration exciter are sequentially connected.
The other object of the invention can be achieved by adopting the following technical scheme:
a vibration measurement method based on the above device, the method comprising:
the lasers of the two groups of binocular vision systems emit laser towards the double-spread solar wings, and vibration detection mark points are projected to the upper surfaces of the front and rear parts of the double-spread solar wings;
the signal generator of the vibration excitation mechanism sends out a vibration signal which is amplified by the power amplifier and then sent to the vibration exciter;
the vibration exciter generates vibration after receiving signals to excite the double-spread solar wing to generate vibration with different frequencies;
in the process of vibrating the double-spread solar wing, synchronous high-frequency shooting is carried out on vibration detection mark point areas on the upper surfaces of the front part and the rear part of the double-spread solar wing by using high-speed cameras of two groups of binocular vision systems, an image sequence is acquired, and the image sequence is sent to a computer;
the computer reads images shot by the high-speed cameras of the two groups of binocular vision systems, calibrates the high-speed cameras of the two groups of binocular vision systems, extracts the light spot characteristics of the images to calculate the coordinates of laser points, further processes the coordinates to obtain vibration information of the double-spread solar wing, performs visualization processing, and displays the result on the display.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the invention, two groups of binocular vision systems are adopted, the two groups of binocular vision systems are arranged on two trusses which are arranged in parallel front and back, the vibration excitation mechanism excites the double-spread solar wing to generate vibration, and the non-contact vibration measurement is carried out on the double-spread solar wing on the premise of no additional effect, so that the vibration information precision of the double-spread solar wing obtained by measurement is relatively high.
2. According to the solar cell film stretching device, the fixing part is fixed on the supporting platform through the two vertical square rods, and the uncoiling part is fixed on the ground base plate through the two vertical square rods, so that the solar cell film is in a stretched state, and the double-spread solar wing is stably positioned in a gravity field.
3. According to the invention, the two trusses are respectively fixed on the inner side of the supporting platform through the corner fittings, and the distance between the horizontal rods of the trusses and the surface of the supporting platform, namely the height of the trusses, can be adjusted by controlling the tightness of the corner fittings, so that the shooting height of the binocular vision system is adjusted.
4. The two groups of binocular vision systems are respectively provided with the two high-speed cameras and the laser, the laser can project the vibration detection mark point onto the upper surface of the double-spread solar wing, the two high-speed cameras can shoot the vibration detection mark point area on the upper surface of the double-spread solar wing, the horizontal positions of the two high-speed cameras and the laser can be adjusted by moving the three sliding blocks on the guide rail, so that the position relation between the two high-speed cameras is changed, each high-speed camera is arranged on the corresponding tripod head, the angle between the high-speed camera and the shooting surface can be changed by the tripod head, so that multipoint measurement is realized, and the double-spread solar wing is detected by adopting a multipoint measurement mode, so that the multi-order coupling vibration of the double-spread solar wing can be decoupled, and the vibration condition of the double-spread solar wing can be restored more accurately.
5. The binocular vision system adopted by the invention can horizontally displace and vertically displace, can adjust the shooting angle of the high-speed camera, is beneficial to the calibration of the camera and the vibration measurement of double-spread solar wings with different shapes and sizes, and obtains more accurate vibration characteristics of the double-spread solar wings.
Drawings
Fig. 1 is a schematic view showing the overall structure of a double-spread solar wing vibration measuring apparatus according to embodiment 1 of the present invention.
Fig. 2 is a front view of a double-spread solar wing vibration measuring apparatus according to embodiment 1 of the present invention.
Fig. 3 is a top view of a double-spread solar wing vibration measuring device according to embodiment 1 of the present invention.
Fig. 4 is a right side view of the double-spread solar wing vibration measuring apparatus of embodiment 1 of the present invention.
Fig. 5 is a schematic diagram of one set of binocular vision systems of the vibration detecting mechanism of embodiment 1 of the present invention.
The device comprises a 1-coiled unwinding component, a 2-triangular truss, a 3-fixing component, a 4-unwinding component, a 5-first solar cell film, a 6-second solar cell film, a 7-supporting platform, a 701-substrate, 702-supporting feet, an 8-ground cushion plate, 9-first vertical square rods, 10-second vertical square rods, 11-vibration exciters, 12-signal generators, 13-power amplifiers, 14-ejector rods, 15-trusses, 16-first high-speed cameras, 17-second high-speed cameras, 18-lasers, 19-guide rails, 20-first sliding blocks, 21-second sliding blocks, 22-third sliding blocks, 23-first cloud platforms, 24-second cloud platforms and 25-computers.
Detailed Description
The present invention will be described in further detail with reference to examples and drawings, but embodiments of the present invention are not limited thereto.
Example 1:
as shown in fig. 1 to 4, the present embodiment provides a double-spread solar wing vibration measuring apparatus including a double-spread solar wing, a vibration excitation mechanism and a vibration detection mechanism, the broken line in fig. 1 indicating the connection relationship between the respective devices, and the directional arrow indicating the transmission direction of the detection and control signal flow.
The double-spread solar wing is of a flexible structure, and comprises a coiled spreading component 1, a triangular truss 2, a fixing component 3, an uncoiling component 4, a first solar cell film 5 and a second solar cell film 6, wherein the fixing component 3 and the uncoiling component 4 are respectively used as the front end and the rear end of the double-spread solar wing, the coiled spreading component 1 is arranged in the middle of the fixing component 3, one end of the triangular truss 2 is connected with the coiled spreading component 1, the other end of the triangular truss 2 is connected with the middle of the uncoiling component 4, the first solar cell film 5 and the second solar cell film 6 are symmetrically arranged on the left side and the right side of the triangular truss 2, the two ends of the first solar cell film 5 are respectively connected with the left part of the fixing component 3 and the left part of the uncoiling component 4, and the two ends of the second solar cell film 6 are respectively connected with the right part of the fixing component 3 and the right part of the uncoiling component 4.
In order to stably support the double-spread solar wing due to insufficient rigidity of the triangular truss 2, the double-spread solar wing vibration measurement device of the embodiment further comprises a support platform 7 and a ground pad 8, the double-spread solar wing is in parallel relation with the surface of the support platform 7, the fixing part 3 is fixed on the support platform 7 through two first vertical square rods 9, the uncoiling part 4 is fixed on the ground pad 8 through two second vertical square rods 10, specifically, one ends of the two first vertical square rods 9 are fixed on the support platform 7 through screw nuts, one ends of the two second vertical square rods 10 are fixed on the ground pad 8 through screw nuts, then the other ends of the two first vertical square rods 9 are fixedly connected with the fixing part 3 through two right-angle support plates, and the other ends of the two second vertical square rods 10 are fixedly connected with the uncoiling part 4 through the two right-angle support plates so as to support the double-spread solar wing, so that the first solar cell film 5 and the second solar cell film 6 are in a tensioned state.
Further, the supporting platform 7 includes a substrate 701 and supporting legs 702, the fixing component 3 is fixed on the upper surface of the substrate 701 through two first vertical rods 9, and four supporting legs 702 are fixedly connected with the lower surface of the substrate 701, so that stability of the supporting platform 7 for supporting double-spread solar wings can be improved, materials of the supporting platform 7 can be saved, and manufacturing cost of the supporting platform 7 is reduced.
In the embodiment, the supporting platform 7 is assembled by three aluminum profiles with the lengths of 2000mm, 1400mm and 500mm respectively, the base plate 701 is a stainless steel plate with the lengths of 2120mm multiplied by 1520mm multiplied by 8mm, the base plate 701 is connected with the profiles through screws, and each connecting part of the profiles is fixed by angle irons; the maximum size of the double-spread solar wing is 2870mm multiplied by 1150mm, the triangular truss 2 and the fixing part 3 are made of aluminum, and the first solar cell film 5 and the second solar cell film 6 are amorphous silicon cell films; the uncoiling part 4 can be made of plastic material rods and has certain elasticity.
The vibration excitation mechanism is used for exciting the double-spread solar wing to generate vibration, the double-spread solar wing vibration excitation mechanism comprises a signal processing module and an exciter 11, the signal processing module comprises a signal generator 12 and a power amplifier 13, the signal generator 12, the power amplifier 13 and the exciter 11 are sequentially connected, the exciter 11 of the embodiment is fixed on a ground base plate 8 and is connected with the middle part of an uncoiling part 4 through a push rod 14, the signal generator sends out a vibration signal, the vibration signal is amplified by the power amplifier 13 and then sent to the exciter, the exciter 11 generates vibration after receiving the signal, the push rod 14 drives the uncoiling part 4 to excite the double-spread solar wing to generate vibration, and the generated signal is changed to generate different vibrations to detect the vibration characteristics of the double-spread solar wing under different vibration excitation.
In the embodiment, the vibration exciter 11 is a vibration exciter with the model JZK-50 manufactured by GST company in U.S.A., the maximum exciting force of the vibration exciter 11 is 500N, the maximum amplitude is +/-12.5 mm, the maximum acceleration is 55g, the maximum input current is 30Arms, the frequency range is DC-2k, the external dimension is phi 240mm multiplied by 345mm, and the output mode is that the ejector rod 14 transmits force to the uncoiling part 4; the power amplifier 13 is a 50WD1000 power amplifier from AR in America, and operates at a frequency of DC-1000MHz.
The vibration detection mechanism comprises two groups of binocular vision systems and two trusses 15, the two trusses 15 are arranged in front and back in parallel, the two groups of binocular vision systems are in one-to-one correspondence with the two trusses 15, each group of binocular vision systems is arranged on the corresponding truss 15, that is to say, the two groups of binocular vision systems are respectively a front group of binocular vision systems and a back group of binocular vision systems, the front group of binocular vision systems are used for detecting vibration detection mark point areas in front of the upper surfaces of the first solar cell film 5 and the second solar cell film 6, and the back group of binocular vision systems are used for detecting vibration detection mark point areas in back of the upper surfaces of the first solar cell film 5 and the second solar cell film 6.
Further, each truss 15 is formed by an aluminum profile, and comprises a horizontal rod and two vertical rods, wherein two ends of the horizontal rod are respectively connected with one ends of the two vertical rods, the other ends of the two vertical rods are fixed on the inner side of the supporting platform 7, specifically, two ends of the horizontal rod are respectively connected with one ends of the two vertical rods through corner pieces, the other ends of the two vertical rods are respectively fixed on the inner side of the base plate 701 of the supporting platform 7 through corner pieces, and the distance between the horizontal rod of the truss 15 and the upper surface of the base plate 701 of the supporting platform 7 can be adjusted through controlling tightness of the corner pieces, namely, the height of the truss 15 is adjusted, so that the shooting height of the binocular vision system is adjusted.
As shown in fig. 1 to 5, each group of binocular vision system includes a first high-speed camera 16, a second high-speed camera 17, a laser 18, a guide rail 19, a first slider 20, a second slider 21, a third slider 22, a first pan-tilt 23, and a second pan-tilt 24, the guide rail 19 is fixed on a horizontal bar corresponding to the truss 15, the first slider 20, the second slider 21, and the third slider 22 are slidably disposed on the guide rail 19, i.e., the first slider 20, the second slider 21, and the third slider 22 are movable on the guide rail 19, and the third slider 22 is located between the first slider 20 and the second slider 21, the first high-speed camera 16 is disposed on the first pan-tilt 23, the second high-speed camera 17 is disposed on the second pan-tilt 24, the first cradle head 23 is fixed on the first sliding block 20, the second cradle head 24 is fixed on the second sliding block 21, the laser 18 is fixed on the third sliding block 22 and is positioned between the first high-speed camera 16 and the second high-speed camera 17, the horizontal positions of the first high-speed camera 16, the second high-speed camera 17 and the laser 18 can be adjusted by moving the first sliding block 20, the second sliding block 21 and the third sliding block 22, so that the position relation between the first high-speed camera 16 and the second high-speed camera 17 is changed, the angles of the first high-speed camera 16 and the second high-speed camera 17 and the shooting surface can be changed by adjusting the first cradle head 23 and the second cradle head 24, and the vibration detection needs of double-spread solar wings with various shapes and sizes can be met; the position of the high-speed camera enables the detection end surface to be approximately positioned in the middle of the view field of the high-speed camera when the double-spread solar wing is static, so that when the double-spread solar wing vibrates, the double-spread solar wing is always positioned in the view field range of the high-speed camera, the measurement continuity is guaranteed, and the optical axis of the high-speed camera is perpendicular to the surface of the solar cell film, so that the high-speed camera can shoot the surface of the solar cell film on the front side; the lasers 18 of the two groups of binocular vision systems project vibration detection mark points on the upper surface of the solar cell film to generate rectangular lattices with the same distance, the size, the distance, the color and the focal length of the points of the vibration detection mark lattices are adjustable, the vibration detection requirements of detection bodies with different sizes and different installation heights can be met, the lasers 18 can continuously work for a long time without generating light attenuation phenomenon, have stronger line forming effect, have shock resistance, reduce the influence caused by vibration of double-spread solar wings, and the color shapes of laser lattices generated by the front and rear lasers 18 of the two groups of binocular vision systems are different due to recognition and splicing, so that more accurate image recognition and splicing are facilitated.
Further, in the front group of binocular vision systems, the emitting port of the laser 18 is aligned with the front middle position of the double-spread solar wing, the lens of the first high-speed camera 16 is aligned with the vibration detection mark point area in front of the upper surface of the first solar cell film 5, and the lens of the second high-speed camera 17 is aligned with the vibration detection mark point area in front of the upper surface of the second solar cell film 6; in the rear group of binocular vision systems, the emitting port of the laser 18 is aligned with the rear middle position of the double-spread solar wing, the lens of the first high-speed camera 16 is aligned with the vibration detection mark point area at the rear part of the upper surface of the first solar cell film 5, and the lens of the second high-speed camera 17 is aligned with the vibration detection mark point area at the rear part of the upper surface of the second solar cell film 6; the images taken by the first high-speed camera 16 and the second high-speed camera 17 of the two sets of binocular vision systems are transmitted to the computer 25.
Further, in each group of binocular vision systems, the horizontal distance between the first high speed camera 16 and the second high speed camera 17 is 400mm, the distance between the lens of the first high speed camera 16 and the upper surface of the first solar cell film 5 is 800mm to 1000mm, and the distance between the lens of the second high speed camera 17 and the upper surface of the second solar cell film 6 is also 800mm to 1000mm.
In this embodiment, the first high-speed camera 16 and the second high-speed camera 17 are selected from the high-speed cameras of model Memrecam HX-3E of Tokyo corporation, having 500 ten thousand pixels, and having a frame rate of 2000 frames/second at the full resolution, 4670 frames/second at the full resolution, 9220 frames/second at 100 ten thousand pixels, and a memory of 64GB, a working temperature range of 0-40 ℃, a weight of about 5.9 kg, and a required power source of 100-240V AC-1.5A,50-60Hz; the laser 18 is a model ZLM100MTX650-16GD laser of Shenzhen Lai science and technology company, the laser wavelength is 650nm, the output power is 100mW, the working current is less than or equal to 180mA, the power supply voltage DC is 2.8-5.2V, the light spot mode, the dot matrix and the optical lens: grating sheet (german inlet).
The embodiment also provides a double-spreading solar wing vibration measurement method, which is realized based on the device and comprises the following steps:
step one, the lasers 18 of the two groups of binocular vision systems emit laser light to the double-spread solar wings, and vibration detection mark points are projected to the front upper surface and the rear upper surface of the first solar cell film 5 and the second solar cell film 6;
step two, the signal generator 12 sends out a vibration signal, and the vibration signal is amplified by the power amplifier 13 and then sent to the vibration exciter 11;
step three, the vibration exciter 11 transmits force to the uncoiling part 4 through the ejector rod 14 to excite the double-spread solar wing to generate vibration with different frequencies;
step four, in the process of double-spreading solar wing vibration, the first high-speed cameras 16 of the two groups of binocular vision systems synchronously shoot the vibration detection mark point areas on the front and rear upper surfaces of the first solar cell film 5 at high frequency, and the second high-speed cameras 17 of the two groups of binocular vision systems synchronously shoot the vibration detection mark point areas on the front and rear upper surfaces of the second solar cell film 6 at high frequency;
and fifthly, the computer 25 reads images shot by the first high-speed camera 16 and the second high-speed camera 17 of the two groups of binocular vision systems, the first high-speed camera 16 and the second high-speed camera 17 of the two groups of binocular vision systems are calibrated through a Zhang Zhengyou calibration method, the coordinates of laser points are calculated by extracting the light spot characteristics of the images, vibration information of the double-spread solar wing is obtained through further processing, visualization processing is carried out, and the results are displayed on a display.
In summary, the invention adopts two groups of binocular vision systems, the two groups of binocular vision systems are arranged on two trusses which are arranged in parallel front and back, the vibration excitation mechanism excites the double-spread solar wing to generate vibration, and the non-contact vibration measurement is carried out on the double-spread solar wing on the premise of no additional effect, so that the vibration information precision of the double-spread solar wing obtained by measurement is relatively high.
The above-mentioned embodiments are only preferred embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art can make equivalent substitutions or modifications according to the technical solution and the inventive concept of the present invention within the scope of the present invention disclosed in the present invention patent, and all those skilled in the art belong to the protection scope of the present invention.
Claims (6)
1. Double-spreading solar wing vibration measuring device is characterized in that: the vibration detection mechanism comprises two groups of binocular vision systems and two trusses, the two groups of binocular vision systems are in one-to-one correspondence with the two trusses, each group of binocular vision systems is arranged on the corresponding truss, and the two groups of binocular vision systems are used for detecting vibration detection mark point areas on the upper surfaces of the front part and the rear part of the double-spread solar wings;
the double-spreading solar wing is of a flexible structure and comprises a coiled spreading component, a triangular truss, a fixing component, an uncoiling component and two solar cell films, wherein the coiled spreading component is arranged in the middle of the fixing component, one end of the triangular truss is connected with the coiled spreading component, the other end of the triangular truss is connected with the middle of the uncoiling component, the two solar cell films are symmetrically arranged on the left side and the right side of the triangular truss, and the two ends of the two solar cell films are respectively connected with the fixing component and the uncoiling component; the vibration excitation mechanism is used for exciting the double-spread solar wing to generate vibration and comprises a signal processing module and a vibration exciter, wherein the signal processing module comprises a signal generator and a power amplifier, the signal generator, the power amplifier and the vibration exciter are sequentially connected, and the vibration exciter is connected with the middle part of the uncoiling part through a push rod;
each group of binocular vision system comprises two high-speed cameras, a laser, a guide rail, three sliding blocks and two cloud platforms, wherein the guide rail is fixed on a corresponding truss, the three sliding blocks are arranged on the guide rail in a sliding manner, the two high-speed cameras, the two cloud platforms and the two sliding blocks are in one-to-one correspondence, each high-speed camera is arranged on the corresponding cloud platform, each cloud platform is fixed on the corresponding sliding block, and the laser is fixed on the other sliding block and is positioned between the two high-speed cameras; in one group of binocular vision systems, the emitting port of the laser is aligned to the middle position of the front part of the double-spread solar wing and is used for projecting vibration detection mark points to the upper surface of the front part of the double-spread solar wing, and the lenses of the two high-speed cameras are aligned to the vibration detection mark point areas of the upper surface of the front part of the double-spread solar wing; in another group of binocular vision systems, the emitting port of the laser is aligned to the middle position of the rear part of the double-spread solar wing, and is used for projecting the vibration detection mark point to the upper surface of the rear part of the double-spread solar wing, and the lenses of the two high-speed cameras are aligned to the vibration detection mark point area of the upper surface of the rear part of the double-spread solar wing.
2. The double-spread solar wing vibration measurement apparatus according to claim 1, wherein: the device also comprises a supporting platform and a ground backing plate, wherein the double-spread solar wing is in parallel relation with the surface of the supporting platform, the fixing part is fixed on the supporting platform through two vertical square rods, the two trusses are respectively fixed on the inner side of the supporting platform through corner fittings, and the uncoiling part is fixed on the ground backing plate through the two vertical square rods.
3. The double-spread solar wing vibration measurement apparatus according to claim 2, wherein: the supporting platform comprises a base plate and four supporting feet, the fixing part is fixed on the upper surface of the base plate through two vertical rods, the two trusses are respectively fixed on the inner side of the base plate through corner fittings, and the four supporting feet are fixedly connected with the lower surface of the base plate.
4. A double-spread solar wing vibration measurement apparatus according to any one of claims 1 to 3, wherein: in each group of binocular vision system, the horizontal distance between the two high-speed cameras is 400mm, and the distance between the lenses of the two high-speed cameras and the upper surface of the double-spread solar wing is 800-1000 mm.
5. A double-spread solar wing vibration measurement apparatus according to any one of claims 1 to 3, wherein: each truss comprises a horizontal rod and two vertical rods, two ends of each horizontal rod are connected with one ends of the two vertical rods respectively, and the other ends of the two vertical rods are fixed.
6. A method of measuring vibration of a double-spread solar wing based on the apparatus of any one of claims 1 to 5, characterized in that: the method comprises the following steps:
the lasers of the two groups of binocular vision systems emit laser towards the double-spread solar wings, and vibration detection mark points are projected to the upper surfaces of the front and rear parts of the double-spread solar wings;
the signal generator of the vibration excitation mechanism sends out a vibration signal which is amplified by the power amplifier and then sent to the vibration exciter;
the vibration exciter generates vibration after receiving signals to excite the double-spread solar wing to generate vibration with different frequencies;
in the process of vibrating the double-spread solar wing, synchronous high-frequency shooting is carried out on vibration detection mark point areas on the upper surfaces of the front part and the rear part of the double-spread solar wing by using high-speed cameras of two groups of binocular vision systems, an image sequence is acquired, and the image sequence is sent to a computer;
the computer reads images shot by the high-speed cameras of the two groups of binocular vision systems, calibrates the high-speed cameras of the two groups of binocular vision systems, extracts the light spot characteristics of the images to calculate the coordinates of laser points, further processes the coordinates to obtain vibration information of the double-spread solar wing, performs visualization processing, and displays the result on the display.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810658122.8A CN108709625B (en) | 2018-06-25 | 2018-06-25 | Double-spreading solar wing vibration measuring device and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810658122.8A CN108709625B (en) | 2018-06-25 | 2018-06-25 | Double-spreading solar wing vibration measuring device and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108709625A CN108709625A (en) | 2018-10-26 |
| CN108709625B true CN108709625B (en) | 2024-01-30 |
Family
ID=63873028
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810658122.8A Active CN108709625B (en) | 2018-06-25 | 2018-06-25 | Double-spreading solar wing vibration measuring device and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108709625B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110095242A (en) * | 2019-05-29 | 2019-08-06 | 华南理工大学 | A kind of the reflecting surface vibration detection device and method of umbrella antenna |
| CN110579326B (en) * | 2019-09-25 | 2024-03-29 | 华南理工大学 | Vibration detection device and method for multi-rotary-joint space solar power station |
| 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107168398A (en) * | 2017-06-16 | 2017-09-15 | 华南理工大学 | Flexible wing vibration detection and control device and method based on high speed camera |
| CN107228748A (en) * | 2017-06-16 | 2017-10-03 | 华南理工大学 | Satellite antenna structural vibration measurement apparatus and method based on non-contact measurement |
| CN207036253U (en) * | 2017-07-18 | 2018-02-23 | 华南理工大学 | Double-flexibility cantilever beam vibration measure and control device based on Binocular stereo vision with laser |
| CN208383289U (en) * | 2018-06-25 | 2019-01-15 | 华南理工大学 | It is double to spread out solar wing vibration measurement device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8899115B2 (en) * | 2011-04-20 | 2014-12-02 | United Technologies Corporation | Method and system for locating a laser vibrometer during non-contact scanning |
-
2018
- 2018-06-25 CN CN201810658122.8A patent/CN108709625B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107168398A (en) * | 2017-06-16 | 2017-09-15 | 华南理工大学 | Flexible wing vibration detection and control device and method based on high speed camera |
| CN107228748A (en) * | 2017-06-16 | 2017-10-03 | 华南理工大学 | Satellite antenna structural vibration measurement apparatus and method based on non-contact measurement |
| CN207036253U (en) * | 2017-07-18 | 2018-02-23 | 华南理工大学 | Double-flexibility cantilever beam vibration measure and control device based on Binocular stereo vision with laser |
| CN208383289U (en) * | 2018-06-25 | 2019-01-15 | 华南理工大学 | It is double to spread out solar wing vibration measurement device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108709625A (en) | 2018-10-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108709625B (en) | Double-spreading solar wing vibration measuring device and method | |
| CN106017839B (en) | Based on flexible, hinged plate benging and twisting vibration detection control apparatus and method | |
| CN107421632B (en) | Double-flexible cantilever vibration measurement and control device and method based on laser binocular vision | |
| CN110132517B (en) | Multi-flexible piezoelectric beam coupling vibration analysis control device and method | |
| CN104776861B (en) | Flexible calibration device for calibrating wind tunnel vision measurement system | |
| CN108760023B (en) | Visual vibration measuring device and method for solar wing with two ends supported | |
| CN108801440B (en) | Flexible board bending vibration detection control device and method | |
| CN104567698A (en) | Both-end clamped piezoelectric beam vibration detection and control device based on non-contact type sensor | |
| CN105628321A (en) | Impact dynamic characteristic test device and test method of inflatable flexible structure | |
| WO2021120394A1 (en) | Slide-resistant pile-transparent soil slope system test apparatus and deformation measurement method | |
| CN112098025B (en) | Vibration detection control device and method for multiple flexible plates with swinging base | |
| CN208383289U (en) | It is double to spread out solar wing vibration measurement device | |
| CN207866248U (en) | A kind of field total powerstation | |
| CN108709632B (en) | Vibration detection device and method for guy cable connection flexible structure | |
| CN109060286B (en) | Digital speckle-based unmanned aerial vehicle low-frequency vibration detection device and method | |
| CN112098024A (en) | Multi-flexible cantilever beam moving and rotating vibration analysis device and control method | |
| CN108760025B (en) | Vibration detection device and method for multiple flexible boards | |
| CN110095242A (en) | A kind of the reflecting surface vibration detection device and method of umbrella antenna | |
| CN110031170A (en) | A kind of flexible hinged plate vibration measurement control device and control method | |
| CN105571470A (en) | On-line detection device for integral profile of tower type solar thermal power generation heliostat | |
| CN209945667U (en) | Multi-flexible piezoelectric beam coupling vibration analysis control device | |
| CN208861185U (en) | Flexible annular panel vibration detection control apparatus | |
| CN109186481B (en) | Device and method for detecting deformation and vibration of polygonal plate based on digital speckle | |
| CN209945668U (en) | Reflection surface vibration detection device of umbrella-shaped antenna | |
| CN212567655U (en) | Multi-spring connection double-moving-plate bending and torsion coupling vibration control device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |