CN103887592A - Plane reflection array antenna integrating solar panel and used for aircraft - Google Patents
Plane reflection array antenna integrating solar panel and used for aircraft Download PDFInfo
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- CN103887592A CN103887592A CN201410092994.4A CN201410092994A CN103887592A CN 103887592 A CN103887592 A CN 103887592A CN 201410092994 A CN201410092994 A CN 201410092994A CN 103887592 A CN103887592 A CN 103887592A
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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
Abstract
The invention discloses a plane reflection array antenna integrating a solar panel and used for an aircraft. The plane reflection array antenna comprises a back cladding layer, the solar panel and an antenna patch layer, wherein the solar panel is arranged on the back cladding layer, and the antenna patch layer is located on the solar panel. The antenna patch layer comprises a plurality of cross-shaped patch units. Phase adjustment is achieved by adjusting the size of each cross-shaped patch unit, and therefore an equiphase surface can be formed on the plane where the antenna patch layer is located. According to the plane reflection array antenna, two parts with the largest quality and space, namely a communication antenna and the solar panel, on the universe aircraft are effectively combined together, and therefore the weight and size of the universe aircraft are effectively reduced, and a great deal of design and launching cost is saved. In addition, the plane reflection array antenna can be installed on the surface of the aircraft, and conformal design of the communication antenna and the aircraft surface on the universe aircraft is achieved by fully utilizing the plane structure on the aircraft surface.
Description
Technical field
The present invention relates to a kind of antenna for aircraft, be specifically related to a kind of plane reflection array antenna of the integrated solar cell plate for aircraft.
Background technology
The carry-on solar panel in existing cosmic space and communication antenna are two independently working cells, have taken the overwhelming majority in aircraft surface space, cosmic space, and complex structure is bulky.This is that its surface is curved surface because traditional communication antenna adopts parabolic antenna (being commonly called as a pot type antenna), cannot be conformal with the surperficial planar section of cosmic space aircraft, and also cannot be conformal with solar panel.
Summary of the invention
The present invention be intended to solve at least to a certain extent above-mentioned cannot be conformal with aircraft, one of the large technical problem that takes up space or at least provide a kind of useful business to select.For this reason, the object of the invention is to propose that a kind of aircraft is conformal, the plane reflection array antenna of the large integrated solar cell plate for aircraft that takes up space.
For achieving the above object, the plane reflection array antenna of the integrated solar cell plate for aircraft of the embodiment of the present invention, comprising: back of the body coating; Solar panel, described solar panel is positioned on described back of the body coating; With antenna patch layer, described antenna patch layer is positioned on described solar panel, described antenna patch layer comprises multiple cross chip units, wherein, realize phase adjusted by the size that regulates each cross chip unit, thereby form in the plane an equiphase surface at antenna patch layer.
The plane reflection array antenna of the integrated solar cell plate for aircraft of above-described embodiment accounts for by carry-on cosmic space two that quality and space the best part---communication antenna and solar panel effectively combine, effectively reduce the weight of cosmic space aircraft, volume; Save a large amount of designs, launch cost.In addition, the present invention can be arranged on aircraft surface, makes full use of the planar structure of aircraft surface, has realized the conformalization design of communication antenna and aircraft surface on the aircraft of cosmic space.
The plane reflection array antenna of the integrated solar cell plate for aircraft of the embodiment of the present invention can also have following technical characterictic:
In one embodiment of the invention, described back of the body coating, as an output electrode of described solar panel, is also used as the ground of described antenna patch layer simultaneously.
In one embodiment of the invention, the material of described back of the body coating is silver.
In one embodiment of the invention, described multiple cross chip unit is of a size of the sub-wavelength order of magnitude.
In one embodiment of the invention, described antenna patch layer is formed on described solar panel by evaporation or photoetching process.
In one embodiment of the invention, described solar panel specifically comprises: substrate; Infrared absorption layer, described infrared absorption layer is formed on described substrate, for absorbing infrared light and being converted into electric energy; UV absorption layer, described UV absorption layer is formed on described infrared absorption layer, for absorbing ultraviolet light and being converted into electric energy; Comb electrode layer, described comb electrode layer is positioned on described UV absorption layer, as another output electrode of described solar panel; And protective clear layer, described protective clear layer is positioned on described comb electrode layer.
Additional aspect of the present invention and advantage in the following description part provide, and part will become obviously from the following description, or recognize by practice of the present invention.
Accompanying drawing explanation
Above-mentioned and/or additional aspect of the present invention and advantage accompanying drawing below combination is understood becoming the description of embodiment obviously and easily, wherein:
Fig. 1 is the perspective view of the plane reflection array antenna of the integrated solar cell plate for aircraft of the embodiment of the present invention.
Fig. 2 is the vertical view of the plane reflection array antenna of the integrated solar cell plate for aircraft shown in Fig. 1.
Fig. 3 is the cross-sectional view of the solar panel of the embodiment of the present invention.
Embodiment
Describe embodiments of the invention below in detail, the example of described embodiment is shown in the drawings, and wherein same or similar label represents same or similar element or has the element of identical or similar functions from start to finish.Be exemplary below by the embodiment being described with reference to the drawings, be intended to for explaining the present invention, and can not be interpreted as limitation of the present invention.
In description of the invention, it will be appreciated that, term " " center ", " longitudinally ", " laterally ", " length ", " width ", " thickness ", " on ", D score, " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", " outward ", " clockwise ", orientation or the position relationship of indications such as " counterclockwise " are based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, rather than device or the element of indication or hint indication must have specific orientation, with specific orientation structure and operation, therefore can not be interpreted as limitation of the present invention.
In addition, term " first ", " second " be only for describing object, and can not be interpreted as indication or hint relative importance or the implicit quantity that indicates indicated technical characterictic.Thus, one or more these features can be expressed or impliedly be comprised to the feature that is limited with " first ", " second ".In description of the invention, the implication of " multiple " is two or more, unless otherwise expressly limited specifically.
In the present invention, unless otherwise clearly defined and limited, the terms such as term " installation ", " being connected ", " connection ", " fixing " should be interpreted broadly, and for example, can be to be fixedly connected with, and can be also to removably connect, or connect integratedly; Can be mechanical connection, can be also electrical connection; Can be to be directly connected, also can indirectly be connected by intermediary, can be the connection of two element internals.For the ordinary skill in the art, can understand as the case may be above-mentioned term concrete meaning in the present invention.
Fig. 1 is the perspective view of the plane reflection array antenna of the integrated solar cell plate for aircraft of the embodiment of the present invention.Fig. 2 is the vertical view of the plane reflection array antenna of the integrated solar cell plate for aircraft shown in Fig. 1.As depicted in figs. 1 and 2, the plane reflection array antenna of the integrated solar cell plate for aircraft of the embodiment of the present invention, can comprise following part: the back of the body coating 10, solar panel 20 and antenna patch layer 30.Wherein solar panel 20 is positioned on back of the body coating 10.Antenna patch layer 30 is positioned on solar panel 20.Antenna patch layer 30 comprises multiple cross chip units 301.Wherein, realize phase adjusted by the size (regulating the length of the cross minor matters in cross chip unit 301) that regulates each cross chip unit 301, thereby form in the plane an equiphase surface at antenna patch layer 30.
As from the foregoing, the present invention accounts for by carry-on cosmic space two that quality and space the best part---communication antenna and solar panel effectively combine, and effectively reduces the weight of cosmic space aircraft, volume; Save a large amount of designs, launch cost.In addition, the present invention can be arranged on aircraft surface, makes full use of the planar structure of aircraft surface, has realized the conformalization design of communication antenna and aircraft surface on the aircraft of cosmic space.
It should be noted that, in the present invention, adopt and account for the less cross chip unit 301 of surface area, can guarantee that solar panel 20 decrease in efficiency degree are little.Also it should be noted that, solar panel 20 has served as the dielectric layer of antenna patch layer 30, and aircraft is at ordinary times in the large cosmic space of high radiation, the temperature difference, and the material character of solar panel 20 is stable, antijamming capability is strong, because of but one preferably select.And it should be noted that, solar panel 20 of the present invention and the antenna patch layer 30 with cross chip unit 301 are not subject to size restrictions, and the size that can design is compared with not increasing greatly and substantially design complexities.
In one embodiment of the invention, back of the body coating 10, as an output electrode of solar panel 10, is also used as the ground of antenna patch layer 30 simultaneously.
In one embodiment of the invention, the material of back of the body coating 10 is silver.Silver has advantages of good conductivity.
In one embodiment of the invention, multiple cross chip units 301 are of a size of the sub-wavelength order of magnitude.Sub-wavelength cell size can effectively reduce and damage the impact of medium on cell signal amplitude.
In one embodiment of the invention, antenna patch layer 30 is formed on solar panel 20 by evaporation or photoetching process.
In one embodiment of the invention, as shown in Figure 3, solar panel 20 specifically can comprise: substrate 201, infrared absorption layer 202, UV absorption layer 203, comb electrode layer 204 and protective clear layer 205.Substrate 201 can be silicon substrate or germanium substrate.Infrared absorption layer 202 is formed on substrate 201, for absorbing infrared light and being converted into electric energy.The material of infrared absorption layer 202 can select main absorption bands be infrared light semi-conducting material for example GaAs doping indium, etc. UV absorption layer 203 be formed on infrared absorption layer 202, for absorbing ultraviolet light and being converted into electric energy.It is for example gallium indium phosphorus etc. of semi-conducting material of ultraviolet light that the material of UV absorption layer 203 can be selected main absorption bands.Comb electrode layer 204 is positioned on UV absorption layer 203, as another output electrode of solar panel 20.Protective clear layer 205 is positioned on comb electrode layer 204, plays a protective role.The material of protective clear layer 205 is selected toughened glass conventionally.Antenna patch layer 30 is arranged on this protective clear layer 205.
In the description of this specification, the description of reference term " embodiment ", " some embodiment ", " example ", " concrete example " or " some examples " etc. means to be contained at least one embodiment of the present invention or example in conjunction with specific features, structure, material or the feature of this embodiment or example description.In this manual, the schematic statement of above-mentioned term is not necessarily referred to identical embodiment or example.And specific features, structure, material or the feature of description can be with suitable mode combination in any one or more embodiment or example.
Although illustrated and described embodiments of the invention above, be understandable that, above-described embodiment is exemplary, can not be interpreted as limitation of the present invention, those of ordinary skill in the art can change above-described embodiment within the scope of the invention in the situation that not departing from principle of the present invention and aim, modification, replacement and modification.
Claims (6)
1. for a plane reflection array antenna for the integrated solar cell plate of aircraft, it is characterized in that, comprising:
Back of the body coating;
Solar panel, described solar panel is positioned on described back of the body coating; With
Antenna patch layer, described antenna patch layer is positioned on described solar panel, and described antenna patch layer comprises multiple cross chip units, wherein, realize phase adjusted by the size that regulates each cross chip unit, thereby form in the plane an equiphase surface at antenna patch layer.
2. the plane reflection array antenna of the integrated solar cell plate for aircraft as claimed in claim 1, is characterized in that, described back of the body coating, as an output electrode of described solar panel, is also used as the ground of described antenna patch layer simultaneously.
3. the plane reflection array antenna of the integrated solar cell plate for aircraft as claimed in claim 1, is characterized in that, the material of described back of the body coating is silver.
4. the plane reflection array antenna of the integrated solar cell plate for aircraft as claimed in claim 1, is characterized in that, described multiple cross chip units are of a size of the sub-wavelength order of magnitude.
5. the plane reflection array antenna of the integrated solar cell plate for aircraft as claimed in claim 1, is characterized in that, described antenna patch layer is formed on described solar panel by evaporation or photoetching process.
6. the plane reflection array antenna of the integrated solar cell plate for aircraft as claimed in claim 1, is characterized in that, described solar panel specifically comprises:
Substrate;
Infrared absorption layer, described infrared absorption layer is formed on described substrate, for absorbing infrared light and being converted into electric energy;
UV absorption layer, described UV absorption layer is formed on described infrared absorption layer, for absorbing ultraviolet light and being converted into electric energy;
Comb electrode layer, described comb electrode layer is positioned on described UV absorption layer, as another output electrode of described solar panel; With
Protective clear layer, described protective clear layer is positioned on described comb electrode layer.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410092994.4A CN103887592A (en) | 2014-03-13 | 2014-03-13 | Plane reflection array antenna integrating solar panel and used for aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410092994.4A CN103887592A (en) | 2014-03-13 | 2014-03-13 | Plane reflection array antenna integrating solar panel and used for aircraft |
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| CN103887592A true CN103887592A (en) | 2014-06-25 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105514622A (en) * | 2015-12-28 | 2016-04-20 | 中国科学院国家空间科学中心 | Four-frequency microstrip reflective array antenna |
| CN106571407A (en) * | 2016-10-11 | 2017-04-19 | 南京奥依菲光电科技有限公司 | Micro nano antenna solar cell with solar energy gathering features and working method |
| CN107274649A (en) * | 2017-06-21 | 2017-10-20 | 国网山东省电力公司诸城市供电公司 | A kind of self-organization of network formula power information central system and method |
| CN107910655A (en) * | 2017-11-08 | 2018-04-13 | 中国电子科技集团公司第三十八研究所 | Conformal antenna and wing and Helios based on solar cell |
| CN108493607A (en) * | 2018-03-16 | 2018-09-04 | 中国电子科技集团公司第三十八研究所 | A kind of active antenna and solar cell integrate big array |
| CN108682941A (en) * | 2018-06-07 | 2018-10-19 | 电子科技大学 | Solar energy circular polarized antenna |
| CN113991300A (en) * | 2021-12-28 | 2022-01-28 | 成都频岢微电子有限公司 | Double-layer transmission array antenna based on Yelu cold cross and implementation method thereof |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105514622A (en) * | 2015-12-28 | 2016-04-20 | 中国科学院国家空间科学中心 | Four-frequency microstrip reflective array antenna |
| CN105514622B (en) * | 2015-12-28 | 2018-11-13 | 中国科学院国家空间科学中心 | A kind of four frequency microstrip reflection array antennas |
| CN106571407A (en) * | 2016-10-11 | 2017-04-19 | 南京奥依菲光电科技有限公司 | Micro nano antenna solar cell with solar energy gathering features and working method |
| CN107274649A (en) * | 2017-06-21 | 2017-10-20 | 国网山东省电力公司诸城市供电公司 | A kind of self-organization of network formula power information central system and method |
| CN107274649B (en) * | 2017-06-21 | 2019-06-28 | 国网山东省电力公司诸城市供电公司 | A kind of self-organization of network formula power information central system and method |
| CN107910655A (en) * | 2017-11-08 | 2018-04-13 | 中国电子科技集团公司第三十八研究所 | Conformal antenna and wing and Helios based on solar cell |
| CN107910655B (en) * | 2017-11-08 | 2020-06-30 | 中国电子科技集团公司第三十八研究所 | Conformal antenna and wing and solar aircraft based on solar cell |
| CN108493607A (en) * | 2018-03-16 | 2018-09-04 | 中国电子科技集团公司第三十八研究所 | A kind of active antenna and solar cell integrate big array |
| CN108493607B (en) * | 2018-03-16 | 2021-02-05 | 中国电子科技集团公司第三十八研究所 | Active antenna and solar cell integrated large array |
| CN108682941A (en) * | 2018-06-07 | 2018-10-19 | 电子科技大学 | Solar energy circular polarized antenna |
| CN113991300A (en) * | 2021-12-28 | 2022-01-28 | 成都频岢微电子有限公司 | Double-layer transmission array antenna based on Yelu cold cross and implementation method thereof |
| CN113991300B (en) * | 2021-12-28 | 2022-05-10 | 成都频岢微电子有限公司 | Double-layer transmission array antenna based on Yelu scattering cross and implementation method thereof |
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Application publication date: 20140625 |
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