JP7737263B2 - Dome fuselage structure, dome structure unit, and fuselage member - Google Patents

Description

The present invention relates to a dome fuselage structure, a dome structure unit, and a fuselage member, and relates to a dome fuselage structure for supporting a dome-shaped structure placed on top, a dome structure unit consisting of a dome-shaped structure and a dome fuselage structure, and a fuselage member for forming the dome fuselage structure.

2. Description of the Related Art Conventionally, dome-shaped structures formed into a polyhedron by combining polygonal panels such as triangular and rectangular panels into a three-dimensional shape have been well known.
An example of a sturdy dome-shaped structure for residential use is a geodesic dome-shaped structure formed by combining triangular wooden or metal plate panels into a three-dimensional shape and fixing them together using metal or other fasteners to form, for example, a regular icosahedron.
On the other hand, such dome-shaped structures require multiple panels, but because they can be assembled by combining multiple panels, some dome-shaped structures are used for a variety of purposes, such as structures for outdoor events, temporary housing in remote areas, temporary housing in emergencies such as earthquakes and disaster areas, simple tents, pet kennels, etc. When installing such a dome-shaped structure, the panels and other portable components required for the dome-shaped structure can be transported and the dome-shaped structure can be assembled at the installation site.

As an example of such a dome-shaped structure, Patent Document 1, filed by one of the present applicants, proposes a dome-shaped structure that can be easily assembled into a dome shape using panel members made of plastic corrugated cardboard with polyhedral outer surfaces, such as triangular or rectangular shapes. The dome-shaped structure described in Patent Document 1 uses panel members that have a polyhedral outer surface, multiple extension pieces that extend along folds along the sides surrounding the outer surface, and insertion holes provided in the extension pieces. Such panel members are assembled so that the extension pieces overlap each other on the outside of the dome-shaped structure, and a binding member is inserted through both insertion holes in the overlapping extension pieces to bind them together and fasten the extension pieces together, thereby assembling the polyhedral dome-shaped structure.
For this reason, the dome-shaped structure described in Patent Document 1 is said to be easily assembled using portable materials. Furthermore, the dome-shaped structure described in Patent Document 1 is said to have the following advantages:

JP 2017-110493 A

The technology disclosed in Patent Document 1 uses panel members made of plastic corrugated cardboard, which, due to the lightweight nature of the panel material itself and its hollow structure, is lighter than wooden or metal plate materials. It is also superior to paper corrugated cardboard in terms of strength, durability, and water repellency. Unlike wooden or metal plate materials, it can be easily folded along its creases to form a polyhedron. Furthermore, by assembling the panel members so that the extension pieces are on the outside of the dome-shaped structure, the extension pieces can also function as gutters during rainy weather.
That is, the dome-shaped structure disclosed in Patent Document 1 has the features of being easy to assemble and being lightweight yet excellent in strength, durability, and water repellency.

However, conventional dome-shaped structures, including the dome-shaped structure disclosed in Patent Document 1, that use lightweight panel members such as plastic or cardboard made of paper or the like have the problem that when sediment accumulates on the upper side, the weight of the sediment causes the lower end to spread and collapse, resulting in low pile strength.
Furthermore, in the prior art dome-shaped structure, when an opening for entry and exit is provided, the lower end becomes even wider, which causes a problem of further reducing the deposition strength.
Furthermore, because the dome-shaped structures of the prior art have a polyhedral shape, such as an icosahedron, their height cannot be increased due to assembly constraints, and the storage space within the dome cannot be increased. For example, in the case of a polyhedral shape that is close to a hemisphere or two-thirds sphere, such as the dome-shaped structure disclosed in Patent Document 1, the height is half or approximately 70% of the diameter of the bottom end, respectively. In order to increase the height and thereby increase the storage space, it is necessary to increase the size of the dome-shaped structure itself and the installation area of the dome-shaped structure, but this is difficult to achieve due to the strength of the structure itself and the aforementioned deposition strength.

Furthermore, when the extension pieces of the panel members are joined together using a large number of binding members such as cable ties, as in the dome-shaped structure disclosed in Patent Document 1, there is a problem in that the workability is poor.
Furthermore, when the extension pieces of the panel members bound together with binding members are on the outer surface, as in the dome-shaped structure disclosed in Patent Document 1, if cardboard made of paper or the like is used, even if the outer surface of the panel member is treated to be water-repellent, the joints of the extension pieces will deteriorate due to rain or snow, etc., and there is a risk that the dome-shaped structure itself may be damaged.

The present invention aims to solve the problems of the prior art described above and provide a dome fuselage structure that firmly and reliably supports a dome-shaped structure without opening it, allowing for the construction of a dome structure unit with improved deposition strength, while also improving workability; a dome structure unit in which a dome-shaped structure is firmly and reliably supported by such a dome fuselage structure; and a flat fuselage member that allows the efficient, easy, and reliable production of fuselage parts that make up the dome fuselage structure.

To achieve the above object, the dome fuselage structure of the first aspect of the present invention is a dome fuselage structure having, at least at the lowest level, a fuselage section configured by combining multiple wall forming sections and at least one opening forming section to enclose a space. A dome-shaped structure that is closed except for its underside is placed and supported on the upper side of the dome fuselage structure, and the lower side of the dome fuselage structure is supported directly or indirectly on the ground or floor. Each of the multiple wall forming sections has an even number of first fuselage parts and an even number of second fuselage parts adjacent to the first fuselage parts. The opening forming section has an even number of third fuselage parts and an even number of fourth fuselage parts each adjacent to the third fuselage parts, and has an opening formed by being surrounded by the even number of third fuselage parts and the even number of fourth fuselage parts.

Here, it is preferable that the first fuselage part and/or the second fuselage part, and the third fuselage part and/or the fourth fuselage part each have a thickness in part and have an enveloping structure that forms a space inside.
It is also preferable that the outer edge of the upper end of the body portion and the outer edge of the lower end of the body portion are the same size.
It is also preferable that the total number of the plurality of wall forming portions and the at least one opening forming portion is an even number, and that the body portion is symmetrical in a plan view.
It is also preferable that the vertices of the first body part and the second body part are both located inward from the outer surface of the body portion.

It is also preferable that the opening of the opening forming portion is located inward from the outer surface of the body portion.
It is also preferable that at least one of the first fuselage part and the second fuselage part, and at least one of the third fuselage part and the fourth fuselage part, have an extension piece extending outward.
Preferably, the first fuselage part, the second fuselage part, the third fuselage part, and the fourth fuselage part each have at least one push-type joint for joining with another part.
It is also preferable that the robot further comprises a boomerang joint member for joining the upper and/or lower sides of the body portion at the boomerang joint.

Furthermore, it is preferable that one vertex corresponding to the long side of each of the triangles of the first and second fuselage parts in a side view is located at the center of the wall forming part, the first fuselage part is located above and below the center and is vertically symmetrical in a side view, and the second fuselage part is located to the left and right of the center and is horizontally symmetrical in a side view, and the center is located inward from the periphery of the wall forming part.
Furthermore, it is preferable that one vertex corresponding to the long side of the triangle of the third body part in side view is located at the upper right and lower left vertices of the opening forming portion, and one vertex corresponding to the long side of the triangle of the fourth body part in side view is located at the upper left and lower right vertices of the opening forming portion, and that opening surfaces are located at the positions of the long sides of the triangles of the third body part and the fourth body part in side view, and that openings in the opening forming portion are formed by the opening surfaces and that the openings are located inward from the periphery of the opening forming portion.

In order to achieve the above object, a dome structure unit according to a second aspect of the present invention is characterized by having the dome fuselage structure according to the first aspect of the present invention and a dome-shaped structure placed and fixed on the upper side of the dome fuselage structure.
In order to achieve the above object, a fuselage member according to a third aspect of the present invention is a fuselage member used in the dome fuselage structure according to the first aspect of the present invention, characterized in that it is used as a flat first fuselage member, a flat second fuselage member, a flat third fuselage member, and a flat fourth fuselage member for forming the dome fuselage structure, respectively.

According to the first aspect of the present invention, it is possible to construct a dome structure unit that firmly and reliably supports a dome-shaped structure without opening it, and improves deposition strength, and it is also possible to provide a dome body structure that improves workability.
Furthermore, according to the first aspect of the present invention, the dome-shaped structure can be assembled efficiently, easily, and reliably, and can firmly and reliably support the dome-shaped structure. It will not collapse even if one or more openings for entry and exit are provided. Furthermore, the height of the dome-shaped structure can be increased without increasing the installation area, and the storage space can be increased.
Furthermore, according to a second aspect of the present invention, a dome structure unit can be provided which comprises such a dome fuselage structure and a dome-shaped structure which is firmly and reliably supported by using the dome fuselage structure, and which can be increased in height without increasing the installation area and has a large storage space.
Furthermore, according to a third aspect of the present invention, it is possible to provide a flat fuselage member that can be used to efficiently, easily, and reliably manufacture fuselage components that constitute such a dome fuselage structure.

FIG. 1 is a perspective view illustrating an example of a dome fuselage structure according to an embodiment of the present invention. 2A and 2B are side views of the dome fuselage structure shown in FIG. 1 , in which (a) is a side view of the dome fuselage structure with a wall forming portion disposed at the center, and (b) is a side view of the dome fuselage structure with an opening forming portion disposed at the center. FIG. 2 is a bottom view of the dome fuselage structure shown in FIG. 1 . 2(a) is a perspective view of a first body part constituting the wall forming portion shown in FIG. 2(a), (a) is a perspective view of the first body part from the outer surface side, and (b) is a perspective view of the first body part from the inner surface side. 2(a) is a perspective view of a second fuselage part constituting the wall forming portion shown in FIG. 2(a), (a) is a perspective view of the second fuselage part from the outer surface side, and (b) is a perspective view of the second fuselage part from the inner surface side. 6 is a perspective view of the first fuselage part and the second fuselage part combined by overlapping and joining the extension piece of the first fuselage part shown in FIG. 4 and the extension piece of the second fuselage part shown in FIG. 5 . FIG. 3A and 3B are perspective views of a third fuselage part constituting the opening forming portion shown in FIG. 2B, in which (a) is a perspective view from the outer surface side and opening surface side of the third fuselage part, and (b) is a perspective view from the inner surface side and joining surface side of the third fuselage part. 3A and 3B are perspective views of a fourth fuselage part constituting the opening forming portion shown in FIG. 2B, in which (a) is a perspective view from the outer surface side and opening surface side of the fourth fuselage part, and (b) is a perspective view from the inner surface side and joining surface side of the fourth fuselage part. 9 is a perspective view of the second fuselage part shown in FIG. 5 and the fourth fuselage part shown in FIG. 8 in a state where the joining surfaces of the second fuselage part and the fourth fuselage part are joined together by overlapping each other. FIG. 2 is a side view of a dome structure unit consisting of the dome fuselage structure and the dome-shaped structure shown in FIG. 1 . FIG. 5 is a plan view of a flat plate-shaped first body member for forming the first body part shown in FIGS. 4( a ) and 4 ( b ). 4(a) and 4(b) is a plan view of a triangular piece for supporting the triangular cross section of the first fuselage part. FIG. FIG. 6 is a plan view of a flat plate-shaped second body member for forming the second body part shown in FIGS. 5( a ) and 5 ( b ). FIG. 8 is a plan view of a flat third body member for forming the third body part shown in FIGS. 7( a ) and 7 ( b ). FIG. 9 is a plan view of a plate-shaped fourth body member for forming the fourth body part shown in FIGS. 8( a ) and 8 ( b ). 12 is a perspective view showing a state in which the first pushing portion shown in FIG. 11 is pushed in. FIG. 12 is a cross-sectional view showing a state in which the first pushing portion shown in FIG. 11 is pushed in. FIG. 12 is a perspective view showing a state in which the third pushing portion shown in FIG. 11 is pushed in. FIG. 12 is a cross-sectional view showing a state in which the third pushing portion shown in FIG. 11 is pushed in. FIG.

The dome fuselage structure, the dome structure unit, and the fuselage member according to the present invention will be described in detail below.
The following description of the components will be given based on a representative embodiment of the present invention, but the present invention is not limited to such an embodiment.

The dome fuselage structure according to the first aspect of the present invention is a structure for placing, fixing, and supporting a dome-shaped structure that is closed except for its lower surface and has an opening for people or animals to enter and exit, or for furniture, tools, materials, etc. As a result, a dome structure unit according to the present invention can be constructed by combining the dome fuselage structure according to the present invention with a dome-shaped structure.
The dome structure unit according to the second aspect of the present invention, which will be described in detail later, has an opening at the bottom and a dome-shaped space inside, which can accommodate people, animals, furniture, tools, materials, etc. Depending on its size, the dome structure unit can be used for a variety of purposes, such as structures for outdoor events, temporary housing in remote areas, temporary housing in emergencies such as earthquakes and disaster areas, simple tents, or pet kennels.

A dome fuselage structure according to a first aspect of the present invention has, at least at the lowest level, a cylindrical fuselage section formed by combining a plurality of wall forming sections and at least one opening forming section, for example in a ring shape, so as to surround a space, and the wall forming sections have an even number of first fuselage parts and an even number of second fuselage parts adjacent to each of the first fuselage parts, and the opening forming sections have an even number of third fuselage parts and an even number of fourth fuselage parts each adjacent to the third fuselage parts, with the opening being formed surrounded by the even number of third fuselage parts and the even number of fourth fuselage parts.
Furthermore, a fuselage member according to a third aspect of the present invention comprises a first fuselage member, a second fuselage member, a third fuselage member, and a fourth fuselage member, each of which has a flat plate shape and is used to form a first fuselage part, a second fuselage part, a third fuselage part, and a fourth fuselage part, respectively, which constitute the dome fuselage structure according to the first aspect of the present invention.
The material constituting the dome fuselage structure of the present invention can be selected from thick paper materials such as cardboard, but the paper may be of any quality, and may be coated with various types of material or made of resin other than paper.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, a dome fuselage structure, a dome structure unit, and a fuselage member according to the present invention will be described in detail with reference to preferred embodiments shown in the accompanying drawings.
(Dome fuselage structure)
Fig. 1 is a perspective view schematically illustrating an example of a dome fuselage structure according to an embodiment of the present invention. Figs. 2(a) and 2(b) are side views, respectively, in which a wall-forming portion and an opening-forming portion of the dome fuselage structure shown in Fig. 1 are arranged at the center. Fig. 3 is a bottom view of the dome fuselage structure shown in Fig. 1.
The dome fuselage structure 10 of the present invention shown in Figure 1 has one tubular fuselage section 16 at the bottom, which is constructed by combining four wall-forming sections 12 and four opening-forming sections 14 alternately in a ring shape. The wall-forming sections 12 form wall portions, and the opening-forming section 14 forms one opening 15.

In the example shown in Figure 1, only one body section 16 having an opening 15 is provided at the bottom, but the present invention is not limited to this. As long as there is an opening-forming section 14 that forms the opening 15 at least at the bottom, one or more wall body sections formed into a cylindrical shape by combining multiple wall forming sections 12 in a ring shape, for example, may be stacked one or more times to surround the space. Furthermore, as shown in Figures 2(a) and (b) and Figure 3, it is preferable that the outer edge of the upper end of the body section 16 is the same size as the outer edge of the lower end of the body section. Note that the wall body section differs from the body section 16 in that it does not have an opening-forming section 14 with an opening 15, but is the same as the body section 16 in that it is composed of multiple wall forming sections 12, and therefore has similar characteristics in that respect. In other words, like the body section 16, it is preferable that the outer edge of the upper end of the wall body section is the same size as the outer edge of the lower end.

Furthermore, the body portion 16 is configured by combining four wall forming portions 12 and four opening forming portions 14 alternately in a ring shape, but the present invention is not limited to this, and it is sufficient that they are combined to surround a space and configured into a cylindrical shape. Furthermore, the number of wall forming portions 12 and opening forming portions 14 that make up the body portion 16 is not particularly limited, and it is sufficient that there are multiple wall forming portions 12 and at least one opening forming portion 14. However, as shown in Figure 3, it is preferable that the total number is an even number, and it is preferable that the body portion 16 is symmetrical in a plan view. Furthermore, it is more preferable that the number of wall forming portions 12 and opening forming portions 14 are each even numbers, and most preferable that they are the same even number.

The dome fuselage structure 10 of the present invention further has boomerang joint members 20a and 20b for joining the upper and/or lower sides thereof, i.e., the upper and/or lower sides of the fuselage section 16 in the example shown in Fig. 1, at the boomerang joint 18. In Fig. 1, the upper boomerang joint 18 is omitted in the fuselage section 16 which is the upper side of the dome fuselage structure 10, but it is the same as the boomerang joint 18 on the bottom side of the dome fuselage structure 10, i.e., the lower side, of the fuselage section 16 shown in Fig. 3, and is joined in the same manner using boomerang joint members 20a and 20b.
The dome fuselage structure 10 of the present invention supports a dome-shaped structure 80 (described later) shown in FIG. 10 via boomerang joint members 20 a and 20 b on its upper side, i.e., on the upper side of the fuselage section 16 in the example shown in FIG. 1 , and the dome fuselage structure 10 is supported directly or indirectly on the ground or floor surface via boomerang joint members 20 a and 20 b on the lower side of the fuselage section 16.

(Wall forming part)
2(a), the wall forming portion 12 has two first body parts 22 and two second body parts 24. The first body parts 22 and the second body parts 24 are both isosceles triangles in side view and are adjacent to each other with no gaps.
The first fuselage part 22 has, on its outer surface, two triangular outer surfaces 22a and 22b adjacent to each other at the center of an isosceles triangle in side view and forming a central adjacent line 23a extending from an apex 23 of the isosceles triangle toward an opposite side 23b. As shown in Fig. 1, the triangular outer surfaces 22a and 22b form a mountain shape that protrudes outward from the apex 23 toward the opposite side 23b along the central adjacent line 23a, and the central adjacent line 23a forms a ridge line. The two first fuselage parts 22 are disposed above and below the wall forming part 12, respectively, and their respective apexes 23 meet at a center point 26 of the wall forming part 12.

As shown in Fig. 2(a), each second body part 24 has a triangular outer surface 24a, which is a flat surface in the shape of an isosceles triangle. As shown in Fig. 1, the two second body parts 24 each have a triangular outer surface 24a, are arranged on the left and right of the wall forming part 12, and vertices 25 of the isosceles triangles of the triangular outer surfaces 24a converge at the center point 26 of the wall forming part 12.
Thus, the wall forming section 12 formed by the two first body parts 22 and the two second body parts 24 is vertically symmetrical and bilaterally symmetrical in a side view, and has a rectangular shape.
It is preferable that the vertices 23 and 25 of the first body part 22 and the second body part 24 are both located at the center point 26 of the wall forming portion 12 and are located inward from the rectangular outer surface of the wall forming portion 12, i.e., the outer surface of the body portion 16.
The first body part 22 and the second body part 24 will be described in detail later.

(Opening forming part)
As shown in Fig. 2(b), the opening forming portion 14 has two third body parts 28 and two fourth body parts 30. The third body part 28 and the fourth body part 30 each have outer surfaces 28a and 30a that are isosceles triangular in side view, and have rectangular opening surfaces 28b and 30b at the portions facing the vertices 27 and 29, respectively, as shown in Fig. 1.
In the opening forming portion 14, two third body parts 28 and two fourth body parts 30 are alternately arranged adjacent to each other so that each vertex 27 and each vertex 29 are located at the four corners of the rectangular opening forming portion 14. As a result, a rectangular opening 15 is formed in the center of the opening forming portion 14 by each opening surface 28b of the two third body parts 28 and each opening surface 30b of the two fourth body parts 30.
Thus, the opening forming section 14 formed by the two third body parts 28 and the two fourth body parts 30 has a rectangular shape and is vertically symmetrical and bilaterally symmetrical when viewed from the side.
The opening surfaces 28b and 30b of the third body part 28 and the fourth body part 30 are both located toward the center of the opening forming portion 14, and are preferably located inward from the rectangular outer peripheral surface of the opening forming portion 14, i.e., the outer surface of the body part 16.
The third fuselage part 28 and the fourth fuselage part 30 will be described in detail later.

(First fuselage part)
Next, as shown in Figures 4(a) and (b) , the first body part 22 constituting the wall forming portion 12 is a three-dimensional part in the shape of a triangular pyramid having triangular outer surfaces 22a and 22b that share a vertex 23 and form the outer surface of the body part 16, a triangular joint surface 22c that faces the vertex 23, and a triangular inner surface 22d that shares the vertex 23 and forms the inner surface of the body part 16.
Here, the triangular joint surface 22c has an isosceles triangle shape with sides 23c and 23d of the triangular outer surfaces 22a and 22b as two sides, the opposing side 23b as the long side, and facing the vertex 23. This triangular joint surface 22c is the upper and/or lower surface of the body 16, and is the surface that is joined to the boomerang joint member 20a shown in Figure 3. The triangular inner surface 22d constitutes the inner surface of the body 16, and has an isosceles triangle shape with the other sides 23e and 23f of the triangular outer surfaces 22a and 22b as two sides, the opposing side 23b as the long side, and the vertex 23 shared.
The first fuselage part 22 further has a rectangular extension piece 22e extending inward a predetermined length from a common side 23e of the triangular outer surface 22a and the triangular inner surface 22d, and a rectangular extension piece 22f extending inward a predetermined length from a common side 23f of the triangular outer surface 22b and the triangular inner surface 22d. Here, the extension piece 22e is intended to be joined to an extension piece 24f of substantially the same shape (described later) of an adjacent second fuselage part 24, and the extension piece 22f is intended to be joined to an extension piece 24e of substantially the same shape (described later) of another adjacent second fuselage part 24.

(Second fuselage part)
5( a) and 5(b), the second body part 24 is a three-dimensional part in the shape of a triangular pyramid, with the outer and inner surfaces reversed, but different in size from the first body part 22. Therefore, it has a triangular outer surface 24a having a vertex 25 and constituting the outer surface of the body section 16, a triangular joint surface 24b opposite the vertex 25, and triangular inner surfaces 24c and 24d that share the vertex 25 and constitute the inner surface of the body section 16.
Here, triangular joint surface 24b forms the base of an isosceles triangular pyramid with opposing side 25a, which is the long side facing vertex 25 of triangular outer surface 24a, as its long side, and equal sides 25b and 25c. This triangular joint surface 24b forms a joint surface in the left-right direction extending in the up-down direction of the body section 16, and is used to join both triangular joint surfaces 28d and 30d of the third body part 28 and the fourth body part 30.

The triangular inner surfaces 24c and 24d are adjacent to each other on the inner surface of the body 16 along a central adjacent line 25d that extends from the vertex 25 to the intersection of the two sides 25b and 25c of the triangular joint surface 24b, forming two triangles with the central adjacent line 25d as a common side and one side of the triangular outer surface 24a and one side of the triangular joint surface 24b as two sides. The triangular inner surfaces 24c and 24d form a mountain shape that protrudes inward as it extends from the vertex 25 to the opposite side 25a along the central adjacent line 25d, and the central adjacent line 25d forms a ridge line.
The second fuselage part 24 further has a rectangular extension piece 24e extending inward a predetermined length from a common side 25e between the triangular outer surface 24a and the triangular inner surface 24c, and a rectangular extension piece 24f extending inward a predetermined length from a common side 25f between the triangular outer surface 24a and the triangular inner surface 24d. As described above, the extension piece 24e is intended to be joined to an extension piece 22f of approximately the same shape on an adjacent first fuselage part 22, and the extension piece 24f is intended to be joined to an extension piece 22e of approximately the same shape on another adjacent first fuselage part 22.

When constructing the wall forming portion 12, as shown in FIGS. 4( a) and (b), 5(a) and (b), and 6, the extension piece 22f of the first body part 22 and the extension piece 24e of the second body part 24 can be overlapped and joined to integrate the first body part 22 and the second body part 24.
Thereafter, the remaining extension piece 22e of the first fuselage part 22 and the extension piece 24f of the other second fuselage part 24 are overlapped and joined together, thereby integrating the first fuselage part 22 and the other second fuselage part 24.
Next, the remaining extension piece 24f of the original second fuselage part 24 and the extension piece 22e of the other first fuselage part 22 are overlapped and joined together to integrate the first fuselage part 22 and the other second fuselage part 24.
Finally, the unjoined extension piece 24e of the other second fuselage part 24 and the extension piece 22f of the other first fuselage part 22 are overlapped and joined to integrate the other second fuselage part 24 and the other first fuselage part 22, thereby assembling one wall forming section 12 as shown in Figures 1 and 2(a).

(Third fuselage part)
Next, as shown in FIGS. 7( a) and 7(b), the third body part 28 constituting the opening forming portion 14 is a three-dimensional part in the shape of a quadrangular pyramid having a triangular outer surface 28a having a vertex 27 and constituting the outer surface of the body section 16, a rectangular opening surface 28b facing the vertex 27 and having a side 27a opposite the vertex 27 of the triangular outer surface 28a as one side, a triangular inner surface 28c sharing the vertex 27 and constituting the inner surface of the body section 16, and triangular connecting surfaces 28d and 28e sharing the vertex 27 and connecting the triangular outer surface 28a and the triangular inner surface 28c on both sides.
Here, triangular outer surface 28a is an isosceles triangle having three sides: opposing side 27a, which is the long side facing vertex 27, and two equal sides 27b and 27c, which share vertex 27. Triangular inner surface 28c is a triangle having three sides: opposing side 27d, which is facing vertex 27, and two sides 27e and 27f, which share vertex 27.

The triangular bonding surface 28d has a triangular shape with three sides defined by the side 27b of the triangular outer surface 28a, the side 27e of the triangular inner surface 28c, and the opposing side 27g that faces the vertex 27. The triangular bonding surface 28d constitutes the bonding surface in the vertical direction of the body section 16, and is intended to be bonded to the upper or lower side of the triangular bonding surface 24b of the second body part 24.
The triangular joint surface 28e has a triangular shape with three sides defined by the side 27c of the triangular outer surface 28a, the side 27f of the triangular inner surface 28c, and the opposing side 27h facing the vertex 27. The triangular joint surface 28e is the upper and/or lower surface of the body 16, and is the surface that is joined to the boomerang joint member 20b shown in FIG.

In addition, rectangular opening surface 28b is a rectangle consisting of four sides, 27a, 27g, 27d, and 27h, and is a combination of triangular surface 28b1 consisting of sides 27a, 27h and adjacent side 27i and triangular surface 28b2 consisting of sides 27d, 27g, and adjacent side 27i.
The third body part 28 further has a triangular inner surface 28c and a triangular extension piece 28f extending a predetermined length inward from the common side 27f of the triangular joint surface 28e. Like the triangular joint surface 28e, this extension piece 28f also forms the upper and/or lower surface of the body section 16 and is joined to the boomerang joint member 20b shown in Figure 3.

(Fourth fuselage part)
Next, as shown in FIGS. 8( a) and 8(b), the fourth fuselage part 30 is a part symmetrical to the third fuselage part 28, and is a three-dimensional part in the shape of a quadrangular pyramid having a triangular outer surface 30a having a vertex 29 and constituting the outer surface of the fuselage section 16, a rectangular opening surface 30b facing the vertex 29, with the opposite side 29a of the vertex 29 of the triangular outer surface 30a as one side, a triangular inner surface 30c sharing the vertex 29 and constituting the inner surface of the fuselage section 16, and triangular connecting surfaces 30d and 30e sharing the vertex 29 and connecting the triangular outer surface 30a and the triangular inner surface 30c on both sides.
Here, the triangular outer surface 30a is an isosceles triangle having three sides: an opposing side 29a that is the long side facing the vertex 29, and two equal sides 29b and 29c that share the vertex 29. The triangular inner surface 30c is a triangle having three sides: an opposing side 29d that is facing the vertex 29, and two sides 29e and 29f that share the vertex 29.

The triangular bonding surface 30d has a triangular shape with three sides defined by the side 29c of the triangular outer surface 30a, the side 29f of the triangular inner surface 30c, and the opposing side 29g that faces the vertex 29. The triangular bonding surface 30d constitutes the bonding surface in the vertical direction of the body section 16, and is intended to be bonded to the upper or lower side of the triangular bonding surface 24b of the second body part 24.
The triangular joint surface 30e has a triangular shape with three sides defined by the side 29b of the triangular outer surface 30a, the side 29e of the triangular inner surface 30c, and the opposite side 29h facing the vertex 29. This triangular joint surface 30e is the upper and/or lower surface of the body portion 16, and is the surface that is joined to the boomerang joint member 20b shown in FIG.

Furthermore, rectangular opening surface 30b is a rectangle consisting of four sides, 29a, 29g, 29d, and 29h, and is a combination of triangular surface 30b1 consisting of sides 29a, 29h, and adjacent side 29i, and triangular surface 30b2 consisting of sides 29d, 29g, and adjacent side 29i.
The fourth body part 30 further has a triangular inner surface 30c and a triangular extension piece 30f extending a predetermined length inward from the common side 29e of the triangular joint surface 30e. Like the triangular joint surface 30e, this extension piece 30f also forms the upper and/or lower surface of the body section 16 and is joined to the boomerang joint member 20b shown in Figure 3.

2(b), 5(a) and 5(b), 7(a) and 7(b), and 9, which is a view from the inside, when forming the opening forming portion 14, first, in a side front view, the triangular joint surface 28d of the third body part 28 that forms the upper left opening surface 28b of the opening forming portion 14 is joined and fixed to the upper side of the triangular joint surface 24b of the second body part 24 that is disposed on the right side of the wall forming portion 12. Furthermore, the triangular joint surface 28e and the extension piece 28f of this third body part 28 are parts that become the upper surface of the body section 16, and are joined and fixed to the boomerang joint member 20b shown in FIG.
2(b), 5(a) and 5(b), 8(a) and 8(b), and 9, in a side front view, the triangular joint surface 30d of the fourth body part 30 that forms the lower left opening surface 30b of the opening forming part 14 is joined and fixed to the underside of the triangular joint surface 24b of the second body part 24 disposed on the right side of the wall forming part 12 so as to be aligned with the triangular joint surface 28d of the upper left third body part 28. The triangular joint surface 30e and extension piece 30f of this fourth body part 28 form the underside of the body section 16, and are joined and fixed to the boomerang joint member 20b shown in FIG.

Next, in a side front view, the triangular joint surface 30d of the fourth fuselage part 30 that forms the upper right opening surface 30b of the opening forming part 14 is joined and fixed to the upper side of the triangular joint surface 24b of the second fuselage part 24 that is disposed on the left side of the other wall forming part 12. The triangular joint surface 30e and extension piece 30f of this fourth fuselage part 28 form the upper surface of the fuselage section 16, and are joined and fixed to the same boomerang joint member 20b that is used to secure the triangular joint surface 28e and extension piece 28f on the upper surface of the third fuselage part 28 that is disposed on the upper left of the opening forming part 14.
Next, in a side front view, the triangular joint surface 28d of the third body part 28 that constitutes the opening surface 28b at the lower right of the opening forming part 14 is joined and fixed to the underside of the triangular joint surface 24b of the second body part 24 that is arranged on the left side of the other wall forming part 12, so as to form a line with the triangular joint surface 30d of the fourth body part 30 at the upper right. Furthermore, the triangular joint surface 28e and extension piece 28f of this third body part 28 form the underside of the body section 16, and are joined and fixed to the same boomerang joint member 20b that was used to secure the triangular joint surface 30e and extension piece 30f on the underside of the fourth body part 30 at the lower left of the opening forming part 14.

In this way, the two third body parts 28 and the two fourth body parts 30 are fixed to the body portion 16, the opening forming portion 14 is assembled and configured, and the opening 15 can be formed.
By alternately arranging a total of eight wall forming sections 12 and opening forming sections 14 configured as described above in a circular pattern, it is possible to form a dome fuselage structure 10 consisting of the fuselage section 16 shown in Figures 1 to 3.
The first body part 22, the second body part 24, the third body part 28, and the fourth body part 30 are each configured as described above, but in the present invention, there are no particular limitations as long as they can configure a plurality of wall forming parts 12 and at least one opening forming part 14 having an opening 15.
In the present invention, the first fuselage part and/or the second fuselage part, and the third fuselage part and/or the fourth fuselage part each preferably have a partially thickened structure that forms a space inside.
Furthermore, the wall forming portion 12 and the opening forming portion 14 having the opening 15 are also configured as described above, but in the present invention, there are no particular limitations as long as the body portion 16 having the opening 15 can be configured.

(Dome structure unit)
Next, the dome structure unit of the present invention will be described.
FIG. 10 is a side view schematically showing an example of a dome structure unit according to an embodiment of the present invention.
10, a dome structure unit 100 can be constructed by placing and fixing a dome-shaped structure 80 having a dome shape of approximately the same diameter on the upper side of the dome body structure 10 constructed as above. The lower surface of the dome-shaped structure 80 and the upper surface of the dome body structure 10 can be fixed together using a bundling member, a joining member such as the boomerang joining member described above, and/or a push-type joining portion described below, although not shown.
The dome-shaped structure 80 may be a dome-shaped structure that is closed except for the underside, since the lower dome body structure 10 has the opening 15 .

The dome structure 80 shown in FIG. 10 is constructed by combining twelve dome pieces 90, each of which is made up of four panels 82, 84, 86, and 88.
The dome structure 80, i.e., the dome sections 90 comprised of panels 82, 84, 86, and 88, may be constructed using materials similar to those of the dome fuselage structure 10 of the present invention.
Panels 82 and 84 are members having right-angled triangular outer surfaces that are symmetrical to each other. Panels 86 and 88 are also made of right-angled triangular members that are symmetrical to each other, but can each be bent convexly in two places. As a result, panel 86 is a member having three right-angled triangular outer surfaces 86a, 86b, and 86c, respectively. Panel 88 is also a member having three right-angled triangular outer surfaces 88a, 88b, and 88c, respectively.
Although not shown, these four panels 82, 84, 86, and 88 can be provided with an extension piece on the inner surface of each panel, and the extension pieces of two panels can be overlapped and joined using binding members and/or joining members, etc.

In the dome structure unit 100 of the present invention, it is only necessary to place the dome-shaped structure 80 on top of the dome fuselage structure 10 having the opening 15 of the present invention, so there is no need to increase the height of the dome-shaped structure 80 to enlarge the storage space, and therefore there is no need to make the strength stronger than necessary, and since there is no need to provide an opening in the dome-shaped structure 80, the strength of the dome-shaped structure 80 can be increased.
Therefore, the dome structure unit 100 of the present invention allows the dome-shaped structure 80 to be placed at a high position, making it possible to increase the overall height and increase the storage space.

(Body member)
Next, the body member of the present invention will be described.
Figures 11 to 15 are plan views schematically showing an example of a fuselage member according to an embodiment of the present invention. Note that the first fuselage member 32, the second fuselage member 34, the third fuselage member 36, and the fourth fuselage member 38 shown in Figures 11, 13, 14, and 15 respectively constitute the first fuselage part 22, the second fuselage part 24, the third fuselage part 28, and the fourth fuselage part 30, and therefore, unless there is a special need to distinguish between them, the same components are given the same names and numbers.

(First body member)
First, the first body member 32 shown in Figure 11 is a flat body member for forming the first body part 22. By bending this first body member 32, it is possible to form the first body part 22 in a triangular pyramid shape. In other words, the first body member 32 can be said to be a development view of the first body part 22 shown in Figures 4(a) and 4(b).
The first fuselage member 32 has two portions that become the triangular outer surfaces 22a and 22b of the first fuselage part 22, a portion that becomes the triangular joining surface 22c, a portion that becomes the triangular inner surface 22d, extension pieces 22e1 and 22e2 that are portions that make up extension piece 22e, which are shown overlapping and integrated in the first fuselage part 22, and extension pieces 22f1 and 22f2 that are portions that make up extension piece 22f, and two symmetrical triangular folded pieces 32a and 32b that are folded between the triangular outer surfaces 22a and 22b toward the interior of the first fuselage part 22 and are confined therein, although they do not appear on the front side of the first fuselage part 22.

Furthermore, a cutting line 33a is provided between the triangular bent pieces 32a and 32b, which is cut when assembling the first fuselage part 22 and reaches the vertex of the triangular joint surface 22c. Furthermore, cutting lines 33b and 33c are provided on the triangular bent pieces 32a and 32b, respectively, extending slightly from the vertex where the cutting line 33a starts toward the respective sides 23a1 and 23a2. The sides 23a1 and 23a2 are mountain fold lines that fold the triangular bent pieces 32a and 32b so that the sides 23a1 and 23a2 themselves face outward, i.e., form mountain ridges. When the first fuselage part 22 is assembled, these lines overlap and merge into a single center adjacent line 23a. Hereinafter, a fold line that faces outward, i.e., forms a mountain fold, or outer fold line, when folded.
As a result, the triangular folded pieces 32 a and 32 b are folded toward the inside of the first fuselage part 22 so as to overlap each other, and are trapped inside the first fuselage part 22 .

The opposing edge 23b indicated by the dotted line between the triangular joint surface 22c and the triangular inner surface 22d is a mountain fold line that bends outward, i.e., toward the mountain side, so that the triangular joint surface 22c and the triangular inner surface 22d are on the outside.
Similarly, the dotted lines 23c and 23d between the opposite triangular joint surface 22c and the triangular outer surfaces 22a and 22b are mountain fold lines that are bent outward, i.e., mountain fold lines.
On the other hand, the edge 23e1 shown by a dotted line between the triangular outer surface 22a and the extension piece 22e1, and the edge 23f1 shown by a dotted line between the triangular outer surface 22b and the extension piece 22f1 are mountain fold lines that bend the extension piece 22e1 and the extension piece 22f1 outward, i.e., toward the mountain side.
In addition, sides 23e2 and 23f2 shown by dashed lines between triangular inner surface 22d and extension pieces 22e1 and 22f2, respectively, are valley fold lines that fold extension pieces 22e2 and 22f2 inward, i.e., toward the valley side so that they themselves become inward, i.e., valley lines. Hereinafter, fold lines that become inward, i.e., toward the valley side when folded, are referred to as valley fold lines or inner fold lines.

Further, extension piece 22e2 and extension piece 22f2 each have a fastening hole 49, a first push-in portion 41, and an alignment hole 48 at both ends, and a fastening hole 49, two third push-in portions 43, and an alignment hole 48 at the center. The number of fastening holes 49, first push-in portions 41, alignment holes 48, and third push-in portions 43 is not particularly limited, and may be set appropriately depending on, for example, the binding and joining of extension pieces such as extension pieces 22e1 and 22e2 and extension pieces 22f1 and 22f2, the binding and joining of joining surfaces of fuselage parts, and the binding and joining of extension pieces, joining surfaces of fuselage parts, and the boomerang joining member.
The first pushing portions 41 are portions that are pushed in when joining extension pieces together or body parts together, and are provided in pairs. Each of the pair of first pushing portions 41 extends from a base end, and is formed so that their respective tip ends are in contact with each other. More specifically, as shown in FIG. 11 , each of the pair of first pushing portions 41 has a base end, a root portion 45 adjacent to the base end, and a continuous portion 46 that is continuous with the root portion 45 on the opposite side from the base end. The outer edge of the first pushing portion 41, excluding the base end (i.e., the outer edges of the root portion 45 and the continuous portion 46), has a notch.

The width of the continuous portion 46 is wider than the width of the root portion 45. In other words, protrusions 47 are provided on both sides of the continuous portion 46, protruding outward in the width direction of the first pushing portion 41. Here, the width direction of the first pushing portion 41 is a direction intersecting (more specifically, perpendicular to) the extension direction of the corresponding extension piece 23. The widths of the root portion 45 and the continuous portion 46 of the first pushing portion 41 are the lengths of the first pushing portion 41 in the width direction.
Before the first pushing portions 41 are operated, as shown in FIG. 11 , the pair of first pushing portions 41 are in a state in which the tips of their respective connecting portions 46 are butted against each other. A fold line L1 is provided at the base end of each of the pair of first pushing portions 41. That is, each first pushing portion 41 can be bent at the base end position. The fold line L1 extends along the width direction of the first pushing portion 41.

The third pushing portion 43 is a portion that is pushed in when joining the extension pieces together or the body parts together, etc. The third pushing portion 43 extends from the base end, and as shown in Fig. 11, like the first pushing portion 41, has a base end, a root portion 45, and a continuous portion 46. The outer edge of the third pushing portion 43, excluding the base end (i.e., the outer edges of the root portion 45 and the continuous portion 46), has a notch.
Furthermore, the width of the continuous portion 46 is wider than the width of the root portion 45. In other words, protrusions 47 are provided on both sides of the continuous portion 46, protruding outward in the width direction of the third push-in portion 43. Here, the width direction of the third push-in portion 43 is along (more specifically, parallel to) the extension direction of the corresponding extension piece 23. The widths of the root portion 45 and the continuous portion 46 of the third push-in portion 43 are the lengths in the width direction of the third push-in portion 43.
A fold line L3 is provided at the base end of the third pushing portion 43. That is, the third pushing portion 43 can be bent at the base end position. The fold line L3 extends along the width direction of the third pushing portion 43. That is, the extension direction of the fold line L2 and the extension direction of the fold line L3 intersect with each other, and preferably are perpendicular to each other.

The alignment holes 48 are holes formed in the tip portions of the first and third push-in portions 41 and 43, more specifically, in the tip portion of the continuous portion 46. The alignment holes 48 formed in the first push-in portion 41 are used to align the position of the first push-in portion 41 with the position of the second push-in portion 42 that overlaps the first push-in portion 41 when joining the extension pieces to each other or the body parts to each other. The alignment holes 48 formed in the third push-in portion 43 are used to align the position of the third push-in portion 43 with the position of the fourth push-in portion 44 that overlaps the third push-in portion 43 when joining the extension pieces to each other or the body parts to each other. The shape of the alignment holes 48 may be any shape, such as a circle, a triangle, a rectangle, or any other polygon, or a star shape.
The fastening holes 49 are holes through which fastening members such as cable ties, strings, or wires are passed when fastening the extension pieces together to join the first small panel 21 and the other panel 14, and two fastening holes 49 are provided at each end in the extension direction of each extension piece 23. Note that the number of fastening holes 49 may be any number, but by providing the first push-in portions 41, the number can be reduced compared to when the first push-in portions 41 are not provided.

Furthermore, extension piece 22e1 and extension piece 22f1 each have fastening holes 49, second push-in portions 42, and alignment holes 48 at both ends, and a fastening hole 49, two fourth push-in portions 44, and alignment holes 48 at the center. Furthermore, triangular joining surface 22c has second push-in portions 42 and fastening holes 49 on both sides of its vertex. The number of fastening holes 49, second push-in portions 42, alignment holes 48, and fourth push-in portions 44 is not particularly limited and may be set appropriately depending on the bonding and joining of extension pieces, such as extension pieces 22e1 and 22e2 and extension pieces 22f1 and 22f2, and the bonding and joining of extension pieces and joining surfaces of fuselage parts, such as triangular joining surface 22c, to the boomerang joining member.

The second pressing portions 42 are portions that are pressed in together with the first pressing portions 41 when joining the extension pieces and the body parts together, and are provided in pairs, similar to the first pressing portions 41. As shown in Fig. 11, a pair of second pressing portions 42 is provided on both end sides of the extension pieces 22e1 and 22f1, and on both sides of the apex of the triangular joining surface 22c. Each second pressing portion 42 faces the first pressing portion 41 when the extension pieces and the body parts are accurately overlapped.
The first push-in portion 41 and the second push-in portion 42 are pushed together to form the push-type joint 40 .
The pair of second pushing portions 42 each extend from a base end, and are formed so that their tip ends are in contact with each other. More specifically, as shown in Fig. 11, each second pushing portion 42 has a base end and an extending portion 50 adjacent to the base end. A notch is provided on the outer edge of the second pushing portion 42, excluding the base end (i.e., the outer edge of the extending portion 50).

The width of each portion of the extending portion 50 is equal to the length of the base end; in other words, the extending portion 50 has a rectangular shape. The width direction of the second pushing portion 42 intersects (more specifically, is perpendicular to) the extension direction of the corresponding extending piece, e.g., extending pieces 22e2 and 22f2. The width of the extending portion 50 of the second pushing portion 42 is the length of the second pushing portion 42 in the width direction. The width of the extending portion 50 is also shorter than the width of the connecting portion 46 of the first pushing portion 41; in other words, the width of the first pushing portion 41 is longer than the width of the second pushing portion 42.
11 , before the second pushing portions 42 are operated, the pair of second pushing portions 42 are in a state in which the tips of the respective extension portions 50 are butted against each other. Furthermore, a bending line L2 is provided at the base end of each second pushing portion 42, and each second pushing portion 42 can be bent at the base end position. The bending line L2 extends along the width direction of the second pushing portion 42.

The fourth pressing portions 44 are pressed in together with the third pressing portions 43 when joining the extension pieces together or the fuselage parts together, and face the third pressing portions 43 when the extension pieces, the joining surfaces of the fuselage parts, or the extension pieces or the joining surfaces of the fuselage parts and the boomerang joining member are accurately overlapped. As shown in Fig. 11, the fourth pressing portions 44 are provided on the central sides of the extension pieces 22e1 and 22f1, respectively. The number of fourth pressing portions 44 provided on the extension pieces and the fuselage parts may be any number as long as it is the same as the number of corresponding third pressing portions 43.
The third push-in portion 43 and the fourth push-in portion 44 are pushed together to form the push-type joint 40 .
The fourth pushing portion 44 extends from the base end and, as shown in FIG. 11 , has a base end and an extending portion 50, similar to the second pushing portion 42. A notch is provided on the outer edge of the fourth pushing portion 44, excluding the base end (i.e., the outer edge of the extending portion 50). A fold line L4 is provided at the base end of the fourth pushing portion 44, allowing the fourth pushing portion 44 to be bent at the base end. The fold line L4 extends along the width direction of the fourth pushing portion 44, which is along (more specifically, parallel to) the extension direction of the corresponding extension pieces 22e1 and 22f1. In other words, the extension direction of the fold line L2 and the extension direction of the fold line L4 intersect each other, preferably perpendicular to each other.

The width of the extending portion 50 of the fourth pushing portion 44 is the length in the width direction of the fourth pushing portion 44, and is shorter than the width of the continuous portion 46 of the third pushing portion 43. In other words, the width of the third pushing portion 43 is longer than the width of the fourth pushing portion 44.
Alignment holes 48 are formed in the tip end portions of the second and fourth push-ins portions 42 and 44 (more specifically, the tip end portions of the extension portions 50). When the alignment hole 48 of the first push-ins portion 41 and the alignment hole 48 of the second push-ins portion 42 are aligned, the first push-ins portion 41 is correctly positioned and properly faces the corresponding second push-ins portion 42. Similarly, when the alignment hole 48 of the third push-ins portion 43 and the alignment hole 48 of the fourth push-ins portion 44 are aligned, the third push-ins portion 43 is correctly positioned and properly faces the corresponding fourth push-ins portion 44. The shapes of the alignment holes 48 formed in the second and fourth push-ins portions 42 and 44 are not particularly limited, but are preferably the same shape as the alignment holes 48 formed in the first and third push-ins portions 41 and 43.
Two fastening holes 49 are provided at each end in the extension direction of each extension piece 33 and at the center. The number of fastening holes 49 may be any number, but by providing the second push-in portions 42, the number can be reduced compared to a case where the second push-in portions 42 are not provided.

After cutting the first body member 32 along cutting lines 33a, 33b, and 33c, triangular folded pieces 32a and 32b are folded outward along sides 23a1 and 23a2, respectively, i.e., mountain folds, so that they overlap each other. Next, they are folded outward along sides 23b, 23c, 23d, 23e1, and 23f1, i.e., mountain folds, and inward along sides 23e2 and 23f2, i.e., valley folds. In this way, triangular joint surface 22c is inclined and erected relative to triangular inner surface 22d, and triangular outer surfaces 22a and 22b are also inclined along erect pieces 23c and 23d of triangular joint surface 22c, respectively. The triangular folded pieces 32a and 32b are inserted into the first fuselage part 22 and integrated, the cutting lines 33b and 33c are also integrated, and the sides 23a1 and 23a2 are overlapped and aligned with the single central adjacent line 23a. In this way, the cut portions of the integrated triangular folded pieces 32a and 32b at the integrated cutting lines 33b and 33c are fitted into the notch 53, which is the cut portion at the vertex of the triangular piece 54 shown in Figure 12.

After this, the vertex of the triangular inner surface 22d and the tip of the central adjacent line 23a between the triangular outer surfaces 22a and 22b are aligned to form the vertex 23 of the first body member 32, and the extension pieces 22e1 and 22e2 are overlapped, and the extension pieces 22f1 and 22f2 are overlapped.
The second push-in portion 42 and/or the fourth push-in portion 44 of the overlapping extension piece 22e1 and the first push-in portion 41 and/or the third push-in portion 43 of the extension piece 22e2 are pressed together and joined to form the push-type joint 40, thereby constituting the integrated extension piece 22e. Similarly, the overlapping extension pieces 22f1 and 22f2 are joined to form the push-type joint 40, thereby constituting the integrated extension piece 22f.
As a result, a first fuselage part 22 having a triangular pyramid shape as shown in Figures 4a and 4b is formed.
At this time, inside the first body part 22, the tip pieces 33d and 33e of the integrated triangular bent pieces 32a and 32b and the triangular piece 54 abut against the triangular inner surface 22d and support the triangular outer surfaces 22a and 22b that form the triangular cross section, thereby increasing the strength of the first body part 22.

(Second body member)
Next, the second body member 34 shown in Figure 13 is a flat body member for forming the second body part 24. By bending this second body member 34, it is possible to form the triangular pyramid-shaped second body part 24. In other words, the second body member 34 can be said to be a development view of the second body part 24 shown in Figures 5(a) and 5(b).
As described above, the second fuselage part 24 is a three-dimensional part in the shape of a triangular pyramid with the outer and inner surfaces reversed to those of the first fuselage part 22, although the size and shape of each face are slightly different. Therefore, the second fuselage member 34 has a similar basic configuration to the first fuselage member 32.
The second fuselage member 34 has a portion that becomes the triangular outer surface 24a of the second fuselage part 24, a portion that becomes the triangular joining surface 24b, two portions that become the triangular inner surfaces 24c and 24d, extension pieces 24e1 and 24e2 that constitute extension piece 24e, which are shown overlapping and integrated in the second fuselage part 24, and extension pieces 24f1 and 24f2 that constitute extension piece 24f, and two symmetrical triangular folded pieces 34a and 34b that are folded between the triangular inner surfaces 24a and 24b toward the interior of the second fuselage part 24, and are confined therein, although they do not appear on the front side of the second fuselage part 24.

Furthermore, a cutting line 35a is provided between the triangular bent pieces 34a and 34b, along which the triangular bent pieces 34a and 34b are cut and reach the apex of the triangular joint surface 24b when assembling the second fuselage part 24. Furthermore, cutting lines 35b and 35c are provided on the triangular bent pieces 34a and 34b, respectively, extending slightly from the apex where the cutting line 35a starts toward the respective sides 25d1 and 25d2. Note that the sides 25d1 and 25d2 are mountain fold lines that fold the triangular bent pieces 34a and 34b so that the sides 25d1 and 25d2 themselves face outward, i.e., form mountain ridges, and when the second fuselage part 24 is assembled, these lines overlap and are unified as the central adjacent line 25d.
As a result, the triangular folded pieces 34 a and 34 b are folded toward the inside of the second fuselage part 24 so as to overlap each other, and are trapped inside the second fuselage part 24 .

The opposing edge 25a indicated by the dotted line between the triangular outer surface 24a and the triangular joint surface 24b is a mountain fold line that bends outward, i.e., toward the mountain side, so that the triangular outer surface 24a and the triangular joint surface 24b are on the outside.
Similarly, the dotted lines 25b and 25c between the opposite triangular joining surface 24b and the triangular inner surfaces 24c and 24d are mountain fold lines that are bent outward, i.e., mountain fold lines.
On the other hand, the dotted lines 25e1 and 25f1 between the triangular outer surface 24a and the extension pieces 24e1 and 24f1, respectively, are mountain fold lines that bend the extension pieces 24e1 and 24f1 outward, i.e., toward the mountain side.
On the other hand, the edge 25e2 indicated by a dotted line between the triangular inner surface 24c and the extension piece 24e2, and the edge 25f2 indicated by a dotted line between the triangular inner surface 24d and the extension piece 24f2 are valley fold lines that bend the extension piece 24e2 and the extension piece 24f2 inward, i.e., toward the valley side.

Furthermore, like the extension pieces 22e2 and 22f2 of the first body member 32 shown in Figure 11, the extension pieces 24e1 and 24f1 each have a fastening hole 49, a first push-in portion 41, and an alignment hole 48 at both ends, and a fastening hole 49, two third push-in portions 43, and an alignment hole 48 at the center. Furthermore, the triangular joining surface 24b has four pairs of first push-in portions 41 on each side of its vertex. The number of fastening holes 49, first push-in portions 41, alignment holes 48, and third push-in portions 43 is not particularly limited and may be set appropriately depending on, for example, the binding and joining of extension pieces such as extension pieces 24e1 and 24e2 and extension pieces 24f1 and 24f2, the binding and joining of joining surfaces of fuselage parts, and the binding and joining of extension pieces, joining surfaces of fuselage parts, and boomerang joining members.

11 , extension piece 24e2 and extension piece 24f2 each have a fastening hole 49, a second push-in portion 42, and an alignment hole 48 at both ends, and a fastening hole 49, two fourth push-in portions 44, and an alignment hole 48 at the center. The numbers of fastening holes 49, second push-in portions 42, alignment holes 48, and fourth push-in portions 44 are not particularly limited, and may be set appropriately depending on the bonding and joining of extension pieces, such as extension pieces 24e1 and 24e2 and extension pieces 24f1 and 24f2, and the bonding and joining of joining surfaces of fuselage parts, such as triangular joining surface 24b and triangular joining surface 28d of third fuselage part 28 and triangular joining surface 30d of fourth fuselage part 30.
The first, second, third and fourth push-in portions 41, 42, 43 and 44, the alignment holes 48 and the fastening holes 49 are the same as those in the first body member 32, and therefore will not be described here.

After cutting the second body member 34 along cutting lines 35a, 35b, and 35c, triangular folded pieces 34a and 34b are folded outward along sides 25d1 and 25d2, respectively, so that they overlap each other. Next, they are folded outward along sides 25a, 25b, 25c, 25e1, and 25f1, so that they overlap each other, and then folded inward along sides 25e2 and 25f2, so that they overlap each other. In this way, the triangular joint surface 24b is inclined and erected relative to the triangular outer surface 24a, and the triangular inner surfaces 24c and 24d are also inclined along the erect pieces 25b and 25c of the triangular joint surface 24b. Triangular folded pieces 34a and 34b are inserted into the second fuselage part 24 and integrated, cutting lines 35b and 35c are also integrated, and sides 25d1 and 25d2 are overlapped and aligned with the single central adjacent line 25d. In this way, the cut portions of the integrated triangular folded pieces 34a and 34b at the integrated cutting lines 35b and 35c are fitted into notches 53, which are the cut portions at the vertices of triangular pieces 54 shown in Figure 12.

After this, the vertex (25) of the triangular outer surface 24a and the tip (25) of the central adjacent line 25d between the triangular inner surfaces 24c and 24d are aligned to form the vertex 25 of the second body member 34, and the extension pieces 24e1 and 24e2 are overlapped, and the extension pieces 24f1 and 24f2 are overlapped.
The first push-in portion 41 and/or the third push-in portion 43 of the overlapping extension piece 24e1 and the second push-in portion 42 and/or the fourth push-in portion 44 of the extension piece 24e2 are pressed together and joined to form the push-type joint 40, thereby constituting the integrated extension piece 24e. Similarly, the overlapping extension pieces 24f1 and 24f2 are joined to form the push-type joint 40, thereby constituting the integrated extension piece 24f.
As a result, the second fuselage part 24 having a triangular pyramid shape as shown in Figures 5a and 5b is formed.
At this time, inside the second fuselage part 24, the tip pieces 35d and 35e of the integrated triangular bent pieces 34a and 34b and the triangular piece 54 abut against the triangular outer surface 24a and support the triangular inner surfaces 24c and 24d that form the triangular cross section, thereby increasing the strength of the second fuselage part 24.

Thereafter, as shown in FIG. 6 , the integrated extension piece 22f of the first body part 22 and the integrated extension piece 24e of the second body part 24 are aligned and overlapped, and the fastening members 56 are passed through two fastening holes 49 on each of the aligned sides and three locations in the center to fasten the extension piece 22f and the extension piece 24e together, thereby integrating the first body part 22 and the second body part 24.
Thereafter, as described above, the extension pieces of the integrated first and second fuselage parts 22 and 24 are joined together in the same manner, thereby integrating the two first fuselage parts 22 and the two second fuselage parts 24, and assembling one wall forming section 12 as shown in Figures 1 and 2(a) In the assembled wall forming section 12, as shown in Figure 1 , four integrated pieces are gathered on the inner side of a center point 26 where the vertices 23 of the two first fuselage parts 22 and the vertices 25 of the two second fuselage parts 24 meet: two integrated pieces formed by joining the extension pieces 22f and 24e together, and two integrated pieces formed by joining the extension pieces 22e and 24f together. 1, the fastening holes 49 on the center point 26 side of each of the four integrated pieces gathered at the center point 26, i.e., the four fastening holes 49, are fastened together using a fastening member 56. In this way, the strength of the wall forming portion 12 can be increased.

(Third fuselage member)
First, the third body member 36 shown in Figure 14 is a flat body member for forming the third body part 28. The quadrangular pyramid-shaped third body part 28 can be formed by bending this third body member 36. In other words, the third body member 36 can be said to be a development view of the third body part 28 shown in Figures 7(a) and 7(b).
The third body member 36 has a portion that becomes the triangular outer surface 28a of the third body part 28, two portions that become triangular surfaces 28b1 and 28b2 that make up the rectangular opening surface 28b, a portion that becomes the triangular inner surface 28c, a portion that becomes the triangular joining surface 28d, a portion that becomes the triangular joining surface 28e, a portion that becomes the triangular extension piece 28f, and, although not visible on the front side, a triangular folded piece 36a on the outside of the triangular surface 28b1, a trapezoidal folded piece 36b on the outside of the triangular surface 28b1, and a trapezoidal folded piece 36c on the outside of the triangular joining surface 28e.

Side 27a is an outer fold curve between triangular outer surface 28a and triangular surface 28b1, side 27b is an outer fold curve between triangular outer surface 28a and triangular joint surface 28d, and side 27c is an outer fold curve between triangular outer surface 28a and triangular joint surface 28e.
Side 27d is an outer fold line between triangular inner surface 28c and triangular surface 28b2, side 27e is an outer fold line between triangular inner surface 28c and triangular joint surface 28d, side 27f1 is an outer fold line between triangular joint surface 28e and trapezoidal folded piece 36c, and side 27f2 is an inner fold line between triangular inner surface 28c and triangular extension piece 28f. When folded into third fuselage part 28, sides 27f1 and 27f2 are adjacent to each other and become integrated side 27f.

Furthermore, when the third body part 28 is bent, the side 27g1 of the triangular surface 28b2 and the side 27g2 of the triangular joining surface 28d are adjacent to each other and integrated together to form one side 27g of the rectangular opening surface 28b.
Furthermore, when the third body part 28 is bent, the side 27h1 of the triangular surface 28b1 and the side 27h2 of the triangular joining surface 28e are adjacent to each other and integrated together to form one side 27h of the rectangular opening surface 28b.
The side 27i1 is an outer bending line between the triangular surface 28b1 and the triangular bent piece 36a, and the side 27i2 is an outer bending line between the triangular surface 28b2 and the trapezoidal bent piece 36b.

When the sides 27i1 and 27i2 are folded to form the third body part 28, the triangular surfaces 28b1 and 28b2 are combined in the opposite directions to form the rectangular opening surface 28b consisting of the four sides 27a, 27g, 27d, and 27h, and the sides 27i1 and 27i2 become adjacent and integrated side 27i.
In addition, when the triangular bending piece 36a is bent along the side 27i1, a notch is made on one side on the side of the triangular bending piece 36a so that the convex insertion piece 36d protrudes from the triangular surface 28b1 through the side 27i1 toward the triangular bending piece 36a, and on the other side, an insertion port 36f is provided on the side 27i1 for inserting and fixing the convex insertion piece 36e, which will be described later and has the same shape as the insertion piece 36d.
On the other hand, on the side of side 27i2, an insertion port 36g is provided at a position on side 27i2 where insertion port 36d on the side of side 27i1 can be inserted when trapezoidal bending piece 36b is bent along side 27i2, and a convex insertion piece 36e for insertion is provided at a position where it can be inserted into insertion port 36f on the side 27i1 so as to protrude from triangular surface 28b2 toward trapezoidal bending piece 36b via side 27i2.

Furthermore, four pairs of second push-in portions 42 are provided on the triangular joint surface 28d at positions corresponding to the four pairs of first push-in portions 41 on the triangular joint surface 24b so that the triangular joint surface 28d is joined to one side of the triangular joint surface 24b of the second body part 24 when configured as the third body part 28.
Furthermore, on the side 27h2 of the triangular joining surface 28e and on the side of the vertex 27 of the extension piece 28f, one fourth push-in portion 44 is provided at a position corresponding to the two third push-in portions 43 on one half of the longitudinal direction of the boomerang joining member 20b shown in Figure 3 so that when configured as the third body part 28, they are joined to one half of the longitudinal direction of the boomerang joining member 20b, and two fastening holes 49 are provided on the outside of each of them.
Furthermore, two fastening holes 49 are provided on the side 27h1 of the triangular surface 28b1, corresponding to the two fastening holes 49 of the triangular joining surface 28e.
The second pushing portion 42, the fourth pushing portion 44, and the fastening hole 49 are as described above, and therefore will not be described again.

In the third body member 36, triangular bent piece 36a is bent outward along side 27i1 relative to triangular surface 28b1, causing insertion piece 36d to protrude, trapezoidal bent piece 36b is bent outward along side 27i2 relative to triangular surface 28b2, causing insertion piece 36e to protrude, and trapezoidal bent piece 36c is bent outward along side 27f1 relative to triangular joint surface 28e. Next, it is bent outward along sides 27a, 27b, 27c, 27d, and 27e, and then inward along side 27f2. In this way, insertion piece 36d of triangular surface 28b1 is inserted into insertion opening 36g on the triangular surface 28b2 side, and insertion piece 36e of triangular surface 28b2 is inserted into insertion opening 36f on the triangular surface 28b side, so that sides 27i1 and 27i2 are adjacent and integrated to form adjacent side 27i, and triangular surfaces 28b1 and 28b2 are adjacent and integrated and fixed to form rectangular opening surface 28b.

As a result, the third body member 36 can be configured as a third body part 28 having a quadrangular pyramid shape with the rectangular opening surface 28b as the bottom surface and four surfaces, namely the triangular outer surface 28a, the triangular joint surface 28d, the triangular inner surface 28c, and the triangular joint surface 28e, each of which has its vertex at vertex 27.
In this way, the third body part 28 having a square pyramid shape as shown in Figures 7a and 7b is formed.
In the third fuselage part 28 having a quadrangular pyramid shape, the triangular bent piece 36a, the trapezoidal bent piece 36b, and the trapezoidal bent piece 36c are woven into the interior of the third fuselage part 28 and are fixed by inserting the insertion piece 36d into the insertion opening 36g and the insertion piece 36e into the insertion opening 36f. As a result, one side 37a of the triangular bent piece 36a and one side 37b of the trapezoidal bent piece 36b rest on the triangular joint surface 28e, so the third fuselage part 36 can have the triangular bent piece 36a and the trapezoidal bent piece 36b inside as reinforcing members that improve strength in the vertical direction. Furthermore, because the other side 37c of the triangular bent piece 36a and the other side 37d of the trapezoidal bent piece 38b are placed perpendicular or substantially perpendicular to the triangular joint surface 28d, the third fuselage member 36 can have the triangular bent piece 36a and the trapezoidal bent piece 36b inside as reinforcing members that improve strength in the left-right direction, thereby increasing the strength of the third fuselage part 28.

(Fourth fuselage member)
Next, a fourth body member 38 shown in Figure 15 is a flat body member for forming the fourth body part 30. By bending this fourth body member 38, it is possible to form the quadrangular pyramid-shaped fourth body part 30. In other words, the fourth body member 38 can be said to be a development view of the fourth body part 30 shown in Figures 8(a) and 8(b).
As described above, the fourth body part 30 is a three-dimensional part having a quadrangular pyramid shape that is vertically symmetrical to the third body part 28, and therefore the fourth body member 38 is also a member that is vertically symmetrical to the third body member 36.
The fourth fuselage member 38 has a portion that becomes the triangular outer surface 30a of the fourth fuselage part 30, two portions that become triangular surfaces 30b1 and 30b2 that make up the rectangular opening surface 30b, a portion that becomes the triangular inner surface 30c, a portion that becomes the triangular joining surface 30d, a portion that becomes the triangular joining surface 30e, a portion that becomes the triangular extension piece 30f, and, although not visible on the front side, a triangular bent piece 38a on the outside of the triangular surface 30b1, a trapezoidal bent piece 38b on the outside of the triangular surface 30b1, and a trapezoidal bent piece 38c on the outside of the triangular joining surface 30e.

Side 29a is the outer fold curve between triangular outer surface 30a and triangular surface 30b1, side 29b is the outer fold curve between triangular outer surface 30a and triangular joint surface 30d, and side 29c is the outer fold curve between triangular outer surface 30a and triangular joint surface 30e.
Side 29d is an outer fold line between triangular inner surface 30c and triangular surface 30b2, side 29e is an outer fold line between triangular inner surface 30c and triangular joint surface 30d, side 29f1 is an outer fold line between triangular joint surface 30e and trapezoidal folded piece 38c, and side 29f2 is an inner fold line between triangular inner surface 30c and triangular extension piece 30f. When folded into fourth fuselage part 30, sides 29f1 and 29f2 are adjacent to each other and become integrated side 29f.

Furthermore, when the fourth body part 30 is bent, the side 29g1 of the triangular surface 30b2 and the side 29g2 of the triangular joining surface 30d are adjacent to each other and integrated together to form one side 29g of the rectangular opening surface 30b.
Furthermore, when the fourth body part 30 is bent, the side 29h1 of the triangular surface 30b1 and the side 29h2 of the triangular joining surface 30e are adjacent to each other and integrated together to form one side 29h of the rectangular opening surface 30b.
The side 29i1 is an outer bending line between the triangular face 30b1 and the triangular bent piece 38a, and the side 29i2 is an outer bending line between the triangular face 30b2 and the trapezoidal bent piece 38b.

When the sides 29i1 and 29i2 are folded to form the fourth body part 30, the triangular faces 30b1 and 30b2 are combined in the opposite directions to form the rectangular opening face 30b consisting of the four sides 29a, 29g, 29d, and 29h, and the sides 29i1 and 29i2 become adjacent and integrated side 29i.
When the triangular bending piece 38a is bent along the side 29i1, a notch is made on one side of the side 29i1 toward the triangular bending piece 38a so that the convex insertion piece 38d protrudes from the triangular surface 30b1 through the side 29i1 toward the triangular bending piece 38a, and on the other side, an insertion port 38f is provided on the side 29i1 for inserting and fixing a convex insertion piece 38e (described later) of the same shape as the insertion piece 38d.
In addition, side 29i2 has an insertion port 38g at a position on side 29i2 where insertion port 38d on side 29i1 can be inserted when trapezoidal bending piece 38b is bent along side 29i2, and a convex insertion piece 38e for insertion is provided at a position where it can be inserted into insertion port 38f on side 29i1 so as to protrude from triangular surface 30b2, via side 29i2, toward trapezoidal bending piece 38b.

Furthermore, four pairs of second push-in portions 42 are provided on the triangular joint surface 30d at positions corresponding to the four pairs of first push-in portions 41 on the triangular joint surface 24b so that the triangular joint surface 30d is joined to one side of the triangular joint surface 24b of the second fuselage part 24 when configured as the fourth fuselage part 30.
Furthermore, on the side 29h2 of the triangular joining surface 30e and on the side of the vertex 29 of the extension piece 30f, one fourth push-in portion 44 is provided at a position corresponding to the two third push-in portions 43 on one half of the longitudinal direction of the boomerang joining member 20b shown in Figure 3 so that when configured as the fourth body part 30, they are joined to one half of the longitudinal direction of the boomerang joining member 20b, and two fastening holes 49 are provided on the outside of each of them.
Furthermore, two fastening holes 49 are provided on the side 29h1 of the triangular surface 30b1, corresponding to the two fastening holes 49 of the triangular joining surface 30e.
The second pushing portion 42, the fourth pushing portion 44, and the fastening hole 49 are as described above, and therefore will not be described again.

In the fourth body member 38, triangular bent piece 38a is bent outward along side 29i1 relative to triangular surface 30b1, causing insertion piece 38d to protrude, trapezoidal bent piece 38b is bent outward along side 29i2 relative to triangular surface 30b2, causing insertion piece 38e to protrude, and trapezoidal bent piece 38c is bent outward along side 29f1 relative to triangular joint surface 30e. Next, it is bent outward along sides 29a, 29b, 29c, 29d, and 29e, and then bent inward along side 29f2. In this way, insertion piece 38d of triangular surface 30b1 is inserted into insertion opening 38g on the triangular surface 30b2 side, and insertion piece 38e of triangular surface 30b2 is inserted into insertion opening 38f on the triangular surface 30b side, so that sides 29i1 and 29i2 are adjacent and integrated to form adjacent side 29i, and triangular surfaces 30b1 and 30b2 are adjacent and integrated and fixed to form rectangular opening surface 30b.

As a result, the fourth body member 38 can be configured as a fourth body part 30 having a quadrangular pyramid shape with the rectangular opening surface 30b as the bottom surface and the triangular outer surface 30a, the triangular joint surface 30d, the triangular inner surface 30c, and the triangular joint surface 30e as four surfaces, each with its vertex at vertex 29.
In this way, the fourth fuselage part 30 having a square pyramid shape as shown in Figures 8a and 8b is formed.
In the quadrangular pyramidal fourth fuselage part 30, the triangular bent piece 38a, the trapezoidal bent piece 38b, and the trapezoidal bent piece 38c are woven into the interior of the fourth fuselage part 30 and are fixed in place by inserting the insertion piece 38d into the insertion opening 38g and the insertion piece 38e into the insertion opening 38f. As a result, one side 39a of the triangular bent piece 38a and one side 39b of the trapezoidal bent piece 38b rest on the triangular joint surface 30e, so the fourth fuselage part 38 has the triangular bent piece 38a and the trapezoidal bent piece 38b inside as reinforcing members that improve strength in the vertical direction. In addition, because the other side 39c of the triangular bent piece 38a and the other side 39d of the trapezoidal bent piece 38b are placed perpendicular or co-perpendicular to the triangular joint surface 30d, the fourth body member 38 can have the triangular bent piece 38a and the trapezoidal bent piece 38b inside as reinforcing members that improve strength in the lateral direction, thereby increasing the strength of the fourth body part 30.

9, the four pairs of first press-in portions 41 on the upper side of the triangular joining surface 24b of the second fuselage part 24 and the four pairs of second press-in portions 42 on the triangular joining surface 28d of the third fuselage part 28 are aligned and overlapped so that their respective alignment holes 48 match, and then the two are pressed together to join, thereby integrating the second fuselage part 24 and the third fuselage part 28. Similarly, the four pairs of first press-in portions 41 on the lower side of the triangular joining surface 24b of the second fuselage part 24 and the four pairs of second press-in portions 42 on the triangular joining surface 30d of the fourth fuselage part 30 are aligned and overlapped so that their respective alignment holes 48 match, and then the two are pressed together to join, thereby integrating the second fuselage part 24 and the fourth fuselage part 30.

Next, in FIG. 9 , with the triangular mating surface 24b of the second fuselage part 24 facing the opposite direction, i.e., with the triangular mating surface 24b on the right and the vertex 25 on the left, the triangular mating surface 30d of the fourth fuselage part 30 is joined to the upper side of the triangular mating surface 24b, and the triangular mating surface 28d of the third fuselage part 28 is joined to the lower side of the triangular mating surface 24b.
The triangular joint surface 28e of the upper third fuselage part 28 joined to the two second fuselage parts 24 in this way and the triangular joint surface 30e of the fourth fuselage part 30 are arranged in a line, and the triangular joint surface 28e and the triangular joint surface 30e are joined by the boomerang joint member 20b.
Next, the triangular joint surface 30e of the lower fourth fuselage part 30 joined to the two second fuselage parts 24 and the triangular joint surface 28e of the third fuselage part 28 are aligned, and the triangular joint surface 30e and the triangular joint surface 28e are joined with the boomerang joint member 20b.
In this way, two third fuselage parts 28 and two fourth fuselage parts 30 can be integrated to assemble one opening forming portion 14 having one opening 15 as shown in Figures 1 and 2(a).

Next, the push joints for easily joining the first, second, third and fourth fuselage sections 22, 24, 28 and 30 will be described.
After aligning and overlapping the first push-in portion 41 and the second push-in portion 42, the first push-in portion 41 is pushed toward the second push-in portion 42, thereby easily and quickly joining the extension pieces together, the body parts together, and the extension pieces or the body parts and the boomerang joining member.
As shown in Figures 16 and 17 , the first pushing portion 41 is bent together with the second pushing portion 42 while overlapping the second pushing portion 42, and enters the inside of the insertion hole 51. The insertion hole 51 is a hole formed in the extension pieces 22e1 and 22f1 (i.e., the extension pieces on the outer surface side of the first body member 32) on which the second pushing portion 42 is provided as the second pushing portion 42 is bent. When the first pushing portion 41 enters the inside of the insertion hole 51, the protrusions 47 provided on both sides of the continuous portion 46 of the first pushing portion 41 bend, as shown in Figure 16 . Then, when the first pushing portion 41 is completely inserted into the insertion hole 51, the bent protrusions 47 return to their original positions and engage with the edge of the insertion hole 51, as shown in Figure 16 .

The above operation is repeated for all of the first push-in portions 41 provided on extension pieces 22e2 and 22f2 of the two overlapping extension pieces. As a result, extension pieces 22e1 and 22e2 are joined together, and extension pieces 22f1 and 22f2 are joined together, producing the first body part 22. As described above, in this embodiment, a simple one-touch operation of pushing in the first push-in portions 41 can join the extension pieces of the first body member 32 and the second body member 34 together, and the joining surfaces of the second body part 24, the third body part 28, and the fourth body part 30 together, etc.
Furthermore, the worker presses in the third pressing portion 43 provided at the center of the extension pieces 22e2 and 22f2 in the extension direction to more firmly fasten the extension pieces together. More specifically, the third pressing portion 43 and the fourth pressing portion 44 are overlapped so that they face each other. By aligning the alignment hole 48 provided in the third pressing portion 43 with the alignment hole 48 provided in the fourth pressing portion 44, the third pressing portion 43 and the fourth pressing portion 44 can be accurately and easily overlapped.

After overlapping the third pushing portion 43 and the fourth pushing portion 44, the operator pushes the third pushing portion 43 toward the fourth pushing portion 44. As a result, as shown in Figures 18 and 19, the third pushing portion 43 bends together with the fourth pushing portion 44 while overlapping with it, and enters the inside of the insertion hole 52. The insertion hole 52 is a hole formed in the extension pieces 22e1 and 22f1 on which the fourth pushing portion 44 is provided, as the fourth pushing portion 44 is bent. When the third pushing portion 43 enters the inside of the insertion hole 52, the protrusions 47 provided on both sides of the connecting portion 46 of the third pushing portion 43 bend, as shown in Figure 18. When the third pushing portion 43 is completely inserted into the insertion hole 52, the bent protrusion 47 returns to its original position and engages with the edge of the insertion hole 52, as shown in Figure 18.

In this embodiment, the direction of extension of the bending line L1 of the first pressing portion 41 intersects with the direction of extension of the bending line L3 of the third pressing portion 43. Correspondingly, the direction of extension of the bending line L2 of the second pressing portion 42 intersects with the direction of extension of the bending line L4 of the fourth pressing portion 44. In other words, the bending directions are different between the first pressing portion 41 and the third pressing portion 43. More specifically, the orientations of the protrusions 47 that engage with the edges of the insertion holes 51 and 52 are different. This allows the extension pieces to be fastened together more firmly, and specifically, prevents the overlapping extension pieces from separating from each other and creating a gap between the extension pieces.
Thereafter, to further firmly fasten the overlapping extension pieces together, a fastening member is passed through the fastening holes 49 provided on each extension piece, and the extension pieces are fastened together with the fastening member. In this embodiment, the extension pieces are fastened together by pushing the first and third pushing members 41 and 43, thereby reducing the number of fastening operations using the fastening member, and thus facilitating the fabrication of the first and second fuselage components 22, 24. Furthermore, reducing the number of fastening operations reduces the number of unfastened portions. Furthermore, reducing the amount of fastening member used reduces the amount of waste generated during assembly or disassembly of the dome fuselage structure 10.

The dome fuselage structure, dome structure unit, and fuselage member of the present invention are basically configured as described above, and have the following features and effects.
First, as shown in FIG. 1 , the dome fuselage structure 10 of the present invention is composed of one or more fuselage sections 16. The fuselage section 16 is composed of four fuselage components 22, 24, 28, and 30 shown in FIGS. 4 , 5 , 7 , and 8 , which are fabricated from four fuselage members 32, 34, 36, and 38 shown in FIGS. 11 , 13 , 14 , and 15 , respectively. Therefore, the fuselage section 16 can be fabricated by repeatedly fabricating the fuselage components 22, 24, 28, and 30. This allows workers to reliably learn the work content and prevents boredom in the work, thereby preventing human error. As a result, fuselage sections can be fabricated with improved work efficiency.
The fuselage section is composed of parts that are symmetrical in both the vertical and horizontal directions when viewed from the side, so that it can be produced without increasing the number of different parts, thereby improving the ease of assembly of the fuselage section, and therefore the dome fuselage structure.

The body is symmetrical from front to back and/or left to right when viewed from above, so the spatial layout of the body (for example, a four-and-a-half-tatami room in the Edo era) matches the usual square-based living style, allowing the user to live comfortably in their daily life (it is also easy to use in conjunction with ordinary furniture layouts and layouts in gymnasiums, etc.).
Furthermore, because the body is made up of an even number of parts in a plan view, when multiple units are placed in a limited area, the openings can be arranged facing each other, and the unit can be placed to match the flow of people and objects, providing high connectivity and expandability.In contrast, geodesic domes, which are conventional technology, are made up of an odd number of parts in a plan view, which creates the problem of dead space for arranging furniture, etc.
10, the dome-shaped structure 80 can be placed and fixed on the body portion 16, i.e., the dome body structure 10, thereby reducing the size and installation area of the dome-shaped structure 80. The body portion 16 allows the dome-shaped structure 80 to be made taller, so the height of the entire dome structure unit 100 can be increased, thereby increasing the storage space.

The first to fourth fuselage components 22, 24, 28, and 30 are formed by folding back the first to fourth fuselage members 32, 34, 36, and 38, respectively, and therefore each has a thickness in some areas, forming an enveloping structure that creates a space inside, thereby improving strength against the load (vertical direction) from the dome-shaped structure 80.
Furthermore, the above-described wrapping structure creates a space inside, allowing air to be trapped inside, thereby improving the heat insulation of the body portion 16.
Furthermore, the above-described enveloping structure allows the surface functionality to be displayed on the storage space side as well. Providing a waterproof function on the outer surface also provides a waterproof function on the inner storage space side. Furthermore, the linings of the materials of the first to fourth body members 32, 34, 36, and 38 are not exposed on the surface.

The third and fourth fuselage parts 28 and 30 can have folded pieces or folded extension pieces embedded therein by folding the third and fourth fuselage parts 28 and 30 along the respective creases (fold lines). That is, the third and fourth fuselage parts 28 and 30 can have triangular folded pieces 36a, trapezoidal folded pieces 36b, triangular folded pieces 38a, trapezoidal folded pieces 38b embedded therein, which serve as reinforcing members for improving strength in the vertical direction.
This improves the strength of the body portion 16 against the load (in the vertical direction) from the dome-shaped structure 80 .
Furthermore, by configuring the third and fourth body parts 28 and 30 so that the folded pieces or folded extension pieces are pulled inward, it is possible to prevent the opening 15 of the opening forming portion 14 made by the third and fourth body parts from bulging.
The cross section of the cardboard material is not placed on the surface, which improves the strength of the body. If the cross section is exposed on the surface, moisture can get in and reduce the strength of the cardboard, but because the cross section is not exposed on the surface, moisture cannot get in and the strength of the cardboard will not be reduced.
Furthermore, by providing an opening 15 in the fuselage portion 16, i.e., the dome fuselage structure 10, people and objects can enter the internal storage space without providing an opening in the dome-shaped structure 80.

The first to fourth fuselage parts have push-type joints on the extension pieces, allowing each fuselage part to be joined with a single touch, thereby improving work efficiency when fabricating the fuselage section and dome fuselage structure.
By joining by fitting, the folded piece or the folded extension piece can be internalized, which prevents the joint from being exposed on the surface. As a result, moisture and the like can be prevented from entering the body part, and a decrease in strength can be prevented.
By joining the upper and lower ends of the fuselage of the dome fuselage structure with a boomerang joint using a boomerang joint member, the load (vertical direction) from the dome-shaped structure can be uniformly supported at the upper end of the fuselage, thereby uniformly canceling out the outward component force due to the load from the dome-shaped structure.
The members are arranged symmetrically in the vertical and horizontal directions with respect to the constriction, specifically, the center point that is recessed inward from the outer surface of the body portion.
By positioning the opening of the opening forming portion and the central region of the wall forming portion inward, the outward component force due to the load from the dome-shaped structure can be offset at the dome fuselage structure, i.e., the upper end of the fuselage, thereby improving the strength of the fuselage.

The construction and manufacturing method of the dome fuselage structure of the present invention will be briefly described below.
The fuselage section of the dome fuselage structure of the present invention is composed of an even number of wall-forming sections and opening-forming sections, which are composed of the first to fourth fuselage parts that are enveloping structures, in total, eight components in the illustrated example. Specifically, the fuselage section is composed of four wall-forming sections and four opening-forming sections.
The wall forming portion is comprised of a first body part and a second body member.
The first body part is formed by folding back the first body member along a plurality of folding lines including the center, folding back the peripheral extension pieces, and overlapping and joining the extension pieces.
The second body part is formed by folding back the second body member along a plurality of folding lines including the center, folding back the peripheral extension pieces, and overlapping and joining the extension pieces.
The extension pieces of the first fuselage part and the second fuselage part are joined together.
The opening forming portion is composed of a third body part and a fourth body member that are vertically symmetrical.
The third fuselage part is formed by folding the third fuselage member along each folding line, and fitting the convex and concave portions together.
The joining region of the third fuselage part is placed opposite the joining region of the second fuselage part, and they are joined at a joint.
The fourth fuselage part is formed by folding the fourth fuselage member along the folding lines, and fitting the convex and concave portions together.

Since the dome fuselage structure of the present invention is configured as described above, an operator can repeatedly create an even number of fuselage parts, such as eight, from fuselage members, and then join the required number of fuselage parts with a single touch using the push-type joints to form the dome fuselage structure.
This allows the workers to reliably learn the work content and prevents them from becoming bored with the work, thereby preventing human error and enabling the dome fuselage structure to be manufactured.
For example, if a work team is made up of three workers, and there are four teams (12 workers), each team will need to make two pieces to form the body.
This can provide the above-mentioned effect of preventing human error.
Next, the worker can form the mating portion by binding the fuselage parts together with a binding member such as a binding band.
As a result, even when using binding members such as cable ties, by providing a push-type joint, the number of binding members such as cable ties used can be reduced, thereby improving work efficiency.

The first to fourth fuselage components are formed by folding back the first to fourth fuselage members, respectively, to form a double-wall structure, which improves strength against the load (vertical direction) from the dome-shaped structure.
Furthermore, the double-wall structure allows an internal space to be formed and air to be contained therein, thereby improving the thermal insulation of the dome fuselage structure, i.e., the fuselage portion.
The third and fourth fuselage parts have a configuration in which the fold-in pieces and fold-out extension pieces are folded inward. That is, the third and fourth fuselage parts have the fold-in pieces and fold-out extension pieces built in. This provides support, improving the strength of the dome fuselage structure against the load (in the vertical direction) from the dome-shaped structure.
By aligning the alignment holes at the joining parts and pressing the protrusion side, the components can be joined with a single touch.

In the dome-shaped body structure of the present invention, the central regions of the opening-forming portion and the wall-forming portion are located inward, so that the weight of the dome-shaped structure causes a force to spread outward, i.e., acts outward. This force is offset by the dome-shaped body structure (body portion) in the central regions of the opening-forming portion and the wall-forming portion. In other words, the dome-shaped body structure (body portion) can cancel out the outward force acting from the lower end of the dome-shaped structure. This improves the load-bearing strength of the dome-shaped structure.
That is, the force acting on the opening of the opening forming portion of the dome body structure due to the weight of the dome-shaped structure is a force acting in the vertical direction of the opening forming portion, and when this force is resolved into the top and bottom of the opening, a force remains that opens the opening to the left and right. When this force is resolved into the circumferential and radial directions of the body portion, the circumferential force is canceled out, and only a radial force acting outward remains. This also remains as a component force in the central region of the wall forming portion.

On the other hand, since the central region of the wall forming portion is located inward, the weight of the dome-shaped structure acts as a pushing force from above along the wall surface of the wall forming portion, and when this component force is taken into consideration, the force acts radially inward in the central region of the wall forming portion.
As a result, the radially outward force remaining in the central region of the wall forming portion and the radially inward force in the central region of the wall forming portion cancel each other out.
As a result, it can be seen that the dome fuselage structure (fuselage portion) cancels the force acting outward from the lower end of the dome-shaped structure.
In other words, since the opening forming portion and the central region of the wall forming portion of the dome body structure are located inward, it can be seen that the weight of the dome-shaped structure acting on the opening forming portion and the weight of the dome-shaped structure acting on the wall forming portion cancel each other out.
In other words, the weight of the dome-shaped structure is distributed because the neck of the fuselage, the cylindrical shape, and the dome-shaped structure are joined to the dome-shaped fuselage structure along the circumference. Note that the neck is provided in the dome-shaped fuselage structure to prevent separation at the joints when the fuselage parts are joined.

In the present invention, the upper and lower ends of the fuselage of the dome-shaped fuselage structure are joined by a boomerang joint. The upper end of the opening-forming portion of the fuselage abuts against the lower end of the dome-shaped structure, and the upper and lower ends of the fuselage are joined by the boomerang joint.
In the present invention, by joining the upper and lower ends of the body with boomerang joints, the load (in the vertical direction) from the dome-shaped structure can be uniformly supported at the upper end of the body.
This makes it possible to uniformly cancel out the outward component force due to the load from the dome-shaped structure.

The dome fuselage structure, dome structure unit, and fuselage member of the present invention have been described in detail above using embodiments, but the present invention is not limited to these embodiments, and various improvements and modifications may of course be made without departing from the spirit and scope of the present invention.

DESCRIPTION OF SYMBOLS 10 Dome fuselage structure 12 Wall forming section 14 Opening forming section 15 Opening 16 Fuselage section 18 Boomerang joint section 20a, 20b Boomerang joint member 22 First fuselage part 22a, 22b, 24a, 28a, 30a Triangular outer surface 22c, 24b, 28d, 28e, 30d, 30e Triangular joint surface 22d, 24c, 24d, 28c, 30c Triangular inner surface 22e, 22e1, 22e2, 22f, 22f1, 22f2, 24e, 24e1, 24e2, 24f, 24f1, 24f2, 28f, 30f Extension piece 23, 25, 27, 29 Vertex 23a, 25d Center adjacent line 23b, 25a, 27a, 27d, 27g, 29a, 29d, 29g Opposite sides 23a1, 23a2, 23c, 23d, 23e, 23e1, 23e2, 23f, 23f1, 23f2, 25b, 25c, 25d, 25d1, 25d2, 25e, 25e1, 25e2, 25f, 25f1, 25f2, 27b, 27c, 27e, 27f, 27f1, 27f2, 27g1, 27g2, 27h, 27h1, 27h2, 27i, 27i1, 27i2, 29b, 29c, 29e, 29f, 29f1, 29f2, 29g1, 29g2, 29h, 29h1, 29h2, 29i, 29i1, 29i2 Side 24 Second fuselage part 26 Center point 28 Third fuselage part 28b, 30b Opening surface 28b1, 28b2, 30b1, 30b2 Triangular surface 30 Fourth fuselage part 32 First fuselage member 32a, 32b, 34a, 34b, 36a, 38a Triangular bent piece 33a, 33b, 33c, 35a, 35b, 35c Cutting line 33d, 33e Tip piece 34 Second fuselage member 36 Third fuselage member 36b, 36c, 38b, 38c Trapezoidal bent piece 36d, 36e, 38d, 38e Insertion piece 36f, 36g, 38f, 38g Insertion port 38 Fourth fuselage member 40 Push-type joint 41 First push-in portion 42 Second push-in portion 43 Third push-in portion 44 Fourth push-in portion 45 Root portion 46 Continuation portion 47 Protrusion portion 48 Alignment hole 49 Fastening hole 50 Extension portion 51, 52 Insertion hole 53 Notch 54 Triangular piece 56 Binding member 80 Dome-shaped structure 82, 84, 86, 88 Panel 86a, 86b, 86c Outer surface 90 Dome piece 100 Dome structure unit L1, L2, L3, L4 Bending line

Claims (14)

A dome fuselage structure having a fuselage section at least at the lowest stage, the fuselage section being configured by combining a plurality of wall forming sections and at least one opening forming section so as to surround a space,
A dome-shaped structure that is closed except for its underside is placed and supported on the upper side of the dome fuselage structure, and the lower side of the dome fuselage structure is directly or indirectly supported on the ground or floor surface,
The outer edge of the upper end of the body portion and the outer edge of the lower end of the body portion are the same size,
each of the plurality of wall forming portions includes an even number of first fuselage parts and an even number of second fuselage parts adjacent to the first fuselage parts;
the opening forming portion has an even number of third fuselage parts and an even number of fourth fuselage parts each adjacent to the third fuselage parts, and has an opening formed by being surrounded by the even number of third fuselage parts and the even number of fourth fuselage parts,
a dome-shaped fuselage structure in which one vertex corresponding to a long side of each of the triangles of the first fuselage part and the second fuselage part in a side view is located at a center position of the wall forming part, the first fuselage part is located above and below the center position and is vertically symmetrical in a side view, the second fuselage part is located left and right about the center position and is left and right symmetrical in a side view, and the center position is located inward from the periphery of the wall forming part . The dome fuselage structure according to claim 1 , wherein the first fuselage part and/or the second fuselage part are each an enveloping structure forming a space therein. The dome fuselage structure according to claim 1 or 2, wherein the third fuselage part and/or the fourth fuselage part are each an enveloping structure forming a space therein. A dome fuselage structure according to any one of claims 1 to 3, wherein the outer edge of the upper end of the fuselage section and the outer edge of the lower end of the fuselage section are the same size. a total number of the plurality of wall forming portions and the at least one opening forming portion is an even number,
The dome fuselage structure of claim 1 , wherein the fuselage section is symmetrical in plan view. 6. The dome fuselage structure according to claim 1, wherein one vertex corresponding to a long side of each of the triangles of the first fuselage part and the second fuselage part in side view is located inward from an outer surface of the fuselage section. A dome fuselage structure as described in any one of claims 1 to 6, wherein the opening of the opening forming portion is located inward from the outer surface of the fuselage portion. A dome fuselage structure as described in any one of claims 1 to 7, wherein at least one of the first fuselage part and the second fuselage part has an extension piece extending outward. A dome fuselage structure as described in any one of claims 1 to 8, wherein at least one of the third fuselage part and the fourth fuselage part has an extension piece extending outward. the first fuselage part and the second fuselage part each have a push-in portion for joining with another part ;
10. The dome fuselage structure according to claim 1, wherein the first fuselage part and the second fuselage part are joined to the other part by overlapping the push-in portions of the first fuselage part and the second fuselage part with each other, and then pressing one of the overlapping push-in portions into the other part, causing both of the overlapping push-in portions to bend . the third fuselage part and the fourth fuselage part each have a push-in portion for joining with another part ;
The dome fuselage structure according to any one of claims 1 to 10, wherein the third fuselage part and the fourth fuselage part are joined to the other part by overlapping the push-in portions of the third fuselage part and the fourth fuselage part with each other, and then pressing one of the two overlapping push-in portions into the other part, causing both of the overlapping push-in portions to bend . vertices corresponding to the long sides of the triangle of the third body part in a side view are located at the upper right and lower left vertices of the opening forming portion, respectively, and vertices corresponding to the long sides of the triangle of the fourth body part in a side view are located at the upper left and lower right vertices of the opening forming portion,
an opening surface is located at the position of the long side of the triangle in side view of each of the third fuselage part and the fourth fuselage part;
the openings of the opening forming portion are formed by the respective opening surfaces,
The dome fuselage structure according to any one of claims 1 to 11 , wherein the opening is located inward from the periphery of the opening forming portion. A dome fuselage structure according to any one of claims 1 to 12 ;
a dome-shaped structure placed on and fixed to the upper side of the dome fuselage structure. A fuselage member used in the dome fuselage structure according to any one of claims 1 to 12 ,
Fuselage members used as flat plate-shaped first fuselage member, second fuselage member, third fuselage member, and fourth fuselage member for respectively forming the first fuselage part, the second fuselage part, the third fuselage part, and the fourth fuselage part that constitute the dome fuselage structure.