JPS62183204A - Expanded antenna reflector - Google Patents

Abstract

PURPOSE:To obtain a reflector with high reliability by providing a loop-shaped cable between two turning shafts adjacent to an optional frame so as to allow the frame to be uniformly expanded synchronizingly. CONSTITUTION:A cable 5 whose shape is the figure 8 is installed between a pulley 4a and another pulley 4a opposite to the frame 1, loop-shaped cables 6a, 7a are installed respectively between pulleys 4b, 4c and between cables 4d, 4e. The angle of the long frame 1 with respect to the inertia space is unchanged from the storage to the expansion. A short frame 2a is turned by 135 deg. counter clockwise, a short frame 2b is turned by 45 deg. clockwise and a short frame 2c is turned by 90 deg. counter clockwise respectively. In selecting the ratio of diameters of the pulleys 4b, 4c as the ratio of turning angle of the frames 2a, 2b (135:45=3:1) and selecting the ratio of diameters of the pulleys 4d, 4e as the ratio of turning angle of the frames 2a, 2c (135:90=3:2), the frames 2a-2c are expanded uniformly while keeping the ratio of the angles from the storage to the complete expansion.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a deployable antenna reflector, particularly for example two
It relates to the configuration of deployable antennas mounted on artificial satellites or space stations.

[Conventional technology]

4 to 7 are a front view when stored, a side view thereof, and a front view after unfolded, showing a conventional deployable antenna reflector disclosed in Japanese Unexamined Patent Publication No. 59-28704.

It is the same side view.

In the figure, (1) a) is a hinge that has a built-in elastic spring such as a thin coiled spring that provides the driving force for rotation, and is equipped with a latch device that locks the rotation when a predetermined rotation angle is reached. When latched at the deployment angle of (A),
(1) b) is a hinge (B) that also latches at a deployment angle of 135 degrees, where each hinge (A) (1) and hinge (B) (1) meet the low #friction condition. 44 with built-in bearings that can be realized! This bearing can be, for example, a spherical bearing. (12a).

(12b) is each h:,y')(Al(+1a),
A tubular member 9 whose ends are joined to each other by a hinge (B) (1) b) and which forms a hoop shape as a whole; - The frame (12a) is attached to the satellite tlltl wall Uυ shown in FIG. 6 at a position opposite to it on the hoop, and the hoop shape is otherwise formed by the short frame (12b) K. Ru. t
13 is a long frame (12a) and each hinge (A) (1)
a) and hinges (B) (1) b) held with adjustable tension by a number of support wires.

[141 denotes two mesh-like readable thin films whose edges are supported by a large number of support wires 3 and at least one of which is conductive;
=ut binding wires that pull inwardly toward each other, the length of which is adjustable. α(
) is a spacer for holding each long frame (12a) and short frame (12b) during storage, and α7j is a mounting tool for fixing the long frame (12a) to the satellite side wall.

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

As shown in Figures 4 and 5, connect the ends to each hinge (A).
(1) a), a hoop consisting of each long frame (12) and short frame (12b) connected by a hinge (B) (1) b).

Each of the above hinges (A) (1)a), hinge (B)
(1) is folded at the +) position. Here, the length of the long frame (1Za) that is attached to the satellite side Liu via the attachment aη and the length of the long frame (12a) located in a position opposite to this is as shown in FIG.
In order to prevent the folded left and right hinges (A) (1) from colliding with each other, the frame is made slightly longer than twice the length of the other short frame (12b). In addition, two mesh-like flexible thin films α, which are provided inside the hoop via a large number of support wires Q3Q and connected to each other with a large number of bonding wires α9, each have long and short frames (12, (12b) )
folded in between. In this state, the spacers (lbl) provided on the adjacent long and short frames (12a) and (12b) are in contact with each other and are bound by an appropriate binding device (not shown).
Fixed to ag.

After reaching the orbit, when the bonding device is released, each hinge (A) (1) a) and hinge (B) (1) b
) Each length and short frame (t2a), (12)))
It started to develop.

Along with this, each long and short frame (12a).

(12b) Two flexible thin films (1
41 is also starting to spread. Here, the hinge (A) (1) a) that was folded inward when stored has an unfolding angle of 180
Hinge (B) (1) k) that was locked by a built-in latching device and folded outward when the
) is locked by a built-in latching device when the deployment angle reaches 135 degrees. Thus, every each hinge (
When A) (1) a) and hinge (B) (1) b) are locked, it is finally formed into an octagonal hoop as shown in FIG. In this state, a large number of bonding wires US
Two mesh-like flexible thin films 141 connected by
Each support wire u! so that a predetermined tension is applied. The length of j has been adjusted in advance.

In addition, the length of each bonding wire U9 is set so that one flexible thin film I forms a parabolic surface (strictly speaking, the bonding point between each bonding wire U51 and the flexible thin film is on a parabolic surface). has been adjusted in advance according to its position.

[Problem that the invention seeks to solve]

Conventional deployable antenna reflectors are configured as described above, so due to uneven hinge torque, friction, etc.
All the frames do not unfold uniformly, which causes problems such as interference between the flexible thin film and the hinge, resulting in decreased reliability of deployment and damage to the flexible thin film.

This invention was made to solve the above-mentioned problems, and it is an object of the present invention to obtain a highly reliable deployable antenna reflector that can deploy frames synchronously and uniformly.

[Means for solving the ru+ problem] The deployable antenna reflector according to the present invention has a loop-shaped cable provided between two rotating shafts adjacent to an arbitrary frame.

[Effect]

The deployable antenna reflector in this invention is:

Due to the relative restraint between the rotation angles by the above cable.

All frames are synchronous and uniform.

[Embodiments of the invention]

DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be explained below.

In addition, considering the orthogonal biaxial symmetry, only the name of the overall view is shown.

In Figures 1 to 3, (1) is a long frame.

(2a), (2b), and (2C) are the first. Second. 3rd short frame, (3a), (31))
, (30), (3d) are the hinges that connect these, (4a) is the hinge (38), and (4b) is the hinge (3b), which is integral with the rotation axis of the first short frame (2a), respectively. pulley.

(4C) is the second short frame (2) at the hinge (3).
b) What is the pulley that is integral with the rotating shaft? (4d) V
In the i upper hinge 3d), the first short frame (2a) is integral with the rotation axis IJ-, (4θ) is the hinge (3e
), the third short frame (2C) is a pulley that is integral with the rotating shaft, (5a) is a pulley (4a),
A figure-eight cable (6
a) and (78) are pulleys (4b) and (4C) respectively
and a loop-shaped cable provided between (4d) and (4e).

(sb), (6b), and (7b) are each a set of two coil springs provided in the above cable,
Q31 is the support wire that connects the frame and the flexible thin film, α
4 is a flexible thin film, and US is a bonding wire that connects two flexible thin films to form a parabolic surface.

The folded frame unfolds due to the action of the spiral spring built into the hinge, and the two flexible thin membranes are stretched out accordingly, and in the final position, each hinge locks with the built-in lock. The two flexible thin films fixed by the device and supported by the frame maintain a parabolic shape with a large number of bonding wires whose lengths are adjusted in advance, similar to a conventional deployable antenna reflector, but with the following points: are different.

The long frame [1] does not change its angle with respect to inertial space from when it is stored until after it is deployed. The short frame (2a) rotates 135 degrees counterclockwise, the short frame (2b) rotates clockwise, and the short frame (2C) rotates 90 degrees counterclockwise. Here, pulley (4b) and (4
The rotation angle ratio of the frames (2a) and (2b) is 135:45=3:1, and the diameter ratio of the pulley (4d
) and (4e) are the diameter ratios of the frames (2a) and (2re).
If the rotation angle ratio is set to 135:90=3:2, the above frames (2a), (2b), C20)
When it is stored, it unfolds uniformly while maintaining the above angle ratio until after it is fully unfolded.

Further, a pulley (not shown) fixed to a rotation axis of the short frame (not shown) and a pulley (not shown) located at a hinge (not shown) located symmetrically to the hinge (3a) with respect to the long frame flll and the aforementioned boo 1j - (4a) If a looped cable is arranged in a figure 8 shape between them, and the pulley diameters are made equal for both, the short frame (2-ri and the short frame (not shown) can be rotated by the same angle in opposite directions. As a result, the rotation of all short frames is performed synchronously from the time of retraction to the time of full deployment.

Note that if a fixing device is provided between each of the cables and the pulley, force can be transmitted without them slipping against each other.

In addition, each cable is equipped with a pair of coil springs to absorb the load due to thermal deformation due to the difference in thermal expansion coefficient between the frame and cable, and to prevent excessive stress on the frame, cables, and other mechanical parts. It is possible to prevent the load from occurring.

In the above embodiment, the case where the expanded shape is octagonal and the number of frames is α-heavy is described, but the same effect can be achieved even in the case of other polygons or number of frames.

〔Effect of the invention〕

As described above, according to the present invention, in a hoop-shaped frame, the two hinge rotation axes adjacent to each frame are restrained by a pulley having a predetermined diameter and a loop cable. The rotation of the frame is synchronized,
Therefore, it is possible to perform a highly reliable unfolding motion, and there is an effect that a flap can be obtained.

[Brief explanation of drawings]

FIG. 1 is a partial perspective view of a deployable antenna reflector according to an embodiment of the present invention, and FIG. 2 is a front view of the same. FIG. 3 is a side view of the same, and FIGS. 4 to 7 are a front view and a side view of a conventional deployable antenna reflector when it is stored and when it is deployed. (1) is a long frame, (2a), (2b), C
20) are short 7L/-m, (3a), (3b
), (3C), (3a), (se) are hinges. (4a), (4b), (4c, (4d)
, (4 is a pulley, (5 is. (Sa), (7a) is a looped cape /l/,
(5b), (6b). (7b) is a coil spring, (13 is a support wire, t1
41 is a readable thin film, US is a bonding wire. Note that the same pipe numbers in Figure 1 indicate the same or equivalent parts.

Claims (7)

[Claims] (1) A large number of hinges each having an elastic spring that provides a driving force for rotation and a latch device that locks the rotation when a predetermined rotation angle is reached; A large number of frames forming a hoop shape,
two mesh-like flexible thin films, at least one of which is surrounded by the frames, whose edges are supported by the frames and hinges via support wires, and at least one of which is electrically conductive; A large number of bonding wires are disposed between the thin films and pull two opposing points on the flexible thin films inwardly to give the two flexible thin films a desired shape as an antenna reflector. A deployable antenna reflector characterized in that a loop-shaped cable is disposed between two rotating shafts adjacent to an arbitrary frame. (2) The deployable antenna reflector according to claim 1, wherein the frame is made of a tubular member, and the member is made of a carbon fiber composite material. (3) The deployable antenna reflector according to claim 1 or 2, wherein the length of the coupling wire is adjustable. (4) Claims 1 to 3, wherein the support wire is held with adjustable tension.
The deployable antenna reflector according to any of paragraphs. (5) The deployable antenna reflector according to any one of claims 1 to 4, wherein the hinge has a built-in bearing that can realize low friction conditions. (6) The deployable antenna reflector according to claim 5, wherein the bearing built into the hinge is a spherical bearing. (7) The deployable antenna reflector according to any one of claims 1 to 6, wherein a part of the loop cable is formed of a coil spring.