JPS62188401A - Expansion antenna reflector - Google Patents

Abstract

PURPOSE:To improve the storage efficiency by providing lots of connecting wires giving a required shape as an antenna reflector to two flexible thin sheets and pulling two opposed points on the flexible thin sheets inward with each other. CONSTITUTION:The two meshed flexible thin sheets 14 tied together by lots of connecting wires 15 via lots of support wires 13 in the inside of a hoop are folded between lots of frame members 20 at the fold-up state, and fixed to the wall at the satellite side while the 1st adjacent hinges are pressed into contact together and tightened by a proper tightening device. The tightening device is loosened at the expansion, each frame member 20 starts expanding by the torque of the elastic spring such as a spiral spring built-in the 1st hinge 21 and the 2nd hinge 22 and the two flexible thin sheets 14 folded between the frame members 20 starts expanding. Thus, the maximum length at the folding-up is decreased remarkably and the storage capacity is reduced mesh, then the storage efficiency is improved.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a deployable antenna reflector, and particularly to the configuration of a deployable antenna mounted on, for example, an artificial satellite or a space station.

[Conventional technology]

5 and 6 are a front view and a side view showing the shape of a conventional deployable antenna reflector disclosed in, for example, Japanese Unexamined Patent Publication No. 59-28704 when it is stored, and FIGS. 7 and 8 are FIG. 6 is a front view and a side view showing the shape of the deployed antenna reflector of FIG. 5 after being deployed.

In each of the above figures, 11a denotes 180 of the hinges that incorporate an elastic spring such as a spiral spring that provides the driving force for rotation, and are equipped with a latch device (not shown) that locks the rotation when a predetermined rotation angle is reached. The hinge Jllb that latches with a deployment angle of 135 degrees is also the hinge IB) that latches with a deployment angle of 135 degrees, where each hinge tAl 11 a
and hinge IB) 1 l b.

A structure with a built-in bearing that can achieve low friction conditions,
This bearing can be, for example, a spherical bearing. 12
a, 12b are each hinge prisoner 11a, hinge (B111b!
A tubular member 1 whose ends are connected to each other to form a hoop shape as a whole 1 is a G-shaped long frame and a short frame made of carbon fiber composite material, for example, and the long frame 12a is a part of the satellite shown in FIG. The attachments to the side walls 18 are provided in portions and at positions opposite thereto on the hoop, while the hoop shape is otherwise constituted by the short frame 12b. Reference numeral 13 denotes a long frame 12a and a number of support wires attached to each hinge prisoner 11a and hinge (B) llb, which are held with adjustable tension. 14 are two mesh-like flexible thin films, at least one of which is electrically conductive, the edges of which are supported by a large number of support wires 13;
is a bonding wire that pulls the two facing flexible thin films 14 inward toward each other, and the length thereof can be set in an adjustable manner. Reference numeral 16 indicates a slot for holding each long frame 12a and short frame 12b during storage, and reference numeral 17 indicates an attachment for fixing the long frame 12a to the satellite side wall 18.

Next, the operation will be explained. At the time of launch.

As shown in Figures 5 and 6, connect the ends to each hinge (A).
11&, a hoop consisting of each long frame 12a and short frame 12b connected by hinge (B) 1 l b, each of the above-mentioned hinges (Al 11 a, hinge (B) 1 l
It is folded at point b. Here, the attachment is carried out by attaching the long frame 12a to the satellite side wall 18 via the tool 17, and the long frame 1 at a position opposite to the long frame 12a.
As shown in FIG. 5, the length of the short frame 2a is slightly longer than twice the length of the other short frame 12b in order to prevent the folded left and right hinges (A) 11a from colliding with each other. . In addition, there are many support wires 1 inside the hoop.
Two mesh-like flexible thin films 14, which are connected to each other by a large number of bonding wires 15, are connected to each other by a long frame 12a and a short frame 12a.

It is folded between 12b. In this state, the spacers 16 provided on the adjacent long and short frames 12a and 12b are in contact with each other, and an appropriate bonding f (not shown) is applied.
It is fixed to the satellite side wall 18 in a tightly bound state by an ail. After reaching the orbit, when the bonding device is released, each hinge prisoner 11&.

Each length and short frame 12a are adjusted by the torque of an elastic spring such as a spiral spring built into the hinge (B) 1lb.

12b begins to develop, and along with this, 6 lengths.

The two flexible thin films 14 folded between the short frames 12a and 12b also begin to unfold. here.

The hinge (A111a) that was folded inward when stored
is locked by the built-in latch device when the unfolding angle reaches 180 degrees, and the hinge (B) 1 l b, which was folded outward, is locked by the built-in latch device when the unfolding angle becomes 135 degrees. Locked by device. Thus, every hinge prisoner 11a.

When the hinge (B) 1 l b is locked, it is finally formed into an octagonal hoop, as shown in FIG.

In this state, two
The length of each support wire 15 is adjusted in advance so that a predetermined tension is applied to the mesh-like flexible thin film 14. Moreover, one of the flexible thin films 14 forms a parabolic surface (strictly speaking, each bonding wire 15 and the flexible thin film 1
The length of each bonding wire 15 is adjusted in advance according to its position so that the bonding point with 4 is on the parabolic plane).

[Problem that the invention seeks to solve]

Since the conventional deployable antenna reflector described above is configured as described above, each of the long and short frames 12a and 12b
has a fixed length, so the maximum length of the deployed antenna reflector when retracted is the long frame 12.
This is determined by the length of a, and when configuring a large diameter deployable antenna reflector, there is a problem that the maximum length when stored becomes long. In addition, each hinge (A) 11 a and hinge (B) 1 l b
Since the respective deployment angles are different and not synchronized, there is a problem in that an imbalance occurs in each deployment motion, which may interfere with the normal deployment motion of the deployable antenna reflector.

This invention was made in order to solve such problems, and provides a highly reliable deployable antenna reflector that is excellent in storage efficiency and allows each member constituting the frame to deploy synchronously. The purpose is to obtain.

[Failure to solve the problem]

The deployable antenna reflector according to the present invention has a large number of hinges equipped with a latch device that locks the rotation when a predetermined rotation angle is reached, and is connected to each other by these hinges to form a hoop shape as a whole, and expands and contracts in a pantograph manner. a large number of unfolded frames, two mesh-like delicate thin films surrounded by each frame and supported at the edges by support wires on the frames and hinges, and these two flexible The flexible thin film is provided with a large number of bonding wires that pull two opposing points on the flexible thin film inwardly to give the flexible thin film a desired shape as an antenna reflector.

[Effect]

In the deployable antenna reflector of this invention.

A number of frames in the unfolded form are connected to each other by a number of hinges equipped with latching devices that lock the rotation when a predetermined rotation angle is reached, and are composed of members that expand and contract in a pantograph manner so as to form a hoop shape as a whole. As a result, the size of the deployable antenna reflector when stored is extremely small, improving storage efficiency.Also, by synchronizing the deploying operations of each frame, a highly reliable and stable deployable antenna reflector is realized. can do.

〔Example〕

1 and 2 are a front view and a side view showing the shape of the deployable antenna reflector, which is a part of the mvA of the present invention, after being deployed, and FIGS. 3 and 4 are views when the deployable antenna reflector is stored in an IF state. It is a front view and a side view which show the shape of. In each of the above figures, numerals 13, 14, and 15 are the same as those in the conventional example shown in FIG. 7 above. Further, 21 is a first hinge provided at each end of the frame member 20, and 22 is a second hinge provided at the center of the frame member 20. Each of the first hinge 21 and the second hinge 22 has a built-in elastic spring such as a thinly wound spring that provides a driving force for one rotation.
A latch device (not shown) is provided to lock the rotation when a predetermined rotation angle is reached. Furthermore, each of the first hinge 21 and the second hinge 22 can be a gable having a built-in bearing capable of realizing low friction conditions, and this bearing can be one, for example a spherical bearing. The first hinge 21 and the second hinge
A number of frame members 20 connected by hinges 22 of
consists of a tubular member forming a hoop shape as a whole, and this member is constructed of, for example, a carbon fiber composite material. Moreover, the first hinge 21 is.

The projection of the frame member 20 onto the opposing symmetry planes 23 of the two mesh-like flexible thin films 14 and the projection onto the symmetry plane 23 of the adjacent frame members 20 connected by the first hinge 21. An angle holding mechanism (not shown) is provided to keep the angle constant.

First, the operation of the deployable antenna reflector shown in FIGS. 11 and 2, which is an embodiment of the present invention, will be explained. When the deployable antenna reflector is launched, as shown in FIGS. 3 and 4, the frame members 20 are connected at each end by a first hinge 21 and at the center by a second hinge 22. A hoop of body is folded at the first hinge 21.

Further, two mesh-like oT flexible membranes 14 are provided inside the hoop via a large number of support wires 13 and are connected to each other by a large number of connecting wires 15.
It is folded between 0. In this state, the adjacent six first hinges 21 are in contact with each other, and the satellite 1l11 wall 18 is in a state of being bound by an appropriate binding device (not shown).
Fixed. Then, when the orbit is reached and the bonding device is released, the 6th first hinge 21. Each frame member 20 begins to expand due to the torque of an elastic spring such as a thin coil spring built into the second hinge 22, and accordingly.

The two flexible membranes 14 folded between each frame member 20 also begin to unfold. Here, 6 first hinges 21
．． The rotation of the second hinge 22 is locked by a built-in latching device when the unfolding angle reaches a preset angle. During this time, the angle holding mechanism built into the first hinge 21 prevents the projection of the frame member 20 onto the symmetry plane 23 and the adjacent frame member in all states and positions before deployment, during deployment, and after deployment. The angle between the projections of the frame members 20 onto the plane of symmetry 23 is always kept constant, and therefore the polygonal shapes formed by each frame member 20 maintain similarity throughout the course of development. I can do it.

In this way, each frame member 20 is unfolded and the six first hinges 21 . When the second hinge 22 is locked, each frame member 20
As shown in the figure, it has a regular polygonal shape with an extremely large projected area compared to when it is stored.

In this state, the length of each support wire 13 is adjusted in advance so that a predetermined tension is applied to the two flexible thin films 14 connected by a large number of bonding wires 15. (9) The length of each bonding wire 15 is adjusted in advance according to its position so that one flexible thin film 14 forms a parabolic surface. In addition, in the folded state, the distance between the first hinge 21 and the first hinges 21 facing each other across the plane of symmetry 23 is the same as that between the six first hinges 21 at the end of unfolding. Although it is longer compared to the distance of
Slack occurs in the flexible thin film 14 in the folded state, and the relationship between the amount of slack and the length of the bonding wire 15 closest to the first hinge 21 is the distance between the six first hinges 21 in the middle of unfolding. The position of each bonding wire 15 is adjusted in advance so that the flexible thin film 14 and the bonding wire 15 are not stretched too much.

Also.

Each frame member 20 and 6 first hinge 21. When forming a polygonal hoop composed of the second hinge 22, each frame member 20 has a folding structure that expands and contracts in a pantograph manner as shown in FIGS. The unfolding operation of the frame member 20 is performed synchronously. Therefore, a stable and highly reliable deployment operation can be realized without causing problems such as the frame members 20 colliding with each other during deployment or the deployment angle becoming uneven depending on the location.

In addition, in the above embodiment, the - side of the hoop is the second
Although the case of a regular polygon is shown, which is composed of two sets of frame members 20 connected at the center by a hinge 22, it may also be composed of frame members having a pantograph structure with many pairs of sides. Furthermore, the overall shape may be a polygon other than a regular polygon.

Further, in the above embodiment, the two mesh-like flexible thin films 14 are made of the same mesh-like material, but the flexible thin film that is not used as the antenna reflector surface is the same as the other flexible thin film. Compared to the flexible thin film used as the antenna reflector surface, a mesh-like material with a coarse mesh may be used, and the flexible thin film may be composed of a cable net that is flexible and has little stretch. , the same effect as the above embodiment is achieved.

〔Effect of the invention〕

As explained above, in the present invention, in a deployable antenna reflector, two mesh-like flexible thin films forming a required shape as an antenna reflector are surrounded by a large number of deployed frames, The frame is connected to each other by a number of hinges equipped with a latching device that locks the rotation when a predetermined rotation angle is reached, and is composed of members that expand and contract in a pantograph manner so as to form a hoop shape as a whole. Compared to conventional models of this type, the maximum length when stored can be significantly reduced, and the storage volume can be made extremely small, which improves storage efficiency, and the synchronization of the unfolding movement of the frame significantly improves storage efficiency. This has the excellent effect of realizing a highly reliable and stable deployable antenna reflector.

[Brief explanation of drawings]

1 and 2 are a front view and a side view showing the shape of a deployable antenna reflector according to an embodiment of the present invention after being deployed, and FIGS. 3 and 4 are views showing how the deployable antenna reflector shown in FIG. 1 is stored. 5 and 6 are front and side views showing the shape of a conventional deployable antenna reflector when folded, and FIGS. 7 and 48 are the front and side views of the conventional deployable antenna reflector. They are a front view and an I11! front view showing the shape of the deployed antenna reflector after deployment. In the figure, 11a...Hinge prisoner, 11b...Hinge (B1.12a...Long frame, 12b...Short frame. 13...Support wire, 14...Mesh-like flexible thin film , 15...Binding wire, 16...S is -S, 1
7...Mounting tools, 18...Satellite side wall, 20...
Frame members, 21... first hinge, 22... second hinge, 23... opposing symmetrical surfaces of two mesh-like flexible thin films 14. In each figure, the same reference numerals indicate the same or equivalent parts.

Claims (7)

[Claims] (1) A large number of hinges equipped with latching devices that lock the rotation when a predetermined rotation angle is reached, and a large number of deployable hinges that are connected to each other by these hinges, form a hoop shape as a whole, and expand and contract in a pantograph manner. a frame; two mesh-like flexible thin films, at least one of which is electrically conductive; A large number of flexible thin films are disposed between the flexible thin films and pull two opposing points on the flexible thin films inwardly to give the two flexible thin films the desired shape as an antenna reflector. A deployable antenna reflector characterized by having a configuration comprising a coupling wire. (2) Among the plurality of hinges, the hinge at the end of each frame is connected to each frame connected by the hinge to a plane perpendicular to the central axis of the hoop shape formed by each frame. The angle that the projections of
2. The deployable antenna reflector according to claim 1, further comprising an angle holding mechanism that keeps the angle constant. (3) The deployable antenna reflector according to claim 1 or 2, wherein the frame is made of a tubular member, and this member is made of a carbon fiber composite material. (4) The deployable antenna reflector according to any one of claims 1 to 3, wherein the length of the coupling wire is adjustable. (5) Claims 1 to 4, wherein the support wire is held with adjustable tension.
Deployable antenna reflector as described in section. (6) The deployable antenna reflector according to any one of claims 1 to 5, wherein the hinge has a built-in bearing that can realize low friction conditions. (7) The deployable antenna reflector according to any one of claims 1 to 6, wherein the hinge includes an elastic spring that provides a driving force for rotation.