KR102446278B1 - Satellite mesh antenna device and mesh antenna manufacturing method - Google Patents

Abstract

The present invention relates to a satellite mesh antenna apparatus with a net structure, and a method for unfolding the antenna with the net structure applied to the same. The satellite mesh antenna apparatus includes: a feeder unit; a reflection unit having flexibility, disposed along a boundary of the feeder unit, and reflecting electromagnetic waves; a shape fixing unit disposed to face the reflection unit for fixing a shape of the reflection unit and connected with the reflection unit; and an unfolding unit for unfolding the shape fixing unit centering around the feeder unit. The present invention can maintain a shape of the reflection unit while reducing a weight of the reflection unit.

Description

Satellite mesh antenna device and mesh antenna manufacturing method

The present invention relates to a satellite mesh antenna device and a mesh antenna manufacturing method, and more particularly, to a satellite mesh antenna device and a mesh antenna manufacturing method capable of reducing the phase non-uniformity of radio waves reflected from the reflecting unit while reducing the weight of the reflecting unit. it's about

The antenna is for transmitting radio waves to the outside and for receiving radio waves from the outside. The antenna includes a dish-shaped reflective panel that forms a curved surface in order to stably transmit and receive radio waves. Antennas used in space are mounted on artificial satellites and launched into space.

On the other hand, the cost of launching a satellite into space increases as its weight increases. Therefore, it is necessary to reduce the weight of the satellite in order to reduce the cost. However, the antenna is designed in a three-dimensional curved shape to maximize the radiation efficiency of radio waves. In addition, the antenna is made of a rigid panel having a metal material in order to stably maintain the designed shape and prevent deformation. At this time, in order to reduce the weight of the rigid panel, the thickness should be reduced. However, even if the thickness of the rigid panel is reduced, since the area must be maintained, the strength of the rigid panel is weakened and it is difficult to stably maintain the shape. That is, it is difficult to reduce the weight of the artificial satellite by reducing the weight of the rigid panel. Therefore, there is a limit to reducing the weight of the artificial satellite with a conventional antenna having a rigid panel.

The technology underlying the present invention is disclosed in the following patent documents.

US 10-2289302 B1

The present invention provides a satellite mesh antenna device and a mesh antenna manufacturing method capable of reducing the phase non-uniformity of radio waves reflected from the reflecting unit while reducing the weight of the reflecting unit.

An artificial satellite mesh antenna device according to an embodiment of the present invention, a feeder unit; a reflective unit having a plurality of openings to reflect radio waves and having a plurality of reflective panels disposed along the periphery of the feeder, wherein the disposition directions of the openings of each reflective panel are different between adjacent reflective panels; and a developing unit for developing the reflective unit around the feeder unit.

The openings of each reflective panel may be disposed toward the center of the reflective part.

The developed portion extends in a radial direction with respect to the feeder portion as a center, is spaced apart in the circumferential direction, is disposed between each of the reflective panels, and the openings of each of the reflective panels are formed around the developed portion disposed between the respective reflective panels. It can be symmetrical left and right.

The plurality of reflective panels may have an opening pattern congruent with each other.

An angle formed by an extension line of the opening pattern of the adjacent reflective panel may be greater than 90 degrees and less than 180 degrees.

Each of the reflective panels may have an opening pattern symmetrical left and right with respect to a center line in an extension direction of the reflective panel.

The plurality of reflective panels may have at least one of a mesh structure and a porous sheet structure.

The opening may include at least one of a mesh on a mesh structure and a void on a porous sheet structure.

A mesh antenna manufacturing method according to an embodiment of the present invention, the process of providing a deployment unit for the satellite antenna; providing a plurality of reflective panels having a plurality of openings; and coupling the plurality of reflective panels to the development unit so that the disposition directions of openings of each reflective panel are different between adjacent reflective panels among the plurality of reflective panels.

The process of preparing the plurality of reflective panels may include: preparing a base material having a plurality of openings and reflecting radio waves; The process of dividing the base material so that the opening patterns of each are congruent with each other when overlapping each other to match the outer shape; may include.

The process of preparing the base material may include a process of preparing the base material having at least one of a network structure and a porous sheet structure.

The process of coupling the plurality of reflective panels to the developing unit includes: disposing the plurality of reflective panels in the circumferential direction so that the arrangement direction of the openings of each reflective panel faces a center point where the center lines in the extension direction of the developing unit meet; may include

In the process of coupling the plurality of reflective panels to the development part, after disposing the plurality of reflective panels in the circumferential direction, a trajectory connecting the extension lines of the opening patterns of the adjacent reflective panels is a concentric polygon with respect to the central point. To achieve this, the process of aligning the plurality of reflective panels in a radial direction; may include.

In the process of coupling the plurality of reflective panels to the developing unit, after aligning the plurality of reflective panels in a radial direction, tension is applied to the plurality of reflective panels in a circumferential direction and a radial direction, respectively, the plurality of reflective panels and supporting each edge of the panel to the deployment unit.

According to an embodiment of the present invention, by including a plurality of reflective panels having a plurality of openings in the reflective part of the satellite mesh antenna device, the weight of the reflective part can be reduced, and the weight of the satellite mesh antenna device is reduced by the reduced weight of the reflective part. can be reduced Accordingly, as much as the weight of the satellite mesh antenna device is reduced, it is possible to reduce the consumption of fuel required to put the satellite mesh antenna device on the orbit, thereby reducing the launch cost.

Further, according to an embodiment of the present invention, when the plurality of reflective panels are disposed along the periphery of the feeder part, the plurality of reflective panels are disposed so that the arrangement directions of the openings of the respective reflective panels are different between the adjacent reflective panels, so that the plurality of reflective panels An opening pattern formed by the openings may have symmetry in the circumferential direction with respect to the center of the reflective portion. From this, by minimizing the difference in length between the reflection paths of the radio wave from each of the plurality of openings to the focal position of the radio wave, thereby reducing the phase non-uniformity between the radio waves reflected at the multiple positions of the reflecting unit in the radial and circumferential directions, the multiple positions of the reflector It is possible to uniformly distribute the phase in Accordingly, it is possible to improve the performance of the satellite mesh antenna device.

1 is a schematic diagram illustrating a state in which a satellite antenna device according to an embodiment of the present invention is folded with a reflector.
2 is a schematic diagram showing a state in which the satellite antenna device according to the embodiment of the present invention unfolds the reflector.
3 is a conceptual diagram illustrating a detailed structure of a plurality of reflective panels provided in a reflective unit according to an embodiment of the present invention.
4 is a conceptual diagram illustrating a detailed structure of a plurality of reflective panels provided in a reflective unit according to a comparative example.

Hereinafter, with reference to the accompanying drawings, an embodiment of the present invention will be described in detail. However, the present invention is not limited to the embodiments disclosed below, and will be implemented in various different forms. Only the embodiments of the present invention are provided to complete the disclosure of the present invention, and to completely inform those of ordinary skill in the art the scope of the invention. The drawings may be exaggerated in order to explain the embodiment of the present invention, and the same reference numerals in the drawings refer to the same elements.

The present invention relates to a satellite antenna device and an antenna deployment method. Hereinafter, an embodiment of the present invention will be described in detail by exemplifying a case in which the satellite antenna device and the antenna deployment method are applied to an artificial satellite operated on an aerial orbit. Of course, the satellite antenna device and the antenna deployment method according to the embodiment of the present invention may be variously applied to various wireless communication facilities operated on land or at sea.

Meanwhile, the satellite antenna device according to an embodiment of the present invention may be referred to as a satellite mesh antenna device having a uniform weaving pattern.

1 is a schematic diagram illustrating a state in which a satellite antenna device according to an embodiment of the present invention is folded with a reflector. In addition, FIG. 2 is a schematic diagram showing a state in which the satellite antenna device according to the embodiment of the present invention unfolds the reflector.

1 and 2 , the satellite antenna device according to an embodiment of the present invention has a plurality of openings in order to reflect the feeder unit 100 and radio waves, and is disposed along the periphery of the feeder unit 100 . The reflector 200 is provided with two reflective panels 210 , and the reflective part 200 and the feeder 100 are the center of the reflective part 200 in which the openings of each reflective panel 210 are disposed between the adjacent reflective panels 210 . ) includes a deployment unit 300 for developing.

In addition, in the satellite antenna device according to an embodiment of the present invention, when the reflection unit 200 is deployed, the transceiver unit ( 400) may be included.

The feeder unit 100 is for positioning the transceiver 400 at a desired height on the center of the reflection unit 200 , and may be installed on the center of the reflection unit 200 . The feeder unit 100 may include a base 110 , a strut 120 , and a torus 130 .

The base 110 serves to support the strut 120 to the body of the satellite. The base 110 may be installed in the body (not shown) of the artificial satellite. The base 110 may have a disk shape with an open center. Of course, the shape of the base 110 may vary. A strut 120 may be installed on one surface, for example, an upper surface of the base 110 . The base 110 may be referred to as a pedestal.

Meanwhile, a deployment device (not shown) may be provided on the upper surface of the base 110 . The deployment device may be positioned relatively close to the edge side of the upper surface of the base 110 , and may be disposed along the periphery of the upper surface of the base 110 . In this case, the strut 120 may be supported on the upper surface of the base 110 so as to be spaced apart from the edge side of the upper surface of the base 110 . From this, it is possible to prevent structural interference between the strut 120 and the deployment device. The deployment device may be connected to the lower part of the deployment part 300 so that the upper part can be rotated around the lower part of the deployment part 300 . Accordingly, the deployment unit 300 may stand up and be deployed by the deployment device. For example, the deployment device may include various parts such as links, rollers, beams, shafts, springs, gears, and the like, and their coupling structures may vary.

The strut 120 serves to position the transceiver 400 at a predetermined height on the center of the base 110 . One end of the strut 120 , for example, an upper end may extend to a predetermined height from the base 110 , and the other end, for example, a lower end, may be mounted on the upper surface of the base 110 . The transceiver 400 is mounted on the upper end of the strut 120 . The number of struts 120 may be plural, for example, three, and may be disposed along the circumference of the upper surface of the base 110 . Of course, the number of struts 120 may vary. The torus 130 may be mounted to connect the plurality of struts 120 at a plurality of heights spaced apart from one side, for example, upward from the base 110 .

The reflector 200 reflects the radio wave transmitted from the free space to the transceiver 400 , and reflects the radio wave transmitted from the transceiver 400 to the base station through the free space. The reflector 200 may be in a folded state in order to reduce the volume when the satellite is launched. In addition, the reflector 200 may be in an unfolded state to reflect radio waves after the artificial satellite enters the orbit.

The reflector 200 may have flexibility. Flexibility refers to a property of being freely bent and unfolded. That the reflective part 200 has flexibility may mean that the reflective part 200 is formed of a thin thickness that allows bending and unfolding freely, a structure that is small in rigidity and easy to bend, and a flexible material.

The reflection unit 200 may be disposed on the base 110 , and may be supported by the deployment unit 300 . The reflection unit 200 is erected at the same angle as the development unit 300 by the development unit 300 standing at a predetermined angle close to or perpendicular to the base 110 with respect to the base 110, and surrounds the outside of the strut 120. A cylinder or a predetermined shape close to a cylinder may be formed (see FIG. 1 ). At this time, the reflector 200 may stably wrap the outside of the strut 120 while at least a part of it is bent or folded between the deployment parts 300 using flexibility.

In addition, the reflection unit 200 may be deployed in the same manner as the deployment unit 300 by the deployment of the deployment unit 300 . Accordingly, the reflector 200 can be spread out in a radial form, and by gently laying down while drawing a predetermined parabola in a direction from the center of the base 110 to the edge, a shape similar to that of the parabolic antenna reflector can be achieved (FIG. 2). Reference).

At this time, the movement of the reflector 200 to be in a state in which the reflector 200 is gently laid down on the base 110 while being unfolded around the strut 120 from a state in which the reflector 200 is erected and folded is expanded. It is said

The reflective unit 200 may have at least one of a mesh structure and a porous sheet structure. Accordingly, the reflection unit 200 may have flexibility. In addition, it is possible to significantly reduce the weight compared to the solid type rigid panel. In this case, the mesh structure and the porous sheet structure may be implemented in various ways.

For example, the reflector 200 may include a fiber aggregate formed by entangled in a network form by weaving a plurality of fibers. In this case, the plurality of fibers may be entangled in a network form by weaving to form a net structure while having a relatively wide free space between each other. In addition, the plurality of fibers may be entangled in a network form by weaving to form a porous sheet structure while having a relatively narrow free space between each other. When the reflector 200 has a mesh structure, the plurality of openings may include a mesh on the mesh structure. When the reflective portion has a porous sheet structure, the plurality of openings may include voids on the porous sheet.

The material of the reflector 200 may be various. For example, the reflector 200 may include a molybdenum material. Specifically, the reflective unit 200 may include a fiber aggregate formed by entangled in a network form by weaving a plurality of metal fibers having a molybdenum material. Of course, as long as the reflective part 200 is a material that can be made of fibers while having flexibility, the material may be varied.

In addition, the reflector 200 may include a metal coating film for reflection of radio waves. In this case, the metal coating film may be a gold (Ag) coating film. In addition, the metal coating film may be coated on the metal fiber. Of course, the material of the reflection unit 200 itself may be made of a metal that can easily reflect radio waves, for example, gold (Ag).

The reflective unit 200 may include a plurality of reflective panels 210 . The plurality of reflective panels 210 may be arranged in a radial shape along the circumference of the base 110 . That is, one group including the plurality of reflective panels 210 is defined as the reflective unit 200 .

Each of the plurality of reflective panels 210 may extend in the radial direction (D). In addition, the plurality of reflective panels 210 may be disposed along the circumference of the base 110 in the circumferential direction (R). Both edges of the plurality of reflective panels 210 in the circumferential direction R may overlap the deployment part 300 . In addition, both edges of the plurality of reflective panels 210 in the circumferential direction R may be elastically connected to the deployment unit 300 . Accordingly, when the deployment part 300 is deployed in the radial direction (D), the plurality of reflective panels 210 may be deployed while being pulled taut in the radial direction (D) and the circumferential direction (R), and the deployed overall shape It can be formed to be close to this three-dimensional curved shape.

That is, each of the plurality of reflective panels 210 may be tensioned in the radial direction (D) and the circumferential direction (R) by elastically connecting both edges to the deployment unit 300 . Accordingly, the overall shape of the plurality of reflective panels 210 may be developed to approximate a three-dimensional curved shape similar to a parabolic antenna reflector, for example. In addition, the plurality of reflective panels 210 may have a predetermined curvature in the radial direction (D). In this case, the curvature may be the same as a predetermined curvature of the unfolding part 300 in the radial direction D. That is, the plurality of reflection units 200 may be developed in a three-dimensional curved shape having a predetermined curvature by the development unit 300 . On the other hand, as the number of the developed parts 300 is large, that is, the more closely the developed parts 300 are arranged in the circumferential direction (R), the uniformity of the shape of the reflective part 200 with respect to the three-dimensional curved shape can be further improved.

Here, in the radial direction D, in a state in which the plurality of reflective panels 210 are deployed, from the lower portion of each reflective panel 210 close to the base 110 to the upper portion of each reflective panel 210 far from the base 110 It can mean the direction toward The circumferential direction R is a direction crossing the radial direction D, and may be a direction in which the plurality of reflective panels 210 are arranged in a state in which the plurality of reflective panels 210 are deployed. The circumferential direction R may also be referred to as a circumferential direction.

3 is a conceptual diagram illustrating a detailed structure of a plurality of reflective panels provided in a reflective unit according to an embodiment of the present invention. Here, the dotted circle mark shown on the center side of the reflection unit 200 in FIG. 3 is the region where the feeder unit 100 is located, and when the reflection unit 200 is coupled to the deployment unit 300 , the reflection unit 200 is It may be a region to be cut from. Of course, in the drawing, a plurality of openings are shown in the dotted circle mark so that the arrangement direction P of the plurality of openings formed in each of the plurality of reflective panels 210 can be seen clearly toward the center C of the reflective part. .

2 and 3 , the plurality of openings formed in each of the plurality of reflective panels 210 may be disposed toward the center C of the reflective portion. Specifically, the plurality of openings formed in each of the plurality of reflective panels 210 may have an arrangement direction P in a direction toward the center C of the reflective part. Here, the center C of the reflective part may be the center of the reflective part 200 when the reflective part 200 is looked down in a state in which the reflective part 200 is deployed. The distance from the center C of the reflective part in the radial direction D of the reflective part 200 may be the same. The center C of the reflector may be vertically aligned with the center of the base 110 of the feeder unit 100 in the vertical direction.

In addition, each of the plurality of reflective panels 210 has an opening formed along the plurality of fibers between the plurality of fibers by weaving a plurality of fibers to have at least one structure of a net structure and a porous sheet structure in one direction. can have a regular pattern. In this case, the direction in which the pattern of the openings (hereinafter, the opening pattern) is regularly arranged may be defined as the arrangement direction P of the plurality of openings.

That is, the plurality of openings formed in each of the plurality of reflective panels 210 have the arrangement direction P toward the center C of the reflective part, so that the opening pattern formed in each of the plurality of reflective panels 210 is the center of the reflective part. It can be listed towards (C).

From this, the opening pattern of each of the plurality of reflective panels 210 may have symmetry in the circumferential direction R with respect to the center C of the reflective part. From this, by minimizing a difference in length between reflection paths of radio waves from each of the plurality of openings to the focal position of the radio waves, it is possible to reduce the phase non-uniformity in the plurality of openings over the entire area of the reflection unit 200 .

Furthermore, the openings of the reflective panel 210 adjacent to each other in the circumferential direction R may be symmetrical with respect to the deployment part 300 disposed between each reflective panel. Also, the angle θ formed by the extension lines A and B of the opening pattern of the adjacent reflective panel 210 may be greater than 90 degrees and less than 180 degrees. In addition, each of the plurality of reflective panels 210 may have an opening pattern symmetrical left and right with respect to a center line H in the extension direction of the reflective panel, where the center line H is the center C of the reflective part and each reflective panel. It may be a line passing through the center of the arc of 210 . Also, the plurality of reflective panels 210 may have an opening pattern congruent with each other. That is, when the plurality of reflective panels 210 are stacked on top of each other so that their external appearances match, the opening patterns may be congruent with each other.

From this, it is possible to further minimize the difference in length between reflection paths of radio waves from each of the plurality of openings to the focal position of the radio waves over the entire area of the reflection unit 200, thereby further reducing the phase non-uniformity in the plurality of openings. .

4 is a conceptual diagram illustrating a detailed structure of a plurality of reflective panels provided in a reflective unit according to a comparative example.

3 and 4, the opening pattern of the plurality of reflective panels according to the embodiment of the present invention will be described in comparison with the comparative example.

Referring to FIG. 4 , in the reflective unit 200 ′ according to the comparative example, the plurality of reflective panels 210 ′ are not designed in consideration of the arrangement direction P′ of the plurality of openings. Accordingly, the arrangement direction P' of the plurality of openings may be the same on all of the reflective panels 210' regardless of the positions in which the plurality of reflective panels 210' are disposed. In this case, the angle θ formed by the extension lines A' and B' of the opening pattern of the adjacent reflective panel 210' may be 90 degrees or 180 degrees.

Accordingly, the opening pattern of each of the plurality of reflective panels 210 ′ does not have symmetry in the circumferential direction R with respect to the center C of the reflective portion. That is, when two reflective patterns 210 adjacent to each other in the plurality of reflective panels 210 are stacked on top of each other so that their external appearances match, their opening patterns are shifted from each other. Accordingly, a difference in length between reflection paths of radio waves from each of the plurality of openings to the focal position of the electric wave increases over the entire area of the reflection unit 200 ′, so that it may be difficult to reduce the phase non-uniformity in the plurality of openings. .

On the other hand, referring to FIG. 3 , in the reflective part 200 according to the embodiment of the present invention, the opening pattern of each of the plurality of reflective panels 210 has symmetry in the circumferential direction (R) with respect to the center (C) of the reflective part. Accordingly, over the entire area of the reflection unit 200 , the difference in length between reflection paths of radio waves from each of the plurality of apertures to the focal position of the radio wave is further minimized, so that, compared to the comparative example, phase non-uniformity at the plurality of apertures can be further reduced, thereby improving the gain performance of the reflective unit 200 .

Hereinafter, the deployment unit 300 and the transceiver 400 according to an embodiment of the present invention will be described next.

1 and 2 , the development unit 300 forms the reflection unit 200 in a shape close to a three-dimensional curved shape, and serves to maintain the shape of the formed reflection unit 200 . In addition, the deployment unit 300 serves to expand the reflective unit 200 while being deployed by the deployment device. A plurality of deployment units 300 may be provided, each of which may be spaced apart from each other in the circumferential direction (R), and may each extend in the radial direction (D) with respect to the feeder unit 100 as a center. The plurality of deployment parts 300 may be disposed between each reflective panel 210 , may overlap an edge of each reflective panel 210 in the circumferential direction R, and may overlap the edge of each reflective panel 210 . can be combined with That is, each of the plurality of development parts 300 may have a shape extending along an edge of the reflective panel 210 . In this case, each of the plurality of deployment parts 300 may be a bar-shaped member having a predetermined curvature in the radial direction (D).

The plurality of deployment units 300 may be folded while being gathered toward the feeder unit 100 by the deployment device, and may be unfolded while unfolding toward the outside of the feeder unit 100 . For example, the developing unit 300 may stand up the plurality of reflective panels 210 by standing at a vertical or near-vertical angle. In addition, the deployment unit 300 may expand the plurality of reflective panels 210 by radially unfolding.

Meanwhile, the deployment unit 300 may be provided in a greater number than the reflective panel 210 . For example, the deployment unit 300 may have one more number than the reflective panel 210 . For example, if eight reflective panels 210 are provided, nine deployment units 300 may be provided, and may be disposed between each of the reflective panels 210 . At this time, in such a way that one developed part 300 supports the edges of the two reflective panels 210 located on both sides in the circumferential direction (R) from the corresponding developed part, three developed parts 300 per two reflective panels 210 are ), when viewed as a whole, the eight reflective panels 210 can be supported by the nine deployment parts 300 . Of course, the above-described number of reflective panels 210 and the number of development units 300 are exemplary, and the number thereof may vary. For example, the number of the deployment units 300 may be double that of the reflective panel 210 .

The transceiver 400 may transmit/receive communication information to and from a satellite terminal provided in a terrestrial base station. The transceiver 400 may be installed on the feeder unit 100 . Specifically, the transceiver 400 may be installed on the upper end of the support 120 of the feeder unit 100 . The height of the transceiver 400 may be a height at which a radio wave reflected from the reflector 200 can be received.

Hereinafter, an antenna manufacturing method applied to the satellite antenna device according to an embodiment of the present invention will be described in detail. In this case, the content overlapping with the above description of the satellite antenna device according to an embodiment of the present invention will be briefly described or the description thereof will be omitted.

An antenna manufacturing method according to an embodiment of the present invention includes a process of preparing the deployment unit 300 for an artificial satellite antenna, a process of providing a plurality of reflective panels 210 having a plurality of openings, and a plurality of reflective panels 210 of and coupling the plurality of reflective panels 210 to the deployment unit 300 so that the arrangement directions P of the openings of each reflective panel 210 are different between the adjacent reflective panels 210 .

First, a process of preparing the deployment unit 300 for the satellite antenna is performed. For example, it is possible to provide a plurality of deployment parts 300 each extending in the radial direction (D) and arranged in the circumferential direction (R). In this case, each development part 300 may have a predetermined curvature in the radial direction (D). In addition, each deployment unit 300 may be provided by being supported by the feeder unit 100 . In this case, the feeder unit 100 may be prepared in a state in which the assembly with the transceiver 400 is completed.

Thereafter, a process of preparing a plurality of reflective panels 210 having a plurality of openings is performed. Specifically, the process of preparing the plurality of reflective panels 210 includes a process of preparing a base material for having a plurality of openings and reflecting radio waves, and when overlapping each other to match the external appearance, the opening patterns each have It may include a process of dividing the base material so as to be congruent with each other.

That is, it is possible to prepare a base material having at least one structure of a network structure and a porous sheet structure. In this case, the base material may be prepared by entangling a plurality of fibers, such as a plurality of metal fibers, in a network form by weaving to form a fiber aggregate. Here, the plurality of metal fibers may include, for example, molybdenum material. In addition, the surface of the metal fiber may be coated with a metal coating film for reflection of radio waves, for example, a gold (Ag) coating film. In this case, the gold coating film may be coated after forming the fiber aggregate, or the fiber aggregate may be formed after the gold coating film is coated. In this case, a plurality of openings may be formed in the base material, and the openings may have a directionality by weaving.

In addition, after preparing the base material, the base material may be divided to provide a plurality of reflective panels 210 . In this case, each of the plurality of reflective panels 210 may be divided into a sectoral shape so that the overall shape of the plurality of reflective panels 210 may be circular when arranged in the circumferential direction R. Also, when the plurality of sector-shaped reflective panels 210 are stacked on top of each other so that their external appearances match, the base material may be divided in consideration of the directionality of the openings so that the opening patterns of each are congruent with each other.

Thereafter, the plurality of reflective panels 210 are provided to the developing unit 300 so that the arrangement directions P of the openings of each reflective panel 210 are different between the adjacent reflective panels 210 among the plurality of reflective panels 210 . perform the bonding process.

That is, the plurality of reflective panels 210 may be disposed in the circumferential direction R so that the arrangement direction of the openings of each reflective panel 210 faces a center point where the center lines in the extension direction of the deployment part 300 meet. At this time, the central point where the center lines in the extension direction of the deployment part 300 meet is a position aligned in the vertical direction with the position of the central point of the base part 110 of the feeder part 100, for example, a plurality of reflective panels 210 in the circumferential direction. It may be a position coincident with the position of the center of the reflective part when it is arranged in (R) and arranged in the shape of the reflective part 200 .

In addition, after disposing the plurality of reflective panels 210 in the circumferential direction (R), the orbits connecting the extension lines of the opening patterns of the adjacent reflective panels 210 form a concentric polygon with respect to the above-mentioned central point. The reflective panel 210 is aligned in the radial direction (D). That is, the positions of the plurality of reflective panels 210 in the radial direction D may be aligned with respect to each other so that the plurality of reflective panels 210 may form a three-dimensional curved shape similar to that of the parabolic antenna reflector.

By the process of disposing the plurality of reflective panels 210 in the circumferential direction (R) and the process of aligning the plurality of reflective panels 210 in the radial direction (D), the opening pattern of each of the reflective panels 210 is reflected It may be arranged to have symmetry in the circumferential direction (R) with respect to the negative center (C).

Then, after aligning the plurality of reflective panels 210 in the radial direction (D), the plurality of reflective panels (210) are respectively applied with tension in the circumferential direction (R) and the radial direction (D). Each edge of the panel 210 in the circumferential direction R is supported by the deployment unit 300 . For example, after each edge of the plurality of reflective panels 210 in the circumferential direction R is brought into contact with the deployment part 300 , the plurality of reflective panels 210 and the plurality of deployment parts 300 may be elastically connected. Meanwhile, there may be various ways to connect them. For example, by bonding and welding, or by using a tension wire to connect a plurality of reflective panels 210 by threading and sealing them to the deployment part 300, or to connect them by a method such as riveting or bolting. can

Thereafter, the reflecting unit 200 and the developing unit 300 may be erected. Specifically, by operating the deployment device, the deployment part 300 may be erected around the feeder part 100 of the satellite antenna device, and the feeder part 100 may be wrapped with the reflective part 200 . From this, the satellite antenna device can be provided. Thereafter, the satellite antenna device may be mounted on the satellite launch vehicle for launching the artificial satellite.

Through the above-described process, the manufactured satellite antenna device may be mounted on a satellite launch vehicle for launching an artificial satellite and launched into the air. In addition, the satellite antenna device may be separated from the satellite launch vehicle at a certain point in time and enter orbit.

When the satellite enters orbit and starts to operate, the deployment unit 300 may be deployed and the reflector 200 supported by the deployment unit 300 may be deployed. Thereafter, by using the reflector 200, the radio wave transmitted from the free space is reflected to the feeder unit 100 of the satellite antenna, and the radio wave transmitted from the feeder unit 100 is reflected into the free space, and the radio wave can be transmitted and received. have.

At this time, by using the arrangement direction P of the plurality of openings provided in the plurality of reflective panels 210 of the reflective part 200 , the phase non-uniformity on the plurality of openings in the entire area of the reflective part 200 is corrected. can be minimized, and from this, it is possible to stably maintain the transmission/reception quality of radio waves.

The above embodiments of the present invention are intended to illustrate the present invention, not to limit the present invention. It should be noted that the configurations and methods disclosed in the above embodiments of the present invention will be combined and modified in various forms by combining or intersecting with each other, and modifications thereof may also be considered as the scope of the present invention. That is, the present invention will be embodied in a variety of different forms within the scope of the claims and the technical spirit equivalent thereto, and those skilled in the art to which the present invention pertains can implement various embodiments within the scope of the technical spirit of the present invention. will be able to understand

100: feeder part
200: reflector
210: reflective panel
300: development part
400: transceiver

Claims (14)

delete delete delete delete delete delete delete delete The process of providing a deployment unit for the satellite mesh antenna;
providing a plurality of reflective panels having a plurality of openings; and
The process of coupling the plurality of reflective panels to the development unit so that the arrangement directions of the openings of each reflective panel are different between adjacent reflective panels among the plurality of reflective panels;
The process of coupling the plurality of reflective panels to the development part,
A process of disposing the plurality of reflective panels in the circumferential direction so that the arrangement direction of the openings of each reflective panel faces a center point where the center lines in the extension direction of the development part meet;
The process of coupling the plurality of reflective panels to the development part,
After disposing the plurality of reflective panels in the circumferential direction, the process of aligning the plurality of reflective panels in the radial direction so that the orbits connecting the extension lines of the opening patterns of the adjacent reflective panels form a concentric polygon with respect to the central point ; A mesh antenna manufacturing method comprising. 10. The method of claim 9,
The process of preparing the plurality of reflective panels,
Having a plurality of openings, the process of preparing a base material for reflecting radio waves;
The process of dividing the base material so that the opening patterns of each are congruent with each other when overlapping each other to match the outer shape; mesh antenna manufacturing method comprising a. 11. The method of claim 10,
The process of preparing the base material,
The process of preparing a base material having at least one structure of a net structure and a porous sheet structure; a method of manufacturing a mesh antenna comprising a. delete delete 10. The method of claim 9,
The process of coupling the plurality of reflective panels to the development part,
After aligning the plurality of reflective panels in the radial direction, the process of supporting each edge of the plurality of reflective panels to the development unit so that tension is applied to the plurality of reflective panels in the circumferential and radial directions, respectively; A method of manufacturing a mesh antenna comprising a.

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