CN117544072A - Light-weight 'cable-rod-beam' structure for supporting space Fresnel lens condensing system - Google Patents
Light-weight 'cable-rod-beam' structure for supporting space Fresnel lens condensing system Download PDFInfo
- Publication number
- CN117544072A CN117544072A CN202311303389.2A CN202311303389A CN117544072A CN 117544072 A CN117544072 A CN 117544072A CN 202311303389 A CN202311303389 A CN 202311303389A CN 117544072 A CN117544072 A CN 117544072A
- Authority
- CN
- China
- Prior art keywords
- fresnel lens
- cable
- solar cell
- pod
- array
- 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.)
- Granted
Links
- 238000003491 array Methods 0.000 claims description 17
- 230000002093 peripheral effect Effects 0.000 claims description 10
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 229920000271 Kevlar® Polymers 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- 239000004761 kevlar Substances 0.000 claims description 3
- 239000000758 substrate Substances 0.000 claims description 3
- 230000005494 condensation Effects 0.000 claims 1
- 238000009833 condensation Methods 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 11
- 230000017525 heat dissipation Effects 0.000 description 8
- 235000010627 Phaseolus vulgaris Nutrition 0.000 description 4
- 244000046052 Phaseolus vulgaris Species 0.000 description 4
- 238000004458 analytical method Methods 0.000 description 4
- 230000001360 synchronised effect Effects 0.000 description 4
- 230000003287 optical effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000036544 posture Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000001687 destabilization Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
- F24S23/00—Arrangements for concentrating solar-rays for solar heat collectors
- F24S23/30—Arrangements for concentrating solar-rays for solar heat collectors with lenses
- F24S23/31—Arrangements for concentrating solar-rays for solar heat collectors with lenses having discontinuous faces, e.g. Fresnel lenses
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
- F24S25/00—Arrangement of stationary mountings or supports for solar heat collector modules
- F24S25/50—Arrangement of stationary mountings or supports for solar heat collector modules comprising elongate non-rigid elements, e.g. straps, wires or ropes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F24—HEATING; RANGES; VENTILATING
- F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
- F24S25/00—Arrangement of stationary mountings or supports for solar heat collector modules
- F24S25/60—Fixation means, e.g. fasteners, specially adapted for supporting solar heat collector modules
- F24S25/63—Fixation means, e.g. fasteners, specially adapted for supporting solar heat collector modules for fixing modules or their peripheral frames to supporting elements
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
- H02S20/00—Supporting structures for PV modules
- H02S20/20—Supporting structures directly fixed to an immovable object
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
- H02S40/00—Components or accessories in combination with PV modules, not provided for in groups H02S10/00 - H02S30/00
- H02S40/20—Optical components
- H02S40/22—Light-reflecting or light-concentrating means
Landscapes
- Engineering & Computer Science (AREA)
- Sustainable Development (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Sustainable Energy (AREA)
- Thermal Sciences (AREA)
- Physics & Mathematics (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention discloses a lightweight 'cable-rod-beam' structure for supporting a space Fresnel lens condensing system, which comprises a satellite platform for adjusting and controlling a sun posture, wherein the satellite platform is fixedly connected with a Fresnel lens array and a solar cell array through a rope structure, the Fresnel lens array is positioned right above the solar cell array, and the Fresnel lens array and the solar cell array are connected with a pod supporting structure for supporting and unfolding. The light-weight design of the condensing system can be realized by expanding and fixing the condensing system of the Fresnel lens in the whole space through the rope and the pod rod with lighter weight, and the problems of complicated and redundant control mechanism, high control difficulty and poor structural stability in the traditional design are solved.
Description
Technical Field
The invention belongs to the technical field of light-weight 'cable-rod-beam' structure design, and relates to a light-weight 'cable-rod-beam' structure for supporting a space Fresnel lens condensing system.
Background
Compared with the novel energy sources such as nuclear energy, wind energy, tidal energy and the like, the solar energy has the characteristics of stability, safety and no limitation of terrains. Space solar power plants (Space Solar Power Station), which are a complex energy solution, place solar panels or other energy collection devices in space, collect solar radiant energy and convert it, transmit it to the earth or for space missions.
Since the us scientist peter glazedoctor proposed a space solar power station in 1968, scholars around the world have proposed various space solar power station schemes for collecting space solar energy and delivering it to the earth by using microwave transmission technology. To date, many representative non-concentrating and concentrating space solar power plant approaches have been proposed by research teams represented by the united states. The non-concentrating space solar power station scheme adopts a common solar panel design, so that sunlight directly irradiates the surface of the solar panel. Due to the characteristics of simple design, high reliability and the like, corresponding space solar power station schemes are proposed by the space technical institute of America, japan and China. The scheme of the concentrating space solar power station is to focus sunlight on a solar cell panel by utilizing optical devices such as a concentrating reflector or a concentrating Fresnel lens, so that more energy is collected in a unit area, the area of the solar cell is reduced, and the power generation capacity of the space solar power station is increased. Because of the characteristics of high energy collection capability, miniaturized design, high adaptability to space complex working conditions and the like, the concentrating space solar power station scheme becomes a research hot spot in recent years, and the representative scheme is an SPS-ALPHA scheme, a symmetrical secondary concentrating scheme and a space solar power station-OMEGA scheme of Baoyan university team of Western electronic technology university in China.
Aiming at the non-concentrating space solar power station scheme, the solar sailboard system is used as a key component of the non-concentrating space solar power station scheme, and the overall configuration of the solar sailboard system passes through several important development stages of star surface patch type, paddle type, rigid semi-rigid expandable type and large flexible expandable type. However, with the design and application of large space vehicles such as space stations and space telescopes, non-concentrating solar array systems require relatively large areas to collect sufficient energy, which results in increased coverage areas of solar cells, dramatically increasing the overall cost of the system.
The condensing space solar power station scheme effectively improves the condensing capacity of the space solar power station system and reduces the cost by means of optical devices such as a condensing reflector or a condensing Fresnel lens. For this reason, a condensing subsystem composed of optical devices such as a condensing mirror or a condensing fresnel lens is a key part in the design of the whole space solar power station scheme. However, the mass of the condensing subsystem increases due to the presence of a large number of optics, further increasing the control difficulty of the overall system.
Disclosure of Invention
The invention aims to provide a lightweight 'rope-rod-beam' structure for supporting a space Fresnel lens condensing system, which utilizes a rope and a pod rod with lighter mass to expand and fix the whole space Fresnel lens condensing system, can realize the lightweight design of the condensing system and solves the problems of complex redundant control mechanism, large control difficulty and poor structural stability in the traditional design.
The technical scheme includes that the lightweight 'rope-rod-beam' structure of the Fresnel lens condensing system in the supporting space comprises a satellite platform for adjusting and controlling the daily attitude, the satellite platform is fixedly connected with a Fresnel lens array and a solar cell array through a rope structure, the Fresnel lens array is located right above the solar cell array, and the Fresnel lens array and the solar cell array are connected with a pod supporting structure for supporting and unfolding.
The invention is also characterized in that:
the rope structure comprises an upper stay rope, a middle rope and a lower stay rope, wherein one ends of the upper stay rope and the lower stay rope are uniformly connected with the satellite platform, the other end of the upper stay rope is connected with the Fresnel lens array, the other end of the lower stay rope is connected with the solar cell array, one end of the middle rope is connected with the Fresnel lens array, and the other end of the middle rope is connected with the solar cell array.
The upper inhaul cable and the lower inhaul cable are Kevlar ropes.
The pod supporting structure comprises an upper pod supporting rod and a lower pod supporting rod, wherein the upper pod supporting rod is connected with the Fresnel lens array, and the lower pod supporting rod is connected with the solar cell array.
The upper bean pod support rod and the lower bean pod support rod are made of carbon fiber and hollow rods.
The Fresnel lens array comprises a plurality of Fresnel lenses which are arranged in an array, the transversely adjacent Fresnel lenses are connected in a matched mode through hinges a, the longitudinally adjacent Fresnel lenses are fixedly connected, each row of first Fresnel lenses are connected with the satellite platform through a peripheral fixed truss, and each row of tail Fresnel lenses are connected with the rope structure and the pod supporting structure in a matched mode.
The solar cell array comprises a plurality of cell modules which are arranged in an array, two laterally adjacent cell modules are connected through a hinge b, two longitudinally adjacent cell modules are fixedly connected, two ends of each row of cell modules are connected with peripheral inhaul cables, each row of first cell modules is connected with a satellite platform through a solar cell array frame, and each row of tail cell modules is connected with a bean pod supporting structure through a rope structure.
Each battery module comprises solar cells, the bottom of each solar cell is connected with a hollow heat dissipation truss in a bonding mode, and the inner bottom of the heat dissipation truss is connected with a heat pipe.
The bottom of the heat dissipation truss is an aluminum honeycomb substrate.
The beneficial effects of the invention are as follows:
1) The Fresnel lens array and the solar cell array can be sequentially arranged into an expandable array structure, and the Fresnel lens array and the solar cell array are very suitable for realizing and expanding a concentrating space solar power station system.
2) The solar energy tracking device is composed of a plurality of independent Fresnel lens arrays and solar cell arrays, can achieve higher light condensing efficiency and light weight, realizes sun tracking by adjusting satellite postures during in-orbit operation, and ensures continuous conversion and output of energy.
3) The invention adopts the rope, the rod and the hinge structure, can realize synchronous control of the Fresnel lens array and the solar cell array, effectively avoid a complex redundant unfolding control mechanism and simultaneously eliminate the control difficulty caused by the extra mass.
4) The light-weight cable-rod-beam structure of the invention only needs small electric power to drive, and the electric energy collected and stored by the light-focusing system can fully realize self-sufficiency.
5) According to the invention, the ropes and the pod rod structures are adopted for supporting and fixing, the Fresnel lens array and the solar cell array reach force balance through the ropes and the pod rod structures, and the Fresnel lens array and the solar cell array do not move mutually, so that additional fixed support between the Fresnel lens array and the solar cell array is avoided, and the Fresnel lens array is simple in form and stable in structure.
Drawings
FIG. 1 is a schematic structural view of a lightweight "cable-rod-beam" structure of a supported space Fresnel lens condensing system of the present invention;
FIG. 2 is a schematic view of a Fresnel lens array of the present invention;
FIG. 3 is a schematic view of a solar cell array of the present invention;
fig. 4 is a schematic structural view of a battery module of the present invention;
FIG. 5 is a schematic view of a perimeter mounting truss of the Fresnel lens array of the present invention;
FIG. 6 is a schematic diagram of a modal analysis of a Fresnel lens array of the present invention;
FIG. 7 is a schematic view of the overall structure of the present invention in a gather-spread operation;
fig. 8 is a schematic diagram of the operation of the present invention.
In the figure, a satellite platform 101, an upper stay 102, a Fresnel lens array 103, a middle stay 104, a solar cell array 105, a pod upper support rod 106, a pod lower support rod 107, a lower stay 108, a stay 201, a hinge a, a Fresnel lens 202, a peripheral fixed truss 203, a hinge b204, a solar cell array side frame 301, a peripheral stay 302, a solar cell 303, a heat pipe 304 and a heat dissipation truss 305 are arranged.
Detailed Description
The invention will be described in detail below with reference to the drawings and the detailed description.
The invention discloses a lightweight 'cable-rod-beam' structure for supporting a space Fresnel lens condensing system, which is shown in fig. 1 and comprises a satellite platform 101, wherein the satellite platform 101 is fixedly connected with a Fresnel lens array 103 and a solar cell array 105 through a rope structure, the Fresnel lens array 103 is positioned right above the solar cell array 105, the Fresnel lens array 103 and the solar cell array 105 are connected with a pod supporting structure, the satellite platform 101 is used for adjusting the sun posture of the whole system, supporting the Fresnel lens array 103 and the solar cell array 105 through the pod supporting structure, and fastening the Fresnel lens array 103 and the solar cell array 105 through ropes after unfolding.
The number of the fresnel lens array 103 and the solar cell array 105 connected to the satellite platform 101 is set according to actual requirements.
Example 1
As shown in fig. 1, in this embodiment, the rope structure includes an upper rope 102, a middle rope 104 and a lower rope 108, wherein a uniform end of the upper rope 102 and a uniform end of the lower rope 108 are connected with the satellite platform 101, the other end of the upper rope 102 is connected with the fresnel lens array 103, the other end of the lower rope 108 is connected with the solar cell array 105, one end of the middle rope 104 is connected with the fresnel lens array 103, the other end is connected with the solar cell array 105, and the upper rope 102, the middle rope 104 and the lower rope 108 are used for fastening the fresnel lens array 103 and the solar cell array 105.
The pod supporting structure comprises an upper pod supporting rod 106 and a lower pod supporting rod 107, the upper pod supporting rod 106 is connected with the Fresnel lens array 103, the lower pod supporting rod 107 is connected with the solar cell array 105, and the upper pod supporting rod 106 and the lower pod supporting rod 107 are used for supporting and unfolding the Fresnel lens array 103 and the solar cell array 105, so that the normal operation and the sun alignment of the whole condensing subsystem are realized.
According to the invention, the rope, the rod and the hinge structure are adopted, so that synchronous control of the Fresnel lens array and the solar cell array is realized, a complex redundant unfolding control mechanism is avoided, and meanwhile, the control difficulty caused by the extra mass is eliminated.
The rope structure and the pod supporting structure are adopted for supporting and fixing, so that the Fresnel lens array and the solar cell array can achieve force balance, no mutual movement is caused, additional fixed support between the Fresnel lens array and the solar cell array is avoided, the form is simple, and the structure is stable.
Example 2
As shown in fig. 2, in this embodiment, the fresnel lens array 103 includes a plurality of fresnel lenses 202 arranged in an array, horizontally adjacent fresnel lenses 202 are cooperatively connected by hinges a201, longitudinally adjacent fresnel lenses 202 are fixedly connected, each row of first fresnel lenses 202 is connected to the satellite platform 101 by a peripheral fixing truss 203, and each row of end fresnel lenses 202 is cooperatively connected with a rope structure and a pod support structure. Since the individual Fresnel lenses 202 are connected in a matched manner through the hinge a201 in the transverse direction, the Fresnel lenses 202 are fixedly connected in the longitudinal direction, and each row of Fresnel lenses 202 can be contracted and expanded conveniently through the hinge a 201.
As shown in fig. 3, the solar cell array 105 includes a plurality of cell modules arranged in an array, two laterally adjacent cell modules are connected by a hinge b204, two longitudinally adjacent cell modules are fixedly connected, two ends of each row of cell modules are connected with a peripheral cable 302, each row of first cell modules is connected with the satellite platform 101 by a solar cell array side frame 301, and each row of end cell modules is connected with a bean pod supporting structure by a rope structure. Because the single battery modules are connected in a matched manner through the hinge b204, the battery modules are connected in a fixed manner in the longitudinal direction, and each row of battery modules can be contracted and expanded conveniently through the hinge b 204.
When the satellite platform 101 detects that the daily attitude needs to be adjusted, the pod support structure is driven to shrink the Fresnel lens array 103 and the solar cell array 105, so that the attitude adjustment of the lightweight 'cable-rod-beam' structure is facilitated, and then the pod support structure is driven to expand the Fresnel lens array 103 and the solar cell array 105.
Example 3
As shown in fig. 4, in this embodiment, each battery module includes solar cells 303, the bottom of each solar cell 303 is attached to a hollow heat dissipation truss 305, the bottom of the heat dissipation truss 305 is connected to a heat pipe 304, and heat generated by the solar cells 303 is transferred through the heat pipe 304, so that the heat is dissipated.
The bottom of the heat dissipation truss 305 is an aluminum honeycomb substrate, so that the heat dissipation capacity is ensured, and the quality is further reduced.
As shown in fig. 5, the fresnel lens arrays each have a peripheral fixing truss 203 for supporting and fixing, and the cross-sectional dimensions of the peripheral fixing trusses are divided into "C" shapes, taking 500mm×500mm×1.5mm fresnel lenses as an example. The first stage is used for the first stage Fresnel lens array and is mutually matched and connected with the satellite platform, and the second stage is used for the rest Fresnel lens arrays.
As shown in fig. 6, the fresnel lens array 103 is cooperatively connected with the upper guy wires 102, the middle guy wires 104, and the pod upper support pole 106. In order to ensure that the pod upper support struts 106 and pod lower support struts 107 can be deployed efficiently and that no destabilization occurs during deployment, a strut stability analysis is required. For this purpose, a 7-group Fresnel lens array was used for instability analysis, which contained 28 Fresnel lenses 500mm by 1.5mm in total. Furthermore, the natural frequency of the condensing subsystem in space plays a very important role in the overall system, for which a modal analysis was performed using 7 sets of fresnel lens arrays as an example. Table one gives the lengths of the pod upper support beam 106 and pod lower support beam 107 in the fully extended state of the 7-set fresnel lens array, calculated at different critical pressures to the corresponding minimum outside diameter, beam wall thickness and mass. Table 2 gives the first fifth order frequencies for the fully extended state of the 7 sets of fresnel lens arrays. It should be noted that the upper guy cable 102 and the middle guy cable 104 are both kevlar guy ropes, and the pod upper support rod 106 and the pod lower support rod 107 are both made of carbon fiber and are hollow rods. In order to ensure reliability in actual engineering, the work safety factor is taken to be 5.
TABLE 1
TABLE 2
| Modality | Frequency (Hz) |
| 1 | 0.093 |
| 2 | 0.222 |
| 3 | 0.309 |
| 4 | 0.505 |
| 5 | 0.528 |
As shown in fig. 7, the folding and unfolding process is schematically performed by taking 7 sets of the fresnel lens array 103 and the solar cell array 105 as an example. The upper pod supporting rod 106 and the lower pod supporting rod 107 are driven to be unfolded, and the upper guy cable 102, the middle guy cable 104 and the lower guy cable 108 play a role in balancing and fixing force.
The working principle of the lightweight cable-rod-beam structure for supporting the space Fresnel lens condensing system is as follows:
as shown in fig. 8, two fresnel lens arrays 103 and two solar cell arrays 105 are mounted on a satellite platform 101 on a solar synchronous orbit, and periodically move around the earth. Because the space for carrying the rocket is limited, the whole system is in a furled state in the initial stage, and when the whole system reaches a solar synchronous orbit, the Fresnel lens array 103 and the two solar cell arrays 105 are unfolded through the hinge a201 under the driving action of the pod upper supporting rod 106 and the pod lower supporting rod 107. Finally, the stability of the whole condensing subsystem is ensured by balancing the upper guy cable 102, the middle guy cable 104 and the lower guy cable 108.
Through the mode, the lightweight 'rope-rod-beam' structure for supporting the space Fresnel lens condensing system comprises a plurality of Fresnel lens arrays and solar cell arrays, wherein each Fresnel lens array is connected through a hinge a, each solar cell array is connected through a hinge b, one ends of a plurality of array modules are fixedly connected to a satellite platform, pod supporting structures positioned on two sides of the Fresnel lens arrays and the solar cell arrays play a supporting role, and the balance and the expansion of the Fresnel lens arrays and the solar cell arrays are realized through ropes and the pod supporting structures. The invention uses the rope with lighter mass and the pod supporting structure to unfold and fix the whole space Fresnel lens condensing system, avoids the complex redundant control mechanism in the traditional design, and has the characteristics of stable structure, simple configuration and easy expansion.
Claims (9)
1. The light-weight 'cable-rod-beam' structure of the Fresnel lens condensation system in the supporting space is characterized by comprising a satellite platform (101) for adjusting and controlling the sun posture, the satellite platform (101) is fixedly connected with a Fresnel lens array (103) and a solar cell array (105) through rope structures, the Fresnel lens array (103) is located right above the solar cell array (105), and the Fresnel lens array (103) and the solar cell array (105) are connected with pod supporting structures for supporting and unfolding.
2. The lightweight "cable-rod-beam" structure of a supported space fresnel lens condensing system according to claim 1, characterized in that the cable structure comprises an upper cable (102), a middle cable (104) and a lower cable (108), the upper cable (102), the lower cable (108) are connected with the satellite platform (101) at a uniform end, the other end of the upper cable (102) is connected with the fresnel lens array (103), the other end of the lower cable (108) is connected with the solar cell array (105), one end of the middle cable (104) is connected with the fresnel lens array (103), and the other end is connected with the solar cell array (105).
3. The lightweight "cord-bar-beam" structure of a supported space fresnel lens concentrator system of claim 2, wherein said pull cords (102) and said down-pull cords (108) are kevlar pull cords.
4. The lightweight "cord-bar-beam" structure of a supported space fresnel lens concentrating system of claim 1, characterized in that the pod support structure comprises pod upper support bars (106), pod lower support bars (107), the pod upper support bars (106) connecting fresnel lens arrays (103), the pod lower support bars (107) connecting solar cell arrays (105).
5. The lightweight "cord-rod-beam" structure of a supported space fresnel lens concentrating system of claim 4 wherein the pod upper support rods (106), pod lower support rods (107) are carbon fibers and are hollow rods.
6. The lightweight "cable-rod-beam" structure of a supported space fresnel lens condensing system according to claim 1, characterized in that the fresnel lens array (103) comprises a plurality of fresnel lenses (202) arranged in an array, the horizontally adjacent fresnel lenses (202) are cooperatively connected by hinges a (201), the longitudinally adjacent fresnel lenses (202) are fixedly connected, each row of the first fresnel lenses (202) is connected to the satellite platform (101) by a peripheral fixed truss (203), and each row of the end fresnel lenses (202) is cooperatively connected with a rope structure and a pod support structure.
7. The lightweight "cable-rod-beam" structure of a supported space fresnel lens concentrating system according to claim 1, wherein the solar cell array (105) comprises a plurality of cell modules arranged in an array, two laterally adjacent cell modules are connected by a hinge b (204), two longitudinally adjacent cell modules are fixedly connected, two ends of each row of cell modules are connected with peripheral cables (302), each row of first cell modules is connected with a satellite platform (101) by a solar cell array side frame (301), and each row of end cell modules is connected with a pod support structure by a rope structure.
8. The lightweight "cord-bar-beam" structure of a supported space fresnel lens concentrating system of claim 7 wherein each of said cell modules comprises a solar cell (303), a hollow heat dissipating truss (305) attached to the bottom of each of said solar cells (303), and a heat pipe (304) attached to the bottom of said heat dissipating truss (305).
9. The lightweight "cord-bar-beam" structure of a supported space fresnel lens concentrator system of claim 8, wherein said heat dissipating truss (305) is aluminum honeycomb substrate at the bottom.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311303389.2A CN117544072B (en) | 2023-10-09 | 2023-10-09 | Light-weight 'cable-rod-beam' structure for supporting space Fresnel lens condensing system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311303389.2A CN117544072B (en) | 2023-10-09 | 2023-10-09 | Light-weight 'cable-rod-beam' structure for supporting space Fresnel lens condensing system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117544072A true CN117544072A (en) | 2024-02-09 |
| CN117544072B CN117544072B (en) | 2024-07-19 |
Family
ID=89794633
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311303389.2A Active CN117544072B (en) | 2023-10-09 | 2023-10-09 | Light-weight 'cable-rod-beam' structure for supporting space Fresnel lens condensing system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117544072B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090314325A1 (en) * | 2008-06-19 | 2009-12-24 | David Borton | Solar concentrator system |
| TW201038975A (en) * | 2009-04-22 | 2010-11-01 | New Concept Aircraft Zhuhai Co Ltd | Unit area light flux enhancing apparatus capable of reducing the distance of light collection for light source |
| JP2014175645A (en) * | 2013-03-13 | 2014-09-22 | Stanley Electric Co Ltd | Photovoltaic power generation apparatus |
| US20150022909A1 (en) * | 2013-07-21 | 2015-01-22 | Mark Joseph O'Neill | Stretched Fresnel Lens Solar Concentrator for Space Power, with Cords, Fibers, or Wires Strengthening the Stretched Lens |
| CN105244413A (en) * | 2015-10-13 | 2016-01-13 | 西安电子科技大学 | Zero refractive index material-based design method for concentrated solar collection device |
| US20170063296A1 (en) * | 2015-09-02 | 2017-03-02 | Airbus Defence And Space Netherlands B.V. | Solar Panel with Flexible Optical Elements |
| CN106527499A (en) * | 2016-12-06 | 2017-03-22 | 北京航空航天大学 | Variable stiffness deployable mechanism and measurement and control method thereof |
| CN117424546A (en) * | 2023-10-17 | 2024-01-19 | 湖北航宇新型材料股份有限公司 | Carbon fiber satellite solar honeycomb panel and application method thereof |
-
2023
- 2023-10-09 CN CN202311303389.2A patent/CN117544072B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090314325A1 (en) * | 2008-06-19 | 2009-12-24 | David Borton | Solar concentrator system |
| TW201038975A (en) * | 2009-04-22 | 2010-11-01 | New Concept Aircraft Zhuhai Co Ltd | Unit area light flux enhancing apparatus capable of reducing the distance of light collection for light source |
| JP2014175645A (en) * | 2013-03-13 | 2014-09-22 | Stanley Electric Co Ltd | Photovoltaic power generation apparatus |
| US20150022909A1 (en) * | 2013-07-21 | 2015-01-22 | Mark Joseph O'Neill | Stretched Fresnel Lens Solar Concentrator for Space Power, with Cords, Fibers, or Wires Strengthening the Stretched Lens |
| US20170063296A1 (en) * | 2015-09-02 | 2017-03-02 | Airbus Defence And Space Netherlands B.V. | Solar Panel with Flexible Optical Elements |
| CN105244413A (en) * | 2015-10-13 | 2016-01-13 | 西安电子科技大学 | Zero refractive index material-based design method for concentrated solar collection device |
| CN106527499A (en) * | 2016-12-06 | 2017-03-22 | 北京航空航天大学 | Variable stiffness deployable mechanism and measurement and control method thereof |
| CN117424546A (en) * | 2023-10-17 | 2024-01-19 | 湖北航宇新型材料股份有限公司 | Carbon fiber satellite solar honeycomb panel and application method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117544072B (en) | 2024-07-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4888063A (en) | Variable aperture, variable flux density, aerospace solar collector | |
| US4719903A (en) | Variable aperture, variable flux density, aerospace solar collector | |
| CN104158471B (en) | A kind of non-concentrating Wireless power transmission | |
| US8322332B2 (en) | Self-erecting gimbal mounted solar radiation collectors | |
| JP2011523775A (en) | Large solar collector with multiple coaxial dish reflectors | |
| US20170047886A1 (en) | Compactable Power Generation Arrays | |
| CN103868246B (en) | The film reflective light concentrating type space solar cumulative station that a kind of power density is adjustable | |
| CN105857643A (en) | Flexible solar wing used for satellite power supply and two-degree-of-freedom storage device applied to flexible solar wing | |
| CN108173477B (en) | Cluster intelligent satellite space power generation system and power generation method | |
| US20170152837A1 (en) | Portable power generating solar cell wind turbine | |
| WO2017027615A1 (en) | Compactable power generation arrays | |
| CN114865991B (en) | OMEGA-2.0 space solar power station designed by optical-mechanical-electrical integration | |
| US20130146124A1 (en) | Large-scale integrated radiant energy collector | |
| Kelzenberg et al. | Design and prototyping efforts for the space solar power initiative | |
| CN112751525A (en) | Foldable modular photovoltaic system | |
| CN113258249B (en) | On-orbit ultra-large deployable space structure system | |
| CN117544072B (en) | Light-weight 'cable-rod-beam' structure for supporting space Fresnel lens condensing system | |
| CN113364148B (en) | Modular multi-rotary-joint space solar power station system | |
| CN109831145B (en) | Space solar power station for energy distribution collection and conversion and wave beam centralized control emission | |
| CN205178975U (en) | Space solar energy basic station | |
| JP2003074988A (en) | Solar beam concentrator | |
| CN111427384B (en) | Solar power station and method capable of expanding line focusing space | |
| CN116743058B (en) | Modularized polygonal prismatic space solar power station system | |
| US20190158014A1 (en) | Apparatuses, systems, and methods for a three-axis space frame, photovoltaic, and infrastructure structural system | |
| CN213243892U (en) | Extensible solar cell panel |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant |