CN111470072A - Solar cell array wiring method and system for GEO orbit three-axis stable satellite round shell structure - Google Patents
Solar cell array wiring method and system for GEO orbit three-axis stable satellite round shell structure Download PDFInfo
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- CN111470072A CN111470072A CN202010198207.XA CN202010198207A CN111470072A CN 111470072 A CN111470072 A CN 111470072A CN 202010198207 A CN202010198207 A CN 202010198207A CN 111470072 A CN111470072 A CN 111470072A
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- 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
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Abstract
The invention provides a solar cell array wiring method and system for a GEO orbit triaxial stabilized satellite round shell structure, which comprises the following steps: step M1: unfolding a solar cell array with a circular shell structure of a GEO orbit triaxial stabilized satellite into a planar two-dimensional structure; step M2: arranging a solar cell array assembly on the front surface of the planar two-dimensional structure; step M3: circularly arranging the solar cell array components; step M4: connecting the laid solar array component to a power output electric connector after passing through a rear isolation diode; step M5: directly connecting the power output electric connector to the satellite power control stand-alone machine; step M6: and obtaining the wiring result information of the solar cell array of the GEO orbit triaxial stabilized satellite round shell structure. The invention is simple and reliable, and convenient to operate: the solar cell array wiring is sequentially wired according to the shunt modules of the corresponding satellite power control single machine, and cross wiring is not needed.
Description
Technical Field
The invention relates to the technical field of spaceflight, in particular to a wiring method and system for a solar cell array of a circular shell structure of a three-axis stable satellite in a GEO orbit.
Background
The GEO orbit satellite running in orbit comprises a sailboard type solar cell array, a self-rotating stable type round shell structure solar cell array satellite and a three-axis stable round shell structure solar cell array satellite at present, the sailboard type solar cell array and the self-rotating stable type round shell structure solar cell array satellite are generally uniformly irradiated and uniformly distributed with heat, solar array components can be in one-to-one correspondence with shunt adjusting modules corresponding to a satellite power control single machine after being connected in parallel, but the three-axis stable round shell structure solar cell array satellite only has one irradiated cycle every day, only about one third of the whole shell is in an irradiated state in a time period, other solar arrays are in a shadow state, the thermal characteristic process is in a gradient state, the heat distribution is extremely uneven, and meanwhile, the mode that the solar cell array components are in one-to-one correspondence with the shunt adjusting modules also has a great safety defect. A solar cell array wiring method for a three-axis stabilized satellite with a GEO orbit round shell structure well solves the problem of influencing satellite safety in a mode of sequential circular sheet layout design and direct connection with a satellite power control single machine.
Patent document CN103563092A discloses a solar cell array structure, which includes: a plurality of solar cells (4) arranged on at least one substrate (2); a plurality of contact pads (5) disposed on the at least one substrate, one contact pad for each of the plurality of solar cells; electrical wiring (8, 9) connecting each of the plurality of solar cells with a corresponding one of the plurality of contact pads; and a diode (7) electrically connected to at least two of the plurality of solar cells. There is still room for improvement in solving the problems affecting satellite security.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a solar cell array wiring method and system for a GEO orbit three-axis stable satellite round shell structure.
The solar cell array wiring method for the three-axis stable satellite circular shell structure of the GEO orbit, provided by the invention, comprises the following steps: step M1: according to the control information of the planar two-dimensional structure, unfolding the solar cell array of the three-axis stable satellite circular shell structure of the GEO orbit into a planar two-dimensional structure; step M2: arranging the solar cell array component on the front side of the planar two-dimensional structure according to the solar cell array component arrangement control information; step M3: circularly arranging the solar cell array components according to the circularly arranging control information; step M4: connecting the laid solar array component to a power output electric connector after passing through a rear isolation diode; step M5: directly connecting the power output electric connector to the satellite power control stand-alone machine; step M6: and obtaining the wiring result information of the solar cell array of the GEO orbit triaxial stabilized satellite round shell structure.
Preferably, the step M2 includes: step M2.1: and arranging the solar cell array components on the front surface of the planar two-dimensional structure according to the solar cell array component arrangement control information in an S-shaped mode.
Preferably, the step M3 includes: step M3.1: according to the cyclic arrangement control information, circularly arranging the solar cell array components according to the number and the sequence of the shunting units corresponding to the satellite power control single machine;
preferably, the step M5 includes: step M5.1: each power output electric connector is directly connected with a satellite power control single machine;
preferably, the step M5 includes: step M5.2: and each power output electric connector corresponds to each shunt unit of the satellite power control stand-alone.
The solar cell array wiring system with the GEO orbit triaxial stabilized satellite round shell structure provided by the invention comprises: module M1: according to the control information of the planar two-dimensional structure, unfolding the solar cell array of the three-axis stable satellite circular shell structure of the GEO orbit into a planar two-dimensional structure; module M2: arranging the solar cell array component on the front side of the planar two-dimensional structure according to the solar cell array component arrangement control information; module M3: circularly arranging the solar cell array components according to the circularly arranging control information; module M4: connecting the laid solar array component to a power output electric connector after passing through a rear isolation diode; module M5: directly connecting the power output electric connector to the satellite power control stand-alone machine; module M6: and obtaining the wiring result information of the solar cell array of the GEO orbit triaxial stabilized satellite round shell structure.
Preferably, said module M2 comprises: module M2.1: and arranging the solar cell array components on the front surface of the planar two-dimensional structure according to the solar cell array component arrangement control information in an S-shaped mode.
Preferably, said module M3 comprises: module M3.1: according to the cyclic arrangement control information, circularly arranging the solar cell array components according to the number and the sequence of the shunting units corresponding to the satellite power control single machine;
preferably, said module M5 comprises: module M5.1: each power output electric connector is directly connected with a satellite power control single machine;
preferably, said module M5 comprises: module M5.2: and each power output electric connector corresponds to each shunt unit of the satellite power control stand-alone.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention is simple and reliable, and convenient to operate: the solar cell array wiring is sequentially wired according to the shunt modules of the corresponding satellite power control single machine, and cross wiring is not needed;
2. the invention has the advantages of high reliability and safety: a wiring cycle corresponding to a shunt module of the satellite power control unit corresponds to a power output connector, and each output connector comprises a power supply point of each shunt module, so that the condition of insufficient power supply of the whole satellite caused by the fault of a certain solar array component or the shunt module is avoided, and meanwhile, the power connector is directly connected with the satellite power control unit, so that an intermediate link is eliminated, and the safety is improved;
3. the invention has good thermal effect: by adopting a sequential wiring mode, each shunting module of the satellite power control single machine is ensured to have power output, and the problem of heat concentration of the shunting modules is avoided;
4. the invention can reduce the weight: the problem that the weight is increased due to multiple bending of the cable caused by cross wiring is solved by adopting a sequential wiring mode, and meanwhile, the power connector is directly connected with the satellite power control single machine, so that an intermediate link is cancelled, and the weight of the intermediate link is also reduced;
5. the invention can reduce remanence: and the residual magnetic distance of the solar cell array can be effectively offset by adopting an S-shaped wiring mode.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic diagram of a solar cell array with a circular shell structure unfolded into a two-dimensional structure according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of the connection between a solar array module and a satellite power control unit according to an embodiment of the present invention;
in the figure:
the device comprises a GEO orbit triaxial stabilized satellite round-shell structure solar cell array 1, a two-dimensional structure diagram 2 after the round-shell structure solar cell array is unfolded, a solar cell array component 3, a power electric connector 4 and a satellite power control single machine 5.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1 and fig. 2, the solar cell array wiring method for the GEO-orbit three-axis stable satellite round-shell structure provided by the invention comprises the following steps: step M1: according to the control information of the planar two-dimensional structure, unfolding the solar cell array of the three-axis stable satellite circular shell structure of the GEO orbit into a planar two-dimensional structure; step M2: arranging the solar cell array component on the front side of the planar two-dimensional structure according to the solar cell array component arrangement control information; step M3: circularly arranging the solar cell array components according to the circularly arranging control information; step M4: connecting the laid solar array component to a power output electric connector after passing through a rear isolation diode; step M5: directly connecting the power output electric connector to the satellite power control stand-alone machine; step M6: and obtaining the wiring result information of the solar cell array of the GEO orbit triaxial stabilized satellite round shell structure.
Preferably, the step M2 includes: step M2.1: and arranging the solar cell array components on the front surface of the planar two-dimensional structure according to the solar cell array component arrangement control information in an S-shaped mode.
Preferably, the step M3 includes: step M3.1: according to the cyclic arrangement control information, circularly arranging the solar cell array components according to the number and the sequence of the shunting units corresponding to the satellite power control single machine;
preferably, the step M5 includes: step M5.1: each power output electric connector is directly connected with a satellite power control single machine;
preferably, the step M5 includes: step M5.2: and each power output electric connector corresponds to each shunt unit of the satellite power control stand-alone.
Specifically, in one embodiment, a wiring method for a solar cell array of a GEO-orbiting three-axis stabilized satellite round-shell structure includes: unfolding a solar cell array 1 with a circular shell structure of a GEO orbit triaxial stabilized satellite into a planar two-dimensional structure chart 2; arranging a solar cell array component 3 on the front surface of the planar two-dimensional structure diagram 2 according to an S-shaped mode; circularly arranging the solar cell array components 3 according to the number and the sequence of the shunting modules corresponding to the satellite power control single machine 5; the laid solar cell array component 3 is connected to a power output electric connector 4 through a rear isolation diode; the power output electrical connector 4 is directly connected to the satellite power control stand-alone 5.
Furthermore, the solar cell array components are arranged in an S-shaped mode;
furthermore, the solar cell array components are circularly arranged according to the number and the sequence of the shunting modules corresponding to the satellite power control single machine;
furthermore, each power output electric connector is directly connected with the satellite power control single machine;
furthermore, each power output electric connector corresponds to each shunt module of the satellite power control single machine.
As shown in fig. 1, the solar cell array of the GEO-orbit three-axis stable satellite round-shell structure is unfolded into a two-dimensional structure, which facilitates the sheet distribution design of the solar cell array; the solar cell array wiring is sequentially subjected to S-shaped wiring according to the shunting modules of the corresponding satellite power control single machine, cross wiring is not needed, and the solar cell array wiring is simple, reliable and convenient to operate; a wiring cycle that corresponds with the reposition of redundant personnel module of satellite power control unit corresponds a power output connector, all contains the power supply point of every reposition of redundant personnel module in every output connector, consequently avoided the whole star power supply not enough condition that causes behind certain solar array subassembly or the reposition of redundant personnel module trouble, power connector is direct to be connected with satellite power control unit simultaneously, has cancelled intermediate link, has improved the security, has alleviateed weight, also is favorable to the heat dissipation problem simultaneously.
The solar cell array wiring method for the three-axis stabilized satellite with the GEO orbit round shell structure provided by the invention can be understood as an embodiment of the solar cell array wiring system for the three-axis stabilized satellite with the GEO orbit round shell structure provided by the invention by the technical personnel in the field. Namely, the wiring system of the solar cell array with the circular shell structure of the GEO-orbit triaxial stabilized satellite can be realized by executing the step flow of the wiring method of the solar cell array with the circular shell structure of the GEO-orbit triaxial stabilized satellite.
The solar cell array wiring system with the GEO orbit triaxial stabilized satellite round shell structure provided by the invention comprises: module M1: according to the control information of the planar two-dimensional structure, unfolding the solar cell array of the three-axis stable satellite circular shell structure of the GEO orbit into a planar two-dimensional structure; module M2: arranging the solar cell array component on the front side of the planar two-dimensional structure according to the solar cell array component arrangement control information; module M3: circularly arranging the solar cell array components according to the circularly arranging control information; module M4: connecting the laid solar array component to a power output electric connector after passing through a rear isolation diode; module M5: directly connecting the power output electric connector to the satellite power control stand-alone machine; module M6: and obtaining the wiring result information of the solar cell array of the GEO orbit triaxial stabilized satellite round shell structure.
Preferably, said module M2 comprises: module M2.1: and arranging the solar cell array components on the front surface of the planar two-dimensional structure according to the solar cell array component arrangement control information in an S-shaped mode.
Preferably, said module M3 comprises: module M3.1: according to the cyclic arrangement control information, circularly arranging the solar cell array components according to the number and the sequence of the shunting units corresponding to the satellite power control single machine;
preferably, said module M5 comprises: module M5.1: each power output electric connector is directly connected with a satellite power control single machine;
preferably, said module M5 comprises: module M5.2: and each power output electric connector corresponds to each shunt unit of the satellite power control stand-alone.
The invention is simple and reliable, and convenient to operate: the solar cell array wiring is sequentially wired according to the shunt modules of the corresponding satellite power control single machine, and cross wiring is not needed; the invention has the advantages of high reliability and safety: a wiring cycle corresponding to a shunt module of the satellite power control unit corresponds to a power output connector, and each output connector comprises a power supply point of each shunt module, so that the condition of insufficient power supply of the whole satellite caused by the fault of a certain solar array component or the shunt module is avoided, and meanwhile, the power connector is directly connected with the satellite power control unit, so that an intermediate link is eliminated, and the safety is improved; the invention has good thermal effect: by adopting a sequential wiring mode, each shunting module of the satellite power control single machine is ensured to have power output, and the problem of heat concentration of the shunting modules is avoided; the invention can reduce the weight: the problem that the weight is increased due to multiple bending of the cable caused by cross wiring is solved by adopting a sequential wiring mode, and meanwhile, the power connector is directly connected with the satellite power control single machine, so that an intermediate link is cancelled, and the weight of the intermediate link is also reduced; the invention can reduce remanence: and the residual magnetic distance of the solar cell array can be effectively offset by adopting an S-shaped wiring mode.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A solar cell array wiring method for a three-axis stable satellite circular shell structure in a GEO orbit is characterized by comprising the following steps:
step M1: according to the control information of the planar two-dimensional structure, unfolding the solar cell array of the three-axis stable satellite circular shell structure of the GEO orbit into a planar two-dimensional structure;
step M2: arranging the solar cell array component on the front side of the planar two-dimensional structure according to the solar cell array component arrangement control information;
step M3: circularly arranging the solar cell array components according to the circularly arranging control information;
step M4: connecting the laid solar array component to a power output electric connector after passing through a rear isolation diode;
step M5: directly connecting the power output electric connector to the satellite power control stand-alone machine;
step M6: and obtaining the wiring result information of the solar cell array of the GEO orbit triaxial stabilized satellite round shell structure.
2. The method for wiring the solar cell array of the GEO orbit triaxial stabilized satellite in the round shell structure according to claim 1, wherein the step M2 comprises the following steps:
step M2.1: and arranging the solar cell array components on the front surface of the planar two-dimensional structure according to the solar cell array component arrangement control information in an S-shaped mode.
3. The method for wiring the solar cell array of the GEO orbit triaxial stabilized satellite in the round shell structure according to claim 1, wherein the step M3 comprises the following steps:
step M3.1: and circularly arranging the solar cell array components according to the number and the sequence of the shunting units corresponding to the satellite power control single machine according to the circularly arranged control information.
4. The method for wiring the solar cell array of the GEO orbit triaxial stabilized satellite in the round shell structure according to claim 3, wherein the step M5 comprises the following steps:
step M5.1: each power output electrical connector is directly connected with the satellite power control unit.
5. The wiring method for the solar cell array of the GEO orbit triaxial stabilized satellite round shell structure of claim 4, wherein the step M5 comprises the following steps:
step M5.2: and each power output electric connector corresponds to each shunt unit of the satellite power control stand-alone.
6. The utility model provides a satellite circle shell structure solar cell array wiring system is stabilized to GEO orbit triaxial which characterized in that includes:
module M1: according to the control information of the planar two-dimensional structure, unfolding the solar cell array of the three-axis stable satellite circular shell structure of the GEO orbit into a planar two-dimensional structure;
module M2: arranging the solar cell array component on the front side of the planar two-dimensional structure according to the solar cell array component arrangement control information;
module M3: circularly arranging the solar cell array components according to the circularly arranging control information;
module M4: connecting the laid solar array component to a power output electric connector after passing through a rear isolation diode;
module M5: directly connecting the power output electric connector to the satellite power control stand-alone machine;
module M6: and obtaining the wiring result information of the solar cell array of the GEO orbit triaxial stabilized satellite round shell structure.
7. The GEO orbit triaxial stabilized satellite round-shell structure solar cell array wiring system according to claim 5, wherein the module M2 comprises:
module M2.1: and arranging the solar cell array components on the front surface of the planar two-dimensional structure according to the solar cell array component arrangement control information in an S-shaped mode.
8. The GEO orbit triaxial stabilized satellite round-shell structure solar cell array wiring system according to claim 5, wherein the module M3 comprises:
module M3.1: and circularly arranging the solar cell array components according to the number and the sequence of the shunting units corresponding to the satellite power control single machine according to the circularly arranged control information.
9. The GEO-orbiting three axis stabilized satellite round shell structured solar cell array cabling system according to claim 8, wherein said module M5 comprises:
module M5.1: each power output electrical connector is directly connected with the satellite power control unit.
10. The GEO-orbiting three axis stabilized satellite round shell structured solar cell array cabling system according to claim 9, wherein said module M5 comprises:
module M5.2: and each power output electric connector corresponds to each shunt unit of the satellite power control stand-alone.
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| CN202010198207.XA CN111470072B (en) | 2020-03-19 | 2020-03-19 | Solar cell array wiring method and system for GEO orbit three-axis stable satellite round shell structure |
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