CN209447811U - A kind of semi-rigid solar cell module of solar powered aircraft Ultralight - Google Patents
A kind of semi-rigid solar cell module of solar powered aircraft Ultralight Download PDFInfo
- Publication number
- CN209447811U CN209447811U CN201821881949.7U CN201821881949U CN209447811U CN 209447811 U CN209447811 U CN 209447811U CN 201821881949 U CN201821881949 U CN 201821881949U CN 209447811 U CN209447811 U CN 209447811U
- Authority
- CN
- China
- Prior art keywords
- solar
- cell module
- semi
- solar cell
- powered aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- 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
Landscapes
- Photovoltaic Devices (AREA)
Abstract
The utility model relates to a kind of semi-rigid solar cell modules of solar powered aircraft Ultralight, including solar battery (1) and the low resistance connection sheet (3) being connected between solar battery (1), lead-out wire (6), skin covering of the surface (5) and tear-proof counterdie (4), the solar cell module is spliced by multiple solar batteries (1), the curved surface overall structure to fit near space dirigible upper surface is spliced by being affixed on the tear-proof counterdie (4) at its back side between solar battery (1), the low resistance connection sheet (3) be used for solar battery (1) between circuit series connection and be connected in parallel, positive and negative anodes of the lead-out wire (6) for spliced muti-piece solar battery (1) entirety are drawn, the skin covering of the surface (5) is affixed on the front of spliced solar battery (1).Compared with prior art, the utility model has many advantages, such as that light weight, curved-surface structure compactness are high, integral strength is high and ageing-resistant.
Description
Technical field
The utility model relates to a kind of solar energy modules, can the semi-rigid sun of aircraft Ultralight more particularly, to a kind of sun
It can battery module.
Background technique
In recent years, China pays close attention to aviation development increasing, and the research of extraordinary aircraft is also more and more extensive,
Middle solar powered aircraft causes the great attention of various countries with its special application environment.
Solar powered aircraft is mainly characterized in that long endurance, long stagnant sky, and realizes that the important leverage of this feature is exactly solar energy
The application of aviation power system technology, this technology can make solar powered aircraft is lasting during cruise to obtain the benefit of the energy
It fills, extends cruise time even realization energy closed loop.And it is suitable for the solar energy airplane power source system of solar powered aircraft application environment
System technology is particularly important.
Solar energy unmanned plane aerofoil surface is mostly globoidal structure, it is desirable that solar battery has certain bendable curvature, mesh
Preceding conventional solar cell area is big, and bending property is poor, and large area easily causes crack, the fragment of battery when being laid with, to make
Decline at solar powered aircraft cell array overall performance electrical performance, the battery portion of fragmentation has security risk for complete machine, and big
The solar battery of area is not easy to carry out pavement construction in assembling.
The solar cell module of solar powered aircraft not only needs to have good compatible degree with aerofoil surface, but also
It is able to satisfy the requirement of aircraft high intensity, lightweight, vibration, variation of ambient temperature in flight course.
Summary of the invention
The purpose of this utility model is exactly to provide a kind of solar energy in order to overcome the problems of the above-mentioned prior art and fly
The semi-rigid solar cell module of machine Ultralight.
The purpose of this utility model can be achieved through the following technical solutions:
A kind of solar powered aircraft Ultralight solar cell module, including solar battery and it is connected to solar battery
Between low resistance connection sheet, lead-out wire, skin covering of the surface and tear-proof counterdie, the solar cell module is by multiple solar-electricities
Pond is spliced, and is spliced into and near space dirigible upper surface phase between solar battery by being affixed on the tear-proof counterdie at its back side
The curved surface overall structure of fitting, the low resistance connection sheet by welding will be described in solar battery interconnections
Low resistance connection sheet be used for solar battery between circuit series connection and be connected in parallel, the lead-out wire be used for spliced muti-piece
The positive and negative anodes of solar battery entirety are drawn, and the skin covering of the surface is affixed on the front of spliced solar battery.Because of the sun
Can aircraft the speed of service far more than dirigible, while the resistance of its flight environment of vehicle also far super near space aircraft, therefore for it
Low resistance connection sheet need to be attached by the way of welding when circuit connection, the bonding strength of requirement is reached with this.
Further, the solar battery is crystal silicon solar energy battery of the thickness less than 100 μm.
Further, welding manner is one of soldering, electric resistance welding or ultrasonic bond.
Further, the welding manner is one of soldering, electric resistance welding or ultrasonic bond.
Further, the low resistance connection sheet is copper connection sheet.
Further, the lead-out wire is the copper wire that surface is coated with PFA plastics, is drawn by PFA material with increasing
The UV resistance of line.
Further, the skin covering of the surface is ETFE or PET material, and ETFE and PET material had both had high light transmittance energy,
With excellent resistance to ultraviolet resistance, therefore it will not influence the normal work of solar battery.
Further, light transmittance >=90% of the skin covering of the surface.
Further, the tear-proof counterdie is ETFE or PET material.
Further, the internal layer of the tear-proof counterdie is equipped with glass fiber or carbon fiber wire establishment grid is reinforced
Layer, tear-proof counterdie increase grid enhancement layer relative to skin covering of the surface, because the effect that tear-proof counterdie is is guarantee solar energy
Being mutually reliably connected between battery needs to provide intensity support by grid enhancement layer, and tear-proof counterdie is located at the sun
The back side of energy battery, does not need the requirement to translucency.
Further, the tear-proof counterdie surface is coated with EVA material.
Compared with prior art, the utility model uses novel designs theory, using the splicing of solar battery, wound
New devises a kind of semi-rigid solar cell module of solar powered aircraft Ultralight, not only has good bending property,
Can be compound in the progress of solar powered aircraft cambered surface aerofoil surface, module quality is light, and has higher electrical property output.This is practical
It is novel can preferably solve the problems, such as that solar energy should be gone up in aircraft using encountering, the innovation of solar powered aircraft of preferable power-assisted and
Development.
Detailed description of the invention
Fig. 1 is the overall structure signal of the semi-rigid solar cell module of solar powered aircraft Ultralight in the utility model
Figure；
Fig. 2 is the cross-section structure signal of the semi-rigid solar cell module of solar powered aircraft Ultralight in the utility model
Figure.
In figure: 1, solar battery, 2, low resistance mutually in flakes, 3, low resistance connection sheet, 4, tear-proof counterdie, 5, surface
Film, 6, lead-out wire.
Specific embodiment
The utility model is described in detail in the following with reference to the drawings and specific embodiments.
Embodiment
Solar powered aircraft Ultralight solar cell module includes solar battery 1 and is connected between solar battery 1
Low resistance connection sheet 3, lead-out wire 6, skin covering of the surface 5 and tear-proof counterdie 4, referring to Fig. 1
In specific 1 splicing of solar battery, by being affixed on the tear-proof counterdie at its back side between solar battery 1
4 are spliced into the curved surface overall structure to fit near space dirigible upper surface, and the low resistance connection sheet 3 is used for solar energy
It the series connection of 1 circuit of battery and is connected in parallel, the lead-out wire 6 is whole just for spliced muti-piece solar battery 1
Cathode is drawn, and the skin covering of the surface 5 is affixed on the front of spliced solar battery 1.The low resistance connection sheet 3 passes through weldering
Solar battery 1 is connected with each other by the mode connect.The welding manner is one of soldering, electric resistance welding or ultrasonic bond.
In terms of material type selecting, low resistance connection sheet 3 is copper connection sheet, and lead-out wire 6 is that surface is coated with PFA plastics
Copper wire, the skin covering of the surface 5 be ETFE or PET material, light transmittance >=90% of skin covering of the surface 5.Tear-proof counterdie 4 be ETFE or
PET material, the internal layer of tear-proof counterdie 4 is equipped with glass fiber or carbon fiber wire works out grid enhancement layer.The tear-proof
4 surface of counterdie is coated with EVA material.
Claims (10)
1. a kind of semi-rigid solar cell module of solar powered aircraft Ultralight, which is characterized in that including solar battery (1)
And low resistance connection sheet (3), lead-out wire (6), skin covering of the surface (5) and the tear-proof counterdie (4) being connected between solar battery (1),
The solar cell module is spliced by multiple solar batteries (1), by being affixed on its back side between solar battery (1)
Tear-proof counterdie (4) be spliced into the curved surface overall structure to fit near space dirigible upper surface, the low resistance connects
Solar battery (1) is connected with each other the low resistance connection sheet (3) by welding and is used for solar-electricity by contact pin (3)
It the series connection of circuit and is connected in parallel between pond (1), the lead-out wire (6) is whole for spliced muti-piece solar battery (1)
Positive and negative anodes draw, the skin covering of the surface (5) is affixed on the front of spliced solar battery (1).
2. a kind of semi-rigid solar cell module of solar powered aircraft Ultralight according to claim 1, feature exist
In the solar battery (1) is crystal silicon solar energy battery of the thickness less than 100 μm.
3. a kind of semi-rigid solar cell module of solar powered aircraft Ultralight according to claim 1, feature exist
In the welding manner is one of soldering, electric resistance welding or ultrasonic bond.
4. a kind of semi-rigid solar cell module of solar powered aircraft Ultralight according to claim 3, feature exist
In the low resistance connection sheet (3) is copper connection sheet.
5. a kind of semi-rigid solar cell module of solar powered aircraft Ultralight according to claim 1, feature exist
In the lead-out wire (6) is the copper wire that surface is coated with PFA plastics.
6. a kind of semi-rigid solar cell module of solar powered aircraft Ultralight according to claim 1, feature exist
In the skin covering of the surface (5) is ETFE or PET material.
7. a kind of semi-rigid solar cell module of solar powered aircraft Ultralight according to claim 6, feature exist
In light transmittance >=90% of the skin covering of the surface (5).
8. a kind of semi-rigid solar cell module of solar powered aircraft Ultralight according to claim 1, feature exist
In the tear-proof counterdie (4) is ETFE or PET material.
9. a kind of semi-rigid solar cell module of solar powered aircraft Ultralight according to claim 8, feature exist
In the internal layer of the tear-proof counterdie (4) is equipped with glass fiber or carbon fiber wire works out grid enhancement layer.
10. a kind of semi-rigid solar cell module of solar powered aircraft Ultralight according to claim 9, feature exist
In tear-proof counterdie (4) surface is coated with EVA material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821881949.7U CN209447811U (en) | 2018-11-15 | 2018-11-15 | A kind of semi-rigid solar cell module of solar powered aircraft Ultralight |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821881949.7U CN209447811U (en) | 2018-11-15 | 2018-11-15 | A kind of semi-rigid solar cell module of solar powered aircraft Ultralight |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209447811U true CN209447811U (en) | 2019-09-27 |
Family
ID=68011513
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821881949.7U Active CN209447811U (en) | 2018-11-15 | 2018-11-15 | A kind of semi-rigid solar cell module of solar powered aircraft Ultralight |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209447811U (en) |
-
2018
- 2018-11-15 CN CN201821881949.7U patent/CN209447811U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN206976368U (en) | A kind of printing opacity flexible photovoltaic component | |
| CN101665153A (en) | Plane wing with solar battery | |
| CN207909887U (en) | A kind of flexibility crystalline silicon photovoltaic module and automobile | |
| CN101922212A (en) | Solar photovoltaic power generation roofing battery tile | |
| CN109390422A (en) | A kind of lightweight photovoltaic module | |
| CN205657072U (en) | Solar PV modules who adds anti - optical film | |
| CN203300669U (en) | Curved-surface solar cell module | |
| CN209447811U (en) | A kind of semi-rigid solar cell module of solar powered aircraft Ultralight | |
| CN202712218U (en) | Ultrathin flexible crystal silicon solar cell module | |
| CN111261739B (en) | Ultra-light flexible thin film solar cell module for near space airship | |
| CN105374890A (en) | Thinning crystalline silica solar battery assembly structure applied to stratosphere airship | |
| CN204029830U (en) | A kind of light and thin type crystal silicon solar photovoltaic module | |
| CN206164468U (en) | Monocrystalline silicon solar cells subassembly structure with reflector panel | |
| CN207353265U (en) | Monocrystaline silicon solar cell component | |
| CN112216753B (en) | Flexible thin film solar cell module for near space aircraft and preparation method | |
| CN209447823U (en) | A kind of plate and solar components | |
| CN210073879U (en) | Solar module structure, solar unmanned aerial vehicle and solar power station of two-sided electricity generation | |
| CN210693821U (en) | Double-sided photovoltaic cell assembly of solar power station | |
| EP2564429B1 (en) | Solar electric compound for curved surfaces | |
| CN107359857A (en) | Film type solar charging device | |
| CN209441681U (en) | A kind of near space unmanned plane semi-rigid solar cell array | |
| CN207602586U (en) | A kind of high solar double-glass assemblies of light utilization ratio | |
| CN209000926U (en) | Curved solar energy battery | |
| CN207082538U (en) | Light-weight photovoltaic module | |
| CN202503009U (en) | ETFE-packed crystalline silica photovoltaic assembly |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |