CN114030647A - Inflatable expansion type semi-rigid lunar surface sealed cabin - Google Patents
Inflatable expansion type semi-rigid lunar surface sealed cabin Download PDFInfo
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- CN114030647A CN114030647A CN202111422257.2A CN202111422257A CN114030647A CN 114030647 A CN114030647 A CN 114030647A CN 202111422257 A CN202111422257 A CN 202111422257A CN 114030647 A CN114030647 A CN 114030647A
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- 238000007789 sealing Methods 0.000 claims abstract description 18
- 230000001681 protective effect Effects 0.000 claims description 31
- 239000002131 composite material Substances 0.000 claims description 5
- 239000006261 foam material Substances 0.000 claims description 4
- 238000005485 electric heating Methods 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 3
- 229920001187 thermosetting polymer Polymers 0.000 claims description 3
- 239000000835 fiber Substances 0.000 claims description 2
- 229920005989 resin Polymers 0.000 claims description 2
- 239000011347 resin Substances 0.000 claims description 2
- 239000002775 capsule Substances 0.000 claims 9
- 229910052751 metal Inorganic materials 0.000 abstract description 6
- 239000002184 metal Substances 0.000 abstract description 6
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 abstract description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 5
- 239000002689 soil Substances 0.000 description 5
- 239000012634 fragment Substances 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 241000282414 Homo sapiens Species 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000002457 bidirectional effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000037213 diet Effects 0.000 description 1
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- 230000007613 environmental effect Effects 0.000 description 1
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- 239000006260 foam Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
- B64G1/2221—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state characterised by the manner of deployment
- B64G1/2227—Inflating
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Tents Or Canopies (AREA)
Abstract
An inflatable unfolding type semi-rigid lunar surface sealed cabin belongs to the technical field of spacecrafts. Aiming at the use requirements of the lunar surface sealed cabin in the aerospace moon exploration, the inflatable semi-rigid lunar surface sealed cabin is provided, particularly considering the problems that the existing metal sealed cabin has large emission mass and large emission volume, the inflatable sealed cabin has low structural rigidity, insufficient stability, insufficient protection performance of space micro-planets and the like. The outer portion of the flexible sealing inner bag is provided with a rigid protection structure, the rigid protection structure can be folded and inflated to expand, the flexible sealing inner bag is internally provided with a rigidifying inflatable expansion supporting truss, one side of the rigid protection structure is provided with a vertical cabin door, the edge of the inner wall of the vertical cabin door is connected with the flexible sealing inner bag in a rigid and flexible mode, and the flexible sealing inner bag is connected with an inflation system. The inflation-unfolding semi-rigid lunar surface sealed cabin can be folded and launched, is formed by inflation and unfolding on the lunar surface, and has a large internal volume. Has the advantages of large folding-unfolding ratio, low manufacturing and launching cost and the like.
Description
Technical Field
The invention belongs to the technical field of spacecrafts, and particularly relates to an inflatable expansion type semi-rigid lunar surface sealed cabin.
Background
The lunar surface sealed cabin is an indispensable activity base for human beings to carry out lunar exploration. The main structural forms of the existing designed sealed cabin are a rigid metal cabin and a flexible deployable cabin. The rigid metal cabin is usually large in structural mass and size, high in launching cost, large in on-orbit assembly difficulty and limited by rocket launching capacity, and the rigid metal cabin can only provide limited activity space for astronauts in an on-orbit mode, so that the use requirement of space exploration cannot be met by a simple rigid metal cabin. In recent years, a flexible deployable cabin is developed, an inflatable airbag is mainly adopted as a main body structure of a cabin body, the flexible deployable cabin is formed by on-rail inflation and deployment, and the flexible deployable cabin has the advantages of light weight, high folding efficiency, low launching cost and the like. However, considering the extreme environmental conditions of atomic oxygen, high and low temperature, ultraviolet radiation, space debris and the like in the space, the adoption of a simple airbag structure is often difficult to meet the requirement of space environment protection. At present, modes such as lunar soil coverage, lunar soil 3D concrete printing and the like are provided for protection of the inflatable cabin body, but the lunar soil performance and the earth soil have large difference, the space operation difficulty is large, and the stability and the reliability of the lunar soil are insufficient.
Disclosure of Invention
Aiming at the use requirements of the lunar surface sealed cabin in the aerospace moon exploration, the inflatable semi-rigid lunar surface sealed cabin is provided, particularly considering the problems that the existing metal sealed cabin has large emission mass and large emission volume, the inflatable sealed cabin has low structural rigidity, insufficient stability, insufficient protection performance of space micro-planets and the like.
The technical scheme adopted by the invention is as follows: an inflatable expansion type semi-rigid lunar surface sealed cabin comprises a rigid protection structure, a flexible sealed inner bag, a vertical cabin door, a rigidifying inflatable expansion support truss and an inflation system; the outer portion of the flexible sealing inner bag is provided with a rigid protection structure, the rigid protection structure can be folded and inflated to expand, an inflation expansion supporting truss is arranged inside the flexible sealing inner bag, one side of the rigid protection structure is provided with a vertical cabin door, the edge of the inner wall of the vertical cabin door is in rigid-flexible connection with the flexible sealing inner bag, and the flexible sealing inner bag is connected with an inflation system.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention can be folded and launched, and is formed by inflating and unfolding on the moon surface, and the internal volume is large. Has the advantages of large folding-unfolding ratio, low manufacturing and launching cost and the like.
2. The multilayer sandwich protective plate adopts multilayer rigid plates (such as aluminum plates) as the space debris protective materials, and has high integral structure rigidity and excellent space debris protective performance.
3. The multilayer sandwich protective plate adopts foam as sandwich materials among rigid plates (such as aluminum plates) of each layer, can form a multilayer large-space fragment protective structure when a sealed cabin is unfolded, can crush and intercept space fragments for many times, and reduces the impact damage of the space fragments to the cabin body, thereby obviously improving the space fragment protective performance and the on-orbit service life of the flexible sealed cabin, and simultaneously adopts foam material for filling to improve the heat insulation performance of the sealed cabin.
4. The rigid protection structure is formed by connecting the multiple layers of sandwich protection plates through the rigidizable flexible connecting belt and can be folded at the rigidizable flexible connecting belt, so that the whole sealed cabin is compactly folded, and the emission volume is remarkably reduced.
5. The rigidifiable flexible connecting belt can be rigidized by electric heating after the rigid protection structure is unfolded and formed, so that the whole cabin body is externally formed into an integral rigid protection shell structure, the integral structural rigidity and external load resistance are improved, and the cabin body still has enough structural rigidity and bearing capacity after air leakage is ensured.
6. The whole sealed cabin is of a cuboid structure, the vertical and flat surface of the sealed cabin is convenient for designing a vertical cabin door for a astronaut to conveniently come in and go out, and meanwhile, the sealed cabin is beneficial to the arrangement of other rigid connecting pieces.
7. The edge of the joint of the protection plates on different planes of the rigid protection structure is provided with the meshed structure, so that bidirectional constraint force can be provided for the mutually contacted multilayer sandwich protection plates, and the internal pressure bearing capacity and the structural stability of the structure are effectively improved.
8. The flexible sealing inner bag can provide a closed space for the cabin body, can provide unfolding driving force for the rigid protection structure in the inflating and unfolding process, and is simple and reliable in unfolding mode. The inflation and unfolding process can be controlled by controlling the inflation quantity, the inflation speed and the like, and the unfolding control mode is simple and reliable.
9. The rigidizable inflation supporting tube is arranged in the flexible sealing inner bag, the rigidizable inflation unfolding supporting truss is formed by utilizing the diagonal supporting inflation tube tie bar, and the inflatable unfolding supporting truss can be electrically heated and rigidized after inflation unfolding, so that the rigid support is formed for the whole flexible sealing inner bag and the rigid protection structure, and the stability and the bearing capacity of the structure are further improved.
10. The electric wire and cable in the cabin and the gas-liquid pipeline are arranged in the rigidizable inflatable unfolding support truss, so that the electric wire and cable and the gas-liquid pipeline can be regularly arranged, the space is effectively utilized, and the protection is provided for a pipeline system.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a perspective view of the overall construction of the present invention;
FIG. 3 is an elevational view of the overall construction of the present invention;
FIG. 4 is a folded front view of a rigidizable inflatable expansion support truss of the present invention with a sealed flexible inner bladder;
FIG. 5 is a front and back folded front view of the multi-layer sandwich panel of the present invention;
FIG. 6 is a side view of a folded side multi-layer sandwich panel according to the present invention;
FIG. 7 is a folded front view of the side multi-layer sandwich panel of the present invention;
FIG. 8 is a folded front view of the bottom multi-layer sandwich panel of the present invention;
FIG. 9 is a top view of the snap-fit structure of the present invention;
FIG. 10 is a schematic view of an inflatable deployment support truss of the present invention;
FIG. 11 is a schematic structural view of a multi-layer sandwich panel material according to the present invention;
wherein: 1. a rigid protective structure; 2. a flexible sealed inner bladder; 3. a vertical hatch door; 4. the inflatable unfolding support truss can be rigidized; 5. a viewing port; 11. a multi-layer sandwich protective plate; 12. a rigidizable flexible connecting strip; 13. an occlusion structure; 111. a rigid plate; 112. a foam material.
Detailed Description
The lunar surface sealed cabin is folded and compressed before being launched, and can be inflated and unfolded at the lunar surface to form a large-size sealed cabin.
The invention can provide activity places such as work, daily life, diet, exercise, entertainment and the like for astronauts in the exploration of the moon, and can be further applied to a world round trip system, a space station, a foreign base, space travel and the like.
The first embodiment is as follows: the embodiment is described with reference to fig. 1 to 11, and provides an inflatable unfolding type semi-rigid lunar surface sealed cabin, which comprises a rigid protective structure 1, a flexible sealed inner bag 2, a vertical cabin door 3, a rigidizable inflatable unfolding support truss 4 and an inflation system; the outside rigid protection structure 1 that has barrier propterty that sets up of flexible seal inner bag 2, rigid protection structure 1 can fold and aerify and expand, and flexible seal inner bag 2 is inside to be provided with the rigidization and to aerify and expand braced truss 4, vertical hatch door 3 is installed to one side of rigid protection structure 1, and 3 inner wall edges of vertical hatch door are connected with flexible seal inner bag 2 rigid-flexible, flexible seal inner bag 2 is connected with inflation system.
In this embodiment, the flexible sealed inner bag 2 and the inflatable unfolding support truss 4 are unfolded by the inflation system and drive the rigid protective structure 1 to unfold.
The second embodiment is as follows: the present embodiment will be described with reference to fig. 1 to 8, and the present embodiment is further limited to a first embodiment, in which the rigid fender structure 1 is formed by connecting a plurality of multi-layer sandwich fender panels 11 by a rigidizable flexible connecting band 12, the rigid fender structure 1 is a rectangular parallelepiped structure after being unfolded, and the multi-layer sandwich fender panels 11 are folded at the rigidizable flexible connecting band 12 when being folded. Other components and connection modes are the same as those of the first embodiment.
The third concrete implementation mode: the present embodiment will be described with reference to fig. 1 to 8, and the present embodiment is further limited to the second embodiment, in the present embodiment, the lower ends of the multi-layered sandwich protective panels 11 positioned at the front and rear sides in the rigid protective structure 1 are connected to the multi-layered sandwich protective panels 11 positioned at the bottom side by the rigidifiable flexible connecting strips 12, the multi-layered sandwich protective panels 11 positioned at the left and right sides in the rigid protective structure 1 are each formed by four panels connected by the rigidifiable flexible connecting strips 12 in the length and width directions, the multi-layered sandwich protective panels 11 positioned at the top and bottom sides in the rigid protective structure 1 are each formed by two panels connected by the rigidifiable flexible connecting strips 12 in the width direction, the multi-layered sandwich protective panels 11 positioned at the front and rear sides are folded by pressing the multi-layered sandwich protective panels 11 positioned at the bottom side, the multi-layered sandwich protective panels 11 positioned at the left and right sides are folded in a zigzag manner, the folding volume is small, and the integral structure is further packed and launched after being folded. The other components and the connection mode are the same as those of the second embodiment.
In this embodiment, as shown in fig. 1 and 2, the rigidifiable flexible connecting tape 12 located in the width direction on the top surface, the bottom surface and both side surfaces is on the same plane.
As shown in fig. 5, the multi-layered sandwich protective plates 11 positioned at the front and rear sides are first folded inward by pressing, and then, as shown in fig. 6, the multi-layered sandwich protective plates 11 positioned at the left and right side surfaces are folded inward, and the multi-layered sandwich protective plates 11 positioned at the top surface are naturally folded downward, and then, as shown in fig. 8, both ends of the multi-layered sandwich protective plates 11 positioned at the bottom surface are folded in half.
In the fourth embodiment, the present embodiment is described with reference to fig. 9, and the second or third embodiment is further limited, in the present embodiment, a snap structure 13 is provided at the edge of the joint between the multiple sandwich protective panels 11 on the rigid protective structure 1 to restrain the unfolded position of each protective panel, so that the overall configuration can be restrained after the rigid protective structure 1 is unfolded and molded.
The fifth concrete implementation mode: in this embodiment, the multi-layered sandwich fender panel 11 is formed by alternately layering a plurality of rigid panels 111 and foam materials 112, and the rigidizable flexible connecting band 12 is made of a flexible composite material. The other components and the connection mode are the same as those of the fourth embodiment.
The sixth specific implementation mode: the present embodiment is described with reference to fig. 3 to 4, and is further limited to the first embodiment, in which the flexible sealing inner bag 2 is folded in a zigzag manner at the lower end of the vertical hatch 3 and the bottom surface of the rigid protection structure 1, and is pressed by the vertical hatch 3 and the rigid protection structure 1. The other components and the connection mode are the same as the fifth embodiment mode.
The seventh embodiment: the present embodiment is described with reference to fig. 1 to 3, and is further limited to a sixth specific embodiment, in the present embodiment, the rigidizable inflatable expanding support truss 4 is formed by a plurality of rigidizable inflatable support tubes which are communicated and built, the rigidizable inflatable expanding support truss 4 and the flexible sealed inner bag 2 are inflated and expanded and molded synchronously during the expanding process, and when the bite-type structure 13 is in contact action, the inflatable support tubes are further rigidized to form the rigidizable inflatable expanding support truss 4 inside the flexible sealed inner bag 2. Other components and connection modes are the same as those of the sixth embodiment.
The specific implementation mode is eight: the seventh embodiment is further limited, in this embodiment, both the flexible sealing inner bag 2 and the rigidifiable inflatable supporting tube may be made of fiber composite thermosetting resin pre-impregnated fabric (for example, carbon fiber composite thermosetting epoxy resin pre-impregnated fabric), the flexible sealing inner bag 2 is inflated and expanded to be formed under the action of the inflation system, the outer layer rigid protection structure 1 is pushed to be expanded to be formed, and the flexible sealing inner bag 2 and the rigidifiable inflatable supporting tube are further rigidified by electrical heating after being inflated and expanded. The other components and the connection mode are the same as those of the seventh embodiment.
In the present embodiment, in order to realize inflation and electric heating, a wire cable, a gas-liquid pipeline, and the like are provided inside the rigidizable inflation support tube.
The specific implementation method nine: the present embodiment will be described with reference to fig. 1 to 2, and is further limited to a specific embodiment in which an attachment such as a viewing port 5 is provided to the pod door 3. Other components and connection modes are the same as those of the first embodiment.
The detailed implementation mode is ten: in this embodiment, the first specific embodiment is further limited, and in this embodiment, the gas charging system adopts a gas cylinder charging method. Other components and connection modes are the same as those of the first embodiment.
It is to be understood that the present invention has been described with reference to certain embodiments, and that various changes in the features and embodiments, or equivalent substitutions may be made therein by those skilled in the art without departing from the spirit and scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.
Claims (10)
1. An inflatable expansion type semi-rigid lunar surface sealed cabin is characterized in that: comprises a rigid protection structure (1), a flexible sealing inner bag (2), a vertical cabin door (3), a rigidifying inflatable unfolding support truss (4) and an inflation system; the flexible seal inner bag (2) outside sets up rigid protection structure (1), and rigid protection structure (1) can fold and aerify and expand, and flexible seal inner bag (2) inside is provided with can rigidify and aerify and expand braced truss (4), vertical hatch door (3) are installed to one side of rigid protection structure (1), and vertical hatch door (3) inner wall edge is connected with flexible seal inner bag (2) rigid-flexible, flexible seal inner bag (2) are connected with inflation system.
2. The inflatable deployment semi-rigid lunar sealed capsule according to claim 1, wherein: the rigid protection structure (1) is formed by connecting a plurality of multilayer sandwich protection plates (11) through rigidizable flexible connecting strips (12), the rigid protection structure (1) is of a cuboid structure after being unfolded, and the multilayer sandwich protection plates (11) are folded at the rigidizable flexible connecting strips (12) during folding.
3. An inflatable deployment semi-rigid lunar sealed capsule according to claim 2, characterized in that: the lower ends of the multilayer sandwich protection plates (11) positioned at the front and the rear in the rigid protection structure (1) are connected with the multilayer sandwich protection plates (11) positioned at the bottom through rigidizable flexible connecting belts (12), the multilayer sandwich protection plates (11) positioned at the left and the right sides in the rigid protection structure (1) are formed by connecting four panels through rigidizable flexible connecting belts (12) in the length direction and the width direction, the multilayer sandwich protection plates (11) positioned at the top and the bottom in the rigid protection structure (1) are formed by connecting two panels through rigidizable flexible connecting belts (12) in the width direction, the multilayer sandwich protection plates (11) positioned at the front and the rear press the bottom to be folded, and the multilayer sandwich protection plates (11) positioned at the left and the right sides are folded in a Z shape.
4. An inflatable deployment semi-rigid lunar sealed capsule according to claim 2 or 3, characterized in that: and the edges of the joints among the multiple multilayer sandwich protective plates (11) on the rigid protective structure (1) are provided with occlusion type structures (13).
5. An inflatable deployment semi-rigid lunar sealed capsule according to claim 4, wherein: the multilayer sandwich protective plate (11) is formed by alternately laying a plurality of layers of rigid plates (111) and foam materials (112), and the rigidizable flexible connecting belt (12) is made of flexible composite materials.
6. An inflatable deployment semi-rigid lunar sealed capsule according to claim 1, characterized in that: the flexible sealing inner bag (2) is folded in a Z shape at the lower end of the vertical cabin door (3) and the bottom surface of the rigid protection structure (1) and is tightly pressed by the vertical cabin door (3) and the rigid protection structure (1).
7. An inflatable deployment semi-rigid lunar sealed capsule according to claim 6, wherein: the rigidifying inflatable unfolding support truss (4) is formed by communicating and building a plurality of rigidifying inflatable support pipes.
8. An inflatable deployment semi-rigid lunar sealed capsule according to claim 7, wherein: the flexible sealing inner bag (2) and the rigidifiable inflatable supporting tube are both made of fiber composite thermosetting resin prepreg fabric, and are rigidified by adopting an electric heating mode after being inflated and unfolded.
9. An inflatable deployment semi-rigid lunar sealed capsule according to claim 1, characterized in that: the vertical cabin door (3) is provided with an observation port (5).
10. An inflatable deployment semi-rigid lunar sealed capsule according to claim 1, characterized in that: the inflation system adopts a gas cylinder inflation mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111422257.2A CN114030647A (en) | 2021-11-26 | 2021-11-26 | Inflatable expansion type semi-rigid lunar surface sealed cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111422257.2A CN114030647A (en) | 2021-11-26 | 2021-11-26 | Inflatable expansion type semi-rigid lunar surface sealed cabin |
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| CN114030647A true CN114030647A (en) | 2022-02-11 |
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| CN202111422257.2A Pending CN114030647A (en) | 2021-11-26 | 2021-11-26 | Inflatable expansion type semi-rigid lunar surface sealed cabin |
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2021
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