KR102321447B1 - Apparatus for testing deployment antenna and method for testing deployment antenna - Google Patents

Abstract

The present invention relates to an antenna deployment test apparatus and an antenna deployment test method. According to the present invention, the antenna deployment test apparatus comprises: a base; a feeder disposed on the base; a plurality of reflective panels rotatably coupled to the base; a support part installed on the plurality of reflective panels to constrain the plurality of reflective panels toward the feeder; and a control part installed on the plurality of reflective panels to adjust the deployment speed of the plurality of reflective panels deployed by their own weight when the support part is released.

Description

Antenna deployment test apparatus and antenna deployment test method {Apparatus for testing deployment antenna and method for testing deployment antenna}

The present invention relates to an antenna deployment test apparatus and an antenna deployment test method, and more particularly, to an antenna deployment test apparatus and an antenna deployment test method capable of reducing the deployment speed of a deployed reflective panel.

In general, an antenna is a wireless communication device for transmitting radio waves to the outside or receiving radio waves from the outside. In the case of a large antenna, a dish-shaped reflective panel having a curved surface is provided in order to stably receive an external radio wave.

The antenna mounted on the satellite is an important part directly connected to the stable operation of the satellite. Therefore, it is necessary to verify the reliability of the antenna by performing various tests on the ground before the antenna is mounted on the artificial satellite.

For example, the deployment operation of the reflective panel may be tested by deploying the reflective panel of the antenna on the ground. That is, the operation of verifying the reliability of the antenna may be performed. On the other hand, when testing the deployment operation of the reflective panel, there is a problem that the deployed reflective panel is accelerated by its own weight and deviates from a preset stop position. In addition, there is a problem in that the reflective panel is accelerated by its own weight, a load is applied to the deployment device supporting the reflective panel, and a malfunction occurs.

US 10-1759620 B

The present invention provides an antenna deployment test apparatus and an antenna deployment test method capable of supporting a plurality of reflective panels deployed.

The present invention provides an antenna deployment test apparatus and an antenna deployment test method capable of adjusting the deployment speed of a plurality of reflective panels to be deployed.

The present invention is a base; a feeder disposed on the base; a plurality of reflective panels rotatably coupled to the base; a support part installed on the plurality of reflective panels to constrain the plurality of reflective panels toward the feeder; and a control unit installed on the plurality of reflective panels to adjust the deployment speed of the plurality of reflective panels deployed by their own weight when the support part is released.

At least a portion of the adjusting unit is formed to be stretchable and contractible so as to move along an imaginary line surrounding the plurality of reflective panels.

The adjustment unit includes a plurality of first adjustment plates, at least a portion of which overlaps each other and has a curvature along the imaginary line.

The plurality of first adjustment plates are rotatably coupled to the plurality of reflection panels to match the plurality of reflection panels one-to-one, and one first adjustment plate and the other first adjustment plate are supported so as to be stretchable and contractible. .

The length of the virtual line is changed according to the extent to which the plurality of reflective panels are deployed, and the plurality of first adjustment plates are formed to adjust overlapping lengths according to the changed length of the virtual line.

The adjusting unit may include a second adjusting plate provided between the plurality of first adjusting plates, having a curvature along the virtual line, and movably coupled to the first adjusting plate.

The first adjustment plate and the second adjustment plate may include a guide slit extending along the virtual line; a guide protrusion protruding outward; and an elastic member disposed in the guide slit and capable of stretching and contracting, wherein the guide protrusion of one first adjustment plate is inserted into the guide slit of the other first adjustment plate or the guide slit of the second adjustment plate.

The first adjustment plate, to be coupled to the connection link of the plurality of reflective panels, coupling pins protruding from both sides intersecting the virtual line; further includes.

The first adjustment plate and the second adjustment plate may include a separation preventing member protruding from a side surface of the guide projection; and a groove recessed in the inner wall of the guide slit, wherein the separation preventing member of one first adjustment plate is inserted into the groove of the other first adjustment plate or the groove of the second adjustment plate.

The support part is installed at at least 2/3 of the long axis length of the plurality of reflective panels with respect to the base, and the adjustment part is disposed between the support part and the base.

The present invention is a process of providing a satellite antenna having a plurality of reflective panels; releasing the support portion constraining the plurality of reflective panels to deploy the plurality of reflective panels; and supporting the plurality of reflective panels deployed by their own weight while deploying the plurality of reflective panels, and reducing a deployment speed of the plurality of reflective panels.

The process of reducing the deployment speed of the plurality of reflective panels includes sliding the control unit in contact with the plurality of reflective panels, and applying a force in a direction opposite to the deployment direction of the plurality of reflective panels.

The process of applying the force in a direction opposite to the unfolding direction of the plurality of reflective panels includes a process of generating a tensile force by contracting at least a portion of the adjusting unit to each other.

In the process of reducing the deployment speed of the plurality of reflective panels, the plurality of reflective panels are deployed at a speed slower than the rotation speed due to their own weight.

According to the embodiment of the present invention, before the antenna is mounted on an artificial satellite and launched into the air, the antenna deployment test in which the reflective panel of the antenna is deployed on the ground and the deployment operation of the reflective panel is tested can be performed. In addition, it is possible to stably support the reflective panel while the reflective panel is deployed.

In addition, it is possible to reduce the deployment speed of the reflective panel. Accordingly, the reflective panel can be more easily stopped at a preset position, and the deployment operation of the reflective panel can be precisely performed.

1 is a perspective view of an antenna deployment test apparatus according to an embodiment of the present invention.
Figure 2 is a perspective view of a state in which the reflective panel of the antenna deployment test apparatus according to an embodiment of the present invention is deployed.
Figure 3 is a view showing the structure of the first adjustment plate.
4 is a view showing a state in which a plurality of first adjustment plates are coupled.
5 is a perspective view of an antenna deployment test apparatus according to another embodiment of the present invention.
6 is a perspective view of a state in which the reflective panel of the antenna deployment test apparatus according to another embodiment is deployed.
7 is a view showing a state in which a plurality of first control plate and the second control plate are coupled.
8 is a flowchart illustrating an antenna deployment test method according to embodiments of the present invention.

Hereinafter, embodiments of the present invention will be described in more detail with reference to the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below, but will be implemented in a variety of different forms, and only these embodiments allow the disclosure of the present invention to be complete, and the scope of the invention to those of ordinary skill in the art completely It is provided to inform you. In order to explain the invention in detail, the drawings may be exaggerated, and like numerals refer to like elements in the drawings.

The antenna deployment testing apparatus according to an embodiment of the present invention may be a device capable of testing whether the reflective panel of the antenna is deployed on the ground and the deployment operation of the reflective panel is smoothly performed.

Of course, the antenna deployment test apparatus and method according to an embodiment of the present invention can be used in various ways as a deployment test device for testing whether the deployment operation is smoothly performed by deploying various structures having a folded portion.

Hereinafter, an embodiment of the present invention will be described in detail with reference to an apparatus for testing the deployment operation of the reflective panel of the antenna.

1 is a perspective view of an antenna deployment test apparatus according to an embodiment of the present invention, and FIG. 2 is a perspective view of a state in which a reflective panel of the antenna deployment test apparatus according to an embodiment of the present invention is deployed.

1 and 2, the structure of the antenna deployment test apparatus 100 according to an embodiment of the present invention will be described. Antenna deployment test apparatus 100 according to an embodiment of the present invention includes a base 110, a feeder 120 disposed on the base 110, and a plurality of reflective panels rotatably coupled to the base 110 ( 130), the support 150 installed on the plurality of reflective panels 130 to constrain the plurality of reflective panels 130 toward the feeder 120, and the plurality of reflective panels deployed by their own weight when the support 150 is released The control unit 160 installed on the plurality of reflective panels 130 may be included to adjust the deployment speed of the 130 . In addition, the antenna deployment test apparatus 100 may include a strut 140 .

The base 110 may support the plurality of reflective panels 130 and the struts 140 . A lower portion of the base 110 may be mounted on the main body of the artificial satellite, and an upper portion may support a plurality of reflective panels 130 and struts 140 . The base 110 may be provided in a shape corresponding to the arrangement structure of the plurality of reflective panels 130 . For example, the base 110 may be provided as a ring-shaped plate to correspond to the structure of the plurality of reflective panels 130 that are arranged radially. That is, the base 110 may be provided as a hollow circular plate extending along the circumferential direction. Here, the circumferential direction may be a circumferential direction of a circle having an up-down direction as a central axis. In addition, the vertical direction may be a direction in which the feeder 120 and the strut 140 are arranged.

In addition, the base 110 may include a deployment member 111 capable of deploying the plurality of reflective panels 130 . The deployment member 111 may be provided in plurality, and may be spaced apart from the base 110 in the circumferential direction. The plurality of deployment members 111 may be matched one-to-one with the plurality of reflective panels 130 , respectively. That is, one deployment member 111 may be connected to the lower portion of one reflective panel 130 , and rotate so that the plurality of reflective panels 130 are disposed along the radial direction to expand the plurality of reflective panels 130 . can be (see FIG. 2). Here, the radial direction may be directions perpendicular to the central axis with the vertical direction as the central axis. Accordingly, the base 110 may elastically support the plurality of reflective panels 130 through the deployment member 111 . For example, the deployment member 111 may include various parts such as a link, a roller, a beam, a shaft, a spring, a gear, and the coupling structure of these parts may be varied.

Referring to FIG. 2 , the feeder 120 may be supported by an upper structure 145 of a strut 140 to be described later. The feeder 120 may include a reflector 121 and a feed horn 122 . Here, the reflector 121 may be a main reflector. The reflecting plate 121 may be formed to extend in a horizontal direction and may have a circular plate shape with a concave center, and a shape of a vertical cross-section thereof may be a predetermined parabolic shape.

The horizontal width of the reflector 121 may be smaller than the horizontal width of the upper reinforcement 144 to be described later. Accordingly, the reflective plate 121 may be supported by the upper structure 145 above the center of the upper reinforcement 144 .

In addition, the feed horn 122 may be supported at the center of the reflection plate 121 . The reflective plate 121 may focus the propagation signals reflected from the plurality of reflective panels 130 to be described later to the feed horn 122 . And the feed horn 122 may receive the radio signal and transmit it to the outside.

The reflective panel 130 may be a shell-shaped foldable reflective panel 130 . A plurality of reflective panels 130 may be provided, and may be spaced apart from the base 110 in a circumferential direction. That is, the plurality of reflective panels 130 may be supported on the base 110 and may be arranged in a radial shape along the circumference of the base 110 .

More specifically, the lower portion of the plurality of reflective panels 130 may be rotatably coupled to the deployment member 111 of the base 110 . The plurality of reflective panels 130 may surround the outside of the strut 140 by standing at a predetermined angle close to or perpendicular to the base 110 in the folded state. For example, when the plurality of reflective panels 130 are in an upright state, a cylinder or a predetermined shape close to a cylinder may be formed (refer to FIG. 1 ).

In addition, the plurality of reflective panels 130 are gently laid down while drawing a predetermined parabola from the center of the base 110 toward the edge in a radially unfolded state, so that, for example, a shape similar to a parabolic antenna reflector can be achieved (Fig. see 2). Here, the movement of the plurality of reflective panels 130 to be in a state in which the plurality of reflective panels 130 are gently laid down while being unfolded is referred to as the unfolding of the plurality of reflective panels 130 . Meanwhile, the reflective panel 130 may be a sub-reflective panel that is distinguished from the main reflective panel that is the aforementioned reflective plate 121 .

In addition, the plurality of reflective panels 130 may include connecting links 131 protruding from side surfaces. The connection links 131 are provided as a pair, and may be vertically spaced apart from each other on the side surfaces of the plurality of reflective panels 130 . In addition, a hole penetrating the inside may be provided in the connection link 131 . The first adjustment plate 161 of the adjustment unit 160 may be rotatably coupled to the hole of the connection link 131 .

The strut 140 may be supported on the base 110 inside the plurality of reflective panels 130 . The strut 140 serves to position the feeder 120 at a focal position of radio waves formed by the reflective panel 130 when the plurality of reflective panels 130 are deployed.

The strut 140 may extend in the vertical direction. The strut 140 may include a lower structure 141 , an intermediate reinforcing body 142 , an intermediate structure 143 , an upper reinforcing body 144 , and an upper structure 145 . The lower structure 141, the intermediate structure 143, and the upper structure 145 may be, for example, a truss structure. The intermediate reinforcement 142 may have, for example, a square ring structure, and the upper reinforcement 144 may have, for example, a circular ring structure. A horizontal width of the intermediate reinforcing body 142 may be greater than a horizontal width of the upper reinforcing body 144 . The lower structure 141 , the intermediate reinforcement 142 , the intermediate structure 143 , the upper reinforcement 144 , and the upper structure 145 may be mounted on the upper portion of the base 110 in this order.

The support 150 may maintain the folded state of the plurality of reflective panels 130 . That is, the support unit 150 binds the plurality of reflective panels 130 standing up (ie, in a folded state) by the deployment member 111 , thereby maintaining the folded state of the plurality of reflective panels 130 . That is, it is possible to prevent the reflective panel 130 from being developed due to its own weight by the support 150 . The support part 150 may be installed on the plurality of reflective panels 130 to bind the plurality of reflective panels 130 . Accordingly, the plurality of reflective panels 130 may be gathered by the support 150 so that the folded state of the plurality of reflective panels 130 is maintained.

In addition, the support 150 may be installed at a position of 2/3 or more of the major axis length of the plurality of reflective panels 130 with respect to the base 110 . That is, when the plurality of reflective panels 130 are in a folded state, the support unit 150 may be installed at a height of 2/3 or more from the lower ends of the plurality of reflective panels 130 in the vertical direction. Accordingly, the support part 150 may effectively support the plurality of reflective panels 130 to prevent the plurality of reflective panels 130 from being developed by their own weight.

Also, the adjustment unit 160 may be disposed between the support unit 150 and the base 110 . That is, the adjustment unit 160 may be disposed between the base 110 and the support unit 150 in the vertical direction. For example, the adjusting unit 160 may be installed at a height of less than 2/3 to more than 1/2 from the lower ends of the plurality of reflective panels 130 in the vertical direction.

Meanwhile, the support 150 may be released from the plurality of reflective panels 130 . For example, at least a portion of the support 150 may be cut and released from the plurality of reflective panels 130 . To this end, the support 150 may include a cutting member 151 . The cutting member 151 is installed on the support part 150 and can cut the support part 150 . For example, the cutting member 151 may be provided by a pyrobolt cutting method, a hot wire cutting method, or the like. On the other hand, the support 150 may be peeled off from the plurality of reflective panels 130 .

FIG. 3 is a view showing the structure of the first adjusting plate, and FIG. 4 is a view showing a state in which a plurality of first adjusting plates are combined.

1 to 4 , the adjusting unit 160 may adjust the deployment speed of the plurality of reflective panels 130 deployed by their own weight when the support unit 150 is released. That is, the control unit 160 may generate a force in a direction opposite to the deployment direction in which the plurality of reflective panels 130 are deployed, thereby reducing the speed at which the plurality of reflective panels 130 are deployed. The control unit 160 is coupled to the plurality of reflective panels 130 and may extend along an imaginary line surrounding the plurality of reflective panels 130 . Here, the imaginary line may be an imaginary line surrounding the outside of the reflective panel 130 (indicated by a dotted line in FIG. 1 ). More specifically, the virtual line is a line connecting points spaced apart from the end of each reflective panel 130 by a predetermined distance, and may be, for example, a circular line. That is, the reflective panel 130 may be an imaginary line connecting points spaced the same distance from the outer edge (ie, the exposed edge) of the reflective panel 130 at the same height. Here, the length of the virtual line may be changed according to the shape (ie, arrangement) of the folded or unfolded reflective panel 130 . Also, the adjusting unit 160 may include a plurality of first adjusting plates 161 .

The plurality of first adjustment plates 161 may be rotatably coupled to the plurality of reflective panels 130 , support the deployed reflective panel 130 , and reduce the deployment speed of the reflective panel 130 . The plurality of first control plates 161 may be rotatably coupled to one-to-one matching to the plurality of reflective panels 130 , and at least some of them may be disposed to overlap each other. In addition, the first adjustment plate 161 may have a curvature along an imaginary line that is changed in response to the shape of the developed reflective panel 130 , and may be formed to be movable along the imaginary line. That is, the plurality of first adjustment plates 161 may be disposed to surround the circumference of the plurality of reflective panels 130 . For example, the plurality of first adjustment plates 161 may be formed in a circular arc or an elliptical arc extending along the curved surface of the reflective panel 130 .

In addition, at least a portion of the plurality of first adjustment plates 161 may be formed to be stretchable and contractible, and one adjacent first adjustment plate 161 and the other first adjustment plate 161 may be supported so as to be stretchable and contractible with each other. . That is, in the process of sliding the plurality of first adjustment plates 161 , one first adjustment plate 161 and the other first adjustment plate 161 may be supported so as to be stretchable and contractible. Accordingly, the plurality of first adjustment plates 161 may slide along the virtual line in association with the operation in which the plurality of reflective panels 130 are deployed. That is, in response to the length of the virtual line that is changed (that is, changed) depending on the degree to which the plurality of reflective panels 130 are deployed, the plurality of first adjustment plates 161 slide to each other and the plurality of first adjustment plates ( 161) can be increased. That is, the length of the overlapping portion of the plurality of first control plates 161 may decrease and the overall length may increase. At this time, the plurality of first control plates 161 supported so as to be stretchable and contractible with each other support the plurality of reflective panels 130 to be deployed and apply a force in the opposite direction to the deployment direction to reduce the deployment speed.

Hereinafter, the structure of the first adjustment plate 161 will be described in more detail with reference to FIG. 3 . In describing the structure of the first adjustment plate 161, as shown in FIG. 3(b), it is assumed that the first adjustment plate 161 is horizontally arranged. However, since the first adjustment plate 161 may be disposed to surround the plurality of reflective panels 130 along the virtual line, the arrangement direction thereof may be changed.

The first adjustment plate 161 extends along an imaginary line (hereinafter, referred to as an extension direction), has a predetermined width (ie, width and length), and has a plate-shaped structure having a predetermined thickness (ie, height and length) can be In the following, while explaining the structure of the first adjustment plate 161, the direction based on the width of the first adjustment plate 161 is referred to as the width direction, and the direction based on the thickness of the first adjustment plate 161 is referred to as the width direction. It is called the thickness direction. The first adjustment plate 161 may be provided in a shape in which the center is curved upward so that the height of the center is higher than the height of both ends based on the thickness direction. For example, the first adjustment plate 161 may be provided in a convex shape at the center. In addition, the first adjustment plate 161 may be provided in a bent shape in the center so that the center protrudes from both ends in the extending direction. That is, the first adjustment plate 161 may be provided in the shape of a plate having a curvature with respect to the thickness direction and the extension direction, respectively. In addition, the first adjustment plate 161 may include a coupling pin 161a, a guide slit 161b, a guide protrusion 161c, an elastic member 161d, a separation preventing member 161e, and a groove 161f. .

The coupling pins 161a may be formed to protrude from both side surfaces (ie, side surfaces located in the width direction) of the first adjustment plate 161 . The coupling pin 161a is provided in a cylindrical shape, and may be rotatably coupled to the connection link 131 of the plurality of reflective panels 130 .

The guide slit 161b may be a slit penetrating through the first adjustment plate 161 in the thickness direction and extending in the extension direction. The length of the guide slit 161b in the extension direction may be shorter than the length of the first adjustment plate 161 in the extension direction.

The guide protrusion 161c may be a protrusion protruding to the outside of the first adjustment plate 161 . For example, the guide protrusion 161c may be provided in a rectangular parallelepiped shape having a length in the thickness direction. Here, the width direction length of the guide protrusion 161c may be equal to or slightly shorter than the width direction length of the guide slit 161b.

The elastic member 161d is disposed in the guide slit 161b, and may be formed so as to be stretchable and contractible along the extension direction. For example, the elastic member 161d provided on the first adjustment plate 161 has one end on the protrusion 161g protruding from the inner wall of the guide slit 161b of the first adjustment plate 161 in the extension direction. can be fixed. In addition, the other end of the elastic member 161d provided on the first adjustment plate 161 may be supported by the guide protrusion 161c of the other first adjustment plate 161 . Here, the length in the extension direction of the elastic member 161d may be shorter than the length in the extension direction of the guide slit 161b. For example, the elastic member 161d may include a spring.

The separation preventing member 161e may protrude from both side surfaces located in the width direction among the side surfaces of the guide protrusion 161c. For example, the guide protrusion 161c may be provided in a cube shape.

The groove 161f may be formed by being depressed in the inner walls of the guide slit 161b located in the width direction. The groove 161f may extend along the extension direction. Here, the thickness direction length of the recessed groove 161f in the inner wall may be formed to be longer than the thickness direction length of the guide protrusion 161c.

Hereinafter, a structure in which the plurality of first adjustment plates 161 are coupled to each other will be described with reference to FIG. 4 . A first adjustment plate 161 disposed on the left side in the drawing among the plurality of first control plates 161 shown in FIG. 4 is referred to as a first control plate 161, and the first control plate disposed on the right side in the drawing (161) is referred to as the other first control plate (161).

Referring to FIG. 4A , the plurality of reflective panels 130 may be in a folded state. In addition, the first adjustment plate 161 and the other first adjustment plate 161 may be rotatably coupled to the connection link 131 of the reflective panel 130 , respectively. In addition, the guide protrusion 161c of the first adjustment plate 161 is inserted into the guide slit 161b of the other first adjustment plate 161, and is inserted into the elastic member 161d of the other first adjustment plate 161. It may be in a state supported so as to be stretchable and contractible. In addition, the separation preventing member 161e of the first adjustment plate 161 may be in a state of being inserted into the groove 161f of the other first adjustment plate 161 . Here, when the plurality of reflective panels 130 are in the folded state, the overlapping length of one first adjustment plate 161 and the other first adjustment plate 161 is in the state in which the plurality of reflective panels 130 are unfolded. It may be longer than the overlapping length of the first adjustment plate 161 and the other first adjustment plate 161 at the time.

Referring to FIG. 4B , the plurality of reflective panels 130 may be in a deployed state. Here, the guide protrusion 161c of the first adjustment plate 161 may move along the extension direction while being inserted into the guide slit 161b of the other first adjustment plate 161 . At this time, the elastic member 161d of the other first adjustment plate 161 may be compressed and contracted by the guide protrusion 161c of the first adjustment plate 161 . Accordingly, one first adjustment plate 161 and the other first adjustment plate 161 may generate a tensile force.

On the other hand, while the guide protrusion 161c of the first adjustment plate 161 moves in the extending direction, the separation preventing member 161e of the first adjustment plate 161 moves into the groove of the other first adjustment plate 161 ( 161f) in the extension direction. Since the separation preventing member 161e of the first adjustment plate 161 is inserted into the groove 161f and supported by the other first adjustment plate 161, the first adjustment plate 161 and the other first adjustment plate ( 161) may not be separated from each other.

5 is a diagram showing the structure of an antenna deployment test apparatus according to another embodiment of the present invention, and FIG. 6 is a perspective view of a state in which a reflective panel of the antenna deployment test apparatus according to another embodiment is deployed. Hereinafter, another embodiment of the present invention will be described. In this case, in describing another embodiment of the present invention, the same reference numerals are used for the same structure as the embodiment of the present invention, and the description of the same structure will be omitted.

The adjustment unit 160 is provided between the plurality of first adjustment plates 161, has a curvature along an imaginary line, and includes a second adjustment plate 162 that is movably coupled to the first adjustment plate 161. may include The second adjustment plate 162 may have the same structure and shape as the first adjustment plate 161 , but may have a structure and shape in which the coupling pin 161a is not provided. The second adjustment plate 162 is provided in plurality, and each second adjustment plate 162 may be coupled to one first adjustment plate 161 and the other first adjustment plate 161 , respectively.

7 is a view illustrating a state in which a plurality of first and second adjustment plates are combined. Hereinafter, a structure in which the plurality of first adjustment plates 161 and the second adjustment plates 162 are coupled to each other will be described with reference to FIG. 7 . A first adjustment plate 161 disposed on the left side in the drawing among the plurality of first control plates 161 shown in FIG. 7 is referred to as a first control plate 161, and the first control plate disposed on the right side in the drawing (161) is referred to as the other first control plate (161). That is, the adjustment unit 160 of the antenna deployment test apparatus according to another embodiment may have a structure in which the second adjustment plate 162 is disposed between the first adjustment plates 161 .

Referring to FIG. 7A , the plurality of reflective panels 130 may be in a folded state. Here, the guide protrusion 161c of the first adjustment plate 161 may be inserted into the guide slit 162b of the second adjustment plate 162 . In addition, the guide protrusion 162c of the second adjustment plate 162 may be inserted into the guide slit 161b of the other first adjustment plate 161 . In addition, the separation preventing member 161e of the first adjustment plate 161 may be inserted into the groove 162f of the second adjustment plate 162 . In addition, the separation preventing member 162e of the second adjustment plate 162 may be inserted into the groove 161f of the other first adjustment plate 161 .

Referring to FIG. 7B , the plurality of reflective panels 130 may be in a deployed state. Here, the guide protrusion 161c of the first adjustment plate 161 may move along the extension direction while being inserted into the guide slit 162b of the second adjustment plate 162 . At this time, the elastic member 162d of the second adjustment plate 162 may be compressed and contracted by the guide protrusion 161c of the first adjustment plate 161 . In addition, the guide protrusion 161c of the second adjustment plate 162 may move along the extension direction while being inserted into the guide slit 161b of the other first adjustment plate 161 . At this time, the elastic member 161d of the other first adjustment plate 161 may be compressed and contracted by the guide protrusion 162c of the second adjustment plate 162 . Accordingly, one first adjusting plate 161 , the second adjusting plate 162 , and the other first adjusting plate 161 may generate a stronger tensile force. Accordingly, when the plurality of reflective panels 130 are deployed, the deployment speed of the plurality of reflective panels 130 may be more effectively reduced.

The structure and shape of the components of the antenna deployment test apparatus 100 described above are not limited thereto, and may vary.

On the other hand, the process of reducing the deployment speed of the plurality of reflective panels deployed using the antenna deployment test apparatus 100 according to an embodiment of the present invention will be described while explaining the antenna deployment test method.

8 is a flowchart illustrating an antenna deployment test method according to embodiments of the present invention.

1 to 7 , in the process of preparing the satellite antenna 100 having a plurality of reflective panels 130 ( S110 ), the plurality of reflective panels 130 are released by releasing the support unit 150 . During the process (S120) of deploying the reflective panel 130 of It may include the process of reducing (S130).

First, the antenna deployment test apparatus 100 having the support part 150 and the adjustment part 160 constraining the plurality of reflective panels 130 may be prepared (S110). More specifically, in the antenna deployment test apparatus 100 , the plurality of reflective panels 130 may be in a folded state, and may be in a state of being perpendicular to or standing at a predetermined angle close to the vertical with respect to the base 110 . In addition, the support 150 may bind and restrain the plurality of reflective panels 130 so that the plurality of reflective panels 130 can be maintained in a folded state. That is, the plurality of reflective panels 130 may be maintained in a standing state by pressing the plurality of reflective panels 130 in a direction toward the feeder 120 around the periphery of the plurality of reflective panels 130 .

On the other hand, when the plurality of reflective panels 130 are in a folded state, the plurality of first adjustment plates 161 of the adjustment unit 160 overlap with a relatively long overlapping length, as shown in FIG. 4( a ). may have been That is, the plurality of first control plates 161 may overlap each other longer than the overlapped length when deployed. Among the plurality of first adjustment plates 161, the guide protrusion 161c of one first adjustment plate 161 located on the left side in the drawing is located on the guide slit 161b of the other first adjustment plate 161 located on the right side in the drawing. It may be in a state supported by the elastic member 161d of the other first adjustment plate 161 .

Thereafter, the support unit 150 constraining the plurality of reflective panels 130 may be released to deploy the plurality of reflective panels 130 ( S120 ). That is, the plurality of reflective panels 130 may be deployed by releasing the support portion 150 tied along the circumference of the plurality of reflective panels 130 and driving the deployment member 111 . In this case, the plurality of reflective panels 130 may be in a state in which they are gently laid down while being unfolded by their own weight and driving of the deployment member 111 . On the other hand, by cutting at least a portion of the support part 150 , the restraints of the plurality of reflective panels 130 may be released, and the plurality of reflective panels 130 may be deployed by driving the deployment member 111 . Hereinafter, a case in which the restraints of the plurality of reflective panels 130 are released by cutting at least a portion of the support part 150 will be exemplarily described.

Meanwhile, while the plurality of reflective panels 130 are deployed, the deployment speed of the plurality of reflective panels 130 may be reduced while supporting the plurality of reflective panels 130 deployed by their own weight. Referring to FIG. 4( b ), the guide protrusion 161c of the first adjustment plate 161 among the plurality of first adjustment plates 161 is inserted into the guide slit 161b of the other first adjustment plate 161 . In this state, it can move along the extension direction. At this time, the elastic member 161d of the other first adjustment plate 161 may be compressed and contracted by the guide protrusion 161c of the first adjustment plate 161 . Accordingly, one first adjustment plate 161 and the other first adjustment plate 161 may generate a tensile force. That is, the elastic member 161d of the first adjustment plate 161 is contracted, and a tensile force generated may apply a force in a direction opposite to the unfolding direction of the plurality of reflective panels 130 . Accordingly, by deploying the plurality of reflective panels 130 at a speed slower than the speed at which the plurality of reflective panels 130 rotate due to their own weight, the unfolding operation of the plurality of reflective panels 130 may be precisely performed.

On the other hand, while the guide protrusion 161c of the first adjustment plate 161 moves in the extending direction, the separation preventing member 161e of the first adjustment plate 161 moves into the groove of the other first adjustment plate 161 ( 161f) in the extension direction. Since the separation prevention member 161e of the first adjustment plate 161 is inserted into the groove 161f of the other first adjustment plate 161, the first adjustment plate 161 and the other first adjustment plate 161 ) may not be separated.

Next, a process in which the control unit 160 supports the plurality of reflective panels 130 in the antenna deployment test apparatus according to another embodiment will be described.

Referring to FIG. 7A , when the plurality of reflective panels 130 are folded, one first control plate 161 , a second control plate 162 , and another first control plate 161 located on the left side of the drawing ) can be sequentially combined. That is, the guide protrusion 161c of the first adjusting plate 161 is inserted into the guide slit 162b of the second adjusting plate 162, and the guide protrusion 162c of the second adjusting plate 162 is formed by another product. 1 It is inserted into the guide slit (161b) of the adjustment plate (161) can be maintained in a state coupled to each other. In this case, the first adjustment plate 161 , the second adjustment plate 162 , and the other first adjustment plate 161 may overlap each other with a relatively long overlapping length. That is, the plurality of first control plates 161 may overlap each other longer than the overlapped length when deployed.

Referring to FIG. 7B , the support 150 may be released and the plurality of reflective panels 130 may be in a deployed state. Here, the guide protrusion 161c of the first adjustment plate 161 may move along the extension direction while being inserted into the guide slit 162b of the second adjustment plate 162 . At this time, the elastic member 162d of the second adjustment plate 162 may be compressed and contracted by the guide protrusion 161c of the first adjustment plate 161 . Accordingly, the first adjustment plate 161 and the second adjustment plate 162 may generate a tensile force. That is, the elastic member 161d of the first adjustment plate 161 is contracted, and a tensile force generated may apply a force in a direction opposite to the unfolding direction of the plurality of reflective panels 130 . In addition, the elastic member 161d of the other first adjustment plate 161 may be compressed and contracted by the guide protrusion 162c of the second adjustment plate 162 . Accordingly, the second adjustment plate 162 and the other first adjustment plate 161 may generate a tensile force, and the generated tensile force may apply a force in a direction opposite to the unfolding direction of the plurality of reflective panels 130 . Accordingly, when the plurality of reflective panels 130 are deployed, the deployment speed of the plurality of reflective panels 130 may be more effectively reduced.

In this way, before the antenna is mounted on the artificial satellite and launched into the air, the antenna deployment test can be performed by deploying the reflective panel of the antenna on the ground and testing the deployment operation of the reflective panel of the antenna. In addition, it is possible to stably support the reflective panel while the reflective panel is deployed. In addition, gravity acting on the reflective panel can be canceled, it is possible to suppress or prevent the reflective panel from being deformed by its own weight due to the earth's gravity, and it is possible to precisely perform the deployment operation of the reflective panel.

As such, although specific embodiments have been described in the detailed description of the present invention, various modifications are possible without departing from the scope of the present invention, and various combinations between the embodiments are possible. Therefore, the scope of the present invention should not be limited to the described embodiments, but should be defined by the claims to be described below as well as the claims and equivalents.

100: antenna deployment test device 110: base
120: feeder 130: reflective panel
140: strut 150: support
160: control unit

Claims (14)

Base;
a feeder disposed on the base;
a plurality of reflective panels rotatably coupled to the base;
a support part installed on the plurality of reflective panels to constrain the plurality of reflective panels toward the feeder; and
a control unit installed on the plurality of reflective panels to adjust the deployment speed of the plurality of reflective panels deployed by their own weight when the support part is released;
The control unit, at least a portion of the antenna deployment test apparatus is formed to be stretchable and contractible so as to move along a virtual line surrounding the plurality of reflective panels. delete The method according to claim 1,
The control unit, at least a portion overlapping each other, a plurality of first control plate having a curvature along the virtual line; Antenna deployment test apparatus comprising a. 4. The method according to claim 3,
The plurality of first adjustment plates are rotatably coupled to the plurality of reflective panels to match the plurality of reflective panels one-to-one,
One first adjustment plate and the other first adjustment plate, the antenna deployment test apparatus supported so as to be stretchable and contractible. 4. The method according to claim 3,
The length of the virtual line is changed according to the degree to which the plurality of reflective panels are deployed,
A plurality of the first adjustment plate, the antenna deployment test apparatus is formed to adjust the overlapping length according to the changed length of the virtual line. 6. The method according to any one of claims 3 to 5,
The control unit, provided between the plurality of first control plates, having a curvature along the imaginary line, a second control plate movably coupled to the first control plate; Antenna deployment test apparatus further comprising . 7. The method of claim 6,
The first adjustment plate and the second adjustment plate,
a guide slit extending along the virtual line;
a guide protrusion protruding outward; and
It is disposed on the guide slit, the elastic member that can be stretched and contracted; includes,
Antenna deployment test apparatus in which the guide projection of the first adjustment plate is inserted into the guide slit of the other first adjustment plate or the guide slit of the second adjustment plate. 8. The method of claim 7,
The first adjustment plate is coupled to the connection link of the plurality of reflective panels, coupling pins projecting from both sides intersecting the virtual line; Antenna deployment test apparatus further comprising a. 8. The method of claim 7,
The first adjustment plate and the second adjustment plate may include a separation preventing member protruding from a side surface of the guide projection; and a groove recessed in the inner wall of the guide slit;
Antenna deployment testing apparatus in which the separation preventing member of the first adjustment plate is inserted into the groove of the other first adjustment plate or the groove of the second adjustment plate. Base;
a feeder disposed on the base;
a plurality of reflective panels rotatably coupled to the base;
a support part installed on the plurality of reflective panels to constrain the plurality of reflective panels toward the feeder; and
a control unit installed on the plurality of reflective panels to adjust the deployment speed of the plurality of reflective panels deployed by their own weight when the support part is released;
The support part is installed at a point of 2/3 or more of the long axis length of the plurality of reflective panels with respect to the base,
The control unit, the antenna deployment test device disposed between the support and the base. providing a satellite antenna having a plurality of reflective panels;
releasing the support portion constraining the plurality of reflective panels to deploy the plurality of reflective panels; and
a process of supporting the plurality of reflective panels deployed by their own weight while deploying the plurality of reflective panels, and reducing the deployment speed of the plurality of reflective panels;
The process of reducing the deployment speed of the plurality of reflective panels comprises:
Antenna deployment test method comprising the step of sliding the control unit in contact with the plurality of reflective panels, and applying a force in a direction opposite to the deployment direction of the plurality of reflective panels. delete 12. The method of claim 11,
The process of applying a force in a direction opposite to the unfolding direction of the plurality of reflective panels,
Antenna deployment test method comprising a; at least a portion of the adjusting unit is contracted with each other to generate a tensile force. 12. The method of claim 11,
The process of reducing the deployment speed of the plurality of reflective panels comprises:
An antenna deployment test method in which the plurality of reflective panels are deployed at a speed slower than the rotation speed due to their own weight.

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