JPH0767045B2 - Deployable antenna reflector - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention is developed such that, for example, an antenna mounted on an artificial satellite is folded and stored small when it is transported to orbit by a rocket or the like, and is expanded when used to form a predetermined shape. Shaped antenna reflector.

FIG. 1 is a diagram showing an example of a conventional deployable antenna reflector, (a) is a perspective view showing a state in which a partial mirror surface shell is folded and stored, and (b) is a mirror surface when deployed. FIG.

In FIG. 1, 1 and 2 are partial mirror shells, 3 is a partial mirror shell 1
And the partial mirror surface shell 2 are connected by a hinge, 4 is a support structure connected to the partial mirror surface shell 2, and 5 is a deployment mechanism in which the entire reflecting mirror is attached to the main body of an artificial satellite or the like. 1 and 2 have a San-Gerache structure with strength, and a supporting structure 4 for supporting the entire antenna is directly attached to the partial mirror shell 2.

In the case of such a conventional structure, since the partial mirror surface shell itself becomes larger as the opening diameter becomes larger, it is difficult to form the Saint-Gerache molding technology for realizing a high-precision mirror surface, and the required rigidity of the mirror surface shell itself is required. Since it is necessary to increase the thickness of the San-Gerache structure, it is unavoidable that the structure becomes heavy.

As described above, in the conventional antenna reflecting mirror of this type, the reflecting mirror surface shell itself is provided with necessary strength to maintain the required shape of the reflecting mirror surface due to its rigidity, and the antenna reflecting mirror can be deployed and expanded. The structure was such that the fixing and mounting mechanisms were directly attached to the reflector shell.

For this reason, the reflector mirror shell is made to have a Saint-Gerache structure, etc., but it is designed to maintain rigidity, but the strength required for supporting the entire antenna depends on the reflector shell.
It is necessary for the reflecting mirror shell to have a solid structure, and it is difficult to reduce the weight of a large reflecting mirror or the like.

Further, in order to improve the precision of the mirror surface, it is necessary to precisely form the reflecting mirror shell, and therefore, there is a drawback in that it is difficult to manufacture because it requires high technology.

In order to solve these drawbacks, the present invention provides the entire antenna with rigidity and strength in a frame structure different from the mirror surface, and the reflecting mirror is made into a thin shell and is connected to the frame structure by a position-adjustable connecting part, and then deployed. The mechanism, fixing mechanism, etc. are arranged in the frame structure, and in particular, shape errors during manufacturing of thin-walled reflecting mirrors can be corrected when assembled in the frame structure, resulting in high mirror surface accuracy and rigidity as a whole. It is intended to provide a lightweight and large-sized deployable antenna reflector.

Embodiments of the present invention will be described in detail below with reference to the drawings.

2 and 3 are views showing an embodiment of the present invention, showing a case of a three-fold type deployable antenna reflector similar to the conventional example shown in FIG.

FIG. 2 (a) is a perspective view when stored, FIG. 2 (b) is a perspective view when unfolded, FIG. 3 (a) is a side view, and FIG. 3 (b) is a rear view. 6 to 10 are reflective materials, 11 and 12 are frame structures, 13 and 14 are hinges, 15 is a fixing mechanism, 16 is a deployment mechanism, 17
Is a main body such as an artificial satellite.

The reflectors 6 to 10 each have a thin-walled shell shape, and the entire reflecting surface is formed by connecting these reflectors. The reflectors 6 and 7 are the frame structure 11, and the reflectors 8, 9 and 10 are the frame. Each structure 12 is adjusted and assembled to have the best mirror surface precision. The skeleton structures 11 and 12 are connected via hinges 13 and 14, can rotate about a straight line passing through the hinges 13 and 14, and are folded as shown in FIG. At the time of use, it is expanded to the state shown in FIG. 2 (b) by the force of the springs incorporated in the hinges 13 and 14. When expanded to a predetermined position, the frame structures 11 and 12 are joined by the fixing mechanism 15 to form an integrated frame structure.

The entire reflecting mirror is attached to a main body 17 such as an artificial satellite via a deployment mechanism 16.

FIG. 4 is a view showing another embodiment of the present invention, which is an example having a frame structure different in shape from those shown in FIGS. 2 and 3, and (a) is a side view at the time of storage. FIG. 6 (b) is a rear view at the time of deployment and FIG. 6 (c) is a sectional view at the time of deployment.
~ 10 and 13 ~ 17 are the same as in Fig. 2 or Fig. 3,
1'denotes a skeleton structure of a folded portion, 12 'denotes a skeleton structure of a central portion, and 18 denotes a stopper.

The stopper 18 has a link structure and is bent as shown in FIG. 4 (a) when it is stored, but when it is deployed, it extends and functions as a stopper as shown in FIG. 4 (c).

The reflectors 6 to 10 are adjusted and attached to the frame structure 11 'or 12' so as to maintain the mirror surface precision, as in the case of the embodiment shown in FIGS.

Whether the shape of the frame structure is as shown in FIG. 3, as shown in FIG. 4, or another shape depends on external load conditions and rigidity of the entire reflector. It may be appropriately selected in consideration of the conditions, weight, size restrictions, and the like.

5A and 5B are views showing an embodiment of the connecting portion of the reflector and the frame structure according to the present invention, FIG. 5A is a perspective view, and FIG. In FIG. 5, a metal fitting having a spherical projection at the tip
19 is adhered to the reflection material 28, and further, the overlay material 20 is adhered and reinforced. The spherical portion is grasped by the quarter bolt 21 and the ring 22 is pushed by the nut 23 to tighten the quarter bolt 21. The quarter bolt 21 is fixed to the base metal fitting 26 by nuts 24 and 25, and the base metal fitting 26 has a frame structure.
It is fixed to 29 with screws 27.

The holes for bolts and screws formed in the base metal fitting 26 are elongated holes that can be adjusted in two orthogonal directions, as shown in FIG. 5 (a). Is adjustable by nuts 24 and 25.

Further, since the metal fitting 19 having the spherical projection at the tip can change the axial direction within a certain range when the spherical portion at the tip is fastened with a quarter bolt, the angle between the reflector 28 and the frame structure 29 can be changed. Can be adjusted.

As described above, the present invention has a structure in which a thin-walled reflective material is assembled to a frame structure that can be folded and deployed, and therefore the reflection surface itself can be made lighter, and the frame structure also makes it lightweight and highly rigid. Can be secured.

Furthermore, each thin-walled reflective material can be manufactured with a relatively small size compared to the size of the entire reflecting mirror, so that each can be manufactured with high precision and assembled into a frame structure. In the attaching step, there is an advantage that the entire structure can be configured while adjusting the mirror surface accuracy of the entire reflective mirror surface to be high.

[Brief description of drawings]

FIG. 1 is a diagram showing an example of a conventional deployable antenna reflector,
2 and 3 are views showing an embodiment of the present invention, FIG. 4 is a view showing another embodiment of the present invention, and FIG. 5 is a view showing a connecting portion between a reflector and a frame structure according to the present invention. It is a figure which shows an Example. 1,2 …… Partial mirror shell, 3,13,14 …… Hinge, 4 …… Support structure, 5,16 …… Deployment mechanism, 6,7,8,9,10,28 …… Reflecting material, 11,
11 ′, 12,12 ′, 29 …… Frame structure, 15 …… Fixing mechanism, 17…
… Main body of artificial satellite, 18 …… Stopper, 19 …… Metal fitting with spherical projection at the tip, 20 …… Overlay material, 21 …… Quarter bolt, 22 …… Ring, 23,24,25 …… Natsu, 26
…… Stand metal, 27 …… Screw

Claims (1)

[Claims] 1. A reflecting mirror formed by connecting a plurality of partial mirror surface shells, and a frame structure formed by folding a plurality of sets of fixed-shape frames so that they can be folded. A deployable antenna reflector, wherein the partial mirror shell that constitutes the reflector is attached by a member having a structure capable of adjusting the relative position between the two.