CN102163633A - Space solar energy utilization method - Google Patents
Space solar energy utilization method Download PDFInfo
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- CN102163633A CN102163633A CN2010105914171A CN201010591417A CN102163633A CN 102163633 A CN102163633 A CN 102163633A CN 2010105914171 A CN2010105914171 A CN 2010105914171A CN 201010591417 A CN201010591417 A CN 201010591417A CN 102163633 A CN102163633 A CN 102163633A
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- solar energy
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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
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Abstract
The invention discloses a space solar energy utilization method, which can effectively utilize space solar energy on a large scale. A solar collection and utilization device in a satellite or an airship or a high-altitude aircraft is supported or fixed or adjusted through a network bracket which accords with the needed specified shape and consists of pipelines filled with gas or liquid. Planar objects for receiving solar energy in the solar collection and utilization device are attached to or fused on the network of the pipelines filled with gas or liquid; the planar objects can be reflective gathering films for sunlight; the sunlight subjected to reflective gathering is converted into parallel light and is projected onto other satellites or airships or various aircrafts or ground receiving stations in a form of the parallel light; the projected objects generate power or continuously transmit the parallel light; if more than one solar collection and utilization device is arranged, the plurality of solar collection and utilization devices at different positions can project the light onto the same projected object.
Description
Affiliated technical field
The present invention relates to a kind of space solar energy and utilize method.
Background technology
At present, the solar energy of collecting based on the engineering complexity that huge solar panel is installed at space and difficulty and space is difficult to pass back the earth, now also space solar energy is not effectively utilized method on a large scale.
Summary of the invention
In order to overcome the technical problem of utilizing space solar energy at present, the invention provides a kind of space solar energy and utilize method, this method can effectively be utilized space solar energy on a large scale.
The technical solution adopted in the present invention is:
The network type support that solar energy collecting use device in satellite or airship or the high-altitude airborne vehicle constitutes by the pipeline with inflation or topping up that meets its required given shape is realized the support of shape or the fixing or regulating of its position of described solar energy collecting use device.
The planar thing of the reception solar energy in the described solar energy collecting use device depends on or is blended on the piping network of described inflation or topping up.
Described solar energy collecting use device both can be a directly Blast Furnace Top Gas Recovery Turbine Unit (TRT) such as solar panel and framework thereof or solar power generation film, also can be the optical device of reflection, optically focused etc., as the sunlight reflectance coating etc.
Space solar energy of the present invention utilizes method, though " space " two words are arranged in its title, but it has also comprised and has faced space or high-altitude, its light weight and the huge characteristics of area also make it face the space or high aerial application has produced tangible beneficial effect, space environment faces space or high-altitude because effect weightless and its solar energy utilization of vacuum event is better than, but the situation of space generally needs bigger cost and the technology of Geng Gao to support, thus the present invention do not repel its apply to face the space or atmospheric in the air.
Among the present invention, the described network type support justice that constitutes with the pipeline of inflation or topping up is called piping network.
Among the present invention, the planar thing of described reception solar energy is the object that accounts for main area in the solar energy collecting use device, for example solar panel or solar power generation film etc.Described reception solar energy is meant its contact sunlight and can makes its place of himself or follow-up phase utilize the energy of these sunlights, and it can be the object of the direct generation of electricity, also can be the optical device etc. of reflection, optically focused.The supporting way of the piping network of inflation of the present invention or topping up also not only is confined to be adopted by described planar thing, the miscellaneous part of described solar energy collecting use device also can adopt this supporting way, for example, if solar panel, then the link between the cell panel also can adopt this mode, depends on described piping network such as the profile or the support of these parts.
A kind of space solar energy of the present invention utilizes method: the solar energy collecting use device in satellite or airship or the airborne vehicle constitutes the support of shape or the fixing or regulating of its position that support is realized described solar energy collecting use device by the pipeline with inflation or topping up; The planar thing of the reception solar energy in the described solar energy collecting use device is the film that depends on or be blended on the inflation or the pipeline of topping up.
As a kind of preferred version, described planar thing of the present invention is that sun reflection of light converges film.
The coat of metal that can plate a floor height reflection characteristic at the inner concave arc surface of flexible film realizes that this sun reflection of light converges film.At this moment, thus can make described piping network become a sphere net after fully launching makes attached reflection thereon converge film to become spherical mirror on the whole.
As further preferred version, there is device of solar generating the center of converging of converging the pairing sunlight of film with described sun reflection of light.Solar panel etc. is for example arranged.
As another further preferred version, converge the Optical devices that the sunlight of center handlebar through converging is converted into the light beam of directional light that converge of the pairing sunlight of film with described sun reflection of light.
For example, described Optical devices are the speculums that converge the reflecting surface evagination that film matches with the described reflection of reflecting surface indent, and described reflection this moment is converged has a loophole or euphotic zone to allow described directional light pass through in the film.In addition, described Optical devices also can be to converge concavees lens that film matches etc. with described reflection.
Described directional light among the present invention be not only index learn definitely exactly parallel on the meaning; It generally is to converge the opposing parallel of being observed on the analogous yardstick of yardstick of film with described reflection; The light beam of described directional light still might be observed tangible beam spread when propagating in this world, the present invention does not get rid of this situation, and certainly, high more its capacity usage ratio of the depth of parallelism is also just high more.
As a kind of preferred version, the present invention proposes: position or the angle of adjusting the solar energy collecting use device on satellite or airship or the airborne vehicle, making it reflect the sunlight form with the sun directional light through converging after described Optical devices are converted into directional light that converges is projeced on other satellite or airship or all kinds of aircraft or grounded receiving station that is mated, above-mentioned is handled the light that it received by missile, and the mode of described processing can comprise generating or continue to be transmitted in the mode of directional light again; If the described light that it received the generating by missile then describedly had device of solar generating on the missile; The light that it received is continued to transmit the then described Optical devices that can make directional light controlled change direction that had on the missile again in the mode of directional light by missile as if described; If have, then can make the described solar energy collecting use device of a plurality of diverse locations the sun directional light that it converged is projeced into same described by on the missile more than one different satellites or the described solar energy collecting use device on airship or the airborne vehicle.
Described other satellite or airship or all kinds of aircraft or grounded receiving station are described by missile.Described all kinds of aircraft contains balloon, dirigible and aircraft etc.Described device of solar generating can be solar panel or solar film battery etc.The described Optical devices that make directional light controlled change direction can be by being that the device of core is realized with level crossing that can controlled rotation.Described a plurality of different described solar energy collecting use device is projeced into its sun directional light through converging same described by in the situation of missile, the solar energy collecting use device that it is related and formed a solar energy utilization system by missile; A plurality of such solar energy that system obtained are if put together with light or electric form, and then these systems have just constituted a bigger solar energy utilization system.
As a kind of preferred version, described planar thing of the present invention is the film that is made of solar film battery.
As a kind of preferred version, described solar energy collecting use device part is made with aeroge.The main body of the described planar thing made from aeroge for example.
As a kind of preferred version, satellite or airship after entering space or airborne vehicle fly to remove to the high-altitude constraint to described planar thing, be loaded with the material that gas maybe can produce gas on described satellite or airship or the airborne vehicle, by inflation of its described pipeline or piping network or topping up are launched into default required geometry in particular to described planar thing.
The invention has the beneficial effects as follows that the present invention makes the solar energy collecting use device of satellite or airship or airborne vehicle have huge area to be used for collecting under the very little situation of very light in weight or quality and utilizes solar energy, it can effectively utilize space solar energy on a large scale.
Description of drawings
The present invention is further described below in conjunction with drawings and Examples.
Fig. 1 is a volume rendering schematic diagram of the present invention.
1. satellites or airship or high-altitude airborne vehicle among the figure, 2. the solar energy collecting use device of satellite or airship or high-altitude airborne vehicle, 3. piping network, 4. planar thing in the solar energy collecting use device or sun reflection of light converge film, 5. light, 6. by satellite that throw or low orbit or airship or all kinds of aircraft, 7. grounded receiving station.
Embodiment
Among the embodiment shown in the figure, the solar energy collecting use device (2) in satellite or airship or the airborne vehicle (1) constitutes the support of shape or the fixing or regulating of its position that network bracket (3) is realized described solar energy collecting use device (2) by the pipeline with inflation or topping up.The planar thing of the reception solar energy in the described solar energy collecting use device (2) is the film (4) that depends on or be blended on the inflation or the pipeline (3) of topping up.Above-mentioned space solar energy utilizes the solar energy collecting use device (2) in the method part to make with aeroge.Satellite or airship are being entered the orbit and stable back or airborne vehicle fly to the high-altitude, open the door that the planar thing (4) in the solar energy collecting use device that sun reflection of light converges film etc. is housed, be distributed with piping network (3) on the described planar thing (4), be loaded with material or liquid that Compressed Gas maybe can produce gas on satellite or airship or the airborne vehicle, can be launched into required regular geometric shapes to described planar thing (4) by mode to its piping network (3) inflation or topping up.Adjust the position or the angle of the solar energy collecting use device (2) on satellite or airship or the airborne vehicle (1), making it reflect the sunlight form with the sun directional light (5) through converging after described Optical devices are converted into directional light (5) that converges is projeced on other satellite or airship or all kinds of aircraft (6) or grounded receiving station (7) that is mated, above-mentioned is handled the light that it received by missile, and the mode of described processing can comprise generating or continue to be transmitted in the mode of directional light (5) again; If the described light (5) that it received the generating by missile then describedly had device of solar generating on the missile; The light (5) that it received is continued to transmit the then described Optical devices that can make directional light (5) controlled change direction that had on the missile again in the mode of directional light (5) by missile as if described; If have more than one different satellites or the described solar energy collecting use device (2) on airship or the airborne vehicle, then can make a plurality of different described solar energy collecting use devices (2) its sun directional light (5) through converging be projeced into same described by missile on.For example, in the track projection plane of above-mentioned satellite or airship (1) or near be provided with many in the air and can rest on aircraft (6) on the cloud layer and can correction position for a long time, have near above-mentioned aircraft (6) top or the close top and receive the device that utilizes the high strength sunlight, above-mentioned aircraft (6) is to solar power generation or transmission again, and aircraft or spacecraft (6) transmit back earth surface to its solar energy of collecting by modes such as cable or microwave or directional light or laser.
Claims (10)
1. a space solar energy utilizes method, it is characterized in that: the network type support that the solar energy collecting use device in satellite or airship or the high-altitude airborne vehicle constitutes by the pipeline with inflation or topping up that meets its required given shape is realized the support of shape or the fixing or regulating of its position of described solar energy collecting use device.
2. space solar energy according to claim 1 utilizes method, it is characterized in that: the planar thing of the reception solar energy in the described solar energy collecting use device depends on or is blended on the piping network of described inflation or topping up.
3. a space solar energy utilizes method, it is characterized in that: the solar energy collecting use device in satellite or airship or the airborne vehicle constitutes the support of shape or the fixing or regulating of its position that support is realized described solar energy collecting use device by the pipeline with inflation or topping up; The planar thing of the reception solar energy in the described solar energy collecting use device is the film that depends on or be blended on the inflation or the pipeline of topping up.
4. utilize method according to claim 2 or 3 described space solar energy, it is characterized in that: described planar thing is that sun reflection of light converges film.
5. space solar energy according to claim 4 utilizes method, it is characterized in that: there is device of solar generating the center of converging of converging the pairing sunlight of film with described sun reflection of light.
6. space solar energy according to claim 4 utilizes method, it is characterized in that: converge the Optical devices that the sunlight of center handlebar through converging is converted into the light beam of directional light that converge of the pairing sunlight of film with described sun reflection of light.
7. space solar energy according to claim 6 utilizes method, it is characterized in that: position or the angle of adjusting the solar energy collecting use device on satellite or airship or the airborne vehicle, making it reflect the sunlight form with the sun directional light through converging after described Optical devices are converted into directional light that converges is projeced on other satellite or airship or all kinds of aircraft or grounded receiving station that is mated, above-mentioned is handled the light that it received by missile, and the mode of described processing can comprise generating or continue to be transmitted in the mode of directional light again; If the described light that it received the generating by missile then describedly had device of solar generating on the missile; The light that it received is continued to transmit the then described Optical devices that can make directional light controlled change direction that had on the missile again in the mode of directional light by missile as if described; If have, then can make the described solar energy collecting use device of a plurality of diverse locations the sun directional light that it converged is projeced into same described by on the missile more than one different satellites or the described solar energy collecting use device on airship or the airborne vehicle.
8. utilize method according to claim 2 or 3 described space solar energy, it is characterized in that: described planar thing is the film that is made of solar film battery.
9. utilize method according to claim 1 or 2 or 3 described space solar energy, it is characterized in that: described its part of solar energy collecting use device is made with aeroge.
10. utilize method according to claim 2 or 3 described space solar energy, it is characterized in that: satellite or airship after entering space or airborne vehicle fly to remove to the high-altitude constraint to described planar thing, be loaded with the material that gas maybe can produce gas on described satellite or airship or the airborne vehicle, by inflation of its described pipeline or piping network or topping up are launched into default required geometry in particular to described planar thing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105914171A CN102163633A (en) | 2009-12-07 | 2010-12-07 | Space solar energy utilization method |
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910229003 | 2009-12-07 | ||
| CN200910229003.1 | 2009-12-07 | ||
| CN2010105914171A CN102163633A (en) | 2009-12-07 | 2010-12-07 | Space solar energy utilization method |
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| Publication Number | Publication Date |
|---|---|
| CN102163633A true CN102163633A (en) | 2011-08-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2010105914171A Pending CN102163633A (en) | 2009-12-07 | 2010-12-07 | Space solar energy utilization method |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103236804A (en) * | 2013-04-27 | 2013-08-07 | 中国空间技术研究院 | Spherical inflatable space solar power station |
| CN103868246A (en) * | 2014-02-24 | 2014-06-18 | 中国空间技术研究院 | Power density adjustable film reflecting and condensing space solar energy collecting station |
| CN106628262A (en) * | 2015-05-17 | 2017-05-10 | 邓鑫 | Multi-mode driven carrying system applicable to space flight |
| CN107738762A (en) * | 2017-09-15 | 2018-02-27 | 深圳市盛路物联通讯技术有限公司 | Equipment adjusting method and Related product |
| CN116841000A (en) * | 2023-08-31 | 2023-10-03 | 中国科学院长春光学精密机械与物理研究所 | Anti-optical imaging interference station |
-
2010
- 2010-12-07 CN CN2010105914171A patent/CN102163633A/en active Pending
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103236804A (en) * | 2013-04-27 | 2013-08-07 | 中国空间技术研究院 | Spherical inflatable space solar power station |
| CN103236804B (en) * | 2013-04-27 | 2015-04-22 | 中国空间技术研究院 | Spherical inflatable space solar power station |
| CN103868246A (en) * | 2014-02-24 | 2014-06-18 | 中国空间技术研究院 | Power density adjustable film reflecting and condensing space solar energy collecting station |
| CN103868246B (en) * | 2014-02-24 | 2016-06-01 | 中国空间技术研究院 | The film reflective light concentrating type space solar cumulative station that a kind of power density is adjustable |
| CN106628262A (en) * | 2015-05-17 | 2017-05-10 | 邓鑫 | Multi-mode driven carrying system applicable to space flight |
| CN107738762A (en) * | 2017-09-15 | 2018-02-27 | 深圳市盛路物联通讯技术有限公司 | Equipment adjusting method and Related product |
| CN116841000A (en) * | 2023-08-31 | 2023-10-03 | 中国科学院长春光学精密机械与物理研究所 | Anti-optical imaging interference station |
| CN116841000B (en) * | 2023-08-31 | 2023-10-31 | 中国科学院长春光学精密机械与物理研究所 | Anti-optical imaging interference station |
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Application publication date: 20110824 |