CN101570250A - Inflatable deploying solar wing capable of replacing panel in orbit - Google Patents
Inflatable deploying solar wing capable of replacing panel in orbit Download PDFInfo
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- CN101570250A CN101570250A CNA2009100722952A CN200910072295A CN101570250A CN 101570250 A CN101570250 A CN 101570250A CN A2009100722952 A CNA2009100722952 A CN A2009100722952A CN 200910072295 A CN200910072295 A CN 200910072295A CN 101570250 A CN101570250 A CN 101570250A
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Abstract
The invention relates to an inflatable deploying solar wing capable of replacing a panel in orbit, which relates to an inflatable deploying solar wing. The inflatable deploying solar panel solves the problems of material waste, poor aircraft stability and no guarantee for cosmonaut's life security existing in the process that the cosmonaut carries out whole replacement when the panel of the solar wing is damaged or ages in orbit. Two supporting tubes are fixedly connected with a first transverse plate and a second transverse plate through flanges; a cell baseplate is fixedly provided with cell slices, air filling pipes are communicated with the supporting tubes; wires are connected with the supporting tubes; each supporting tube is sleeved by an open slip ring; the cell baseplate is fixedly connected with the open slip ring; the second transverse plate is fixedly provided with two suspension links; the two flanges fixedly connected with the first transverse plate are respectively fixedly provided with a reel; and one end of a pull rope is wound on the reel, and the other end passes through the pull rope through holes in the suspension link and the open slip rings. The cell baseplate and the cell slices thereon can be conveniently replaced through the pull ropes, thereby ensuring cosmonaut's life security, reducing material waste and obtaining good spacecraft stability.
Description
Technical field
The present invention relates to a kind of inflatable deploying solar wing, belong to the space technology field.
Background technology
The sun wing is the main form of power of space vehicle such as satellite, is extensive use of on space vehicles such as satellite, manned spacecraft, space station.Space environment is extremely complicated, and high vacuum, intensive ultraviolet, atom oxygen, " cold black " and a large amount of micrometeors and the space debris that exist, the cell panel that makes the sun wing occur damaging or aging problem in orbit the time, and this just need change it.Traditional way is by the cosmonaut sun wing that the cell panel that damages or worn out is arranged to be carried out integral replacing, and damage in some cases is sub-fraction, integral replacing can cause the waste of resource, size was very big after the sun span was opened in addition, cosmonaut's far distance of need walking in space environment could be changed it, and cosmonaut's life security is threatened.The complexity of space environment is unfavorable for the enforcement of this work, and it is not only threatening cosmonaut's life security, and also affects the stability of space vehicle in the process of changing.As can be seen from the above analysis, the cell panel of designing a kind of sun wing that is easy to change is extremely important, and it not only can protect cosmonaut's personal safety, economizes on resources, and also helps the stable of space vehicle.
Summary of the invention
The purpose of this invention is to provide a kind of inflatable deploying solar wing that can change cell panel at rail, when occurring damage or catabiosis in orbit to solve sun wing cell panel, by the cosmonaut to damaging or the sun wing of aging cell panel carries out integral replacing, not only the life security to the cosmonaut threatens, and goes back waste material simultaneously, influences the problem of space vehicle stability.
The present invention solves the problems of the technologies described above the technical scheme of taking to be: the sun wing of the present invention comprises that polylith cell substrates, a plurality of battery sheet, two support tubes, first transverse slat, second transverse slat, two control cock, two leads, four clips, two gas ductings and four connect dish; Described two support tubes be arranged in parallel, described first transverse slat and second transverse slat are separately positioned on the two ends of two support tubes, the two ends of every support tube are inserted into respectively in the corresponding centre hole that connects dish, support tube and the corresponding centre hole flush fit that connects dish, every support tube is by connecing the two ends affixed formation integral frame-type structure of the dish and first transverse slat and second transverse slat, the two ends of every support tube are fixed with a clip, be provided with the polylith cell substrates between two support tubes, be fixed with a plurality of battery sheets of arranging in length and breadth on the upper surface of every cell substrates, the two ends of every support tube are closed end, one end of described two gas ductings passes first transverse slat respectively and is communicated with two support tubes, a control cock is housed on the every gas ducting, a lead is housed in the every support tube, lead is connected with the electric heating layer of support tube, support tube is passed at the two ends of lead and first transverse slat is exposed, but support tube is the steel charge expansion support tube; The described sun wing also comprises a plurality of opening slip rings, two draw rings, two stay cords and two kinking runners; Be set with a plurality of opening slip rings on the every support tube, opening slip ring and support tube bearing fit, the two ends of every cell substrates are contained in respectively in the opening of at least one opening slip ring, described opening slip ring and cell substrates are affixed, the opening slip ring is provided with at least one stay cord and passes the hole, two ends on the inboard face of described second transverse slat respectively are fixed with a draw ring, connect with affixed two of first transverse slat and respectively to be fixed with a kinking runner on the dish, one end of stay cord is wrapped on the kinking runner, and the other end of stay cord passes draw ring and alternately passes stay cord on the opening slip ring successively from top to bottom and pass the hole and reach the stay cord that passes from bottom to top on the opening slip ring and pass the hole; Pass from bottom to top alternately successively perhaps that stay cord on the opening slip ring passes the hole and the stay cord that passes from top to bottom on the opening slip ring passes the hole.
The invention has the beneficial effects as follows: but one, the present invention since the support tube that adopts steel charge expansion as agent structure can be easily suit opening slip ring thereon.Two, the present invention since on support tube suit the opening slip ring, when the cell substrates of the sun wing or battery sheet damage or wear out, effect by stay cord, can be easily to cell substrates and on the battery sheet change, guaranteed cosmonaut's life security, also reduced the waste of material simultaneously, guaranteed that space vehicle has stability preferably.Three, the present invention is owing to be equipped with control cock on gas ducting, and the may command gas ducting charges into support tube gas inside flow and flow velocity, makes the support tube expansion process comparatively stable.
Description of drawings
Fig. 1 is integral structure scheme drawing of the present invention (two ends of every cell substrates 1 is affixed with an opening slip ring 11 respectively); Fig. 2 is integral structure scheme drawing of the present invention (two ends of every cell substrates 1 is affixed with two opening slip rings 11 respectively); Fig. 3 is the A portion enlarged drawing of Fig. 2; Fig. 4 is integral structure scheme drawing of the present invention (two ends of every cell substrates 1 is affixed with four opening slip rings 11 respectively).
The specific embodiment
The specific embodiment one: in conjunction with Fig. 1～Fig. 4 present embodiment is described, the described sun wing of present embodiment comprises that polylith cell substrates 1, a plurality of battery sheet 2, two support tubes 3, first transverse slat 4, second transverse slat 5, two control cock 6, two leads 7, four clips 8, two gas ductings 9 and four connect dish 10; Described two support tubes 3 be arranged in parallel, described first transverse slat 4 and second transverse slat 5 are separately positioned on the two ends of two support tubes 3, the two ends of every support tube 3 are inserted into corresponding connecing in dish 10 the centre hole respectively, support tube 3 and the corresponding centre hole flush fit that connects dish 10, every support tube 3 is by connecing the two ends affixed formation integral frame-type structure of dish 10 and first transverse slat 4 and second transverse slat 5, the two ends of every support tube 3 are fixed with a clip 8, be provided with polylith cell substrates 1 between two support tubes 3, be fixed with a plurality of battery sheets of arranging in length and breadth 2 on the upper surface of every cell substrates 1, the two ends of every support tube 3 are closed end, one end of described two gas ductings 9 passes first transverse slat 4 respectively and is communicated with two support tubes 3, a control cock 6 is housed on the every gas ducting 9, gas flow rate during with the control inflation, a lead 7 is housed in the every support tube 3, lead 7 is connected with the electric heating layer of support tube 3, support tube 3 is passed at the two ends of lead 7 and first transverse slat 4 is exposed, but support tube 3 is the steel charge expansion support tube, but the material of steel charge expansion support tube and structure and the patent No. are ZL 200510010368.7, the applying date is on 09 26th, 2005, the patent of invention name be called " plane framework supporting structure capable of steel charge expansion " but in the support tube of steel charge expansion identical, the described sun wing also comprises a plurality of opening slip rings 11, two draw rings 12, two stay cords 13 and two kinking runners 14; Be set with a plurality of opening slip rings 11 on the every support tube 3, opening slip ring 11 and support tube 3 bearing fits, the two ends of every cell substrates 1 are contained in respectively in the opening of at least one opening slip ring 11, described opening slip ring 11 is affixed by rivet 15 with cell substrates 1, opening slip ring 11 is provided with at least one stay cord and passes hole 11-1, two ends on the inboard face of described second transverse slat 5 respectively are fixed with a draw ring 12, connect on the dish 10 with affixed two of first transverse slat 4 and respectively to be fixed with a kinking runner 14, one end of stay cord 13 is wrapped on the kinking runner 14, and the other end of stay cord 13 passes draw ring 12 and alternately passes stay cord on the opening slip ring 11 successively from top to bottom and pass hole 11-1 and reach the stay cord that passes from bottom to top on the opening slip ring 11 and pass hole 11-1; Pass from bottom to top alternately successively perhaps that stay cord on the opening slip ring 11 passes hole 11-1 and the stay cord that passes from top to bottom on the opening slip ring 11 passes hole 11-1.
The specific embodiment two: in conjunction with Fig. 1～Fig. 3 present embodiment is described, the described opening slip ring 11 of present embodiment is provided with two stay cords and passes hole 11-1.Be fit to the bigger situation of opening slip ring 11 width dimensions, be convenient to spur opening slip ring 11.Other is identical with the specific embodiment one.
The specific embodiment three: in conjunction with Fig. 1 present embodiment is described, the two ends of the every cell substrates 1 of present embodiment are contained in respectively in the opening of an opening slip ring 11, are fit to be convenient to install under the bigger situation of opening slip ring 11 width dimensions.Other is identical with the specific embodiment one or two.
The specific embodiment four: in conjunction with Fig. 2 present embodiment is described, the two ends of the every cell substrates 1 of present embodiment are contained in respectively in the opening of two opening slip rings 11, are fit under the not too big situation of opening slip ring 11 width dimensions.Other is identical with the specific embodiment one or two.
The specific embodiment five: in conjunction with Fig. 4 present embodiment is described, the two ends of the every cell substrates 1 of present embodiment are contained in respectively in the opening of four opening slip rings 11, are fit to can alleviate the overall weight of the sun wing under the less situation of opening slip ring 11 width dimensions.Other is identical with the specific embodiment one or two.
Principle of work: the stay cord that stay cord 13 passes on the opening slip ring 11 passes hole 11-1, can spur on support tube 3 cell substrates 1.When the battery sheet 2 on a certain cell substrates 1 is damaged or is aging, the cosmonaut can unload the control cock 6 that is enclosed within on the gas ducting 9 earlier with hand, unloading first transverse slat 4 with hand and coiling 10 with 4 affixed the connecing of first transverse slat, with the hands hold stay cord 13 pulling opening slip rings 11 on support tube 3, slides (kinking runner 14 rotation unwrapping wire) then, cell substrates 1 piecemeal winning over, again cell substrates 1 is taken off from support tube 3, till taking off the cell substrates 1 that is destroyed or worn out, change new cell substrates 1 again, the stay cord that stay cord 13 is enclosed within opening slip ring 11 passes in the 11-1 of hole, then both hands spur stay cord 13, cell substrates 1 is retracted original position, again stay cord 13 is being entangled on the draw ring 12, support tube 3 is affixed by connecing dish 10 and first transverse slat 4, lead 7 and gas ducting 9 pass first transverse slat 4 and are contained on the support tube 3, with clip 10 support tube 3 is fixed, control cock 6 is contained on the gas ducting 9 at last again and gets final product, this embodiment needs two cosmonaut to cooperate to finish.
Claims (5)
1, a kind of inflatable deploying solar wing that can change cell panel at rail, the described sun wing comprise that polylith cell substrates (1), a plurality of battery sheet (2), two support tubes (3), first transverse slat (4), second transverse slat (5), two control cock (6), two leads (7), four clips (8), two gas ductings (9) and four connect dish (10); Described two support tubes (3) be arranged in parallel, described first transverse slat (4) and second transverse slat (5) are separately positioned on the two ends of two support tubes (3), the two ends of every support tube (3) are inserted into respectively in the corresponding centre hole that connects dish (10), support tube (3) and the corresponding centre hole flush fit that connects dish (10), every support tube (3) is by connecing the two ends affixed formation integral frame-type structure of dish (10) and first transverse slat (4) and second transverse slat (5), the two ends of every support tube (3) are fixed with a clip (8), be provided with polylith cell substrates (1) between two support tubes (3), be fixed with a plurality of battery sheets of arranging in length and breadth (2) on the upper surface of every cell substrates (1), the two ends of every support tube (3) are closed end, one end of described two gas ductings (9) passes first transverse slat (4) respectively and is communicated with two support tubes (3), a control cock (6) is housed on the every gas ducting (9), a lead (7) is housed in the every support tube (3), lead (7) is connected with the electric heating layer of support tube (3), support tube (3) is passed at the two ends of lead (7) and first transverse slat (4) is exposed, support tube (3) but be the steel charge expansion support tube; It is characterized in that: the described sun wing also comprises a plurality of opening slip rings (11), two draw rings (12), two stay cords (13) and two kinking runners (14); Be set with a plurality of opening slip rings (11) on the every support tube (3), opening slip ring (11) and support tube (3) bearing fit, the two ends of every cell substrates (1) are contained in respectively in the opening of at least one opening slip ring (11), described opening slip ring (11) is affixed with cell substrates (1), opening slip ring (11) is provided with at least one stay cord and passes hole (11-1), two ends on the inboard face of described second transverse slat (5) respectively are fixed with a draw ring (12), connect with affixed two of first transverse slat (4) and respectively to be fixed with a kinking runner (14) on the dish (10), one end of stay cord (13) is wrapped on the kinking runner (14), and the other end of stay cord (13) passes draw ring (12) and alternately passes stay cord on the opening slip ring (11) successively from top to bottom and pass hole (11-1) and reach the stay cord that passes from bottom to top on the opening slip ring (11) and pass hole (11-1); Pass from bottom to top alternately successively perhaps that stay cord on the opening slip ring (11) passes hole (11-1) and the stay cord that passes from top to bottom on the opening slip ring (11) passes hole (11-1).
2, according to the described inflatable deploying solar wing that can change cell panel at rail of claim 1, it is characterized in that: described opening slip ring (11) is provided with two stay cords and passes hole (11-1).
3, according to claim 1 or the 2 described inflatable deploying solar wings that can change cell panel at rail, it is characterized in that: the two ends of every cell substrates (1) are contained in respectively in the opening of an opening slip ring (11).
4, according to claim 1 or the 2 described inflatable deploying solar wings that can change cell panel at rail, it is characterized in that: the two ends of every cell substrates (1) are contained in respectively in the opening of two opening slip rings (11).
5, according to claim 1 or the 2 described inflatable deploying solar wings that can change cell panel at rail, it is characterized in that: the two ends of every cell substrates (1) are contained in respectively in the opening of four opening slip rings (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100722952A CN101570250B (en) | 2009-06-15 | 2009-06-15 | Inflatable deploying solar wing capable of replacing panel in orbit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100722952A CN101570250B (en) | 2009-06-15 | 2009-06-15 | Inflatable deploying solar wing capable of replacing panel in orbit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101570250A true CN101570250A (en) | 2009-11-04 |
| CN101570250B CN101570250B (en) | 2011-12-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009100722952A Expired - Fee Related CN101570250B (en) | 2009-06-15 | 2009-06-15 | Inflatable deploying solar wing capable of replacing panel in orbit |
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| CN (1) | CN101570250B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101823566A (en) * | 2010-03-30 | 2010-09-08 | 哈尔滨工业大学 | Locking and unlocking device for solar array |
| CN101913434A (en) * | 2010-08-23 | 2010-12-15 | 哈尔滨工业大学 | Inflatable and expandable three-dimensional truss on-track maintainable solar panel |
| CN106564626A (en) * | 2016-10-14 | 2017-04-19 | 上海微小卫星工程中心 | Compacting and releasing mechanism for wing cell |
| CN112977892A (en) * | 2021-03-18 | 2021-06-18 | 航天科工空间工程发展有限公司 | Method for determining unfolding posture of inflatable solar wing in place on track |
| CN113675575A (en) * | 2021-08-25 | 2021-11-19 | 哈尔滨工业大学 | Z-shaped folding planar antenna supported by inflatable truss |
| CN114348300A (en) * | 2022-01-11 | 2022-04-15 | 沈阳航天新光集团有限公司 | Automatic retractable sun wing unfolding device |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3948468A (en) * | 1971-09-27 | 1976-04-06 | Rca Corporation | Replaceable solar array panels |
| DE19728844C2 (en) * | 1997-07-05 | 1999-04-15 | Daimler Benz Aerospace Ag | Gearbox for moving panels provided with solar cells on a spacecraft |
| CN100362693C (en) * | 2005-09-26 | 2008-01-16 | 哈尔滨工业大学 | Plane framework supporting structure capable of steel charge expansion |
| CN101383568B (en) * | 2008-10-24 | 2011-01-26 | 哈尔滨工业大学 | Synchronous expansion mechanism for foldable inflating expansion solar cell paddles |
-
2009
- 2009-06-15 CN CN2009100722952A patent/CN101570250B/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101823566A (en) * | 2010-03-30 | 2010-09-08 | 哈尔滨工业大学 | Locking and unlocking device for solar array |
| CN101913434A (en) * | 2010-08-23 | 2010-12-15 | 哈尔滨工业大学 | Inflatable and expandable three-dimensional truss on-track maintainable solar panel |
| CN101913434B (en) * | 2010-08-23 | 2012-11-21 | 哈尔滨工业大学 | Inflatable and expandable three-dimensional truss on-track maintainable solar panel |
| CN106564626A (en) * | 2016-10-14 | 2017-04-19 | 上海微小卫星工程中心 | Compacting and releasing mechanism for wing cell |
| CN106564626B (en) * | 2016-10-14 | 2019-09-17 | 上海微小卫星工程中心 | The compression relieving mechanism of wing group |
| CN112977892A (en) * | 2021-03-18 | 2021-06-18 | 航天科工空间工程发展有限公司 | Method for determining unfolding posture of inflatable solar wing in place on track |
| CN112977892B (en) * | 2021-03-18 | 2022-09-23 | 航天科工空间工程发展有限公司 | Method for determining in-place unfolding posture of inflatable solar wing on orbit |
| CN113675575A (en) * | 2021-08-25 | 2021-11-19 | 哈尔滨工业大学 | Z-shaped folding planar antenna supported by inflatable truss |
| CN113675575B (en) * | 2021-08-25 | 2023-09-05 | 哈尔滨工业大学 | Z-shaped folding planar antenna supported by inflatable truss |
| CN114348300A (en) * | 2022-01-11 | 2022-04-15 | 沈阳航天新光集团有限公司 | Automatic retractable sun wing unfolding device |
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| Publication number | Publication date |
|---|---|
| CN101570250B (en) | 2011-12-21 |
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Granted publication date: 20111221 Termination date: 20130615 |