JP2003276693A - Space structural body - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To easily assemble a space structural body after launching into the space. <P>SOLUTION: The structural body 1 is a triangular shape formed of a thin plate-like structural material, and launched into the space by a rocket as a contracted shape with structural bodies successively smaller in the order of 1a, 1b, 1c, 1d and 1e as shown in (a) accommodated therein. After the structural body is launched in the space, it is assembled in one structural body 1 as shown in (c), or in a long shape with two structural bodies 1 joined with each other at a joining part 2 as shown in (b). Base parts of four structural bodies 1 are inserted in a connection part 3 of the structural body as shown in (d), four reflecting mirrors 50 are fitted as shown in (e), and the structural body to receive the solar beam and collect the light to a power generation unit is constituted. The assembly is easy because the structural body 1 can be formed only by being drawn. <P>COPYRIGHT: (C)2004,JPO

Description

Detailed Description of the Invention

[0001]

TECHNICAL FIELD The present invention relates to a space structure,
In particular, it is a structure for mounting a circular structure such as an antenna or a reflecting mirror of a space station, a solar power generation satellite, a space telescope, an artificial satellite or the like in outer space, which facilitates assembly.

[0002]

2. Description of the Related Art At present, photovoltaic power generation is attracting attention as an energy source of the future, and a system for launching a photovoltaic power generation satellite into space to generate electric power and transmitting the generated electric power to the earth has been studied. And various plans have been announced. FIG. 8 outlines the concept of a solar power generation satellite in space.

In FIG. 8, connecting portions 52 are attached to both ends of the support column 51, and a plurality of rod-shaped structures 55 (four in the figure) are attached to the connecting portions 52. Each of the four structures 55 has three reflecting mirrors 50 (concentrators).
Is installed. The reflecting mirror 50 has a concave surface, and the concave surface is a mirror surface, which receives sunlight and reflects the light rays so as to concentrate the light rays on a predetermined point. Two power generators 53a and 53b are attached to the center of the column 51,
Power generation elements are embedded in the entire surfaces of the power generation units 53a and 53b and receive sunlight to generate power. Power generation unit 5
3a receives the sun rays from the group of the reflecting mirrors 50 on one side (lower reflecting mirror in the figure), and the power generation unit 53b receives the sun rays from the group of the reflecting mirrors 50 on the other side. Power generation section 53a, 53
The electric power generated in b is sent to the electric power transmission unit 54 and converted into an electromagnetic wave, and the converted electromagnetic wave is transmitted from the power transmission antenna 56 to the earth as an electromagnetic wave. The transmitted electromagnetic waves are received by an antenna on the earth (not shown) and converted into electric power. Each structural component of such a power generation satellite is launched into space by a space shuttle or the like and assembled in space.

[0004]

The solar power generation satellite as described above is assembled by an astronaut in space or by a work robot by launching each component constituting the satellite with a rocket. Therefore, assembling in space is required to be as simple as possible, and it is necessary to adopt a structure and mechanism that facilitates assembling each component. Particularly, the reflector 50 as shown in FIG.
A large size of 00m is planned, and the rod-shaped structure to which this is attached is also a long shape with a diameter of several meters. It is necessary to launch it as a split structure to launch it with a space shuttle, etc. It has been an issue to simplify the work such as mounting the reflecting mirror.

Therefore, the present invention has a rod-shaped structure for facilitating the assembly in space of a rod-shaped structure for mounting a reflector of a solar power generation satellite, a parabolic antenna used in a satellite such as a space station, etc. The body is reduced in shape when launched by a rocket, extended and stretched during assembly in space after launch to form a structure of a specified length, and a rod-shaped structure is joined to form a large cross section It was made for the purpose of providing a space structure that can be used as a body.

[0006]

The present invention provides the following means in order to solve the above-mentioned problems.

(1) An internal structure having an outer shape smaller than that of the cylindrical structure is inserted slidably in an axial direction inside a structure having a predetermined length, and a plurality of the internal structures are sequentially multiplexed. A multi-structure is formed by arranging them, and pushing means for moving the internal structure forward on the bottom surface of each structure constituting the multiple structure and a stopper for locking the internal structure at the tip. The multiple structure is in a contracted state during transportation and in a stretched state during assembly, and is a structure for arranging devices such as a plurality of reflecting mirrors in the axial direction. Space structure to do.

(2) The space structure according to (1), wherein the multi-structure has a triangular cross-section.

(3) The space structure according to (1), wherein the cross-sectional shape of the multiple structure is a quadrangular shape.

(4) The space structure according to (1), wherein the cross-sectional shape of the multiple structure is circular or elliptical.

(5) A part of each surface of the cross-sectional shape of the multiple structure or a side surface in the longitudinal direction is formed of a truss member, according to any one of (1) to (4). Space structure.

(6) The space structure according to any one of (1) to (5), wherein the pushing means is a gas generator.

(7) The space structure according to any one of (1) to (5), wherein the pushing means is a spring, and the elastic force of the spring pushes out the internal structure.

(8) In any one of (1) to (7), the multiple structure includes a plurality of multiple structures, and the multiple structures are connected by a connecting portion that radially supports the base of each multiple structure. The described space structure.

(9) The space structure according to (8), characterized in that the support of the base of the multiple structure of the connecting portion is supported by pressing the tip of the pin by the elastic force of the spring.

(10) One rod-shaped structure is formed by using four unit structures each having a tubular shape and a right-angled isosceles triangle in cross section and having a predetermined length. A space structure characterized in that the two vertexes of the unit structure are joined so as to form a ring and the cross section constitutes a regular quadrangle.

(11) A rod-shaped structure is formed by using eight unit structures having a tubular shape and a right-angled isosceles triangle in cross section and having a predetermined length. The two unit structures are joined to form a combined structure that forms a right-angled isosceles triangle, and each vertex of the four combined structures is connected so as to form a ring, and the cross section forms a regular quadrangle. Space structure characterized by.

According to the first aspect of the present invention, when the space structure is launched into space, the multi-structure is carried in a reduced state, and when the space structure is assembled in space, the pushing means is operated to operate the multi-structure. Stretch it into a long shape. Each internal structure is moved forward by the pushing means, and the bottom part thereof is locked by the stopper part provided at the tip of the outer structure so that the entire internal structure can be stretched into a rod shape.
Devices such as a plurality of reflecting mirrors are attached to the structure extended in the rod shape in the longitudinal direction. With such a structure, the volume can be reduced when launched into space, and the work of assembling the structure in space is facilitated.

In (2) of the present invention, the cross-sectional shape of the structure is a triangle, in (3) a quadrangular shape, in (4) a circular or elliptical shape, and in (5) each side of the cross section or the longitudinal side surface. Since the structure is formed by the truss member, the strength can be improved and the weight can be reduced. Further, in (6) of the present invention, the extruding means is a method of extruding the internal structure by the pressure of the gas generated by the gas generator,
Further, in the invention of (7), the elastic force of the spring is used, and both of them operate reliably when the multiple structure is extended, and the assembling work is simplified.

In (8) of the present invention, since the space structure is constructed by connecting a plurality of multiple structures as a structure that extends radially at the connecting portion, it is possible to attach many devices such as reflecting mirrors. It is possible to construct a large-scale space structure and expand its application range.

In (9) of the present invention, the method of supporting the base portion of the structure by the connecting portion of the invention of (8) is performed by pressing the tip of the pin by the elastic force of the spring, so that the connecting portion of the structure is connected to the connecting portion. Only by inserting the base, reliable support can be realized with a simple mechanism.

In (10) of the present invention, four unit structure bodies are combined and joined, and in (11), eight unit structure bodies are combined and joined to form one regular square space structure. , Such as a solar power generation satellite, can be applied as a structure such as a pillar that supports the above-mentioned structure that supports many reflecting mirrors at both ends, and such a large pillar supports a unit structure. It can be realized by Further, since the unit structure can also have a volume and shape suitable for launching into space by a rocket or the like, it can be easily transported.

[0023]

BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of the present invention will be specifically described below with reference to the drawings. 1A and 1B show a space structure according to a first embodiment of the present invention. FIG. 1A is a reduced state, FIG. 1B is an extended state and two are joined, and FIG. 1C is an extended state. And (d) are plan views showing a state in which a reflecting mirror is mounted, and (e) is a view taken along the line A-A in (d).

In the figure, (a) shows a structure 1 having a structure in which five structures are sequentially expanded and contracted so as to be contracted.
(B) is sequentially expanded, and the base structure 1a, the second structure 1b, the third structure 1c, and the fourth structure 1a are shown.
d, the fifth structure, that is, the tip 1e, respectively, and two of the extended structures 1 are joined to each other at the joining portion 2 at the tip structure 1e. Further, (c) shows a case where one extended structure 1 is used. As will be described later, the shape of this structure is formed of a thin structural material,
The external cross-sectional shape is triangular.

The shape is not limited to the triangular shape,
It may have a quadrangular shape, a circular shape, or an elliptical shape, and, for example, one or both of the bottom surface portion or the side surface in the length direction of each structure 1a to 1e is formed of a truss member so that it can be stretched and accommodated in multiple layers. May be.

In (d), 1 in (c) above
It is a top view which assembled the structure 1 which the book extended and installed the reflecting mirror. In the figure, reference numeral 3 denotes a connecting portion of structures to be described later, in which four structures 1 are connected in a cross shape, and four reflecting mirrors 50 are mounted on each structure 1. The connection to the structure connecting portion 3 is made by inserting the structure 1 as will be described later, and the reflecting mirror 50 is mounted as follows.
As shown in (d), the bottom surface of the concave reflecting mirror is attached by adhesion or the like.

Assembling and mounting operations such as stretching the structure 1 described above, mounting the structure 1 to the connecting portion 3, mounting the reflecting mirror 50 to the structure 1, etc. After being launched into space by, etc., it is assembled in space by an astronaut and a work robot, and is assembled as a satellite having a plurality of reflecting mirrors at both ends of the support as shown in FIG.

2A and 2B show details of the structure 1 according to the first embodiment of the present invention. FIG. 2A is a sectional view in a state of being reduced and stored, FIG. 2B is a side view, and FIG. ) In B-
It is a B sectional view. In these figures, the structure 1 has a hollow triangular cross-section, and the material is a thin plate having a thickness of about 1 cm formed of a structural material or the like. Its outer shape is about 4 to 5 m on a side of a triangle,
The length of the extension is as long as several hundred meters.
Further, the outer shape is not limited to the triangular shape, and may be, for example, a quadrangular shape or a round shape, but a triangular shape is preferable in consideration of weight, strength, workability and the like. If a guide member is provided in the axial direction and the member is stretched along the guide member in order to facilitate the stretching, more accurate movement is possible.

In FIG. 2, the triangular structure 1 is 1
a, 1b, 1c, 1d, 1e, the outer shape of which gradually becomes smaller, and the outer shape of which is successively smaller is accommodated inside, and the overall size of the outermost 1a is slightly larger than the reduced size. It has a structure. In addition, the structure 1a-
Inside the tip of 1e, stopper portions 4a, 4b, 4c, 4d that project over the entire circumference of a triangular shape are provided,
As will be described later, they serve as stoppers by engaging with protrusions on the bottom surface of the structure housed inside when they are stretched.

Reference numerals 5a, 5b, 5c, 5d and 5e are bottom plates of the structures 1a, 1b, 1c, 1d and 1e, respectively.
Except for the bottom plate 5a, it has protrusions 6b, 6c, 6d, and 6e all around the circumference, and when extended, prevents contact with the stoppers of the outer structures and separation from the tips of the outer structures. Have the function to Reference numeral 8 denotes a lid on the tip surface of the innermost structure 1e. 7a to 7d are gas generators,
7a is inside the bottom plate 5a of the structure 1a, and 7b is the structure 1
Inside the bottom plate 5b of b, 7c is attached inside the bottom plate 5c of the structure 1c, and 7d is attached inside the bottom plate 5d of the structure 1d, respectively.

These gas generators 7a, 7b, 7c, 7
d is an external bottom plate 5a and 7a, 7b, 7c,
By heating the outer periphery of the attachment portion of 7d from the outside of the structure 1a, gas is generated by vaporization, and the interior of the sealed space is pressurized, whereby the respective structures 1b, 1
The c, 1d, and 1e project to the outside and extend as shown in FIG. 1 (c) to form the elongated structure 1.

FIG. 3 shows the structure 1 according to the first embodiment of the present invention.
FIG. 6 is a detailed cross-sectional view of a stretched state. As shown in the figure, the structure 1b in the structure 1a is pushed outward by the gas pressure of the gas generator 7a, and the protrusion 6b around the outer periphery of the bottom plate 5b of the structure 1a has the stopper 4a at the tip of the structure 1a.
And then come to rest at this position. Similarly, the structures 1c in the structure 1b, 1d in the structure 1c, and 1e of 1d are extruded toward the outside, respectively, and the protruding portions 6c of 1c are the stopper portions 4b and the protruding portions 6d of 1d are the stopper portions. 4c
Then, the protruding portion 6e of 1e collides with the stopper portion 4d to stop the movement of each structural body, and the structural body 1 elongated as shown in FIG. 1C is completed.

FIG. 4 shows the details of the connecting portion of the space structure according to the first embodiment described above, (a) is a side view,
(B) is CC sectional drawing in (a). In (a), the connecting portions are attached to both ends of the column 51 as shown in FIG. Triangular grooves 12a are provided on four side surfaces of the connecting portion 3 in the orthogonal direction, and circular grooves 12b are provided on the upper surface and the lower surface of the groove 12a.

The groove 12a has a shape slightly larger than the base of the structure 1, and the base of the triangular structure 1 is inserted therein. A spring 13 is mounted in the groove 12b,
The pin 14 is arranged so as to urge the pin 14 into the groove 12b, and when the structure 1 is inserted, the structure 1 can be slid on the inclined surface of the pin 14 and can be inserted. The surface of the structure 1 after being stationary is pressed by a predetermined pressing force of the spring 13 and is pressed against the surface by a sharp tip portion, and the structure 1 is fixed so as not to separate.

(B) is a view taken along the line C--C of (a), showing the same triangular shape in the triangular groove 12a.
A slightly smaller structure 1 is inserted, and circular grooves 12b are provided above and below the connecting portion 3. Groove 1
A spring 13 is attached to the bottom of the back of 2b, has an inclined surface toward the tip, and biases the pin 14 having a sharp tip with its elastic force so that the tip of the pin 14 causes the surface of the structure 1 to move. The structure 1 is fixed by pressing it to such an extent that it is plastically deformed so that the structure 1 does not come out of the groove 12a.

FIGS. 5A and 5B are views showing the action of the pin 14 described above. FIG. 5A shows a state in which the structure 1 is not inserted, and FIG. 5B shows a state in which the structure is inserted. It is a side view. As shown in (a), the structure 1 has the connecting portion 3
Before being inserted into the groove 12a, the pin 14 is biased by the spring 13 so that the tip portion projects from the groove 12b into the groove 12a. As shown in (b), when the structure 1 is inserted, the inclined surface of the protruding pin 14 is changed to the structure 1.
Since an inclined surface that forms an acute angle with the plane of is formed, the pin 14 can be pushed by the structure 1 against the elastic force of the spring 13 and easily drawn into the groove 12b. 1 can be inserted by sliding with the tip of the pin 14.

When the structure 1 tries to move in the opposite pulling direction, the sharp tip 15 of the pin 14 is pressed by the spring 13 in the direction orthogonal to the structure 1, so that the structure 1 is pulled out from the groove 12a. You will be prevented from being struck. Although it is assumed that the structure 1 has to be pulled out from the groove 12a for some reason after the structure 1 is connected to the groove 12a of the connecting portion 3, in this case, although not shown, for example, a circular shape is used. A plug is provided so that the upper surface of the groove 12b is opened from the outer surface of the connecting portion 3 so that the spring 13 and the pin 14 can be taken out for repair or replacement, and the plug can be removed to open the groove 12b from the outer surface. Preferably.

According to the first embodiment of the above description, the structure 1a, 1b, 1c, 1d, 1e is sequentially inserted into the inside to form a reduced multiple structure, and the space shuttle is used to enter the universe. Launching and stretching in space to form a long structure 1, and by inserting the base of the long structure 1 into the groove 12a of the connecting portion 3, the four structures 1 are connected to each other. Can be easily connected and assembled. After that, since a plurality of reflecting mirrors 50 are attached as shown in FIGS. 1D and 1E, the solar power generation satellite can be easily assembled.

FIG. 6 shows a space structure according to a second embodiment of the present invention, (a) is a side view and (b) is a detailed sectional view. In the second embodiment, instead of extending the structure reduced by the gas generator shown in the first embodiment, a spring is used to mechanically extend the elastic structure of the spring. Other configurations are the same as those of the first embodiment shown in FIGS. 1 to 5.

That is, (a) is the springs 12a, 12
The b, 12c, and 12d are stretched, the elastic bodies force the respective structural bodies 1a to 1e to be extruded, and the inertial force is applied to the structural bodies 1a to 1e, thereby completely extending. (B) shows the details of the reduced structure 11, and the spring 12a is the structure 1a.
Inside the bottom plate 5a, 12b inside the bottom plate 5b of the structure 1b, 12c inside the bottom plate 5c of the structure 1c,
d is attached to the inside of the bottom plate 5d of the structure 1d.

At the time of contraction, the springs 12a to 12e are contracted in the state as shown in (b), and although not shown, the tip end structure 1e is fixed to the 1a side by a rope or the like and locked. It is launched into space in a state. After launching into space, unlocking this rope will push each structure by springs 12a-12d,
The structures 1b, 1c, 1d, and 1e project outward and extend as shown in FIG. 6A to form the elongated structure 1. Other structures and operations are the same as those of the first embodiment.

Also in the second embodiment described above, instead of the gas generators 7a, 7b, 7c, 7d, springs 12a, 12 which can be mechanically stretched are used.
Even in the configuration using b, 12c, and 12d, the same effect as that of the first embodiment described above can be obtained, and there is no malfunction of the gas generators 7a to 7d, etc. Various operations are possible.

In the first and second embodiments described above, an example is shown in which four structures 1 and 11 are connected to the connecting portion in a four-cross shape, but the present invention is not limited to this example. It goes without saying that a plurality of connecting portions 3 may be provided radially in a range allowed by design.

FIG. 7 shows a space structure according to a third embodiment of the present invention, showing a structure applicable to the support column 51 shown in FIG. 8, and FIG. 7A shows a single unit structure 21, which is illustrated. Not have a triangular outer cross-section with a certain length,
It is formed from a thin plate of structural material. (B) shows a cross-sectional shape of the unit structure 21 when two unit back surfaces are combined and transported by a rocket or the like, and (c) and (d) are pillars having a rectangular cross section as a whole by combining the unit structures. 31,
It is the figure which constituted 32.

That is, in (a), a unit structure having a right-angled isosceles triangular cross-section having an angle of 90 degrees forming a half of a square is shown, and the length thereof is not shown. The length should be such that it can be carried. In (b), the size of the triangular bottom surface of the unit structure 21 is a large structure having a length of about 4 m, and naturally there is a space limitation in transporting this into a space using a rocket or the like. Therefore, as shown in (b), the unit structures 21 can be launched by a rocket in the forward direction with the back surfaces aligned to each other and in the shape of about 2.8 to 3 m square.

FIG. 6C is a sectional view showing the support column 31 assembled by the work after launching into space. As shown in the drawing, when two points of four right-angled isosceles triangles are joined to each other at a joining portion 8 to form a quadrangle at the bottom, two square sides of each unit structure 21 form a regular quadrangle. Can be formed. If one side of the regular square is, for example, 4 m at the bottom of the unit structure 21, one side orthogonal to each other is about 2.8 m, and one side of the regular square formed as a whole is about 2.8 × 2 = 5.6 m. Thus, the pillar 31 having a square cross-sectional shape of 5.6 m is formed.

Similarly, in (d), eight unit structures 21 are combined and their vertices are joined at the joining portion 8, and one side is 8
m square pillars 32 can also be formed, and the pillars 31, depending on the cross-sectional shape of the solar power generation satellite,
It is only necessary to select and adopt 32.

In the third embodiment described above, the unit structure 21 is set to a predetermined length, the back surfaces are aligned as shown in (b), and the unit structure 21 is launched into space by a rocket or the like. After being launched into space, as shown in (c) and (d), a plurality of unit structures 21 are joined at the joining portion 8 in the outer space to form the columns 31 or 32. A plurality of pillars 31 or 32 formed in this way are joined in the length direction, and pillars 51 supporting a plurality of reflecting mirrors 50 at both ends as shown in FIG. 8 are combined with a simple triangular unit structure. By doing so, it can be easily configured.

[0049]

EFFECTS OF THE INVENTION The space structure of the present invention is as follows: (1) An internal structure having a smaller outer shape than that of the structure is inserted slidably in an axial direction inside a cylindrical structure having a predetermined length, A plurality of the same internal structures are sequentially arranged to form one multiple structure,
The bottom surface of each structure forming the multiple structure is provided with a pushing means for moving the internal structure forward and a stopper portion for locking the internal structure at the tip, and the multiple structure is constructed when being transported. It is characterized in that it is in a contracted state and in an expanded state at the time of assembly, and has a structure for arranging a plurality of reflecting mirrors and other devices in the axial direction.

By the space structure described above, each internal structure is moved forward by the pushing means, and the bottom part thereof is locked by the stopper part provided at the tip of the outer structure, and the whole structure is rod-shaped. Can be extended to. Devices such as a plurality of reflecting mirrors are attached to the structure extended in the rod shape in the longitudinal direction. With such a structure, the volume can be reduced when launched into space, and the work of assembling the structure in space is facilitated.

In (2) of the present invention, the sectional shape of the structure is triangular, in (3) a quadrangular shape, in (4) a circular or elliptical shape, and in (5) each surface of the cross section or the side surface in the longitudinal direction. Is a structure formed by a truss member, and the strength can be improved and the weight can be reduced. or,
In (6) of the present invention, the extruding means is a method of extruding the internal structure by the pressure of the gas generated by the gas generator,
Further, in the invention of (7), the elastic force of the spring is utilized, and both of them operate reliably when the multiple structure is stretched, and the assembling work is simplified.

In (8) of the present invention, since the space structure is constructed by connecting a plurality of multiple structures as a structure that extends radially at the connecting portion, many reflecting mirrors and other equipment can be attached. It is possible to construct a large-scale space structure and expand its application range.

In (9) of the present invention, the method of supporting the base of the structure by the connecting portion of the invention of (8) is performed by pressing the tip of the pin by the elastic force of the spring, so that the connecting portion of the structure is connected to the connecting portion. Only by inserting the base, reliable support can be realized with a simple mechanism.

In (10) of the present invention, four unit structure bodies are combined and joined, and in (11), eight unit structure bodies are combined and joined to form one regular quadrangle space structure. , Such as a solar power generation satellite, can be applied as a structure such as a pillar that supports the above-mentioned structure that supports many reflecting mirrors at both ends, and such a large pillar supports a unit structure. It can be realized by Further, since the unit structure can also have a volume and shape suitable for launching into space by a rocket or the like, it can be easily transported.

[Brief description of drawings]

1A and 1B show a space structure according to a first embodiment of the present invention, in which FIG. 1A is a reduced structure, FIG. 1B is a structure in which two pieces are joined in an extended state, and FIG. 1C is one. 3D is a side view showing the structure of FIG. 4A, FIG. 7D is a plan view of a structure in which a reflecting mirror is attached, and FIG.

FIG. 2 shows a structure according to a first embodiment of the present invention,
(A) is sectional drawing of a structure, (b) is a side view, (c) is BB sectional drawing in (a).

FIG. 3 is a cross-sectional view showing a stretched state of the structure according to the first embodiment of the present invention.

FIG. 4 shows a structure connecting portion according to the first embodiment of the present invention, (a) is a side view, (b) is CC in (a).
FIG.

5A and 5B are explanatory views showing the connection between the structure connecting portion and the connection body according to the first embodiment of the present invention, FIG. 5A is a state in which the structure is not inserted, and FIG. The inserted states are shown respectively.

6A and 6B show a space structure according to a second embodiment of the present invention, where FIG. 6A is a sectional view of the structure in a stretched state and FIG.

FIG. 7 shows a space structure according to a third embodiment of the present invention, (a) is a sectional view of the basic structure, (b) is a sectional view of the basic structure at the time of launch by a rocket, ( c), (d)
3A and 3B are cross-sectional views in which a plurality of basic structures are joined to form a square pillar.

FIG. 8 is a conceptual diagram showing a photovoltaic power generation satellite in space.

[Explanation of symbols]

1,1a to 1e, 11 structures 2 joints 3 connection 8 joints 4a-4d stopper part 5a-5e bottom plate 6b to 6e protrusion 7a-7d Gas generator 12a-12b groove 13 spring 14 pin 15 Tip 21 unit structure 31,32 prop assembly 50 reflector

Claims (11)

[Claims] 1. An internal structure having a smaller outer shape than that of the cylindrical structure having a predetermined length is slidably inserted in the axial direction, and the internal structures are sequentially arranged in multiple layers. One structure is provided to form one multiple structure, and pushing means for moving the internal structure forward is provided on the bottom surface of each structure constituting the multiple structure, and a stopper portion for locking the internal structure at the tip. Is provided, and the multiple structure is in a contracted state during transportation and in a stretched state during assembly, and is a structure for arranging a plurality of reflecting mirrors and other devices in the axial direction. Space structure. 2. The space structure according to claim 1, wherein a cross-sectional shape of the multiple structure is triangular. 3. The space structure according to claim 1, wherein the cross-sectional shape of the multiple structure is a quadrangular shape. 4. The space structure according to claim 1, wherein the cross-sectional shape of the multiple structure is circular or elliptical. 5. The space structure according to claim 1, wherein a part of each surface of the cross-sectional shape of the multiple structure or a side surface in the longitudinal direction is formed by a truss member. 6. The space structure according to claim 1, wherein the pushing means is a gas generator. 7. The space structure according to claim 1, wherein the pushing means is a spring, and the elastic force of the spring pushes out the internal structure. 8. The universe according to claim 1, wherein the multiple structure includes a plurality of multiple structures, and the multiple structures are connected by a connecting portion that radially supports the bases of the multiple structures. Structure. 9. The space structure according to claim 8, wherein the support of the base of the multi-structure of the connecting portion is supported by pressing the tip of the pin with the elastic force of a spring. 10. A rod-shaped structure is formed by using four unit structures having a tubular shape and a right-angled isosceles triangle in cross-section, and having a predetermined length. A space structure characterized in that two apexes of a unit structure are joined so as to form a ring and the cross section forms a regular quadrangle. 11. A rod-shaped structure is formed by using eight unit structures having a tubular shape and a right-angled isosceles triangle in cross-section, and having a predetermined length. A unit structure is formed by joining two unit structures to form a right-angled isosceles triangle, and the four vertexes of the unit structure are joined so as to form an annulus and the cross section forms a regular quadrangle. Characteristic space structure.