JP6390949B2 - Deployable mesh antenna - Google Patents

Description

The present invention is, for example, a deployable mesh antenna having a deformable conductive mesh formed by braiding a metal wire or the like as a reflecting mirror surface among parabolic antennas mounted on an artificial satellite or the like. The present invention relates to a deployable mesh antenna that can be provided with any irregularities on the reflective surface of a conductive mesh, which is usually a concave surface, so as to obtain a desired accurate electric field strength distribution according to the service to be provided. .

  Antennas that transmit radio waves for communication and broadcasting from space accurately form the desired electric field strength distribution even if the shape of the area where the service is provided or the area where the radio wave is supplied is complex according to the service provided. There is a need to.

  As one of the above-mentioned specific methods, there is a method of using a modified specular reflector antenna having an uneven surface instead of a parabolic mirror surface that is a uniform concave surface.

  FIG. 9 shows such a conventional modified specular reflector antenna.

  In FIG. 9, 101 is a modified specular reflector antenna formed of, for example, an aluminum honeycomb sandwich plate, 102 is an arm that supports the antenna, 103 is a deployment hinge, and 104 is a satellite on which the modified specular reflector antenna is mounted. , 105 are power supply units.

In addition, a spider web-like pattern is drawn on the surface of the modified specular reflector antenna 101 in the figure, but this is schematically drawn in order to emphasize the unevenness of the surface. In, such a pattern is not drawn.

  At the time of launch, the satellite 104 is housed in a rocket fairing (not shown) with the modified specular reflector antenna 101 housed along the satellite 104, and after reaching a predetermined orbit in space. The unfolded hinge 103 unfolds the corrected mirror reflector antenna 101, and the arm 102 keeps the positional relationship between the modified mirror reflector antenna 101 and the power feeding unit 105 in a predetermined state.

  The radio wave transmitted by the power feeding unit 105 is reflected by the corrected specular reflector antenna 101 having an uneven surface and reaches the ground.

  Since the unevenness of the modified mirror reflector antenna 101 is formed in accordance with a complicated radio wave supply area, a desired electric field intensity distribution can be accurately formed on the ground.

  However, if the modified specular reflector antenna 101 is formed of an aluminum honeycomb sandwich plate, it must be housed inside the rocket fairing at the time of launch, as described above, so that the size depends on the size of the rocket fairing. It was limited to ˜4 m, and this was a limitation of accurately forming the electric field strength distribution.

  As described above, as a reflector antenna having a large opening that is not affected by the size of the rocket fairing, an antenna using a deformable conductive mesh is known (Patent Document 1).

  10 and 11 show such a conventional mesh reflector antenna.

  Since the mesh-type reflecting mirror 110 uses a deformable conductive mesh 111 as a reflecting surface, it can be folded and stored inside the deployable deployment truss 112 at the time of launch, and the deployment truss stored at the time of launch. 112 is deployed on the track by the umbrella mechanism 113.

  Therefore, unlike the reflector formed by the aluminum honeycomb sandwich plate, the size of the opening is not limited by the size of the rocket fairing, and an antenna having an opening of several tens of meters can be configured. It has been.

  A first wire network 114 is sewn into the conductive mesh 111, and the first wire network 114 is supported at an end by a support column 115 fixed to the deployment truss 112, and a support portion is also provided at the other end. If there is no tension, tension is applied so as to be substantially flat.

  A second wire network 116 is fixed to the deployment truss 112, and the second wire network 116 of the tie wire 117 is fixed to the deployment truss 112.

  In this state, when the tie wire 117 and the first wire network 114 are connected so that tension is applied to the tie wire 117, the first wire network 114 is recessed toward the deployment truss 112, so that a concave surface is formed. can do.

  In the conventional mesh-type deployable antenna, using this action, the concave surface is configured as a parabolic surface, and a radio wave from a power supply unit (not shown) is reflected to transmit the radio wave.

  However, in the configuration as described above, a convex portion cannot be formed on the reflecting surface, which has been a limitation on accurately forming the electric field strength distribution.

JP 2001-233299 A

  In a conventional antenna reflector, the opening of a modified mirror reflector with irregularities on the reflector surface is limited by the size of the rocket fairing, and in a mesh reflector that can form a large opening, the reflector mirror surface It cannot be a corrected specular reflecting mirror provided with projections and depressions, which hinders accurate formation of the electric field strength distribution in accordance with an arbitrary region where radio waves are desired to be supplied.

  The present invention has been made in view of the above circumstances, so that a modified mirror reflector having a large opening area can be accommodated in the rocket fairing when launched by using a deformable conductive mesh on the reflecting surface. Fold it small and deploy it on the orbit to configure the above large-aperture correction specular reflector to obtain the desired accurate field strength distribution that matches the service area and the service provided. Objective.

In 1st invention, the electroconductive mesh which forms a mirror surface in an unfolded state, the 1st wire network sewn and fixed to this, the 2nd wire network installed in the opposite side to the reflective surface of the above-mentioned mirror surface, in the reflecting surface of the mirror surface, first tie wire connecting the third wire network installed position remote from the conductive mesh, and the first wire network the second wire network If a second tie wire for connecting any point between the third wire network of the first wire network, a support member for supporting the third wire network from the first, the support member And a deployment truss to support.

According to the above configuration, when the conductive mesh folded small so as to be housed inside the fairing in the launched state is expanded on the track on the deployment truss and the support member fixed thereto, The first wire network that is sewn and fixed to the conductive mesh is connected to the second wire network that is installed on the side opposite to the reflecting surface by the first tie wire, and any part on the reflecting surface side is connected. By connecting to the third wire network and the second tie wire installed away from the conductive mesh, the conductive mesh can be drawn to either side of the reflective surface. Therefore, it is usually possible to provide any irregularities on the conductive mesh that is a uniform concave surface (parabolic surface). By configuring, regions and to provide services, tailored to the service to be provided, it is possible to obtain a desired accurate electric field strength distribution.

Moreover, in 2nd invention, the electroconductive mesh which forms a mirror surface in an unfolded state, the 1st wire network sewn and fixed to this, and the 2nd wire installed on the opposite side to the reflective surface of the mirror surface A network, a tie wire connecting the first wire network and the second wire network, a rod-shaped member installed in parallel with the tie wire and capable of receiving a compressive force, and the first and second The first wire network is configured to have a supporting member that supports the wire network, and a deployment truss that supports the supporting member, and the first wire network is attached to the conductive mesh only in a portion adjacent to the rod-shaped member. The mirror surface is arranged on the opposite side of the reflecting surface.

  According to the above configuration, when the conductive mesh folded small so as to be housed inside the fairing in the launched state is expanded on the track on the deployment truss and the support member fixed thereto, The first wire network that is sewn and fixed to the conductive mesh is connected to the second wire network that is installed on the opposite side of the reflecting surface by a tie wire, and an arbitrary portion of the first wire network is Since it is installed in parallel with the tie wire and can be pushed by a rod-shaped member that can receive a compressive force, it is usually optional for the conductive mesh that forms a uniform concave surface (parabolic surface). By constructing a large-aperture correction mirror reflector, it is possible to match the area where the service is provided and the service provided. And, it is possible to obtain a desired accurate electric field strength distribution.

  In general, in a mesh-type deployable antenna for space use, a quartz cable is used as a material for a wire network, which has a low coefficient of thermal expansion and is not easily affected by ultraviolet rays or radiation. It is difficult to use this as a sewing thread.

  Therefore, for the sewing of the conductive mesh and the first wire network, organic fibers such as Nomex and Kevlar having higher flexibility are used as sewing threads. There is a high risk of damage, damage to strength, and tearing.

According to the above configuration, since the first wire network is arranged on the concave surface side of the conductive mesh only in the portion adjacent to the rod-shaped member, the expanded conductive mesh is always flat. Since the force is acting in the returning direction, that is, in the direction of the first wire network, even if the sewing thread is torn, the conductive mesh and the first wire network will not deviate. The mirror surface accuracy of the reflecting surface does not deteriorate, and the initial performance can be maintained on the orbit.

Moreover, in the said 1st invention, the member which couple | bonds the said 3rd wire network and the said 2nd tie wire with the member which does not have electroconductivity was comprised.

  According to the above configuration, the coupling member positioned on the reflective surface side of the mirror surface of the conductive mesh, that is, the side through which radio waves pass, is replaced with a non-conductive member, that is, engineering plastic, for example, a heat-resistant polyimide molded body. By using the Sepra or the like, it is possible to prevent scattering of the radio wave that is not intended by the reflector, and as a result, a desired accurate electric field strength distribution can be obtained.

Moreover, in the said 1st invention, the mesh-shaped entanglement prevention member which consists of a member which does not have electroconductivity is arrange | positioned on the outer side of the said 3rd wire network and the said 2nd tie wire connected to this, These It was configured to wrap up.

According to the above configuration, since the third wire network and the second tie wire connected to the third wire network are confined between the conductive mesh, when the deployment truss is deployed, the umbrella mechanism of the deployment truss As a result, it is possible to obtain a predetermined performance on the orbit, that is, a desired accurate electric field strength distribution.

  According to the present invention, it is possible to provide the conductive mesh, which is normally a uniform concave surface (parabolic surface), with an arbitrary unevenness with a simple configuration, so that it can be stored inside the fairing in the launched state. It is possible to configure a modified specular reflector in a state where it is folded into a small aperture and expanded to a large aperture mirror surface on the orbit, and this makes it possible to configure the service area and the service provided. It is possible to obtain the desired accurate electric field strength distribution, and even if the strength of the sewing thread deteriorates due to the environment on the track, the mirror surface accuracy of the reflecting surface by the conductive mesh does not deteriorate. Thus, it is possible to provide a deployable mesh antenna that can maintain the above performance and realize a reliable deploying operation.

1 is a configuration diagram of a deployable mesh antenna according to an embodiment of the present invention. It is sectional drawing of the expandable mesh antenna of FIG. It is a figure which shows the state in the middle of expansion | deployment of the expandable mesh antenna of FIG. It is a perspective view which shows the sewing part of the mesh of the expandable mesh antenna of FIG. It is sectional drawing of the expansion | deployment type mesh antenna concerning the reference example of this invention. It is sectional drawing of the expandable mesh antenna concerning other embodiment of this invention. It is sectional drawing of the expandable mesh antenna concerning other embodiment of this invention. It is a perspective view of the expandable mesh antenna comprised combining the expandable mesh antenna concerning other embodiment of this invention. 1 shows a conventional modified specular reflector antenna. A conventional mesh reflector antenna is shown. It is sectional drawing which shows the conventional mesh type reflective mirror antenna.

  Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings.

  1, 2 and 3 show a deployable mesh antenna 1 according to a first embodiment of the present invention. FIG. 1 shows a configuration of the deployable mesh antenna 1, and FIG. FIG. 3 shows a state during development, and FIG. 4 shows a meshed portion of the mesh.

Note that FIG. 3 is a diagram illustrating a deployment function, and therefore, the third wire network 30, the node 31, the fixture 32, the second tie wire 33, the extended support pillar 61, and the like are not illustrated.

  The first wire network 10 is formed by connecting non-conductive wires formed of quartz or the like in the form of a cobweb, and is stretched on the radio wave reflecting surface side of the conductive mesh 40 (see FIG. 1). The first wire network 10 and the conductive mesh 40 are sewn and fixed by a mesh sewing thread 81 made of organic fiber such as Nomex or Kevlar having flexibility as a sewing thread (see FIG. 4). And the node 11 made from a nonelectroconductive resin material is each assembled | attached to the intersection of this 1st wire network 10 (refer FIG. 1).

  The conductive mesh 40 is a deformable radio wave reflecting member which is a woven fabric in which a metal material such as a molybdenum wire plated with gold is woven in a mesh shape and has the stretchability and flexibility characteristic of the woven fabric. The electric resistance can be lowered by the above gold plating, and as a result, the modulation when the radio wave is reflected can be lowered.

  The end portion of the first wire network 10 is fixed to the fixing tool 12, and the fixing tool 12 is fixed to the distal end side of the support column 60 fixed to the deployment truss 50 (see FIG. 1).

The second wire network 20 is formed by connecting the same non-conductive wires, for example, in a ladder shape (catenary structure), and the end portion is fixed to the deployment truss 50, and the conductive mesh 40 has a radio wave. It is stretched on the opposite side of the reflective surface.

  Then, for example, a node 21 is assembled at the intersection of the second wire network 20 (see FIG. 1).

  The third wire network 30 is formed by connecting the same non-conductive wires, for example, in the form of a spider web, on the radio wave reflection surface side of the conductive mesh 40, away from the conductive mesh 40, It is stretched. And the node 31 made from a nonelectroconductive resin material is each assembled | attached to the intersection of this 3rd wire network 30, for example.

  The end of the third wire network 30 is fixed to a fixing tool 32, and the fixing tool 32 is fixed to, for example, the tip of an extended support column 61 fixed to the tip side of the support column 60 ( (See FIG. 1).

A first tie wire 23 is connected to the node 21 provided at the intersection of the second wire network 20 and the node 22 fixed on the lateral member 53 of the deployment truss 50, and the first tie wire 23 is By inserting through a hole (not shown) of the conductive mesh 40, the conductive mesh 40 is connected to a predetermined portion of the node 11 provided at the intersection of the first wire network 10 (see FIG. 1 and FIG. 2).

A second tie wire 33 is connected to the node 31 provided at the intersection of the third wire network 30 and is connected to a predetermined portion of the node 11 provided at the intersection of the first wire network 10 ( (See FIG. 1 and FIG. 2).

Between the first and second wire networks 10 and 20, a mesh-like entanglement preventing member 70 made of a non-conductive resin material is encased in a mirror surface so as to wrap the first tie wire 23. Installed in the direction. The entanglement preventing member 70 is attached to the first tie wire 23 using a thread or the like so as to have a predetermined degree of freedom.

In addition, when the entanglement preventing member 70 is loosened in a state of being stretched between the first and second wire networks 10 and 20, it affects the folding and unfolding of the first and second wire networks 10 and 20. The first and second wire networks 10 and 20 are appropriately attached using a thread or the like to such an extent that they do not affect. For example, the entanglement preventing member 70 is all disposed at a position where the first tie wire 23 of the second wire network 20 is disposed (see FIG. 1).

  The deployment truss 50 is composed of six sets of outer vertical members 52 sharing a central vertical member 51, and a four-sided link 55, each of which includes a horizontal member 53 and a horizontal member 54, each of which is rotatably attached. In the expanded state, for example, it is configured to have a substantially hexagonal frustum shape.

  A slant member 56 is disposed inside the four-sided link 55, one end of the slant member 56 is rotatably attached to the horizontal member 54, and the other end of the slant member 56 is the axis of the central vertical member 51. It is rotatably attached to a well-known umbrella mechanism 57 that is slidably attached in the direction.

  The umbrella mechanism 57 can be moved in the axial direction of the central vertical member 51 via a drive unit (not shown), and in conjunction with the movement, the folding truss 50 can be folded and accommodated from the folding position. ing.

  Thus, the unfolding truss 50 can be folded and unfolded, and in the unfolded state, for example, has a substantially hexagonal frustum shape (see FIG. 3).

  In the storage shape, the deformable conductive mesh 40 can be folded and stored in a hexagonal frustum-shaped gap generated between the six lateral members 53.

  The six support columns 60 described above are fixed so as to be joined to the outer vertical member 52.

  The length of the support column 60 is set so that the point of the tip of the support column 60 is at a predetermined position in order to make the conductive mesh 40 have a predetermined shape in order to satisfy the function as an antenna reflector. ing.

Similarly, by adjusting the lengths of the first tie wire 23 and the second tie wire 33, the node 11 provided at the intersection of the first wire network 10 can be installed at a predetermined position. Since the wire network 10 can be pulled to the reflecting surface side by the second tie wire 33, the first wire network 10 can be in an arbitrary position, that is, an uneven shape. 10, the conductive mesh 40 sewn and fixed by the mesh sewing thread 81 can also be installed at an arbitrary predetermined position (see FIG. 2).

  As a result, it is possible to provide the conductive mesh 40 with any irregularity (see FIG. 2). By configuring a large-aperture correction mirror reflector, it is possible to provide a service area or a service to be provided. It is possible to obtain a desired and accurate electric field strength distribution.

  As described above, by making the node 31 attached to the intersection of the third wire network 30 made of a non-conductive resin material, the reflective surface side of the mirror surface of the conductive mesh 40 where the node 31 exists, That is, it is possible to prevent the scattering of the radio wave unintentionally designed on the side where the radio wave passes, and as a result, a desired accurate electric field intensity distribution can be obtained.

  Moreover, although the said embodiment demonstrated the case where the expansion | deployment truss 50 was comprised in the hexagonal frustum shape, it can comprise not only in this shape. Furthermore, the deployable mesh antenna according to the present invention is not limited to the above embodiment, and can be configured using deployable trusses having various shapes.

Subsequently, a reference example of the present invention will be described. In the following description of the reference example, the same components as those in the first embodiment described above are denoted by the same reference numerals, and redundant description is omitted.

FIG. 5 shows a cross-sectional view of a deployable mesh antenna 1a according to a reference example of the present invention.

This reference example is different from the first embodiment in that the hollow rod-shaped member 80 is not used without using the third wire network 30, the node 31, the fixture 32, the second tie wire 33, the extended support pillar 61, and the like. By pushing up the first wire network 10 through the first tie wire 23 inside, the first wire network 10 is in an arbitrary position, that is, an uneven shape, and accordingly, the first wire network 10 10, the conductive mesh 40 which is sewn and fixed by the mesh sewing thread 81 can also be installed at an arbitrary predetermined position.

With the above configuration, the second wire network 20 (not shown in the present reference example ) has a convex shape on the opposite side to the direction shown in FIG. 1, but the first wire network 20 is tensioned by the tension generated in the second wire network 20. The position of the wire network 10 can be determined.

Next, a description will be given of a second embodiment of the present invention. In the following description of each embodiment, the same components as those in the first embodiment described above are denoted by the same reference numerals, and redundant description is omitted.

FIG. 6 is a sectional view of a deployable mesh antenna 1b according to the second embodiment of the present invention.

  The present embodiment is different from the first embodiment in that the positions of the first wire network 10 and the conductive mesh 40 are exchanged.

In the first embodiment, the conductive mesh 40 to the first wire network 10 has been positioned on the lower side in FIG. 1, in this embodiment, as shown in FIG. 6, the second tie The first wire network 10 adjacent to the wire 33 is configured to be placed under the conductive mesh 40 by inserting a hole (not shown) provided for installing the node 11 into the conductive mesh 40. doing.

  In addition, in FIG. 6, in order to understand the positional relationship between the first wire network 10 and the conductive mesh 40, each is schematically depicted as being displaced, but in the actual machine, the displacement is small enough to be ignored, The impact on function and performance due to this deviation is negligible.

  In general, in a mesh-type deployable antenna for space use, a quartz cable is used as a material for a wire network, which has a low coefficient of thermal expansion and is not easily affected by ultraviolet rays or radiation. It is difficult to use this as a sewing thread.

  Therefore, for the sewing of the conductive mesh and the first wire network, organic fibers such as Nomex and Kevlar having higher flexibility are used as sewing threads. There is a high risk of damage, damage to strength, and tearing.

According to the said structure, since the 1st wire network 10 is comprised so that it may arrange | position to the concave surface side of the electroconductive mesh 40, the expanded electroconductive mesh always returns to a plane, ie, the 1st Since the force is acting in the direction in which the wire network is arranged, even if the sewing thread is torn, the conductive mesh 40 and the first wire network 10 do not deviate from each other. The mirror surface accuracy of the surface does not deteriorate, and the initial performance can be maintained on the track.

Further, in this embodiment, the positions of the first wire network 10 and the conductive mesh 40 are exchanged with respect to the first embodiment. However, as in the above reference example , the hollow rod-shaped member 80 is used. It goes without saying that the same effect can be obtained when applied to the deployed mesh antenna 1a.

Subsequently, a third embodiment of the present invention will be described. In the following description of each embodiment, the same components as those in the first embodiment described above are denoted by the same reference numerals, and redundant description is omitted.

FIG. 7 shows a cross-sectional view of a deployable mesh antenna 1c according to a third embodiment of the present invention.

This embodiment is different from the first embodiment in that the third wire network 30, the node 31, the fixture 32, the second tie wire 33, the extended support pillar 61, and the like are prevented from being entangled and covered with the cover 82. In other words, the conductive mesh 40 is enclosed in a space.

According to the above configuration, since the third wire network 30 and the second tie wire 33 connected to the third wire network 30 are confined between the conductive mesh, when the deployment truss is deployed, the umbrella mechanism of the deployment truss As a result, it is possible to obtain a predetermined performance on the orbit, that is, a desired accurate electric field strength distribution.

  In addition, by making the anti-tanglement cover 82 made of a non-conductive resin material, the design is intended on the reflective surface side of the mirror surface of the conductive mesh 40 where the anti-tanglement cover 82 exists, that is, the side through which radio waves pass. Radio wave scattering can be prevented, and as a result, a desired accurate electric field strength distribution can be obtained.

Subsequently, a fourth embodiment of the present invention will be described. In the following description of each embodiment, the same components as those in the first embodiment described above are denoted by the same reference numerals, and redundant description is omitted.

FIG. 8 is a perspective view of a deployable mesh antenna assembly 103a configured by combining deployable mesh antennas 1d according to the fourth embodiment of the present invention.

  In the deployable mesh antenna assembly 103a shown in FIG. 8, the deployable truss 50 of each deployable mesh antenna 1d is combined with a coupling bracket (not shown) attached to an outer vertical member 52, and this is combined with a satellite (not shown). Are combined with a deployment boom 83.

  In this configuration, the length of the support column 60 is set in order to make the conductive mesh 40 have a predetermined shape in order to satisfy the function as an antenna reflector in accordance with the position where each deployment truss 50 exists. Has been.

Similarly, by adjusting the lengths of the first tie wire 23 and the second tie wire 33 (not shown), the node 11 (not shown) provided at the intersection of the first wire network 10 is installed at a predetermined position. However, since the wire network 10 can be pulled to the reflecting surface side by the second tie wire 33, the first wire network 10 can be in an arbitrary position, that is, an uneven shape.

The difference between the present embodiment and the first embodiment is that in FIG. 1, six second tie wires 33 to be coupled to the third wire network 30 are arranged in an annular shape in the deployment truss 50. On the other hand, in the present embodiment, the nodes 11 (in the present embodiment, convex nodes 84) that are raised upward in FIG. It is in that it was not provided.

  As described above, in the deployable mesh antenna assembly 103a configured by combining the deployable mesh antenna 1d, a predetermined state is obtained in a combined state even if the convex nodes 84 are not arranged annularly with respect to each deployable truss 50. If it is configured so as to have a corrected mirror surface, an antenna having an opening size that cannot be achieved by an individual deployable mesh antenna using one deployable truss 50 can be configured.

The present invention is not limited to the above-described embodiments, and it goes without saying that various modifications can be made without departing from the spirit of the present invention.

10: First wire network.
11 Node.
12: Fixing tool.
20 ... Second wire network.
21 ... node.
22 Node.
23: First tie wire.
30 ... Third wire network.
31: Node.
32: Fixing tool.
33 ... Second tie wire.
40: Conductive mesh.
50 ... Deployment truss.
51: Center longitudinal member.
52 ... Outside vertical member.
53 ... A transverse member.
54: Transverse member.
55 ... Four-sided link.
56: Diagonal member.
57 ... Umbrella mechanism.
60: Support pillar.
61 ... Extension support column.
70: Tangle prevention member.
80: Hollow rod-shaped member.
81 ... Mesh sewing thread.
82 ... Tangle prevention cover.
83 ... Deployment boom.
84 ... convex node.
101: Modified specular reflector antenna.
102: Arm.
103 ... Deployment hinge.
104 ... satellite.
105: Power feeding unit.
110... Mesh reflector 111... Conductive mesh.
112 ... Deployment truss.
113 ... Umbrella mechanism.
114: First wire network.
115 ... Support pillar.
116 ... The second wire network.
117 ... Tie wire.

Claims (5)

A conductive mesh forming a mirror surface in the unfolded state, a first wire network sewn and fixed thereto, a second wire network installed on the opposite side of the reflective surface of the mirror surface, and the reflection of the mirror surface On the surface side, a third wire network installed at a location away from the conductive mesh, a first tie wire connecting the first wire network and the second wire network, and the first A second tie wire connecting the third wire network with an arbitrary portion of the wire network, a support member supporting the first to third wire networks, and a deployment truss supporting the support member. A deployable mesh antenna comprising: The first wire network is disposed on the side opposite to the reflecting surface of the mirror surface with respect to the conductive mesh only in a portion adjacent to the second tie wire connected to the third wire network. 2. The deployable mesh antenna according to claim 1, wherein the deployable mesh antenna is installed. A conductive mesh that forms a mirror surface in the unfolded state, a first wire network that is sewn and fixed thereto, a second wire network that is installed on the opposite side of the reflective surface of the mirror surface, and the first wire A tie wire that connects the network and the second wire network, a rod-like member that is installed in parallel with the tie wire and can receive a compressive force, and a support member that supports the first and second wire networks And a deployable mesh antenna having a deployable truss that supports the support member,
The unfolding type characterized in that the first wire network is installed so as to be disposed on the side opposite to the reflecting surface of the mirror surface with respect to the conductive mesh only in a portion adjacent to the rod-shaped member. Mesh antenna. 2. The deployable mesh antenna according to claim 1, wherein a member that joins the third wire network and the second tie wire is configured by a member having no conductivity. 2. The development according to claim 1, wherein a mesh-like entanglement preventing member made of a member having no conductivity is arranged outside the third wire network and the second tie wire connected to the third wire network. Type mesh antenna.

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