Radiation protection layer forming method and device

Abstract

The application provides a kind of radiation protection layer forming method and device.The method first carries out model analysis, disassembly and layering processing to target space curved surface, and according to the judgment of surface developability, respectively adopts the strategy of direct development or development after curvature calculation and correction, obtains the optimized development figure and carries out splicing and layering numbering.Subsequently, aramid fabric is precisely cut, punched, deburred and stacked in unit, and unit preforming and quilting are carried out with the help of frame.Then, each unit is sequentially preassembled and integrally formed and quilted, and then it is coated with multiple layers and assembled and fastened with a metal frame.Finally, the finished product is strictly tested for mechanics and thermal vacuum, and after passing the test, it is sterilized and sent to the astronauts for on-orbit assembly and installation.The application realizes the whole process closed loop from complex curved surface design, unit manufacturing to on-orbit assembly, and ensures the reliability and assembly feasibility of the structure in space environment.

Description

Technical Field

[0001] This application relates to the field of processing technology for spatial curved surface protective layers, and more specifically, to a method and apparatus for forming a radiation protection protective layer. Background Technology

[0002] In the manufacturing of high-performance protective equipment, high-performance fiber cloths such as aramid fibers (e.g., Kevlar) are often used to make protective layers. For complex spatial curved surface models, thicker layers are typically designed to ensure protective performance, and splicing is not permitted. Specifically, to address the protection requirements of micrometeoroids and space debris on the surface cables of space stations, a high-curvature protective component was designed to reduce damage to the cables from debris impacts. Through analysis of the design model, the spatial curved surface model of the protective device was determined. Because the unfolded surface resulted in significant graphic distortion, proportional fabrication was impossible. The protective device used multiple layers of aramid cloth, but these layers were difficult to stack to form a spatial curved surface, and the transitions between layers were also challenging.

[0003] However, aramid fabric is an anisotropic material with significant differences in stiffness between the warp and weft directions. Traditional surface flattening methods typically rely solely on pure geometry for calculations, neglecting the material's physical properties (such as elastic modulus). This leads to "arching" or "inability to fit" phenomena caused by material stiffness during actual layup, resulting in deviations between the theoretically flattened shape and the actual required shape. This not only wastes material but may also cause wrinkles or stress concentrations in the product, affecting its protective effect. Furthermore, there is still considerable room for improvement in the fabrication and processing of the protective layer, as well as in enhancing the environment inside the space station and the ease of operation for astronauts in orbit.

[0004] Therefore, it is necessary to provide a method and apparatus for forming a radiation protection layer to solve one of the above-mentioned technical problems. Summary of the Invention

[0005] The purpose of this application is to provide a method and apparatus for forming a radiation-shielding protective layer, which can solve at least one of the technical problems mentioned above. The specific solution is as follows:

[0006] According to a specific embodiment of this application, this application provides a method for forming a radiation protection layer, including: performing spatial surface model analysis, disassembly, and layering processing on the radiation protection layer outside the flexible spatial structure; unfolding the spatial surface model to be processed of the generated radiation protection layer; if it is determined to be a developable surface, the spatial surface model to be processed is directly flattened; if it is determined to be a non-developable surface, a surface transformation is performed before unfolding, wherein the method includes: determining the key points of the non-developable surface; extracting the radius of curvature of the key points, and performing curvature correction based on material properties to obtain a weighted effective curvature to further obtain an optimized equivalent radius of curvature; splicing, layering, numbering, and cutting the unfolded graphic to stack multiple aramid protective fabric units together to form a flexible protective unit; stitching the flexible protective unit to form a protective unit; and pre-forming the protective unit to obtain the final radiation protection layer.

[0007] According to a specific embodiment of this application, this application also provides a radiation protection layer forming device, which executes the radiation protection layer forming method described in this application, including: an analysis and processing module, used to perform spatial surface model analysis, disassembly, and layering processing on the radiation protection layer outside the flexible spatial structure; an unfolding and correction module, used to unfold the spatial surface model to be processed of the radiation protection layer to be generated, and when it is determined to be a developable surface, the spatial surface model to be processed is directly flattened; and when it is determined to be a non-developable surface, it is unfolded after surface transformation, wherein the process includes: determining the key points of the non-developable surface; extracting the curvature radius of the key points, and performing curvature correction based on material properties to obtain a weighted effective curvature to further obtain an optimized equivalent curvature radius; a splicing processing module, used to splice, layer number, and cut the unfolded graphic, stacking multiple aramid protective fabric units together to form a flexible protective unit; a forming module, used to perform unit seam stitching on the flexible protective unit to form a protective unit; and a molding module, used to pre-form the protective unit to obtain the final radiation protection layer.

[0008] According to specific embodiments of this application, this application also provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the method described in any of the preceding claims.

[0009] According to specific embodiments of this application, this application also provides an electronic device, including: one or more processors; and a storage device for storing one or more programs, which, when executed by the one or more processors, cause the one or more processors to perform the method described in any of the preceding claims.

[0010] Compared with the prior art, the above-described solutions of this application have at least the following beneficial effects:

[0011] This application utilizes a layered and partitioned strategy to decompose the spatial curved surface model for generating the radiation protection layer into multiple independent units, breaking it down into smaller parts to improve fabrication operability. Based on material properties, curvature correction is performed to obtain a weighted effective curvature to further obtain an optimized equivalent curvature radius. This can accurately correct the geometric principal curvature of the spatial curved surface, accurately identify curvature abrupt change boundaries, and accurately distinguish between the main principal curvature regions and regions with large curvature changes. This application effectively realizes the process of forming spatial curved surface laminated materials with smooth curvature transition and no structural wrinkles after multi-layer (e.g., 30-60 layers) aramid fabric lamination, and can effectively meet the requirements of the space station cabin environment and the operational convenience of astronauts in orbit. Attached Figure Description

[0012] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application. It is obvious that the drawings described below are merely some embodiments of this application, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort. In the drawings:

[0013] Figure 1 This is a schematic flowchart of a method for forming a radiation protection layer according to an embodiment of this application;

[0014] Figure 2 This is a schematic diagram illustrating an example of dividing a spatial curvature model to be processed into multiple regions in the radiation protection layer forming method of this application embodiment;

[0015] Figure 3 This is a schematic diagram of another angle of the spatial curvature model to be processed in the radiation protection layer forming method of this application embodiment;

[0016] Figure 4 This is a schematic flowchart of a radiation protection layer forming apparatus according to an embodiment of this application;

[0017] Figure 5 This is a schematic diagram of the electronic device structure shown in an embodiment of this application. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of this application clearer, the application will be further described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0019] The terminology used in the embodiments of this application is for the purpose of describing particular embodiments only and is not intended to limit the application. The singular forms “a,” “said,” and “the” used in the embodiments of this application and the appended claims are also intended to include the plural forms, and “multiple” generally includes at least two unless the context clearly indicates otherwise.

[0020] It should be understood that the term "and / or" used in this article is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, and B existing alone. Additionally, the character " / " in this article generally indicates that the preceding and following related objects have an "or" relationship.

[0021] It should be understood that although the terms first, second, third, etc., may be used in the embodiments of this application, these descriptions should not be limited to these terms. These terms are only used to distinguish the descriptions. For example, first may also be referred to as second without departing from the scope of the embodiments of this application, and similarly, second may also be referred to as first.

[0022] It should also be noted that the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that an article or device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such an article or device. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the article or device that includes said element.

[0023] In view of the above problems, this application provides a method for forming a radiation-shielding protective layer. This method utilizes a layered and partitioned strategy to decompose the spatial curved surface model for generating the radiation-shielding protective layer into multiple independent units, breaking it down into smaller parts to improve the operability of the fabrication. Based on material properties, curvature correction is performed to obtain a weighted effective curvature to further obtain an optimized equivalent radius of curvature. This method can accurately correct the geometric principal curvature of the spatial curved surface, accurately identify curvature abrupt change boundaries, and accurately distinguish between the main principal curvature regions and regions with large curvature changes. This application effectively realizes the forming process of spatial curved surface laminated materials with smooth curvature transition and no structural wrinkles after multi-layer (e.g., 30-60 layers) aramid fabric lamination, and can effectively meet the requirements of the space station cabin environment and the operational convenience of astronauts in orbit. Compared with ordinary bulletproof vests, this application can combine 30-60 layers of aramid fabric into curved surface protective components, which can adapt to more complex, harsher, and extreme application environments, and effectively improve the structural integrity, curved surface fitting accuracy, and environmental tolerance after dozens of layers are stacked.

[0024] It should be noted that this application is particularly applicable to space station personnel making or preparing protective layers or devices, and can effectively test the protective effect consistent with that on the ground.

[0025] The following is in conjunction with the appendix Figures 1 to 3 Detailed description of optional embodiments of the method of this application.

[0026] like Figure 1 As shown, in step S101, the radiation protection layer outside the flexible space structure is subjected to spatial surface model analysis, disassembly, and layering.

[0027] Specifically, the curvature magnitude change boundary of the spatial curvature model to be processed is decomposed, and the maximum curvature region, geometric abrupt change region, and boundary constraint point on the surface of the spatial curvature model to be processed are identified using curvature analysis tools, including the first type of region and the second type of region.

[0028] First, partition the space, for example, by splitting the spatial curvature model to be processed into... Figure 2 The multiple regions shown include the first type of region (e.g., regions represented by labels 1 and 2) and the second type of region (region represented by label 3).

[0029] Specifically, regions with gentle curvature changes are defined as the first type of region, and regions with large curvature changes are defined as the second type of region. For example, regions with curvature less than a first specified value of 0.001 mm are considered the second type of region. -1 Regions with a curvature greater than or equal to the second specified value of 0.003 mm are defined as the first type of region. -1 Regions with a value of 0.01 (for example) are defined as the second type of region.

[0030] Next, the partitioned spatial curvature model is analyzed, decomposed, and layered. For example, the outer surface of the spatial curvature model is considered as a single layer, with a thickness of 20 mm. See details... Figure 3 .

[0031] Optionally, the number of layers of the spatial curvature model to be processed is 30 to 60, that is, the number of layers k of the protective cloth is 30 to 60.

[0032] The disassembly involves dividing the spatial curvature model to be processed into multiple independent units. Each independent unit is divided into multiple sub-parts from the inside out and includes multiple layers of protective fabric, including aramid protective fabric.

[0033] Optionally, 6 to 15 layers of protective fabric can be used as an independent unit to independently form a curved surface of the radiation protection layer.

[0034] In this example, the protective fabric is an aramid protective fabric, for example, an aramid protective fabric with 30 layers.

[0035] Specifically, m represents the number of sub-parts, and the number of independent units is the product of m and k, i.e., m*k.

[0036] By employing parametric design, the same model is first analyzed and then decomposed according to its curvature, which can accurately quantify the spatial curvature model to be processed, and thus more accurately quantify the radiation protection layer on the outside of the flexible spatial structure to be generated.

[0037] It should be noted that the above is only an optional example and should not be construed as a limitation of the present invention.

[0038] Next, in step S102, the spatial surface model to be processed for the generated radiation protection layer is unfolded. If it is determined to be a developable surface, the spatial surface model to be processed is directly flattened; if it is determined to be a non-developable surface, a surface transformation is performed before unfolding. This includes: determining the key points of the non-developable surface; extracting the curvature radius of the key points; and performing curvature correction based on material properties to obtain a weighted effective curvature to further obtain the optimized equivalent curvature radius.

[0039] Specifically, the spatial surface model of the radiation protection layer to be generated is unfolded.

[0040] When the surface is determined to be developable, the spatial surface model to be processed is directly flattened.

[0041] For example, you can use the software's "curvature analysis" or "zebra stripe analysis" tools to visualize curvature changes and find key points. At the key point location, you can directly query and display the principal curvature value or principal curvature radius of that key point.

[0042] Optionally, a mathematical model is used for expansion, specifically converting each spatial surface of the spatial surface model to be processed into a triangular mesh M = (V, E, F). The core of the expansion is to keep all side lengths unchanged.

[0043] Specifically, inputting the transformed triangular mesh into, for example, a data model will output a two-dimensional unfolded graph (where all edges remain unchanged).

[0044] When the surface is determined to be non-developable, it is unfolded after surface transformation, which includes: determining the key points of the non-developable surface; extracting the curvature radius of the key points, and performing curvature correction based on material properties to obtain a weighted effective curvature in order to further obtain an optimized equivalent curvature radius.

[0045] The flattening process specifically includes the following steps.

[0046] Step S201: Determine the key points of the spatial surface model to be processed.

[0047] Specifically, the regions with the greatest curvature and the regions with the least curvature are identified, i.e., the regions with the greatest curvature R1 or the regions with the least curvature R2. Furthermore, the intersection point where the regions with the greatest curvature K1 and the least curvature K2 are perpendicular to each other is obtained, and this intersection point is used as the key point.

[0048] Furthermore, at any point on the surface of the spatial surface model to be processed, there exist countless curves, each with its own curvature and radius of curvature. Among them, there are two extreme values: the maximum curvature K1 and the minimum curvature K2. These two directions are usually perpendicular to each other, and the corresponding radii of curvature are R1 = 1 / K1 and R2 = 1 / K2, respectively. These two radii of curvature R1 and R2 are the radii of the "osculating circle" and define the best approximation of the surface curvature at that point.

[0049] Furthermore, the locations where the geometry changes abruptly are taken as key points.

[0050] Specifically, regions with abrupt changes in geometry, such as the area where a sphere transitions to a cylinder and its corresponding location points.

[0051] Next, the boundary constraint points are used as key points, such as the locations where they are connected to or fixed to other components.

[0052] It should be noted that the above is only an optional example and should not be construed as a limitation of the present invention.

[0053] Step S202: Extract the principal curvature radius of the determined key points.

[0054] The principal curvature radii of the extracted key points are optimized and calculated.

[0055] Specifically, the weighted effective curvature is calculated using the following expression:

[0056] K weighted = a·K1+β·K2

[0057] Among them, K weighted K1 represents the weighted effective curvature of the spatial curvature model to be processed; K2 represents the maximum principal radius of curvature of the spatial curvature model to be processed; α represents the first weighting coefficient determined based on the elastic modulus of the material along the radial direction and the elastic modulus along the latitudinal direction perpendicular to the radial direction; β represents the second weighting coefficient determined based on the elastic modulus of the material along the radial direction and the elastic modulus along the latitudinal direction.

[0058] The radiation protection layer is generated using aramid protective fabric, wherein the radial direction of the aramid protective fabric in the fiber direction is aligned with the main direction of curvature, and a first weighting coefficient and a second weighting coefficient are calculated and determined based on the ratio between the elastic modulus of the aramid protective fabric in the radial direction and the elastic modulus in the weft direction perpendicular to the radial direction.

[0059] Assume that the radial direction (the stiffest direction) of the aramid protective fabric in the fiber direction is aligned with the principal direction of curvature. The elastic modulus E1 of the aramid protective fabric in the warp direction is 5 to 10 times that in the weft direction, specifically taking the following ratio E1:E2 = 8:1, and calculate the weighting coefficients. Based on the ratio of the elastic moduli of the aramid protective fabric, calculate the first weighting coefficient and the second weighting coefficient.

[0060]

[0061] Wherein, α represents a first weighting coefficient determined based on the elastic modulus of the material along the radial direction and the elastic modulus along the weft direction perpendicular to the radial direction, for example, 0.78; E1 represents the elastic modulus of the aramid protective fabric along the warp direction; E2 represents the elastic modulus of the aramid protective fabric along the weft direction (the direction perpendicular to the radial direction).

[0062]

[0063] Wherein, β represents a second weighting coefficient determined based on the elastic modulus of the material along the radial direction and the elastic modulus along the weft direction perpendicular to the radial direction, for example, 0.22; E1 represents the elastic modulus of the aramid protective fabric along the warp direction; E2 represents the elastic modulus of the aramid protective fabric along the weft direction (the direction perpendicular to the radial direction).

[0064] Optionally, the value of the first weighting coefficient is 0.6 to 0.8, preferably 0.87.

[0065] Optionally, the value of the second weighting coefficient is 0.2 to 0.4, preferably 0.13.

[0066] It should be noted that in this application, the material property parameter (warp and weft modulus ratio) is used as a correction parameter to optimize the principal curvature radius of the extracted key points. The greater the radial stiffness, the greater the contribution of its curvature change to the internal force of the material. Therefore, the determined weight parameter will be higher.

[0067] By introducing material property parameters (warp and weft modulus ratio) during the flattening process as correction parameters, the principal curvature radius of the extracted key points was optimized. Specifically, the geometric curvature was corrected using the aforementioned optimization formula. Due to the high warp stiffness of the aramid protective fabric, the actual bending is gentler than the geometric shape. By increasing the calculated curvature radius (e.g., correcting it from 220.4 mm to 241.5 mm), structural wrinkles were effectively eliminated, minimizing the flattening distortion of the curved surface.

[0068] Optionally, flattening calculations can be performed using numerical flattening techniques (such as the finite element method) based on the corrected weighted curvature. For example, the flattening results can be calculated using the area where the curvature of the bottom edge on the right side of the model changes gently as the calculation benchmark, generating a two-dimensional flattening diagram. This can effectively predict the stress distribution generated by the material during bending, avoiding internal stress concentration and wrinkles caused by pure geometric flattening, thereby improving flattening accuracy and processing adaptability.

[0069] To accurately determine the first and second weighting coefficients, quasi-static tensile tests were performed on specimens of aramid fiber composite materials (e.g., aramid protective fabric) under specified test conditions.

[0070] The evolution of anisotropic mechanical properties of aramid fiber composites over a wide temperature range, especially under extreme low-temperature conditions in space, was investigated. Typical temperature environments at 50°C intervals were simulated experimentally, with the specific experimental conditions as follows.

[0071] Four characteristic temperature points were set: +20℃ (room temperature), -30℃, -80℃, and -130℃, to cover the main stages from room temperature to near-space extreme environments. The characteristic temperature point of -130℃ was used to approximate and infer performance trends at 150℃.

[0072] For materials and specimens, unidirectional aramid fiber fabric was used as the standard specimen material. Tensile specimens were prepared according to ASTM D3039 standard, both along the fiber warp (0°) and perpendicular to the fiber weft (90°).

[0073] Regarding the equipment and methods, the above tests were conducted in an environmental chamber equipped with a high-precision temperature control system. For example, an electronic universal testing machine was used to perform quasi-static tensile tests on tensile specimens held to the target temperature, and strain values ​​were directly measured using an extensometer to obtain accurate stress-strain relationships. See Table 1 for details.

[0074] Table 1

[0075]

[0076] Table 1 is a table of examples of parameters obtained from the above experiments. In the table, the modulus ratio refers to the ratio of the radial elastic modulus to the latitudinal elastic modulus, and the weight ratio refers to the ratio of the first weight coefficient to the second weight coefficient.

[0077] As shown in Table 1, the first weighting coefficient α decreased from 0.900 to 0.796, while the second weighting coefficient β increased from 0.100 to 0.204. At -130℃, the second weighting coefficient β for latitudinal curvature is more than twice that at room temperature. These parameter changes mean that when analyzing curved structures at extreme low temperatures, if the weighting coefficients corresponding to room temperature are incorrectly applied, the mechanical contribution of curvature in the fiber direction will be severely overestimated, while the influence of curvature in the matrix direction will be significantly underestimated, leading to misjudgments of the actual stress state and potential failure modes of the structure.

[0078] Based on experimental results, wrinkles and excessive stretching during the lamination process of multilayer aramid protective fabrics both affect the protective effect. In extremely low temperatures of -150 degrees Celsius, the optimal lamination combination for 30-60 layers of aramid protective fabric is 6-15 layers, with each 6-15 layers forming a single unit to independently construct a curved surface. The higher the number of layers, the smaller the decrease in strength and stiffness. However, with increasing layer count, especially during the curved surface forming process of multilayer aramid protective fabrics, it becomes difficult to eliminate localized damage caused by wrinkles and stretching. The increased layer count also makes the curved surface forming and fixing process prone to loosening, failing to achieve the desired protective effect. In extreme environments, wrinkles and stretching exacerbate the brittle fracture tendency and interlayer failure risk of aramid protective fabrics, thus failing to meet design requirements.

[0079] Optionally, the optimal layering combination for 30 to 60 layers of aramid protective fabric is 6 to 15 layers, with 6 to 15 layers forming a unit to independently construct the curved surface.

[0080] For aramid protective fabrics with different numbers of layers, the values ​​of radial elastic modulus and weft elastic modulus can be adjusted according to the above parameter data. Furthermore, by adjusting the values ​​of the first weighting parameter and the second weighting parameter, the brittle fracture tendency and interlayer failure risk of the aramid protective fabric caused by wall wrinkles and stretching under extreme environments can be effectively controlled, thereby achieving the best protective effect.

[0081] Furthermore, the flattened graphics are precisely spliced ​​together. The following will explain the subsequent process in detail with reference to steps S103 to S106.

[0082] It should be noted that the above is only an optional example and should not be construed as a limitation of the present invention.

[0083] Next, in step S103, the unfolded graphic is spliced, layered, numbered, and cut to stack the multi-layer aramid protective fabric units together to form a flexible protective unit.

[0084] Specifically, all unfolded graphics are processed in layers, first by splicing them together. Each spliced ​​two-dimensional graphic unit (corresponding to the aramid protective fabric unit layer) is uniquely and systematically numbered according to its spatial position and layer sequence within the radiation protection layer. This layered numbering uses identifiers that include layer number information, unit location information (e.g., row, column), and material batch information. A complete digital management archive is established based on these identifiers to ensure traceability of the processing and quality control process for each unit.

[0085] Next, cutting is performed. The assembled two-dimensional graphic units are precisely projected onto the aramid protective fabric to be used using a projection method. The aramid protective fabric is then cut, with corresponding tools used for different lines. These tools include pneumatic knives, vibrating knives, roller cutters, and electric scissors.

[0086] When cutting, the aramid protective fabric is prone to loose edges after cutting, resulting in excess material that can damage the environment inside the space station. Each layer of aramid fabric is individually edged with 25mm wide polyester pressure-sensitive tape to completely cover the cut edges of the aramid protective fabric.

[0087] For example, using a projection device (such as a laser projector), the stitched two-dimensional graphic units are precisely projected onto the aramid protective fabric to be used at a 1:1 scale, ensuring that the cutting path perfectly matches the design drawings. Based on the geometric characteristics of the cutting lines, the appropriate cutting tools are automatically selected. For straight sections, pneumatic or electric roller cutters can be used to improve efficiency. For complex curves and internal angles, high-precision vibrating cutters or laser cutting are used to ensure smooth, burr-free edges. During the cutting process, the cutting speed and pressure should be strictly controlled to avoid thermal damage to the material or edge delamination.

[0088] After each batch of cutting is completed, each cut piece (i.e., the component part of the aramid protective fabric unit layer) is sampled or fully inspected. The inspection includes: dimensional accuracy (using calipers, vernier calipers, or video measuring instruments), edge flatness, presence of burrs, delamination, or heat damage. If it is found that there are any non-compliance with design requirements or defects (such as dimensional deviations, uneven edges, severe burrs, etc.), the batch or piece of aramid protective fabric is judged as unqualified and recut, which can effectively prevent unqualified products from flowing into subsequent processes.

[0089] Next, the multi-layer aramid protective fabric units are stacked together to form a flexible protective unit.

[0090] It should be noted that the above is only an optional example and should not be construed as a limitation of the present invention.

[0091] Next, in step S104, the flexible protective unit is joined together to form a protective unit;

[0092] Specifically, the cut pieces of the same unit (i.e., the component parts of the aramid protective fabric unit layer) are stacked together, pre-formed using a frame, and each unit is quilted with a quilting spacing of, for example, 100mm to 150mm, along the edge of the aramid protective fabric, with the seam thread kept loose.

[0093] For the quilting of each unit, check whether all quilting is appropriate. If it is not up to standard, remove the quilting stitches and re-quilt.

[0094] In one specific embodiment, considering the issue of reserved hole positions during the fabrication of the aramid protective fabric, a projection method is used in conjunction with a pneumatic punching gun to ensure precise punching. The cut aramid protective fabric units are fixed on a dedicated tooling table. The hole positions from the design drawings are then precisely projected onto the surface of the aramid protective fabric using a projection device. Next, a high-precision pneumatic punching gun or CNC drilling equipment is used for punching. The selection and parameters of the punching tools (such as drill diameter, rotation speed, and feed rate) should be optimized according to the characteristics of the aramid protective fabric to ensure smooth hole walls, free of burrs, tears, and delamination.

[0095] After punching, each hole undergoes a meticulous inspection. The inspection includes: hole diameter, hole position accuracy (relative position to the reference point), and hole wall quality (presence of burrs, delamination, and tearing). A hole gauge and optical magnifying glass are used for inspection. Any non-conformities, such as out-of-tolerance hole diameter, hole position deviation, rough hole wall, or delamination, are deemed unacceptable. This process effectively ensures that the quality of all connecting holes meets high-precision assembly requirements, completely eliminates fiber debris, ensures a clean working environment, and improves the durability of the protective layer.

[0096] Optionally, after deburring, use a 25mm wide single-sided polyimide tape to fully wrap all cut and punched edges of the aramid protective fabric. The tape should be applied evenly and without bubbles to form a completely sealed surface, ensuring that all aramid fibers are completely wrapped and preventing them from falling off during use or vibration.

[0097] It should be noted that the above is only an optional example and should not be construed as a limitation of the present invention.

[0098] Next, in step S105, the protective unit is pre-formed to obtain the final radiation protection layer.

[0099] Specifically, M5 screws are used to assemble the aramid protective fabric units in sequence (to obtain the protective units) and then insert them into a metal frame for overall molding. After molding, the entire frame is quilted to obtain the assembled radiation protection layer, i.e., the final radiation protection layer.

[0100] By assembling the protective layer with the metal frame, specifically by aligning the metal frame with the protective layer, multiple people can simultaneously install and tighten the screws, reducing the impact of the installation process on the curvature changes of the protective layer.

[0101] It should be noted that, in order to reduce the weight of the space station's uplink products, the metal frame is extremely small. The design of the protective components, such as the aramid fabric soft body, and the metal frame, should minimize the number of fixing points while ensuring reliable connection. The screw spacing should be between 100-180mm.

[0102] By using M5 screws and matching pins for installation, the curved surface configuration of the soft protective layer of the protective unit remains unchanged after fixing, and has no impact on the frame structure.

[0103] Next, install the fasteners and measure the force to 2.5 Nm. Then, seal them with a special anti-loosening adhesive. When sealing, apply the adhesive to only 1 / 4 of the nut's end face to facilitate on-orbit maintenance by astronauts. Check the force measurement and sealing status. If they do not meet the requirements, reinstall, measure the force, and reseal.

[0104] Optionally, a multi-layered protective device or equipment can be fabricated, using a 5-unit multi-layered outer covering of white atomic oxygen flame-retardant fabric, and secured with Velcro fasteners to facilitate on-orbit assembly and disassembly by astronauts.

[0105] The entire protective device is wrapped in multiple layers, and the common interfaces are protected to avoid affecting on-orbit installation.

[0106] Optionally, mechanical and thermal tests are conducted on the manufactured protective device to determine whether the test results meet the design requirements. If problems are found, the causes are analyzed; if the test problems are found, the mechanical test is repeated; if other problems are found, the device is remanufactured or reassembled. For thermal testing, the results are used to determine whether the test results meet the design requirements. If problems are found, the causes are analyzed; if the test problems are found, the mechanical test is repeated; if other problems are found, the device is remanufactured or reassembled.

[0107] The protective devices were disinfected and packaged, and the placement order and location were recorded to facilitate on-orbit assembly by astronauts.

[0108] Quality inspection checkpoints are set up after each critical manufacturing and assembly step, including cutting accuracy, punching quality, edge binding integrity, seam strength, and forming accuracy. Any non-conforming product will immediately trigger a closed-loop feedback mechanism (specifically including "material or assembly problem location - testing - root cause analysis - remanufacturing / assembly"), ensuring that only products that meet the highest standards can proceed to the next process stage.

[0109] It should be noted that the above is only an optional example and should not be construed as a limitation of the present invention.

[0110] Compared with existing technologies, this application utilizes a layered and partitioned strategy to decompose the spatial surface model for generating the radiation protection layer into multiple independent units, breaking it down into smaller parts to improve fabrication operability. Based on material properties, curvature correction is performed to obtain a weighted effective curvature to further obtain an optimized equivalent curvature radius. This can accurately correct the geometric principal curvature of the spatial surface, accurately identify curvature abrupt change boundaries, and accurately distinguish between the main principal curvature regions and regions with large curvature changes. This application effectively realizes the process of forming spatial surface laminated materials with smooth curvature transition and no structural wrinkles after multi-layer (e.g., 30-60 layers) aramid fabric lamination, and can effectively meet the requirements of the space station cabin environment and the operational convenience of astronauts in orbit.

[0111] In addition, to meet the special requirements of the space station environment, the edges of each layer and each unit are wrapped with anti-chip material. This ensures that no fibers are exposed and completely eliminates the generation of excess material.

[0112] Furthermore, the protective layer or protective device manufactured or prepared using the molding method of this application can adapt to launch segment vibration and on-orbit thermal deformation, and effectively reduces the weight of the protective layer or protective device frame.

[0113] The following is in conjunction with the appendix Figure 4 Detailed description of optional embodiments of the device in this application.

[0114] like Figure 4 As shown, this application provides a radiation shielding layer forming apparatus 500, which performs the radiation shielding layer forming method described in this application. The radiation shielding layer forming apparatus 500 includes an analysis and processing module 510, an unfolding and correction module 520, a splicing processing module 530, a forming module 540, and a forming module 550.

[0115] Specifically, the analysis and processing module 510 is used to perform spatial surface model analysis, disassembly, and layering processing on the radiation protection layer outside the flexible spatial structure. The unfolding and correction module 520 is used to unfold the spatial surface model of the radiation protection layer to be generated. When it is determined to be a developable surface, the spatial surface model to be processed is directly flattened; when it is determined to be a non-developable surface, it is unfolded after surface transformation, including: determining the key points of the non-developable surface; extracting the radius of curvature of the key points, and performing curvature correction based on material properties to obtain a weighted effective curvature to further obtain an optimized equivalent radius of curvature. The splicing processing module 530 is used to splice, layer, number, and cut the unfolded graphic, stacking multiple layers of aramid protective fabric units together to form a flexible protective unit. The forming module 540 is used to stitch the flexible protective units together to form a protective unit. The molding module 550 is used to pre-form the protective unit to obtain the final radiation protection layer.

[0116] According to an optional implementation, the curvature magnitude change boundary of the spatial curvature model to be processed is decomposed, and the maximum curvature region, geometric abrupt change region, and boundary constraint point on the surface of the spatial curvature model to be processed are identified using curvature analysis tools, including a first type of region and a second type of region.

[0117] The disassembly involves dividing the spatial curvature model to be processed into multiple independent units. Each independent unit is divided into multiple sub-parts from the inside out and includes multiple layers of protective fabric, including aramid protective fabric.

[0118] According to an optional implementation, the weighted effective curvature is calculated using the following expression:

[0119] K weighted = a·K1+β·K2

[0120] Among them, K weighted K1 represents the weighted effective curvature of the spatial curvature model to be processed; K2 represents the maximum principal radius of curvature of the spatial curvature model to be processed; α represents the first weighting coefficient determined based on the elastic modulus of the material along the radial direction and the elastic modulus along the latitudinal direction perpendicular to the radial direction; β represents the second weighting coefficient determined based on the elastic modulus of the material along the radial direction and the elastic modulus along the latitudinal direction.

[0121] According to an optional embodiment, the radiation protection layer is formed using aramid protective fabric, wherein the radial direction of the aramid protective fabric in the fiber direction is aligned with the main direction of curvature, and a first weighting coefficient and a second weighting coefficient are calculated and determined based on the ratio between the elastic modulus of the aramid protective fabric in the radial direction and the elastic modulus in the weft direction perpendicular to the radial direction.

[0122] According to an optional implementation, the number of layers k of the protective fabric is 30 to 60 layers, m represents the number of sub-parts, and the number of independent units is the product of m and k; a surface of 6 to 15 layers of protective fabric is independently constructed to form a radiation protection layer.

[0123] According to an optional implementation method, the aramid protective fabric is precisely projected to a proportional scale using an equipment projection method, and then cut. The corresponding cutting tools are used according to the different lines being cut, including pneumatic knives, vibrating knives, roller cutters, and electric scissors.

[0124] According to an optional implementation, the development parameters of the non-developable surface are calculated using a triangular mesh method that keeps all side lengths unchanged for the processing space surface model, and then converted into a three-dimensional developable surface triangular mesh. This mesh is then input into the relevant data model to obtain a two-dimensional open graph.

[0125] It should be noted that, in this embodiment, the content of the radiation protection layer forming method performed by the radiation protection layer forming device of this application is substantially the same as the content of the radiation protection layer forming method described in the above embodiments of this application, therefore the description of the same content is omitted.

[0126] Compared with existing technologies, this application utilizes a layered and partitioned strategy to decompose the spatial surface model for generating the radiation protection layer into multiple independent units, breaking it down into smaller parts to improve fabrication operability. Based on material properties, curvature correction is performed to obtain a weighted effective curvature to further obtain an optimized equivalent curvature radius. This can accurately correct the geometric principal curvature of the spatial surface, accurately identify curvature abrupt change boundaries, and accurately distinguish between the main principal curvature regions and regions with large curvature changes. This application effectively realizes the process of forming spatial surface laminated materials with smooth curvature transition and no structural wrinkles after multi-layer (e.g., 30-60 layers) aramid fabric lamination, and can effectively meet the requirements of the space station cabin environment and the operational convenience of astronauts in orbit.

[0127] In addition, to meet the special requirements of the space station environment, the edges of each layer and each unit are wrapped with anti-chip material. This ensures that no fibers are exposed and completely eliminates the generation of excess material.

[0128] Furthermore, the protective layer or protective device manufactured or prepared using the molding method of this application can adapt to launch segment vibration and on-orbit thermal deformation, and effectively reduces the weight of the protective layer or protective device frame.

[0129] like Figure 5As shown, this embodiment provides an electronic device, which includes: at least one processor; and a memory communicatively connected to the at least one processor; wherein the memory stores instructions executable by the at least one processor, which are executed by the at least one processor to enable the at least one processor to perform the method steps described in the above embodiment.

[0130] This application provides a non-volatile computer storage medium storing computer-executable instructions that can perform the steps described in the above embodiments.

[0131] The following is for reference. Figure 5 The diagram illustrates a structural schematic of an electronic device suitable for implementing the embodiments of this application. The terminal devices in the embodiments of this application may include, but are not limited to, mobile terminals such as mobile phones, laptops, digital broadcast receivers, PDAs (personal digital assistants), PADs (tablet computers), PMPs (portable multimedia players), in-vehicle terminals (e.g., in-vehicle navigation terminals), and fixed terminals such as digital TVs and desktop computers. Figure 5 The electronic device shown is merely an example and should not impose any limitation on the functionality and scope of use of the embodiments of this application.

[0132] like Figure 5 As shown, the electronic device may include a processing unit (e.g., a central processing unit, a graphics processing unit, etc.) 401, which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 402 or a program loaded from a storage device 408 into a random access memory (RAM) 403. The RAM 403 also stores various programs and data required for the operation of the electronic device. The processing unit 401, ROM 402, and RAM 403 are interconnected via a bus 404. An input / output (I / O) interface 405 is also connected to the bus 404.

[0133] Typically, the following devices can be connected to I / O interface 405: input devices 406 including, for example, touchscreens, touchpads, keyboards, mice, cameras, microphones, accelerometers, gyroscopes, etc.; output devices 407 including, for example, liquid crystal displays (LCDs), speakers, vibrators, etc.; storage devices 408 including, for example, magnetic tapes, hard disks, etc.; and communication devices 409. Communication device 409 allows electronic devices to communicate wirelessly or wiredly with other devices to exchange data. Although Figure 5 Electronic devices with various devices are shown, but it should be understood that it is not required to implement or have all of the devices shown. More or fewer devices may be implemented or have alternatively.

[0134] Specifically, according to embodiments of this application, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, embodiments of this application include a computer program product comprising a computer program carried on a computer-readable medium, the computer program containing program code for performing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via a communication device 409, or installed from a storage device 408, or installed from a ROM 402. When the computer program is executed by the processing device 401, it performs the functions defined in the methods of the embodiments of this application.

[0135] It should be noted that the computer-readable medium described above in this application can be a computer-readable signal medium, a computer-readable storage medium, or any combination thereof. A computer-readable storage medium can be, for example,—but not limited to—an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of a computer-readable storage medium may include, but are not limited to: an electrical connection having one or more wires, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage device, magnetic storage device, or any suitable combination thereof. In this application, a computer-readable storage medium can be any tangible medium containing or storing a program that can be used by or in conjunction with an instruction execution system, apparatus, or device. In this application, a computer-readable signal medium can include a data signal propagated in baseband or as part of a carrier wave, carrying computer-readable program code. Such propagated data signals can take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium can be any computer-readable medium other than a computer-readable storage medium, which can send, propagate, or transmit a program for use by or in connection with an instruction execution system, apparatus, or device. The program code contained on the computer-readable medium can be transmitted using any suitable medium, including but not limited to: wires, optical fibers, RF (radio frequency), etc., or any suitable combination thereof.

[0136] The aforementioned computer-readable medium may be included in the aforementioned electronic device; or it may exist independently and not assembled into the electronic device.

[0137] Computer program code for performing the operations of this application can be written in one or more programming languages ​​or a combination thereof, including object-oriented programming languages ​​such as Java, Smalltalk, and C++, and conventional procedural programming languages ​​such as the "C" language or similar programming languages. The program code can be executed entirely on the user's computer, partially on the user's computer, as a standalone software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving remote computers, the remote computer can be connected to the user's computer via any type of network—including a local area network (LAN) or a wide area network (WAN)—or can be connected to an external computer (e.g., via the Internet using an Internet service provider).

[0138] The flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of systems, methods, and computer program products according to various embodiments of this application. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing a specified logical function. It should also be noted that in some alternative implementations, the functions indicated in the blocks may occur in a different order than those indicated in the drawings. For example, two consecutively indicated blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in the block diagrams and / or flowcharts, and combinations of blocks in the block diagrams and / or flowcharts, can be implemented using a dedicated hardware-based system that performs the specified function or operation, or using a combination of dedicated hardware and computer instructions.

[0139] The units described in the embodiments of this application can be implemented in software or hardware. The names of the units are not, in some cases, limiting the scope of the unit itself.

Claims

1. A method for forming a radiation-shielding protective layer, characterized in that, include: The radiation protection layer on the outside of the flexible space structure is analyzed, disassembled, and layered using a spatial curved surface model. The spatial surface model to be processed for the generated radiation protection layer is unfolded. If it is determined to be a developable surface, the spatial surface model is directly flattened. If it is determined to be a non-developable surface, a surface transformation is performed before unfolding. The key points of the non-developable surface are determined. The curvature radius of the key points is extracted, and curvature correction is performed based on material properties to obtain a weighted effective curvature to further obtain the optimized equivalent curvature radius. The unfolded graphic is spliced, layered, numbered, and cut to stack multiple aramid protective fabric units together to form a flexible protective unit. The flexible protective unit is joined together to form a protective unit; The protective unit is pre-formed to obtain the final radiation protection layer.

2. The method for forming a radiation-shielding protective layer according to claim 1, characterized in that, The analysis, disassembly, and layering of the external radiation protection layer of the flexible spatial structure using a spatial surface model includes: The curvature magnitude change boundary of the spatial curvature model to be processed is decomposed, and the maximum curvature region, geometric abrupt change region, and boundary constraint point on the surface of the spatial curvature model to be processed are identified using curvature analysis tools, including the first type of region and the second type of region. The disassembly involves dividing the spatial curvature model to be processed into multiple independent units. Each independent unit is divided into multiple sub-parts from the inside out and includes multiple layers of protective fabric, including aramid protective fabric.

3. The method for forming a radiation-shielding protective layer according to claim 1, characterized in that, The process of extracting the radius of curvature of the key points and correcting the curvature based on material properties to obtain a weighted effective curvature to further obtain the optimized equivalent radius of curvature includes: The weighted effective curvature is calculated using the following expression: K weighted =α·K1+β·K2 Among them, K weighted K1 represents the weighted effective curvature of the spatial curvature model to be processed; K2 represents the maximum principal radius of curvature of the spatial curvature model to be processed; α represents the first weighting coefficient determined based on the elastic modulus of the material along the radial direction and the elastic modulus along the latitudinal direction perpendicular to the radial direction; β represents the second weighting coefficient determined based on the elastic modulus of the material along the radial direction and the elastic modulus along the latitudinal direction.

4. The method for forming a radiation-shielding protective layer according to claim 1 or 3, characterized in that, Further includes: The radiation protection layer is formed using aramid protective fabric, wherein the radial direction of the aramid protective fabric in the fiber direction is aligned with the main direction of curvature, and a first weighting coefficient and a second weighting coefficient are calculated and determined based on the ratio between the elastic modulus of the aramid protective fabric in the radial direction and the elastic modulus in the weft direction perpendicular to the radial direction.

5. The method for forming a radiation-shielding protective layer according to claim 2, characterized in that, Further includes: The number of layers k of the protective fabric is between 30 and 60 layers, m represents the number of sub-parts, and the number of independent units is the product of m and k. Each layer of protective fabric, ranging from 6 to 15 layers, forms an independent unit, creating a curved surface that independently constitutes the radiation protection layer.

6. The method for forming a radiation-shielding protective layer according to claim 1, characterized in that, The process of splicing, layering, numbering, and cutting the unfolded graphic to stack multiple layers of aramid protective fabric units together to form a flexible protective unit includes: The aramid protective fabric is precisely projected to a fixed scale using an equipment projection method, and then cut. Different cutting tools are used for different lines, including pneumatic knives, vibrating knives, roller cutters, and electric scissors.

7. The method for forming a radiation-shielding protective layer according to claim 1, characterized in that, For the processed spatial surface model, the development parameters of the non-developable surface are calculated using the triangular mesh method that keeps all side lengths unchanged, and then converted into a three-dimensional developable surface triangular mesh. This mesh is then input into the relevant data model to obtain a two-dimensional open graph.

8. A radiation protection layer forming device, characterized in that, The method for forming a radiation-shielding protective layer according to any one of claims 1 to 7 includes: The analysis and processing module is used to perform spatial surface model analysis, disassembly, and layering processing on the radiation protection layer outside the flexible space structure; The unfolding and correction module is used to unfold the spatial surface model of the radiation protection layer to be generated. When it is determined to be a developable surface, the spatial surface model is directly flattened; when it is determined to be a non-developable surface, a surface transformation is performed before unfolding. This includes: determining the key points of the non-developable surface; extracting the radius of curvature of the key points; and performing curvature correction based on material properties to obtain a weighted effective curvature to further obtain an optimized equivalent radius of curvature. The splicing module is used to splice, layer, number, and cut the unfolded graphic, stacking multiple aramid protective fabric units together to form a flexible protective unit. A forming module is used to stitch the flexible protective unit together to form the protective unit; A molding module is used to pre-form the protective unit to obtain the final radiation protection layer.

9. The radiation protection layer forming device according to claim 8, characterized in that, The curvature magnitude change boundary of the spatial curvature model to be processed is decomposed, and the maximum curvature region, geometric abrupt change region, and boundary constraint point on the surface of the spatial curvature model to be processed are identified using curvature analysis tools, including the first type of region and the second type of region. The disassembly involves dividing the spatial curvature model to be processed into multiple independent units. Each independent unit is divided into multiple sub-parts from the inside out and includes multiple layers of protective fabric, including aramid protective fabric.

10. The radiation protection layer forming device according to claim 8, characterized in that, The weighted effective curvature is calculated using the following expression: K weighted =α·K1+β·K2 Among them, K weighted K1 represents the weighted effective curvature of the spatial curvature model to be processed; K2 represents the maximum principal radius of curvature of the spatial curvature model to be processed; a represents the first weighting coefficient determined based on the elastic modulus of the material along the radial direction and the elastic modulus along the latitudinal direction perpendicular to the radial direction; β represents the second weighting coefficient determined based on the elastic modulus of the material along the radial direction and the elastic modulus along the latitudinal direction.

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