On-orbit inflatable deployment and stiffened protection system against space fragment and micrometeoroid

An inflatable deployment and protection system technology, which is applied in the fields of aerospace vehicle anti-meteorite devices, aerospace safety/emergency devices, etc., can solve the problems of difficult to achieve the folding efficiency of protective screens, large folding volume of rigid protective screens, and difficulty in building multi-layer protection. , to achieve the effects of stable inflation and deployment process, good deployment reliability and good protection effect

Inactive Publication Date: 2009-01-28
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to solve the problems of high cost, difficulty, or even difficulty in realizing large-sized protective screens that are space-assembled by one-time launch or multiple launches, and the low folding efficiency and low deployment reliability of protective screens that are mechanically unfolded. , The volume is small after unfolding,

Method used

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  • On-orbit inflatable deployment and stiffened protection system against space fragment and micrometeoroid
  • On-orbit inflatable deployment and stiffened protection system against space fragment and micrometeoroid
  • On-orbit inflatable deployment and stiffened protection system against space fragment and micrometeoroid

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specific Embodiment approach 1

[0007] Specific embodiment one: in conjunction with Fig. 1, Fig. 6, Figure 8 with Figure 9 Describe this embodiment, the protective system of this embodiment includes two to twenty layers of rigidizable inflatable unfolding planar frame 1, two to twenty protective screens 2 to be rigidified, and multiple rigidizable inflatable and deployable supporting risers. 3. Two first inflation pipes 7, two second inflation pipes 8, four vertical inflation pipes 9, four horizontal inflation control valves 10 and four control valves 11; The inflatable and inflatable unfolding planar frame 1 is vertically facing and arranged in parallel, and the four corners of the adjacent two layers of inflatable inflatable and inflatable unfolding planar frame 1 are connected by four rigid inflatable and inflatable unfolding support riser assemblies 3 to form a sealed inflatable Expand the support frame, each layer of the stiffened inflatable unfolded plane frame 1 is provided with a protective screen...

specific Embodiment approach 2

[0009] Specific embodiment two: in conjunction with Fig. 1, Figure 13 to Figure 16To illustrate this embodiment, each layer of stiffenable inflatable and unfoldable planar frame 1 of this embodiment consists of two stiffenable inflatable expandable long support tubes 14, two stiffenable inflatable expandable short support tubes 16, four connectors 18, Composed of eight end caps 19, eight clamps 20 and eight sealing rubber rings 21; the two stiffenable inflatable expandable long support tubes 14 and the two rigidizable inflatable expandable short support tubes 16 are respectively arranged opposite and constitute Rectangular frame, each corner of the rectangular frame is respectively provided with a connector 18, the two ends of each stiffenable inflatable expandable long support tube 14 and each stiffenable inflatable expandable short support tube 16 An end cover 19 is respectively housed in the two ends of the inner wall, and the end cover 19 is airtightly connected with the ...

specific Embodiment approach 3

[0010] Specific Embodiment Three: This embodiment is described with reference to FIG. 6 . The number of layers of the rigidizable inflatable planar frame 1 of this embodiment is two layers. Other components and connections are the same as those in the second embodiment.

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Abstract

The invention relates to a protection system that resists space junk and micrometeoroid, rigidifies and space inflates in orbit, which aims at solving the problems of high cost and sheer difficulty for big-size protection screen space-assembly for single or multiple launching, the problems of low folding efficiency, low reliability, small unfolded size in mechanical protection screen unfolding, and the problems of large folding size, inflexible folding, large launching size and small unfolded size of rigid protection screens. Two adjacent layers of rigid space inflating plane frame are connected by the rigid space inflating support vertical tube assembly; protection screens waiting for rigidifying are arranged in the rigid space inflating plane frame; a first and a second inflating pipe are arranged in the rigid space inflating plane frame; vertical inflating pipes are arranged in the rigid space inflating support vertical tube assembly. The protection system has the advantages of simple structure, low cost, high reliability, light weight, high folding efficiency, small folding size, flexible folding and small launching size, which can applied to aircrafts such as satellites, spacecrafts and space stations.

Description

technical field [0001] The invention relates to a protection system against space debris and micrometeoroid. Background technique [0002] There are a large number of high-speed moving (speed ≥ 8km / s) micrometeoroids and space debris in the orbital space of spacecraft such as satellites. The impact of these micrometeoroids and space debris will cause damage, destruction or even failure of the aircraft. It poses a serious threat to the safety of astronauts. For space debris larger than 1 cm, early warning can be given through on-orbit debris monitors, and active protective measures such as avoidance can be taken; for space debris smaller than 1 cm, only passive protective measures can be used. At present, the protection schemes of spacecraft mainly include two kinds of protective screen mechanisms: fixed type and mechanical type. Spacecraft often require a larger-sized protective area and a larger-sized protective screen. Due to the limitation of launch volume and cost, it...

Claims

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Application Information

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IPC IPC(8): B64G1/52B64G1/56
Inventor 苗常青谭惠丰曹昱谢志民杜星文
Owner HARBIN INST OF TECH
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