Solar wing sailboard similarity experiment verification device

Abstract

The utility model belongs to the technical field of dynamic characteristic model experiments of satellite solar wing sailboards, and discloses a solar wing sailboard similarity experiment verification device. The solar wing sailboard is composed of three cellular boards, the cellular boards are connected with each other through hinges, two connecting rods are arranged in the middle of the sailboard to simulate pressing points, and the cellular boards are kept fixed in a folded state. The solar wing honeycomb combined thin plate structure is fixed to the stand column through the stand column connecting device and the pressing device, and the whole structure is placed on the vibration table. And designing a solar wing sailboard model according to the similarity relationship, and processing and manufacturing the scaling model. Testing the prototype and the scale model of the solar panel, predicting the dynamic characteristics of the prototype through the test result of the scale model, and analyzing the similarity of the dynamic characteristics of the solar panel.

Description

Technical Field

[0001] This utility model relates to the field of experimental technology of dynamic characteristic model of satellite solar panels, and in particular to a similar experimental verification device for solar panels. Background Technology

[0002] In aerospace, satellite solar panels have complex structures and large dimensions, and their dynamic characteristics and failure mechanisms are not yet fully understood. Due to limitations in theoretical modeling and simulation analysis, there are still discrepancies with reality, making it difficult to accurately reflect the vibration characteristics of satellite solar panels. Therefore, conducting dynamic characteristic tests on solar panels is an essential and crucial step in the design and development of solar panels. However, due to the complexity of solar panel structures, long development cycles, high testing risks, and high manufacturing costs, directly conducting dynamic characteristic tests on satellite solar panels remains very difficult. To address this problem, this invention utilizes similarity theory to design and manufacture a scaled-down prototype, ensuring that the dynamic characteristics of the scaled-down model reflect those of the original prototype, thereby reducing testing difficulty, shortening the testing cycle, and lowering testing costs. Utility Model Content

[0003] The purpose of this invention is to provide a similar experimental verification device for solar panels to solve the problems described in the background art.

[0004] The technical solution of this utility model is as follows: A similar experimental verification device for solar panels includes a vibration table, a support platform 6, a solar panel 5, a male hinge 4, a column 1, a female hinge 3, a column connecting device 2, a clamping device 7, and an acceleration sensor.

[0005] The support platform 6 is placed on the vibration table; the column 1 is fixed on the support platform 6; the column 1 is connected to the solar panel or the clamping device 7 through the column connecting device 2.

[0006] The solar panel 5 is composed of three honeycomb panels arranged parallel to each other vertically. Through holes are provided at the ends of the honeycomb panels for installing female hinges 3 or male hinges 4. The ends of the honeycomb panels are connected by female hinges 3 and male hinges 4, forming a serpentine connection. Two clamping devices 7 are arranged in the middle of the solar panel to simulate clamping points and maintain the honeycomb panels in a folded state. One end of the bottom honeycomb panel is connected to a column 1 via a column connecting device 2.

[0007] One accelerometer is positioned at the center of the cantilever of the top honeycomb panel, two accelerometers are positioned at the clamping points of the two clamping devices 7, two accelerometers are positioned at the male hinge 4 of the top honeycomb panel, and one accelerometer is positioned at the center of the male hinge 4 of the top honeycomb panel.

[0008] The clamping device 7 includes a clamping block, a connecting rod, and a nut; a through hole a is made at 1 / 2 the length of the honeycomb panel from the end through hole; the clamping block is connected to the column 1 through the column connecting device 2, corresponding to the position of the through hole a; one end of the connecting rod passes through the through hole a of the three honeycomb panels and is connected to the clamping block; the other end of the connecting rod is fastened with a nut.

[0009] The honeycomb panel has a honeycomb core structure, and the two end faces are connected to flat plates.

[0010] Compared with the prior art, the present invention has the following beneficial effects and advantages:

[0011] This invention presents a similarity test verification device for solar panels, demonstrating that the structure within the device can proportionally correlate with the motion response of an actual solar panel. This solves the problem of experimental verification of solar panel structural dynamics similarity methods and is primarily applied to vibration testing of products in the aerospace field. The solar panel similarity test verification device is tested, and the test results can be used to predict the dynamic characteristics of an actual solar panel based on proportionality, thus analyzing the similarity of the solar panel's dynamic characteristics. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0013] Figure 2 This is the supporting platform of the present invention;

[0014] Figure 3 This is a schematic diagram of the honeycomb panel of this utility model;

[0015] Figure 4 This is a schematic diagram of the honeycomb core of this utility model;

[0016] Figure 5 The curves are the average acceleration response curves collected by six acceleration sensors under different excitations; (a)-(d) are four different excitation conditions.

[0017] In the diagram, 1-column, 2-column connecting device, 3-female hinge, 4-male hinge, 5-solar wing panel, 6-support platform, 7-clamping device. Detailed Implementation

[0018] Various exemplary embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It should be noted that, unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these specific embodiments do not limit the scope of the present invention.

[0019] like Figure 1As shown, a similar experimental verification device for a solar panel includes a column 1, a column connecting device 2, a female hinge 3, a male hinge 4, a solar panel 5, a support platform 6, and a clamping device 7. The solar panel 5 is connected by the female hinge 3 and the male hinge 4. The connected solar panel 5 is then fastened to the column connecting device 2 and the clamping device 7 with bolts. The column connecting device 2 and the clamping device 7 are then installed on the column 1 by bolts. The installed device is then placed on the support platform 6. One accelerometer is positioned at the center of the cantilever end of the uppermost honeycomb panel, two accelerometers are positioned near the two clamping points, two other accelerometers are positioned at the male hinge 4 of the uppermost honeycomb panel, and one accelerometer is positioned at the center of the uppermost honeycomb panel on one side of the male hinge 4.

[0020] Based on the similarity experiment verification device for solar panels, two scaled-down solar panel devices were set up. The first and second solar panel devices used the same materials as the prototype solar panel, therefore the similarity ratio for elastic modulus, density, and Poisson's ratio was 1. The internal loss factor mainly considers the effect of the structural loss factor, which is generally determined by the subsystem. j The material property function determines that when the structural loss factor is less than 0.1, the difference in system response is very small. Empirical evidence shows that a 10% error in the structural loss factor will lead to a 1 dB error in response estimation, and a 100% error will lead to a 3 dB error in response estimation. Therefore, the similarity relationship of the internal damping loss factor can be approximately defined as... If the first and second solar panel devices are swept using the same amplitude as the prototype, then... To reduce manufacturing complexity, the hinge connection structure, connecting rods at the clamping points, bolts, pins, supports, tooling, and other structures are identical between the prototype solar panel and the first and second solar panel devices. Therefore, the thickness of the honeycomb panel prototype remains unchanged compared to the first and second solar panel devices. = 1. Set the acceleration response similarity ratio between the prototype solar panel and the first solar panel device to 1. According to the similarity formula of acceleration response It can be concluded that So for There are multiple possible values ​​for , but due to the size effect, the length and width similarity ratio of the honeycomb panel model cannot differ too much. Therefore, the length and width similarity ratios of the honeycomb panels of the first solar panel device and the solar panel prototype are as follows: =0.5, = 0.5. Let the acceleration response similarity ratio between the prototype solar panel and the second type of solar panel device be 0.5. According to the acceleration response similarity formula It can be concluded that The similarity ratios of the length and width of the honeycomb panel in the second type of solar panel device and the prototype solar panel are as follows: = 2, = 2. Based on the dimensional similarity between the solar panel prototype and the two types of solar panel devices, a scaled-down model was manufactured. The solar panel 5 and column 1 of the scaled-down model of the honeycomb composite thin plate structure were fastened and installed and subjected to vibration response tests in the same manner. The acceleration responses of the two types of solar panel devices were collected and compared with the acceleration response curves of the solar panel prototype to verify whether the acceleration response similarity ratio was equal to the set acceleration response similarity ratio.

[0021] The test was conducted using the aforementioned solar panel dynamic similarity test rig, including the following steps:

[0022] Step 1: Select a honeycomb composite thin plate prototype. The parameters of the honeycomb composite thin plate prototype designed and manufactured are shown in Table 1.

[0023] Table 1. Parameters of the prototype structure of the honeycomb composite thin plate

[0024]

[0025] Step 2: Conduct vibration response tests on the honeycomb composite thin plate prototype:

[0026] Vibration response test of honeycomb composite thin plate structure;

[0027] The prototype was tested by placing one accelerometer at the center of the cantilever end of the top honeycomb panel, two accelerometers near the two clamping points, two accelerometers at the two hinges, and a final accelerometer at the center of one hinge boundary. A sinusoidal excitation frequency sweep of 4 Oct / min was input to a vibration table with amplitudes of 0.1g, 0.15g, 0.2g, and 0.25g, covering a frequency range of 5-500 Hz for the prototype structure. As the frequency changed, the signals collected by the accelerometers were continuously transmitted to the LMS data acquisition system. The data acquired by the LMS system was saved to a computer, and after analysis and processing, the acceleration response curves of the honeycomb composite thin plate prototype were plotted using specialized plotting software. Figure 5 The average acceleration response collected by six acceleration sensors was plotted to represent the global vibration response.

[0028] Step 3: Based on the dynamic similarity theory of honeycomb composite thin plates, determine the similarity relationships of various parameters between the two solar panel devices and the solar panel prototype, and design and manufacture honeycomb composite thin plate structural models. The specific steps for creating two honeycomb composite thin plate models in this invention are as follows:

[0029] Step A: Determine the parameters of the honeycomb composite thin plate for the first type of solar panel device;

[0030] Since the first solar panel device uses the same material as the prototype solar panel, the similarity ratio of elastic modulus, density, and Poisson's ratio is 1. The internal loss factor mainly considers the effect of the structural loss factor, which is generally determined by the subsystem. j The material property function determines that when the structural loss factor is less than 0.1, the difference in system response is very small. Empirical evidence shows that a 10% error in the structural loss factor will lead to a 1 dB error in response estimation, and a 100% error will lead to a 3 dB error in response estimation. Therefore, the similarity relationship of the internal damping loss factor can be approximately defined as... Similarly, the same amplitude was used to sweep the frequency of the honeycomb panel model. To reduce manufacturing complexity, the hinge connection structure, connecting rods at the clamping points, bolts, pins, supports, tooling, and other structures are identical between the prototype solar panel and the first type of solar panel device. Therefore, the thickness of the prototype solar panel remains unchanged from the first type of solar panel device. = 1. Let According to the formula It can be concluded that So for There are multiple possible values ​​for , but due to the size effect, the length and width similarity ratio of the honeycomb panel model cannot differ too much.

[0031] The similarity ratios of the length, width, and thickness of the honeycomb panel in the first solar panel device and the prototype solar panel are as follows:

[0032] Length similarity ratio: = 0.5

[0033] Width similarity ratio: = 0.5

[0034] Thickness similarity ratio: = 1

[0035] Step B: Determine the structural dimensional parameters of the first type of solar panel device using honeycomb composite thin panels;

[0036] Based on the analysis in step A, the structural dimensional parameters of scaled-down model 1 are shown in Table 2.

[0037] Table 2 Structural parameters of scaled-down model 1 of honeycomb composite thin plate

[0038]

[0039] Step C: Determine the parameters of the honeycomb composite thin plate for the second type of solar panel device;

[0040] If the second type of solar panel device uses the same material as the prototype solar panel, then the similarity ratio of its elastic modulus, density, and Poisson's ratio is 1. The similarity relationship of the internal damping loss factor of the second type of solar panel device is also defined as... The second type of solar panel device was subjected to frequency sweep using the same amplitude. The hinge connection structure, clamping point connecting rods, bolts, pins, supports, tooling, and other structures of the prototype and the second type of solar panel are identical. Therefore, the thickness of the prototype and the second type of solar panel remains unchanged. = 1. Let According to the formula It can be concluded that Similarly, due to the size effect, the length and width similarity ratio of the honeycomb panel model cannot differ too much.

[0041] therefore:

[0042] The similarity ratios of the length, width, and thickness of the honeycomb panel in the second type of solar panel device to the prototype solar panel are as follows:

[0043] Length similarity ratio: = 2

[0044] Width similarity ratio: = 2

[0045] Thickness similarity ratio: = 1

[0046] Step D: Determine the structural dimensional parameters of the second type of solar panel device;

[0047] Based on the analysis in step C, the structural dimensional parameters of the second type of solar panel device are shown in Table 3.

[0048] Table 3 Structural parameters of scaled-down model 2 of honeycomb composite thin plate

[0049]

[0050] Step 4: Fabricate and manufacture the honeycomb composite thin plate model according to its structural parameters;

[0051] Step 5: Conduct vibration response tests on the honeycomb composite thin plate model:

[0052] Vibration response test of honeycomb composite thin plate structure;

[0053] Similar to the vibration response test of the solar panel prototype, one accelerometer was placed at the center of the cantilever of the uppermost honeycomb panel, two accelerometers were placed at the clamping points of the two clamping devices 7, two accelerometers were placed at the male hinge 4 of the uppermost honeycomb panel, and one accelerometer was placed at the center of the uppermost honeycomb panel on one side of the male hinge 4. A sinusoidal excitation sweep frequency of 4 Oct / min was input to the vibration table, with amplitudes of 0.1g, 0.15g, 0.2g, and 0.25g, covering a sweep frequency range of 5-2000 Hz. As the frequency changed, the signals collected by the accelerometers were continuously transmitted to the LMS data acquisition system. The data collected by the LMS data acquisition system was saved to a computer, and after data analysis and processing, the acceleration response curve of the honeycomb composite thin plate model was plotted using professional plotting software. The acceleration response curves of the solar panel prototype and the two solar panel devices were plotted together as shown in the figure. Figure 5 As shown; P-0.1g, P-0.15g, P-0.2g, and P-0.25g represent the actual acceleration responses of the solar panel prototype under excitations of 0.1g, 0.15g, 0.2g, and 0.25g, respectively. M-0.1g, M-0.15g, M-0.2g, and M-0.25g represent the acceleration responses of the first type of solar panel device under excitations of 0.1g, 0.15g, 0.2g, and 0.25g, respectively; M(R) is the predicted acceleration response value of the solar panel prototype calculated based on the similarity ratio of the first type of solar panel device.

Claims

1. A solar wing sail similar experiment verification device, characterized in that, The vibration table, the support table (6), the solar wing sailboard (5), the male hinge (4), the stand (1), the female hinge (3), the stand connecting device (2), the pressing device (7) and the acceleration sensor are included. The support table (6) is placed on the vibration table; the stand (1) is fixed on the support table (6); the stand (1) is connected with the solar wing sailboard or the pressing device (7) through the stand connecting device (2). The solar wing sailboard (5) is composed of three honeycomb plates, the three honeycomb plates are arranged in parallel with each other from top to bottom, the end of the honeycomb plate is provided with a through hole, the through hole is used for installing the female hinge (3) or the male hinge (4); the honeycomb plates are connected through the female hinge (3) and the male hinge (4) between the end of the honeycomb plate, the connection form of the three honeycomb plates forms a snake-shaped connection; two pressing devices (7) are arranged in the middle of the solar wing sailboard, which are used for simulating the pressing point and keeping the fixed honeycomb plate in the folded state; one end of the lowermost honeycomb plate is connected with the stand (1) through the stand connecting device (2). One acceleration sensor is arranged at the center position of the cantilever of the uppermost honeycomb plate, two acceleration sensors are arranged at the pressing points of the two pressing devices (7) respectively, two acceleration sensors are arranged at the male hinge (4) of the uppermost honeycomb plate respectively, and one acceleration sensor is arranged at the center position of the male hinge (4) of the uppermost honeycomb plate.

2. The solar wing panel similar experiment verification device according to claim 1, characterized in that, The pressing device (7) includes a pressing block, a connecting rod and a nut; a through hole a is formed at a position 1 / 2 of the length of the honeycomb plate from the end of the honeycomb plate, the pressing block is connected with the stand (1) through the stand connecting device (2) and corresponds to the position of the through hole a; one end of the connecting rod passes through the through hole a of the three honeycomb plates and is connected with the pressing block; the other end of the connecting rod is fastened by the nut.

3. The solar wing panel similar experiment verification device according to claim 1, characterized in that, The inner core of the honeycomb plate adopts a honeycomb core structure, and the two end faces are connected with flat plates.

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