CN117416533B - Magnetically-controlled compacting, unfolding and locking multi-fold solar wing and working method thereof - Google Patents
Magnetically-controlled compacting, unfolding and locking multi-fold solar wing and working method thereof Download PDFInfo
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- CN117416533B CN117416533B CN202311743363.XA CN202311743363A CN117416533B CN 117416533 B CN117416533 B CN 117416533B CN 202311743363 A CN202311743363 A CN 202311743363A CN 117416533 B CN117416533 B CN 117416533B
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- 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
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- 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
- H02S30/00—Structural details of PV modules other than those related to light conversion
- H02S30/20—Collapsible or foldable PV modules
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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 provides a magnetically-controlled compacting, unfolding and locking multi-fold solar wing and a working method thereof, and belongs to the technical field of space product structure and mechanism design. Solves the problems of complex design, high cost and the like of the traditional multi-fold solar wing. The solar energy power generation device comprises a plurality of permanent magnet units, a plurality of electromagnetic units, a plurality of hinges, a plurality of solar wing substrates and a plurality of solar energy battery pieces, wherein the electromagnetic units and the permanent magnet units are combined to be matched with unpowered hinges, so that the whole compressing, unfolding and locking effects can be achieved. The invention can be simplified and split into a plurality of independent single-folded solar wing assemblies, the effect of increasing the solar wing area can be realized by additionally installing the single-folded solar wing assemblies, the effect of reducing the solar wing area can be realized by dismantling the outer single-folded solar wing assemblies, and complicated redesign is not needed.
Description
Technical Field
The invention belongs to the technical field of space product structure and mechanism design, and particularly relates to a magnetically-controlled compacting, unfolding and locking multi-fold solar wing and a working method thereof.
Background
With the increasing demand for satellite power, the use of multi-fold, spread-out solar wings has been increasingly frequent. The traditional multi-fold solar wing is generally composed of a solar wing substrate, a hinge mechanism, a pressing mechanism and the like; before the satellite enters orbit, the multi-fold sun is folded and fixed on the surface of a satellite cabin board or other structural members through a pressing mechanism; after the satellite enters orbit, the pressing point is unlocked, and the solar wing base plate is unfolded and locked under the action of the hinge mechanism.
Conventional multi-fold solar wings suffer from several disadvantages, including: firstly, the traditional multi-fold solar wing needs various mechanisms to realize the compressing, expanding and locking processes, and the mechanism has complex design and high precision requirement, so that the processing period is long and the cost is high; secondly, besides the pressing mechanism and the hinge mechanism, the multi-fold solar wing generally needs to be additionally provided with a locking mechanism design, so that the design complexity of the mechanism is further improved: thirdly, the pressing mechanism always needs to pass through the position of the solar wing substrate to complete fixation, and the substrate is additionally provided with through holes to reduce the area of the substrate and reduce the efficiency of the solar cell; fourth, in the ground unfolding test, a special test environment is needed by using a compressing mechanism for unlocking the initiating explosive device, and the test cost is high; fifthly, after the ground unfolding test, the folding operation difficulty of the multi-fold solar wing is high due to the action effect of the hinge and the locking mechanism; six, in the design process, the solar wing size is changed, and the design and simulation analysis of related institutions need to be developed again to meet new technical indexes.
Disclosure of Invention
In view of the above, the present invention provides a magnetically controlled compact, unfolding and locking multi-fold solar wing and a working method thereof, so as to simplify the mechanism type and design, improve the solar wing substrate sheet distribution efficiency, reduce the ground test cost and operation difficulty, and reduce the redesign workload caused by the solar wing size change.
In order to achieve the above purpose, the present invention adopts the following technical scheme: the utility model provides a magnetic control compresses tightly, expands, many rolls over solar wing of locking, includes a plurality of permanent magnet unit, a plurality of electromagnetic unit, a plurality of hinge, a plurality of solar wing base plate and a plurality of solar cell piece, every solar wing base plate surface mounting has a plurality of solar cell piece, connects through a plurality of hinge between adjacent solar wing base plate and between solar wing base plate and the satellite cabin board, installs a plurality of pairs of permanent magnet unit and electromagnetic unit between adjacent solar wing base plate and between solar wing base plate and the satellite cabin board, permanent magnet unit and electromagnetic unit set up in opposite pairs, and a plurality of permanent magnet unit symmetry are fixed in one side of a solar wing base plate, and a plurality of electromagnetic unit symmetry are fixed in the opposite side of a solar wing base plate.
Furthermore, the permanent magnet unit comprises two first armatures, a magnetic steel groove, magnetic steel, a magnetic steel cushion block and a shell, wherein the two first armatures are fixed at two ends of the magnetic steel groove, the magnetic steel is embedded into the magnetic steel groove and is compressed by the magnetic steel cushion block, and then the combination body is installed in the shell and is fixed.
Furthermore, the magnetic steel material is neodymium iron boron, and the direction of the magnetic steel in the magnetic steel groove is adjusted, so that the direction of the N pole and the S pole of the permanent magnet unit can be changed.
Furthermore, the electromagnetic unit comprises a second armature, an iron core and a coil group, wherein the iron core penetrates into a hole of the coil group, the two second armatures are fixed at two ends of the iron core, and then the combination body is installed in the shell and fixed.
Further, the first armature comprises a forward magnetic attraction seat and a lateral magnetic attraction seat; the second armature comprises a forward magnetic suction head and a lateral magnetic suction head, after installation, the forward magnetic suction seat and the forward magnetic suction head are used for locking and separating in an unfolding state, and the lateral magnetic suction seat and the lateral magnetic suction head are used for compressing and separating in a folding state.
Furthermore, the first armature, the second armature, the magnetic steel groove and the iron core are made of electromagnetic pure iron, the magnetic steel cushion block is made of high-tearing-resistance silicon rubber, and the shell is made of aluminum alloy.
Furthermore, the coil assembly comprises a framework, enamelled wires and wires, wherein the enamelled wires are wound on the framework, after the winding is completed, two ends of each enamelled wire are led out through the wires and used for being electrified in a working stage, and the N pole and the S pole at two ends of the coil assembly can be changed through changing the winding direction of the enamelled wires; by changing the current-carrying direction, the N pole and the S pole at the two ends of the coil assembly can be switched, and the N pole and the S pole of the electromagnetic unit can be changed.
Still further, the backbone material is polyimide.
The working method of the magnetic control compaction, unfolding and locking multi-fold solar wing comprises the steps of carrying out the folding and compaction of the magnetic control compaction, unfolding and locking multi-fold solar wing on the ground, continuously electrifying all electromagnetic units in the forward direction, generating a magnetic field by the electromagnetic units through a coil group, enabling the magnetic pole directions of the electromagnetic units to be the same as those of the opposite permanent magnet units, unlocking adjacent solar wing substrates under the action of magnetic repulsion force, and manually folding the multi-fold solar wing on the basis of repulsive force; in the process of folding the multi-fold solar wing, one side of the adjacent solar wing substrate is provided with a hinge connection, the forward magnetic suction head of the electromagnetic unit is separated from the forward magnetic suction seat of the permanent magnet unit, and the lateral magnetic suction head and the lateral magnetic suction seat are positioned at the outer sides of the adjacent surfaces after rotating around the hinge; the electromagnetic unit is close to the permanent magnet unit at one side of the adjacent solar wing substrate without hinge connection, and the lateral magnetic suction head and the lateral magnetic suction seat are positioned at the adjacent inner side, so that the magnetic poles are opposite in direction, and the lateral magnetic suction head and the lateral magnetic suction seat are contacted and sucked under the action of magnetic attraction to form a closed magnetic loop; all the electromagnetic units are powered off, and the permanent magnet units continuously attract the electromagnetic units through magnetic force to complete fixation.
The working method of the magnetically controlled compaction, unfolding and locking multi-fold solar wing comprises the steps of reversely and continuously powering on all electromagnetic units in a locking mode, wherein the electromagnetic units generate magnetic fields through coil groups, the magnetic pole directions of adjacent solar wing substrates are the same, the electromagnetic units and the permanent magnet units are separated under the action of magnetic repulsion force, and the side generating the repulsive force is far away from a hinge, so that the moment is large, and the magnetic repulsive force is enough to push the solar wing substrates to unfold; after the multi-fold solar wing is fully unfolded, the adjacent solar wing substrate is provided with one side connected by a hinge, the magnetic pole directions of the electromagnetic unit and the permanent magnetic unit are opposite, and the forward magnetic suction head of the electromagnetic unit is attracted with the forward magnetic suction seat of the permanent magnetic unit to form a closed magnetic loop; all the electromagnetic units are powered off, and the permanent magnet units continuously attract the electromagnetic units through magnetic force to complete locking.
Compared with the prior art, the multi-fold solar wing with the magnetic control compressing, expanding and locking functions and the working method thereof have the advantages that:
(1) The multi-folding solar wing is simple in composition, and the whole compacting, unfolding and locking effects can be achieved through the combination of the electromagnetic unit and the permanent magnet unit and the unpowered hinge.
(2) The multi-fold solar wing has the advantages of simple design of each mechanism, small size of component parts, lower precision requirement, low processing cost and short processing period.
(3) The multi-folded solar wing can be simply split into a plurality of independent single-folded solar wing assemblies, the effect of increasing the solar wing area can be realized by additionally installing the single-folded solar wing assemblies, the effect of reducing the solar wing area can be realized by dismantling the outer single-folded solar wing assemblies, and complicated redesign is not needed.
(4) According to the multi-folding solar wing, the electromagnetic unit, the permanent magnet unit and the hinge are fixed at the position where the edge of the surface of the solar wing substrate cannot be coated, so that the waste of the coating area of the solar wing substrate is reduced, and the coating efficiency is improved.
(5) Compared with the traditional compaction mode, the impact of the multi-fold solar wing unfolding process is smaller, the impact influence on platform equipment is reduced, the in-orbit attitude disturbance of a satellite is reduced, and the attitude control is facilitated.
(6) The mechanisms of the multi-fold solar wing disclosed by the invention can be repeatedly used, so that the ground test cost is reduced.
(7) The multi-fold solar wing ground test has low operation difficulty, can be folded by a single person, and reduces the manpower waste of operators; no special requirement on the operation environment, and reduced environmental cost.
(8) According to the multi-fold solar wing, the electromagnetic unit and the permanent magnet unit form a complete closed magnetic loop in the attraction state, so that the magnetic leakage is low, and the normal operation of satellite magnetic equipment is not influenced.
(9) The multi-fold solar wing disclosed by the invention has the advantages of simple structure of each part, small processing difficulty and convenience for industrial production and application.
(10) The multi-fold solar wing disclosed by the invention has the advantages that all parts are mutually independent, secondary design/selection can be performed according to specific satellite requirements, and the device has strong adaptability.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:
FIG. 1 is a schematic view of the overall composition of a multi-fold solar wing;
FIG. 2 is a schematic view of a partial composition of a multi-fold solar wing;
FIG. 3 is an exploded view of a permanent magnet unit;
FIG. 4 is a schematic diagram of a permanent magnet unit structure 1;
FIG. 5 is a schematic diagram of a permanent magnet unit structure 2;
FIG. 6 is an exploded view of an electromagnetic unit;
FIG. 7 is a schematic diagram of the electromagnetic unit structure 1;
FIG. 8 is a schematic diagram of the electromagnetic unit structure 2;
FIG. 9 is a schematic diagram of a coil assembly;
FIG. 10 is a schematic view of a hinge assembly 1;
FIG. 11 is a schematic view of a hinge assembly 2;
FIG. 12 is a schematic view of a single-fold solar wing installation;
FIG. 13 is an overall schematic of a multi-fold solar wing installation;
FIG. 14 is a partial schematic view of a multi-fold solar wing installation;
FIG. 15 is a schematic view of the magnetic pole direction and closed magnetic circuit when the electromagnetic unit is not energized;
FIG. 16 is a schematic view of the pole direction of the electromagnetic unit when it is positively energized;
FIG. 17 is a schematic view of a multi-fold solar wing gathering process when the electromagnetic unit is powered on in the forward direction;
FIG. 18 is an overall schematic of a multi-fold solar wing compression state;
FIG. 19 is a partial schematic view of a multi-fold solar wing compression state;
FIG. 20 is a schematic view of a multi-fold solar span opening process when the electromagnetic unit is energized in reverse;
fig. 21 is a schematic view of the magnetic pole direction and the closed magnetic circuit when the electromagnetic unit is electrified reversely.
The symbols in the drawings are as follows: the solar energy power generation device comprises a permanent magnet unit 1, an electromagnetic unit 2, a hinge 3, a solar wing substrate 4, a solar cell 5, a satellite cabin plate 6, a first armature 1-1, a forward magnetic attraction seat 1-1, a lateral magnetic attraction seat 1-1-2, a magnetic steel groove 1-2, a magnetic steel 1-3, a magnetic steel cushion block 1-4, a first shell 1-5, a second shell 1-6, a third shell 1-7, a second armature 2-1, a forward magnetic suction head 2-1-1, a lateral magnetic suction head 2-1-2, an iron core 2-2, a coil group 2-3, a framework 2-3-1, enameled wires 2-3-2, a lead wire 2-3-3, a first hinge rod 3-1, a second hinge rod 3-2, a third hinge rod 3-3, a rotating shaft 3-4 and a nut 3-5.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It should be noted that, in the case of no conflict, embodiments of the present invention and features of the embodiments may be combined with each other, and the described embodiments are only some embodiments of the present invention, not all embodiments.
Referring to fig. 1-21, the embodiment is illustrated as a magnetically controlled compacting, unfolding and locking multi-fold solar wing, which comprises a permanent magnet unit 1, an electromagnetic unit 2, a hinge 3, solar wing substrates 4, solar cells 5 and corresponding standard components, wherein a plurality of solar cells 5 are installed on the surface of each solar wing substrate 4, a plurality of pairs of permanent magnet units 1 and electromagnetic units 2 are installed between adjacent solar wing substrates 4 and between the solar wing substrates 4 and a satellite cabin board 6 through a plurality of hinges 3, the permanent magnet units 1 and the electromagnetic units 2 are oppositely arranged in pairs, a plurality of permanent magnet units 1 are symmetrically fixed on one side of one solar wing substrate 4, and a plurality of electromagnetic units 2 are symmetrically fixed on the other side of one solar wing substrate 4.
In this embodiment, as shown in fig. 3, the permanent magnet unit 1 includes a first armature 1-1, a magnetic steel groove 1-2, a magnetic steel 1-3, a magnetic steel pad 1-4, a first housing 1-5, a second housing 1-6, a third housing 1-7, and corresponding standard components, and the installation relationship is as follows: the two first armatures 1-1 are fixed at two ends of the magnetic steel groove 1-2 through standard components, the magnetic steel 1-3 is embedded into the magnetic steel groove 1-2 and is compressed by the magnetic steel cushion block 1-4, then the combination body is installed in the shell, and the fixing is completed through the standard components. The permanent magnet units 1 used between the solar wing substrates 4 are fixed with the second shells 1-6 through the first shells 1-5, as shown in fig. 4. The permanent magnet unit 1 used between the solar wing base plate 4 and the satellite cabin plate 6 is fixed by a first shell 1-5 and a third shell 1-7, as shown in fig. 5.
In the embodiment, the structure of the first armature 1-1 is shown in fig. 4 and 5, and comprises a forward magnetic attraction seat 1-1-1 and a lateral magnetic attraction seat 1-1-2, wherein the forward magnetic attraction seat 1-1-1 and the lateral magnetic attraction seat 1-1-2 are matched for use; the structure of the second armature 2-1 is shown in fig. 7 and 8, and comprises a forward magnetic suction head 2-1-1 and a lateral magnetic suction head 2-1-2, wherein the forward magnetic suction head 2-1-1 and the lateral magnetic suction head 2-1-2 are matched for use. After the installation is completed, the forward magnetic suction head 2-1-1 and the forward magnetic suction seat 1-1 are used for locking and separating in an unfolding state, and the lateral magnetic suction head 2-1-2 and the lateral magnetic suction seat 1-1-2 are used for compressing and separating in a folding state. The magnetic suction seat and the magnetic suction head are matched in structure, the ball head and the conical surface play a role in guiding in the suction process, the blocking can be avoided in the separation process, and the suction position of the magnetic suction seat and the suction position of the magnetic suction head are in a close fit state in the suction state.
In the embodiment, the magnetic steel 1-3 material is preferably neodymium iron boron, and the magnetic energy product of the magnetic steel material is large, so that the miniaturization design of permanent magnet single indication can be realized; the magnetic steel material has wide use limit temperature range and can avoid the magnetic steel demagnetizing caused by the high and low temperature environment of the space. The direction of the magnetic steel 1-3 in the magnetic steel groove 1-2 is adjusted according to the requirement, and the direction of the N pole and the S pole of the permanent magnet unit 1 can be changed.
In the embodiment, materials of the first armature 1-1, the second armature 2-1, the magnetic steel groove 1-2 and the iron core 2-2 are preferably electromagnetic pure iron, materials of the magnetic steel cushion block 1-4 are preferably high-tear-resistance silicon rubber, materials of the framework 2-3-1 are preferably polyimide, and materials of the first shell 1-5, the second shell 1-6 and the third shell 1-7 are preferably aluminum alloy.
In the present embodiment, as shown in fig. 6, the electromagnetic unit 2 includes: the installation relationship of the second armature 2-1, the iron core 2-2, the coil group 2-3, the first shell 1-5, the second shell 1-6, the third shell 1-7 and corresponding standard components is as follows: the iron core 2-2 is penetrated into the holes of the coil group 2-3, the two second armatures 2-1 are fixed at the two ends of the iron core 2-2 through standard components, then the combination body is installed in the shell, and the fixation is completed through the standard components. Wherein the electromagnetic unit 2 used between the solar wing substrates 4 is fixed with the second housing 1-6 through the first housing 1-5, as shown in fig. 7. The electromagnetic unit 2 used between the solar wing base plate 4 and the satellite capsule plate 6 is fixed by a first housing 1-5 and a third housing 1-7, as shown in fig. 8.
In this embodiment, the coil assembly 2-3 is shown in fig. 9, and its composition includes: 2-3-1 of framework, 2-3-2 of enamelled wire and 2-3-3 of lead wire, and the installation relationship is as follows: winding the enameled wire 2-3-2 on the framework 2-3-1, and leading out two ends of the enameled wire 2-3-2 through the lead 2-3-3 after winding is completed for electrifying in a working stage. The N pole and the S pole at two ends of the coil group 2-3 can be changed by changing the winding direction of the enameled wire 2-3-2; by changing the current direction, the N pole and the S pole at the two ends of the coil assembly 2-3 can be switched, so that the N pole and the S pole of the electromagnetic unit 2 can be changed.
In the present embodiment, the hinge 3 is composed of: a first hinge rod 3-1, a second hinge rod 3-2, a third hinge rod 3-3, a rotating shaft 3-4 and a nut 3-5. As shown in FIG. 10, the hinge 3 used between the solar wing substrates 4 is characterized in that the rotating shafts 3-4 penetrate through the rotating shaft holes of the first hinge rod 3-1 and the second hinge rod 3-2 and are fixed by nuts 3-5; the hinge 3 used between the solar wing base plate 4 and the satellite cabin plate 6 is shown in fig. 11, and the rotating shaft 3-4 passes through the rotating shaft holes of the first hinge rod 3-1 and the third hinge rod 3-3 and is fixed by the nut 3-5. The rotating shaft 3-4 of the hinge 3 is preferably coated with molybdenum disulfide to reduce sliding friction resistance and prevent cold welding in a vacuum environment.
In this embodiment, the mounting manner of the single-folded solar wing in the magnetically controlled compact, unfolded and locked multi-folded solar wing is as follows: as shown in fig. 12, two permanent magnet units 1 are symmetrically fixed to one side of one solar wing substrate 4, two electromagnetic units 2 are symmetrically fixed to the other side of one solar wing substrate 4, and solar cells 5 are arranged on one side of the solar wing substrate 4.
In this embodiment, the installation mode of the multi-fold solar wing in the multi-fold solar wing that is magnetically controlled to compress, expand and lock is as follows: as shown in fig. 13 and 14, two adjacent single-folded solar wings are connected through two hinges 3, one side of each of the two connected solar wing substrates 4, which is adjacent, is respectively provided with a permanent magnet unit 1 and an electromagnetic unit 2, and solar cells 5 are coplanar. When the electromagnetic unit 2 is not electrified, the adjacent solar wing substrate 4 is provided with one side connected by the hinge 3, the magnetic steel 1-3 in the permanent magnet unit 1 provides magnetic force, the forward magnetic attraction seat 1-1-1 of the permanent magnet unit 1 is attracted and fixed with the forward magnetic attraction head 2-1-1 of the electromagnetic unit 2, and a closed loop is formed, as shown in fig. 15. The surface of the satellite cabin board 6 for fixing the multi-fold solar wing is provided with two permanent magnet units 1, two electromagnetic units 2 and two hinges 3, the solar wing assembly which is installed is connected with the satellite cabin board 6 through the two hinges 3, and the permanent magnet units 1 on the surface of the satellite cabin board 6 are sucked to complete fixation.
In this embodiment, a working method of a magnetically controlled compacting, unfolding and locking multi-fold solar wing includes the steps of: the electromagnetic units 2 generate magnetic fields through the coil sets 2-3 by continuously energizing all the electromagnetic units 2 in the forward direction. As shown in fig. 16, the magnetic pole direction of the electromagnetic unit 2 is designed, and the adjacent solar wing substrates 4 are unlocked under the action of magnetic repulsion force, as the adjacent permanent magnet units 1; at this time, the manual folding of the multi-fold solar wing is assisted on the basis of the repulsive force. As shown in fig. 17, in the process of folding the multi-fold solar wing, the adjacent solar wing substrate 4 is provided with one side connected by the hinge 3, the forward magnetic suction head 2-1-1 of the electromagnetic unit 2 is separated from the forward magnetic suction seat 1-1-1 of the permanent magnet unit 1, and after rotating around the hinge 3, the lateral magnetic suction head 2-1-2 and the lateral magnetic suction seat 1-1-2 are positioned at the outer side of the adjacent surface, so that the electromagnetic unit 2 is not contacted with the permanent magnet unit 1 after being separated; the electromagnetic unit 2 and the permanent magnet unit 1 are close to each other along the dotted line direction at one side of the adjacent solar wing substrate 4, which is not connected by the hinge 3, and the lateral magnetic suction head 2-1-2 and the lateral magnetic suction seat 1-1-2 are positioned at the adjacent inner side, so that the magnetic poles are opposite in direction, contact and suction under the action of magnetic attraction force, and a closed magnetic loop is formed. All the electromagnetic units 2 are powered off, and the permanent magnet units 1 continuously attract the electromagnetic units 2 through magnetic force to complete fixation, as shown in fig. 18 and 19.
In this embodiment, the permanent magnet unit 1, the electromagnetic unit 2 and the hinge 3 are all fixed on the solar wing substrate 4 by a set screw-set nut, and the fixing on the surface of the satellite cabin board 6 is all realized by a standard component.
In this embodiment, a working method of a magnetically controlled compacting, unfolding and locking multi-fold solar wing includes the following steps: as shown in fig. 20, the reverse continuous energization is performed to all the electromagnetic units 2, the electromagnetic units 2 generate magnetic fields through the coil groups 2-3, and the magnetic pole directions of the electromagnetic units 2 are completely opposite to those of the electromagnetic units 2 in the embodiment 2. The magnetic pole directions of the electromagnetic unit 2 and the permanent magnet unit 1 are the same on one side of the adjacent solar wing substrate 4, which is not connected by the hinge 3, and the two are separated under the action of magnetic repulsion force, and the solar wing substrate 4 is far away along the dotted line direction; since the side where the repulsive force is generated is far from the hinge 3, the moment is large and the magnetic repulsive force is enough to push the solar wing substrate 4 to be unfolded. After the multi-fold solar wing is fully unfolded, the adjacent solar wing substrate 4 is provided with one side connected by the hinge 3, the magnetic pole directions of the electromagnetic unit 2 and the permanent magnet unit 1 are opposite, and the forward magnetic suction head 2-1-1 of the electromagnetic unit 2 and the forward magnetic suction seat 1-1-1 of the permanent magnet unit 1 are attracted to form a closed magnetic loop, as shown in fig. 21. All the electromagnetic units 2 are powered off, and the permanent magnet units 1 continuously attract the electromagnetic units 2 through magnetic force to complete locking, as shown in fig. 15.
In this embodiment, when the permanent magnet unit 1 and the electromagnetic unit 2 are in the attraction state: because the magnetic steel 1-3, the first armature 1-1, the second armature 2-1 and the iron core 2-2 form a closed magnetic loop, the magnetic leakage is very small, the other components of the mechanism are not influenced, and meanwhile, the normal operation of the satellite magnetic equipment is not influenced.
The permanent magnet unit 1, the electromagnetic unit 2 and the hinge 3 are fixed on the solar wing base plate 4 through sleeve screws and sleeve nuts, and the surface of the satellite cabin plate 6 is fixed through standard components.
The solar wing base plates 4 can be changed in size and number according to specific satellite requirements.
The magnetic force design of the permanent magnet unit 1 and the electromagnetic unit 2 can be adjusted in a matching way according to the size and the unfolding technical index of the solar wing substrate 4.
The embodiments of the invention disclosed above are intended only to help illustrate the invention. The examples are not intended to be exhaustive or to limit the invention to the precise forms disclosed. Many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best understand and utilize the invention.
Claims (7)
1. A magnetic control compresses tightly, expands, many solar wings of locking which characterized in that: the solar photovoltaic module comprises a plurality of permanent magnet units (1), a plurality of electromagnetic units (2), a plurality of hinges (3), a plurality of solar wing substrates (4) and a plurality of solar cell pieces (5), wherein the solar cell pieces (5) are arranged on the surface of each solar wing substrate (4), the adjacent solar wing substrates (4) and the satellite cabin board (6) are connected through the hinges (3), a plurality of pairs of permanent magnet units (1) and electromagnetic units (2) are arranged between the adjacent solar wing substrates (4) and between the solar wing substrates (4) and the satellite cabin board (6), the permanent magnet units (1) and the electromagnetic units (2) are oppositely arranged in pairs, the permanent magnet units (1) are symmetrically fixed on one side of one solar wing substrate (4), and the electromagnetic units (2) are symmetrically fixed on the other side of one solar wing substrate (4);
the permanent magnet unit (1) comprises two first armatures (1-1), a magnetic steel groove (1-2), magnetic steel (1-3), a magnetic steel cushion block (1-4) and a shell, wherein the two first armatures (1-1) are fixed at two ends of the magnetic steel groove (1-2), the magnetic steel (1-3) is embedded into the magnetic steel groove (1-2) and is compressed by the magnetic steel cushion block (1-4), and then the assembly is installed in the shell and fixed;
the electromagnetic unit (2) comprises a second armature (2-1), an iron core (2-2) and a coil assembly (2-3), the iron core (2-2) is penetrated into a hole of the coil assembly (2-3), the two second armatures (2-1) are fixed at two ends of the iron core (2-2), and then the combination body is installed in a shell and fixed;
the first armature (1-1) comprises a forward magnetic attraction seat (1-1-1) and a lateral magnetic attraction seat (1-1-2), and the forward magnetic attraction seat (1-1-1) and the lateral magnetic attraction seat (1-1-2) are matched for use; the second armature (2-1) comprises a forward magnetic suction head (2-1-1) and a lateral magnetic suction head (2-1-2), the forward magnetic suction head (2-1-1) and the lateral magnetic suction head (2-1-2) are matched for use, and after installation, the forward magnetic suction seat (1-1-1) and the forward magnetic suction head (2-1-1) are used for locking and separating in an unfolding state, and the lateral magnetic suction seat (1-1-2) and the lateral magnetic suction head (2-1-2) are used for compressing and separating in a folding state.
2. The magnetically controlled compacting, expanding, locking multi-fold solar wing of claim 1, wherein: the magnetic steel (1-3) is made of neodymium iron boron, the direction of the magnetic steel (1-3) in the magnetic steel groove (1-2) is adjusted, and the direction of the N pole and the S pole of the permanent magnet unit (1) can be changed.
3. The magnetically controlled compacting, expanding, locking multi-fold solar wing of claim 1, wherein: the first armature (1-1), the second armature (2-1), the magnetic steel groove (1-2) and the iron core (2-2) are made of electromagnetic pure iron, the magnetic steel cushion block (1-4) is made of high-tearing-resistance silicon rubber, and the shell is made of aluminum alloy.
4. The magnetically controlled compacting, expanding, locking multi-fold solar wing of claim 1, wherein: the coil assembly (2-3) comprises a framework (2-3-1), enameled wires (2-3-2) and a conducting wire (2-3-3), wherein the enameled wires (2-3-2) are wound on the framework (2-3-1), after winding is completed, two ends of the enameled wires (2-3-2) are led out through the conducting wire (2-3-3) and are used for being electrified in a working stage, and N poles and S poles at two ends of the coil assembly (2-3) can be changed through changing the winding direction of the enameled wires (2-3-2); by changing the current-carrying direction, the N pole and the S pole at the two ends of the coil group (2-3) can be switched, and the N pole and the S pole of the electromagnetic unit (2) can be changed.
5. The magnetically controlled compacting, expanding, locking multi-fold solar wing of claim 4, wherein: the framework (2-3-1) is made of polyimide.
6. A method for operating a magnetically controlled compacting, unfolding and locking multi-fold solar wing as claimed in claim 1, characterized by: the method for folding and compacting the multi-fold solar wing on the ground comprises the steps of magnetic control compaction, unfolding and locking, and specifically comprises the following steps: the electromagnetic units (2) generate magnetic fields through the coil groups (2-3), the magnetic pole directions of the electromagnetic units (2) are the same as those of the opposite permanent magnet units (1), and the adjacent solar wing substrates (4) are unlocked under the action of magnetic repulsion force; in the process of folding the multi-fold solar wing, one side, connected by a hinge (3), of the adjacent solar wing substrate (4), the forward magnetic suction head (2-1-1) of the electromagnetic unit (2) is separated from the forward magnetic suction seat (1-1-1) of the permanent magnetic unit (1), and the lateral magnetic suction head (2-1-2) and the lateral magnetic suction seat (1-1-2) are positioned on the outer side of the adjacent surface after rotating around the hinge (3); the side of the adjacent solar wing substrate (4) which is not connected with the hinge (3) is close to the permanent magnet unit (1), and the lateral magnetic suction head (2-1-2) and the lateral magnetic suction seat (1-1-2) are positioned at the adjacent inner side, so that the magnetic poles are opposite in direction and contact and suction under the action of magnetic attraction to form a closed magnetic loop; all the electromagnetic units (2) are powered off, and the permanent magnet units (1) continuously attract the electromagnetic units (2) through magnetic force to complete fixation.
7. A method for operating a magnetically controlled compacting, unfolding and locking multi-fold solar wing as claimed in claim 1, characterized by: the unfolding and locking method of the multi-fold solar wing comprises the steps of magnetic control compaction, unfolding and locking, and specifically comprises the following steps: the electromagnetic units (2) are electrified reversely and continuously, the electromagnetic units (2) generate magnetic fields through the coil groups (2-3), the adjacent solar wing substrates (4) are connected on one side without hinges (3), the magnetic pole directions of the electromagnetic units (2) and the permanent magnet units (1) are the same, the electromagnetic units and the permanent magnet units are separated under the action of magnetic repulsion force, and the side generating the repulsive force is far away from the hinges (3), so that the moment is large, and the magnetic repulsive force is enough to push the solar wing substrates (4) to be unfolded; after the multi-fold solar wing is fully unfolded, the adjacent solar wing substrate (4) is provided with one side connected with the hinge (3), the magnetic pole directions of the electromagnetic unit (2) and the permanent magnet unit (1) are opposite, and the forward magnetic suction head (2-1-1) of the electromagnetic unit (2) is attracted with the forward magnetic suction seat (1-1-1) of the permanent magnet unit (1) to form a closed magnetic loop; all the electromagnetic units (2) are powered off, and the permanent magnet units (1) continuously attract the electromagnetic units (2) through magnetic force to complete locking.
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