Device for measuring interlayer friction coefficient of solar blanket on spacecraft

Abstract

The present disclosure relates to a device for measuring interlayer friction coefficient of a solar blanket on a spacecraft, comprising a base, a compression assembly, a counterweight assembly, a sample, a traction assembly and a measuring assembly. The compression assembly is arranged on the base, and comprises a first pressing plate for clamping the solar blanket and a second pressing plate movably connected with the first pressing plate; the counterweight assembly is arranged above the second pressing plate and provides a compression force to the solar blanket through the second pressing plate; the sample is inserted into the interlayer of the solar blanket; the traction assembly is arranged on the base; one end of the measuring assembly is connected with the sample, and the other end is connected with the traction assembly; the traction assembly provides a pulling force to the sample through the measuring assembly; and the measuring assembly is used for measuring the pulling force. The measuring device provided by the present disclosure can directly measure the interlayer friction of the solar blanket, and has smaller measurement error compared with the prior art scheme which excessively simplifies the friction environment of the solar blanket, and can meet the engineering requirements.

Description

Technical Field

[0001] This disclosure relates to the field of aerospace technology, specifically to a device for measuring the friction coefficient between layers of a solar blanket on a spacecraft. Background Technology

[0002] With the development of aerospace technology, more and more spacecraft are adopting flexible solar panels. As a primary power generation component, the solar blanket is a crucial part of the flexible solar panel. The solar blanket contains solar cells and has low stiffness. During the spacecraft launch phase, it needs to be compressed and held firmly against the satellite to withstand the impact and vibration loads of the launch. In the compressed state, the folded solar blanket resists delamination under impact and vibration conditions through interlayer friction. To ensure the reliability of the solar blanket's fixation during launch, the risk of it slipping must be eliminated.

[0003] When the clamping force is too high, the solar panels on the sun blanket are prone to breakage; when the clamping force is too low, the friction between the layers of the sun blanket is insufficient to resist the delamination movement under impact and vibration conditions, and the sun blanket is prone to slippage and breakage. In order to obtain a suitable clamping force, it is necessary to measure the coefficient of friction between the layers of the sun blanket under different pressure conditions to determine the appropriate clamping force.

[0004] Existing technologies oversimplify the friction environment of solar blankets, resulting in large measurement errors that fail to meet engineering requirements. Utility Model Content

[0005] This disclosure provides a device for measuring the coefficient of friction between layers of a solar blanket on a spacecraft in order to address the problems existing in the prior art.

[0006] According to a first aspect of this disclosure, a measuring device for the interlayer friction coefficient of a solar blanket on a spacecraft is provided, comprising: Base; A clamping assembly is disposed on the base. The clamping assembly includes a first pressure plate and a second pressure plate for clamping the sun blanket. The first pressure plate is fixed on the base, and the second pressure plate is configured to be movably connected to the first pressure plate. A counterweight assembly, which is placed above the second pressure plate and configured to provide a clamping force to the sun blanket through the second pressure plate; A sample, which is configured to be inserted between the layers of the solar blanket; A traction assembly, wherein the traction assembly is disposed on the base; A measuring component, one end of which is connected to the sample and the other end of which is connected to the traction component; the traction component is configured to provide tension to the sample through the measuring component; the measuring component is configured to measure the tension.

[0007] In one embodiment of this disclosure, the sun blanket includes a flexible substrate folded into at least four layers, with at least two adjacent flexible substrate layers having simulated solar cells or glass covers attached to their opposing surfaces; the opposing surfaces of at least two adjacent flexible substrate layers are configured to maintain the original surfaces of the flexible substrate; and the sample is configured to be consistent with the interlayer material to be tested.

[0008] In one embodiment of this disclosure, the first pressure plate is configured to be locked in the position after being pressed by the counterweight assembly by a locking device.

[0009] In one embodiment of this disclosure, the locking device is a screw configured to pass through the first pressure plate and lock together with the second pressure plate.

[0010] In one embodiment of this disclosure, an elastic device is provided between the measuring component and the traction component, and the traction force provided by the traction component is configured to be transmitted backward through the elastic device.

[0011] In one embodiment of this disclosure, two measuring components are provided, and the two measuring components are configured to be connected to the sample respectively via a first traction rope. The two sides of the traction component are configured to be connected to the two measuring components respectively via a second traction rope.

[0012] In one embodiment of this disclosure, a pad is provided at the bottom of the measuring component, and the measuring device is configured to set its height by means of the pad, such that the first traction rope and the sample are at the same horizontal level.

[0013] In one embodiment of this disclosure, the traction assembly includes: A loading support is configured to be mounted on the base; a nut is provided on the loading support. A loading beam is configured to be located on the loading support and to be connected to the measuring component via the second traction rope; A loading screw is configured to engage with the nut, with one end of the loading screw configured to connect to the loading beam and the other end configured to have a keyway.

[0014] In one embodiment of this disclosure, the loading support is configured to be mounted on the base by an adjusting screw; and the loading support is configured to hold the second traction rope at the same height as the sample by the adjusting screw.

[0015] In one embodiment of this disclosure, an adjusting shim is provided between the base and the loading support.

[0016] One beneficial effect of this disclosure is that, by setting up a first and second pressure plate with movable connections to hold the sun blanket, the sample is inserted between the layers of the sun blanket during testing. A counterweight component is applied to the second pressure plate to simulate the actual storage environment of the sun blanket at high altitude, thus enabling direct measurement of the interlayer friction force of the sun blanket. The testing device of this disclosure has small measurement errors and can meet engineering requirements.

[0017] Other features and advantages of this disclosure will become clear from the following detailed description of exemplary embodiments with reference to the accompanying drawings. Attached Figure Description

[0018] The accompanying drawings, which are incorporated in and form a part of this specification, illustrate embodiments of the present disclosure and, together with their description, serve to explain the principles of the present disclosure.

[0019] Figure 1 This is a schematic diagram of the structure of the measuring device disclosed herein; Figure 2 This is a side view of the measuring device disclosed herein; Figure 3 This is a schematic diagram of the structure of the solar blanket to be tested disclosed in this publication; Figure 4 This is a schematic diagram of the structure of the sample with the adhesive material disclosed in this publication; Figure 5 This is a schematic diagram of the structure of the uncoated sample disclosed in this invention; Figure 6 This is a schematic diagram of the measurement data of the measuring device disclosed herein.

[0020] Figures 1 to 6 The one-to-one correspondence between the component names and the reference numerals in the figures is as follows: 1. Base; 2. Pressing assembly; 21. First pressure plate; 22. Second pressure plate; 23. Locking device; 3. Sun blanket; 31. Flexible substrate; 32. Foam board; 4. Sample; 5. Traction assembly; 51. Loading support; 52. Loading beam; 53. Loading screw; 54. Adjusting screw; 55. Adjusting shim; 6. Measuring assembly; 61. First traction rope; 62. Second traction rope; 63. Pad; 7. Elastic device. Detailed Implementation

[0021] Various exemplary embodiments of the present disclosure 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 embodiments do not limit the scope of the present disclosure.

[0022] The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit this disclosure or its application or use.

[0023] Techniques, methods, and equipment known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and equipment should be considered part of the specification.

[0024] It should be noted that similar labels and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be discussed further in subsequent figures.

[0025] In this article, terms such as "up," "down," "front," "back," "left," and "right" are used only to indicate the relative positional relationship between related parts, rather than to define the absolute position of these related parts.

[0026] In this article, "first," "second," etc., are used only to distinguish one another, and not to indicate degree of importance, order, or prerequisite for each other.

[0027] In this document, terms such as “equal” and “same” are not strict mathematical and / or geometric limitations, but also include errors that are understandable to those skilled in the art and permissible in manufacturing or use.

[0028] To address the problems existing in the prior art, this disclosure provides a measuring device for the coefficient of friction between layers of a solar blanket on a spacecraft, comprising at least: a base, a clamping assembly, a counterweight assembly, a sample, a traction assembly, and a measuring assembly. The base provides the foundation for mounting the entire measuring device. The clamping assembly is disposed on the base and includes a first pressure plate and a second pressure plate for clamping the solar blanket. The first pressure plate is fixed to the base, and the second pressure plate is movably connected to the first pressure plate. The counterweight assembly is placed above the second pressure plate and provides clamping force to the solar blanket through the second pressure plate. The counterweight assembly can be any object of known weight. When it is necessary to measure the frictional force between two layers of the solar blanket, the sample is inserted between the layers of the solar blanket. The traction assembly is disposed on the base and provides a pulling force capable of pulling the sample. The measuring assembly is used to measure the pulling force. One end of the measuring assembly is connected to the sample, and the other end is connected to the traction assembly, which provides the pulling force to the sample through the measuring assembly.

[0029] The measuring device provided in this disclosure uses a first and second pressure plate with movable connections to hold the sun blanket. During testing, the sample is inserted between the layers of the sun blanket, and a counterweight component is applied to the second pressure plate to simulate the actual storage environment of the sun blanket at high altitude, thereby enabling direct measurement of the interlayer friction force of the sun blanket. The measuring device of this disclosure has a small measurement error and can meet engineering requirements.

[0030] The specific embodiments of this disclosure are described below with reference to the accompanying drawings.

[0031] This disclosure provides a device for measuring the coefficient of friction between layers of a solar blanket on a spacecraft, such as... Figure 1 and Figure 2 As shown, the measuring device includes at least: a base 1, a clamping assembly 2, a counterweight assembly (not shown), a sample 4, a traction assembly 5, and a measuring assembly 6. The base 1 provides the foundation for mounting the entire measuring device. The clamping assembly 2 is mounted on the base 1 and includes a first pressure plate 21 and a second pressure plate 22 for clamping the sun blanket 3. The first pressure plate 21 is fixed to the base 1, and the second pressure plate 22 is movably connected to the first pressure plate 21. The areas of the first pressure plate 21 and the second pressure plate 22 can be the same. The counterweight assembly is placed above the second pressure plate 22 and provides clamping force to the sun blanket 3 through the second pressure plate 22. The counterweight assembly can be any object with a known weight. When it is necessary to measure the frictional force between two layers of the sun blanket 3, the sample 4 is inserted between the layers of the sun blanket 3. The traction assembly 5 is mounted on the base 1 and provides a pulling force capable of pulling the sample 4. The measuring component 6 is used to measure the tensile force. One end of the measuring component 6 is connected to the sample 4, and the other end is connected to the traction component 5. The traction component 5 provides tensile force to the sample 4 through the measuring component 6.

[0032] During the measurement process, the traction component 5 provides a pulling force capable of moving the sample 4. The measuring component 6 may include a force sensor and a data acquisition device. The force sensor and data acquisition device can record in real time the value of the pulling force on the sample 4 during the time period from when the sun blanket 3 has not been pulled to when it has been pulled a certain distance. After recording these values, the weight of the counterweight component is changed and the above process is repeated.

[0033] The existing methods for measuring the interlayer friction of a solar blanket 3 are relatively simple. Typically, samples are taken from different parts of the solar blanket 3 to create test samples 1, 2, 3, etc. Test sample 1 is first fixed on a test bench, then test sample 2 is pressed against the upper surface of test sample 1. Test sample 2 is then dragged and slid, and the sliding resistance is measured. The friction coefficient between test samples 1 and 2 is then measured using this sliding resistance, and so on, to complete the measurement of the friction coefficient between different interfaces. However, existing techniques cannot directly measure the interlayer friction coefficient of the solar blanket 3. They oversimplify the friction environment of the solar blanket 3, resulting in significant measurement errors and failing to meet engineering requirements.

[0034] The measuring device provided in this disclosure, by setting a first pressure plate 21 and a second pressure plate 22 that can clamp the solar blanket 3, allows the entire solar blanket 3 to be clamped between the first pressure plate 21 and the second pressure plate 22 as the test object. When it is necessary to measure the frictional force between two layers of the solar blanket 3, the sample 4 is inserted between the two layers of the solar blanket 3, the traction component 5 provides tension to the sample 4, and the measuring component 6 records the tension experienced by the sample 4 from rest to displacement of a certain distance, thereby enabling direct measurement of the interlayer frictional force of the solar blanket 3. Compared with the prior art solutions that oversimplify the frictional environment of the solar blanket 3, the measuring device provided in this disclosure has a smaller error and can meet engineering requirements.

[0035] In one embodiment of this disclosure, such as Figure 1 , Figure 2 and Figure 3 As shown, the solar blanket 3 includes a flexible substrate 31 folded into at least four layers. Simulated solar cells or glass covers are attached to the opposing surfaces of at least two adjacent flexible substrate layers 31. The opposing surfaces of at least two adjacent flexible substrate layers 31 retain the original surfaces of the flexible substrate 31. The sample 4 is consistent with the interlayer material to be tested. Opposing surfaces refer to the two surfaces of the flexible substrate 31 that are in contact with each other in the folded state, such as... Figure 3 As shown, the opposite surfaces refer to the upper and lower surfaces in the interlayer gap indicated by the arrow.

[0036] It should be noted that the glass cover is a key protective component of the spacecraft's solar cell array, primarily used to protect the cells from damage caused by high-energy particle radiation and the harsh space environment. In actual testing, the situation of attaching simulated solar cells under real-world conditions can be simulated by attaching glass covers to the opposing surfaces of at least two adjacent flexible substrate layers 31.

[0037] Specifically, in the actual testing process, the frictional force of two contact interfaces can be tested: the frictional force between simulated battery cells and the frictional force between flexible substrates 31. Based on this, when testing the frictional force between simulated battery cells, the structure of sample 4 is identical to that of the simulated battery cell, and the material composition is the same. That is, a flexible substrate covered with simulated battery cells is selected as sample 4, and sample 4 is inserted into the interlayer between the layers with simulated battery cells on the opposite surface during the test. Similarly, when testing the frictional force between flexible substrates 31, the structure of sample 4 is identical to that of flexible substrate 31, and the material composition is the same. Sample 4 is inserted into the interlayer between the layers with flexible substrate 31 on the opposite surface during the test.

[0038] Those skilled in the art will know that the solar blanket 3 is a combination of a battery, a flexible substrate 31, and a cable. Its coefficient of friction is related to factors such as the battery distribution pattern and battery height. Existing technologies simplify the friction test process but do not take into account the above-mentioned influences, resulting in a large deviation between the test results and the actual results. By using a sample 4 that is consistent with the interlayer material to be tested and inserting the sample 4 into the interlayer formed by the relative surfaces of the simulated battery sheet or glass cover, or the flexible substrate 31, compared with the existing technology, the actual state of the solar blanket 3 during the folding and retraction process can be directly simulated, thereby more accurately reflecting the interlayer friction characteristics of the solar blanket 3 under actual working conditions and effectively reducing test errors.

[0039] In one embodiment of this disclosure, such as Figure 1 As shown, the second pressure plate 22 is locked in the position after pressure is applied by the counterweight assembly via the locking device 23. The locking device can be a screw, a spring clip, a spring pin, etc. In the actual test, after the positions of the sun blanket 3 and the sample 4 are adjusted, the counterweight assembly can be placed on the second pressure plate 22, and the distance between the second pressure plate 22 and the first pressure plate 21 can be recorded. Then, the second pressure plate is locked in the position after pressure is applied by the counterweight assembly via the locking device 23. Afterward, the counterweight assembly is removed, and the distance between the second pressure plate 22 and the first pressure plate 21 is adjusted to be equal to the distance between them when the counterweight assembly is not removed, so as to ensure that the pressure applied to the sun blanket 3 is equal before and after. Through this equivalence, compared with the scheme where the counterweight assembly is never removed during the test, it is possible to effectively prevent the counterweight assembly from falling off during the pulling of the sample 4.

[0040] In one embodiment of this disclosure, such as Figure 1 As shown, specifically, the locking device 23 is a screw that passes through the first pressure plate 21 and locks together with the second pressure plate 22. The adjustability of the screw structure allows for fine-tuning of the locking force, facilitating precise control of the pressure according to different testing requirements. Furthermore, screws, as standard parts, offer advantages such as low cost, ease of acquisition and replacement, and their compact structure does not occupy excessive space, making the overall design of the testing device more concise.

[0041] In one embodiment of this disclosure, such as Figure 1As shown, an elastic device 7 is provided between the measuring component 6 and the traction component 5, through which the traction force provided by the traction component 5 is transmitted backward. In the entire measuring device, the position of the traction component 5 is defined as the relatively rear, and the position of the pressing component 2 is defined as the relatively front. The elastic device 7 can be a spring or a silicone elastomer. In a specific embodiment of this disclosure, the elastic device 7 is a tension spring. When the traction component 5 provides a backward traction force to the sample 4, the tension spring can buffer the traction force, making the force application process smoother and avoiding damage to the measuring component 6 and the sample 4 from instantaneous impact, while improving the stability and repeatability of the measurement data.

[0042] In one embodiment of this disclosure, such as Figure 1 As shown, two measuring components 6 are provided. Each measuring component 6 is connected to the sample 4 via a first traction rope 61. The two sides of the traction component 5 are connected to the two measuring components 6 via second traction ropes 62. The left and right sides of the traction component 5 are defined as the two sides in the horizontal direction perpendicular to the front-back direction. By setting up two measuring components 6 and adopting a double traction rope structure, synchronous measurement of the force state at different parts of the sample 4 is achieved. The two measuring components 6 are connected to the sample 4 via independent first traction ropes 61, enabling synchronous acquisition of the tensile force data of the sample 4, effectively avoiding data deviations that may occur with single-point measurements. Furthermore, the traction component 5 connects the two measuring components 6 via second traction ropes 62 on both sides, forming a stable force transmission path and ensuring uniform distribution of the traction force. This layout not only improves the reliability of the measurement data but also detects possible eccentric forces on the sample 4 during the test, ensuring the stability of the measurement system under dynamic loading conditions. Simultaneously, the mutual verification of the dual-path measurement data significantly improves the accuracy of the test results.

[0043] In one embodiment of this disclosure, such as Figure 1 As shown, a pad 63 is provided at the bottom of the measuring component 6. The height of the measuring component 6 is set by the pad 63 so that the first traction rope 61 and the sample 4 are at the same horizontal level. In the actual measurement process, when it is necessary to measure the interlayer friction force of the sun blanket 3 at different heights, the height of the pad 63 can be adjusted to keep the tension on the sample 4 horizontal. The pad 63 ensures that the first traction rope 61 and the sample 4 are horizontally aligned, eliminates measurement errors caused by height differences, ensures that the traction force is accurately transmitted in the horizontal direction, maintains the structural stability of the measuring system, and avoids interference from the test by the component force whose direction of action is inconsistent with the tensile direction of the sample, thereby ensuring the accuracy and reliability of the test data.

[0044] It should be noted that during the actual measurement process, there may be a slight difference in the height of the first traction rope 61 and the horizontal plane of the sample 4 due to changes in traction force. This is unavoidable, and such minor errors are permissible without violating the basic requirements of the technical solution of this disclosure.

[0045] In one embodiment of this disclosure, such as Figure 1 As shown, the traction assembly 5 includes a loading support 51, a loading beam 52, and a loading screw 53. The loading support 51 is mounted on the base 1. A nut is provided on the loading support 51. The loading beam 52 is located on the loading support 51 and connected to the measuring assembly 6 via a second traction rope 62. The loading screw 53 engages with the nut, with one end connected to the loading beam 52 and the other end having a keyway. In the actual measurement process, an L-shaped wrench can be inserted into the keyway of the loading screw 53, and then the L-shaped wrench can be rotated to make the loading screw 53 rotate axially, thereby causing the loading beam 52 to move away from the clamping assembly 2. The movement of the loading beam 52 can cause the second traction rope 62 to move in the same direction, and so on, ultimately causing the sample 4 to move away from the clamping assembly 2, thus applying a traction force to the sample 4. Simultaneously, the force is monitored by the measuring assembly 6, completing the measurement of the interlayer friction force of the solar blanket 3.

[0046] The design of the traction assembly 5, through the rigid fixation of the loading support 51 and the threaded engagement of the loading screw 53, enables control over the displacement of the loading beam 52, thereby ensuring the stability and repeatability of the tensile load on the specimen 4. The screw connection between the loading support 51 and the base 1 provides a reliable installation reference, while the keyway structure of the loading screw 53 facilitates the matching and use of operating tools and effectively prevents slippage, making the application of the loading force more precise and controllable. The structural design of the traction assembly 5 not only improves the accuracy of the test data but also enhances the ease of operation of the entire system.

[0047] In one embodiment of this disclosure, such as Figure 1 As shown, the loading support 51 is mounted on the base 1 by adjusting screw 54, and the loading support 51 keeps the second traction rope 62 at the same height as the sample 4 by adjusting screw 54.

[0048] It should be noted that during the actual measurement process, there may be a slight difference in the height of the second traction rope 62 and the horizontal plane of the sample 4 due to changes in traction force. This is unavoidable, and such minor errors are permissible without violating the basic requirements of the technical solution of this disclosure.

[0049] The height of the loading support 51 is adjusted by adjusting screw 54 to ensure that the second traction rope 62 and the specimen 4 are kept at the same horizontal position. This effectively eliminates the lateral force caused by the angular deviation of the second traction rope 62, allowing the tensile load to be transmitted entirely along the axial direction of the specimen, thus improving the accuracy and reliability of the test data. At the same time, this adjustable structure can adapt to the installation requirements of specimens of different sizes, enhancing the versatility and operational flexibility of the equipment and ensuring accurate mechanical loading under different experimental conditions.

[0050] In one embodiment of this disclosure, such as Figure 1 As shown, an adjusting shim 55 is provided between the base 1 and the loading support 51. By adding or removing the number of adjusting shims 55 or replacing them with shims of different thicknesses during actual measurement, the height of the loading support 51 can be finely adjusted, thereby precisely controlling the traction angle of the second traction rope 62 and avoiding test errors caused by height deviations. This structural design not only improves the stability and repeatability of the test but also enhances the adaptability of the equipment to samples of different sizes, while simplifying the adjustment process and making operation more convenient and reliable.

[0051] The measuring device disclosed herein can be used to measure the maximum static friction force between the layers of a sun blanket 3. Static friction is the force generated on the contact surface that opposes the tendency of two objects to move relative to each other but has not yet begun to slide relative to each other. Its magnitude and direction are automatically adjusted according to changes in external force to prevent the objects from starting to slide, but its maximum value is determined by the roughness of the contact surface and the normal force, and is called the maximum static friction force.

[0052] To facilitate understanding of how the measuring device of this disclosure is used, the entire testing process for the maximum static friction force is described here. It should be noted beforehand that, to ensure that the sample 4 slides relative to the sun blanket 3, one or more gradations are set on the sample 4 before measurement. The case of setting two gradations, namely gradation A and gradation B, is as follows... Figure 4 and Figure 5 As shown, the arrow indicates the direction in which the traction component 5 pulls the sample 4 during the measurement process.

[0053] The specific operating steps of the measurement process are as follows: 1. Insert the sample 4 into the interface of the solar blanket 3 where the measurement is to be performed, such as... Figure 4 and Figure 5 As shown, the scribe line A of the sample 4 is aligned with the side edge of the sun blanket 3.

[0054] 2. Place a counterweight assembly of known mass above the second pressure plate 22 to apply pressure to the foam board 32 and the sun blanket 3 (when the sun blanket 3 is folded, its weight is as follows). Figure 3(The two ends are provided with foam boards 32 for protecting the sun blanket 3). The distance between the first pressure plate 21 and the second pressure plate 22 at this time is recorded as L1.

[0055] 3. Lock the locking device 23 between the first pressure plate 21 and the second pressure plate 22. After the locking device 23 is locked, the distance between the first pressure plate 21 and the second pressure plate 22 remains L1. 4. Remove the counterweight assembly applied to the second pressure plate 22; 5. Start the data acquisition device to continuously record the measurement data from the tension sensor; 6. Continuously and slowly rotate the loading screw 53 to apply tension to the sample 4; 7. Observe the movement of sample 4 through the gradation lines A and B on sample 4; 8. Stop the test when the specimen 4 is observed to have moved to the point where the scribe line B is aligned with the side of the sun blanket 3; 9. By changing the mass of the counterweight component or altering the position of the sample 4 and the interface inserted into the sun blanket 3, and repeating steps 1 to 8 above, the friction coefficients of the sun blanket 3 at different interfaces under different pressure conditions can be obtained.

[0056] In one specific embodiment of this disclosure, such as Figure 6 As shown, Figure 6 This paper presents the measurement results of the friction coefficient at different interfaces of a solar blanket 3 under different pressure conditions. The solar blanket 3 used in the experiment is a scaled-down model of the real solar blanket 3. The experimental loading pressure is the weight of the counterweight assembly. Two measuring components 6 are used in the experiment, with a spacing of 129 mm between the traction ropes. The resultant force is the sum of the maximum tensions collected by the two tension sensors, the force difference is the absolute value of the difference between the maximum tensions collected by the two tension sensors, the additional torque is the product of the spacing between the traction ropes and the force difference, and the equivalent static friction coefficient is the ratio of the resultant force to the experimental loading pressure.

[0057] In the actual measurement process, the tension provided by measuring component 6 is prone to deflection. Two tension sensors are set up to measure the two tension values. An adjustment device is used to make the two tensions as equal as possible, thereby reducing the impact of tension deflection on the friction test. The force difference, the ratio of the force difference to the resultant force, and the additional torque are used to measure the degree of tension deflection.

[0058] The various embodiments of this disclosure have been described above. These descriptions are exemplary and not exhaustive, and are not limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or technical improvements to the embodiments in the market, or to enable others skilled in the art to understand the embodiments disclosed herein. The scope of this disclosure is defined by the appended claims.

Claims

1. A device for measuring the coefficient of friction between layers of a solar blanket on a spacecraft, characterized in that, include: Base (1); A clamping assembly (2) is disposed on the base (1). The clamping assembly (2) includes a first pressure plate (21) and a second pressure plate (22) for clamping the sun blanket (3). The first pressure plate (21) is fixed on the base (1), and the second pressure plate (22) is configured to be movably connected to the first pressure plate (21). A counterweight assembly, which is placed above the second pressure plate (22) and configured to provide a clamping force to the sun blanket (3) through the second pressure plate (22); Sample (4), which is configured to be inserted into the interlayer of the sun blanket (3); A traction assembly (5) is disposed on the base (1); A measuring component (6) is connected at one end to the specimen (4) and at the other end to the traction component (5); the traction component (5) is configured to provide tension to the specimen (4) through the measuring component (6); the measuring component (6) is configured to measure the tension.

2. The measuring device according to claim 1, characterized in that, The solar blanket (3) includes a flexible substrate (31) folded into at least four layers, with at least two adjacent flexible substrates (31) having simulated battery cells or glass covers on their opposing surfaces; the opposing surfaces of at least two adjacent flexible substrates (31) are configured to maintain the original surface of the flexible substrate (31); the sample (4) is configured to be consistent with the interlayer material to be tested.

3. The measuring device according to claim 1, characterized in that, The second pressure plate (22) is configured to be locked in the position after being pressed by the counterweight assembly by the locking device (23).

4. The measuring device according to claim 3, characterized in that, The locking device (23) is a screw, which is configured to pass through the second pressure plate (22) and lock together with the first pressure plate (21).

5. The measuring device according to claim 1, characterized in that, An elastic device (7) is provided between the measuring component (6) and the traction component (5), and the traction force provided by the traction component (5) is configured to be transmitted backward through the elastic device (7).

6. The measuring device according to claim 1, characterized in that, Two measuring components (6) are provided. The two measuring components (6) are configured to be connected to the sample (4) respectively via a first traction rope (61). The two sides of the traction component (5) are configured to be connected to the two measuring components (6) respectively via a second traction rope (62).

7. The measuring device according to claim 6, characterized in that, A pad (63) is provided at the bottom of the measuring component (6), and the measuring component (6) is configured to set its height by means of the pad (63) such that the first traction rope (61) and the sample (4) are at the same level.

8. The measuring device according to claim 7, characterized in that, The traction assembly (5) includes: A loading support (51) is configured to be mounted on the base (1); a nut is provided on the loading support (51); A loading beam (52) is configured to be located on the loading support (51) and is configured to be connected to the measuring component (6) via the second traction rope (62); A loading screw (53) is configured to engage with the nut, and one end of the loading screw (53) is configured to connect to the loading beam (52), and the other end is configured to have a keyway.

9. The measuring device according to claim 8, characterized in that, The loading support (51) is configured to be mounted on the base (1) by means of an adjusting screw (54); and the loading support (51) is configured to keep the second traction rope (62) at the same height as the sample (4) by means of the adjusting screw (54).

10. The measuring device according to claim 8, characterized in that, An adjusting shim (55) is provided between the base (1) and the loading support (51).

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