WO2019120205A1 - 空间充气展开舱段 - Google Patents

空间充气展开舱段 Download PDF

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Publication number
WO2019120205A1
WO2019120205A1 PCT/CN2018/121933 CN2018121933W WO2019120205A1 WO 2019120205 A1 WO2019120205 A1 WO 2019120205A1 CN 2018121933 W CN2018121933 W CN 2018121933W WO 2019120205 A1 WO2019120205 A1 WO 2019120205A1
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WO
WIPO (PCT)
Prior art keywords
layer
ring
disposed
expansion
cabin
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PCT/CN2018/121933
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English (en)
French (fr)
Inventor
刘金国
陈科利
田远征
Original Assignee
中国科学院沈阳自动化研究所
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Application filed by 中国科学院沈阳自动化研究所 filed Critical 中国科学院沈阳自动化研究所
Publication of WO2019120205A1 publication Critical patent/WO2019120205A1/zh

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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
    • 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

Definitions

  • the present invention relates to the field of space capsule technology, and more particularly to a space inflated deployment section.
  • the rigid metal sealed cabin has the disadvantages of heavy mass, large volume, high launching cost, and difficulty in assembly in orbit.
  • the traditional rigid metal sealed cabin must be designed to be relatively compact, which results in a narrow effective space in the cabin, which makes it difficult for many scientific experiments to be carried out smoothly. It is difficult to meet the needs of future deep space exploration development. .
  • the object of the present invention is to provide a space inflatable deployment cabin, which has the advantages of being foldable, small in quality, low in production cost, good in protection performance, and the like, and has wide application prospects in the field of deep space detection.
  • a space inflation deployment section includes an air lock cabin, a cabin core and a flexible outer casing, the cabin core is disposed in a flexible outer casing, the air lock cabin is disposed at an upper end of the cabin core and disposed outside the flexible outer casing, the flexible outer casing Inflated and unfolded;
  • the nacelle stem comprises a stem frame, and an upper end layer, an intermediate layer and a lower end layer are sequentially arranged from the top to the bottom on the stem frame, and the end layer and the lower end layer are each provided with an end layer a plate assembly, and the upper end layer and the lower end layer are divided into a plurality of movable regions by the end laminate assembly, the intermediate layer is provided with an intermediate laminate assembly, and the intermediate layer is divided by the intermediate laminate assembly a movable area, in the flexible outer casing, a space expansion component is disposed outside the cabin core, the space expansion component is provided with a plurality of expansion plates, and an expansion support bar is disposed between adjacent expansion plates,
  • a drive deployment mechanism is
  • the air lock cabin includes a rigid cabin and an air lock door, and an upper end plate and a lower end plate are respectively disposed at upper and lower ends of the rigid cabin, and an air lock is hinged to the lower side of the upper end plate and the lower side of the lower end plate a door, a lower side of the upper end plate and the lower end plate are provided with a locking groove, the air lock door is provided with a retractable locking block, and the air lock door protrudes in the locking block Insert the corresponding lock slot lock.
  • the air brake door includes a door shell, an operating handle, an intermediate gear, a planetary gear, a ring gear, a connecting rod and a locking block, wherein the intermediate gear, the planetary gear, the ring gear and the connecting rod are disposed in the cabin In the door housing, the intermediate gear and the planetary gear are disposed in the ring gear, the plurality of planetary gears are evenly distributed in the circumferential direction, and the inner side meshes with the intermediate gear, and the outer side meshes with the ring gear, the intermediate gear
  • the two ends of the gear shaft respectively extend out of the door shell and are respectively connected with the operating handles on both sides of the door shell, and the outer side of the ring gear is evenly distributed with a plurality of connecting rods on the circumferential edge of the door shell
  • the cloth has a plurality of sliding through holes, and each of the sliding through holes is provided with a locking block, and the locking blocks are connected to the connecting rods in one-to-one correspondence.
  • the end layer plate assembly comprises an end layer bottom plate, an end layer fixed partition plate and an end layer moving partition plate, wherein the end layer bottom plate is fixed on the core column frame, and the end layer fixing partition plate has a right angle shape and is fixed at the end On the bottom plate, the end layer fixed partitions are provided with end layer moving partitions at both ends.
  • the intermediate layer board assembly comprises an intermediate layer bottom plate, an intermediate layer vertical plate and an annular sleeve, wherein the intermediate layer bottom plate is fixed on the core column frame, and the intermediate layer vertical plate and the annular sleeve are fixed on the intermediate layer bottom plate, and the plurality of The intermediate layer risers are evenly distributed in the annular sleeve along the circumferential direction.
  • the space expansion component includes a plurality of upper expansion boards and a plurality of lower expansion boards, and an upper expansion support bar is disposed between the adjacent two upper expansion boards, and a lower expansion support is provided between the adjacent two lower expansion boards.
  • a plurality of bottom plate support rings are disposed on the stem frame, and the upper end layer and the intermediate layer are fixed on different bottom plate support rings, and the upper extended support bar is hinged on the bottom plate support ring supporting the upper end layer,
  • an upper driving ring is disposed on an upper side of the bottom plate support ring, and the upper extended support rod is connected to the upper driving ring through an upper driving link, and the lower extended supporting rod is hinged on a bottom plate supporting ring supporting the intermediate layer,
  • a lower drive ring is disposed on a lower side of the bottom plate support ring, and the lower extension support rod is connected to the lower drive ring through a lower drive link, and the upper drive ring and the lower drive ring are driven by the drive deployment mechanism Move to.
  • the drive deployment mechanism includes two sets of structurally identical and symmetrically arranged drive assemblies, the upper drive ring and the lower drive ring being respectively driven to move by different drive assemblies, the drive assembly including a drive motor, a lead screw, a nut and a connection block The lead screw is driven to rotate by the driving motor, and a thread is arranged on the lead screw, and the connecting block is fixedly connected with the upper driving ring or the lower driving ring.
  • the stem frame is provided with a guiding mechanism, the guiding mechanism comprises two sets of identical guiding components, the guiding component comprises a guiding rod and a guiding block, the guiding block is sleeved on the guiding rod, and the upper driving The ring and lower drive ring are respectively connected to guide blocks in different guide assemblies.
  • the space expansion assembly further includes an upper inflatable ring and a lower inflatable ring disposed inside the flexible outer casing, and a connecting post is disposed between the upper inflatable ring and the lower inflatable ring, and the upper inflatable body is inflated when the flexible outer casing is inflated
  • the ring, the lower inflatable ring and the interior of the connecting post are both inflated, the fully expanded rear edge of the upper expansion plate abuts the upper inflatable ring, and the lower expanded plate is fully deployed with the rear edge abutting the lower inflatable ring.
  • the flexible outer casing is provided with an atomic oxygen protective layer, a thermal protective layer, an outer protective layer, an outer foam layer, an intermediate protective layer, an inner foam layer, an inner protective layer, a structural limiting layer, an airtight layer, and an interval from the outside to the inside. Layer, main airtight layer and inner liner.
  • the flexible outer casing of the present invention can be folded before being launched, and then inflated and deployed after entering a predetermined track, so that it has a higher volume-to-mass ratio than the conventional rigid aluminum-shell structure, and the launching cost is greatly reduced.
  • the material of the flexible outer casing is easy to obtain, and the manufacturing process of the flexible cabin only needs to be in a semi-clean environment, and the manufacturing cost is low.
  • the invention has a space expansion component inside, which can be deployed to form a platform for the astronauts to move.
  • the upper end layer and the lower end layer of the invention are provided with an extendable end layer moving partition, which fully guarantees the inside of the cabin. There is enough room for astronauts to move.
  • the present invention is greatly reduced in volume and mass, so that the on-orbit assembly is easy to implement after being carried by the launch vehicle to the working rail.
  • Figure 1 is a schematic view showing the structure of the present invention
  • FIG. 1 is a schematic view of the core segment of the cabin of Figure 1
  • Figure 3 is a schematic view showing the structure of the air brake cabin of Figure 2;
  • FIG. 4 is a schematic view of the air brake door of Figure 3
  • Figure 5 is a schematic view showing the internal structure of the air brake door of Figure 4.
  • Figure 6 is a schematic view showing the structure of the upper end layer of Figure 2;
  • Figure 7 is a schematic view showing the structure of the intermediate layer in Figure 2;
  • Figure 8 is a schematic view showing the structure of the lower end layer of Figure 2;
  • Figure 9 is another perspective view of the lower end layer of Figure 8.
  • Figure 10 is a schematic view of the stem frame of Figure 2
  • FIG 11 is a schematic view of the drive deployment mechanism of Figure 10
  • Figure 12 is a schematic view of the guiding mechanism of Figure 10
  • Figure 13 is a schematic view showing the folding of the flexible casing of Figure 1.
  • 1 is an airlock compartment
  • 101 is a sealing ring
  • 102 is a lower end plate
  • 103 is a rigid cabin
  • 104 is an upper end plate
  • 105 is an airbag embedded part
  • 106 is a second end cover
  • 107 is a first end cover
  • 108 is a tank flange
  • 2 is an end layer assembly
  • 201 is an end layer bottom plate
  • 202 is an end layer moving partition
  • 203 is an end layer fixed partition
  • 204 is a partition fixing member
  • 3 is an intermediate layer
  • 301 is The middle layer vertical plate
  • 302 is the middle layer bottom plate
  • 303 is the vertical plate fixing member
  • 304 is the annular sleeve
  • 4 is the space expansion component
  • 401 is the upper inflation ring
  • 402 is the lower inflation ring
  • 403 is the connecting column
  • 404 is the upper expansion Plate
  • 4041 is the upper extension support rod
  • 4042 is the upper drive link
  • 4043 is the upper drive
  • the present invention includes an airlock cabin 1, a nacelle core and a flexible outer casing 5, the nacelle core is disposed in the flexible outer casing 5, the airlock compartment 1 is disposed at the upper end of the nacelle, and the flexible outer casing 5
  • the upper side is disposed at one end of the airlock chamber 1 and the nacelle core column, and a bottom end flange 8 is disposed at a lower end of the nacelle core column, and a lower side of the flexible outer casing 5 is set on the bottom end flange 8
  • the flexible outer casing 5 can be folded along the nacelle core before the section is fired to reduce the volume, and the inflation can be deployed when in use.
  • FIGS. 13 the flexible outer casing 5 can be folded along the nacelle core before the section is fired to reduce the volume, and the inflation can be deployed when in use.
  • the nacelle stem comprises a stem frame 7, an upper end layer, an intermediate layer 3 and a lower end layer, and the upper end layer, the intermediate layer 3 and the lower end layer are both mounted on the stem frame 7,
  • the upper end layer is disposed on the upper side of the intermediate layer 3
  • the lower end layer is disposed on the lower side of the intermediate layer 3
  • the end layer plate assembly 2 is disposed in the upper end layer and the lower end layer, and the upper end layer and the lower end layer are respectively passed through
  • the end laminate assembly 2 is divided into a plurality of movable regions
  • an intermediate laminate assembly is disposed in the intermediate layer 3
  • the intermediate layer 3 is divided into a plurality of active regions by the intermediate laminate assembly. As shown in FIGS.
  • a space expansion assembly 4 is disposed outside the intermediate layer 3 of the nacelle, and the space expansion assembly 4 is provided with a plurality of expansion plates.
  • an expansion support bar is disposed between the adjacent expansion plates, and a drive deployment mechanism 702 is disposed in the core frame 7, and the expansion support bar drives the synchronous swing through the drive deployment mechanism 702 to drive the expansion.
  • the panels are unfolded to form a platform for activities.
  • the airlock compartment 1 includes a rigid cabin 103 and an airlock door 6, and two airlock doors 6 are disposed at upper and lower ends of the rigid cabin 103, in the rigid cabin 103.
  • the lower end is provided with a cabin flange 108, and a first end cover 107 and a second end cover 106 are sequentially disposed from top to bottom on the upper side of the cabin flange 108.
  • the flexible outer casing 5 has a multi-layer structure, and the flexible outer casing 5 is provided with an atomic oxygen protection layer 501, a thermal protection layer 502, an outer protective layer 503, an outer foam layer 504, an intermediate protective layer 505, and an inner portion.
  • the airbag embedded component 105 is fixed on the upper end of the core frame 7, and the inner liner 512 is disposed on the lower side of the airbag embedded component 105.
  • the airtight layer 509, the spacer layer 510 and the main air are provided.
  • the dense layer 511 is disposed on the upper side of the airbag embedded member 105 and is fixed by the cabin flange 108.
  • the spacer layer 510 separates the airtight layer 509 from the main airtight layer 511.
  • the structural limiting layer 508 is disposed on the airtight layer 511.
  • the upper side of the cabin flange 108 is pressed and fixed by the second end cover 106, the atomic oxygen protection layer 501, the heat protection layer 502, the outer protective layer 503, the outer foam layer 504, the intermediate protective layer 505, and the inner foam.
  • the layer 506 and the inner protective layer 507 are disposed on the upper side of the second end cover 106 and are fixed by the first end cover 107.
  • the lower side of the flexible outer casing 5 is fixed to the bottom end flange 8 and the mounting structure is the same as the upper side.
  • an upper end plate 104 and a lower end plate 102 are respectively disposed at upper and lower ends of the rigid cabin 103.
  • a hinge plate 604 is provided on one side of the air lock door 6
  • the airlock door 6 is respectively hinged to the lower side of the upper end plate 104 and the lower side of the lower end plate 102 of the rigid cabin 103 through the hinge plates 604 and the hinges, and the lower sides of the upper end plate 104 and the lower end plate 102 are circumferentially
  • a locking groove is provided.
  • the airlock door 6 is uniformly distributed with a plurality of synchronously expandable locking blocks 605 along the circumferential direction. When the locking block 605 is extended and inserted When the slot is locked, the airlock door 6 is locked.
  • the airlock door 6 includes a door housing, an operating handle 603, an intermediate gear 611, a planetary gear 610, a ring gear 609, a connecting rod 608, and a locking block 605.
  • the door shell is formed by the upper end cover 607 of the hatch and the lower end cover 606 of the hatch.
  • the upper and lower sides of the hatch door are provided with an operating handle 603, and are disposed on the upper and lower sides of the hatch door.
  • the intermediate gear 611, the planetary gear 610, the ring gear 609 and the link 608 are all disposed in the door housing, and the intermediate gear 611 and the plurality of planetary gears 610 are disposed on the teeth
  • the plurality of planetary gears 610 are evenly distributed in the circumferential direction, and the inner side is meshed with the intermediate gear 611, and the outer side is meshed with the ring gear 609.
  • the two ends of the gear shaft 612 of the intermediate gear 611 respectively protrude to
  • the door shells are respectively connected to the operating handles 603 on the upper and lower sides of the door shells, and the outer side of the ring gear 609 is evenly distributed with a plurality of connecting rods 608 in the circumferential direction, and the circumferential edges of the door shells are evenly distributed.
  • a plurality of sliding through holes and each of the sliding through holes is provided with a locking block 605, the locking block 605 and the Link 608 and is connected to one correspondence telescopic movement by the drive link 608.
  • two sealing rings 101 are provided between the upper end plate 104 of the rigid cabin 103 and the upper airlock door 6, on the lower end plate 102 and the lower side of the rigid cabin 103. There are also two sealing rings 101 between the airlock doors 6 .
  • the end layer plate assembly 2 includes an end layer bottom plate 201, an end layer fixing partition 203 and an end layer moving partition 202, wherein the end layer bottom plate 201 is fixed on the core column frame 7,
  • the end layer fixing partition plate 203 is formed in a right angle shape and is fixed on the end layer bottom plate 201 through the partition fixing member 204, and an end layer moving partition plate 202 is disposed at both ends of the end layer fixing partition plate 203.
  • a total of four end layer fixed partitions 203 are formed and a cross-shaped movable area is formed, and the end layer moving partition 202 is extended to extend the range of the movable area, and the end layer moving partition 202 passes the slide rail slider.
  • the structure is slidably coupled to the end layer fixed partition 203.
  • the intermediate layer board assembly includes an intermediate layer bottom plate 302, an intermediate layer vertical plate 301, and an annular sleeve 304.
  • the intermediate layer bottom plate 302 is fixed to the core column frame 7, and the intermediate layer vertical plate 301 and the annular sleeve 304 are
  • the inner layer bottom plate 302 is fixed on the intermediate layer bottom plate 302, and the plurality of intermediate layer vertical plates 301 are evenly distributed in the annular sleeve 304 in the circumferential direction, thereby equally dividing the annular sleeve 304 into a plurality of movable regions.
  • the annular sleeve 304 is an annular water jacket, and the intermediate layer vertical plate 301 is fixed to the intermediate layer bottom plate 302 by a vertical plate fixing member 303.
  • a plurality of bottom plate support rings 704 are disposed on the stem frame 7, and the end layer bottom plate 201 of the upper end layer and the intermediate layer bottom plate 302 of the intermediate layer 3 are respectively fixed to different bottom plate support rings.
  • the end layer bottom plate 201 of the lower end layer is fixed to the bottom end of the stem frame 7.
  • the space expansion assembly 4 includes a plurality of upper expansion plates 404 and a plurality of lower expansion plates 405, and the plurality of upper expansion plates 404 are unfolded to form an upper movable position.
  • the platform, the plurality of lower expansion boards 405 are unfolded to form a movable lower platform, and an upper expansion support rod 4041 is disposed between the adjacent two upper expansion boards 404, and the upper expansion board 404 passes through
  • the expansion support bar 4041 is swinging or unfolding
  • a lower extension support bar 4051 is disposed between the adjacent two lower expansion plates 405, and the lower expansion plate 405 is swinging or unfolded by the lower extension support bar 4051 or Collapse.
  • the upper extension support rods 4041 are each hinged to the bottom plate support ring 704 supporting the upper end layer end plate 201, and an upper drive ring 4043 is disposed on the upper side of the bottom plate support ring 704.
  • the support rods 4041 are connected to the upper drive ring 4043 through upper drive links 4042, respectively.
  • the lower extension support rods 4051 are respectively hinged on the bottom plate support ring 704 supporting the intermediate layer bottom plate 302, and a lower drive ring 4053 is disposed on the lower side of the bottom plate support ring 704, and the lower extension support rods 4051 are respectively driven through the lower drive A rod 4052 is coupled to the lower drive ring 4053.
  • the upper driving ring 4043 and the lower driving ring 4053 are sleeved on the outside of the stem frame 7, and a driving and unwinding mechanism 702 is disposed on the stem frame 7 to drive the upper driving ring 4043 and the lower driving ring 4053.
  • the upper extension plate 404 and the lower expansion plate 405 are unfolded or stowed, and a guide mechanism 703 is provided on the stem frame 7 to guide the upper drive ring 4043 and the lower drive ring 4053 to move up and down.
  • a guide mechanism 703 is provided on the stem frame 7 to guide the upper drive ring 4043 and the lower drive ring 4053 to move up and down.
  • a drive deployment mechanism 702 and a guide mechanism 703 are provided on the front and rear sides of the stem frame 7, and the stem frame 7 includes a plurality of frame side beams 701, and each drive The deployment mechanism 702 and the respective guide mechanisms 703 are mounted on different frame side members 701, respectively.
  • the drive deployment mechanism 702 includes two sets of symmetrically disposed drive assemblies, and the upper drive ring 4043 and the lower drive ring 4053 are driven to move by different drive assemblies.
  • the driving assembly includes a driving motor 7021, a lead screw 7025, a female core 7023, and a connecting block 7024.
  • the driving motor 7021 is fixed on the frame side beam 701, and the two ends of the lead screw 7025 are respectively passed.
  • the bearing housing 7022 is supported and mounted on the frame side beam 701, and the lead screw 7025 is driven to rotate by the driving motor 7021, and the threaded spindle 7025 is set on the lead screw 7025, and the female nut 7023 is fixedly connected.
  • Block 7024 is affixed to upper drive ring 4043 or lower drive ring 4053.
  • the guide mechanism 703 includes two sets of guide assemblies, and the upper drive ring 4043 and the lower drive ring 4053 are guided by different guide assemblies.
  • the guiding assembly includes a guiding bracket 7031, a guiding rod 7032 and a guiding block 7033.
  • the two ends of the guiding rod 7032 are respectively supported and mounted on the frame side beam 701 by a guiding bracket 7031.
  • the guiding block 7033 is set.
  • the guide bar 7032 is fixed to the upper drive ring 4043 or the lower drive ring 4053.
  • the space expansion assembly 4 further includes an upper inflation ring 401 and a lower inflation ring 402 disposed inside the flexible outer casing 5, and a connection is provided between the upper inflation ring 401 and the lower inflation ring 402.
  • the upper inflatable ring 401, the lower inflatable ring 402 and the connecting post 403 are inflated to increase the rigidity, thereby increasing the rigidity of the flexible outer casing 5, and the upper expansion plate 404 is expanded.
  • the edge abuts the upper inflatable ring 401, the rear edge of the lower expansion plate 405 abuts the lower inflation ring 402, and the upper expansion plate 404 and the lower expansion plate 405 are supported by the connecting post 403.
  • the working principle of the invention is:
  • the flexible outer casing 5 can be folded along the central section core before being launched, and after being transported to the predetermined working track by the carrier rocket, the inside of the flexible casing 5 starts to be inflated and the expansion of the flexible casing 5 is achieved by the internal air pressure.
  • the inside of the upper inflation ring 401 and the lower inflation ring 402 are also inflated, and the rigidity becomes larger as the pressure is increased, thereby increasing the rigidity of the flexible outer casing 5.
  • the drive motor 7021 in the drive deployment mechanism 702 is then activated, and the upper drive ring 4043 and the lower drive ring 4053 are driven to move by the lead screw mechanism, so that the upper expansion plate 404 and the lower expansion plate 405 are fully deployed to form an active upper platform.
  • the lower platform in addition, the end layer moving partition 202 in the upper end layer and the lower end layer may also extend to extend the active area in the layer.
  • the atomic oxygen barrier layer 501 and the heat protection layer 502 in the flexible outer casing 5 can respectively perform atomic oxygen protection and thermal protection during the operation of the cabin in the orbit, the outer protective layer 503, the outer foam layer 504, and the middle.
  • the protective layer 505, the inner foam layer 506, and the inner protective layer 507 can serve as a microscopic meteorite and orbital debris protection, the main airtight layer 511 functions as a gas tight, and the airtight layer 509 is in the main airtight layer 511.
  • the structural limiting layer 508 is the most important bearing layer in the flexible outer casing 5 for receiving the gas pressure in the cabin.
  • the main function of the inner liner 512 is The main airtight layer 511 is prevented from being pierced by the in-cabin sharpener.
  • the main function of the airlock 1 is to provide a pressure transition zone during the astronaut's entry and exit of the cabin.
  • the astronaut first raises the pressure in the airlock 1 to the pressure in the cabin.
  • the lower airlock door 6 is opened, the astronaut enters the airlock compartment 1, and then the lower airlock door 6 is closed, and the airlock compartment 1 pressure is adjusted to be the same as the gas pressure to be entered into the cabin, and the upper end is opened.
  • the order of return is reversed from the outbound.

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  • Aviation & Aerospace Engineering (AREA)
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Abstract

一种空间充气展开舱段，包括气闸舱（1）、舱段芯柱和柔性外壳（5），舱段芯柱设置于柔性外壳（5）中，气闸舱（1）设置于舱段芯柱上端且设置于柔性外壳（5）外侧，柔性外壳（5）充气展开；舱段芯柱包括一个芯柱框架（7），且在芯柱框架（7）上依次设有上端层、中间层（3）和下端层，上端层和下端层内均设有端层板组件（2），中间层（3）内设有中间层板组件，在舱段芯柱外侧设有空间扩展组件（4），空间扩展组件（4）设有多个扩展板，且相邻扩展板之间均设有扩展支撑杆，在芯柱框架内设有驱动展开机构（702），扩展支撑杆通过驱动展开机构（702）驱动摆动并展开或收起扩展板。该空间充气展开舱段具有可折叠、质量小、制作成本低，防护性能好等优点，在深空探测领域具有广泛的应用前景。

Description

空间充气展开舱段 技术领域
本发明涉及太空舱技术领域，具体地说是一种空间充气展开舱段。
背景技术
现有技术中，包括国际空间站在内的在轨道航天器大多以刚性金属舱为主，刚性金属密封舱存在质量重、体积大、发射成本高、在轨组装困难等缺点。此外，由于受运载火箭包络尺寸的限制，传统刚性金属密封舱必须设计的相对紧凑，这就造成舱内有效空间狭窄，导致诸多科学试验难以顺利开展，已经难以满足未来深空探测发展的需要。
发明内容
本发明的目的在于提供一种空间充气展开舱段，具有可折叠、质量小、制作成本低、防护性能好等优点，在深空探测领域具有广泛的应用前景。
本发明的目的是通过以下技术方案来实现的：
一种空间充气展开舱段，包括气闸舱、舱段芯柱和柔性外壳，所述舱段芯柱设置于柔性外壳中，气闸舱设置于所述舱段芯柱上端且设置于柔性外壳外侧，所述柔性外壳充气展开；所述舱段芯柱包括一个芯柱框架，且在所述芯柱框架上由上到下依次设有上端层、中间层和下端层，所述上端层和下端层内均设有端层板组件，且所述上端层和下端层通过所述端层板组件分成多个活动区域，所述中间层内设有中间层板组件，且所述中间层通过所述中间层板组件分成多个活动区域，在所述柔性外壳内，在所述舱段芯柱外侧设有空间扩展组件，所述空间扩展组件设有多个扩展板，且相邻扩展板之间均设有扩展支撑杆，在所述芯柱框架内设有驱动展开机构，扩展支撑杆通过所述驱动展开机构驱动摆动，扩展板通过所述扩展支撑杆摆动驱动展开。
所述气闸舱包括刚性舱体和气闸舱门，在所述刚性舱体上下两端分别设有上端板和下端板，且所述上端板下侧和下端板下侧均铰接有一个气闸舱门，所述上端板和下端板下侧均设有锁紧槽，所述气闸舱门上设有可伸缩的锁紧块，且所述气闸舱门在所述锁紧块伸出插入对应锁紧槽锁定。
所述气闸舱门包括舱门壳体、操作手柄、中间齿轮、行星齿轮、齿圈、连杆和锁紧块，所述中间齿轮、行星齿轮、齿圈和连杆均设置于所述舱门壳体内，且所述中间齿轮和行星齿轮设置于所述齿圈内，多个行星齿轮沿圆周方向均布且内侧与所述中间齿轮啮合、外侧与所述齿圈啮合，所述中间齿轮的齿轮轴两端分别伸出至舱门壳体外并分别与舱门壳体两侧的操作手柄相连，所述齿圈外侧均布有多个连杆，在所述舱门壳体圆周边缘均布有多个滑动通孔，且每个滑动通孔内均设有一个锁紧块，所述锁紧块与所述连杆一一对应相连。
所述端层板组件包括端层底板、端层固定隔板和端层移动隔板，其中端层底板固装于芯柱框架上，端层固定隔板呈直角形状并固装于所述端层底板上，所述端层固定隔板两端均设有端层移动隔板。
所述中间层板组件包括中间层底板、中间层立板和环形套，中间层底板固装于芯柱框架上，中间层立板和环形套固装于所述中间层底板上，且多个中间层立板沿着圆周方向均布于环形套内。
所述空间扩展组件包括多个上扩展板和多个下扩展板，且相邻两个上扩展板之间设有上扩展支撑杆，在相邻两个下扩展板之间设有下扩展支撑杆，所述芯柱框架上设有多个底板支撑环，且所述上端层和中间层固装于不同底板支撑环上，所述上扩展支撑杆铰接于支撑上端层的底板支撑环上，且在该底板支撑环上侧设有上驱动环，所述上扩展支撑杆通过上驱动连杆与所述上驱动环相连，所述下扩展支撑杆铰接于支撑中间层的底板支撑环上，且在该底板支撑环下侧设有下驱动环，所述下扩展支撑杆通过下驱动连杆与所述下驱动环相连，所述上驱动环和下驱动环通过所述驱动展开机构驱动反向移动。
所述驱动展开机构包括两组结构相同且对称设置的驱动组件，所述上驱动环和下驱动环分别通过不同驱动组件驱动移动，所述驱动组件包括驱动电机、丝杠、丝母和连接块，所述丝杠通过所述驱动电机驱动旋转，在所述丝杠上套装有丝母，所述丝母上固设有连接块与上驱动环或下驱动环固连。
所述芯柱框架上设有导向机构，所述导向机构包括两组结构相同的导向组件，所述导向组件包括导向杆和导向块，所述导向块套装于导向杆上，且所述上驱动环和下驱动环分别与不同导向组件中的导向块相连。
所述空间扩展组件还包括设置于柔性外壳内侧的上充气环和下充气环，在所述上充气环和下充气环之间设有连接柱，所述柔性外壳充气展开时，所述上充气环、下充气环和连接柱内部均充气，所述上扩展板完全展开后边缘与所述上充气环相抵，所述下扩展板完全展开后边缘与所述下充气环相抵。
所述柔性外壳由外到内依次设有原子氧防护层、热防护层、外防护层、外泡沫层、中间防护层、内泡沫层、内防护层、结构限制层、备气密层、间隔层、主气密层和内衬层。
本发明的优点与积极效果为：
1.本发明的柔性外壳可在发射前处于折叠状态，进入预定轨道后再充气展开，因此与传统的刚性铝壳结构舱体相比，具有更高的容积质量比，且发射成本大大降低，另外柔性外壳的材料容易获取，柔性舱体的制作过程中只需要在半洁净的环境中即可，制作成本低。
2.本发明内部设有空间扩展组件，可展开形成供航天员活动的平台，另外 本发明上端层和下端层内均设有可伸出的端层移动隔板，这些都充分保证舱段内有足够空间供航天员活动。
3.本发明与传统刚性金属舱相比，由于体积和质量大大降低，因此经运载火箭运载至工作轨道之后，在轨组装易于实施。
附图说明
图1为本发明的结构示意图，
图2为图1中的舱段芯柱示意图，
图3为图2中的气闸舱结构示意图，
图4为图3中的气闸舱门示意图，
图5为图4中的气闸舱门内部结构示意图，
图6为图2中的上端层结构示意图，
图7为图2中的中间层结构示意图，
图8为图2中的下端层结构示意图，
图9为图8中的下端层另一角度示意图，
图10为图2中的芯柱框架示意图，
图11为图10中的驱动展开机构示意图，
图12为图10中的导向机构示意图，
图13为图1中的柔性外壳折叠示意图。
其中，1为气闸舱，101为密封圈，102为下端板，103为刚性舱体，104为上端板，105为气囊预埋件，106为第二端盖，107为第一端盖，108为舱体法兰；2为端层板组件，201为端层底板，202为端层移动隔板，203为端层固定隔板，204为隔板固定件；3为中间层，301为中间层立板，302为中间层底板，303为立板固定件，304为环形套；4为空间扩展组件，401为上充气环，402为下充气环，403为连接柱，404为上扩展板，4041为上扩展支撑杆，4042为上驱动连杆，4043为上驱动环，405为下扩展板，4051为下扩展支撑杆，4052为下驱动连杆，4053为下驱动环；5为柔性外壳，501为原子氧防护层，502为热防护层，503为外防护层，504为外泡沫层，505为中间防护层，506为内泡沫层，507为内防护层，508为结构限制层，509为备气密层，510为间隔层，511为主气密层，512为内衬层；6为气闸舱门，601为操作提示牌，602为锁紧螺母，603为操作手柄，604为铰接板，605为锁紧块，606为舱门下端盖，607为舱门上端盖，608为连杆，609为齿圈，610为行星齿轮，611为中间齿轮，612为齿轮轴；7为芯柱框架，701为框架侧梁，702为驱动展开机构，7021为驱动电机，7022为轴承座，7023为丝母，7024为连接块，7025为丝杠，703为导向机构，7031为导向支架，7032为导向杆，7033为导向块，704为底板支 撑环；8为底端法兰。
具体实施方式
下面结合附图对本发明作进一步详述。
如图1～13所示，本发明包括气闸舱1、舱段芯柱和柔性外壳5，所述舱段芯柱设置于柔性外壳5中，气闸舱1设置于所述舱段芯柱上端，且柔性外壳5上侧套装于所述气闸舱1与所述舱段芯柱相连一端，在所述舱段芯柱下端设有底端法兰8，柔性外壳5下侧套装于所述底端法兰8上，如图13所示，所述柔性外壳5在舱段发射前可沿着所述舱段芯柱折叠以减小体积，使用时充气即可展开。如图1～2所示，所述舱段芯柱包括芯柱框架7、上端层、中间层3和下端层，所述上端层、中间层3和下端层均安装在所述芯柱框架7上，且上端层设置于中间层3上侧，下端层设置于中间层3下侧，所述上端层和下端层内均设有端层板组件2，且所述上端层和下端层内部均通过所述端层板组件2分成多个活动区域，所述中间层3内设有中间层板组件，且所述中间层3通过所述中间层板组件分成多个活动区域。如图1～2和图6～7所示，在所述柔性外壳5内，在所述舱段芯柱的中间层3外侧设有空间扩展组件4，所述空间扩展组件4设有多个扩展板，且相邻扩展板之间均设有扩展支撑杆，在所述芯柱框架7内设有驱动展开机构702，且所述扩展支撑杆通过所述驱动展开机构702驱动同步摆动，进而驱动扩展板展开形成可供活动的平台。
如图3所示，所述气闸舱1包括刚性舱体103和气闸舱门6，两个气闸舱门6分设于所述刚性舱体103的上下两端，在所述刚性舱体103下端设有舱体法兰108，且在所述舱体法兰108上侧由上到下依次设有第一端盖107和第二端盖106。所述柔性外壳5为多层结构，且所述柔性外壳5由外到内依次设有原子氧防护层501、热防护层502、外防护层503、外泡沫层504、中间防护层505、内泡沫层506、内防护层507、结构限制层508、备气密层509、间隔层510、主气密层511和内衬层512，其中在所述内衬层512端部设有气囊预埋件105，所述气囊预埋件105固装于芯柱框架7上端，且所述内衬层512设置于气囊预埋件105下侧，所述备气密层509、间隔层510和主气密层511设置于气囊预埋件105上侧并通过舱体法兰108压住固定，所述间隔层510将备气密层509和主气密层511分离，所述结构限制层508设置于舱体法兰108上侧并通过所述第二端盖106压住固定，所述原子氧防护层501、热防护层502、外防护层503、外泡沫层504、中间防护层505、内泡沫层506和内防护层507设置于所述第二端盖106上侧并通过所述第一端盖107压住固定。所述柔性外壳5下侧固装于所述底端法兰8上且安装结构与上侧相同。
如图3所示，在所述刚性舱体103上下两端分别设有上端板104和下端板 102，如图4所示，在所述气闸舱门6一侧设有铰接板604，两个气闸舱门6即通过所述铰接板604和铰链分别铰接于刚性舱体103的上端板104下侧和下端板102下侧，所述上端板104和下端板102下侧均沿圆周方向设有锁紧槽，如图4～5所示，所述气闸舱门6上沿着圆周方向均布有多个可同步伸缩的锁紧块605，当所述锁紧块605伸出插入所述锁紧槽时，所述气闸舱门6即锁定。
如图4～5所示，所述气闸舱门6包括舱门壳体、操作手柄603、中间齿轮611、行星齿轮610、齿圈609、连杆608和锁紧块605，本实施例中，所述舱门壳体由舱门上端盖607和舱门下端盖606扣合而成，在舱门壳体上下两侧均设有操作手柄603，且在舱门壳体上下两侧均设有操作提示牌601，所述中间齿轮611、行星齿轮610、齿圈609和连杆608均设置于所述舱门壳体内，且所述中间齿轮611和多个行星齿轮610设置于所述齿圈609内，所述多个行星齿轮610沿圆周方向均布且内侧与所述中间齿轮611啮合、外侧与所述齿圈609啮合，所述中间齿轮611的齿轮轴612两端分别伸出至舱门壳体外并分别与舱门壳体上下侧的操作手柄603相连，所述齿圈609外侧沿着圆周方向均布有多个连杆608，在所述舱门壳体圆周边缘均布有多个滑动通孔，且每个滑动通孔内均设有一个锁紧块605，所述锁紧块605与所述连杆608一一对应相连并通过所述连杆608驱动伸缩移动。
如图3所示，在所述刚性舱体103的上端板104与上侧的气闸舱门6之间设有两道密封圈101，在所述刚性舱体103的下端板102与下侧的气闸舱门6之间也设有两道密封圈101。
如图6和图8所示，所述端层板组件2包括端层底板201、端层固定隔板203和端层移动隔板202，其中端层底板201固装于芯柱框架7上，端层固定隔板203呈直角形状并通过隔板固定件204固装于所述端层底板201上，且在所述端层固定隔板203两端均设有端层移动隔板202，本实施例中，共包括四个端层固定隔板203并形成十字形状的活动区域，端层移动隔板202伸长即可延伸活动区域范围，所述端层移动隔板202通过滑轨滑块结构与所述端层固定隔板203滑动连接。
如图7所示，所述中间层板组件包括中间层底板302、中间层立板301和环形套304，中间层底板302固装于芯柱框架7上，中间层立板301和环形套304固装于所述中间层底板302上，且多个中间层立板301沿着圆周方向均布于环形套304内，从而将环形套304内等分成多个活动区域，本实施例中，所述环形套304为环形水套，所述中间层立板301通过立板固定件303固装于所述中间层底板302上。
如图10所示，在所述芯柱框架7上设有多个底板支撑环704，所述上端层 的端层底板201和中间层3的中间层底板302分别固装于不同的底板支撑环704上，所述下端层的端层底板201固装于所述芯柱框架7的底端。
如图2和图6～7所示，所述空间扩展组件4包括多个上扩展板404和多个下扩展板405，且所述多个上扩展板404展开后形成一个可供活动的上平台，所述多个下扩展板405展开后形成一个可供活动的下平台，在相邻两个上扩展板404之间均设有上扩展支撑杆4041，且所述上扩展板404通过所述上扩展支撑杆4041摆动展开或收起，在相邻两个下扩展板405之间均设有下扩展支撑杆4051，且所述下扩展板405通过所述下扩展支撑杆4051摆动展开或收起。
如图10所示，所述上扩展支撑杆4041均铰接于支撑上端层端层底板201的底板支撑环704上，且在该底板支撑环704上侧设有上驱动环4043，所述上扩展支撑杆4041分别通过上驱动连杆4042与所述上驱动环4043相连。所述下扩展支撑杆4051均铰接于支撑中间层底板302的底板支撑环704上，且在该底板支撑环704下侧设有下驱动环4053，所述下扩展支撑杆4051分别通过下驱动连杆4052与所述下驱动环4053相连。所述上驱动环4043和下驱动环4053均套设于所述芯柱框架7外侧，且在所述芯柱框架7上设有驱动展开机构702驱动所述上驱动环4043和下驱动环4053反向移动，从而使所述上扩展板404和下扩展板405展开或收起，另外在所述芯柱框架7上设有导向机构703引导上驱动环4043和下驱动环4053升降移动。本实施例中，如图10所示，在所述芯柱框架7前后侧均设有一个驱动展开机构702和一个导向机构703，所述芯柱框架7包括多个框架侧梁701，各个驱动展开机构702和各个导向机构703分别安装在不同的框架侧梁701上。
如图11所示，所述驱动展开机构702包括两组对称设置的驱动组件，且所述上驱动环4043和下驱动环4053通过不同驱动组件驱动移动。
如图11所示，所述驱动组件包括驱动电机7021、丝杠7025、丝母7023和连接块7024，所述驱动电机7021固装在框架侧梁701上，所述丝杠7025两端分别通过轴承座7022支承安装于框架侧梁701上，且所述丝杠7025通过所述驱动电机7021驱动旋转，在所述丝杠7025上套装有丝母7023，所述丝母7023上固设有连接块7024与上驱动环4043或下驱动环4053固连。
如图12所示，所述导向机构703包括两组导向组件，且所述上驱动环4043和下驱动环4053通过不同导向组件导向。
如图12所示，所述导向组件包括导向支架7031、导向杆7032和导向块7033，所述导向杆7032两端分别通过导向支架7031支承安装于框架侧梁701上，所述导向块7033套装于导向杆7032上，且所述导向块7033与上驱动环4043或下驱动环4053固连。
如图1～2所示，所述空间扩展组件4还包括设置于柔性外壳5内侧的上充气环401和下充气环402，在所述上充气环401和下充气环402之间设有连接柱403，所述柔性外壳5充气展开时，所述上充气环401、下充气环402和连接柱403内部均充气使刚度变大，进而增加柔性外壳5刚度，所述上扩展板404展开后边缘与所述上充气环401相抵，所述下扩展板405展开后边缘与所述下充气环402相抵，且上扩展板404和下扩展板405之间通过连接柱403支撑限位。
本发明的工作原理为：
如图13所示，柔性外壳5在发射之前可以沿中央舱段芯柱进行折叠，经运载火箭运至预定工作轨道之后，柔性外壳5内部开始充气并在内部气压的作用下实现柔性外壳5的展开，与此同时上充气环401和下充气环402内部也充气，并随着压力升高刚度变大，从而增加柔性外壳5的刚度。
然后驱动展开机构702中的驱动电机7021启动，通过丝杠丝母机构驱动上驱动环4043和下驱动环4053移动，从而使上扩展板404和下扩展板405完全展开形成可供活动的上平台和下平台，另外所述上端层和下端层内的端层移动隔板202也可伸出，从而延伸层内活动区域。
所述柔性外壳5中的原子氧防护层501和热防护层502在舱段在轨运行过程中可分别起到原子氧防护和热防护作用，所述外防护层503、外泡沫层504、中间防护层505、内泡沫层506、内防护层507可起到微小陨石及轨道碎片防护作用，所述主气密层511起到气密性作用，备气密层509为在主气密层511无法保证气密性时确保舱内气不会泄露，所述结构限制层508为柔性外壳5中最主要的承力层，用于承受舱内气体压力，所述内衬层512的主要作用是防止主气密层511被舱内锐器刺破。
所述气闸舱1的主要作用为在航天员进出舱段的过程中提供一个压力过渡区，以出舱为例，航天员首先在舱内将气闸舱1内压力升至与舱内压力一致，接着开启下端的气闸舱门6，航天员进入气闸舱1内，然后关闭下端的气闸舱门6，调整气闸舱1压力下降至与待进入舱内气体压力一致，开启上端的气闸舱门6，航天员进入别的舱室，并关闭上端的气闸舱门6，最后气闸舱内气体压力复原。返回时操作顺序与出舱相反。

Claims (10)

  1. 一种空间充气展开舱段，其特征在于：包括气闸舱(1)、舱段芯柱和柔性外壳(5)，所述舱段芯柱设置于柔性外壳(5)中，气闸舱(1)设置于所述舱段芯柱上端且设置于柔性外壳(5)外侧，所述柔性外壳(5)充气展开；所述舱段芯柱包括一个芯柱框架(7)，且在所述芯柱框架(7)上由上到下依次设有上端层、中间层(3)和下端层，所述上端层和下端层内均设有端层板组件(2)，且所述上端层和下端层通过所述端层板组件(2)分成多个活动区域，所述中间层(3)内设有中间层板组件，且所述中间层(3)通过所述中间层板组件分成多个活动区域，在所述柔性外壳(5)内，在所述舱段芯柱外侧设有空间扩展组件(4)，所述空间扩展组件(4)设有多个扩展板，且相邻扩展板之间均设有扩展支撑杆，在所述芯柱框架(7)内设有驱动展开机构(702)，扩展支撑杆通过所述驱动展开机构(702)驱动摆动，扩展板通过所述扩展支撑杆摆动驱动展开。
  2. 根据权利要求1所述的空间充气展开舱段，其特征在于：所述气闸舱(1)包括刚性舱体(103)和气闸舱门(6)，在所述刚性舱体(103)上下两端分别设有上端板(104)和下端板(102)，且所述上端板(104)下侧和下端板(102)下侧均铰接有一个气闸舱门(6)，所述上端板(104)和下端板(102)下侧均设有锁紧槽，所述气闸舱门(6)上设有可伸缩的锁紧块(605)，且所述气闸舱门(6)在所述锁紧块(605)伸出插入对应锁紧槽锁定。
  3. 根据权利要求2所述的空间充气展开舱段，其特征在于：所述气闸舱门(6)包括舱门壳体、操作手柄(603)、中间齿轮(611)、行星齿轮(610)、齿圈(609)、连杆(608)和锁紧块(605)，所述中间齿轮(611)、行星齿轮(610)、齿圈(609)和连杆(608)均设置于所述舱门壳体内，且所述中间齿轮(611)和行星齿轮(610)设置于所述齿圈(609)内，多个行星齿轮(610)沿圆周方向均布且内侧与所述中间齿轮(611)啮合、外侧与所述齿圈(609)啮合，所述中间齿轮(611)的齿轮轴(612)两端分别伸出至舱门壳体外并分别与舱门壳体两侧的操作手柄(603)相连，所述齿圈(609)外侧均布有多个连杆(608)，在所述舱门壳体圆周边缘均布有多个滑动通孔，且每个滑动通孔内均设有一个锁紧块(605)，所述锁紧块(605)与所述连杆(608)一一对应相连。
  4. 根据权利要求1所述的空间充气展开舱段，其特征在于：所述端层板组件(2)包括端层底板(201)、端层固定隔板(203)和端层移动隔板(202)，其中端层底板(201)固装于芯柱框架(7)上，端层固定隔板(203)呈直角形状并固装于所述端层底板(201)上，所述端层固定隔板(203)两端均设有端层移动隔板(202)。
  5. 根据权利要求1所述的空间充气展开舱段，其特征在于：所述中间层板组件包括中间层底板(302)、中间层立板(301)和环形套(304)，中间层底板(302)固装于芯柱框架(7)上，中间层立板(301)和环形套(304)固装于所述中间层底板(302)上，且多个中间层立板(301)沿着圆周方向均布于环形套(304)内。
  6. 根据权利要求1所述的空间充气展开舱段，其特征在于：所述空间扩展组件(4)包括多个上扩展板(404)和多个下扩展板(405)，且相邻两个上扩展板(404)之间设有上扩展支撑杆(4041)，在相邻两个下扩展板(405)之间设有下扩展支撑杆(4051)，所述芯柱框架(7)上设有多个底板支撑环(704)，且所述上端层和中间层(3)固装于不同底板支撑环(704)上，所述上扩展支撑杆(4041)铰接于支撑上端层的底板支撑环(704)上，且在该底板支撑环(704)上侧设有上驱动环(4043)，所述上扩展支撑杆(4041)通过上驱动连杆(4042)与所述上驱动环(4043)相连，所述下扩展支撑杆(4051)铰接于支撑中间层(3)的底板支撑环(704)上，且在该底板支撑环(704)下侧设有下驱动环(4053)，所述下扩展支撑杆(4051)通过下驱动连杆(4052)与所述下驱动环(4053)相连，所述上驱动环(4043)和下驱动环(4053)通过所述驱动展开机构(702)驱动反向移动。
  7. 根据权利要求6所述的空间充气展开舱段，其特征在于：所述驱动展开机构(702)包括两组结构相同且对称设置的驱动组件，所述上驱动环(4043)和下驱动环(4053)分别通过不同驱动组件驱动移动，所述驱动组件包括驱动电机(7021)、丝杠(7025)、丝母(7023)和连接块(7024)，所述丝杠(7025)通过所述驱动电机(7021)驱动旋转，在所述丝杠(7025)上套装有丝母(7023)，所述丝母(7023)上固设有连接块(7024)与上驱动环(4043)或下驱动环(4053)固连。
  8. 根据权利要求6所述的空间充气展开舱段，其特征在于：所述芯柱框架(7)上设有导向机构(703)，所述导向机构(703)包括两组结构相同的导向组件，所述导向组件包括导向杆(7032)和导向块(7033)，所述导向块(7033)套装于导向杆(7032)上，且所述上驱动环(4043)和下驱动环(4053)分别与不同导向组件中的导向块(7033)相连。
  9. 根据权利要求6所述的空间充气展开舱段，其特征在于：所述空间扩展组件(4)还包括设置于柔性外壳(5)内侧的上充气环(401)和下充气环(402)，在所述上充气环(401)和下充气环(402)之间设有连接柱(403)，所述柔性外壳(5)充气展开时，所述上充气环(401)、下充气环(402)和连接柱(403)内部均充气，所述上扩展板(404)完全展开后边缘与所述上充气环(401)相 抵，所述下扩展板(405)完全展开后边缘与所述下充气环(402)相抵。
  10. 根据权利要求1所述的空间充气展开舱段，其特征在于：所述柔性外壳(5)由外到内依次设有原子氧防护层(501)、热防护层(502)、外防护层(503)、外泡沫层(504)、中间防护层(505)、内泡沫层(506)、内防护层(507)、结构限制层(508)、备气密层(509)、间隔层(510)、主气密层(511)和内衬层(512)。
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