Zero-constraint splicing method for mesh antenna metal net

Abstract

The invention discloses a mesh antenna metal net zero-constraint splicing method. A metal net is tiled and hung on a working tension applying device, and working tension is applied to the metal net in the transverse direction and the longitudinal direction; in the working tension state, tension control belts are sewn on the edges of the two sides of the metal net in the length direction; lapping two metal nets which need to be spliced and are sewn with the same tension control belts, wherein the sections of the lapping positions are lapped according to the sequence of belt-net-net-belt; sewing two layers of metal nets along the two sides of the tension control belt by adopting composite material sewing lines; and repeating the steps, and sewing all the metal meshes required by the whole antenna reflecting surface in sequence. According to the method, the metal net is spliced by adopting an overlock stitching method, the tension control belt can be detached after splicing is completed, the formed splicing seam is of a net-net structure, the thickness is only 0.07-0.08 mm, the elasticity keeps the original elasticity of the metal net, the net surface tension is more uniform, and the risk that the antenna expansion resistance is increased due to micro shrinkage of the tension control belt at high temperature is effectively eliminated.

Description

Technical Field

[0001] The invention belongs to the technical field of antennas, and in particular relates to a zero-constraint splicing method for a mesh antenna metal net. Background Art

[0002] With the development and application of deployable antennas, the diameter of large mesh antennas has reached tens of meters and even hundreds of meters. Since the metal mesh used for antennas is limited by the metal mesh weaving equipment, the size of a single metal mesh cannot meet the size requirements of the reflective surface of the metal mesh of large-diameter antennas, and the metal mesh used for antennas needs to be spliced.

[0003] The metal mesh used in deployable antennas is a fabric woven from ultrafine alloy wires, known for its electromagnetic wave reflectivity. This fabric is a flexible material with a warp-knit structure, and the inherent weave imparts a certain degree of elasticity to the mesh. To ensure a smooth, wrinkle-free surface after assembly, the mesh and antenna require additional low-elongation materials to control and maintain tension during splicing.

[0004] The existing method for splicing metal mesh for antennas involves directly sewing two pieces of metal mesh together. This method, when assembled with the antenna, primarily involves uneven application of working tension to the metal mesh, resulting in an uneven mesh surface. Patent document CN103521661B discloses a "metal mesh splicing device under a preset tension state." This device applies uniform pre-tension to the metal mesh along its length and width. A composite material with low elongation is then sewn onto the metal mesh along its length and width. The composite materials on different metal meshes are stretched to their natural lengths and then sewn together, overlapping them. The composite materials are then sewn together directly at their ends in the width direction, allowing for the splicing of multiple metal meshes to meet the requirements of large antenna diameters. When the metal mesh is assembled onto the antenna, the pre-tension is reapplied by stretching the composite material already on the metal mesh to its natural length. The resulting seam is inelastic, and during use of ultra-large antenna metal mesh assemblies, there is a risk of slight contraction of the tension control band at high temperatures, leading to increased deployment resistance. Summary of the Invention

[0005] The purpose of the present invention is to provide a zero-constraint splicing method for a mesh antenna metal mesh, which adopts a lock stitch method to splice the metal mesh. After the splicing is completed, the tension control belt can be removed. The formed seam presents a "mesh-mesh" structure with a thickness of only 0.07-0.08mm. The elasticity maintains the original elasticity of the metal mesh, which is conducive to the laying of the reflective surface, makes the mesh tension more uniform, and effectively eliminates the risk of increased antenna deployment resistance due to slight shrinkage of the tension control belt under high temperature.

[0006] The technical solution adopted by the present invention is a zero-constraint splicing method of a mesh antenna metal mesh, comprising the following steps:

[0007] Step 1: Hang the metal mesh flat on a working tension applying device that is larger than its own width. Calculate the longitudinal and transverse working tension values ​​of the metal mesh according to the working tension requirements. Apply transverse tension first and then longitudinal tension to allow the metal mesh to expand naturally.

[0008] Step 2: Lay tension control tape at least 10 mm from the edge along the length of the metal mesh on both sides. Stretch the tension control tape naturally and fit it onto the metal mesh surface. Preliminary fixation is performed on both ends. Composite material sutures are used to sew the tension control tape to the metal mesh using a flat stitch method.

[0009] Step 3, remove the sewn metal mesh from the working tension applying device and sew the next piece of metal mesh;

[0010] Step 4, overlapping the two metal meshes with the same tension control belts sewn on them;

[0011] Step 5: Preliminarily fix the suture starting point, and use composite material suture thread to sew the two layers of metal mesh along the edges of both sides of the tension control belt, using a lock stitch method for suturing;

[0012] Step 6: Repeat steps 1-5 to sew all the metal meshes required for the entire antenna reflector surface.

[0013] Furthermore, in step 1, after the metal mesh expands naturally, it is left to stand for at least 30 minutes to observe whether the metal mesh surface is flat and wrinkle-free and whether the mesh openings are uniform.

[0014] Furthermore, in step 2, the composite material suture lines are two parallel lines. To facilitate removal, the composite material suture lines are 1-2 mm away from the edge of the tension control belt, and the stitches are controlled at 15-20 mm. After suturing, the mesh surface is flat and wrinkle-free.

[0015] Furthermore, in step 4, the specific overlapping step is: align the tension control belts of the two layers of metal mesh during overlapping, overlap the cross-section at the overlapping point in the order of "belt-mesh-mesh-belt", and the tension control belts are distributed on the outer surfaces of the two layers of metal mesh.

[0016] Furthermore, in step 5, the overlock stitch method is specifically as follows: the stitch size is controlled at 5-8 mm, the stitch method is raised from bottom to top, and three stitches form a coil.

[0017] The beneficial effects of the present invention are:

[0018] The present invention adopts the lock stitch method to splice the metal mesh. After the splicing is completed, the tension control belt can be removed. The formed seam presents a "mesh-mesh" structure with a thickness of only 0.07-0.08mm. The elasticity maintains the original elasticity of the metal mesh, which is conducive to the laying of the reflecting surface, makes the mesh tension more uniform, and effectively eliminates the risk of increased antenna deployment resistance due to slight shrinkage of the tension control belt under high temperature. It can be widely promoted in the development of ultra-large deployable antenna reflective surfaces. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 Schematic diagram of the overall process of the method of the present invention;

[0020] Figure 2 Schematic diagram of laying out the metal mesh and applying working tension according to the present invention;

[0021] Figure 3 This is a schematic diagram of the auxiliary tension control belt suturing of the present invention;

[0022] Figure 4 This is a schematic diagram of the structure of the seam joint of the present invention;

[0023] Figure 5 This is a schematic diagram of suturing stitches during splicing according to the present invention;

[0024] Figure 6 This is a schematic diagram of the seam formed after splicing of the present invention;

[0025] Explanation of the accompanying symbols: 1. Tension applying device; 2. Metal mesh; 3. Tension control belt; 4. Composite material sewing line, 5. Metal mesh 1; 6. Metal mesh 2; 7. Starting line; 8. Suturing direction (where ①, ②, ③, ④ are the sewing order); 9. Composite material sewing coil. DETAILED DESCRIPTION

[0026] In order to make the objectives, technical solutions and advantages of the present invention clearer and more understandable, the technical solutions of the present invention will be further described in detail below with reference to the accompanying drawings.

[0027] A zero-constraint splicing method for a mesh antenna metal mesh, such as Figure 1 As shown, the specific steps include:

[0028] Step 1, such as Figure 2 As shown, hang the metal mesh 2 flat on a special working tension applying device 1 that is larger than its own width. Calculate the longitudinal and transverse working tension values ​​of the metal mesh 2 according to the working tension requirements. Load the transverse tension first and then the longitudinal tension to allow the metal mesh 2 to expand naturally. Let it stand for at least 30 minutes and observe whether the metal mesh surface is flat and wrinkle-free and whether the mesh holes are uniform.

[0029] Step 2, such as Figure 3As shown, a low-elongation auxiliary tension control belt 3 is laid on both sides of the metal mesh 2 at a distance of more than 10 mm (dimension A) from the edge in the length direction. The tension control belt 3 is naturally flattened and fits the metal mesh surface. The two ends are preliminarily fixed. The tension control belt 3 and the metal mesh 2 are sutured with a composite material suture 4. The needle method can be a flat needle method. The composite material suture 4 is two parallel lines. For easy removal, the composite material suture 4 is 1-2 mm (dimension B) away from the edge of the tension control belt 3. The stitches can be controlled at 15-20 mm (dimension C). After suturing, the mesh surface is flat and wrinkle-free.

[0030] Step 3, such as Figure 4 As shown, the sewn mesh 5 (i.e. Figure 4 The metal mesh 1 in the workpiece is removed from the dedicated working tension applying device 1 and the next piece of mesh 6 (i.e. Figure 4 2) Sewing of the metal mesh.

[0031] Step 4, overlap the two pieces of metal mesh 2 with the same tension control belt 3. The specific overlapping steps are: align the tension control belts 3 of the two layers of metal mesh 2 during overlapping, and overlap the cross-section of the overlapping part in the order of "belt-mesh-mesh-belt". The tension control belts 3 are distributed on the outer surface of the two layers of metal mesh 2, which is convenient for installation with the antenna mechanism or removal after installation.

[0032] Step 5: Preliminarily fix the suture starting point, use composite material suture thread 4 to sew the two layers of metal mesh 2 along the edges of both sides of the tension control belt 3, and use the lock stitch method to sew. The lock stitch method is as follows:

[0033] like Figure 5 As shown, the stitch size is controlled at 5-8mm (size D), and the needle is raised from bottom to top, with three needles forming a loop (as shown in the figure). Figure 5 The needle raising 7 and the sewing direction 8 are shown in the figure, where ①, ②, ③, and ④ are shown as the sewing order).

[0034] Step 6: Repeat steps 1-5 to sew all the metal meshes required for the entire antenna reflector surface.

[0035] When assembling the metal mesh component and the antenna mechanism, the auxiliary tension control belt 3 can be removed. After removal, the two metal meshes (metal mesh 1 and metal mesh 2) are spliced ​​together as shown in FIG. Figure 6 As shown, the formed suture seam is composed of two composite material suture coils 9. The composite material suture coils 9 have relatively large elasticity, which can achieve zero constraint on the metal mesh 2, maintain the elasticity of the metal mesh 2 itself at the seam, facilitate the laying of the reflective surface, make the mesh tension more uniform, and effectively eliminate the risk of increased resistance to antenna deployment due to slight contraction of the tension control belt under high temperature.

[0036] The contents not described in detail in the specification of the present invention belong to the existing common technologies in this technical field.

Claims

1. A zero-constraint splicing method for a mesh antenna metal mesh, characterized in that: The following steps are involved: Step 1: Hang the metal mesh flat on a working tension applying device that is larger than its own width. Calculate the longitudinal and transverse working tension values ​​of the metal mesh according to the working tension requirements. Apply transverse tension first and then longitudinal tension to allow the metal mesh to expand naturally. Step 2: Lay tension control tape at least 10 mm from the edge along the length of the metal mesh on both sides. Stretch the tension control tape naturally and fit it onto the metal mesh surface. Preliminary fixation is performed on both ends. Composite material sutures are used to sew the tension control tape to the metal mesh using a flat stitch method. Step 3, remove the sewn metal mesh from the working tension applying device and sew the next piece of metal mesh; Step 4: Overlap two pieces of metal mesh with the same tension control tape sewn on them; Step 5: Preliminarily fix the suture starting point, and use composite material suture thread to sew the two layers of metal mesh along the edges of both sides of the tension control belt, using a lock stitch method for suturing; Step 6: Repeat steps 1-5 to sew all the metal meshes required for the entire antenna reflector surface.

2. The zero-constraint splicing method for mesh antenna metal mesh according to claim 1, characterized in that: In step 1, after the metal mesh expands naturally, it is left to stand for at least 30 minutes to observe whether the metal mesh surface is flat and wrinkle-free and whether the mesh openings are uniform.

3. The zero-constraint splicing method for mesh antenna metal mesh according to claim 1, characterized in that: In step 2, the composite material suture lines are two parallel lines. To facilitate removal, the composite material suture lines are 1-2 mm away from the edge of the tension control belt, and the stitches are controlled at 15-20 mm. After suture, the mesh surface is flat and wrinkle-free.

4. The zero-constraint splicing method for mesh antenna metal mesh according to claim 1, characterized in that: In step 4, the specific overlapping steps are: align the tension control belts of the two layers of metal mesh during overlapping, overlap the cross-section at the overlapping point in the order of "belt-mesh-mesh-belt", and the tension control belts are distributed on the outer surfaces of the two layers of metal mesh.

5. The zero-constraint splicing method for mesh antenna metal mesh according to claim 1, characterized in that: In step 5, the overlock stitch method is specifically as follows: the stitch length is controlled at 5-8 mm, the stitch method is raised from bottom to top, and three stitches form a coil.

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