CN213502958U - Solar cell array storage device for spacecraft - Google Patents

Abstract

The utility model relates to a space flight technical field especially relates to a solar cell battle array storage device that spacecraft was used, include: expanding the support structure, the compressed gas cylinder and the containing cabin; the expansion supporting structure is arranged inside the containing cabin, and the compressed gas cylinder is arranged inside the satellite and used for inflating the elastic supporting rod, so that the pipe body can be supported outside the satellite after being inflated; the utility model effectively realizes the storage of the flexible wings through the arrangement of the containing cabin structure, when the satellite enters the track, the heating device inside the upper cover plate works, the screw thread on the wall of the central plate is heated and melted, and then the annular side plate is separated from the upper cover plate, the annular side plate is contracted under the action of self elasticity, thereby the elastic supporting rod is not limited by the annular side plate to be extended outwards, the whole structure is simple, and the flexible wings are convenient to store and expand; and the annular flexible side plate is adopted, so that the weight is relatively lighter, and the satellite launching operation is facilitated.

Description

Solar cell array storage device for spacecraft

Technical Field

The utility model relates to an aerospace technical field especially relates to a solar cell battle array storage device that spacecraft was used.

Background

The power supply of the artificial satellite generally adopts solar cells, and a solar cell panel assembly is arranged on the satellite and used for collecting sunlight and converting light energy into electric energy to supply power to the satellite. The traditional satellite solar cell array structure is heavy in weight and high in cost, and the micro-nano satellite cannot carry a large-area traditional rigid solar cell array due to the limitation of volume and weight. By combining the flexible solar cell with the inflatable and expandable solar sail, a large-area solar cell array which is folded before being launched on the ground, has small volume and light weight and is launched on the rail and expanded by inflation is formed.

Therefore, for the micro-nano satellite, it is particularly important that the storage device with reasonable design is matched with the expansion of the solar cell wing.

Disclosure of Invention

Therefore, the utility model discloses just make in view of above problem, the utility model discloses a setting of holding cabin structure realizes rationally matching the storage of solar cell wing and expandes. The utility model discloses a realize above-mentioned purpose through following technical scheme:

a solar battery array storage device for a spacecraft comprises a satellite, a compressed gas cylinder and a containing cabin; the satellite is arranged in the accommodating cabin, and the compressed gas cylinder is arranged in the satellite; an expansion supporting structure is arranged around the satellite and comprises an elastic supporting rod, the inner end of the elastic supporting rod is fixedly connected with the periphery of the satellite, and the compressed gas cylinder is communicated with the elastic supporting rod; a flexible wing is arranged between the elastic support rods, the inner end of the flexible wing is fixedly connected with the periphery of the satellite, and two sides of a symmetrical axis of the flexible wing are connected with the elastic support rods through springs; the upper surface of the flexible wing is provided with a solar cell; the accommodation cabin comprises a bottom plate, and the satellite is arranged above the bottom plate; a support column is arranged in the middle of the top end of the satellite, a limit groove is formed in the top end of the support column, an upper cover plate is arranged in the limit groove, a central plate is arranged in the middle of the bottom of the upper cover plate, and a heating device is arranged in the central plate; the middle part of the upper cover plate is provided with a through hole which is matched with the limiting groove; an annular groove is formed in the periphery of the bottom surface of the upper cover plate, and a first thread is arranged in the annular groove; the top of the bottom plate is fixedly connected with an annular side plate close to the outer side of the satellite, the inner wall above the annular side plate is provided with a second thread, and the second thread is matched with the first thread.

Preferably, an elastic support frame is arranged inside the annular side plate and is formed by elastically hinging and combining a plurality of small hard support rods.

Preferably, the inner wall of the annular side plate is provided with four clamping plates; the clamping plates are matched with the flexible wings.

The utility model has the advantages as follows:

1. the utility model effectively realizes the storage of the flexible wings through the arrangement of the containing cabin structure, when the satellite enters the track, the heating device inside the upper cover plate works, the screw thread on the wall of the central plate is heated and melted, and then the annular side plate is separated from the upper cover plate, the annular side plate is contracted under the action of self elasticity, thereby the elastic supporting rod is not limited by the annular side plate to be extended outwards, the whole structure is simple, and the flexible wings are convenient to store and expand;

2. the utility model discloses an adopt the flexible curb plate of annular, the quality is lighter relatively, does benefit to the satellite transmission operation.

Drawings

Fig. 1 is a schematic structural view of the flexible solar wing according to the present invention.

Fig. 2 is a schematic view of the connection between the elastic support rod and the satellite according to the present invention.

Fig. 3 is a schematic view of the overall structure of the accommodation cabin of the present invention.

Fig. 4 is a first detailed schematic view of the accommodation chamber of the present invention.

Fig. 5 is a second detailed schematic view of the accommodation chamber of the present invention.

Fig. 6 is a schematic view of the overall structure of the annular side plate after contraction of the flexible wing.

Fig. 7 is a schematic partial sectional view of the annular side plate of the present invention.

Fig. 8 is a schematic sectional view of the clamping plate arranged on the inner wall of the annular side plate of the present invention.

Description of the drawings: 1. deploying the support structure; 11. an elastic support bar; 12. a flexible wing; 13. a solar cell; 2. a compressed gas cylinder; 3. a housing compartment; 31. a base plate; 32. a support pillar; 33. a limiting groove; 34. an upper cover plate; 341. a center plate; 35. a through hole; 36. an annular groove; 37. a first thread; 38. an annular side plate; 381. an elastic support frame; 39. a second thread; 382. clamping a plate; 4. and (4) a satellite.

Detailed Description

The preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings, which are easily implemented by those having ordinary skill in the art to which the present invention pertains. The invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. In addition, for the purpose of more clearly describing the present invention, parts not connected with the present invention will be omitted from the drawings.

As shown in fig. 1 to 3, a solar cell array storage device for a spacecraft includes: unfolding a supporting structure 1, a compressed gas cylinder 2 and a containing cabin 3;

the unfolding support structure 1 is arranged inside the containment compartment 3, the unfolding support structure 1 comprising: the flexible support rod 11, the flexible wings 12 and the solar cell 13; the elastic support rods 11 are supported at four corners of the square satellite 4, the satellite 4 is located at the center, the elastic support rods 11 are inflatable tubes, the elastic support rods 11 are supported and unfolded after the tubes are inflated, and the unfolding of the elastic support rods 11 further drives the flexible wings 12 connected with the elastic support rods 11 to unfold together; the flexible wing 12 is composed of four triangular blocks, the flexible wing 12 is integrally of a square structure, one corner of each triangular block of the flexible wing 12 is connected with the satellite 4, and the other two corners of each triangular block are connected with two adjacent elastic supporting rods 11 through springs, so that the square flexible wing 12 composed of the four triangular blocks is formed, a plurality of solar cells 13 are arrayed on each triangular block, and sunlight is converted into electric energy through the solar cells 13; the compressed gas bottle 2 is arranged inside the satellite 4, and the compressed gas bottle 2 is communicated with the tube body of the elastic support rod 11 and is used for inflating the elastic support rod 11, so that the tube body can be supported outside the satellite 4 after being inflated;

as shown in fig. 3 to 6, the accommodation compartment 3 includes: the structure comprises a bottom plate 31, a support pillar 32, a limiting groove 33, an upper cover plate 34, a through hole 35, an annular groove 36, a first thread 37, an annular side plate 38 and a second thread 39; the bottom plate 31 is provided with a satellite 4, the middle of the top end of the satellite 4 is provided with a support column 32, the support column 32 is provided with a limit groove 33, the middle of an upper cover plate 34 is provided with a through hole 35, the through hole 35 of the upper cover plate 34 penetrates through the support column 32 and is arranged in the limit groove 33 of the support column 32, the bottom surface of the upper cover plate 34 is provided with an annular groove 36, the inner side wall of the annular groove 36 is provided with a first thread 37, the first thread 37 is made of a high-temperature meltable material, and a heating device (not shown) is arranged inside a central; the annular side plate 38 is made of an annular flexible plate, the annular side plate 38 is elastically retractable and foldable, the bottom surface of the annular side plate 38 is fixedly arranged on the bottom plate 31, a second thread 39 is arranged on the inner wall of the annular side plate 38 close to the upper part, the upper end of the annular side plate 38 is inserted into the annular groove 36 of the upper cover plate 34, and the second thread 39 is meshed with the first thread 37; when the upper cover plate 34 is screwed, the center of the upper cover plate 34 rotates along the limiting groove 33, the second screw thread 39 is meshed with the first screw thread 37, and the annular side plate 38 is in an extended state, so that the bottom plate 31, the upper cover plate 34 and the annular side plate 38 form the whole accommodating chamber 3 with an accommodating function;

as shown in fig. 7, preferably, as an implementation mode, the annular side plate 38 is provided with elastic supports 381 inside, the elastic supports 381 are uniformly distributed inside the annular side plate 38 at intervals, and the elastic supports 381 are a combination of a plurality of small hard support rods which are elastically hinged, so that the support strength and elasticity of the annular side plate 38 are enhanced, and the contraction of the annular side plate 38 is further facilitated;

as shown in fig. 8, preferably, as an implementation mode, four clip boards 382 having a shape of "bar" are disposed on the inner wall of the circular side plate 38, and are uniformly distributed in the middle of the circular side plate 38, and the four clip boards 382 respectively correspond to four corners of the square structure of the flexible wing 12, which facilitates further pressing of the flexible wing 12.

The utility model discloses a theory of operation:

before the satellite 4 is launched, the containing cabin 3 is installed on the satellite 4, and at this time, the bottom plate 31, the upper cover plate 34 and the annular side plate 38 form the whole containing cabin 3 with a containing function; launching the satellite 4 into space, when the satellite 4 enters the orbit, the heating device inside the upper cover plate 34 works to raise the temperature of the edge of the central plate 341 of the upper cover plate 34, the first thread 37 on the wall of the central plate 341 is heated and melted, and then the annular side plate 38 is separated from the upper cover plate 34, the annular side plate 38 contracts under the action of the self elasticity, and the annular side plate 38 contracts to a position close to the bottom plate 31; after annular curb plate 38 contracts, elastic support rod 11 does not receive the outside bullet of annular curb plate 38 restriction to stretch, the solenoid valve of compressed gas cylinder 2 is opened afterwards, inflate elastic support rod 11 by compressed gas cylinder 2, make elastic support rod 11 inflate the expansion, support in the outside in structure cabin, the in-process that elastic support rod 11 expandes is driving flexible wing 12 and is expanding together, make flexible wing 12 be in the planar state of expansion under elastic support rod 11's support at last, the positive solar cell 13 of flexible wing 12 carries out photoelectric conversion, supply power to satellite 4.

Claims (3)

1. A solar battery array storage device for a spacecraft comprises a satellite (4), a compressed gas cylinder (2) and a containing cabin (3); the method is characterized in that: the satellite (4) is arranged inside the accommodating cabin (3), and the compressed gas bottle (2) is arranged inside the satellite (4); an expansion supporting structure (1) is arranged on the periphery of the satellite (4), the expansion supporting structure (1) comprises an elastic supporting rod (11), the inner end of the elastic supporting rod (11) is fixedly connected with the periphery of the satellite (4), and the compressed gas cylinder (2) is communicated with the elastic supporting rod (11); flexible wings (12) are arranged between the elastic supporting rods (11), the inner ends of the flexible wings (12) are fixedly connected with the periphery of the satellite (4), and two sides of the symmetry axis of the flexible wings (12) are connected with the elastic supporting rods (11) through springs; the upper surface of the flexible wing (12) is provided with a solar cell (13); the accommodation compartment (3) comprises a floor (31), the satellite (4) being arranged above the floor (31); a support column (32) is arranged in the middle of the top end of the satellite (4), a limit groove (33) is formed in the top end of the support column (32), an upper cover plate (34) is arranged in the limit groove (33), a central plate (341) is arranged in the middle of the bottom of the upper cover plate (34), and a heating device is arranged in the central plate (341); a through hole (35) is formed in the middle of the upper cover plate (34), and the through hole (35) is matched with the limiting groove (33); an annular groove (36) is formed in the periphery of the bottom surface of the upper cover plate (34), and a first thread (37) is arranged on the annular groove (36); the satellite-borne satellite support is characterized in that an annular side plate (38) is fixedly connected to the periphery of the top of the bottom plate (31) and close to the outer side of the satellite (4), a second thread (39) is arranged on the inner wall above the annular side plate (38.

2. A solar array container for a spacecraft as claimed in claim 1, wherein: the annular side plate (38) is internally provided with an elastic support frame (381), and the elastic support frame (381) is formed by elastically hinging a plurality of small hard support rods.

3. A solar array container for a spacecraft as claimed in claim 1, wherein: the inner wall of the annular side plate (38) is provided with four clamping plates (382), and the number of the clamping plates (382) is four; the catch plate (382) is matched with the flexible wing (12).

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