CN103956968A - Solar module frame - Google Patents
Solar module frame Download PDFInfo
- Publication number
- CN103956968A CN103956968A CN201410164841.6A CN201410164841A CN103956968A CN 103956968 A CN103956968 A CN 103956968A CN 201410164841 A CN201410164841 A CN 201410164841A CN 103956968 A CN103956968 A CN 103956968A
- Authority
- CN
- China
- Prior art keywords
- frame
- short
- wing aircraft
- sectional material
- long margin
- 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.)
- Pending
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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
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- Photovoltaic Devices (AREA)
Abstract
The invention discloses a solar module frame. The solar module frame is composed of a long frame, a short frame, corner brackets and sectional material flying wings. The side face of the long frame and the side face of the short frame are respectively provided with one sectional material flying wing, the sectional material flying wing of the long frame can also enter a cavity of the short frame to be fixed through the corresponding corner bracket, and the sectional material flying wing part on the side face of the long frame and the sectional material flying wing part on the side face of the short frame are spliced freely. The solar module frame is characterized in that the sectional material flying wing of the short frame enters a cavity of the long frame to be fixed through the corresponding corner bracket, and the components are connected together to form a whole. According to the solar module frame, the sectional material flying wing part on the side face of the long frame and the sectional material flying wing part on the side face of the short frame can be spliced freely, so that the components are connected together to form a whole, and the cost for riveting twice is lowered.
Description
Technical field
The present invention relates to photovoltaic solar component technology field, especially about one band all-wing aircraft aluminium alloy solar components frame.
Background technology
The installation of conventional photovoltaic solar components is all that a point 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 object of the present invention is to provide a kind of solar components frame, be that length frame multi-band has all-wing aircraft, long margin frame and short frame can free splicing, and are fixed by corner brace, can avoid length frame to occur gap, and its stability is better.
Technical scheme of the present invention is achieved in the following ways: a kind of solar components frame, by long margin frame, short frame, corner brace, section bar all-wing aircraft composition, described long margin frame and the side of short frame are equipped with section bar all-wing aircraft, 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, long margin frame, side section bar all-wing aircraft part on short frame is carried out free splicing, 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 entirety.
Structure of the present invention, 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 entirety, 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.
Brief description of the drawings
Fig. 1 is structural representation of the present invention.
Fig. 2 is the vertical view of Fig. 1.
Fig. 3 is the cavity structure figure of long margin frame.
Embodiment
Known by Fig. 1, Fig. 2, a kind of solar components frame, formed by corner brace 1, long margin frame 2, short frame 3, section bar all-wing aircraft 4, 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 entirety.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.
Being known by Fig. 3, is the cavity structure figure of long margin frame.The die cavity 2-1 of long margin frame 2 is in the time of 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 entirety.
Claims (1)
1. a solar components frame, formed by long margin frame, short frame, corner brace, section bar all-wing aircraft, described long margin frame and the side of short frame are equipped with section bar all-wing aircraft, 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, side section bar all-wing aircraft part on long margin frame, short frame is carried out free splicing, 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 entirety.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410164841.6A CN103956968A (en) | 2014-04-23 | 2014-04-23 | Solar module frame |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410164841.6A CN103956968A (en) | 2014-04-23 | 2014-04-23 | Solar module frame |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103956968A true CN103956968A (en) | 2014-07-30 |
Family
ID=51334211
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410164841.6A Pending CN103956968A (en) | 2014-04-23 | 2014-04-23 | Solar module frame |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103956968A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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
- 2014-04-23 CN CN201410164841.6A patent/CN103956968A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140730 |