CN113562197A - Large-scale air of space constructs thoughtlessly moves flexible cabin - Google Patents
Large-scale air of space constructs thoughtlessly moves flexible cabin Download PDFInfo
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- CN113562197A CN113562197A CN202110762424.1A CN202110762424A CN113562197A CN 113562197 A CN113562197 A CN 113562197A CN 202110762424 A CN202110762424 A CN 202110762424A CN 113562197 A CN113562197 A CN 113562197A
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- 239000002131 composite material Substances 0.000 claims description 5
- 230000007423 decrease Effects 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims description 4
- 229920000271 Kevlar® Polymers 0.000 claims description 3
- 229920000784 Nomex Polymers 0.000 claims description 3
- 229920005830 Polyurethane Foam Polymers 0.000 claims description 3
- 239000000835 fiber Substances 0.000 claims description 3
- 239000004761 kevlar Substances 0.000 claims description 3
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- 238000003825 pressing Methods 0.000 description 4
- 239000004433 Thermoplastic polyurethane Substances 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 229920002803 thermoplastic polyurethane Polymers 0.000 description 3
- 150000001875 compounds Chemical class 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 239000011241 protective layer Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- RNFJDJUURJAICM-UHFFFAOYSA-N 2,2,4,4,6,6-hexaphenoxy-1,3,5-triaza-2$l^{5},4$l^{5},6$l^{5}-triphosphacyclohexa-1,3,5-triene Chemical compound N=1P(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP=1(OC=1C=CC=CC=1)OC1=CC=CC=C1 RNFJDJUURJAICM-UHFFFAOYSA-N 0.000 description 1
- 229910001008 7075 aluminium alloy Inorganic materials 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
-
- 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
-
- 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
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/54—Protection against radiation
-
- 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
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
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- Emergency Medicine (AREA)
- Toxicology (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Tents Or Canopies (AREA)
Abstract
The invention discloses a large-space pneumatic hybrid flexible cabin, and particularly relates to the technical field of manned deep space detection equipment. A large-space air structure hybrid flexible cabin comprises a bottom plate, a top plate and a skin layer coated between a base and the top plate, wherein a plurality of fixed beams are distributed in the bottom plate at equal intervals in the circumferential direction, a cabin wall arranged on the bottom plate is connected between every two adjacent fixed beams, all the fixed beams and the cabin wall are enclosed to form an inner cavity, an air bottle and an inflation pipeline communicated with the air bottle are arranged in the inner cavity, and an inflation valve is arranged on the inflation pipeline; a folding and unfolding mechanism is arranged between the bottom plate and the top plate and used for folding or unfolding the space between the bottom plate and the top plate, and a cabin door and a deflation valve positioned on one side of the cabin door are arranged on the top plate. By adopting the technical scheme of the invention, the problem that the launching and carrying capacity and the launching task of the existing rocket cannot be simultaneously considered is solved, and the manned deep space exploration can be met.
Description
Technical Field
The invention relates to the technical field of manned deep space exploration equipment, in particular to a spatial large-scale pneumatic hybrid flexible cabin.
Background
The manned deep space exploration is an effective way for expanding the human activity field and developing and utilizing resources, and the large-scale space flexible cabin body is used as typical equipment for the manned deep space exploration, can be used for building a space station, and can lay a foundation for the construction of a subsequent lunar base. The contradiction between the launching and carrying capacity of the rocket and the launching task is more and more prominent, so that a space capsule capable of solving the contradiction is urgently needed.
Disclosure of Invention
The invention aims to provide a large-space air structure hybrid flexible cabin, which solves the problem that the launching and carrying capacity and the launching task of the existing rocket cannot be simultaneously considered.
In order to achieve the purpose, the technical scheme of the invention is as follows: a large-space air structure hybrid flexible cabin comprises a bottom plate, a top plate and a skin layer coated between a base and the top plate, wherein a plurality of fixed beams are distributed in the bottom plate at equal intervals in the circumferential direction, a cabin wall arranged on the bottom plate is connected between every two adjacent fixed beams, all the fixed beams and the cabin wall are enclosed to form an inner cavity, an air bottle and an inflation pipeline communicated with the air bottle are arranged in the inner cavity, and an inflation valve is arranged on the inflation pipeline; a folding and unfolding mechanism is arranged between the bottom plate and the top plate and used for folding or unfolding the space between the bottom plate and the top plate, and a cabin door and a deflation valve positioned on one side of the cabin door are arranged on the top plate.
Furthermore, the folding and unfolding mechanism comprises a U-shaped rod and composite hinge mechanisms arranged on the inner side and the outer side of the U-shaped rod, each composite hinge mechanism comprises two hinge bases, one side of each hinge base is rotatably connected with two connecting arms, a central rotating shaft is arranged at the same position of the four connecting arms in a penetrating mode, the two hinge bases are symmetrically arranged on two sides of the central rotating shaft, each hinge base is rotatably connected with the corresponding connecting arm, a base rotating shaft is arranged in each hinge base in a penetrating mode, and a coil spring is arranged between each base rotating shaft and the hinge base; and a lock tongue is further arranged on any one of the hinge bases, and a locking hole matched with the lock tongue is formed in the other hinge base.
Furthermore, the top plate is provided with sliding grooves which are the same as the folding and unfolding mechanisms in number and correspond to the folding and unfolding mechanisms, each sliding groove is internally connected with a sliding block in a sliding mode, and the sliding blocks are rotatably connected with the corresponding folding and unfolding mechanisms.
Further, the skin layer from interior to exterior comprises abrasionproof decreases layer, air-tight layer, load layer, piece inoxidizing coating, insulating layer and atomic oxidation inoxidizing coating in proper order, the abrasionproof decreases the layer and adopts the Nomex fabric to make, the air-tight layer adopts the TPU film to make, the load layer adopts the Kevlar fibre to weave and forms, the piece inoxidizing coating is by multilayer ceramic fabric and set up polyurethane foam between two adjacent ceramic fabrics, the insulating layer adopts the Pyrogel material to make, atomic oxidation inoxidizing coating adopts the MLI film material to make.
Through the arrangement, the situation that objects in the cabin pierce the skin layer can be prevented by the anti-abrasion layer, and a better flame retardant effect can be achieved; the airtight layer can prevent the gas leakage in the cabin, and the stability of the scheme is maintained; the bearing layer can bear the air pressure load in the cabin; the fragment protective layer can prevent or reduce the damage of the micrometeor and the space fragments to the skin layer; the heat insulation layer can effectively resist ultraviolet radiation and has good heat insulation effect; the atomic oxidation protective layer has oxidation resistance and corrosion resistance.
Compared with the prior art, the beneficial effect of this scheme:
1. the scheme has small volume, light weight and high folding and unfolding efficiency, can meet the limit of carrying capacity and reduce the carrying cost; 2. the scheme is inflated and expanded, the engineering construction is simple, and the life and work of deep space exploration astronauts can be met.
Drawings
FIG. 1 is a cross-sectional view of a space large air structure hybrid flexible cabin in an unfolded state;
FIG. 2 is a cross-sectional view A-A of FIG. 1;
FIG. 3 is an enlarged partial view at B of FIG. 1;
FIG. 4 is a schematic view of the construction of the compound hinge mechanism of the present invention;
FIG. 5 is a schematic structural diagram of a space large-scale air structure hybrid flexible cabin in an unfolded state;
fig. 6 is a cross-sectional view of C-C in fig. 5.
Detailed Description
The present invention will be described in further detail below by way of specific embodiments:
reference numerals in the drawings of the specification include: the air inflation device comprises a bottom plate 1, a top plate 2, a fixed beam 3, a bulkhead 4, an air bottle 5, an inflation pipeline 6, an inflation valve 7, a U-shaped rod 8, a hinge base 9, a rotating shaft 10, a connecting arm 11, a central rotating shaft 12, a base rotating shaft 13, a coil spring 14, a lock tongue 15, a cabin door 16, an air release valve 17, a skin layer 18, a sliding groove 19 and a pressing strip 20.
Examples
As shown in figures 1, 2 and 5: the utility model provides a large-scale air of space constructs thoughtlessly moves flexible cabin, includes bottom plate 1, roof 2 and the cladding at the skin layer 18 between base and roof 2, and the circumferential equidistance distributes in bottom plate 1 has many fixed beams 3, adopts eight fixed beams 3 in this embodiment, and the equal fixedly connected with supporting seat of lower extreme of every fixed beam 3, supporting seat bolted connection are on bottom plate 1. The gomphosis has between per two adjacent fixed beams 3 to set up bulkhead 4, and the equal interval symmetric distribution of the lower extreme of every bulkhead 4 has a connecting plate, wears to be equipped with the fastening bolt with bulkhead 4 threaded connection jointly on the connecting plate of per two correspondences, and the common welding of connecting plate bottom of per two correspondences has the fixed plate, and fixed plate bolted connection is on bottom plate 1. All fixed beams 3 and bulkhead 4 enclose to close and form the inner chamber, and the internal peripheral equidistance of inner chamber distributes and has four pairs of gas cylinder 5 groups, and every pair of gas cylinder 5 group all contains two adjacent gas cylinders 5 and block at the block board of two gas cylinder 5 upside, and it has the support still to weld on the lateral wall of every gas cylinder 5, and the other end welding of support is on bulkhead 4, all communicates gas charging line 6 on the air cock of every gas cylinder 5, is equipped with inflation valve 7 on the gas charging line 6. The bottom plate 1 is provided with a groove positioned outside the bulkhead 4, two pressing strips 20 used for clamping the top of the skin layer 18 are clamped in the groove, and the end parts of the two pressing strips 20 are in Z-shaped contact.
As shown in fig. 3 and 4, a plurality of folding and unfolding mechanisms are arranged between the bottom plate 1 and the top plate 2, the folding and unfolding mechanisms are used for folding or unfolding the space between the bottom plate 1 and the top plate 2, each folding and unfolding mechanism comprises a U-shaped rod 8 and a composite hinge mechanism arranged on the inner side and the outer side of the U-shaped rod 8, the U-shaped rods 8 are made of 7075 aluminum alloy material commonly used in aerospace, a hinge base 9 in the folding and unfolding mechanism close to the bottom plate 1 is arranged on the fixed beam 3, and a hinge base 9 in the folding and unfolding mechanism close to the top plate 2 is arranged on a corresponding sliding block. Every compound the hinge mechanism all includes two hinge base 9, and one side of every hinge base 9 all rotates and is connected with axis of rotation 10, and it has the gliding recess of confession axis of rotation to open on the both sides wall of every hinge base 9, and two linking arms 11 are worn to be equipped with at the interval on axis of rotation 10, and central pivot 12 is worn to be equipped with jointly in the same department of four linking arms 11, and four linking arms 11 cross distribution on two axis of rotation 10 are on central pivot 12, and two hinge base 9 symmetries set up the both sides at central pivot 12. A base rotating shaft 13 penetrates through each hinge base 9, and a coil spring 14 is connected between each base rotating shaft 13 and each hinge base 9; a bolt 15 is further arranged on any hinge base 9, and a locking hole matched with the bolt 15 is formed in the corresponding position of the other hinge base 9.
As shown in fig. 6, the ceiling plate 2 is provided with a hatch 16 and a purge valve 17 located on one side of the hatch 16. The bottom of propping of roof 2 circumference equidistance distributes and has the spout 19 that is located the hatch door 16 outside, and the quantity of spout 19 is the same with folding deployment mechanism's quantity, and just every spout 19 all is located the folding deployment mechanism that corresponds directly over, all sliding connection has the slider in every spout 19, and the slider rotates with hinge base 9 in the folding deployment mechanism to be connected. The top of the top plate 2 is also provided with a groove which is positioned outside the sliding groove 19 and is the same as that on the bottom plate 1, and a pressing strip 20 for clamping the top of the skin layer 18 is also clamped in the groove.
The mask layer 18 is composed of an anti-abrasion layer, an airtight layer, a force bearing layer, a fragment protection layer, a heat insulation layer and an atomic oxidation protection layer from inside to outside in sequence, wherein the anti-abrasion layer is made of Nomex fabric, the airtight layer is made of TPU (thermoplastic polyurethane) film, the force bearing layer is woven of Kevlar fiber, the fragment protection layer is made of multilayer ceramic fabric and polyurethane foam arranged between two adjacent ceramic fabrics, the heat insulation layer is made of Pyrogen material, and the atomic oxidation protection layer is made of MLI film material.
The working process of this scheme, when this flexible cabin is in initial condition, folding deployment mechanism is in fold condition, and two hinge bases 9 of every folding deployment mechanism are in parallel state this moment, and the torsional spring on two above-mentioned hinge bases 9 all does not have torsional force and produces, and every folding deployment mechanism all is located the inner chamber this moment, and the shared volume of whole flexible cabin is less simultaneously, is convenient for carry on the rocket of various differences.
After the rocket conveys the flexible cabin to a preset track, the inflation valve 7 is opened to inflate the flexible cabin by utilizing the space enclosed by the bottom plate 1, the top plate 2 and the skin layer 18 of the gas cylinder 5, and meanwhile, the folding and unfolding mechanism is driven to unfold by utilizing gas. The self-hardening of the skin layer 18 after the flexible cabin is inflated can meet the requirement of the flexible cabin on the rigidity performance, a pressure sensor is also arranged in the flexible cabin and is electrically connected with the inflation valve 7 and the deflation valve 17 respectively, so that the inflation valve 7 can be opened or closed by means of the gas pressure value measured by the pressure sensor, namely, the inflation valve 7 is closed when the real-time pressure value in the flexible cabin is equal to the target pressure value required by the living environment of astronauts; when the real-time pressure value in the flexible cabin is larger than the target pressure value required by the living environment of the astronaut, closing the inflation valve 7 and opening the deflation valve 17; when the real-time pressure value in the flexible cabin is smaller than the target pressure value required by the living environment of the astronaut, the inflation valve 7 is continuously in an opening state, and when the real-time pressure in the flexible cabin is equal to the target pressure value, the valve is closed and the pressure in the flexible cabin is measured in real time, so that the target pressure value is kept in the cabin, and the inflation performance of the cabin is met.
In the process of inflating the flexible cabin, the skin layer 18 expands outwards under the action of gas, and meanwhile, the top plate 2 starts to move upwards, so that the U-shaped rod 8 is driven to rotate by virtue of the sliding block, the two hinge bases 9 at the other end of the U-shaped rod 8 can be driven to rotate by virtue of the rotation of the U-shaped rod 8, when the two hinge bases 9 rotate to the same straight line, the inclined plane of the end part of the bolt 15 and the rotating shaft 10 are locked at opposite positions, so that the two hinge bases 9 are connected and locked, and then the other folding unfolding mechanism is driven to be opened by virtue of the hinge bases 9 and the U-shaped rod 8 after the two hinge bases 9 are locked, the unfolding process is the same as that of the folding unfolding mechanism, and finally, after all the folding unfolding mechanisms are unfolded, the space between the bottom plate 1 and the top plate 2 can be supported and expanded, and the operation can be convenient for multiple persons.
The foregoing are merely examples of the present invention and common general knowledge of known specific structures and/or features of the schemes has not been described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (4)
1. The utility model provides a large-scale air of space constructs flexible cabin that thoughtlessly moves which characterized in that: the gas cylinder type gas-filling machine comprises a bottom plate, a top plate and a skin layer coated between a base and the top plate, wherein a plurality of fixed beams are distributed in the bottom plate at equal intervals in the circumferential direction, a bulkhead arranged on the bottom plate is connected between every two adjacent fixed beams, all the fixed beams and the bulkhead are enclosed to form an inner cavity, a gas cylinder and a gas charging pipeline communicated with the gas cylinder are arranged in the inner cavity, and a gas charging valve is arranged on the gas charging pipeline; a folding and unfolding mechanism is arranged between the bottom plate and the top plate and used for folding or unfolding the space between the bottom plate and the top plate, and a cabin door and a deflation valve positioned on one side of the cabin door are arranged on the top plate.
2. The large-scale air structure mixing flexible cabin in space of claim 1, characterized in that: the folding and unfolding mechanism comprises a U-shaped rod and composite hinge mechanisms arranged on the inner side and the outer side of the U-shaped rod, each composite hinge mechanism comprises two hinge bases, one side of each hinge base is rotatably connected with two connecting arms, a central rotating shaft is arranged at the same position of the four connecting arms in a penetrating mode, the two hinge bases are symmetrically arranged on two sides of the central rotating shaft, each hinge base is rotatably connected with the corresponding connecting arm, a base rotating shaft is arranged in each hinge base in a penetrating mode, and a coil spring is arranged between each base rotating shaft and the hinge base; and a lock tongue is further arranged on any one of the hinge bases, and a locking hole matched with the lock tongue is formed in the other hinge base.
3. A large-scale air-mix flexible space tank according to claim 1 or 2, wherein: the top plate is provided with sliding grooves which are the same as the folding and unfolding mechanisms in number and correspond to the folding and unfolding mechanisms, each sliding groove is internally connected with a sliding block in a sliding mode, and the sliding blocks are connected with the corresponding folding and unfolding mechanisms in a rotating mode.
4. The large-scale air structure mixing flexible cabin in space of claim 1, characterized in that: skin layer from interior to exterior comprises abrasionproof decreases layer, air tight layer, load layer, piece inoxidizing coating, insulating layer and atomic oxidation inoxidizing coating in proper order, the abrasionproof decreases the layer and adopts the Nomex fabric to make, the air tight layer adopts the TPU film to make, the load layer adopts the Kevlar fibre to weave and forms, the piece inoxidizing coating is by multilayer ceramic fabric and set up polyurethane foam between two adjacent ceramic fabrics, the insulating layer adopts the Pyrogenl material to make, atomic oxidation inoxidizing coating adopts the MLI film material to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110762424.1A CN113562197B (en) | 2021-07-06 | 2021-07-06 | Large-scale air of space constructs thoughtlessly moves flexible cabin |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110762424.1A CN113562197B (en) | 2021-07-06 | 2021-07-06 | Large-scale air of space constructs thoughtlessly moves flexible cabin |
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| CN113562197A true CN113562197A (en) | 2021-10-29 |
| CN113562197B CN113562197B (en) | 2022-07-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110762424.1A Active CN113562197B (en) | 2021-07-06 | 2021-07-06 | Large-scale air of space constructs thoughtlessly moves flexible cabin |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113338674A (en) * | 2021-06-02 | 2021-09-03 | 哈尔滨工业大学建筑设计研究院 | Moon pit type manned moon building structure based on future moon base and construction method |
| CN114030649A (en) * | 2021-11-26 | 2022-02-11 | 哈尔滨工业大学 | Inflatable unfolding semi-rigid sealed cabin adopting compressible multilayer sandwich protective layer |
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|---|---|---|---|---|
| US6231010B1 (en) * | 1999-01-25 | 2001-05-15 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Advanced structural and inflatable hybrid spacecraft module |
| JP2003247693A (en) * | 2002-02-21 | 2003-09-05 | Nippon Telegr & Teleph Corp <Ntt> | Hardening type inflatable device |
| FR2876984A1 (en) * | 2004-10-26 | 2006-04-28 | Ideamech Soc Par Actions Simpl | Inflatable tube for being transported in rocket, has spring that is compressed to exert axial stress on support plate in direction of base, where plate and spring remain in their initial positions during deployment of tube |
| US20100166988A1 (en) * | 2006-07-12 | 2010-07-01 | Astrium Sas | Assembly of prepregs for producing structures, for example ones which deploy through inflation |
| US8122646B1 (en) * | 2009-03-12 | 2012-02-28 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method and apparatus for an inflatable shell |
| CN104648697A (en) * | 2014-12-31 | 2015-05-27 | 哈尔滨工业大学 | Dual-layer cabin wall type inflation cabin body |
| RU164263U1 (en) * | 2016-02-19 | 2016-08-20 | Акционерное Общество "Ордена Ленина Научно-Исследовательский И Конструкторский Институт Энерготехники Имени Н.А. Доллежаля" | SPACE DEVICE MOVEMENT FROM NUCLEAR POWER INSTALLATION |
| CN107963241A (en) * | 2017-12-21 | 2018-04-27 | 中国科学院沈阳自动化研究所 | Developing space inflation bay section |
-
2021
- 2021-07-06 CN CN202110762424.1A patent/CN113562197B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6231010B1 (en) * | 1999-01-25 | 2001-05-15 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Advanced structural and inflatable hybrid spacecraft module |
| JP2003247693A (en) * | 2002-02-21 | 2003-09-05 | Nippon Telegr & Teleph Corp <Ntt> | Hardening type inflatable device |
| FR2876984A1 (en) * | 2004-10-26 | 2006-04-28 | Ideamech Soc Par Actions Simpl | Inflatable tube for being transported in rocket, has spring that is compressed to exert axial stress on support plate in direction of base, where plate and spring remain in their initial positions during deployment of tube |
| US20100166988A1 (en) * | 2006-07-12 | 2010-07-01 | Astrium Sas | Assembly of prepregs for producing structures, for example ones which deploy through inflation |
| US8122646B1 (en) * | 2009-03-12 | 2012-02-28 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method and apparatus for an inflatable shell |
| CN104648697A (en) * | 2014-12-31 | 2015-05-27 | 哈尔滨工业大学 | Dual-layer cabin wall type inflation cabin body |
| RU164263U1 (en) * | 2016-02-19 | 2016-08-20 | Акционерное Общество "Ордена Ленина Научно-Исследовательский И Конструкторский Институт Энерготехники Имени Н.А. Доллежаля" | SPACE DEVICE MOVEMENT FROM NUCLEAR POWER INSTALLATION |
| CN107963241A (en) * | 2017-12-21 | 2018-04-27 | 中国科学院沈阳自动化研究所 | Developing space inflation bay section |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113338674A (en) * | 2021-06-02 | 2021-09-03 | 哈尔滨工业大学建筑设计研究院 | Moon pit type manned moon building structure based on future moon base and construction method |
| CN114030649A (en) * | 2021-11-26 | 2022-02-11 | 哈尔滨工业大学 | Inflatable unfolding semi-rigid sealed cabin adopting compressible multilayer sandwich protective layer |
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| Publication number | Publication date |
|---|---|
| CN113562197B (en) | 2022-07-08 |
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