CN103786903A - Solar sail for spacecraft - Google Patents
Solar sail for spacecraft Download PDFInfo
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- CN103786903A CN103786903A CN201210418924.4A CN201210418924A CN103786903A CN 103786903 A CN103786903 A CN 103786903A CN 201210418924 A CN201210418924 A CN 201210418924A CN 103786903 A CN103786903 A CN 103786903A
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- solar sail
- spacecraft
- light reflecting
- annular inflatable
- inflatable capsule
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Abstract
Disclosed is a solar sail for a spacecraft. The main structure of the solar sail comprises a circular inflatable air bag made of flexible materials, a reflective film made of flexible materials and a support rod made of rigid materials. The reflective film is fixed on the circular surface of the circular inflatable air bag, and a reflective layer is plated on the reflective film. The support rod penetrates the center of the reflective film and is connected with the circular inflatable air bag through drawing ropes. The reflective film in the folding state is expanded when the circular inflatable air bag is in the inflated state. The solar sail has the advantages that the ratio of the expansion area to the folded volume is large, the folded state volume is small, blasting off is facilitated, and the expansion area at the space stage is large, so that large thrust can be obtained.
Description
Technical field
The invention belongs to space industry, relate to the technology of utilizing optical pressure to obtain spacecraft thrust, relate more specifically to a kind of solar sail for spacecraft.
Background technology
The antagonistic force being produced by the photon being radiated on minute surface, as the power of airship navigation, is come true by imagination.
Nineteen twenty-four, you clearly propose " use and shine the thrust acquisition cosmic velocity that the sunlight on very thin huge catadioptre produces " the pioneer Constantine Tsiolkovsky of Russia's aerospace industry and its colleague's Freed Reed.
2005,4: 46 on the 22nd Beijing time, Russia with " wave " rocket launching " No. one, universe " take light as power (Cosmos-1) in the world first solar sail spacecraft in airship, receive confusion signal but launch surface control station after approximately 20 minutes, after this just lost and contacted with airship suddenly.
The airship of lift-off is made up of 8 triangle mylar windsurfings, and 4,000,000 dollars of costs are that U.S.'s Russian Academy Of Sciences and Moscow La Woqijin science are produced conjuncted cost several years temporal joint construction.
2010, JAXA claimed, confirms that the solar sail of " Ikaros " solar sail airship is successfully launched, and discloses the image that on airship, camera takes.This airship launches film in space as sail, using the slight pressure of sunshine as onward impulse.
Report is pointed out, after same Venus probe in " Ikaros " May " daybreak " number is launched together, rotates the cylindrical body of 1.6 meters, high 0.8 meter of diameter, slowly launches film sail under centrifugal action.
Japan scientific research personnel confirms that " Ikaros " launched smoothly the square sail of 14 meters of the length of sides in the space apart from approximately 7,700,000 kilometers of the earth.The camera being placed on the body of sail center takes this image and has passed the earth back.
The film sail of " Ikaros " by can free adjustment light the special material of reflection make, can be used for accelerating, slow down and change direction.In pact half a year before approaching Venus, will repeatedly carry out solar sail test, and in the future not develop deep space probe and accumulate experience.
Can find out from above-mentioned brief introduction, long-range spacecraft adopts solar sail to obtain thrust, is paid much attention to by international space flight circle.
The solar sail of above-mentioned oceangoing voyage spacecraft is all folding, to reduce shared volume in transmitting.Reflecting element used is all to use reflective thin plate.Unfolding mode adopts mechanical centrifugal power to throw (as fan is thrown away) away substantially, or with inflating post, reflective thin plate is strutted.
In known technology, adopt the shortcoming of the folding solar sail of template to be:
(1) large solar sail is made up of several platelets, and the platelet of each fritter is not folding, its yardstick is subject to rocket dimensional constraints, so its gross area can not do to obtain super large, for example, film is accomplished the hundreds of rice of diameter in principle, all possibilities of even thousands of rice, and template is not accomplished;
(2) quality of plate wants recuperation many than film, even if area is not very big, also many than film-type recuperation, its launch cost is also much higher.
Summary of the invention
The solar sail that the object of the present invention is to provide a kind of spacecraft to use.
For achieving the above object, solar sail keystone configuration provided by the invention is:
The annular inflatable capsule that one flexible material is made;
The light reflecting membrane that one flexible material is made is fixed in the circular face of this annular inflatable capsule, on this light reflecting membrane, is coated with reflector layer;
The strut bar that one rigid material is made, through the center of light reflecting membrane, and is connected with annular inflatable capsule by hauling rope;
Annular inflatable capsule, in the time of inflated condition, extends the light reflecting membrane of folded state.
The solar sail that described spacecraft is used, wherein, the flexible material of annular inflatable capsule is rubber or plastics or airtight fabric.
The solar sail that described spacecraft is used, wherein, the flexible material of light reflecting membrane is rubber, plastics or fabric.
The solar sail that described spacecraft is used, wherein, the rigid material of strut bar is magnesium aluminum alloy, corrosion-resistant steel, titanium alloy or carbon fiber.
The solar sail that described spacecraft is used, wherein, hauling rope is nylon, vegetable fibre, animal fibers or carbon fiber.
Because the feature of annular inflatable capsule of the present invention and light reflecting membrane material therefor is:
1, the flexible folding property to obtain;
2, solid and anti-ultraviolet radiation good;
3, lightweight.
Thus, advantage of the present invention is: obtain area after expansion with folding after the ratio maximum of volume.That is to say with known solar sail and compare, the ratio of reflective area of the present invention and volume after folding is large; In addition, reflective area of the present invention is large with the ratio of folding rear quality.These are for being very important with rocket launching.
Accompanying drawing explanation
Fig. 1 is the structural representation after solar sail expansion of the present invention.
Main mark nomenclature in accompanying drawing:
1 annular inflatable capsule; 2 light reflecting membranes; 4 strut bars; 3,5,6,7 hauling ropes.
The specific embodiment
The reflecting element that solar sail of the present invention adopts is film-type, and unfolding mode is to strut an annular air-pocket together with pasting with light reflecting membrane edge with pressure gas.This air bag, just as a bicycle tube, can be extended to an annulus after the gas of certain pressure intensity is poured in inside, irrelevant with state folded before inflation.After the expansion of annular inflatable capsule is come, the light reflecting membrane of pasting thereon is also extended to circular type light deflector by folded state.
Describe below in conjunction with Fig. 1.
Annular inflatable capsule 1 of the present invention is by flexible, and the material that air-tightness is good is made (as rubber, plastics or other airtight fabric), when unaerated, in folded state, is extended to a large circle when inflation.Light reflecting membrane 2 is also by flexibility, and mechanical strength good material is made (as rubber, plastics or fabric), on two faces of light reflecting membrane, is coated with efficient reflector layer with film plating process.Light reflecting membrane is pasted in the circular face on annular air-pocket.Hauling rope the 3,5,6, the 7th, makes (as nylon, vegetable fibre, animal fibers or carbon fiber) with lightweight, material that breaking limit pulling force is large, in order to connection, fixation balloon and strut bar.Strut bar 4 is made up of the rigid material (as magnesium aluminum alloy, corrosion-resistant steel or titanium alloy) of light weight, strut bar 4 is fixed together with light reflecting membrane 2 centres, also be connected with annular inflatable capsule 1 by hauling rope 3,5,6,7 simultaneously, annular inflatable capsule 1, light reflecting membrane 2 and strut bar 4 are connected as one.
When rocket launching, solar sail is in folded state, to reduce shared spatial volume, goes up to the air and arrives behind desired location.Remove the constraint of folding solar sail, then inflate in air bag by Air filling and discharging valves, make balloon expansion become a large circle, light reflecting membrane is extended to a large light deflector, sunshine is mapped on catadioptre, and the optical pressure on catadioptre conducts to airship with crossing strut bar, and airship has just obtained onward impulse.Just can change airship acquisition power direction by adjusting the length of each hauling rope.
As shown in Figure 1.Annular inflatable capsule 1 is by flexible, and the elastomeric material that air-tightness is good is made.4 centimetres of the internal diameters of annular inflatable capsule, the diameter of the circular area after expansion is 2 meters.Light reflecting membrane 2 is by flexibility, and the good plastic film material of mechanical strength is made, and light reflecting membrane is pasted in the circular face of annular air-pocket, and the two sides of light reflecting membrane is coated with efficient silver-colored reflector layer with film plating process.
Hauling rope 3,5,6,7 is made up of high-strength nylon; Strut bar 4 is made up of the rigid material plastic conduit of the lightweight of 5 centimetres of external diameters, 5 millimeters of thickness of pipe.
One end of strut bar 4 is bolted on a support (replacement airship).
The device of the present embodiment can well fold, and is extended to very soon the light deflector of 2 meters of diameters after inflation.10 kilograms of fold wts, volume 0.015 cubic meter.The optical pressure thrust producing is 0.66 dyne.
As shown in Figure 1.Wherein annular inflatable capsule 1 is made for plastic material, 6 centimetres of its internal diameters, and after expansion, the diameter of circular area is 4 meters.Light reflecting membrane 2 is to be made up of plastic film material, pastes in the circular face of annular inflatable capsule, on two faces of light reflecting membrane, is coated with efficient golden reflector layer with film plating process.Hauling rope 3 is made up of high-strength nylon; Strut bar 4 is made up of the rigid material magnesium aluminum alloy pipe of the lightweight of 8 centimetres of external diameters, 6 millimeters of thickness of pipe.The other the same as in Example 1.
The device of the present embodiment can well fold, and is extended to very soon the light deflector of 4 meters of diameters after inflation.23 kilograms of fold wts, volume 0.069 cubic meter.The optical pressure thrust producing is 2.64 dyne.
As shown in Figure 1.Annular inflatable capsule 1 is by flexible, and the plastic material that air-tightness is good is made, and the internal diameter of annular inflatable capsule 1 is 8 centimetres, and the diameter of the circular area after expansion is 8 meters.Light reflecting membrane 2 flexibilities, the good film of fabric material of mechanical strength are made.Hauling rope 3,5,6,7 is made up of high-strength nylon; Strut bar 4 is made up of the rigid material magnesium aluminum alloy pipe of the lightweight of 10 centimetres of external diameters, 8 millimeters of thickness of pipe.Other structure is with embodiment 1.
The device of the present embodiment can well fold, and is extended to very soon diameter and is the light deflector of 8 meters after inflation.85 kilograms of fold wts, volume 0.246 cubic meter.The optical pressure thrust producing is 5.28 dyne.
It is good pressure memory cell that the present invention adopts the air bag that flexible material is made.The annular inflatable capsule made from folding flexible material, is to fold in inside while being infrabar, thereby obtains less volume.And while filling anticyclonic pressure in inside, be just extended to a circular rings.In above-mentioned circular face, fix light reflecting membrane, then add necessary support to obtain long-range spacecraft solar sail.Therefore, solar sail of the present invention has the advantages that expanding area is large to the ratio of folding volume, is suitable for preparing the solar sail of super large (for example diameter km).Little being conducive to of folded state volume launches, and is conducive to greatly obtain large thrust at space stage expanding area.
Claims (5)
1. the solar sail that spacecraft is used, its keystone configuration is:
The annular inflatable capsule that one flexible material is made;
The reflective membrane that one flexible material is made is fixed in the circular face of this annular inflatable capsule, on this light reflecting membrane, is coated with reflector layer;
The strut bar that one rigid material is made, through the center of light reflecting membrane, and is connected with annular inflatable capsule by hauling rope;
Annular inflatable capsule, in the time of inflated condition, extends the light reflecting membrane of folded state.
2. the solar sail that spacecraft is used according to claim 1, wherein, the flexible material of annular inflatable capsule is rubber or plastics or fiber airtight fabric.
3. the solar sail that spacecraft is used according to claim 1, wherein, the flexible material of light reflecting membrane is rubber, plastics or fabric.
4. the solar sail that spacecraft is used according to claim 1, wherein, the rigid material of strut bar is magnesium aluminum alloy, corrosion-resistant steel, titanium alloy, rigid plastic or carbon fiber.
5. the solar sail that spacecraft is used according to claim 1, wherein, hauling rope is nylon, vegetable fibre, animal fibers or carbon fiber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210418924.4A CN103786903A (en) | 2012-10-26 | 2012-10-26 | Solar sail for spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210418924.4A CN103786903A (en) | 2012-10-26 | 2012-10-26 | Solar sail for spacecraft |
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| Publication Number | Publication Date |
|---|---|
| CN103786903A true CN103786903A (en) | 2014-05-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210418924.4A Pending CN103786903A (en) | 2012-10-26 | 2012-10-26 | Solar sail for spacecraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104002994A (en) * | 2014-05-16 | 2014-08-27 | 中国科学院空间科学与应用研究中心 | Sliding block executing mechanism used for attitude control over solar sail spacecraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN85200506U (en) * | 1985-04-01 | 1986-01-15 | 彭继源 | Solar range of gasbag type having concentrating element |
| DE19825785C2 (en) * | 1998-06-10 | 2000-04-27 | Deutsch Zentr Luft & Raumfahrt | Solar sailer with sail film and folding tubes |
| CN1341536A (en) * | 2000-09-07 | 2002-03-27 | 黄上立 | Spin-stabilized film reflector and its application in space |
| US20100276547A1 (en) * | 2009-05-04 | 2010-11-04 | Rubenchik Alexander M | Systems for solar power beaming from space |
| CN102437404A (en) * | 2011-08-18 | 2012-05-02 | 哈尔滨工业大学 | Integrated structure of rigidized inflatable deployable truss type planar antenna and solar array |
-
2012
- 2012-10-26 CN CN201210418924.4A patent/CN103786903A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN85200506U (en) * | 1985-04-01 | 1986-01-15 | 彭继源 | Solar range of gasbag type having concentrating element |
| DE19825785C2 (en) * | 1998-06-10 | 2000-04-27 | Deutsch Zentr Luft & Raumfahrt | Solar sailer with sail film and folding tubes |
| CN1341536A (en) * | 2000-09-07 | 2002-03-27 | 黄上立 | Spin-stabilized film reflector and its application in space |
| US20100276547A1 (en) * | 2009-05-04 | 2010-11-04 | Rubenchik Alexander M | Systems for solar power beaming from space |
| CN102437404A (en) * | 2011-08-18 | 2012-05-02 | 哈尔滨工业大学 | Integrated structure of rigidized inflatable deployable truss type planar antenna and solar array |
Non-Patent Citations (2)
| Title |
|---|
| 沈自才等: "IKAROS太阳帆的关键技术分析与启示", 《航天器工程》 * |
| 王伟志: "太阳帆技术综述", 《航天返回与遥感》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104002994A (en) * | 2014-05-16 | 2014-08-27 | 中国科学院空间科学与应用研究中心 | Sliding block executing mechanism used for attitude control over solar sail spacecraft |
| CN104002994B (en) * | 2014-05-16 | 2016-08-24 | 中国科学院空间科学与应用研究中心 | A kind of slide block executing agency for Solar sail spacecraft gesture stability |
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Application publication date: 20140514 |