KR102446276B1 - Antenna apparatus for satellite with mesh and method for unfolding antenna with mesh - Google Patents

Abstract

The present invention relates to a satellite antenna apparatus with a mesh structure and a method for unfolding the antenna with the mesh structure. The satellite antenna apparatus with the mesh structure 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

A network-structured satellite antenna device and a network-structured antenna deployment method TECHNICAL FIELD

The present invention relates to a network-structured satellite antenna device and a network-structured antenna deployment method, and more particularly, to a network-structured satellite antenna device capable of maintaining the shape of a reflective part while reducing the weight of the reflective part and a network-structured antenna deployment method is 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 10-2282878 B1 US 10-2289300 B1

The present invention provides a satellite antenna device having a network structure and a method for deploying an antenna having a network structure, which can maintain the shape of the reflector while reducing the weight of the reflector.

A satellite antenna device having a network structure according to an embodiment of the present invention includes: a feeder unit; a reflection unit having flexibility, disposed along the periphery of the feeder unit, and reflecting radio waves; a shape fixing part disposed opposite the reflective part and connected to the reflective part to fix the shape of the reflective part; and a deployment part for expanding the shape fixing part around the feeder part.

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The reflective unit may include a fiber aggregate formed by entangled fibers in a network form by weaving.

The reflective part may be elastically connected to the shape fixing part at a plurality of positions on the rear surface of the reflective part in radial and circumferential directions in order to be fixed in a three-dimensional curved shape, and tension may be applied in the radial and circumferential directions.

The reflector may have a first curvature in a circumferential direction and a second curvature different from the first curvature in a radial direction.

The shape fixing part may include: a membrane having a three-dimensional curved shape, and having bending rigidity and thickness capable of maintaining the three-dimensional curved shape by itself; and a plurality of strings disposed along an area of the membrane in radial and circumferential directions between the membrane and the reflective part and connecting the reflective part to the membrane.

The string is formed in a bar shape to prevent bending due to the acceleration applied to the reflection unit, and may include a rigid material.

The membrane may include a fiber fabric formed in a single layer or a plurality of layers.

The development portion extends in a radial direction, is spaced apart in the circumferential direction, is disposed on both sides of the shape fixing portion in the circumferential direction, is rotatably connected to the feeder portion, and the shape fixing portion is supported by both edges of the development portion, respectively can be

The development part may have the same curvature as the shape fixing part in a radial direction.

The deployment part includes a front flange relatively close to the feeder part, a rear flange relatively far from the feeder part, and a web connecting the front flange and the rear flange, the edge of the reflection part is supported on the front flange, , the edge of the shape fixing part may be supported on the rear flange.

An antenna deployment method of a network structure according to an embodiment of the present invention includes the steps of: providing an artificial satellite antenna including a flexible reflector; launching the satellite antenna into the air; maintaining the shape of the reflective part using a shape fixing part of the satellite antenna while the satellite antenna is launched into the air; and developing the shape fixing part and developing the reflective part while maintaining the shape of the reflective part.

The step of emitting the satellite antenna into the air includes: emitting the satellite antenna with the reflection part and the shape fixing part standing up to surround the periphery of the feeder part of the satellite antenna; including, the shape of the reflection part The process of maintaining the shape fixing part may include;

The process of preparing the satellite antenna includes a process of preparing a fiber assembly formed by fibers entangled in a network form by weaving as the reflection unit; The process of reducing the inertial resistance due to the launch of the satellite antenna by using; may include.

After the process of developing the reflector, the radio wave transmitted from the free space is reflected to the feeder unit of the satellite antenna using the three-dimensional curved shape of the reflector, and the radio wave transmitted from the feeder unit is reflected into the free space. process of sending and receiving; The process of applying tension in a radial direction and a circumferential direction at a plurality of positions of the reflection unit to prevent deformation of the reflection unit due to an external force applied to the reflection unit during transmission and reception of the radio wave, respectively; may include.

According to the embodiment of the present invention, since the satellite antenna device having a network structure includes a flexible reflector, the weight of the satellite antenna device having a network structure can be reduced. In addition, the shape of the reflective part can be formed and fixed in a desired shape by using the shape fixing part.

Accordingly, as much as the weight of the network-structured satellite antenna device is reduced, it is possible to reduce the consumption of fuel required to put the network-structured satellite antenna device on orbit, thereby reducing the launch cost. In addition, it is possible to improve the reflection efficiency of radio waves by using a reflection unit having a fixed shape in a desired shape, thereby improving the performance of the satellite antenna device having a network structure. In addition, it is possible to prevent the shape of the reflector from being deformed while operating the satellite antenna device of the network structure on the orbit, thereby maintaining the performance of the satellite antenna device of the network structure.

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 schematic diagram showing an enlarged part of a satellite antenna device according to an embodiment of the present invention.
4 is a schematic diagram for illustrating an example of a reflector of an artificial satellite antenna device according to an embodiment of the present invention.

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. In order to explain the embodiment of the present invention, the drawings may be exaggerated, parts irrelevant to the description may be omitted from the drawings, and the same reference numerals in the drawings refer to the same elements.

The present invention relates to a network-structured satellite antenna device and a network-structured antenna deployment method. Hereinafter, an embodiment of the present invention will be described by exemplifying a case in which the satellite antenna device and the antenna deployment method are applied to an artificial satellite operated in orbit in the air. It will be described in detail. 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.

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, the feeder unit 100, is flexible and disposed along the periphery of the feeder unit 100, a reflector for reflecting radio waves ( 200), a shape fixing part 300 that is disposed opposite to the reflective part 200 and connected to the reflective part 200 in order to fix the shape of the reflective part 200, and a shape fixing part around the feeder part 100 ( It includes a deployment unit 400 for deploying 300).

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 ( 500) may be included.

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 feeder unit 100 is to position the transceiver 500 at a desired height on the center of the reflector 200 , and may be installed on the center of the reflector 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 connected to the lower portion of the deployment unit 400 , and may be deployed while rotating the deployment unit 400 . For example, the deployment device may include various parts, such as links, rollers, beams, shafts, springs, and gears, and the coupling structure of these parts may vary.

The strut 120 serves to position the transceiver 500 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 500 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, upwards from the base 110 .

3 is an enlarged schematic view showing a part of the satellite antenna device according to an embodiment of the present invention, and FIG. 4 is a schematic diagram for exemplarily showing a reflector of the satellite antenna device according to an embodiment of the present invention.

3 and 4 , the reflector 200 reflects the radio wave transmitted from the free space to the transceiver 500 and reflects the radio wave transmitted from the transceiver 500 to the base station through the free space. do 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 reflective unit 200 may be disposed on the base 110 , and may be supported by the deployment unit 400 . A plurality of reflectors 200 may be provided, and may be arranged in a radial form along the circumference of the base 110 .

In addition, the reflection unit 200 is erected at the same angle as the development unit 400 by the development unit 400 standing at a predetermined angle close to or perpendicular to the vertical with respect to the vape 110 , and the outside of the strut 120 . It can form a cylindrical shape or a predetermined shape close to a cylinder (see FIG. 1). In addition, the reflection unit 200 may be rotated and deployed in the same manner as the deployment unit 400 by the rotation and deployment of the deployment unit 400 , and may be spread in a radial form. In addition, the reflector 200 can form a shape similar to that of a parabolic antenna reflector, for example, by being gently laid down while drawing a predetermined parabola in a direction from the center of the base 110 to the edge in a radially unfolded state (FIG. 2). Reference).

Here, 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 standing and folded state is the development of the reflector 200 . It is said

The reflective unit 200 may have at least one structure selected from the group consisting of a mesh structure, a sheet structure, and a perforated 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, the sheet structure, and the hole-perforated sheet structure may be implemented in various ways.

That is, the reflection unit 200 may include a fiber aggregate formed by entangled fibers in a network form by weaving. In this case, the fiber aggregate may be formed in a network structure. Here, the network structure may be various. For example, by applying a method of forming a square wire mesh, it is possible to weave the fiber aggregate to form a square mesh structure (see Fig. 4 (a)). In addition, by applying a method of forming a honeycomb wire mesh, it is possible to weave the fiber aggregate to form a honeycomb network structure (see FIG. 4(b) ). In addition, the fiber aggregate may be woven in a plain weave method, a twill weave method, a water-weave method, etc. to form a sheet structure. In addition, after the fiber assembly is formed into a sheet structure, a hole is perforated to form a perforated sheet structure (refer to FIG. 4(c) ). Since the reflective part 200 has the above-described structure, the weight of the reflective part 200 can be significantly reduced compared to, for example, a solid type rigid panel.

Of course, the reflection unit 200 may be directly formed into a mesh structure, a sheet structure, and a sheet structure in which holes are perforated by using a powder of a flexible material and a 3D printer.

The material of the reflector 200 may be various. For example, the reflector 200 may include a molybdenum material. Specifically, the reflective portion 200 may be formed by weaving a fiber aggregate using a molybdenum wire or a molybdenum wire bundle as a fiber. Of course, the reflector 200 may be made of various materials as long as the material can have flexibility.

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. The metal coating film may be coated on the molybdenum wire. 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 part 200 may be elastically connected to the shape fixing part 300 at a plurality of positions on the rear surface of the reflective part 200 in the radial direction (R) and the circumferential direction (C) to be fixed in a three-dimensional curved shape. . Also, both edges of the reflective unit 200 in the circumferential direction C may be supported by the deployment unit 400 , respectively.

Here, the radial direction R is a direction from a lower portion of the reflective unit 200 close to the base 110 to an upper portion of the reflective unit 200 far from the base 110 in a state in which the reflective unit 200 is deployed. can mean The circumferential direction (C) is a direction intersecting the radial direction (R), and may be a direction in which the reflectors 200 are arranged in a state in which the reflectors 200 are deployed. The circumferential direction C may also be referred to as a circumferential direction.

Also, the rear surface of the reflective part 200 may be in a direction toward the shape fixing part 300 among both sides of the reflective part 200 . Meanwhile, a surface opposite to the rear surface of the reflection unit 200 may be defined as a front surface of the reflection unit 200 . The front surface of the reflector 200 may be a surface that reflects radio waves.

A plurality of positions on the rear surface of the reflection unit 200 are elastically connected to the shape fixing unit 300 , so that tension may be applied in the radial direction (R) and the circumferential direction (C), and the shape of the reflection unit 200 is adjusted. It is formed in a shape substantially identical to the shape of the shape fixing part 300 , and the formed shape can be stably maintained. In this case, as the number of the plurality of positions on the rear surface where the reflective part 200 is connected to the shape fixing part 300 increases, the sameness of the shapes of the reflective part 200 and the shape fixing part 300 may be further improved.

With the above-described structure, the reflection unit 200 may have a first curvature in the circumferential direction C and a second curvature different from the first curvature in the radial direction R. Accordingly, the reflection unit 200 may be formed in a three-dimensional curved shape having a first curvature and a second curvature.

The shape fixing part 300 forms the shape of the reflective part 200 in a three-dimensional curved shape, and serves to maintain the shape of the formed reflective part 200 . The shape fixing part 300 may be provided in the same number as the reflective part 200 so as to correspond one-to-one with the reflective part 200 . The shape fixing part 300 may have both edges supported by the deployment part 400, respectively.

Since the shape fixing part 300 can maintain the shape of the reflective part 200 , the area of the reflective part 200 can be greatly increased in the circumferential direction C, and the area of the reflective part 200 can be increased. The number of the deployment parts 400 can be reduced as much as necessary. Accordingly, it is possible to significantly reduce the overall weight of the satellite antenna device.

The shape fixing part 300 has a three-dimensional curved shape, and a membrane 310 having a bending rigidity and thickness capable of maintaining a three-dimensional curved shape by itself, and a radial direction between the membrane 310 and the reflective part 200 ( R) and a plurality of strings 320 arranged along the area of the membrane 310 in the circumferential direction C and connecting the reflective unit 200 to the membrane 310 may be included.

The membrane 310 may include a fiber fabric formed in a single layer or a plurality of layers, and the fiber fabric may have bending rigidity and thickness capable of maintaining a three-dimensional curved shape by itself. The membrane 310 may have the same or similar area as the reflector 200 .

The membrane 310 may include beta cloth. In this case, the beta cloth may be a type of cloth woven with silica fibers having fire resistance and coated with Teflon. Of course, as long as the membrane 310 is a material that is lighter than the metal for the satellite panel of the same volume and can maintain its shape, the material may be varied.

The string 320 serves to fix the reflector 200 to the membrane 310 . A plurality of strings 320 may be provided, and may be arranged in a radial direction (R) and a circumferential direction (C) along the curved surface of the membrane 310 .

Meanwhile, as the number of strings 320 increases, the distance between them may become narrower. In addition, when the distance between the strings 320 is narrowed, the string 320 may pull the reflective unit 200 more closely. Accordingly, as the number of strings 320 increases, the shape of the reflective part 200 may become closer to the shape of the membrane 310 .

On the other hand, in one view of the string 320, the reflector 200 and the membrane 310 are connected point-to-point, but in the overall view of the plurality of strings 320, the radial direction R and the circumferential direction C ) by connecting a plurality of positions of the reflective unit 200 to a plurality of positions of the membrane 310 , the same or similar effect as that of connecting the reflective unit 200 and the membrane 310 face-to-face may be obtained. Accordingly, it may be seen that the plurality of strings 320 connect the entire surface of the reflective unit 200 to the entire surface of the membrane 310 .

The string 320 is formed in a bar shape to prevent bending due to the acceleration applied to the reflection unit 200 , and may include a rigid material. For example, the reflector 200 and the membrane 310 may have the same area, but may have different weights, so that even when the same acceleration is applied, the inertial resistance may be different, and relative motion may occur with each other. In this case, the string 320 constrains the distance H between the reflector 200 and the membrane 310 to the length of the string 320 , thereby preventing relative motion between them.

One end of the string 320 may be mounted or attached to the reflective unit 200 , and the other end of the string 320 may be mounted or attached to the membrane 310 . In this case, mounting and attaching methods may be various. For example, a hook may be formed at one end and the other end of the string 320 , and the hook may be mounted by passing the hook through the reflector 200 and the membrane 310 . In addition, the ice plies may be formed at one end and the other end of the string 320 , and the ice splices may be attached to the reflective unit 200 and the membrane 310 using a wire or thread to be sewn together. Also, one end and the other end of the string 320 may be riveted or bolted to be mounted on the reflector 200 and the membrane 310 . In addition, one end and the other end of the string 320 may be attached to the reflective unit 200 and the membrane 310 by bonding or welding. The string 320 may be referred to as a tension wire.

The developing part 400 serves to support the reflective part 200 and the shape fixing part 300 and to develop the reflective part 200 and the shape fixing part 300 . The deployment part 300 may be provided in plurality, each of which may extend in the radial direction (R) and may be spaced apart from each other in the circumferential direction (C). That is, the deployment unit 300 may be arranged along the circumference of the feeder unit 100 . In addition, each of the plurality of deployment parts 300 may be disposed on both sides of the shape fixing part 300 in the circumferential direction (C). At this time, one shape fixing part 300 may be disposed within the two deployment parts 300 . That is, the two deployment parts 300 may support one shape fixing part 300 . Of course, the arrangement relationship between the deployment unit 300 and the shape fixing unit 300 may vary. In addition, the development part 400 may have the same curvature as the shape fixing part 300 in the radial direction (R). That is, the unfolding part 400 may have a shape extending along the edge of the shape fixing part 300 from both sides of the shape fixing part 300 .

The deployment part 400 may be rotatably connected to the lower part of the feeder part 100 so as to be folded while gathering toward the feeder part 100 or unfolded while unfolding toward the outside of the feeder part 100 . Specifically, the lower portion of the deployment unit 400 may be rotatably connected to the deployment device provided on the upper surface of the base 110 , and may stand up or be deployed by the operation of the deployment device. In this case, the developing unit 400 may stand upright or at a predetermined angle close to vertical, so that the reflective unit 200 and the shape fixing unit 300 may stand up. In addition, the developing part 400 may expand the reflecting part 200 and the shape fixing part 300 by unfolding in a radial form.

A bracket (not shown) may be provided at the upper end of the deployment unit 400 . The bracket may be formed to protrude from the top of the deployment unit 400, and its shape may vary. The bracket may fix the deployment part 400 to the strut 120 when the deployment part 400 is in a folded state. In addition, the bracket may be separated from the strut 120 by releasing the fixing force when the deployment unit 400 is deployed. On the other hand, a fixing device (not shown) may be provided at a predetermined position of the strut 120 corresponding to the height of the bracket in the state in which the deployment unit 400 is folded. The bracket may be fixed in contact with the fixing device in a state in which the deployment unit 400 is folded. The manner in which the fixing device secures the bracket may vary. A fixing device may secure the bracket, for example using an electromagnet. In addition, when the deployment unit 400 is deployed, the fixing force may be released by stopping the operation of the fixing device.

The deployment part 400 is a web connecting the front flange 410 relatively close to the feeder part 100 , the rear flange 420 relatively far from the feeder part 100 , the front flange 410 and the rear flange 420 . It may be a structure including 430 . Of course, the structure of the deployment unit 400 may vary. For example, the deployment unit 400 may have a structure of a hollow square pipe. The deployment unit 400 may include a carbon fiber reinforced plastic (CFRP) material. Of course, the material of the deployment unit 400 may vary.

An edge of the reflection unit 200 may be supported on the front flange 410 . In addition, the edge of the shape fixing part 300 may be supported on the rear flange 420 . In this case, a method of mounting the edge of the reflective unit 200 to the front flange 410 may be various. For example, the edge of the reflective unit 200 may be mounted on the front flange 410 by bonding or bolting. Similarly, a method of mounting the edge of the shape fixing part 300 to the rear flange 420 may be various such as bonding or bolting.

The transceiver 500 may transmit/receive communication information to and from a satellite terminal provided in a terrestrial base station. The transceiver 500 may be installed on the feeder unit 100 . Specifically, the transceiver 500 may be installed on the upper end of the support 120 of the feeder unit 100 . The height of the transceiver 500 may be a height capable of receiving radio waves reflected from the reflector 200 .

Hereinafter, an antenna deployment method to which the satellite antenna device according to an embodiment of the present invention is applied 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 deployment method according to an embodiment of the present invention includes a process of preparing a satellite antenna including a reflector 200 having a flexibility, a process of emitting the satellite antenna into the air, and a process of launching the satellite antenna into the air while the satellite antenna is launched into the air The process of maintaining the shape of the reflective part 200 using the shape fixing part 300 of the satellite antenna, and the shape fixing part 300 while maintaining the shape of the reflective part 200 to expand the reflective part 200 It includes the process of developing.

First, a process of preparing the satellite antenna including the flexible reflector 200 is performed. In this case, the process of preparing the satellite antenna may include a process of preparing the fiber aggregate formed by entangled fibers in a network form by weaving as the reflective unit 200 . In addition, the process may include a process of supporting the edge of the prepared reflective part 200 on the deployment part 400 and a process of supporting the back surface of the prepared reflective part 200 on the shape fixing part 300 .

Specifically, a molybdenum wire, for example, is prepared as a fiber to be woven into the fiber assembly. Thereafter, the molybdenum wire is woven to form a fiber aggregate. In this case, the structure of the formed fiber assembly may be formed in at least one of a network structure, a sheet structure, and a sheet structure in which holes are perforated. In this case, when the fiber aggregate is formed to have a plurality of structures, a different structure may be formed for each portion of the fiber aggregate or a different structure may be formed for each thickness of the fiber aggregate. Here, forming different structures for each thickness means, for example, when the direction from the back of the fiber assembly to the front facing the back is the thickness direction, forming a fiber aggregate of different structures in a plurality of layers in the thickness direction of the fiber assembly. can mean that Of course, in addition to this, the fiber aggregate may be formed to have a plurality of structures in various ways. On the other hand, before or after weaving the fiber assembly, a metal film may be coated on the fiber or the fiber assembly. Here, the metal layer is a metal layer for smoothly reflecting radio waves, and may include, for example, a gold (Ag) layer. Of course, the material itself of the fiber assembly may be formed of a material that easily reflects radio waves. Thereafter, the reflective part 200 may be prepared by cutting the formed fiber assembly into the same area and shape as the shape fixing part 300 .

At this time, while the reflection unit 200 is being prepared, the assembly of the feeder unit 100 , the shape fixing unit 300 , the deployment unit 400 , and the transceiver unit 500 may be completed. Of course, before or after preparing the reflector 200 , the feeder unit 100 , the shape fixing unit 300 , the deployment unit 400 , and the transceiver 500 may be prepared in a completed state.

Thereafter, the edge and the rear surface of the reflection unit 200 may be supported by the development unit 400 and the shape fixing unit 300 . Specifically, the edge of the reflection unit 200 may be supported by the deployment unit 400 , and the prepared rear surface of the reflection unit 200 may be supported by the shape fixing unit 300 . In this case, the order of supporting the edge and the rear surface of the reflective unit 200 may vary. For example, the rear surface of the reflection unit 200 may be supported first, and the edge of the reflection unit 200 may be supported.

On the other hand, after the reflective part 200 is supported on the shape fixing part 300 , the reflective part 200 and the shape fixing part 300 are assembled to the deployment part 400 , and the deployment part 400 is attached to the feeder part 100 . ) can also be assembled with

Thereafter, the developing part 400 can be erected to stand up the reflective part 200 and the shape fixing part 300, and the developing part 400 is fixed to the feeder part 100 to fix the reflecting part 200 and the shape fixing part ( 300) can be maintained in an upright state. 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.

After that, the satellite antenna is launched into the air. That is, the satellite antenna may be launched in a state in which the reflection unit 200 and the shape fixing unit 300 are erected to surround the periphery of the feeder unit 100 of the satellite antenna. At this time, by reducing the total weight of the artificial satellite by using the weight of the fiber assembly forming the reflective unit 200, it is possible to reduce the inertial resistance caused by the launch of the satellite antenna.

Thereafter, while the satellite antenna is launched into the air, the shape of the reflection unit 200 is maintained by using the shape fixing unit 300 of the satellite antenna. Specifically, a plurality of positions of the rear surface of the reflective unit 200 in the radial direction (R) and the circumferential direction (C) to follow the three-dimensional curved shape of the shape fixing unit 300 toward the shape fixing unit 300 is elastic can be pulled by

When the artificial satellite enters orbit and starts to operate, the shape fixing unit 300 is deployed while maintaining the shape of the reflection unit 200 and the reflection unit 200 is deployed. At this time, the deployment part 400 may be expanded outwardly from the feeder part 100 to expand the shape fixing part 300 , and the reflective part 200 may be deployed in the same manner as the shape fixing part 300 .

After the reflection unit 200 is deployed, the radio wave transmitted from the free space is reflected to the feeder unit 100 of the satellite antenna using the three-dimensional curved shape of the reflection unit 200 and transmitted from the feeder unit 100 . It reflects the radio waves to free space and performs the process of transmitting and receiving radio waves. In this case, radio waves may be transmitted/received using the transceiver 500 supported on the upper portion of the feeder unit 100 .

In addition, during transmission and reception of radio waves, in the radial direction (R) and the circumferential direction (C) at a plurality of positions of the reflection unit 200 to prevent deformation of the reflection unit 200 due to an external force applied to the reflection unit 200 . Perform the process of applying tension to each. Here, the external force applied to the reflector 200 may be an external force due to an acceleration applied to the reflector 200 or may include an external force caused by particles passing through outer space. That is, by using the shape fixing unit 300 while operating the satellite, pulling in the radial direction (R) and the circumferential direction (C) at a plurality of positions of the reflection unit 200, the reflection unit 200 in the radial direction (R) And by continuously applying tension in the circumferential direction (C), when acceleration is applied to the reflector 200 or when the reflector 200 collides with particles in outer space, the external force generated therefrom is reflected by the reflector 200 ) can be prevented from being deformed. Accordingly, it is possible to prevent the transmission/reception efficiency of radio waves from changing momentarily and irregularly, and 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
300: shape fixing part
310: membrane
320: string
400: development part
500: transceiver

Claims (15)

feeder unit;
a reflection unit having flexibility, disposed along the periphery of the feeder unit, and reflecting radio waves;
a shape fixing part disposed opposite the reflective part to fix the shape of the reflective part and connected to the reflective part;
Containing;
The reflective part is elastically connected to the shape fixing part at a plurality of positions on the rear surface of the reflective part in the radial and circumferential directions in order to be fixed in a three-dimensional curved shape, and tension is applied in the radial and circumferential directions. Device. delete The method according to claim 1,
The reflective unit is a satellite antenna device of a network structure comprising a fiber aggregate formed by entangled fibers in a network form by weaving. delete 4. The method according to any one of claims 1 to 3,
The reflective part has a first curvature in a circumferential direction and a second curvature different from the first curvature in a radial direction. feeder unit;
a reflection unit having flexibility, disposed along the periphery of the feeder unit, and reflecting radio waves;
a shape fixing part disposed opposite the reflective part and connected to the reflective part to fix the shape of the reflective part;
Including; a deployment part for expanding the shape fixing part around the feeder part
The shape fixing part,
a membrane having a three-dimensional curved shape and having bending rigidity and thickness capable of maintaining the three-dimensional curved shape by itself;
and a plurality of strings disposed along an area of the membrane in radial and circumferential directions between the membrane and the reflective part and connecting the reflective part to the membrane. 7. The method of claim 6,
The string is formed in a bar shape to prevent bending due to the acceleration applied to the reflective part, and the satellite antenna device of a network structure including a rigid material. 7. The method of claim 6,
The membrane is a satellite antenna device of a network structure comprising a fiber fabric formed in one or multiple layers. feeder unit;
a reflection unit having flexibility, disposed along the periphery of the feeder unit, and reflecting radio waves;
a shape fixing part disposed opposite the reflective part and connected to the reflective part to fix the shape of the reflective part;
Including; a deployment part for expanding the shape fixing part around the feeder part
The deployment part extends in the radial direction, is spaced apart in the circumferential direction, is disposed on both sides of the shape fixing part in the circumferential direction, and is rotatably connected to the feeder part,
The shape fixing part is an artificial satellite antenna device of a network structure in which both edges are supported by the deployment part, respectively. 10. The method of claim 9,
The satellite antenna device of the network structure having the same curvature as the shape fixing part in the radial direction of the deployment part. feeder unit;
a reflection unit having flexibility, disposed along the periphery of the feeder unit, and reflecting radio waves;
a shape fixing part disposed opposite the reflective part and connected to the reflective part to fix the shape of the reflective part;
Including; a deployment part for expanding the shape fixing part around the feeder part
The deployment portion includes a front flange relatively close to the feeder portion, a rear flange relatively far from the feeder portion, and a web connecting the front flange and the rear flange,
An edge of the reflective part is supported on the front flange,
A satellite antenna device of a network structure in which an edge of the shape fixing part is supported on the rear flange. providing a satellite antenna including a flexible reflector;
launching the satellite antenna into the air;
maintaining the shape of the reflective part using a shape fixing part of the satellite antenna while the satellite antenna is launched into the air;
While maintaining the shape of the reflective part, the process of developing the shape fixing part and developing the reflective part;
The process of launching the satellite antenna into the air,
The process of emitting the satellite antenna in a state in which the reflection part and the shape fixing part are erected so as to surround the periphery of the feeder part of the satellite antenna;
The process of maintaining the shape of the reflective part,
The process of elastically pulling a plurality of positions of the rear surface of the reflective part in the radial and circumferential directions to follow the three-dimensional curved shape of the shape fixing part toward the shape fixing part; delete 13. The method of claim 12,
The process of preparing the satellite antenna,
The process of preparing a fiber aggregate formed by entangled fibers in a network form by weaving as the reflection unit;
The process of launching the satellite antenna into the air,
The process of reducing inertial resistance due to the launch of the satellite antenna by using the weight of the fiber assembly; 13. The method of claim 12,
After the process of developing the reflector,
a process of reflecting radio waves transmitted from free space to a feeder unit of the satellite antenna using the three-dimensional curved shape of the reflection unit, reflecting radio waves transmitted from the feeder unit into the free space, and transmitting/receiving radio waves;
The process of applying tension in a radial direction and a circumferential direction at a plurality of positions of the reflection unit to prevent deformation of the reflection unit due to an external force applied to the reflection unit while transmitting and receiving the radio wave; Way.

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