CN103929122A - Heat control method for solar photovoltaic batteries of airship - Google Patents
Heat control method for solar photovoltaic batteries of airship Download PDFInfo
- Publication number
- CN103929122A CN103929122A CN201410129192.6A CN201410129192A CN103929122A CN 103929122 A CN103929122 A CN 103929122A CN 201410129192 A CN201410129192 A CN 201410129192A CN 103929122 A CN103929122 A CN 103929122A
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- solar
- voltaic cell
- energy photo
- airship envelope
- airship
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- 238000000034 method Methods 0.000 title claims abstract description 19
- 239000004677 Nylon Substances 0.000 claims description 43
- 230000001464 adherent effect Effects 0.000 claims description 43
- 229920001778 nylon Polymers 0.000 claims description 43
- 230000008878 coupling Effects 0.000 claims description 8
- 238000010168 coupling process Methods 0.000 claims description 8
- 238000005859 coupling reaction Methods 0.000 claims description 8
- 238000007789 sealing Methods 0.000 claims description 8
- 238000003780 insertion Methods 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 abstract description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 230000000712 assembly Effects 0.000 abstract 1
- 238000000429 assembly Methods 0.000 abstract 1
- 239000007789 gas Substances 0.000 abstract 1
- 239000002918 waste heat Substances 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 12
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 230000002045 lasting effect Effects 0.000 description 1
- 230000033001 locomotion Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
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- Photovoltaic Devices (AREA)
Abstract
The invention discloses a heat control method for solar photovoltaic batteries of an airship. A distance is reserved between the solar photovoltaic batteries and an airship skin. The solar photovoltaic batteries are laid continuously in the axial direction of the airship or laid discontinuously in the circumferential direction to form a solar photovoltaic battery array. The solar photovoltaic batteries and the airship skin are connected through a plurality of connection assemblies uniformly distributed. According to the heat control method, the distance is reserved between the solar photovoltaic batteries and the airship skin so that the temperature of the solar photovoltaic batteries can be lowered, the electrical efficiency can be improved, and transmission of waste heat of the solar photovoltaic batteries to floating gas of the airship is eliminated at the same time. The solar photovoltaic batteries do not need to be flexible, and the difficulty of manufacturing the solar photovoltaic batteries is lowered.
Description
Technical field
The invention discloses a kind of dirigible solar-energy photo-voltaic cell heat control method, for dirigible thermal control, operation, control and energy resource system, the thermal control, the operation that belong to the aircraft that is lighter than air are controlled and energy technology field.
Background technology
For HAA, particularly stratospheric airship, flies when a basic demand is long boat.This just requires its energy resource system that lasting power and the needed electric energy of payload work can be provided.Solar-energy photo-voltaic cell is arranged on to airship envelope top, from solar energy, obtains power and electric power, the essential selection of flying while being the long boat of stratospheric airship.
The installation method of solar-energy photo-voltaic cell in airship envelope directly affects the electrical efficiency of solar-energy photo-voltaic cell and the thermal characteristics of dirigible.Patent 201310226141.0 discloses solar-energy photo-voltaic cell is placed in to the shirt rim of making in airship envelope, prevents that wind from entering the method between solar-energy photo-voltaic cell and airship envelope.The disclosed solar-energy photo-voltaic cell installation method of patent 201210403368.3 is, utilizes nylon adherent buckle that insulating assembly is closely connected with airship envelope, then solar-energy photo-voltaic cell covered on insulating assembly, do not stay gap.The common feature of these two inventions is, very close to each other between from solar-energy photo-voltaic cell to airship envelope, air-flow can not enter therebetween.This is also the common trait that solar-energy photo-voltaic cell is installed in airship envelope both at home and abroad at present.
Airship envelope is flexible curved surface, and traditional thinking is that it is also flexible only having solar-energy photo-voltaic cell, could adapt to the flexible curved surface characteristic of airship envelope.And if flexible solar photovoltaic cell is not fitted with covering or thermal insulation layer, entering of wind can cause solar-energy photo-voltaic cell shake, causes solar-energy photo-voltaic cell damaged.Here it is both at home and abroad prior art at solar-energy photo-voltaic cell to not staying the foundation in gap between airship envelope.
Utilize said method, solar-energy photo-voltaic cell temperature daytime can be up to more than 80 ℃.10 ℃ of the every risings of temperature, solar-energy photo-voltaic cell electrogenesis amount can reduce by 5% left and right, and this has had a strong impact on the electrical efficiency of solar-energy photo-voltaic cell.Meanwhile, the covering temperature that solar-energy photo-voltaic cell covers is than not having the covering temperature of solar-energy photo-voltaic cell can exceed 30 ℃ daytime, and this has had a strong impact on hot property and the height control ability of dirigible.
Summary of the invention
For solving above-mentioned technical barrier, a kind of dirigible solar-energy photo-voltaic cell heat control method is provided, can reduce solar-energy photo-voltaic cell temperature, improve its electrical efficiency, the present invention is achieved in that
A kind of dirigible solar-energy photo-voltaic cell heat control method, it is characterized in that: between solar-energy photo-voltaic cell and airship envelope, leave spacing, solar-energy photo-voltaic cell is along the axial continuous laying of dirigible, or interrupted laying circumferentially form solar-energy photo-voltaic cell array, between solar-energy photo-voltaic cell and airship envelope, by some equally distributed coupling assemblings, be connected.
In the present invention, described coupling assembling refers to the flexible sleeve assembly that comprises sleeve pipe, nylon adherent buckle, action pipe and manifold, described quill to dirigible axially parallel, its upper and lower surface is the rigid plane that is provided with nylon adherent buckle, both sides are flexible flat, the bottom surface of solar-energy photo-voltaic cell and airship envelope outer surface are respectively arranged with sleeve pipe upper and lower surface to corresponding nylon adherent buckle, and sleeve pipe is connected respectively with airship envelope outer surface with the bottom surface of solar-energy photo-voltaic cell by nylon adherent buckle; Action pipe is through sleeve pipe, and two ends are connected with two manifolds that are the circumferential arc of airship envelope respectively; Manifold is in parallel by the everything pipe of a solar-energy photo-voltaic cell array, wherein manifold one end sealing, and the other end is provided with automatic cut-off valve, another manifold one end sealing, the other end is installed unidirectional valve; Check valve inlet connects Mini-size inflation pump, and Mini-size inflation pump is given the inflation of action pipe at sunrise; Automatic cut-off valve is closed daytime, keeps action overpressure, makes to keep spacing between solar-energy photo-voltaic cell and airship envelope, and stay open night, bleeds off action inner air tube, and at this moment sleeve pipe is flat, and solar-energy photo-voltaic cell and airship envelope are mutually close.
In the present invention, described coupling assembling is the connection hinge that comprises hinge, hinge bolt and latch, described hinge both sides all have symmetrical connecting bolt hole, it is female that the bottom surface of airship envelope outer surface and solar-energy photo-voltaic cell is respectively arranged with the pin meshing with connecting bolt hole, two hinges interconnect by hinge bolt on one side, and another side connects with corresponding airship envelope outer surface or the mother of the pin on solar-energy photo-voltaic cell bottom surface respectively; Described hinge bolt insertion end is connected with drag-line locking, a termination motor of drag-line, and after motor energising, cable pull, the complete flare up plane of hinge, lifts solar-energy photo-voltaic cell, makes to keep spacing between solar-energy photo-voltaic cell and airship envelope; After motor power-off, drag-line loosens, and hinge is close, and solar-energy photo-voltaic cell and airship envelope are mutually close.
In the present invention, described coupling assembling is level altitude assembly, and level altitude component height is identical with spacing, and its upper surface and lower surface are provided with nylon adherent buckle; The bottom surface of solar-energy photo-voltaic cell is respectively arranged with the nylon adherent buckle corresponding with planar rigidity assembly with the outer surface of airship envelope, and planar rigidity assembly connects by nylon adherent buckle, makes to keep spacing between solar-energy photo-voltaic cell and airship envelope.
In the present invention, described level altitude assembly refers to axially and the rigid rectangular tube of dirigible axially parallel.
The invention has the advantages that, by leave spacing between airship envelope and solar-energy photo-voltaic cell, to reduce solar-energy photo-voltaic cell temperature, improve electrical efficiency, eliminate solar-energy photo-voltaic cell used heat to the transmission of dirigible buoyance lift gas simultaneously; On the other hand, the present invention does not require that solar-energy photo-voltaic cell is flexible, has reduced solar-energy photo-voltaic cell manufacture difficulty.
Accompanying drawing explanation
Fig. 1 is the solar-energy photo-voltaic cell schematic diagram that flexible sleeve assembly is installed.
Fig. 2 is the A-A profile in Fig. 1.
Fig. 3 is the local enlarged diagram in A place in Fig. 2.
Fig. 4 is provided with the solar-energy photo-voltaic cell schematic diagram that connects hinge.
Fig. 5 is the A-A profile in Fig. 4.
Fig. 6 is the local enlarged diagram in B place in Fig. 5.
Fig. 7 is the solar-energy photo-voltaic cell schematic diagram that level altitude assembly is installed.
Fig. 8 is the A-A profile in Fig. 7.
Fig. 9 is the local enlarged diagram in C place in Fig. 8.
Wherein, 1. solar-energy photo-voltaic cell, 2. airship envelope, 3. sleeve pipe, 4. nylon adherent buckle, 5. nylon adherent buckle, 6. nylon adherent buckle, 7. nylon adherent buckle, 8. action is managed, 9. manifold, 10. manifold, 11. automatic cut-off valves, 12. unidirectional valves, 13. Mini-size inflation pumps, 14. connect hinge, 15. hinges, 16. hinges, 17. hinge bolts, 18. latches, 19. pins are female, 20. latches, 21. solar cell latches are female, 22. drag-lines, 23. rigid rectangular tubes, 23. nylon adherent buckles, 24. nylon adherent buckles, 25. nylon adherent buckles, 26. nylon adherent buckles, 27. nylon adherent buckles.
Embodiment
Embodiment 1
As shown in Figure 1, 2, 3, wherein, Fig. 1 is the solar-energy photo-voltaic cell schematic diagram that flexible sleeve assembly is installed,
Fig. 2 is the A-A profile in Fig. 1, and Fig. 3 is the local enlarged diagram of flexible sleeve assembly in Fig. 2 (A place):
A dirigible solar-energy photo-voltaic cell heat control method leaves spacing between solar-energy photo-voltaic cell 1 and airship envelope 2, forms narrow air flow channel; Solar-energy photo-voltaic cell is along axial (the being dirigible long axis direction) continuous laying of 1 dirigible, between solar-energy photo-voltaic cell 1 and airship envelope 2, by some, is all connected with the flexible sleeve assembly of distribution.
Flexible sleeve assembly upper and lower surface is that rigid plane, both sides are flexible surface, and by sleeve pipe 3, nylon adherent buckle 4,5,6,7, action pipe 8 and manifold 9,10 form, and the upper plane suture of sleeve pipe 3 is shaped with nylon adherent buckle 4, and lower plane is sewed with nylon adherent buckle 5; Nylon adherent buckle 6 is made in the bottom surface of solar-energy photo-voltaic cell 1; The outer surface of airship envelope 2 is made respectively nylon adherent buckle 7; Sleeve pipe 3 axially and dirigible axially parallel; The upper plane nylon adherent buckle 4 of sleeve pipe 3 is connected with solar-energy photo-voltaic cell bottom surface nylon adherent buckle 6, and lower plane nylon adherent buckle 5 is connected with airship envelope outer surface nylon adherent buckle 7; Along circumferentially arrange some row (being axially row) sleeve pipe 3 between solar-energy photo-voltaic cell array and airship envelope 2, action pipe 8 of every row sleeve pipe 3 use passes, action pipe 8 is made for dirigible capsule clothing, its outer perimeter is slightly less than sleeve pipe 3 inner rim length, action pipe 8 two ends connect respectively manifold 9 and manifold 10, manifold 9 and manifold 10 are the circumferential arc of airship envelope, slightly be longer than solar-energy photo-voltaic cell array circumferential lengths, manifold 9 and manifold 10 are by everything pipe 8 parallel connections of a solar-energy photo-voltaic cell array; One end sealing of manifold 9, the other end is provided with automatic cut-off valve 11, one end sealing of manifold 10, and the other end is installed unidirectional valve 12, the effect of unidirectional valve 12 is when Miniature inflatable air pump inoperative, play sealing function, the inner air tube that prevents from moving flows backwards, and unidirectional valve 12 air inlets connect Mini-size inflation pump 13, Mini-size inflation pump 13 gives action pipe 8 inflations at sunrise, shut-off valve cuts out for 11 daytimes, keeps action pipe 8 internal pressures, makes to keep spacing between solar-energy photo-voltaic cell 1 and airship envelope 2; Shut-off valve stays open for 11 nights, bleeds off action pipe 8 interior air, and at this moment sleeve pipe 3 is flat, and solar-energy photo-voltaic cell 1 is mutually close with airship envelope 2.
Daytime is under Sunlight Action, solar-energy photo-voltaic cell 1 easily heats up, need cooling to spread in dirigible to improve solar-energy photo-voltaic cell efficiency and to reduce solar-energy photo-voltaic cell used heat, so need larger air-flow by the air flow channel between solar-energy photo-voltaic cell 1 and airship envelope 2, take away solar-energy photo-voltaic cell used heat, this just needs the spacing between solar-energy photo-voltaic cell and airship envelope larger, this air flow channel has increased dirigible aerodynamic drag, spacing between solar-energy photo-voltaic cell and airship envelope is larger, aerodynamic drag is larger, so when do not need air flow night, reduce spacing, reduce aerodynamic drag.
In practical operation, nylon adherent buckle also can be connected by the mode of pasting with bottom surface, the airship envelope outer surface of sleeve pipe, solar-energy photo-voltaic cell.
In the present embodiment, between solar-energy photo-voltaic cell 1 and airship envelope 2, leave spacing, between solar-energy photo-voltaic cell and airship envelope, spacing is too small daytime, and runner deficiency of air, can not effectively take away solar-energy photo-voltaic cell used heat.Between solar-energy photo-voltaic cell and airship envelope, spacing is excessive, causes that unnecessary aerodynamic drag increases.
Embodiment 2
As shown in Figure 4,5, 6, wherein, Fig. 4 is provided with the solar-energy photo-voltaic cell schematic diagram that connects hinge, and Fig. 5 is the A-A profile in Fig. 4, and Fig. 6 connects the local enlarged diagram of hinge (B place) in Fig. 5:
A kind of dirigible solar-energy photo-voltaic cell heat control method, between solar-energy photo-voltaic cell 1 and airship envelope 2, leave spacing, solar-energy photo-voltaic cell 1 is along axially interrupted laying of dirigible, form solar-energy photo-voltaic cell array, between solar-energy photo-voltaic cell 1 and airship envelope 2 by some equally distributed hinges 14 connections that are connected.
Connect hinge 14 by hinge 15,16,, hinge bolt 17, latch 18,20, the bottom surface of airship envelope outer surface and solar-energy photo-voltaic cell is respectively arranged with the pin mother meshing with connecting bolt hole 19,21; Two hinges 15,16 that connect hinge 14 connect by hinge bolt 17, can be around hinge bolt 17 rotations; When connecting hinge 14 in maximum opening, two 15,16 pairs of hinges are connected into a plane, cannot turn again; Hinge 15,16, both sides all there is symmetrical connecting bolt hole; After hinge 15 is connected by hinge bolt 17 with hinge 16, the another side of hinge 15 is connected with airship envelope latch female 19 by latch 18, and the another side of hinge 16 is connected with solar cell latch female 21 by latch 20; Hinge bolt 17 insertion ends and drag-line 22 lockings, drive hinge bolt 17 motions by drag-line 22, prevents that hinge bolt 17 from departing from pin hole simultaneously; Along circumferential all connection hinges 14 in a row side by side, share a drag-line 22; One termination motor of drag-line 22, after motor energising, drag-line 22 tensions, hinge 15 and the complete flare up plane of hinge 16, lift solar-energy photo-voltaic cell 1, makes to keep spacing between solar-energy photo-voltaic cell 1 and airship envelope 2; After motor power-off, drag-line 22 loosens, and hinge 15 is close with hinge 16, mutually close between solar-energy photo-voltaic cell 1 and airship envelope 2.
For the ease of connecting the startup of hinge 14, avoid drag-line 22 and airship envelope 2 frictions simultaneously, the present embodiment similarly starts pipe along several of dirigible circumferential arrangement and axially parallel with pneumatic tube at air flow channel, start the sealing of pipe one end, another termination Mini-size inflation pump, starts pipe and is located at drag-line 22 belows; Before drag-line motor starting, first start Mini-size inflation pump, give and start pipe inflation; solar-energy photo-voltaic cell is raised a bit, made hinge page have certain aperture, the motor starting being at this moment connected with drag-line; tension drag-line is opened hinge page, and after drag-line motor starting, Mini-size inflation pump is shut down.
In the present embodiment, solar-energy photo-voltaic cell is along axially interrupted laying of dirigible, circumferentially form solar-energy photo-voltaic cell array, the object that adjacent solar-energy photo-voltaic cell array is axially kept at a distance along dirigible is shortening runner, makes solar-energy photo-voltaic cell waste thermal energy be rejected in time atmosphere.Adjacent solar-energy photo-voltaic cell array pitch is too small, and the used heat that upstream air runner is got rid of can enter air downstream runner; Adjacent solar-energy photo-voltaic cell array pitch is excessive, can increase unnecessary solar-energy photo-voltaic cell array management difficulty.
Embodiment 3
As shown in Fig. 7,8,9, wherein, Fig. 7 is the solar-energy photo-voltaic cell schematic diagram that level altitude assembly is installed, and Fig. 8 is the A-A profile in Fig. 7, and Fig. 9 is the local enlarged diagram of level altitude assembly in Fig. 8 (C place):
A dirigible solar-energy photo-voltaic cell heat control method leaves spacing between solar-energy photo-voltaic cell 1 and airship envelope 2, forms narrow air flow channel, solar-energy photo-voltaic cell 1 is along axially interrupted laying of dirigible, form solar-energy photo-voltaic cell array, adjacent solar-energy photo-voltaic cell array axially keeps certain distance along dirigible, between solar-energy photo-voltaic cell 1 and airship envelope 2, by some equally distributed rigid rectangular tubes 23, be connected, rigid rectangular tube 23 axially and dirigible axially parallel, highly equals the spacing between solar-energy photo-voltaic cell 1 and airship envelope 2, on rigid rectangular tube 23, plane is made nylon adherent buckle 24, lower plane is made nylon adherent buckle 25, the bottom surface of solar-energy photo-voltaic cell 1 is respectively arranged with the nylon adherent buckle 26 corresponding with rigid rectangular tube 23 with the outer surface of airship envelope 2, 27, nylon adherent buckle 26 is made in the bottom surface of solar-energy photo-voltaic cell 1, the outer surface of airship envelope 2 is made nylon adherent buckle 27, on rigid rectangular tube 23, plane nylon adherent buckle 24 is connected with solar-energy photo-voltaic cell bottom surface nylon adherent buckle 26, lower plane nylon adherent buckle 25 is connected with airship envelope outer surface nylon adherent buckle 27, make to keep spacing between solar-energy photo-voltaic cell 1 and airship envelope 2.
Claims (5)
1. a dirigible solar-energy photo-voltaic cell heat control method, it is characterized in that: between solar-energy photo-voltaic cell and airship envelope, leave spacing, solar-energy photo-voltaic cell is along the axial continuous laying of dirigible, or interrupted laying circumferentially form solar-energy photo-voltaic cell array, between solar-energy photo-voltaic cell and airship envelope, by some equally distributed coupling assemblings, be connected.
2. dirigible solar-energy photo-voltaic cell heat control method according to claim 1, it is characterized in that: described coupling assembling refers to and comprises sleeve pipe, nylon adherent buckle, the flexible sleeve assembly of action pipe and manifold, described quill to dirigible axially parallel, on it, plane and lower plane are the rigid plane that is provided with nylon adherent buckle, both sides are flexible flat, the bottom surface of solar-energy photo-voltaic cell is respectively arranged with sleeve pipe upper and lower surface to corresponding nylon adherent buckle with airship envelope outer surface, sleeve pipe is connected respectively with airship envelope outer surface with the bottom surface of solar-energy photo-voltaic cell by nylon adherent buckle, action pipe is through sleeve pipe, and two ends are connected with two manifolds that are the circumferential arc of airship envelope respectively, manifold is in parallel by the everything pipe of a solar-energy photo-voltaic cell array, wherein manifold one end sealing, and the other end is provided with automatic cut-off valve, another manifold one end sealing, the other end is installed unidirectional valve, check valve inlet connects Mini-size inflation pump, and Mini-size inflation pump is inflated to setting pressure at sunrise action pipe, automatic cut-off valve is closed daytime, keeps action overpressure, makes to keep spacing between solar-energy photo-voltaic cell and airship envelope, and night, shut-off valve stayed open, and bled off action inner air tube, and solar-energy photo-voltaic cell and airship envelope are mutually close.
3. dirigible solar-energy photo-voltaic cell heat control method according to claim 1, it is characterized in that: described coupling assembling is the connection hinge that comprises hinge, hinge bolt and latch, described hinge both sides all have symmetrical connecting bolt hole, it is female that the bottom surface of airship envelope outer surface and solar-energy photo-voltaic cell is respectively arranged with the pin meshing with connecting bolt hole, two hinges interconnect by hinge bolt on one side, and another side connects with corresponding airship envelope outer surface or the mother of the pin on solar-energy photo-voltaic cell bottom surface respectively by latch; Described hinge bolt insertion end is connected with drag-line locking, a termination motor of drag-line, and after motor energising, cable pull, the complete flare up plane of hinge, lifts solar-energy photo-voltaic cell, makes to keep spacing between solar-energy photo-voltaic cell and airship envelope; After motor power-off, drag-line loosens, and hinge is close, and solar-energy photo-voltaic cell and airship envelope are mutually close.
4. dirigible solar-energy photo-voltaic cell heat control method according to claim 1, is characterized in that: described coupling assembling is level altitude assembly, and described level altitude assembly upper surface and lower surface are provided with nylon adherent buckle, and its height is identical with spacing; The bottom surface of solar-energy photo-voltaic cell is respectively arranged with the nylon adherent buckle corresponding with level altitude assembly with the outer surface of airship envelope, level altitude assembly is connected with airship envelope outer surface with the bottom surface of solar-energy photo-voltaic cell respectively by nylon adherent buckle, makes to keep spacing between solar-energy photo-voltaic cell and airship envelope.
5. dirigible solar-energy photo-voltaic cell heat control method according to claim 4, is characterized in that: described level altitude assembly refers to axially and the rigid rectangular tube of dirigible axially parallel.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410129192.6A CN103929122B (en) | 2014-04-02 | 2014-04-02 | A kind of dirigible solar-energy photo-voltaic cell heat control method |
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| CN201410129192.6A CN103929122B (en) | 2014-04-02 | 2014-04-02 | A kind of dirigible solar-energy photo-voltaic cell heat control method |
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| CN103929122B CN103929122B (en) | 2016-05-18 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104967396A (en) * | 2015-07-23 | 2015-10-07 | 北京天航华创科技股份有限公司 | Flexible solar cell module of hasp connection type, and development scheme therefor |
| CN107856833A (en) * | 2017-10-31 | 2018-03-30 | 中国科学院光电研究院 | It is a kind of mat formation have the HAA and its operating method of thin-film solar cells |
| CN108974317A (en) * | 2017-06-02 | 2018-12-11 | 海口未来技术研究院 | Aerostatics |
| CN111130431A (en) * | 2019-12-26 | 2020-05-08 | 北京临近空间飞艇技术开发有限公司 | Solar cell array supporting structure applied to aerostat |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103606580B (en) * | 2013-12-04 | 2016-01-20 | 新誉集团有限公司 | Flexible solar plate and preparation method thereof, dirigible |
-
2014
- 2014-04-02 CN CN201410129192.6A patent/CN103929122B/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104967396A (en) * | 2015-07-23 | 2015-10-07 | 北京天航华创科技股份有限公司 | Flexible solar cell module of hasp connection type, and development scheme therefor |
| CN104967396B (en) * | 2015-07-23 | 2017-05-31 | 北京天航华创科技股份有限公司 | A kind of fastener connected flexible solar battery pack and its research and development proposal |
| CN108974317A (en) * | 2017-06-02 | 2018-12-11 | 海口未来技术研究院 | Aerostatics |
| CN107856833A (en) * | 2017-10-31 | 2018-03-30 | 中国科学院光电研究院 | It is a kind of mat formation have the HAA and its operating method of thin-film solar cells |
| CN107856833B (en) * | 2017-10-31 | 2023-11-07 | 中国科学院光电研究院 | High-altitude airship paved with thin-film solar cells and operation method thereof |
| CN111130431A (en) * | 2019-12-26 | 2020-05-08 | 北京临近空间飞艇技术开发有限公司 | Solar cell array supporting structure applied to aerostat |
| CN111130431B (en) * | 2019-12-26 | 2021-01-01 | 北京临近空间飞艇技术开发有限公司 | Solar cell array supporting structure applied to aerostat |
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| CN103929122B (en) | 2016-05-18 |
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