CN203800876U - Solar assembly frame provided with flying wing aluminium alloy - Google Patents
Solar assembly frame provided with flying wing aluminium alloy Download PDFInfo
- Publication number
- CN203800876U CN203800876U CN201420179479.5U CN201420179479U CN203800876U CN 203800876 U CN203800876 U CN 203800876U CN 201420179479 U CN201420179479 U CN 201420179479U CN 203800876 U CN203800876 U CN 203800876U
- Authority
- CN
- China
- Prior art keywords
- frame
- section bar
- wing aircraft
- long margin
- aluminium alloy
- 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.)
- Expired - Fee Related
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
- Joining Of Building Structures In Genera (AREA)
Abstract
The utility model discloses a solar assembly frame provided with flying wing aluminium alloy. The solar assembly frame is composed of long frames (2), short frames (3), corner pieces (1), and section bar flying wings (4). Side surfaces of the long frames (2) and the short frames (3) are all provided with the section bar flying wings (4). The solar assembly frame is characterized in that the section bar flying wings (4) of the short frames (3) enter section cavities (2-1) of the long frames (2) through the corner pieces (1) for fixation so as to make assemblies are connected together to form an integral body. According to the structure of the utility model, the side section bar flying wing portions on the long frames and the short frames can be jointed freely so as to make the assemblies are connected together to form an integral body, so the twice riveting cost can be reduced.
Description
Technical field
The utility model relates to photovoltaic solar component technology field, especially about a kind of band all-wing aircraft aluminium alloy solar components frame.
Background technology
The installation of conventional photovoltaic solar components is all that a minute monolithic is arranged separately on retort stand and combines, and its relevance is poor like this, and energy utilization rate reduces, and can not form unified conduction mode.Now, handle component frame re-starts design, increases the all-wing aircraft part that it assembles mutually, makes that integraty is installed stronger, and conductibility is better, installs more convenient.
Summary of the invention
For above problem, the purpose of this utility model is to provide a kind of band all-wing aircraft aluminium alloy solar components frame, is that length frame multi-band has all-wing aircraft, long margin frame and short frame can free splicing, and be fixed by corner brace, can avoid length frame to occur gap, its stability is better.
The technical solution of the utility model is achieved in the following ways: a kind of band all-wing aircraft aluminium alloy solar components frame, by long margin frame, short frame, corner brace, section bar all-wing aircraft, formed, described long margin frame and the side of short frame are equipped with section bar all-wing aircraft, it is characterized in that: the die cavity that the section bar all-wing aircraft of described short frame enters long margin frame by corner brace is fixed, assembly and assembly are linked together and form an integral body.
The die cavity that the section bar all-wing aircraft of described long margin frame also can enter short frame by corner brace is fixed, and the side section bar all-wing aircraft on long margin frame, short frame partly carries out free splicing.
The utility model structure, side section bar all-wing aircraft part on long margin frame, short frame is freely assembled, assembly and assembly are linked together and form an integral body, can estimate on-the-spot environment free splicing and install, the convenient electric installation of installing, the position of length frame also can freely change, and does not affect its presentation quality.Solar energy is in assembling, and the die cavity that the corner brace of use short frame enters long margin frame is fixed, and reduces the cost of twice riveted.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Fig. 2 is the A partial enlarged drawing of Fig. 1.
Fig. 3 is the structural representation of long margin frame.
Fig. 4 is the structural representation that assembly connects with assembly.
Fig. 5 is the B partial enlarged drawing of Fig. 4.
Embodiment
By Fig. 1, Fig. 2, known, a kind of band all-wing aircraft aluminium alloy solar components frame, by corner brace 1, long margin frame 2, short frame 3, section bar all-wing aircraft 4, formed, described long margin frame 2 and the side of short frame 3 are equipped with section bar all-wing aircraft 4, the die cavity that the section bar all-wing aircraft of short frame 3 enters long margin frame 2 by corner brace 1 is fixed, and assembly and assembly is linked together and forms an integral body.
By Fig. 3, known, the die cavity that the section bar all-wing aircraft of long margin frame 2 also can enter short frame 3 by corner brace 1 is fixed by splicing part 5, and side section bar all-wing aircraft 4 parts on long margin frame 2, short frame 3 can be carried out free splicing.The die cavity 2-1 of long margin frame 2 is when assembling, and the die cavity 2-1 that the side section bar all-wing aircraft 4 on short frame 3 enters long margin frame 2 by corner brace 1 is fixed, and assembly and assembly is linked together and forms an integral body.
By Fig. 4, Fig. 5, being known, is the structural representation that assembly connects with assembly.Between assembly and assembly, be to connect by splicing part 5.
The utility model, is used the all-wing aircraft on long limit or minor face partly to carry out free splicing at building-site, easy to assembly, can reduce the corresponding cost of twice riveted, does not also need specific purpose tool.Particularly, in work high above the ground, do not need to carry heavy erecting tools, reduce dangerous generation.Also can be according to freely the arrange in pairs or groups splicing mounting means of assembly of on-the-spot environment position.The position of length frame also can freely change, and environment position adaptive faculty is more intense, when roof is installed, also can remove keel from especially, directly with length frame, fixes assembly, simplifies complicated traditional mounting means.
Claims (2)
1. be with all-wing aircraft aluminium alloy solar components frame for one kind, by long margin frame (2), short frame (3), corner brace (1), section bar all-wing aircraft (4), formed, the side of described long margin frame (2) and short frame (3) is equipped with section bar all-wing aircraft (4), it is characterized in that: the die cavity (2-1) that the section bar all-wing aircraft (4) of described short frame (3) enters long margin frame (2) by corner brace (1) is fixed, assembly and assembly are linked together and form an integral body.
2. a kind of band all-wing aircraft aluminium alloy solar components frame according to claim 1, it is characterized in that: the die cavity that the section bar all-wing aircraft (4) of described long margin frame (2) also can enter short frame (3) by corner brace (1) is fixed, side section bar all-wing aircraft (4) part on long margin frame (2), short frame (3) is carried out free splicing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420179479.5U CN203800876U (en) | 2014-04-15 | 2014-04-15 | Solar assembly frame provided with flying wing aluminium alloy |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420179479.5U CN203800876U (en) | 2014-04-15 | 2014-04-15 | Solar assembly frame provided with flying wing aluminium alloy |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203800876U true CN203800876U (en) | 2014-08-27 |
Family
ID=51383060
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420179479.5U Expired - Fee Related CN203800876U (en) | 2014-04-15 | 2014-04-15 | Solar assembly frame provided with flying wing aluminium alloy |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203800876U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105720904A (en) * | 2014-12-01 | 2016-06-29 | 中电电气(上海)太阳能科技有限公司 | Anti-PID (Potential Induced Degradation) plastic frame photovoltaic module |
| CN107093981A (en) * | 2017-06-21 | 2017-08-25 | 奥特斯维能源（太仓）有限公司 | A kind of photovoltaic overlap component |
-
2014
- 2014-04-15 CN CN201420179479.5U patent/CN203800876U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105720904A (en) * | 2014-12-01 | 2016-06-29 | 中电电气(上海)太阳能科技有限公司 | Anti-PID (Potential Induced Degradation) plastic frame photovoltaic module |
| CN105720904B (en) * | 2014-12-01 | 2018-06-19 | 中电电气(上海)太阳能科技有限公司 | A kind of plastic frame photovoltaic module of anti-PID |
| CN107093981A (en) * | 2017-06-21 | 2017-08-25 | 奥特斯维能源（太仓）有限公司 | A kind of photovoltaic overlap component |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140827 Termination date: 20210415 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |