CN104210647A - Wing structure-meshed solar wing design and development scheme - Google Patents

Wing structure-meshed solar wing design and development scheme Download PDF

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Publication number
CN104210647A
CN104210647A CN201410485823.8A CN201410485823A CN104210647A CN 104210647 A CN104210647 A CN 104210647A CN 201410485823 A CN201410485823 A CN 201410485823A CN 104210647 A CN104210647 A CN 104210647A
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solar
wing
gridding
film
soft
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祝明
姜晓爱
张馨运
孙康文
孙谋
许冬冬
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Beihang University
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Beihang University
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Abstract

The invention provides a wing structure-meshed solar wing design and development method. The method comprises the following steps: with a high-efficiency rigid solar cell as a substrate, with wing ribs and a main beam which are formed by honeycomb sandwich structures as a support frame, arranging the solar cell in fiber mesh fabrics among the wing ribs by virtue of a tensile film structure in the building industry; by utilizing a double-layer film material, performing flexible modular encapsulation on the meshed rigid solar cell by virtue of a glue film to form a rigid and flexible integrated meshed solar cell module; effectively fixing the meshed solar cell module on the upper surfaces of the wings by utilizing a locking mechanism; and performing sealing and smooth transition treatment by using flexible sealing rubber. According to the meshed solar wings developed by the method, the service aim of lightness and high efficiency of the solar cell module for an unmanned aerial vehicle is achieved, and the problem that film wing covers are insufficient in strength is solved. Moreover, the wing structure weight of the solar unmanned aerial vehicle can be reduced to the greatest degree, and the flight performance and load capacity of the solar unmanned aerial vehicle are improved.

Description

A kind of wing structure-gridding solar power wing design and evaluation scheme
One, technical field:
The invention provides a kind of wing structure-gridding solar power wing design and evaluation method, belong to aerospace vehicle energy resource system technical field.
Two, background technology:
Altitude Long Endurance Unmanned Air Vehicle is as the unmanned vehicle that can run at advection layer and above height thereof, Intelligence, Surveillance, and Reconnaissance can be performed, communication repeating, Target indication, injure assessment, telecommunications and TV service, the multiple military affairs such as atmosphere environment supervision and weather forecast and Civil Affairs Mission, become the focus of current research.
On the other hand, using solar power as the auxiliary energy of future aircraft and even main energy sources, it is the important research target that human development has directivity and frontier nature.Solar powered aircraft occurs along with the reduction of solar cell cost in the seventies in last century, because solar powered aircraft flight does not need from carrying fuel, for flight during long boat creates condition.Therefore, many developed countries are all devoted to the research and development of the Altitude Long Endurance Unmanned Air Vehicle based on solar power.
Current solar power unmanned plane mainly adopts solar-energy photo-voltaic cell as main power supply part, is limited by aircraft surfaces limited area, must carry out efficiency utilization to solar cell.For the application of high performance solar batteries battle array, first-elected rigidity solar cell at present, applicablely mainly contain gallium arsenide solar cell and monocrystaline silicon solar cell, but owing to being subject to the restriction of solar power Unmanned Aerial Vehicle Airfoil radian, mounting structure and weight constraints, the problem of rigidity cell array plane and airfoil camber reasonable combination still fails efficient solution certainly so far.
For this reason, the invention provides a kind of wing structure-gridding solar power wing design and evaluation method, by to the rational modification of flexible thin-film solar cell manufacture method and perfect, apply it in the lighting encapsulation of rigidity solar cell, and between adjacent ribs high strength glass fiber cellular structure in addition, not only can protect the rigidity solar cell in grid, the bulk strength of thin film solar wing can also be improved, again based on this, in conjunction with to rib, the Appropriate application of main beam structure supporting role, cell array can be realized support, the integrated design of wing profile dimension shape.Thus more meet in current designs solar powered aircraft structure light wt, the composite request exporting energy efficient.
Three, summary of the invention:
(1) object: the object of the present invention is to provide a kind of wing structure-gridding solar power wing design and evaluation method, solar power unmanned plane wing based on the method development can meet the composite request of solar power unmanned plane in battery conversion efficiency and unit area battery specific power two, and can effectively solve the yielding problem of aerofoil surface covering brought because rigidity solar array is combined with aircraft wing curved surface.In addition, based on the method, effectively can reduce the loss of solar power unmanned plane in structural weight, and then improve the load capacity of solar power unmanned plane.
(2) technical scheme: a kind of wing structure-gridding solar power wing design and evaluation method of the present invention, the technical measures of the method is as follows: based on efficient rigidity solar cell, the rib formed using honeycomb sandwich construction and girder are as support frame, by using for reference the jacking membrane structure of surface structures industry, glass fibre or Kafra fiber tow is utilized to form grid between rib, and solar module is arranged in grid, by to the draw reasonable of flexible thin-film solar cell encapsulation technology and improvement, utilize duplicature based material, be equipped with glued membrane and the rigidity solar cell of gridding is carried out flexible modularized encapsulation, form the solar module of hard and soft one gridding, catch gear is utilized effectively to fix at the upper surface of wing the solar module of above-mentioned hard and soft one gridding again, with soft seal glue, the edge between the solar module of hard and soft one gridding is carried out sealing and smooth excess processes.
Based on such scheme, both the application target of the lighting of unmanned plane solar module, high efficiency can have been met, solve again during solar module is effectively combined with wing structure the problem of the film wing cover undercapacity caused, and the wing structure weight of solar power unmanned plane can be reduced to greatest extent, improve airworthiness and the load capacity of solar power unmanned plane.
Described gridding solar powered aircraft wing, primarily of the 7 layer material compositions stacked successively, comprises surface encapsulation film A, transparent adhesive film, rigidity solar battery sheet, fiberglass gridding, electrode wires, lightweight glued membrane A, surface encapsulation film B from top to bottom.Wherein rigidity solar battery sheet, fiberglass gridding, electrode wires are in same layer.
This surface encapsulation film A is positioned at the upper surface of gridding solar power wing, plays a part to protect solar battery sheet when meeting enough light transmittances; This transparent adhesive film is filled among the gap of rigidity solar battery sheet upper surface of surface encapsulation film and gridding; Fiberglass gridding, between adjacent two ribs, plays and fixes and protect rigidity solar battery sheet, increases the effect of membrane structure intensity.This electrode wires is mainly used in the electric energy that output rigidity solar battery sheet produces; This lightweight glued membrane A is filled among the rigidity solar battery sheet lower surface of gridding and the gap of surface encapsulation film B; this surface encapsulation film B is positioned at the lower surface of the solar module of hard and soft one gridding; while meeting solar battery sheet seal protection, play the effect of support structure.
Wherein, this surface encapsulation film A can adopt the PET film of modification or transparent TPT film;
Wherein, the light transmittance of this surface encapsulation film A need reach more than 90%;
Wherein, this transparent adhesive film can adopt light transmittance need reach the hot melt glued membrane of more than 90%;
Wherein, this rigidity solar battery sheet can adopt efficient gallium arsenide solar cell, efficiently monocrystaline silicon solar cell or efficient polysilicon solar cell;
Wherein, fiber mesh structure can adopt the glass fiber material or Kafra fiber with good insulation properties;
Wherein, this electrode wires can adopt silver-plated annealing oxygen-free copper, the pure silver foil of annealing or the silver-plated fine aluminium of annealing;
Wherein, this lightweight glued membrane A can adopt hot melt glued membrane;
Wherein, this surface encapsulation film B can adopt PET film or the TPT film of modification.
Described rib and girder mainly adopt carbon fiber honeycomb sandwich construction or glass fibre honeycomb sandwich construction to form.For ease of solar module fixing of hard and soft one gridding, in needing in above-mentioned honeycomb sandwich construction, bury the built-in fitting being processed with connecting bore.
Wherein, carbon fiber honeycomb sandwich construction adopts carbon fiber prepreg, lightweight glued membrane B and honeycomb core vacuum lamination to form, and wherein, this carbon fiber prepreg can adopt close type Orthogonal Double of knitting to form to the lamination preimpregnation of woven cloth or carbon fiber unidirectional cloth; This lightweight glued membrane B can adopt light and thin type epoxy resin glued membrane; This honeycomb core can adopt aluminium honeycomb or NOMEX paper honeycomb.
Wherein, glass fibre honeycomb sandwich construction adopts glass fibre prepreg, lightweight glued membrane B and honeycomb core vacuum lamination to form, and wherein, this glass fibre prepreg can adopt close type Orthogonal Double of knitting to form to woven cloth preimpregnation; This lightweight glued membrane B can adopt light and thin type epoxy resin glued membrane; This honeycomb core can adopt aluminium honeycomb or NOMEX paper honeycomb.
Wherein, this built-in fitting can adopt polyformaldehyde or aerolite to form by the machinework of given design size.
Described catch gear can be bolt connecting mechanism, also can be pin catch gear.
Described soft seal glue can adopt the rubber-type sealant or resin type sealant commonly used during battery ground component sealing.
A kind of wing structure in the present invention-gridding solar power wing design and evaluation method, its basic step is as follows:
1. materials procurement, inspection, ensure that selected materials meets operating needs and technological forming requirement, especially compatible with environment requirement;
2. gridding welding of battery film with join: for gridding solar module encapsulates solar battery sheet grid for welding used, its technological process comprise monolithic welding and multi-disc series welding; When monolithic welds, on main gate line direction, the length that is initial, that stop contact point distance solar battery sheet edge of welding remains on about 2 ~ 3mm, and the temperature of constant temperature electric iron remains on about 350 ~ 400 DEG C; Multi-disc series welding preferably carries out in the serial connection template of band pre-heating system, can ensure the distortion that solar battery sheet is little as far as possible, thus reduces fragment rate;
Wherein, when carrying out solar battery sheet welding, for guaranteeing the high efficiency that this solar module exports, welding process should complete in clean room (being generally more than 1,000,000 grades).
3. the while of with step 2, cutting, cleaning process can be carried out, comprise: with the honeycomb core of special cutter assembly needed for specification (surrounding leaves the stock left for machining of 5 ~ 10mm) cutting, cutting film based material (comprising surface encapsulation film A, transparent adhesive film, lightweight glued membrane A, surface encapsulation film B, lightweight glued membrane B) needed for wiping, clean the built-in fitting processing mounting hole in advance, clean the mould prepared needed for rib and girder, ensure foreign, impurity on film based material, built-in fitting, mould; Trimmed grid cloth, sizing grid need be determined according to cell piece size, and the Gitterfasern along rib orientation need leave the connection surplus of 7-15cm.
4. the solar battery sheet after surface encapsulation film A, transparent adhesive film, series welding being joined, fibrous mesh cloth, lightweight glued membrane A, surface encapsulation film B are by top-down order lamination, ensure that each solar battery sheet puts into the fiber mesh of reserved location, stacked good half-blank is put into laminating machine heating, lamination, heating and temperature control is at 120 ~ 150 DEG C, temperature rise time controls at 30 ~ 60 minutes, Stress control is at 0.998 ~ 1.5 standard atmosphere, time of heat is no less than 0.5 hour, the hard and soft one gridding solar module of final formation;
Laminating technology is key one step that hard and soft one gridding solar module is produced, and laminating temperature and lamination times comprehensively need be determined according to the character of transparent adhesive film and lightweight glued membrane (solidification temperature, cure time all with high person for benchmark).
5. the while of with step 4, utilize mould that fiber prepreg material, lightweight glued membrane B, honeycomb core, built-in fitting are carried out lamination by set design plan and prepare rib and girder, specific as follows: stacked good half-blank to be put into vacuum hotpressing tank carries out pressurizeing, heat treatment, Stress control is at 2 ~ 3 standard atmospheres, and time of heat is no less than 2 hours; Temperature controls at 120 ~ 150 DEG C, and the temperature rise time controls at 30 ~ 60 minutes; In addition, for guaranteeing the planarization on surface, the flat-type objects such as case hardened glass should be placed in the outside of upper and lower fiber prepreg material;
6. rib and girder are carried out combination according to given design scheme and form wing element structure;
7., by Gitterfasern reserved in advance, utilize catch gear to be arranged in wing element structure by hard and soft one gridding solar module;
8., for the overlapping place between hard and soft one solar module, utilize sealant to carry out sealing and fill, and smooth transition process is carried out to it;
9. pair whole wing element carries out fairing correction of the flank shape process, ensures that it has good aerodynamic characteristic, finally forms wing element and place in operation.
(3) advantage and effect: the invention provides a kind of wing structure-gridding solar power wing design and evaluation method, solar power unmanned plane wing based on the method development can meet the composite request of solar power unmanned plane in battery conversion efficiency and unit area battery specific power two, and can effectively solve the yielding problem of aerofoil surface covering brought because rigidity solar array is combined with aircraft wing curved surface.The raising of the lighting design and load capacity that thus can be solar power unmanned plane provides technical support.
Four, accompanying drawing illustrates:
Fig. 1 is the structural representation that the present invention is applied in certain concrete solar power unmanned plane wing structure-gridding solar power wing embodiment, and what adopt in the present embodiment is the main girder structures in front and back;
Fig. 2 is the structural representation of hard and soft one gridding solar module in embodiment;
Fig. 3 is the rib, the main beam structure that adopt in the present embodiment;
Fig. 4 is the basic development flow process of wing structure in the present embodiment-gridding solar power wing module.
Number in the figure is described as follows:
1. hard and soft one gridding solar module, 2. rib and girder, 3. catch gear, 4. soft seal glue, 5. fiberglass gridding, 6. surface encapsulation film A, 7. transparent adhesive film, 8. electrode wires, 9. efficient rigidity solar battery sheet, 10. lightweight glued membrane A, 11. surface encapsulation film B, 12. fiberglass gridding 13. carbon fiber prepregs, 14. lightweight glued membrane B, 15. honeycomb cores, 16. built-in fittings
Five, detailed description of the invention:
Be further described below in conjunction with a kind of wing structure in Fig. 1,2,3,4 couples of the present invention-gridding solar power wing design and evaluation method:
A kind of wing structure-gridding solar power wing of the present invention, as shown in Figure 1, mainly comprises hard and soft one gridding solar module 1, rib and girder 2, catch gear 3, soft seal glue 4 four parts.
The specific constructive form of this hard and soft one gridding solar module 1 as shown in Figure 2, mainly comprises surface encapsulation film A 6, transparent adhesive film 7, electrode wires 8, efficient rigidity solar battery sheet 9, lightweight glued membrane A 10, surface encapsulation film B 11, fiber mesh 12 7 parts.
This surface encapsulation film A 6 is positioned at the outside face of battery component of the present invention, and the present embodiment adopts light transmittance to be the modified PET of 91%, can play a part to protect efficient rigidity solar battery sheet 9 when meeting enough light transmittances;
This transparent adhesive film 7 is filled among the gap of surface encapsulation film A 6 and efficient rigidity solar battery sheet 9 upper surface, and the present embodiment adopts modified EVA glued membrane;
This electrode wires 8 is welded in the main gate line of efficient rigidity solar battery sheet 9 upper and lower surface, plays a part to export electric energy, and the present embodiment adopts the silver-plated fine aluminium of annealing;
Adopt in this efficient rigidity solar battery sheet 9 the present embodiment conversion efficiency be 18% efficient monocrystaline silicon solar cell sheet;
This lightweight glued membrane A 10 is filled among the gap of efficient rigidity solar battery sheet 9 lower surface and surface encapsulation film B 11, and the present embodiment adopts TPU hot melt adhesive film;
This surface encapsulation film B 11 is positioned at the lower surface of hard and soft one solar module, while meeting solar battery sheet seal protection, plays the effect of support structure, adopts TPT film in the present embodiment.
Fiber mesh 12 is positioned among the interval of each efficient rigidity solar battery sheet 9, plays the effect of the intensity of protection rigidity solar battery sheet 9 and raising monolithic film membrane wing.The present embodiment adopts the fiberglass gridding of good insulation preformance.
The specific constructive form of this rib and girder 2 as shown in Figure 3, mainly comprises carbon fiber prepreg 13, lightweight glued membrane B 14, honeycomb core 15, built-in fitting 16.
This carbon fiber prepreg 13 adopts close type Orthogonal Double of knitting to form to woven cloth preimpregnation; This lightweight glued membrane B 14 adopts light and thin type epoxy resin glued membrane; This honeycomb core 15 adopts aluminium honeycomb; This built-in fitting 16 is formed by aerolite machinework by given dimensional.
This catch gear 3 is pin catch gear.
What this soft seal glue 4 adopted is resin type sealant.
A kind of wing structure-solar cell integral module of the present invention, its basic development flow process is as follows:
Whole development flow process is as shown in Figure 4:
1. materials procurement, inspection, ensure that selected materials meets operating needs and technological forming requirement, especially compatible with environment requirement;
2. gridding solar battery sheet welding: for hard and soft one gridding solar module 1 encapsulates efficient rigidity solar battery sheet 9 grid for welding line 8 used, its technological process comprises monolithic welding and multi-disc series welding; When monolithic welds, on main gate line direction, the length that is initial, that stop contact point distance solar battery sheet edge of welding remains on about 2.5mm, and the temperature of constant temperature electric iron remains on about 380 DEG C; Multi-disc series welding need carry out in the serial connection template of band pre-heating system, can ensure the distortion that solar battery sheet is little as far as possible, thus reduces fragment rate;
3. the while of with step 2, cutting, cleaning process can be carried out, comprise: with the honeycomb core 15 of special cutter assembly needed for specification (surrounding leaves the stock left for machining of 5mm) cutting, cutting film based material needed for wiping (comprises surface encapsulation film A 6, transparent adhesive film 7, lightweight glued membrane A 10, surface encapsulation film B 11, lightweight glued membrane B 14), clean the built-in fitting 16 processing mounting hole in advance, clean and prepare rib and the mould needed for girder 2, ensure foreign, impurity on film based material, built-in fitting, mould; Trimmed grid cloth, sizing grid need be determined according to cell piece size, and the Gitterfasern along rib orientation need leave the connection surplus of 10cm;
4. by surface encapsulation film A 6, transparent adhesive film 7, solar battery sheet 9 after series welding joins, fiberglass gridding cloth 12, lightweight glued membrane A 10, surface encapsulation film B 11 is by top-down order lamination, ensure that each efficient rigidity solar battery sheet 9 puts into the 2200tex of reserved location, coating material is in the fiberglass gridding cloth 12 of epoxy resin, stacked good half-blank is put into laminating machine heat, lamination, heating and temperature control is at 145 DEG C, temperature rise time controls at 45 minutes, the display Data Control of vacuum instrumentation is at≤200Pa, time of heat 0.5 hour, final formation hard and soft one gridding solar module 1,
5. the while of with step 4, utilize mould that carbon fiber prepreg 13, lightweight glued membrane B 114, honeycomb core 15, built-in fitting 16 are carried out lamination by set design plan and prepare rib and girder 2, specific as follows: stacked good half-blank to be put into vacuum hotpressing tank carries out pressurizeing, heat treatment, Stress control is at 2 standard atmospheres, and time of heat is 2 hours; Temperature controls at 145 DEG C, and the temperature rise time controls at 45 minutes; In addition, for guaranteeing the planarization on surface, the flat-type objects such as case hardened glass should be placed in the outside of upper and lower carbon fiber prepreg;
6. rib and girder 2 are carried out combination according to given design scheme and form wing element structure;
7. output mounting hole by design plan at the edge of hard and soft one solar module 1, utilize catch gear 3 to be arranged in wing element structure by hard and soft one solar module 1 by mounting hole and reserved 10cm glass fibre;
8., for the overlapping place between hard and soft one solar module 1, utilize sealant 4 to carry out sealing and fill, and smooth transition process is carried out to it;
9. pair whole wing element carries out fairing correction of the flank shape process, ensures that it has good aerodynamic characteristic, finally forms wing element and place in operation.
It should be pointed out that this example only listing property application process of the present invention is described, but not for limiting the present invention.Any personnel being familiar with this kind of operation technique, all can without departing from the spirit and scope of the present invention, modify to above-described embodiment.Therefore, the scope of the present invention, should listed by claims.

Claims (4)

1. gridding solar powered aircraft wing scheme, is characterized in that:
Based on efficient rigidity solar cell, the rib formed using honeycomb sandwich construction and girder are as support frame, by using for reference the jacking membrane structure of surface structures industry, glass fibre or Kafra fiber tow is utilized to form grid between rib, and solar module is arranged in grid, by to the draw reasonable of flexible thin-film solar cell encapsulation technology and improvement, utilize duplicature based material, be equipped with glued membrane and the rigidity solar cell of gridding is carried out flexible modularized encapsulation, form the solar module of hard and soft one gridding; Catch gear is utilized effectively to fix at the upper surface of wing the solar module of above-mentioned hard and soft one gridding again; With soft seal glue, the edge between the solar module of hard and soft one gridding is carried out sealing and smooth excess processes.
2. gridding solar powered aircraft wing scheme, is characterized in that:
Described gridding solar powered aircraft wing, primarily of the 7 layer material compositions stacked successively, comprises surface encapsulation film A, transparent adhesive film, rigidity solar battery sheet, fiberglass gridding, electrode wires, lightweight glued membrane A, surface encapsulation film B from top to bottom.
3. gridding solar powered aircraft wing scheme, is characterized in that:
Described rib and girder mainly adopt carbon fiber honeycomb sandwich construction or glass fibre honeycomb sandwich construction to form.Fixing for ease of hard and soft one gridding solar module, buries the built-in fitting that be processed with connecting bore in needing in above-mentioned honeycomb sandwich construction.
4. gridding solar powered aircraft wing scheme, is characterized in that: its basic development flow process is as follows:
(1) materials procurement, inspection, ensure that selected materials meets operating needs and technological forming requirement, especially compatible with environment requirement;
(2) welding of battery film with join: for gridding solar module encapsulates solar battery sheet grid for welding used, its technological process comprise monolithic welding and multi-disc series welding; When monolithic welds, on main gate line direction, the length that is initial, that stop contact point distance solar battery sheet edge of welding remains on about 2 ~ 3mm, and the temperature of constant temperature electric iron remains on about 350 ~ 400 DEG C; Multi-disc series welding preferably carries out in the serial connection template of band pre-heating system, can ensure the distortion that solar battery sheet is little as far as possible, thus reduces fragment rate;
(3) while of with step 2, cutting, cleaning process can be carried out, comprise: with the honeycomb core of special cutter assembly needed for specification (surrounding leaves the stock left for machining of 5 ~ 10mm) cutting, cutting film based material (comprising surface encapsulation film A, transparent adhesive film, lightweight glued membrane A, surface encapsulation film B, lightweight glued membrane B) needed for wiping, clean the built-in fitting processing mounting hole in advance, clean the mould prepared needed for rib and girder, ensure foreign, impurity on film based material, built-in fitting, mould; Trimmed grid cloth, sizing grid need be determined according to cell piece size, and the Gitterfasern along rib orientation need leave the connection surplus of 7-15cm.
(4) solar battery sheet after surface encapsulation film A, transparent adhesive film, series welding being joined, fibrous mesh cloth, lightweight glued membrane A, surface encapsulation film B are by top-down order lamination, ensure that each solar battery sheet puts into the fiber mesh of reserved location, stacked good half-blank is put into laminating machine heating, lamination, heating and temperature control is at 120 ~ 150 DEG C, temperature rise time controls at 30 ~ 60 minutes, Stress control is at 0.998 ~ 1.5 standard atmosphere, time of heat is no less than 0.5 hour, the hard and soft one gridding solar module of final formation;
(5) while of with step 4, utilize mould that fiber prepreg material, lightweight glued membrane B, honeycomb core, built-in fitting are carried out lamination by set design plan and prepare rib and girder, specific as follows: stacked good half-blank to be put into vacuum hotpressing tank carries out pressurizeing, heat treatment, Stress control is at 2 ~ 3 standard atmospheres, and time of heat is no less than 2 hours; Temperature controls at 120 ~ 150 DEG C, and the temperature rise time controls at 30 ~ 60 minutes; In addition, for guaranteeing the planarization on surface, the flat-type objects such as case hardened glass should be placed in the outside of upper and lower fiber prepreg material;
(6) rib and girder are carried out combination according to given design scheme and form wing element structure;
(7) output mounting hole by design plan at the edge of hard and soft one solar module, utilize catch gear to be arranged in wing element structure by hard and soft one gridding solar module by mounting hole and reserved fiber;
(8) for the overlapping place between hard and soft one gridding solar module, utilize sealant to carry out sealing and fill, and smooth transition process is carried out to it;
(9) fairing correction of the flank shape process is carried out to whole wing element, ensure that it has good aerodynamic characteristic, finally form wing element and place in operation.
CN201410485823.8A 2014-09-22 2014-09-22 Wing structure-meshed solar wing design and development scheme Pending CN104210647A (en)

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CN105235890A (en) * 2015-10-19 2016-01-13 北京航空航天大学 Aircraft wing structure capable of realizing rapid disassembly and assembly for cell array
CN105355685A (en) * 2015-10-19 2016-02-24 北京航空航天大学 Rigid-flexible integrated solar cell considering heat insulation and development method thereof
CN105460201A (en) * 2015-11-13 2016-04-06 中国人民解放军国防科学技术大学 Wing leading edge of multifunctional solar aircraft
CN105383072A (en) * 2015-11-19 2016-03-09 航天材料及工艺研究所 Carbon fiber/high tenacity epoxy composite material grid fillet molding method
GB2568003A (en) * 2016-09-09 2019-05-01 Walmart Apollo Llc Solar rechargeable unmanned vehicle systems and methods to monitor a geographic area
US20180075760A1 (en) * 2016-09-09 2018-03-15 Wal-Mart Stores, Inc. Solar rechargeable unmanned vehicle systems and methods to monitor a geographic area
WO2018048627A1 (en) * 2016-09-09 2018-03-15 Wal-Mart Stores, Inc. Solar rechargeable unmanned vehicle systems and methods to monitor a geographic area
CN106585956B (en) * 2016-11-03 2019-04-12 上海空间电源研究所 The thin silicon solar module integration shaping method and structure of large scale wing
CN106585956A (en) * 2016-11-03 2017-04-26 上海空间电源研究所 Integrated shaping method and structure for thin silicon solar cell module of large-size wing
CN109545878A (en) * 2017-09-21 2019-03-29 中国电子科技集团公司第四十八研究所 A kind of interconnection structure and its preparation process of solar energy wing battery component
CN109545878B (en) * 2017-09-21 2021-06-11 中国电子科技集团公司第四十八研究所 Interconnection structure of solar wing battery assembly and preparation process thereof
CN108820245A (en) * 2018-06-26 2018-11-16 北京航空航天大学 A kind of solar powered aircraft aerofoil mask film tensioning installation equipment
CN112046729A (en) * 2020-08-11 2020-12-08 南京航空航天大学 Support connection structure of variable camber trailing edge sectional type wing rib and flexible skin

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Application publication date: 20141217