JP2005082092A - Deployment space structure - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a large deployment space structure not restricted by the height of a storage space of a launch rocket. <P>SOLUTION: In the deployment space structure provided with a deployment truss, the deployment truss is provided with a planar link mechanism that is expandable/contractable relative to the arrangement direction of the expansion/contraction element 2 by providing a plurality of expansion/contraction elements 2 composed of at least two beams 2a rotatably connected midway respectively in a row in parallel and rotatably connecting both ends of the beams 2a of the adjacent expansion/contraction element 2 to each other with a hinge 3. <P>COPYRIGHT: (C)2005,JPO&NCIPI

Description

  The present invention relates to a deployable space structure that can be folded in a small space and stored in a rocket and deployed and used in outer space.

  As a method for constructing a large structure such as an antenna reflector in outer space, a structure in which the structure is folded in a small size and stored in a launch rocket and deployed again in outer space is known. In this method, a deployment truss that is easy to fold during storage and easy to deploy during construction is often used as the frame structure that constitutes the structure.

  FIG. 12 is a perspective view showing a configuration of a deployment truss used as a framework structure in a conventional deployment space structure.

  As shown in FIG. 12, this deployment truss is composed of six planar mechanisms 100. These planar mechanisms 100 include an upper member 101, a lower member 102, a vertical member 103, an oblique member 104, and a center member 105 that are rotatably connected.

  Each planar mechanism 100 shares a central member 105 and is equally distributed radially around the central member 105. By sliding the central member 105 along its axis, the planar mechanism 100 is stored and deployed. It has become.

  A configuration in which six flat link mechanisms that can expand and contract in the axial direction are radially arranged as a deployment truss is also known. In this configuration, the development truss is stored and deployed by driving the plurality of planar link mechanisms to extend and contract.

An annular cable disposed around the deploying truss is used for expansion and contraction driving of the planar link mechanism. This cable is movably connected to the tip of each planar link mechanism, and the planar link mechanism is extended and contracted in synchronization by adjusting the winding amount of the cable by the rotation of the motor. (For example, refer nonpatent literature 1.).
Proceedings of the 42nd Space Chemistry Technology Joint Lecture Meeting (October 28, 1998) (Pages 255 to 262, "Experimental Module Coupling of Large Mesh Antenna")

  However, the unfolded truss with the conventional configuration has a complicated frame structure and cannot be folded small. For this reason, the size of the deployment space structure has been limited by the size of the launch rocket storage space.

  The present invention has been made in view of the above circumstances, and an object of the present invention is to provide a large deployment space structure that is not limited by the size of the launch rocket storage space.

  In order to solve the above problems and achieve the object, the deployable space structure of the present invention is configured as follows.

(1) In a deployable space structure provided with a deployable truss, the deployable truss has a plurality of extendable elements formed by connecting at least two beams so as to be rotatable in the middle of each other in a row and adjacent to each other. A planar link mechanism is provided which is capable of expanding and contracting in the direction in which the expansion and contraction elements are juxtaposed by connecting both ends of the beams of the expansion and contraction elements in a rotatable manner by connecting means.

(2) The deployable space structure described in (1), wherein a rope body is disposed around the deployable truss, and the rope body is movably connected to the ends of the beams. The length of the striated body is adjusted by an adjusting means, so that the expansion truss is expanded and contracted in the direction in which the expansion and contraction elements are arranged.

(3) The deployable space structure described in (2), wherein the adjusting means includes a motor and a rotating body that is rotated by the motor and advances and retracts the strip in the longitudinal direction. It is characterized by that.

(3) The expanded space structure described in (1), wherein the connecting portions of the beams connected by the connecting means are connected by a bending member that is bent toward the axial center line side of the expanding truss. It is characterized by.

  According to the present invention, a large deployment space structure can be accommodated in a launch vehicle without being limited by the height of the storage space.

  The best mode for carrying out the present invention will be described below with reference to the drawings.

  First, a first embodiment of the present invention will be described with reference to FIGS.

  FIG. 1 is a schematic diagram showing a configuration of a first planar link mechanism according to the first embodiment of the present invention, and FIG. 2 is a schematic diagram showing a state in which the first planar link mechanism according to the embodiment is extended. FIG. 3 is a schematic view showing a state in which the first planar link mechanism according to the embodiment is contracted.

  As shown in FIG. 1, each first planar link mechanism 1 is composed of a plurality of expansion elements 2 arranged in a line. Each telescopic element 2 has two beam members 2a having the same length, and these beam members 2a are connected to each other so as to be rotatable. The ends of the beam members 2a of the adjacent expansion / contraction elements 2 are rotatably connected by hinges (not shown), and by changing the length a with respect to the direction orthogonal to the parallel arrangement direction of the expansion / contraction elements 2, As shown in FIGS. 2 and 3, the first planar link mechanism 1 can be expanded and contracted in the parallel arrangement direction.

  FIG. 4 is a perspective view showing a configuration of a deployment truss configured by the first planar link mechanism according to the embodiment.

  As shown in FIG. 4, a deployment truss T that supports a deployment space structure such as a deployment antenna can be configured by combining a plurality of the first planar link mechanisms 1 configured as described above, six in the present embodiment. it can. These first planar link mechanisms 1 are equally distributed radially around the connecting body 10 by connecting one end portion thereof to the connecting body 10.

  The connecting body 21 has two discs 22 arranged to face each other, and the discs 22 are connected by a connecting member 23. The connecting member 23 is configured to be extendable / contractable in the axial direction, and the connecting member 23 is extended / contracted by a driving device (not shown) to increase the distance between the two disks 22. Can change.

  The ends of the two beam members 2a disposed at one end of each first planar link mechanism 1 are rotatably connected to the outer periphery of each disk 22 by hinges 3, respectively, and are rotated by a drive device. By changing the distance between the plates 22, all the first planar link mechanisms 1 can be expanded and contracted in synchronization.

  When constructing a deployment space structure such as a deployment antenna in outer space, as shown in FIG. 3, the deployment space structure is folded small by contracting each first planar link mechanism 1. Then, after the folded unfolded space structure is launched and transported to space by a rocket, the unfolded space structure is unfolded by extending each first planar link mechanism 1 as shown in FIG.

  According to the deployment space structure having the above-described configuration, the first planar link mechanism 1 constituting the deployment truss is configured to be extendable and contractable by the plurality of extension elements 2.

  Therefore, regardless of the size of the deployed space structure, the height dimension of the deployed truss at the time of storage can be suppressed to the same level as the length dimension of the beam material 2a. By setting to, a large deployment space structure can be accommodated in the launch vehicle without being restricted by the height of the accommodation space.

  In addition, since the deployable truss is composed of the expansion and contraction element 2 having the same configuration, a large deployable space structure can be constructed with a simple configuration.

  Next, a second embodiment of the present invention will be described with reference to FIGS. In addition, about the same structure as 1st Embodiment, the same code | symbol is attached | subjected and the description is abbreviate | omitted.

  FIG. 5 is a schematic diagram illustrating a state in which the second planar link mechanism according to the second embodiment of the present invention is extended, and FIG. 6 is a diagram in the middle of extending the second planar link mechanism according to the same embodiment. FIG. 7 is a schematic diagram showing a state in which the second planar link mechanism according to the embodiment is contracted, and FIG. 8 is a motor and cable according to the embodiment. It is the schematic which shows the structure of these.

  As shown in FIGS. 5 to 8, the second planar link mechanism 11 according to the present embodiment is obtained by hanging a cable 12 around the planar link mechanism 1 according to the first embodiment. The cable 12 is movably connected to a hinge 3 provided at the end of each beam member 2a, and the flat link mechanism 11 can be expanded and contracted by winding and feeding the cable 12 by a motor 13. It has become. Therefore, it is possible to easily and quickly deploy a space structure in space without relying on human hands.

  Next, a third embodiment of the present invention will be described with reference to FIGS. In addition, about the same structure as 1st, 2nd embodiment, the same code | symbol is attached | subjected and the description is abbreviate | omitted.

  FIG. 9 is a schematic view showing a state in which the third planar link mechanism according to the third embodiment of the present invention is extended. FIG. 10 is a diagram in the middle of extending the third planar link mechanism according to the embodiment. Or it is the schematic which shows the state in the middle of shrinking, FIG. 11 is the schematic which shows the state in the middle of shrinking the 3rd plane link mechanism which concerns on the embodiment.

  As shown in FIGS. 9-11, the 3rd plane link mechanism 21 which concerns on this Embodiment is a bending member between the front-end | tip parts of each beam material 2a which comprises the expansion-contraction element 2 which concerns on 1st Embodiment. 22 is connected. The bent member 22 is configured to be bent inward in the vicinity of the central portion thereof, and both end portions thereof are rotatably connected to the hinge 3 provided at the distal end portion of the beam member 2a. For this reason, when the deployment truss is deployed, the third planar link mechanism 21 is restricted from extending beyond a predetermined length, and thus each third a that occurs when the distance a becomes smaller than a predetermined value. A decrease in the rigidity of the planar link mechanism 21 can be prevented.

  Note that the present invention is not limited to the above-described embodiment as it is, and can be embodied by modifying the constituent elements without departing from the scope of the invention in the implementation stage. Further, various inventions can be formed by appropriately combining a plurality of constituent elements disclosed in the embodiment. For example, some components may be deleted from all the components shown in the embodiment. Furthermore, you may combine suitably the component covering different embodiment.

Schematic which shows the state which extended the 1st plane link mechanism which concerns on the 1st Embodiment of this invention. Schematic which shows the state in the middle of extending the 1st plane link mechanism which concerns on the embodiment, or the state in the middle of shrinking. Schematic which shows the state which shrunk | reduced the 1st plane link mechanism which concerns on the embodiment. The perspective view which shows the structure of the expansion | deployment truss comprised by the 1st planar link mechanism which concerns on the embodiment. Schematic which shows the state which extended the 2nd plane link mechanism which concerns on the 2nd Embodiment of this invention. Schematic which shows the state in the middle of extending the 2nd plane link mechanism which concerns on the embodiment, or the state in the middle of shrinking. Schematic which shows the state which shrunk | reduced the 2nd plane link mechanism which concerns on the embodiment. Schematic which shows the structure of the motor and cable which concern on the same embodiment. Schematic which shows the state which extended the 3rd plane link mechanism which concerns on the 3rd Embodiment of this invention. Schematic which shows the state in the middle of extending the 3rd plane link mechanism which concerns on the same embodiment, or shrinking. Schematic which shows the state in the middle of contracting the 3rd plane link mechanism which concerns on the embodiment. The perspective view which shows the structure of the expansion | deployment truss used as the frame structure in the conventional expansion | deployment space structure.

Explanation of symbols

  DESCRIPTION OF SYMBOLS 1 ... 1st plane link mechanism, 2 ... Expansion / contraction element, 2a ... Beam material (beam), 3 ... Hinge (connection means), 11 ... 2nd plane link mechanism, 12 ... Cable, 13 ... Motor (adjustment means) , 21 ... a third planar link mechanism, 22 ... a bent member.

Claims (4)

In a deployable space structure with a deployable truss,
The above deployment truss
A plurality of expansion / contraction elements formed by connecting at least two beams rotatably in the middle of each other are arranged in a line, and both ends of the beams of adjacent expansion / contraction elements are connected to each other by connecting means so as to be rotatable. A deployable space structure comprising a planar link mechanism capable of expanding and contracting in the direction in which the expansion elements are arranged side by side.   By arranging a rope body around the deployment truss, connecting the rope body to the end of each beam movably, and adjusting the length of the rope body by an adjusting means, 2. The deployable space structure according to claim 1, wherein the deployable truss is expanded and contracted in a direction in which the expandable elements are juxtaposed. The adjusting means is
A motor,
A rotating body that is rotated by this motor and advances and retracts the strip body in the longitudinal direction;
The expanded space structure according to claim 2, comprising:   2. The expanded space structure according to claim 1, wherein the connecting portions of the beams connected by the connecting means are connected by a bending member that is bent toward the axial center line side of the expanding truss.

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