A stitch structure and sewing method for multi-piece splicing of warp-knitted metal mesh

Abstract

This application relates to a stitch structure and sewing method for splicing multiple pieces of warp-knitted metal mesh, and pertains to the field of application technology of medium and large-sized metal mesh for satellite antenna reflector surfaces. The method for splicing and sewing warp-knitted metal mesh includes: S1, providing at least two pieces of warp-knitted metal mesh to be spliced; S2, overlapping the edges of adjacent pieces of mesh with a width of 1-1.5cm to form an overlap area; S3, using polyimide or aramid filaments with a specification of 200-600D as sewing thread, and sewing along the overlap area using sewing equipment, wherein the stitch spacing is 0.8-1.2cm and the stitch density is 3-5 stitches / cm. This application improves surface accuracy by using an overlap width of 1-1.5cm and automated parameter control for sewing, a stitch length of 0.8-1.2cm, a density of 3-5 stitches / cm, and high-performance polyimide or aramid thread of 200-600D. This effectively avoids the problems of easy aging and embrittlement of traditional polyester thread or webbing, and improves long-term stability.

Description

Technical Field

[0001] This application relates to the field of medium and large-sized metal mesh application technology for satellite antenna reflector surfaces, and in particular to a multi-piece splicing stitch structure and sewing method for warp-knitted metal mesh. Background Technology

[0002] In the field of aerospace engineering, the research on satellite antennas is of great significance to my country's major aerospace science and technology projects. Due to the limitations of rocket launch space and capabilities, large-aperture deployable antennas are the core components for satellites to achieve high-performance signal reception and transmission. The surface accuracy, structural strength, and long-term on-orbit stability of the reflector directly determine the antenna's electrical performance. As the core carrier for realizing the electromagnetic function of the reflector, warp-knitted metal mesh must possess excellent conductivity, flexibility, and surface shape retention capabilities. However, limited by the inherent width of warp knitting machinery, the size of a single mesh panel cannot meet the requirements of large-aperture antennas. Therefore, multiple mesh panels are usually spliced ​​together with high precision and high strength to form a complete reflector, which has become a key process in antenna development.

[0003] Currently, the industry generally uses traditional sewing and splicing techniques to connect wire mesh. This process mainly relies on manual operation and can be divided into two common methods: one is as follows... Figure 1 As shown in Figure a, in this method, the metal mesh edges and the mesh surface used in the splicing are made of the same weave and material, and the edges of the two pieces of metal mesh are directly aligned and sewn together using stitches; the second method is as follows: Figure 1 As shown in b, the edges of the two pieces of metal mesh to be spliced ​​are first individually treated with webbing overlap stitching. Then, the two mesh pieces with completed webbing overlap stitching are spliced ​​a second time. Ordinary polyester webbing is sewn to the edge of one mesh piece, and then the other mesh piece is sewn to the webbing to distribute stress with the help of the webbing. Both methods require the operator to manually align the mesh openings and control the sewing trajectory and stitch spacing.

[0004] However, the aforementioned traditional sewing process has several problems. First, manual operation is prone to uneven tension and misalignment, leading to localized deformation of the mesh. Furthermore, the significant difference in thermal expansion coefficients between polyester webbing and the metal mesh can cause surface distortion under alternating temperatures in orbit. Second, direct sewing causes stress concentration at the needle holes in the rigid metal wires, making the threads susceptible to breakage under the vibrations of satellite launches and the fatigue loads of repeated expansion and contraction in orbit. When using ordinary polyester webbing, the material is prone to aging and embrittlement in the extreme environments of space, such as ultraviolet radiation and atomic oxygen, becoming a weak point in the structure and posing a risk of mesh tearing. Finally, existing technologies heavily rely on worker experience, resulting in slow splicing speeds and difficulties in achieving uniform stitch density and mesh alignment. Summary of the Invention

[0005] The purpose of this application is to provide a multi-piece stitch structure and sewing method for warp-knitted metal mesh to solve the problems existing in the prior art.

[0006] To achieve the above objectives, the technical solution adopted in this application is as follows: This application provides a method for stitching together multiple pieces of warp-knitted metal mesh, including the following steps: S1. Provide at least two pieces of warp-knitted metal wire mesh to be spliced; S2. The edges of the adjacent mesh panels to be spliced ​​are overlapped with a width of 1-1.5cm to form an overlap area; S3. Use polyimide or aramid filament with a specification of 200-600D as sewing thread, and sew along the overlap area using sewing equipment. The stitch spacing width is 0.8-1.2cm, and the stitch density is 3-5 stitches / cm.

[0007] Furthermore, in S3, the suturing method is as follows: Within the overlapping area, at least two vertical stitches are provided, formed by the sewing needle only moving up and down, and at least one cyclic zigzag stitch is provided, formed by the sewing needle moving up and down while also moving left and right. The cyclic zigzag stitch overlaps and is fixed with the vertical stitches to achieve the sewing of the overlapping area.

[0008] Furthermore, in S3, the suturing method includes the following steps: S31: Stack a polyimide webbing and sew it to one side of the first mesh to form a composite mesh edge with webbing; S32: Place the edge of the second mesh piece to be spliced ​​on the edge of the composite mesh piece, so that the polyimide webbing is between the two mesh pieces, and then sew the second mesh piece, the polyimide webbing and the first mesh piece together.

[0009] Furthermore, in S31, the polyimide webbing is smoothly sewn onto the edge of the first mesh using an overlapping stitching process.

[0010] Furthermore, in S23, the edge of the second mesh panel is aligned with the edge of the first mesh panel along the splicing direction.

[0011] This application also provides a warp-knitted metal mesh multi-piece splicing stitch structure prepared by any of the above-mentioned warp-knitted metal mesh multi-piece splicing and sewing methods, comprising at least two warp-knitted metal mesh pieces, the two mesh pieces being connected by overlapping and sewing to form an overlapping area, the width of the overlapping area being 1-1.5cm, and fixed by sewing parameters of 200-600D polyimide or aramid filament sewing thread with a stitch interval width of 0.8-1.2cm and a stitch density of 3-5 stitches / cm.

[0012] Furthermore, the splicing structure is a three-needle single-thread chain splicing overlap structure, and the overlap area includes mutually overlapping and fixed vertical stitches and cyclic zigzag stitches.

[0013] Furthermore, the splicing structure is a three-layer composite reinforcement structure. The overlapping area includes an upper mesh, a polyimide webbing, and a lower mesh layer stacked in sequence. The polyimide webbing is pre-stitched and fixed to the edge of the lower mesh layer, and the upper mesh layer is stitched and fixed to the polyimide webbing and the lower mesh layer.

[0014] This application also provides a metal wire mesh assembly for a large-aperture deployable spaceborne antenna, which is made by stitching together multiple warp-knitted metal wire mesh sheets using any of the above-mentioned warp-knitted metal mesh multi-sheet splicing and sewing methods.

[0015] Furthermore, when the number of mesh pieces is greater than two, the method of splicing and sewing multiple pieces of warp-knitted metal mesh is repeated, and multiple mesh pieces are spliced ​​together in sequence and cut as a whole according to the preset outline.

[0016] The beneficial effects of the technical solution provided in this application include at least the following: (1) This application achieves a high-precision and high-stability splicing surface by using a standardized overlap width of 1-1.5cm and automated parameter control for suturing, a stitch length of 0.8-1.2cm, and a density of 3-5 stitches / cm. This eliminates the alignment error and uneven force caused by manual operation, improves the surface accuracy, and effectively improves long-term stability.

[0017] (2) This application selects high-performance polyimide or aramid thread with a density of 200-600D. The inherent resistance of polyimide or aramid material to space environment can resist vacuum, ultraviolet radiation, atomic oxygen erosion and extreme high and low temperature cycles in orbit for a long time. This effectively avoids the problem of easy aging and embrittlement of traditional polyester thread or webbing, and ensures the structural integrity and functional reliability of the antenna throughout the entire mission life.

[0018] (3) This application uses a cyclic zigzag stitch to interweave horizontally in vertical stitches, which effectively resists the mutual slippage of the mesh when it is under force, thereby improving the integrity and dimensional stability of the splicing structure.

[0019] (4) By introducing polyimide webbing as an intermediate layer, this application effectively absorbs the concentrated stress at the splice seam and disperses it laterally to a wider area, thereby improving the static strength and fatigue life of the splice. Attached Figure Description

[0020] The accompanying drawings are provided to further illustrate the present application and form part of the specification. They are used together with the embodiments of the present application to explain the application and do not constitute a limitation thereof. In the drawings: Figure 1 This is a side view diagram of the metal mesh splicing and stitching method in the prior art; Figure 2This is a side view of the splicing and stitching method in Embodiment 1 of the present invention; Figure 3 This is a front view schematic diagram of the splicing structure in Embodiment 1 of the present invention; Figure 4 This is a schematic diagram of the splicing structure from another perspective in Embodiment 1 of the present invention; Figure 5 This is a schematic diagram of the thread coil structure in Embodiment 1 of the present invention; Figure 6 This is a side view of the splicing and stitching method in Embodiment 2 of the present invention; Figure 7 This is a front view schematic diagram of the splicing structure in Embodiment 2 of the present invention; Figure 8 This is a schematic diagram of the webbing overlapping process in Embodiment 2 of the present invention; Figure 9 This is a structural schematic diagram of the mesh splicing process in Embodiment 2 of the present invention; Figure 10 This is a schematic diagram of the seam effect of a metal wire mesh assembly in one embodiment of the present invention.

[0021] Explanation of key figure labels: 10. Mesh sheet; 11. Overlap area; 12. Composite mesh edge; 20. Sewing thread; 21. Circular zigzag stitch; 22. Vertical stitch; 30. Polyimide webbing. Detailed Implementation

[0022] The technical solutions of the embodiments of this application will be clearly and completely described 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 of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0023] In this specification, identical components are represented by the same reference numerals. It should be noted that the terms "front," "rear," "left," "right," "upper," and "lower" used in the following description refer to directions in the accompanying drawings, while the terms "bottom surface," "top surface," "inner," and "outer" refer to directions towards or away from a specific component, respectively. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this specification, "multiple" means two or more.

[0024] Example 1 Please refer to Figures 2-5 A method for stitching together multiple pieces of warp-knitted metal mesh includes the following steps: S1. Provide at least two warp-knitted metal wire mesh sheets 10 to be spliced; S2. The edges of the two adjacent mesh panels 10 to be spliced ​​are overlapped with a width of 1-1.5cm to form an overlap area 11. S3. Use polyimide or aramid filament with a specification of 200-600D as sewing thread 20, and sew along the overlap area 11 using sewing equipment. The stitch spacing is 0.8-1.2cm, and the stitch density is 3-5 stitches / cm.

[0025] In this embodiment, as Figure 2 , Figure 3 , Figure 4 As shown, in step S1, at least two warp-knitted metal wire mesh sheets 10 that meet the design requirements are provided. These mesh sheets 10 are typically made of conductive fibers suitable for aerospace environments, such as gold-plated molybdenum wire or silver-plated fiberglass wire. Before splicing, the edges of the mesh sheets 10 to be spliced ​​need to be inspected and trimmed to ensure that the mesh edges are straight and free of loose or protruding metal wires, thus creating conditions for subsequent precise overlapping.

[0026] In step S2, the edges of the two mesh pieces 10 to be spliced ​​are overlapped along the splicing direction. Using a positioning fixture with precise graduations or a vision-assisted alignment system, the overlap width between the edges of the two mesh pieces 10 is strictly controlled within the range of 1-1.5cm, forming an overlap area 11 with a consistent width. This width range is the optimal range verified by experiments. A width less than 1cm may result in insufficient splicing strength, while a width greater than 1.5cm will increase unnecessary weight and thickness and may affect the flexibility of the mesh surface. After alignment, low-adhesion, residue-free temporary fixing adhesive dots or special clamping tools can be used to initially fix the overlap area 11 to prevent misalignment during the sewing process.

[0027] In step S3, an automated sewing machine is used. The sewing thread 20 is selected from polyimide or aramid filaments with a specification of 200D to 600D. Threads within this specification range possess sufficient tensile strength and flexibility, and polyimide or aramid materials have excellent resistance to high and low temperatures, UV radiation, and antigenic oxygen erosion, making them fully adaptable to the extreme environment of space. The selected sewing thread 20 is loaded onto a dedicated sewing machine. Key sewing parameters are preset in the machine's control system: the stitch spacing is 0.8-1.2cm, which balances sewing efficiency and stress distribution uniformity; the stitch density is set to 3-5 stitches / cm, ensuring sufficient sewing points per centimeter of overlap to provide a strong grip while preventing damage to the metal wire or hardening of the mesh 10 due to excessively dense stitches. The machine is then started, guiding the sewing needle to automatically sew along the pre-fixed center line of the overlap area 11 or a preset trajectory. Sewing equipment must maintain constant tension and feed speed to ensure even and consistent stitches. After sewing is completed, cut the thread and heat-seal or knot the thread ends to prevent them from coming loose.

[0028] The above method, through a standardized overlap width of 1-1.5cm and automated parameter control of stitching, a stitch pitch of 0.8-1.2cm, and a density of 3-5 stitches / cm, achieves a high-precision and high-stability splicing surface, eliminating alignment errors and uneven force caused by manual operation. Furthermore, the spliced ​​mesh 10 exhibits minimal deformation, improving surface accuracy and effectively enhancing long-term stability. High-performance polyimide or aramid thread of 200-600D is selected, offering high strength and fatigue resistance. Combined with optimized stitch parameters, this allows the stitching points to uniformly and effectively bear the load, significantly reducing the risk of breakage caused by rigid contact and stress concentration of metal wires in traditional processes. Moreover, the inherent space environment resistance of polyimide or aramid materials ensures that the stitched area, like the main body of mesh 10, can withstand long-term on-orbit vacuum, ultraviolet radiation, atomic oxygen corrosion, and extreme high and low temperature cycles. This effectively avoids the aging and embrittlement problems of traditional polyester thread or webbing, ensuring the structural integrity and functional reliability of the antenna throughout its entire mission lifespan.

[0029] Furthermore, key parameters in this method—overlap width, stitch specifications, stitch length, and stitch density—are all quantitatively controlled, significantly reducing the number of operators, accelerating the splicing speed, and ensuring that the quality of spliced ​​mesh panels produced by different batches and operators is highly consistent, resulting in a significant improvement in the yield rate and fully meeting the production requirements of mass production and high reliability for aerospace products.

[0030] In the specific sewing method, in S3, the sewing method is as follows: within the overlapping area 11, at least two vertical stitches 22 are provided, which are formed by the sewing needle only moving up and down, and at least one cyclic zigzag stitch 21 is formed by the sewing needle moving up and down while moving left and right. The cyclic zigzag stitch 21 overlaps and is fixed with the vertical stitches 22 to achieve sewing of the overlapping area 11.

[0031] In this embodiment, as Figure 5 As shown, this sewing method is suitable for splicing small-sized metal meshes. "Small-sized" specifically refers to meshes with a diameter of 4-8 μm, requiring only two mesh panels 10 to be spliced. A three-needle sewing method is used, with all stitches being single-thread chain stitch, and the overlap width of the mesh panels is 1-1.5 cm. Specifically, a multi-head sewing machine is used, with at least three independent sewing needles installed on the machine head. At least two of these needles are designated as first sewing needles, which perform only up-and-down reciprocating piercing movements perpendicular to the plane of the mesh panel 10. Additionally, at least one second sewing needle is installed between the two first sewing needles, which, while performing the up-and-down reciprocating piercing movement, drives the needle tip to perform a regular left-and-right reciprocating swing in the horizontal plane.

[0032] Two precisely overlapped mesh panels 10 are placed and fixed in the sewing equipment's working area. Upon starting the equipment, all sewing needles begin working simultaneously: the two first sewing needles sew two parallel, straight longitudinal stitches within the overlap area 11, according to a preset stitch spacing width (e.g., 0.8-1.2 cm) and stitch density (e.g., 3-5 stitches / cm), to achieve a secure fastening function perpendicular to the mesh surface. The second sewing needle, located in the middle, shifts its needle tip horizontally relative to the forward direction during each stitch insertion and withdrawal. As the mesh panel 10 or the sewing head feeds at a uniform speed, the stitches produced by this needle form continuous zigzag or wavy loops. These looping stitches 21 repeatedly intersect, entwine, or interlock with the two vertical stitches 22 along their path. This creates a spatially integrated network of three stitches, mechanically securing the upper and lower mesh panels 10 within the overlap area 11 through multi-dimensional, interlocking stitching.

[0033] In the above-described stitching method, the cyclic zigzag stitches 21 interweave laterally within the vertical stitches 22, forming a strong constraint in the horizontal direction. This effectively resists the mutual slippage of the mesh 10 under stress, effectively solving the problems of mesh edge misalignment and loosening, and improving the overall integrity and dimensional stability of the spliced ​​structure. Furthermore, because the stitches form a spatially interwoven network, loads from any direction on the mesh 10 can be quickly distributed across multiple stitches and a larger area, avoiding stress concentration at a few straight needle points. This reduces the risk of thread breakage or fatigue fracture of the wire mesh at needle holes, extending the on-orbit service life of the spliced ​​parts.

[0034] Correspondingly, a multi-piece splicing stitch structure of warp-knitted metal mesh, prepared by a multi-piece splicing and sewing method, includes at least two warp-knitted metal mesh sheets 10. The two mesh sheets 10 are connected by overlapping and sewing to form an overlapping area 11. The width of the overlapping area 11 is 1-1.5cm, and it is fixed by sewing parameters of 200-600D polyimide or aramid filament sewing thread with a stitch interval width of 0.8-1.2cm and a stitch density of 3-5 stitches / cm. The splicing structure is a three-needle single-thread chain splicing overlapping structure. The overlapping area 11 includes mutually overlapping and fixed vertical stitches 22 and cyclic zigzag stitches 21.

[0035] In this embodiment, as Figure 4 As shown, the warp-knitted wire mesh splicing structure formed using the above-described sewing method comprises at least two independent warp-knitted wire mesh sheets 10. The sheets 10 are typically woven from metal wires (such as gold-plated molybdenum wire), possessing good conductivity and flexibility. The two sheets 10 overlap each other with a width of 1-1.5 cm, forming a clearly defined overlap area 11. Within the overlap area 11, the two layers of mesh sheets 10 are securely sewn together using 20 polyimide or aramid filament sewing thread with a specification of 200D to 600D. The sewing is performed according to the following process parameters: stitch spacing width of 0.8-1.2 cm, and stitch density of 3-5 stitches / cm. Within the overlap area 11, the specific stitching structure is as follows: there are at least two parallel, basically perpendicular straight stitches to the edge of the mesh 10, with a fastening force perpendicular to the mesh surface direction, constraining the interlayer separation of the mesh 10; there is at least one stitch that changes periodically in a zigzag or wavy shape, which runs horizontally between the vertical stitches 22, and intersects, wraps around or hooks with the vertical stitches 22 in space to form a mechanical interlock, forming a single-line chain structure.

[0036] Example 2 Please see Figures 6-9 A method for stitching multiple pieces of warp-knitted metal mesh is presented in Embodiment 2. The structure and steps are basically the same as those in Embodiment 1. The difference is that in step S3 of this embodiment, the stitching method includes the following steps: S31: A polyimide webbing 30 is stacked and sewn to one side of the first mesh 10 to form a composite mesh edge 12 with webbing; S32: Place the edge of the second mesh 10 to be spliced ​​on the composite mesh edge 12, so that the polyimide webbing 30 is located between the two meshes 10, and then sew the second mesh 10, the polyimide webbing 30 and the first mesh 10 together.

[0037] Specifically, in S31, the polyimide webbing 30 is smoothly sewn onto the edge of the first mesh 10 using an overlapping stitching process.

[0038] In addition, in S23, the edge of the second mesh 10 is aligned with the edge of the first mesh 10 along the splicing direction.

[0039] In this embodiment, as Figure 6 , Figure 7 As shown, this stitching method is suitable for splicing medium and large-sized metal meshes. Medium and large-sized specifically refer to scenarios where the diameter is greater than 8m and more than two mesh panels 10 need to be spliced ​​together. The splicing method uses polyimide webbing 30. The specific stitching method is as follows: Select a reinforcing webbing of appropriate width and material is polyimide, and the first piece of metal wire mesh 10 to be spliced. Place the polyimide webbing 30 along one side of the mesh edge to be spliced ​​on the reference mesh panel 10, ensuring that one side edge of the webbing is strictly aligned with the mesh edge of the mesh panel 10. The alignment process can be achieved by means of optical projection, the edge of a precision jig, or the weave markings on the mesh edge itself. The aligned polyimide webbing 30 is flatly stacked on the upper surface of the edge of the reference mesh 10. It is gently smoothed by hand or with a roller to remove air bubbles or wrinkles, ensuring a tight fit between the webbing and the mesh. Using 200-600D polyimide or aramid sewing thread 20, it is sewn along the area where the webbing and mesh edge are attached, using the sewing method described in Example 1. The sewing thread 20 includes vertical stitches 22 and circular zigzag stitches 21. Alternatively, a layering process can be used, where the needle passes sequentially through the webbing and the underlying metal mesh 10, firmly fixing them together to form a composite mesh edge 12 with webbing, thus completing the webbing layering process. Figure 8 As shown. The first prepared mesh panel 10 is laid flat and fixed, with its composite mesh edge 12 facing upwards. Then, the second mesh panel 10 to be spliced ​​is taken, and its edge to be spliced ​​is precisely aligned with the edge of the sewn webbing on the first mesh panel 10. The edge of the second mesh panel 10 must be aligned with the edge of the first mesh panel 10 itself along the splicing direction. Then, the second mesh panel 10 is flatly stacked on top of the first mesh panel 10. At this time, the polyimide webbing 30 is sandwiched between the two mesh panels 10. Using the same sewing equipment and thread, along the aligned splicing seam, the upper connecting mesh panel 10, the middle polyimide webbing 30, and the lower reference mesh panel 10 are sewn together in one go to complete the mesh splicing process. Figure 9 As shown, this forms a three-layer composite splicing structure of metal mesh 10, polyimide webbing 30, and metal mesh 10.

[0040] In the above steps, by introducing polyimide webbing 30 as an intermediate layer, the concentrated stress at the splicing seam can be effectively absorbed and laterally dispersed to a wider area, thereby reducing the stress peak at the direct stress point of the metal mesh. This solves the problem of stress concentration causing breakage at the seam, improving the static strength and fatigue life of the splicing area. Polyimide is chosen as the webbing material because it possesses extreme high and low temperature resistance, UV resistance, antigenic oxygen resistance, and low gas release characteristics that match high-performance seams. This ensures that the entire splicing structure, like the main metal mesh, can maintain stable performance throughout its entire orbital lifespan, avoiding the catastrophic failure risk caused by aging and embrittlement of traditional materials such as polyester in the space environment. Furthermore, the polyimide webbing 30 is completely encapsulated between the two metal mesh layers; its non-conductive nature does not affect the surface current distribution of the antenna, ensuring that the splicing area and the main mesh 10 have consistent electromagnetic reflection performance.

[0041] Correspondingly, in a warp-knitted metal mesh multi-piece splicing stitch structure prepared by a warp-knitted metal mesh multi-piece splicing and sewing method, for the splicing structure of the overlapping area 11, specifically, the splicing structure is a three-layer composite reinforcement structure. The overlapping area 11 includes an upper mesh 10, a polyimide webbing 30 and a lower mesh 10 stacked in sequence. The polyimide webbing 30 is pre-stitched and fixed to the mesh edge of the lower mesh 10, and the upper mesh 10 is stitched and fixed to the polyimide webbing 30 and the lower mesh 10.

[0042] In this embodiment, the three-layer composite reinforcement structure is a three-layer material stacked structure, consisting of a metal wire mesh 10, a polyimide reinforcing webbing, and another metal wire mesh 10 from top to bottom. These three layers completely overlap in space and are integrally fixed by stitching, forming a structural unit. This structure can disperse stress at the seams and avoid localized stress concentration through the mechanical buffering and strength enhancement effect of the polyimide webbing 30. Specifically, the lower mesh 10 and the polyimide webbing 30 are pre-stitched securely to the edge of the lower mesh 10, ensuring that the webbing and the lower mesh 10 are combined into a rigid composite unit before splicing, guaranteeing precise webbing positioning and no slippage. The upper mesh 10 is then fixed to both the pre-fixed polyimide webbing 30 and the lower mesh 10 through the final stitching process. The stitches pass sequentially through the upper mesh 10 and the middle polyimide webbing 30, thereby locking the three layers into a single unit. The overlap width of the entire structure, i.e., the width of the three-layer composite structure, is 1-1.5cm. The sewing thread 20 that fixes the three layers is 200D-600D polyimide or aramid filament, and the resulting stitches have an interval width of 0.8-1.2cm and a density of 3-5 stitches / cm. The mesh edges of the upper mesh 10 and the lower mesh 10 are precisely aligned in the splicing direction.

[0043] Example 3 Please see Figure 10 A large-diameter deployable spaceborne antenna metal mesh assembly is made by stitching together multiple warp-knitted metal mesh panels 10 using a warp-knitted metal mesh splicing and sewing method. When the number of mesh panels 10 is greater than two, the warp-knitted metal mesh splicing and sewing method is repeated to splice multiple mesh panels 10 in sequence and then cut as a whole according to a preset outline.

[0044] In this embodiment, taking the splicing of 6 single-width metal meshes as an example, each single-width metal mesh is numbered from 1 to 6 from left to right along the splicing direction. Metal meshes 1 and 6 serve as the outer edge mesh 10 of the overall mesh surface, participating in the splicing of adjacent mesh 10 only on one side. The remaining metal meshes, 2 to 5, require splicing on both sides. Specifically, the standardized operation of the warp-knitted metal mesh splicing method described above is repeated. This embodiment uses polyimide webbing 30 to splice multiple metal meshes sequentially, ultimately forming the following... Figure 8 The diagram shows the overall metal mesh structure; the dotted lines in the diagram represent the preset cutting outline. After splicing, precise cutting is performed according to this outline to achieve complete forming of the metal mesh area, meeting the needs of satellite antennas and other scenarios for large-size, high-precision metal mesh.

[0045] In the embodiments disclosed in this application, the terms "installation," "connection," "linking," and "fixing" should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; "linking" can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the embodiments disclosed in this application according to the specific circumstances.

[0046] The above description is only a preferred embodiment of this application. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this application, and these improvements and modifications should also be considered within the scope of protection of this application.

Claims

1. A method for stitching together multiple pieces of warp-knitted metal mesh, characterized in that, Includes the following steps: S1. Provide at least two pieces of warp-knitted metal wire mesh to be spliced; S2. The edges of the two adjacent mesh panels to be spliced ​​are overlapped with a width of 1-1.5cm to form an overlap area; S3. Use polyimide or aramid filament with a specification of 200-600D as sewing thread, and sew along the overlapping area using sewing equipment. The stitch spacing is 0.8-1.2cm, and the stitch density is 3-5 stitches / cm.

2. The method for splicing and sewing multiple pieces of warp-knitted metal mesh according to claim 1, characterized in that, In S3, the suturing method is as follows: Within the overlapping area, at least two vertical stitches are provided, formed by the sewing needle only making up-down reciprocating movements, and at least one cyclic zigzag stitch is provided, formed by the sewing needle making up-down movements while also making left-right reciprocating movements. The cyclic zigzag stitch overlaps and is fixed with the vertical stitches to achieve the sewing of the overlapping area.

3. The method for splicing and sewing multiple pieces of warp-knitted metal mesh according to claim 1, characterized in that, In S3, the suturing method includes the following steps: S31: Stack a polyimide webbing and sew it to one side of the first mesh to form a composite mesh edge with webbing; S32: Place the edge of the second mesh piece to be spliced ​​on the edge of the composite mesh piece, so that the polyimide webbing is located between the two mesh pieces, and then sew the second mesh piece, the polyimide webbing and the first mesh piece together.

4. The method for splicing and sewing multiple pieces of warp-knitted metal mesh according to claim 3, characterized in that, In S31, the polyimide webbing is smoothly sewn onto the edge of the first mesh piece using an overlapping stitching process.

5. The method for splicing and sewing multiple pieces of warp-knitted metal mesh according to claim 4, characterized in that, In step S23, the edge of the second mesh panel is aligned with the edge of the first mesh panel along the splicing direction.

6. A warp-knitted metal mesh multi-piece splicing stitch structure prepared by the method of splicing and sewing multiple pieces of warp-knitted metal mesh according to any one of claims 1-5, characterized in that, It includes at least two warp-knitted metal wire mesh panels, which are connected by overlapping and sewing to form the overlapping area. The width of the overlapping area is 1-1.5cm, and it is fixed by sewing parameters of 200-600D polyimide or aramid filament sewing thread with a stitch interval width of 0.8-1.2cm and a stitch density of 3-5 stitches / cm.

7. The multi-piece spliced ​​stitch structure of warp-knitted metal mesh according to claim 6, characterized in that, The splicing structure is a three-needle single-thread chain splicing overlap structure, and the overlap area includes vertical stitches and cyclic zigzag stitches that overlap and are fixed to each other.

8. The multi-piece spliced ​​stitch structure of warp-knitted metal mesh according to claim 6, characterized in that, The splicing structure is a three-layer composite reinforcement structure. The overlapping area includes an upper mesh, a polyimide webbing, and a lower mesh layer stacked in sequence. The polyimide webbing is pre-stitched and fixed to the edge of the lower mesh layer. The upper mesh layer is stitched and fixed to the polyimide webbing and the lower mesh layer.

9. A metal mesh assembly for a large-aperture deployable spaceborne antenna, characterized in that, It is made by stitching together multiple warp-knitted metal wire mesh sheets using the warp-knitted metal mesh multi-piece splicing sewing method as described in any one of claims 1-5.

10. A metal mesh assembly for a large-aperture deployable spaceborne antenna according to claim 9, characterized in that, When the number of mesh pieces is greater than two, the method of splicing and sewing multiple pieces of warp-knitted metal mesh is repeated, and the multiple mesh pieces are spliced ​​together in sequence and cut as a whole according to the preset outline.

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