CN103407581A - Integrated thin-film solar cell solar sail - Google Patents
Integrated thin-film solar cell solar sail Download PDFInfo
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- CN103407581A CN103407581A CN2013102937620A CN201310293762A CN103407581A CN 103407581 A CN103407581 A CN 103407581A CN 2013102937620 A CN2013102937620 A CN 2013102937620A CN 201310293762 A CN201310293762 A CN 201310293762A CN 103407581 A CN103407581 A CN 103407581A
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Abstract
The invention discloses an integrated thin-film solar cell solar sail and belongs to the field of satellite application. According to the integrated thin-film solar cell solar sail, thin-film solar cells, a passive control system and a satellite antenna gain system are integrated based on the integrated technology, the thin-film solar cells are fixed to the inner ring of the upper surface of a base of a solar sail body in a pasting mode, a light pressure stabilization coating is arranged on the outer ring of the upper surface of the solar sail body in a coating mode, and an electromagnetic signal gain coating is fixed to the lower surface of the solar sail body in a coating mode. According to the integrated thin-film solar cell solar sail, the thin-film solar cells, the light pressure stabilization coating and the electromagnetic signal gain coating are integrated onto the solar sail body to be integrally designed, and therefore the light receiving area of satellite solar cells can be enlarged; meanwhile, the integrated thin-film solar cell solar sail has high design value because the multiple subsystems can be integrated into one structure.
Description
Technical field
The invention belongs to the satellite application field, is a kind of multi-functional integrated thin-film solar cells solar sail, and it relates to satellite sun energy hull cell, relates to the satellite sun sail, relates to the satellite passive attitude stabilization and controls.
Prior art
Existing solar sail technology mainly concentrates on the application of propelling aspect, universe, and " universe-No. 1 " solar sail of the U.S. and Russian R & D Cooperation test spacecraft is used for track and the speed of change of flight device by sunshine, and controls its motion.This solar sail main body consists of the long triangle mylar of 8 14m.In case arrive at track, spacecraft will inflation sail mast, and solar sail is extended.After as sail body image petal, strutting, area reaches sq m more than 600, and sunlight is supplied with light sail power immediately, and " universe-No. 1 " height by original 800km is raised on higher track.
In the Ge Dade space research center of NASA (GSFC), jet propulsion laboratory (JPL), Langley Research Center (LaRC), all there are the solar sail project in Marshall space research center (MSFC) and NASA advanced concept research institute, wherein LaRC has adopted four supports, foursquare sail body design, JPL has carried out the design study of annular sail and rotary-type sail, the annular sail launches a huge sail body folded that is placed in small containers removed fold from compressive state by light and handy structure, the sail body structure is fixed in a large number on the ring consisted of very light pipe, to keep the tension force of sail film.
At present also by solar sail, do not realize that the optical pressure of satellite stablize the document of aspect and puts down in writing, only have a kind of of Cornell Univ USA's research to realize stable chip satellite by optical pressure, by three chip combinations of satellites, and utilize optical pressure to make satellite maintain attitude stabilization at the device of satellite edge installation high reflectance.
Electromagnetic horn is a kind of antenna mode more common in satellite, its technology maturation, but there is no the document record about the integrated design aspect of solar sail and electromagnetic horn.
Current microsatellite solar cell mainly adopts solar panel, by the solar panels development mechanism, solar panels is launched or directly solar panels are attached to satellite surface to power to satellite in space.At satellite sun sail design aspect, generally adopt the solar array of simple function, utilize space radiation to carry out the interplanetary and interstellar navigation of satellite, solar sail adopts the poly-ester fibres of thin metallic material or composite material to make, and the solar sail system is separated design with other subsystems.For the design that the satellite passive attitude stabilization is controlled, generally adopt in two ways, the one, body rotates and keeps stable spin stabilization mode around an axle that points to fixed-direction via satellite, another kind is exactly that while utilizing satellite to orbit the earth, on satellite, overhead the gravitation that is subject to of the different position of distance is different and moment that produce is stablized, and also is gravity gradient stabilization.
Due to solar panels weight and thickness all larger, and the weight of microsatellite and mounting space are all very limited, so the light-receiving area of solar panels suffers restraints, power supply capacity is poor.Be subjected to simultaneously the restriction of antenna and storage battery power supply ability, the ability to communicate of satellite is poor, need to realize by repeater satellite the signal transmission on microsatellite and ground.
Passive attitude stabilization for microsatellite is controlled, although there is the people to propose to adopt the space radiation optical pressure to control, owing to being subject to the less impact of satellite system raying area, can't carry out the design of optical pressure passive attitude stabilization control.And spin stabilization is controlled and the control of gravity gradient stabilization attitude, satellite is had to the requirement of direction and structure, make the design of satellite construction difficulty larger.
Satellite runs in the process to the miniaturization development subject matter has: 1. volume is little, what cause traditional satellite solar array is subjected to illuminating area little, the electric energy that satellite produces is also less, if take large development mechanism can have a strong impact on q&r again.2. on the satellite of having taked solar sail, solar sail is designed to independently system, and the design dimension that has not only increased whole satellite has also been brought the problems such as the complicated and quality of mechanism is larger.3., if the stable control of the satellite mode of taking the initiative, both increased the requirement of satellite to electric energy, also wasted the mounting space of satellite preciousness; If take passive attitude to control, so traditional spin stabilization mode and gravity gradient mode can be larger to direction and the Structural Design Requirement of satellite, on microsatellite, are difficult to realize.
Summary of the invention
The objective of the invention is: take full advantage of existing technology, by integrated design, the solar cell of satellite, solar sail and passive attitude stabilization mode are integrated to a unitized platform, will play a key effect to microsatellite future development.
Technical scheme of the present invention is: integrated thin-film solar cells solar sail, by integrated technique, thin-film solar cells, passive control system and satellite antenna gain system are carried out integratedly, described solar sail comprises solar film battery, optical pressure stable coatings and electromagnetic signal gain coating; Described solar sail sail body has upper and lower surfaces, described solar film battery is fixed on the inner ring of the upper surface of solar sail substrate by the mode of pasting, described optical pressure stable coatings is arranged on the outer ring of solar sail upper surface by the mode of smearing, described electromagnetism gain coating is fixed on the lower surface of solar sail by the mode of smearing.
Further technical scheme of the present invention is: solar film battery adopts the flexible solar hull cell, and the solar sail substrate of usining can be carried out integrated to thin film solar cell as substrate, as photoelectric conversion device.
Further technical scheme of the present invention is: thereby the optical pressure stable coatings is a kind of solar sail outer ring that spreads upon, form a kind of coating to the optical pressure sensitivity, coating material is generally the reflectance coefficients such as silver (reflectance coefficient 0.9), aluminum alloy (reflectance coefficient 0.85) at the high reflectance material more than 0.8.
Further technical scheme of the present invention is: electromagnetic signal gain coating is a kind of echo material, at the solar sail lower surface, smears the signal that strengthens transmission and receive.
Further technical scheme of the present invention is: satellite antenna can be embedded in to solar sail inside, along exhibition to distribution, combine together with sail body skeleton, realize to the support of sail body with to reception and the transmission of signal.
Further technical scheme of the present invention is: solar sail can be designed to the difformities such as turriform or umbrella, their characteristics are that space three-dimensional launches, one little one large, upper surface faces south lower surface over the ground.
Beneficial effect of the present invention: the present invention proposes thin-film solar cells, optical pressure stable coatings and electromagnetic signal gain coating are integrated on solar sail and carry out integrated design, can not only increase the light-receiving area of satellite sun energy battery, simultaneously also a plurality of subsystems can be integrated into to a structure, have very high design value.1. the present invention introduces thin-film solar cells, and the thin-film solar cells quality is light, thickness is little, and the space that takies satellite is also little, improves the satellite spatial degree of utilization; Be designed to simultaneously large-area expansion form, increased widely as the illuminating area of satellite sun energy battery, increase the electric power supply of satellite.2. because the film developed area is large, utilize sunshine produces on reflectance coating optical pressure can produce larger moment in thin film exterior layer, utilize this moment can maintain the attitude stabilization of satellite, realize the control of satellite passive attitude stabilization.3. bottom surface of the present invention scribbles the echo material, is conducive to strengthen radar signal, thereby has strengthened microsatellite ability to communicate over the ground.4. these designs are to be integrated in the integrated design of carrying out on solar sail, by the design of solar sail system and a plurality of system, coupled, have changed in the past single function, and value of service is higher.
The optical pressure stable coatings of solar sail upper surface outer ring is subject to producing larger moment after illumination, can guarantee that the solar sail upper surface is all the time over against the sun, both can guarantee passive attitude stabilization control, and the suffered light efficiency of thin-film solar cells is improved greatly.
Satellite Communication System can utilize the profile characteristics of solar sail, horn-like antenna is combined with the present invention, geotropism due to heliotropism and the lower surface of upper surface, make the directionality of signal good, signal to noise ratio is large, in the solar sail substrate lower surface, be coated with the echo material simultaneously, can further strengthen communication signal, guarantee directly communication over the ground of satellite.
The as a whole system of integrated solar sail, each functional unit all are fixed on public substrate, seamless link between each unit.By integrated design, solar power translation function, attitude stabilization function and communication function are integrated, take full advantage of that the solar sail illuminating area is large, the Edge Distance satellite is far away, lower surface is the characteristics such as tubaeform, practical function is integrated, both overcome the function shortcoming of small satellite, also saved the installing space of satellite preciousness.
With the microsatellite that does not adopt this invention, compare (this sentences 2U cube of star is example), the solar cell light-receiving area increases 200 times.With general solar panel, compare, the quality of solar sail is little, and area is large, and accepting too can the illumination abundance, and thin-film solar cells can provide sufficient electric energy for satellite; The thickness of solar sail is very little in addition, even developed area is larger, but shared volume is still very little when celestial body loads emission, can greatly save the inner space of satellite.
The accompanying drawing explanation
Fig. 1 is the laying design diagram of the integrated thin-film solar cells solar sail that proposes of the present invention;
Fig. 2 is organic thin film solar cell;
Fig. 3 is the layout of solar sail upper surface;
Fig. 4 is the layout of solar sail lower surface;
Fig. 5 is solar sail is used on cube star imaginary design sketch.
In figure: 1-substrate plate, 2-thin-film solar cells, 3-optical pressure stable coatings, 4-echo coating, 5-skeleton structure
Concrete embodiment
Below in conjunction with concrete embodiment, technical scheme of the present invention is further described.
Consult Fig. 1, integrated thin-film solar cells solar sail, described solar sail comprise solar film battery 2, optical pressure stable coatings 3 and electromagnetic signal gain coating, and namely the echo coating 4; Described solar sail sail body has upper and lower surfaces, described solar film battery 2 is fixed on the inner ring of the upper surface of solar sail substrate by the mode of pasting, described optical pressure stable coatings 3 is arranged on the outer ring of solar sail upper surface by the mode of smearing, the echo coating 4 of described electromagnetism gain is fixed on the lower surface of solar sail by the mode of smearing.
The multifunctional solar sail that is based on integrated design that Fig. 3 and Fig. 4 show, the solar sail body divides upper and lower two surfaces, upper surface is installed thin-film solar cells 2, and in outer ring, smear optical pressure stable coatings 3, simultaneously at the solar sail lower surface, be coated with echo coating 4, along four antennas of solar sail spanwise arrangement as skeleton structure 5.When thin-film solar cells 2 receives solar light irradiation, the optical pressure stable coatings 3 of outer ring also receives illumination, optical pressure stable coatings 3 materials adopt silver, reflectance coefficient is up to 0.9, be subjected to the optical pressure produced after illumination larger, and coating is far away apart from position, solar sail axis, can produce larger moment, after solar sail pose deviation balance position, the net torque overbalance that the optical pressure stable coatings is subject to, ordering about the solar sail attitude adjusts, realization is controlled the passive stabilization attitude of solar sail attitude, make simultaneously thin-film solar cells 2 all the time over against the sun, increased by the payload space of solar light irradiation.Utilize spill and the echo coating 4 of solar sail lower surface greatly to strengthen the microsatellite ability of communication over the ground.
Shown in Figure 5, the specific embodiment of the present invention is: apply the present invention on a kind of microsatellite, the final solar sail normal direction of launching is projected as the square of 2m * 2m, wherein the area of thin-film solar cells 5 is 3.84 ㎡, membrane process is 3.2 ㎡ to area of conter, the maximum useful power of thin-film solar cells is 183.6w, and quality is 30g; Optical pressure stable coatings 6 normal direction areas of conter in outer ring are 0.8 ㎡, and quality is 40g; Whole substrate lower surface is coated with echo gain coating 8, and quality is 30g; The quality of solar sail substrate plate 1 is 100g; Final integral solar energy battery quality is 200g, and thickness is 0.2mm.Because developed area is larger, thin film solar can provide sufficient electric energy for microsatellite, and can realize the Passive Control to microsatellite attitude in the optical pressure stable coatings of sunny slope solar sail outer ring, saves the power consumption of attitude control system.Simultaneously, based on the loudspeaker profile of solar sail and the electromagnetic signal gain coating of lower surface, the ability to communicate of microsatellite is strengthened greatly.
Above content is the further description of the present invention being done in conjunction with concrete preferred implementation, can not assert that specific embodiment of the invention is confined to these explanations.For the common technique personnel of the technical field of the invention, without departing from the inventive concept of the premise, can also make some simple deduction or replace, all should be considered as protection scope of the present invention.
Claims (6)
1. integrated thin-film solar cells solar sail, comprise solar sail sail body, it is characterized in that: comprise solar film battery, optical pressure stable coatings and electromagnetic signal gain coating; Described solar film battery is fixed on the inner ring of the upper surface of solar sail substrate by the mode of pasting, described optical pressure stable coatings is arranged on the outer ring of solar sail upper surface by the mode of smearing, described electromagnetism gain coating is fixed on the lower surface of solar sail by the mode of smearing.
2. integrated thin-film solar cells solar sail as claimed in claim 1, is characterized in that: described solar film battery employing flexible solar hull cell.
3. integrated thin-film solar cells solar sail as claimed in claim 1, it is characterized in that: thereby described optical pressure stable coatings is a kind of solar sail outer ring that spreads upon, form a kind of coating to the optical pressure sensitivity, coating material is that reflectance coefficient is at the high reflectance material more than 0.8.
4. integrated thin-film solar cells solar sail as claimed in claim 1 is characterized in that: described electromagnetic signal gain coating is a kind of echo material, at the solar sail lower surface, smears the signal that strengthens transmission and receive.
5. integrated thin-film solar cells solar sail as claimed in claim 1, it is characterized in that: described solar sail inside is embedded with satellite antenna, satellite antenna, along exhibition to distribution, combines together with sail body skeleton, realizes to the support of sail body with to reception and the transmission of signal.
6. integrated thin-film solar cells solar sail as claimed in claim 1 is characterized in that: described solar sail is turriform or the umbrella that space three-dimensional launches, one little one large, upper surface faces south lower surface over the ground.
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| CN2013102937620A CN103407581A (en) | 2013-07-12 | 2013-07-12 | Integrated thin-film solar cell solar sail |
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| CN2013102937620A CN103407581A (en) | 2013-07-12 | 2013-07-12 | Integrated thin-film solar cell solar sail |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103863580A (en) * | 2014-03-10 | 2014-06-18 | 中国空间技术研究院 | Folding method applicable to sail surfaces of blocked square support rod type solar sails |
| CN104058105A (en) * | 2014-06-24 | 2014-09-24 | 中国空间技术研究院 | Deep space solar sail spacecraft driven by utilizing sunlight pressure |
| CN104340380A (en) * | 2014-10-24 | 2015-02-11 | 兰州空间技术物理研究所 | Attitude control method for solar sail spacecraft |
| CN105857643A (en) * | 2016-04-01 | 2016-08-17 | 上海微小卫星工程中心 | Flexible solar wing used for satellite power supply and two-degree-of-freedom storage device applied to flexible solar wing |
| RU2682154C1 (en) * | 2015-12-07 | 2019-03-14 | Сергей Александрович Филин | Space vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1751965A (en) * | 2005-10-31 | 2006-03-29 | 哈尔滨工业大学 | Ultraviolet light rigidization composite film capable of aeration expanding outer space structure |
| CN102030112A (en) * | 2010-11-19 | 2011-04-27 | 哈尔滨工业大学 | Integrated actuating mechanism for realizing satellite attitude control and electric energy acquisition by combining liquid momentum wheel loop with solar array |
| CN103136444A (en) * | 2013-01-29 | 2013-06-05 | 北京空间飞行器总体设计部 | Analysis method of illuminated status of solar panel under different control modes of navigation satellite |
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2013
- 2013-07-12 CN CN2013102937620A patent/CN103407581A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1751965A (en) * | 2005-10-31 | 2006-03-29 | 哈尔滨工业大学 | Ultraviolet light rigidization composite film capable of aeration expanding outer space structure |
| CN102030112A (en) * | 2010-11-19 | 2011-04-27 | 哈尔滨工业大学 | Integrated actuating mechanism for realizing satellite attitude control and electric energy acquisition by combining liquid momentum wheel loop with solar array |
| CN103136444A (en) * | 2013-01-29 | 2013-06-05 | 北京空间飞行器总体设计部 | Analysis method of illuminated status of solar panel under different control modes of navigation satellite |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103863580A (en) * | 2014-03-10 | 2014-06-18 | 中国空间技术研究院 | Folding method applicable to sail surfaces of blocked square support rod type solar sails |
| CN103863580B (en) * | 2014-03-10 | 2016-06-29 | 中国空间技术研究院 | A kind of method for folding being suitable to piecemeal quadrate support rod-type solar sail sail face |
| CN104058105A (en) * | 2014-06-24 | 2014-09-24 | 中国空间技术研究院 | Deep space solar sail spacecraft driven by utilizing sunlight pressure |
| CN104058105B (en) * | 2014-06-24 | 2015-12-30 | 中国空间技术研究院 | One utilizes the power-actuated deep space Solar sail spacecraft of solar light pressure |
| CN104340380A (en) * | 2014-10-24 | 2015-02-11 | 兰州空间技术物理研究所 | Attitude control method for solar sail spacecraft |
| RU2682154C1 (en) * | 2015-12-07 | 2019-03-14 | Сергей Александрович Филин | Space vehicle |
| CN105857643A (en) * | 2016-04-01 | 2016-08-17 | 上海微小卫星工程中心 | Flexible solar wing used for satellite power supply and two-degree-of-freedom storage device applied to flexible solar wing |
| CN105857643B (en) * | 2016-04-01 | 2018-05-25 | 中国科学院上海微系统与信息技术研究所 | The flexible solar wing of power satellite and the two degrees of freedom storage device applied to the flexibility solar wing |
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Application publication date: 20131127 |