CN112688630A - Extensible space solar cell panel structure - Google Patents
Extensible space solar cell panel structure Download PDFInfo
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- CN112688630A CN112688630A CN202110226907.XA CN202110226907A CN112688630A CN 112688630 A CN112688630 A CN 112688630A CN 202110226907 A CN202110226907 A CN 202110226907A CN 112688630 A CN112688630 A CN 112688630A
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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
- Y02E10/40—Solar thermal energy, e.g. solar towers
- Y02E10/47—Mountings or tracking
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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
本发明公开了一种可扩展的空间太阳能电池板结构，包括空心桁架结构、折叠式太阳能电池板子阵、连接关节、推动轨道装置和控制电路等组成部分，所述空心桁架结构由圆柱面构成；所述连接关节在空心桁架结构两端；所述折叠式太阳能电池板子阵在空心桁架结构的左右两侧，所述电磁力推动轨道在空心桁架结构的上侧；所述电枢在空心桁架结构的下侧，所述电生磁模块和控制电路在空心桁架结构的内部。本发明可以随着空间太阳能电站供电功率的提升而增加太阳能电池板的数量，提高了空间太阳能电池板结构的灵活性，具有稳定、安全和方便等优点。
The invention discloses an expandable space solar cell panel structure, which includes a hollow truss structure, a foldable solar cell panel sub-array, a connection joint, a push rail device, a control circuit and other components, and the hollow truss structure is composed of cylindrical surfaces; The connecting joints are at both ends of the hollow truss structure; the foldable solar panel arrays are on the left and right sides of the hollow truss structure, the electromagnetic force pushes the track on the upper side of the hollow truss structure; the armature is on the hollow truss structure On the lower side, the electromagnetic generating module and the control circuit are inside the hollow truss structure. The invention can increase the number of solar cell panels with the increase of the power supply of the space solar power station, improve the flexibility of the space solar cell panel structure, and has the advantages of stability, safety and convenience.
Description
Technical Field
The invention relates to the technical field of space solar power stations, and provides an extensible space solar cell panel structure.
Background
With the rapid development of society, the electric energy required by people is larger and larger. The energy sources of coal, oil, natural gas and the like required by our power generation are limited, and the energy sources are combustedBurning these energy sources is very harmful to the environment, so it is necessary to eliminate the old power generation mode and develop clean new energy power stations in the future. The sunlight in the space is not attenuated by the atmosphere and is not influenced by the change of seasons and day and night, the solar radiation intensity is stable and is about 1353W/m2The average irradiation intensity of the ground sun is more than 5 times, so people find that building a space solar power station in the space is one of ideal novel power generation modes in the search.
Space Solar Power Stations (SSPS) attract more and more research from domestic and foreign experts with their unique advantages. Several dozen concept concepts of space solar power stations have been proposed internationally. Researches have been carried out for many years in the United states, Japan, European Union and the like, and proposals for 1979 SPS reference systems, integrated symmetrical light-gathering systems, distributed tethered solar power stations, solar Sail towers and other space solar power stations are respectively provided. Concepts such as a multi-rotary joint space solar power station and an OMEGA type space solar power station are also put forward in China.
The collection of solar energy is the first step in a spatial solar power station, the spatial solar panel structure being an important component of a spatial solar power station. Suppose a space solar power station with 1GW of power supply is to be built. In this case, the rectenna efficiency is considered to be 80%. Thus, 1.25 gigawatts of microwave power is required at the ground rectenna location to produce so much electrical output. The space satellite transmits microwave power of 1.25 GW on the ground. Assuming a beam efficiency of 87%, the microwave power required for the transmitting antenna is 1.44 gigawatts. On the space satellite, a DC microwave conversion device can convert DC energy into microwaves. Thus, the DC power required for a DC to microwave conversion efficiency of 70% is 2 GW. Photovoltaic power generation is used to convert solar energy into DC energy in space. Photovoltaic power generation has a power conversion efficiency of 20% from solar energy to DC. Thus, 10 gigawatts of solar energy are required at the spatial end to provide 1 gigawatt of available electrical power on earth. The size of the photovoltaic array required to produce a 2 gigawatt DC power output is about 10 square kilometers (2 kilometers by 5 kilometers). Such bulky photovoltaic arrays cannot be launched into space at once and must be launched in batches. However, the solar panels of the space solar power station have insufficient structural flexibility, do not meet practical requirements, and cannot increase the number of the solar panels along with the improvement of the power supply of the space solar power station.
Disclosure of Invention
The invention aims to overcome the defects that the structure of a solar cell panel in the existing space solar power station scheme has insufficient flexibility, does not meet the actual requirement, and cannot increase the number of the solar cell panels along with the improvement of the power supply power of the space solar power station, and the like, and provides a space solar cell panel structure which has good flexibility and meets the actual requirement.
The technical scheme of the invention is as follows: the invention discloses an extensible space solar cell panel structure which comprises a hollow truss structure, a folding solar cell panel subarray, a connecting joint, a pushing track device, a control circuit and the like. The outer cylindrical surface is an insulating outer cylinder made of insulating material and is connected with the connecting joint and the control circuit, and the inner cylindrical surface is a conductive inner cylinder made of conductive material and is connected with the folding solar cell panel subarray to output electric energy outwards; the connecting joints are arranged at two ends of the hollow truss structure and consist of connecting joints 1 and connecting joints 2. The connection joint 1 is provided with a rotary joint 1, a rotary joint 2 and an outgoing line which are respectively connected with the motor 1, the motor 2 and the motor 3, and the connection joint 2 is provided with a round hole. The connecting joint 1 and the connecting joint 2 are connected through a connecting and fixing structure; the outgoing line and the surface with the round hole are provided with infrared correctors for correcting the outgoing line so that the outgoing line just enters the round hole; the pushing track device is composed of an electromagnetic force pushing track, an armature and an electromagnetic generating module. The invention improves the flexibility of the space solar panel structure, can increase the number of the solar panels along with the improvement of the power supply power of the space solar power station, and has good economy and flexibility.
The folding solar cell panel subarrays are arranged on the left side and the right side of the hollow truss structure, solar cells of the solar cell panel subarrays are three-junction gallium arsenide cells, and electric energy of the solar cell panel subarrays is output outwards through the conductive rotating structure and the conductive inner cylinder.
The connecting and fixing structure is composed of a connecting and fixing structure 1 and a connecting and fixing structure 2 and is used for fixing two connecting joints and ensuring that two connected space solar cell panel units are stable and reliable in structure.
The track is two parallel aluminum alloy grooves and is matched with the armature to transport the spatial solar cell panel unit.
The armature is arranged on the lower side of the hollow truss structure and is made of aluminum alloy, the shape of the armature is matched with the electromagnetic force pushing track, and the armature is matched with the electromagnetic force pushing track to transport the extensible space solar cell panel structure unit.
The electromagnetic modules are single-phase windings at two ends of the inner side of the hollow truss structure, generate a constant magnetic field, provide a magnetic field for the electromagnetic force to push the track, and require that the directions of the magnetic fields at two sides are opposite.
The control circuit is respectively connected with the connecting joint and the pushing track device to control the operation of the connecting joint and the pushing track device.
The insulating outer cylinder and the conductive inner cylinder are connected by a conductive rotating structure; the inner wall of the insulating outer barrel and the outer wall of the conductive inner barrel are both provided with a plurality of grooves surrounding the circumference of the insulating outer barrel, the grooves formed in the inner wall of the insulating outer barrel correspond to the grooves formed in the outer wall of the conductive inner barrel one by one, and a conductive rotating structure is arranged between every two corresponding grooves.
The invention has the beneficial effects that:
the hollow truss structure in the scheme is composed of an outer insulating outer cylinder and an inner conductive inner cylinder, two cylindrical surfaces are connected through a rolling ring, and the angle of a solar cell panel is adjusted by rotating the insulating outer cylinder when necessary, so that the flexibility of the solar cell panel is ensured; the connecting joint is responsible for connecting and splitting the two cell panel units, and the number of the spatial solar cell panel structural units can be flexibly adjusted; the pushing track device pushes the battery panel unit through electromagnetic force, and the size and the direction of pushing force are adjusted through controlling the current size and the magnetic field direction. The invention has the advantages of flexibility, economy, safety, stable structure and the like.
Drawings
Fig. 1 is an overall structure diagram of an expandable space solar panel.
Fig. 2 is a structural view of a spatial solar panel unit.
Fig. 3 is a structural view of a hollow truss.
Fig. 4 is a view showing a structure of a joint.
Fig. 5 is a structure view of an electromagnetic force pushing rail.
Fig. 6 is a structural view of an armature.
Fig. 7 is a schematic diagram of an electromagnetic module.
Fig. 8 is a schematic diagram of electromagnetic force pushing.
FIG. 9 is a structural diagram of an infrared corrector.
Description of reference numerals:
(1) a hollow truss structure; (2) a folding solar panel subarray; (3) a connecting joint; (4) pushing the rail device; (101) an insulating outer cylinder; (102) a conductive inner barrel; (103) a conductive rotary structure; (104) a groove; (105) a motor 4; (301) a connecting joint 1; (302) a connecting joint 2; (303) motor 1, (304) motor 2; (305) a motor 3; (306) a circular hole; (307) a rotary joint 1; (308) a rotary joint 2; (309) an outgoing line; (310) an infrared corrector; (3101) an infrared emitter; (3102) a sensing reception surface; (401) the track is pushed by electromagnetic force; (402) an armature; (403) an electromagnetic generating module; (404) and a motor 5.
Detailed Description
The invention is further illustrated with reference to the following figures and examples.
As shown in fig. 1, the present invention provides an expandable space solar panel structure, which can increase the number of solar panels with the increase of the capacity of the space solar power station. Fig. 2 is a structural diagram of a spatial solar cell panel unit, which comprises a hollow truss structure, a folding solar cell panel subarray, a connecting joint, a pushing track device, a control circuit and the like. Fig. 3 is a structure diagram of a hollow truss, wherein an insulating outer cylinder of the hollow truss structure is respectively and fixedly connected with an electromagnetic force pushing track, an armature, a rotary joint and a folding solar cell panel subarray. Fig. 4 is a structure diagram of a connection joint, which is mainly responsible for connecting and fixing two space solar cell panel units. And the electric energy from the folding solar panel subarray is output outwards through the conductive inner cylinder of the hollow truss structure. Fig. 5, 6 and 7 are views illustrating a structure of a pushing rail, and the present invention mainly uses electromagnetic force to push a solar cell panel unit to be connected to a space. Fig. 9 is a structural view of an infrared corrector for securing a circuit connection of two space solar cell panel units.
The hollow truss structure comprises an insulating outer cylinder, a conductive inner cylinder, a conductive rotating structure and a motor 4, and a control circuit can complete angle adjustment of the folded solar cell panel subarray by controlling the motor. The insulating outer cylinder is the outer side of the hollow truss structure and mainly used for protecting the internal structure and connecting all structural parts (a conductive part, a control circuit, a motor and the like are arranged in the insulating outer cylinder, and the outside of the insulating outer cylinder is connected with the pushing track device and the folding solar panel subarray). The conductive inner cylinder and the conductive rotating structure are conductive and ensure stable and safe electrification when the external folding solar cell panel subarray and the insulating outer cylinder are adjusted in a rotating mode. The motor 4 provides power for the rotation adjustment of the folding solar panel subarray and the insulating outer cylinder.
The pushing track device is arranged on the upper side of the hollow truss structure, the tracks are two parallel aluminum alloy grooves, and the tracks are matched with the armature and the electromagnetic module to transport the spatial solar cell panel unit. After the armature of the space solar panel unit is aligned with the electromagnetic force pushing track, the control circuit supplies power to the electromagnetic force pushing track and the electromagnetic generating module, and after the electromagnetic force pushing track and the electromagnetic generating module are electrified, the armature part can be subjected to the electromagnetic force
. Electromagnetic force
The size of (A) is as follows:
in the formula:
as to the strength of the magnetic field,
in order to be the magnitude of the current,
is the armature effective length. Can be adjusted by
,
,
Controlling electromagnetic forces
。
The electromagnetic module of the scheme is a single-phase winding at two ends of the inner side of the hollow truss structure, and a constant magnetic field is generated by introducing direct current to provide a magnetic field for the electromagnetic force to push the track. The calculation formula of the magnetic field intensity is as follows:
in the formula:His the magnetic field strength inA/m；NThe number of turns of the exciting coil;Ithe unit is A for introducing direct current;lfor testing the effective magnetic path length of the sample, the unit ism(ii) a And the directions of the magnetic fields on the two sides are opposite, namely the initial end is accelerated, the tail end is decelerated, and the small speed and small impulse are ensured when the space solar cell panel unit reaches the tail end.
The connecting joints are arranged at two ends of the hollow truss structure and consist of connecting joints 1 and 2. The connection joint 1 is provided with a rotary joint 1, a rotary joint 2 and an outgoing line which are respectively connected with the motor 1, the motor 2 and the motor 3, and the connection joint 2 is provided with a round hole as shown in figure 4. In addition, the fixing device ensures the safety of the two connecting joints and ensures the firm connection.
The connecting and fixing devices are respectively positioned on the connecting joint 1 and the connecting joint 2, as shown in fig. 4, the connecting and fixing part in the connecting joint 1 is a thick cylinder, a large round hole is formed in the middle, and a plurality of small round holes are formed around the large round hole. The round holes corresponding to the connecting joints 1 on the connecting joints 2 are provided with a plurality of cylinders, the middle large cylinder is connected with the outgoing line through the large round hole and does not play a role in fixed connection, and the small cylinders around the middle large cylinder are formed by combining the cylinders and the cones and are matched with the small round holes to play a role in fixing the two connecting joints.
The infrared corrector consists of an infrared emitter and a receiving surface and provides a correction angle for the control circuit. The receiving surface surrounds the circular hole and is composed of a plurality of optical sensors. When the outgoing line does not correspond to the round hole, infrared rays can irradiate on the receiving surface, the sensor on the receiving surface can generate voltage, and the position of the generated voltage can be known, and the angle of the outgoing line needing to be adjusted can be obtained by comparing the position of the generated voltage with the position of the round hole. When the center of the circle is taken as the origin of coordinates (0, 0), the coordinates of the circular hole are set to (a,b) Let the coordinates of the sensor be (x,y). Assuming that light is irradiated on (A)x ,1 y 1) In this case, the lead-out line needs to be adjusted.
The control circuit is respectively connected with the motors of the connecting joints, the track and the electromagnetic generation module of the track pushing device and the control motor of the hollow truss structure. When the armature of the space solar panel unit enters the electromagnetic force pushing track, the current added into the electromagnetic track and the electromagnetic generation module is controlled according to the kinetic energy required when the corresponding fixing device of the connecting joint 1 is connected with the corresponding fixing device of the connecting joint 2. And the motors are connected with the connecting joints and the plurality of motors in the truss result to control the rotating angles of the motors, and the motors are connected with the infrared light sensor to calculate the required adjusting distance of the outgoing line and control the motors to adjust.
The specific operation of each part is described below.
Launching a satellite carrying a spatial solar panel from the groundAnd the star is in butt joint with the space solar power station, and the space solar panel unit is adjusted on the pushing track. After the armature of the space solar panel unit is aligned with the electromagnetic force pushing track, a worker supplies power to the electromagnetic force pushing track and the electromagnetic generating module through the control circuit, and after the electromagnetic force pushing track and the electromagnetic generating module are electrified, the armature part can be subjected to the electromagnetic force
. When the armature slides in the magnetic field, the space solar panel unit slides forwards in an accelerated manner, and the armature slides through the electromagnetic generation module 1 and then forwards at a constant speed. The armature slides for a period of time and then enters the electromagnetic generating module 2, because the magnetic field direction of the electromagnetic generating module 2 and the armature opposite to the electromagnetic generating module 1 slide forwards in a speed reducing way, when the connecting joint 1 of the space solar panel unit 1 and the connecting joint 2 of the space solar unit 2 are just connected through the connecting and fixing device, the armature speed is zero, and at the moment, the control circuit cuts off the power supply for the electromagnetic force pushing track and the electromagnetic generating module.
When the spatial solar panel structural unit 2 slides over, the control circuit controls the motor 1 to rotate 180 degrees counterclockwise, and then controls the motor 2 to rotate 180 degrees. When the connecting joint 1 and the connecting joint 2 are connected and fixed, the motor 5 is controlled to rotate an armature, the armature is separated from an electromagnetic force pushing track, the motor 2 is controlled to rotate 180 degrees in the opposite direction, at the moment, the two spatial solar cell panel structure units are on the same line, then the infrared ray calibrators on the two connecting surfaces work to judge whether the outgoing line of the connecting joint 1 and the round hole on the connecting joint 2 are on the same horizontal plane, if the angle required to be corrected is not calculated by the infrared ray calibrators and fed back to the control device, and the control device commands the motor 4 to finish the correction work. And finally, controlling the motor 3 to enable the outgoing line to be inserted into the round hole in the connecting joint 2. At this time, the connection of the two solar cell panel units is completed. And finally, the control circuit controls the motor 1 to rotate 180 degrees clockwise, the pushing tracks of the two solar cell panel units are mutually butted, and the number of the solar cell panels can be expanded according to the steps.
Claims (9)
1. An extensible spatial solar panel structure is characterized by comprising a hollow truss structure (1), a folding solar panel subarray (2), a connecting joint (3), a pushing track device (4), a control circuit (5) and the like; the hollow truss structure (1) is composed of an inner cylinder, an outer cylinder, a conductive rotating structure (103) and a motor 4 (105); the outer cylinder is an insulating outer cylinder (101) made of insulating material and is connected with the connecting joint (3) and the control circuit (5), and the inner cylinder is a conductive inner cylinder (102) made of conductive material; the connecting joints (3) are arranged at two ends of the hollow truss structure (1) and consist of connecting joints 1(301) and connecting joints 2 (302); the rotary joint 1(307), the rotary joint 2(308) and the leading wire (309) of the connecting joint 1(301) are respectively connected with the motor 1(303), the motor 2(304) and the motor 3(305), and the connecting joint 2(302) is provided with a round hole (306); an infrared corrector (310) is arranged on the outgoing line (309) and the surface (306) with the round hole and is used for correcting the outgoing line (309) so that the outgoing line (309) just enters the round hole (306); the pushing track device (4) is composed of an electromagnetic force pushing track (401), an armature (402) and an electromagnetic generating module (403).
2. The scalable space solar panel structure according to claim 1, wherein the folding solar panel sub-arrays (2) are on the left and right sides of the hollow truss structure (1), and the solar cells of the solar panel sub-arrays are triple junction gallium arsenide cells.
3. The expandable spatial solar panel structure of claim 1, wherein the connection joint 1(301) has a connection fixing structure 1(311), and the connection joint 2(302) has a connection fixing structure 2(312) for fixing the two connection joints.
4. An expandable space solar panel structure according to claim 1, characterized in that the electromagnetic force pushes rails (401) on the upper side of the hollow truss structure (1), the rails are two parallel aluminum alloy grooves, and the expandable space solar panel structure unit is transported in cooperation with the armature (402).
5. The scalable space solar panel structure according to claim 1, wherein the armature (402) is connected to the motor 5(404) at the lower side of the hollow truss structure (1), is made of aluminum alloy, and has a shape matching the electromagnetic force pushing rail (401) to transport the scalable space solar panel structure unit in cooperation with the electromagnetic force pushing rail (401).
6. The scalable spatial solar panel structure according to claim 1, wherein the infrared corrector (310) is comprised of an infrared emitter (3101) and a sensing reception surface (3102) to provide correction amounts to the control circuitry.
7. The scalable space solar panel structure according to claim 1, wherein the electromagnetic modules (403) are single-phase windings at both ends of the inner side of the hollow truss structure (1), generate a constant magnetic field, provide a magnetic field for the electromagnetic force pushing rail (401), and the directions of the magnetic fields at both sides are opposite.
8. The scalable spatial solar panel structure according to claim 1, wherein the control circuit (5) is connected to the connection joint (3) and the push rail device (4), respectively.
9. The scalable space solar cell panel structure according to claim 1, wherein the insulating outer cylinder (101) and the conductive inner cylinder (102) are connected by a conductive rotating structure (103); the inner wall of the insulating outer cylinder (101) and the outer wall of the conductive inner cylinder (102) are respectively provided with a plurality of grooves (104) surrounding the circumference of the insulating outer cylinder, the grooves (104) formed in the inner wall of the insulating outer cylinder (101) correspond to the grooves (104) formed in the outer wall of the conductive inner cylinder (102) one by one, and a conductive rotating structure (103) is arranged between every two corresponding grooves (104).
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115765606A (en) * | 2022-11-21 | 2023-03-07 | 地卫二空间技术(杭州)有限公司 | Novel architecture for realizing space solar energy conversion and transmission |
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