JP2003291897A - Inflatable structure - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide an inflatable structure capable of achieving an assured expanded status with provision for avoiding the breakage of bags during the expansion, while permitting lightweight and small size. <P>SOLUTION: In the inflatable structure for inflation expansion of foldable bags 10 in which a hardened compound layer of fiber-reinforced resin is provided between inner and outer film layers, the bag 10 has an inner which is compartmented by a plurality of closed parts 10a, 10b, etc., expanding means 20a, 30a, 40a, etc., deposited for each closed part 10a, 10b, etc., and control means for controlling each expanding means 20a, 30a, 40a, etc., independently. <P>COPYRIGHT: (C)2004,JPO

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an inflatable structure, and more particularly to an inflatable structure which is stored in a predetermined storage portion in a folded state and can be inflated and deployed in outer space or on the ground.

[0002]

2. Description of the Related Art With the recent development of aerospace technology,
Missions for constructing large structures such as large antennas, sun shields, and condenser mirrors in outer space are being carried out. This type of large structure is usually stored in the storage part of the rocket in a state of being folded small on the ground, and is expanded and deployed in outer space after being launched, so various deployment methods are adopted.

As a conventional deployment method, a so-called "deployment truss mechanism" is employed which deploys a plurality of space trusses by an actuator. However, this deployable truss mechanism is complicated in structure because the truss members cannot be freely folded and various mechanisms for connecting these truss members are required. As a result, the weight of the entire structure is increased and the manufacturing cost is increased, but the reliability of the deployment mechanism is low.

Therefore, an inflatable structure has been proposed and is being put into practical use, which constitutes a foldable bag body made of a predetermined composite material and expands and deploys the bag body like a balloon in internal space by internal pressure. Conventionally, the bag body of the inflatable structure has been composed of a molding layer made of a composite material made of a thermosetting (or thermoplastic) resin, and a film layer covering the inside and outside of the molding layer. . Then, after expanding and expanding this bag in outer space, the molded layer is heated and cured to obtain a desired three-dimensional structure.

[0005]

The inflatable structure is provided with a gas supply mechanism for inflating the bag body. The conventional gas supply mechanism is composed of a cylinder 200, a valve 300 and a pipe 400 as shown in FIG. Then, the gas stored in the cylinder 200 is supplied to the inside of the bag body 100 through the pipe 400 while controlling the supply amount with the valve 300.
The whole 0 was developed at once.

However, if the conventional deployment method of deploying the entire bag at once by the gas supply mechanism is adopted, the following problems may occur.

That is, the bag body 100 (FIG.
As a result of supplying the gas inside the bag (see (a)),
There is a risk that a part of the bag 100 will come into contact with the inner wall 510 of the predetermined storage section 500 (see FIG. 11B) and a part of the bag body 100 will be damaged. Further, depending on the folding method and the storage form of the bag body 100, the whole or a part of the bag body 100 may have a predetermined storage portion 50.
There is a possibility that the bag 100 does not come out from 0 and the expansion of the bag 100 is hindered (see FIG. 11C). It is considered that such problems as described above become more remarkable as the size of the inflatable structure increases.

Wastes such as satellites and rockets whose missions have been completed may be used while the entire bag is unfolded at once by the gas supply mechanism and before the molded layer of the unfolded bag is heated and cured. (Space debris) and meteorites may collide with the bag. When such a situation occurs, the gas used for deployment leaks out from the bag body, which may cause a malfunction of the entire inflatable structure. Such a problem may significantly hinder the future increase in size of the inflatable structure (total length of several kilometers).

A conventional gas supply mechanism (see FIG. 9)
Since it has the cylinder 200 and the valve 300, there is a limit to miniaturization. Therefore, when the inflatable structure is applied to an ultralight small satellite, the weight and volume of the gas supply mechanism becomes relatively large with respect to the bag body, which hinders the weight reduction and downsizing of the inflatable structure. It was.

An object of the present invention is to provide an inflatable structure which can prevent the bag body from being damaged at the time of deployment and can surely realize the deployed state, and which can be reduced in weight and size. Is.

[0011]

In order to solve the above-mentioned problems, the invention according to claim 1 discloses, for example, as shown in FIGS. 1 and 2, a cured molding layer made of fiber reinforced resin between inner and outer film layers. In a inflatable structure having a foldable bag body provided with, and a deployment means for inflating and deploying the bag body, the bag body is configured such that the inside thereof is partitioned into a plurality of closed portions, It is characterized in that it is provided with a deployment means for deploying each of the partitioned closing portions, and a control means for independently controlling the deployment means.

According to the first aspect of the present invention, the inside of the bag body is divided into a plurality of closed portions, and the divided closed portions are independently expanded by the expansion means under the control of the control means. You can Therefore, it is possible to solve various problems at a time when the conventional deployment method in which the entire bag is deployed at once is adopted.

Specifically, even if a part of the bag body is damaged when it comes into contact with a predetermined storage portion when the bag body is unfolded, it is possible to stop the damage only to that portion, and Can be expanded in parts. Further, by sequentially deploying from the one end side of the bag body, it is possible to prevent all or a part of the bag body from coming out of the predetermined storage portion and hindering the deployment, and it is possible to realize a completely deployed state. . Furthermore, since it can be expanded and cured for each of the divided closed portions of the bag,
For example, even when space debris or meteorites collide with the expansion-hardened closed portion, the entire inflatable structure does not malfunction.

The invention according to claim 2 is the inflatable structure according to claim 1, wherein, for example, FIGS.
As shown in FIG. 5, the closing part includes the expanding means inside thereof and has a expanding part which is expanded by the expanding means, and the expanding means is a gas filling filled with gas supplied to the expanding part. Portion, a sealing portion made of a thermoplastic resin provided between the developing portion and the gas filling portion, and heating means for heating and melting the sealing portion, and the sealing portion by the heating means. It is characterized in that the gas filled in the gas filling section is supplied to the developing section to be expanded through a through hole formed by heating and melting.

According to the second aspect of the present invention, the expanding means is provided inside the closing portion, and the expanding means is provided with a through hole formed by heating and melting the seal portion by the heating means. Since the gas filled in the gas filling part is supplied to the expanding part to expand it, it is possible to make it much lighter and smaller than the conventional expanding means (gas supply mechanism) equipped with a cylinder and a valve. Become. Therefore, it is possible to reduce the weight and size of the inflatable structure itself.

[0016]

BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of the present invention will be described below in detail with reference to the drawings.

[First Embodiment] As shown in FIG. 1, an inflatable structure 1 according to the present embodiment is used as a ring of a large planar antenna 60 constructed in outer space or a large sun. It is used as a skeleton of the shield 70. The inflatable structure 1 includes a bag body 10 that can be deployed into an annular body or a tubular body, a deployment means that supplies a predetermined gas to the bag body 10 to deploy the bag body, and a control means that controls the deployment means. Equipped with.

First, the structure of the bag 10 will be described.
FIG. 2 is a sectional view of the bag body 10 in the unfolded state (II in FIG. 1).
-II is a sectional view of a portion). As shown in FIG. 2, the bag body 10 includes a cured molding layer 11 formed by weaving a fibrous thermoplastic resin and reinforcing fibers together, and the cured molding layer 11
An outer film layer 12 provided on the outside so as to wrap
And an inner film layer 13 provided inside the hardening and molding layer 11.

The hardened and molded layer 11 is a layer that is heated and hardened and molded after the bag body 10 is unfolded by the unfolding means, which will be described later, and serves to retain the shape of the inflatable structure 1 after unfolding.

The cured molding layer 11 is one woven fabric (hereinafter referred to as "thermoplastic woven fabric") formed by weaving a fibrous thermoplastic resin and reinforcing fibers, or a plurality of the thermoplastic woven fabrics. It is constructed by stacking. The diameter of the fibrous thermoplastic resin is about several μm, and a bundle of thousands of these is used. When the thermoplastic resin is made fibrous in this manner, each fibrous thermoplastic resin has extremely high flexibility because the fiber diameter is small. Moreover, since the fibrous thermoplastic resins are not adhered or adhered to each other, high flexibility can be maintained even if they are bundled.

Examples of the fibrous thermoplastic resin include polyamide, PPS (polyphenylene sulfide), polypropylene, and polyetherimide. In the present embodiment, as the fibrous thermoplastic resin, “TEXXES” is used. (Trade name: Nitto Boseki Co., Ltd.) is used. Examples of the type of reinforcing fiber include glass fiber, carbon fiber, aramid fiber, alumina fiber and various metal fibers.

The hardened and molded layer 11 has a planar shape, and ends thereof are overlapped with each other by about 10 mm and joined to each other to form a part of the bag body 10. Examples of means for connecting the ends of the cured molding layer 11 include adhesion with a polyimide film tape having excellent heat resistance, fusion with a soldering iron, and the like.

Even if the cured molding layer 11 is formed by laminating a plurality of thermoplastic woven fabrics as described above, the storability does not deteriorate. That is, the fibrous thermoplastic resin itself has high flexibility as described above,
Even if a plurality of thermoplastic fabrics are laminated, it is difficult for these thermoplastic fabrics to adhere or adhere to each other, and therefore, it is possible to maintain high flexibility by slipping between the fibers during bending.

The outer film layer 12 serves to cover and protect the outside of the cured molding layer 11. The outer film layer 12 has high heat resistance capable of withstanding a severe temperature environment in outer space and a high temperature when heating the cured molding layer 11,
It is made of a material having a high pressure resistance that can withstand the pressure applied from the inside when the bag body 10 is inflated and deployed. Examples of the material having such characteristics include FEP (fluoroethylene propylene) and polyimide.

The outer film layer 12, like the cured molding layer 11, has planar ends whose ends are overlapped by about 10 mm and connected to each other, and is placed outside the cured molding layer 11 to form one of the bags 10. To be a part. Examples of means for connecting the ends of the outer film layer 12 include heat fusion, sewing with reinforcing fibers, and adhesion with a tape having excellent heat resistance. In addition, the outer film layer 12 is provided with a plurality of minute holes such that the thermoplastic resin does not flow out,
Ensure breathability.

The inner film layer 13 is provided inside the hardening and molding layer 11, has airtightness, and has a function of transmitting pressure applied from the inside to the hardening and molding layer 11 to expand and expand it. The inner film layer 13 is made of a material having high heat resistance capable of withstanding the high temperature when the thermosetting molding layer 11 is thermoformed. Examples of the material having such characteristics include FEP (fluoroethylene propylene) and polyimide.

The inner film layer 13 is arranged on the inner side of the hardened and molded layer 11 by stacking the end portions of the flattened one by about 10 mm and connecting them like the hardened and molded layer 11 and the outer film layer 12. It is a part of the bag body 10.
As a means for connecting the ends of the inner film layer 13 to each other, heat fusion capable of achieving high airtightness is preferable.

The inner film layer 13, the cured molding layer 11 and the outer film layer 12 are arranged in this order from the inside to form the bag body 10. Here, the diameter of the (circular) cross section of the inner film layer 13 when inflated without restriction is
It is slightly larger than the diameter of the (circular) cross section of the outer film layer 12. When the bag body 10 is a tubular body, the length of the inner film layer 13 in the tubular body length direction when inflated without restriction is made slightly longer than the length of the outer film layer 12. Keep it. By thus providing the dimensional difference in the diameter and length of the cross section between the inner film layer 13 and the outer film layer 12, the pressure applied from the inner side can be sufficiently transmitted to the curing molding layer 11.

Further, the cured molding layer 11 and the outer film layer 1
A film-shaped heater (not shown) is provided between the two. After the bag body 10 in the folded state is unfolded by the unfolding means described later to form an annular body or a tubular body having a circular cross section, the hardening molding layer 11 can be heated and hardened by the film heater. .

At this time, the thermoplastic resin in the thermoplastic fabric of the hardening / molding layer 11 can be melted by the film-shaped heater and allowed to permeate between the reinforcing fibers. The plastic resin can be solidified while permeating between the reinforcing fibers. As a result, the thermoplastic resin that is the matrix resin is reinforced by the reinforcing fibers, and a structure having extremely excellent strength and rigidity is constructed.

In the present embodiment, as shown in FIG. 3, the bag body 10 has a plurality of closing portions 10a, 10b, 10c,
It is divided into ... Then, each of the partitioned closing parts can be independently expanded by the expanding means. The developing means will be described below.

The developing means includes a cylinder 20a (20b, 20c, ...) Filled with an inert gas and the cylinder 2
0a (20b, 20c, ...) to the closing part 10a (1
0b, 10c, ...) Valves 30a (30b, 30) for adjusting the flow rate and pressure of the inert gas supplied to the inside of
c, ...) and a pipe 40a that serves as a flow path for the inert gas.
(40b, 40c, ...).

Cylinder 20a (20b, 20c, ...)
The pressure of the inert gas supplied from the inside of the closed portion 10a (10b, 10c, ...) To the closed portion 10a (10b, 10c, ...) Depends on the type of the thermoplastic resin forming the cured molding layer 11 and the weave of the thermoplastic woven fabric. Then, the optimum value is appropriately set by the test. For example, 10 kPa to 20 kPa can be set as a standard.

Valves 30a, 30b, 30 of the expanding means
The opening degrees of c, ... Are independently controlled by control means (not shown). That is, the flow rate, the pressure, the opening order, etc. of the inert gas are controlled by the opening degree control of the valves 30a, 30b, 30c, ...
Each will be adjusted to an appropriate value.

Next, the expanding operation of the inflatable structure 1 according to this embodiment will be described with reference to FIG.

First, the inflatable structure 1 is launched into outer space while being folded and stored in a predetermined storage section 50. In the present embodiment, FIG.
As shown in (a), it is configured to be folded at the joint of each closed portion. When a predetermined deployment time arrives in outer space, the control means controls the opening degree of the valve 30a of the deployment means for deploying the closure portion 10a to close the closure portion 10a.
To deploy. Then, by the control means, the closure 10
The opening of the valve 30b of the expanding means for expanding b is controlled to expand the closing portion 10b (see FIG. 4 (b)).

Similarly, the closing portion 10c, the closing portion 10d, ... Are successively expanded by the control means and the expanding means (see FIG. 4 (c)), and finally a predetermined shape (annular body or tubular body). ). After that, the curing molding layer 11 is heated and cured by a film-shaped heater, and a part of a predetermined structure (the large planar antenna 60 constructed in outer space).
Or the skeleton of the large sunshield 70).

In the inflatable structure 1 according to the present embodiment, the bag body 10 has a plurality of closing portions 10a, 10a.
b, 10c, ..., and these partitioned closing parts 10a, 10b, 10c, ... Can be independently deployed by a control means and a deployment means (cylinder, valve and piping). it can. Therefore, the bag body 10
It is possible to solve various problems at a time when the conventional expansion method in which the whole is expanded at once is adopted.

Specifically, when the bag 10 is unfolded, the bag 1
It is possible to prevent a part of 0 from coming into contact with the inner wall of the storage part 50 and being damaged. In addition, it is possible to prevent the bag 10 from being entirely or partially out of the storage part 50 and hindering the expansion. Further, the closed portion 10 of the bag body 10 is divided.
Since a, 10b, 10c, ... Can be independently expanded and hardened, even if space debris or meteorite collides with any of the expanded and hardened closed parts, the entire inflatable structure 1 fails. There is no fall.

[Second Embodiment] The inflatable structure 1A according to the present embodiment is the inflatable structure 1 according to the first embodiment with the configuration of the expanding means changed.

First, the construction of the expanding means for the inflatable structure 1A according to this embodiment will be described with reference to FIG. In the present embodiment, the bag closing portion 10A (1
0B), the developing means 20A (20B) is provided. Then, the expansion means 2 in the closing portion 10A (10B)
0A (20B) except for the expansion means 20A (20
The expansion unit 14A (14B) is expanded by B). Since the expanding means 20A and 20B have the same configuration, only the expanding means 20A will be described below.

The expanding means 20A comprises a gas filling capsule (gas filling portion) 21A filled with an inert gas supplied to the developing portion 14A, the gas filling capsule 21A and the developing portion 1
4A and thermoplastic resin seal portion 22 provided between
A and a heating wire (heating means) 23A for heating and melting the seal portion 22A.

Gas-filled capsule 21A which is a gas-filled portion
Is filled with an inert gas supplied to the developing unit 14A. The gas-filled capsule 21A is made in advance from a material having a strength capable of withstanding the pressure of the filled inert gas, for example, a thermoplastic resin, a thermosetting resin, lightweight and high-strength CFRP, or the like. Also, a gas-filled capsule 2
The shape of 1A is preferably a curved surface for the purpose of preventing damage to the inside of the closed portion 10A. In this embodiment, both ends are formed in a hemispherical shape (see FIG. 5).

The pressure (internal pressure) of the inert gas filled in the gas-filled capsule 21A is the pressure required for the deployment of the deployment section 14A and the gas-filled capsule 21 for the deployment section 14A.
It can be appropriately set in consideration of the volume ratio of A. In the present embodiment, the pressure required for the expansion of the expansion part 14A is 10 kPa, and the volume ratio of the gas-filled capsule 21A to the expansion part 14A is 1/10, so the pressure of the inert gas in the gas-filled capsule 21A is small. (Internal pressure) 10
It is set to 0 kPa. The inert gas filling operation into the gas filling capsule 21A can be easily performed in the atmosphere, and the internal pressure can be easily set.

A through hole 21Aa is provided in the hemispherical portion of the gas filling capsule 21A on the side of the developing portion 14A. The through hole 21Aa is a sealing portion 2 made of a thermoplastic resin described later.
Sealed at 2A. Further, the through hole 21Aa is partially or entirely opened by heating and melting the sealing portion 22A by a heating wire 23A described later. As a result, the inert gas filled in the gas-filled capsule 21A passes through the opened through-hole 21Aa and spreads through the developing portion 14.
It is supplied to the A side. That is, the opened through hole 21Aa
Serves as a gas supply port.

As described above, the sealing portion 22A made of the thermoplastic resin has the through hole 21Aa of the gas filling capsule 21A.
To prevent the inert gas filled in the gas-filled capsule 21A from leaking. The seal portion 22A is heated and melted by a heating wire 23A described later. Due to the melting of the sealing portion 22A, a part or the whole of the through hole 21Aa is opened, and the inert gas filled in the gas filling capsule 21A is supplied to the developing portion 14A side.

The kind of the thermoplastic resin used as the material of the seal portion 22A is not particularly limited as long as it has a strength capable of withstanding the pressure (internal pressure) of the inert gas filled in the gas filling capsule 21A. is not. For example, polyethylene, polyamide, PPS (polyphenylene sulfide), polypropylene, polyether imide, etc. can be mentioned.

The heating wire 23A serving as a heating means has a function of heating and melting the seal portion 22A, and is attached to a part of the seal portion 22A (see FIG. 5). The heating wire 23A may be any wire as long as it can be energized to generate heat, but a nichrome wire is preferable.
The heat generation timing and heat generation temperature of the heating wire 23A are controlled by a control means (not shown).

FIG. 6 is an enlarged view of the vicinity of the expanding means 20A. The bag according to the present embodiment has a cured molding layer 11A,
It is composed of an outer film layer 12A and an inner film layer 13A. Gas-filled capsule 2 of developing means 20A
As shown in FIG. 6, 1A is fixed to the inner side of the inner film layer 13A with an adhesive or the like. Then, the gas-filled capsule 21A partitions the closed portion 10A and the closed portion 10C adjacent to the closed portion 10A. The cured molding layer 11A and the outer film layer 1
Since 2A and the inner film layer 13A are substantially the same as those in the first embodiment, the description thereof will be omitted.

Next, the expansion means 20 in the present embodiment
A procedure for deploying the closing portion 10A (deployment portion 14A) by A will be described. First, a part or all of the through hole 21Aa is opened by heating and melting the seal portion 22A with the heating wire 23A which is a heating means. And
Through the through hole 21Aa, the inert gas filled in the gas filling capsule 21A, which is the gas filling portion, is introduced into the developing portion 14
Supply to A. As a result, the expanding unit 14A expands.

Therefore, as compared with the conventional gas supply mechanism including the cylinder and the valve, the weight of the expanding means is remarkably reduced.
Miniaturization is possible. Therefore, it is possible to reduce the weight and size of the inflatable structure itself. The inflatable structure 1A according to the present embodiment is lightweight and
Since it can be miniaturized, it is suitable for mounting on ultra-small space structures. For example, a weight of 10 kg as shown in FIG.
The deployment portion 82 of the solar cell panel 81 provided on the rectangular parallelepiped microsatellite 80 having sides of 50 cm can be configured with the inflatable structure 1A according to the present embodiment.

Further, in the above-mentioned embodiments, an example in which the curing molding layer constituting the bag of the inflatable structure 1 (1A) is composed of a thermoplastic resin composite material (thermoplastic woven fabric) is shown. However, it is also possible to form the curing molding layer with a composite material made of a thermosetting resin such as a thermosetting prepreg (an intermediate base material in which a predetermined reinforcing fiber is impregnated with an uncured thermosetting resin). it can.

In addition, in the inflatable structure adopting the conventional deployment method of deploying the entire bag at once,
In the case of constructing one columnar body as shown in FIG. 9, if space debris or meteorites collide with the bag body before the entire body completes the expansion, the entire inflatable structure will fail. On the other hand, since the inflatable structure 1 (1A) according to the above-described embodiment can be independently expanded and hardened for each closed part, space debris, meteorites, and the like are generated in any of the expanded and hardened closed parts. As described above, even if a collision occurs, the entire inflatable structure does not malfunction.

Further, four columnar inflatable structures 1 (1A) according to the above-mentioned embodiment are used and connected by a link 91, and a redundant structure 9 as shown in FIG.
You can also build 0. Such a redundant structure 90
If you build, one inflatable structure 1
Even if space debris or meteorites collide with (1A), the remaining three inflatable structures 1 (1A) can be supplemented, so that the reliability of the structure is significantly improved.

Further, the inflatable structure 1 (1A) according to the above-described embodiment is adopted for constructing a large or small structure in outer space, but the present invention is not limited to this, and in the event of a disaster on the ground. It can also be used to construct a simple house.

[0056]

According to the first aspect of the present invention, the inside of the bag is divided into a plurality of closed portions, and the divided closed portions are independently expanded by the expansion means by the control of the control means. Therefore, it is possible to realize a completely deployed state while preventing damage to the bag body during deployment. Further, since the bag body can be expanded and hardened for each of the partitioned closing parts, for example, even when space debris or meteorites collide with the expanded and hardened closing part, the entire inflatable structure fails. There is no.

According to the second aspect of the present invention, the expanding means is provided inside the closing portion, and the expanding means is provided with a through hole formed by heating and melting the seal portion by the heating means. Since the gas filled in the gas filling section is supplied to the developing section to be expanded, the expanding means can be significantly reduced in weight and size. Therefore, it is possible to reduce the weight and size of the inflatable structure itself.

[Brief description of drawings]

FIG. 1 is an explanatory diagram for explaining a usage mode of an inflatable structure according to a first embodiment of the present invention.

FIG. 2 is an enlarged sectional view of a II-II portion of FIG.

FIG. 3 is an explanatory diagram for explaining a deployment means of the inflatable structure according to the first embodiment of the present invention.

FIG. 4 is an explanatory diagram for explaining an expanding operation of the inflatable structure according to the first embodiment of the present invention.

FIG. 5 is an explanatory diagram for explaining a deployment means of the inflatable structure according to the second embodiment of the present invention.

FIG. 6 is an enlarged view of an inflatable structure deploying means and its vicinity according to a second embodiment of the present invention.

FIG. 7 is a conceptual diagram showing a state in which the inflatable structure according to the second embodiment of the present invention is applied to a micro structure.

FIG. 8 is a conceptual diagram showing a state in which a redundant structure is constructed using the inflatable structure according to the present invention.

FIG. 9 is an explanatory diagram for explaining a conventional inflatable structure deploying means.

FIG. 10 is an explanatory diagram for explaining a deployment operation of a conventional inflatable structure.

[Explanation of symbols]

1,1A inflatable structure 10 bags 10a to 10e closed part 10A-10C Closed part 11, 11A molding layer 12, 12A outer film layer 13, 13A inner film layer 20a-20c cylinder 20A, 20B deployment mechanism 21A gas filled capsule 21Aa through hole 22A seal part 23A heating wire 30a-30c valve 40a-40c piping 50 storage 60 planar antenna 70 Sun Shield 80 Micro satellite 81 solar panel 82 Development Department 90 redundant structure 91 links 100 bags 200 cylinders 300 valves 400 piping 500 storage 510 inner wall

Claims (2)

[Claims] 1. An inflatable structure comprising a foldable bag body having a cured molding layer made of a fiber reinforced resin provided between inner and outer film layers, and expanding means for inflating and expanding the bag body. The inside of the bag body is divided into a plurality of closed portions, and the bag body is provided with a deployment means for deploying each of the partitioned closure portions, and a control means for independently controlling the deployment means. And inflatable structure. 2. The closing section includes the expanding section inside thereof and has a expanding section which expands by the expanding section, wherein the expanding section is filled with gas supplied to the expanding section. Section, a seal portion made of a thermoplastic resin provided between the developing portion and the gas filling portion, and heating means for heating and melting the seal portion, and the seal by the heating means. The inflatable structure according to claim 1, wherein the gas filled in the gas filling portion is supplied to the developing portion to be developed through a through hole formed by heating and melting the portion.