CN111361761A - Flexible foldable large porthole spacecraft structure - Google Patents
Flexible foldable large porthole spacecraft structure Download PDFInfo
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- CN111361761A CN111361761A CN202010187199.9A CN202010187199A CN111361761A CN 111361761 A CN111361761 A CN 111361761A CN 202010187199 A CN202010187199 A CN 202010187199A CN 111361761 A CN111361761 A CN 111361761A
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- flexible
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- porthole
- tower
- spacecraft
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- 230000007246 mechanism Effects 0.000 claims abstract description 38
- 238000003032 molecular docking Methods 0.000 claims abstract description 30
- 230000001681 protective effect Effects 0.000 claims abstract description 9
- 239000000463 material Substances 0.000 claims description 8
- 239000002775 capsule Substances 0.000 claims description 6
- 210000001503 joint Anatomy 0.000 claims description 6
- 238000007789 sealing Methods 0.000 claims description 4
- 239000012634 fragment Substances 0.000 claims description 3
- 230000005855 radiation Effects 0.000 claims description 3
- 238000011084 recovery Methods 0.000 claims description 3
- 239000003566 sealing material Substances 0.000 claims description 3
- 230000017105 transposition Effects 0.000 claims description 3
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000003340 mental effect Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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Classifications
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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
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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
Abstract
The invention provides a flexible and foldable large porthole spacecraft structure which comprises a lookout tower, a flexible cabin, a connecting cover, a docking mechanism and a cabin door. The docking mechanism of the spacecraft can be in-orbit docked with other aircrafts; the flexible cabin is in a compressed state when being launched, and can be inflated and expanded to form a flexible inflatable cabin body after being in orbit operation; the gazebo tower is provided with a 360-degree large-area immersed porthole consisting of 7 parts, and a porthole protective cover can be unfolded on a rail; the cabin door is arranged in the docking mechanism and can be opened outwards, a astronaut enters the spacecraft through the docking mechanism and the cabin door, and reaches the lookout tower through the flexible cabin, and can look out through the porthole to the external space, and the porthole provides a large-view observation window and also has the functions of improving the living environment of the astronaut and relieving the psychological pressure under the closed space environment; the connecting cover is used for connecting the berthhing mechanism and the observation tower in the launching stage, plays the roles of protecting the flexible cabin and bearing force, and before the cabin body is inflated and unfolded on the rail, the connecting cover is disconnected with the observation tower.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a flexible foldable large porthole spacecraft structure.
Background
The space flexible inflatable unfolding structure is a space structure which is constructed by flexible composite materials, is in a folding state when being launched, is unfolded by the pressure of an air source after reaching a preset track, and keeps a desired configuration by a certain method.
One of the advantages of the inflatable deployment structure is that the limitation of rocket launching envelope on the outer volume of the spacecraft is overcome. With the deep development of space technologies such as deep space exploration, space transportation, manned space flight and the like, higher requirements are put forward on the launching efficiency and the functional diversity of the spacecraft, so that a novel spacecraft configuration with higher space utilization efficiency is needed.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a flexible and foldable large porthole spacecraft structure which can effectively improve the utilization efficiency of a launching space, a 360-degree large-view porthole can be used for astronauts to observe outwards in an immersed manner and release the mental pressure of life in a space-closed environment, and a docking mechanism provides a flexible docking channel.
The invention provides a flexible and foldable large porthole spacecraft structure which comprises a lookout tower, a flexible cabin, a connecting cover, a docking mechanism and a cabin door. The docking mechanism of the spacecraft can be in-orbit docked with other aircrafts; the flexible cabin can be inflated and unfolded on the rail to form a flexible inflatable cabin body; 7 porthole protection covers of the watchtower are unfolded on the rail; a spaceman enters the spacecraft through the docking mechanism and the cabin door, reaches the observation tower through the flexible cabin, and observes the observation through the porthole; the connecting cover is used for connecting the parking mechanism with the observation tower in the transmitting stage.
The gazebo tower is in a hexagonal pyramid structure, the top of the gazebo tower is provided with 1 round porthole, the side of the gazebo tower is provided with 6 trapezoidal portholes, and the portholes provide a large-view observation window and also have the functions of improving the living environment of astronauts and relieving and releasing psychological pressure in a space-closed environment; the porthole protective cover on the outer side of the porthole can be automatically opened and closed, and when the porthole is not used, the protective device is in a closed state, so that most space radiation, micrometeors or fragments are isolated.
The flexible cabin is flexible and can open up the structure, and the tower bottom is watched in the connection of seal structure to the upper end, and berth mechanism and hatch door are connected to the lower extreme for seal structure, are in compression state when the transmission, under the restriction of transmitting condition, occupy minimum launch space and launch mass, and inflatable expansion is cylindrical after the admission, and the inlayer is sealing material, and the centre is the load material, and the skin is protective material.
The connecting cover is cylindrical, the lower end is connected with a parking mechanism during launching, the upper end is connected with the observation tower, the interior of the flexible cabin is in a compressed state, a mechanical arm adapter is arranged on the outer side of the flexible cabin, and the connecting cover and a connecting device of the observation tower are automatically unlocked and disconnected after entering a track, so that an expanded space condition is provided for an internal flexible material; the mechanical arm adapter can be matched with mechanical arms on other capsule bodies to work and is used for butt joint and transposition of the capsule bodies.
The docking mechanism is used for being in butt joint with or separated from other cabin bodies during on-orbit, the upper end face of the docking mechanism is connected with the flexible cabin, the outer ring of the lower end face of the docking mechanism is connected with the rigid connecting cover, and the cabin door is installed inside the docking mechanism.
The cabin door is arranged in the parking mechanism, is in a closed state in a normal state, and can be manually opened outwards by a astronaut when needed to form a passage with the diameter of 850 mm; the door frame is provided with a pressure relief and pressure recovery assembly, and the door is provided with a balance valve.
The invention provides a flexible and foldable large porthole spacecraft structure, so that a flexible cabin body is organically combined with a rigid porthole and a docking mechanism, the utilization efficiency of a launching space is effectively improved, the 360-degree large-view porthole can be used for astronauts to observe in an immersed mode outwards and release the mental pressure of life in a space closed environment, and the docking mechanism provides a flexible docking channel. At present, no explanation or report of the similar technology of the invention is found, and similar data at home and abroad are not collected.
Drawings
Fig. 1 is a schematic diagram of the spacecraft of the invention in an on-orbit deployed state configuration.
Fig. 2 is a schematic view of the spacecraft of the present invention in a collapsed launch configuration.
Fig. 3 is a schematic plan view of the spacecraft of the present invention in a collapsed state.
Detailed Description
The structural components of the present invention will be further described with reference to the accompanying drawings. Description of reference numerals: 1 is the observation tower, and 2 are the porthole safety cover, and 3 are flexible cabin, and 4 are berth mechanisms, and 5 are the hatch door, and 6 are the arm adapter, and 7 are the connecting cover.
As shown in fig. 1, the invention provides a spacecraft configuration, which comprises a lookout tower 1, a porthole protection cover 2, a flexible cabin 3, a docking mechanism 4, a cabin door 5, a mechanical arm adapter 6 and a connecting cover 7. Fig. 1 is a configuration of the spacecraft in an on-orbit unfolding state, fig. 2 is a configuration of the spacecraft in a folded state for launching, and fig. 3 is a top view of the spacecraft in the folded state. The configuration is characterized in that the configuration can be in butt joint with other aircrafts on rails; when in use, the flexible inflatable cabin body can be inflated and unfolded on the rail to form a flexible inflatable cabin body; the astronaut can enter the spacecraft and observe outwards through the porthole.
Lookout tower 1 is hexagonal pyramid configuration, and there is 1 circular porthole at the top, and there are 6 trapezoidal portholes in the side, has formed 360 big fields of vision immersive experience space, also plays the function that improves astronaut's living environment when the porthole provides large tracts of land observation window, alleviates release psychological pressure under the airtight environment in space.
The porthole protective cover 2 on the outer side of the porthole can be automatically opened and closed, and when the porthole is not used, the protective device is in a closed state, so that most space radiation, micrometeors or fragments are isolated.
The flexible cabin 3 is a flexible foldable structure, the upper end of the flexible cabin is connected with the bottom of the gazebo tower 1 through a sealing structure, the lower end of the flexible cabin is connected with the parking mechanism 4 and the cabin door 5 through the sealing structure, the flexible cabin is in a compression state during launching, as shown in figures 2 and 3, the flexible cabin can be folded in a Z shape, the flexible cabin occupies the minimum launching space and launching mass under the limitation of launching conditions, the flexible cabin can be expanded in a cylindrical shape after being guided into a rail, the inner layer is made of sealing materials, the middle part of the flexible cabin is made of bearing materials, and.
The connecting cover 7 is cylindrical, as shown in fig. 2, the lower end is connected with a parking mechanism during launching, the upper end is connected with a lookout tower, the interior of the lookout tower is a flexible cabin in a Z-shaped compression state, a mechanical arm adapter 6 is installed on the outer side of the lookout tower, the connecting cover 7 and a connecting device of the lookout tower 1 are automatically unlocked and disconnected after entering the track, and unfolded space conditions are provided for internal flexible materials, as shown in fig. 1;
the robot arm adapter 6 can work in cooperation with robot arms on other capsule bodies and is used for butt joint and transposition of the capsule bodies.
The docking mechanism 4 is used for being in butt joint with or separated from other cabin bodies during on-orbit, the upper end face of the docking mechanism is connected with the flexible cabin, the outer ring of the lower end face of the docking mechanism is connected with the rigid connecting cover, and the cabin door is installed inside the docking mechanism.
The cabin door 5 is arranged in the parking mechanism, is in a closed state in a normal state, and can be manually opened outwards by a astronaut when needed to form a passage with the diameter of 850 mm; the door frame is provided with a pressure relief and pressure recovery assembly, and the door is provided with a balance valve.
The spacecraft structure of the invention organically combines the flexible cabin body, the rigid porthole and the docking mechanism, effectively improves the utilization efficiency of the launching space, enables the porthole with a large area of 360 degrees to be used for astronauts to observe outwards in an immersed manner and release the mental pressure of life in a space-closed environment, and the docking mechanism provides a flexible docking channel. At present, no explanation or report of the similar technology of the invention is found, and similar data at home and abroad are not collected.
Claims (6)
1. A flexible, collapsible, large porthole spacecraft configuration comprising: the system comprises a lookout tower, a flexible cabin, a connecting cover, a docking mechanism and a cabin door;
the docking mechanism can be in on-orbit docking with other aircrafts;
the flexible cabin can be inflated and unfolded on the rail to form a flexible inflatable cabin body;
7 porthole protection covers of the watchtower are unfolded on rails; the astronaut enters the spacecraft through the docking mechanism and the cabin door, reaches the observation tower through the flexible cabin, and observes the observation through the porthole;
the connecting cover is used for connecting the parking mechanism with the observation tower in the transmitting stage.
2. The flexible and foldable large porthole spacecraft configuration of claim 1, wherein the lookout tower is of a hexagonal pyramid configuration, the top of the lookout tower is provided with 1 round porthole, the side of the lookout tower is provided with 6 trapezoid portholes, and the portholes provide a large-view observation window and also have the functions of improving the living environment of astronauts and relieving the psychological pressure under the closed space environment; the porthole protective cover on the outer side of the porthole can be automatically opened and closed, and when the porthole is not used, the protective device is in a closed state, so that most space radiation, micrometeors or fragments are isolated.
3. The configuration of claim 1, wherein the flexible cabin is of a flexible and expandable structure, the upper end of the flexible cabin is connected with the bottom of the lookout tower through a sealing structure, the lower end of the flexible cabin is connected with the parking mechanism and the cabin door through a sealing structure, the flexible cabin is in a compressed state during launching, the flexible cabin occupies the minimum launching space and launching mass under the limitation of launching conditions, and can be expanded into a cylindrical shape after being in orbit, the inner layer is made of a sealing material, the middle layer is made of a bearing material, and the outer layer is made of a protective material.
4. The configuration of the large porthole spacecraft of claim 1, wherein the connecting cover is cylindrical, the lower end of the connecting cover is connected with a parking mechanism during launching, the upper end of the connecting cover is connected with a lookout tower, the interior of the connecting cover is a compressed flexible cabin, a mechanical arm adapter is arranged on the outer side of the connecting cover, and a connecting device of the connecting cover and the lookout tower is automatically unlocked and disconnected after track entering, so that expanded space conditions are provided for internal flexible materials; the mechanical arm adapter can be matched with mechanical arms on other capsule bodies to work and is used for butt joint and transposition of the capsule bodies.
5. The configuration of claim 1, wherein the docking mechanism is adapted to dock with or disconnect from other vessels when in orbit, and has an upper end connected to the flexible vessel, a lower end outer ring connected to the rigid connection cover, and an internal port.
6. A flexible and expandable large porthole spacecraft configuration according to claim 1, wherein said door is mounted inside a docking mechanism, normally closed, and manually opened by a astronaut to form a channel 850mm in diameter when needed; the door frame is provided with a pressure relief and pressure recovery assembly, and the door is provided with a balance valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010187199.9A CN111361761A (en) | 2020-03-17 | 2020-03-17 | Flexible foldable large porthole spacecraft structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010187199.9A CN111361761A (en) | 2020-03-17 | 2020-03-17 | Flexible foldable large porthole spacecraft structure |
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| Publication Number | Publication Date |
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| CN111361761A true CN111361761A (en) | 2020-07-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010187199.9A Pending CN111361761A (en) | 2020-03-17 | 2020-03-17 | Flexible foldable large porthole spacecraft structure |
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Citations (10)
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|---|---|---|---|---|
| US4880186A (en) * | 1985-12-05 | 1989-11-14 | John Mecca | Prefabricated space station |
| JP2001090897A (en) * | 1999-09-24 | 2001-04-03 | Nippon Telegr & Teleph Corp <Ntt> | Inflatable tube |
| 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 |
| CN104554822A (en) * | 2014-12-31 | 2015-04-29 | 哈尔滨工业大学 | Multilayer hollow interlayer inflated cabin |
| CN204323675U (en) * | 2014-12-11 | 2015-05-13 | 天津航天机电设备研究所 | Near space vehicle manned capsule |
| CN105059567A (en) * | 2015-08-12 | 2015-11-18 | 北京空间飞行器总体设计部 | Porthole device for flexible inflatable cabin of spacecraft |
| CN105711857A (en) * | 2016-04-28 | 2016-06-29 | 兰州空间技术物理研究所 | Membrane aerospace craft deploying and locking mechanism |
| CN106143907A (en) * | 2016-06-30 | 2016-11-23 | 宁波市成大机械研究所 | A kind of jet flying saucer |
| CN107416230A (en) * | 2017-07-05 | 2017-12-01 | 上海宇航系统工程研究所 | A kind of configuration of the goods airlock of spacecraft |
| 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 |
-
2020
- 2020-03-17 CN CN202010187199.9A patent/CN111361761A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4880186A (en) * | 1985-12-05 | 1989-11-14 | John Mecca | Prefabricated space station |
| 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 |
| JP2001090897A (en) * | 1999-09-24 | 2001-04-03 | Nippon Telegr & Teleph Corp <Ntt> | Inflatable tube |
| CN204323675U (en) * | 2014-12-11 | 2015-05-13 | 天津航天机电设备研究所 | Near space vehicle manned capsule |
| CN104554822A (en) * | 2014-12-31 | 2015-04-29 | 哈尔滨工业大学 | Multilayer hollow interlayer inflated cabin |
| CN105059567A (en) * | 2015-08-12 | 2015-11-18 | 北京空间飞行器总体设计部 | Porthole device for flexible inflatable cabin of spacecraft |
| CN105711857A (en) * | 2016-04-28 | 2016-06-29 | 兰州空间技术物理研究所 | Membrane aerospace craft deploying and locking mechanism |
| CN106143907A (en) * | 2016-06-30 | 2016-11-23 | 宁波市成大机械研究所 | A kind of jet flying saucer |
| CN107416230A (en) * | 2017-07-05 | 2017-12-01 | 上海宇航系统工程研究所 | A kind of configuration of the goods airlock of spacecraft |
| 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 |
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Application publication date: 20200703 |
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