CN113619811B - Plate-shaped satellite group structure - Google Patents
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- CN113619811B CN113619811B CN202110901769.0A CN202110901769A CN113619811B CN 113619811 B CN113619811 B CN 113619811B CN 202110901769 A CN202110901769 A CN 202110901769A CN 113619811 B CN113619811 B CN 113619811B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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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
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
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Abstract
The invention relates to the technical field of satellites, in particular to a plate-shaped satellite group structure. The slab satellite group structure includes: the cross section of the central star is a polygon with the number of sides N being more than or equal to five, and the edge stars are sequentially arranged around the central star end to end in a surrounding manner; when the plate-shaped satellite group structure is projected to a plane where the cross section of the central star is located, two adjacent edge stars share one side edge; the central star body is provided with a central connecting piece, and the edge star body is provided with a first connecting piece and a second connecting piece; the first connecting piece is connected with the central connecting piece, and the second connecting piece on one edge star body is connected with the second connecting piece on the other edge star body.
Description
Technical Field
The invention relates to the technical field of satellites, in particular to a plate-shaped satellite group structure.
Background
The use of satellites has profound effects on the development of the society in aspects of economy, science, information, safety, humanity and the like. Therefore, the satellite launching technology is rapidly developed, and a rocket-rocket launching mode is developed to a rocket-rocket launching mode, wherein the rocket-rocket launching mode is an efficient spacecraft launching mode, can fully utilize the carrying capacity of a rocket and reduce launching cost, and has a good practical value for multi-satellite networking. A plurality of satellites are generally stacked and tightly placed in the fairing, and after the fairing reaches a set orbit, the satellites in the fairing are released and scattered and reach respective preset positions.
The plate-shaped satellite is a novel satellite structure, and the weight and the volume size of the satellite can be greatly reduced under the condition that the requirement of the satellite on the ground communication function is met. Generally, the plate-shaped satellite is arranged in a rectangular shape, and when one-rocket multi-satellite launching is carried out, a plurality of plate-shaped satellites are stacked and placed in a fairing, and the plate-shaped satellite with the structure cannot fully utilize the space of the fairing.
Disclosure of Invention
The invention aims to provide a plate-shaped satellite group structure, which solves the technical problem that the plate-shaped satellite in the prior art cannot fully utilize the space of a fairing to a certain extent.
The invention provides a plate-shaped satellite group structure, which comprises: the cross section of the central star is a polygon with the number of sides N being more than or equal to five, and the edge stars are sequentially arranged around the central star end to end in a surrounding manner; when the plate-shaped satellite group structure is projected to a plane where the cross section of the central star is located, two adjacent edge stars share one side edge; the central star body is provided with a central connecting piece, and the edge star body is provided with a first connecting piece and a second connecting piece; the first connecting piece is connected with the central connecting piece, and the second connecting piece on one edge star body is connected with the second connecting piece on the other edge star body.
The central star body is arranged in a polygon shape, the number N of the sides of the polygon is more than or equal to five, namely the central star body is at least a pentagon, an obtuse angle exists at the inner angle of the central star body, and a plurality of edge star bodies are arranged around the central star body in an enclosing manner; when the plate-shaped satellite group structure is projected to the plane where the cross section of the central star body is located, two adjacent edge star bodies share one side edge, namely the side edge of one edge star body is the same as the corresponding side plate of the other edge star body in length and is abutted against each other, and the central star body is surrounded by the edge star bodies; compared with a circular fairing with a rectangular plate-shaped satellite, the invention is based on the polygonal central star, and a plurality of edge stars can occupy the blank position between the side edge of the rectangle and the circle, thereby fully utilizing the space of the circular fairing and improving the utilization rate of the circular fairing.
It should be noted that a satellite forms a satellite.
Further, the cross section of the central star body is a regular hexagon.
As an alternative, the cross section of the edge star is in an isosceles trapezoid shape, and the number of the edge stars is six; when the plate-shaped satellite group structure is projected to the plane of the cross section of the central star body, the short side of the edge star body is superposed with one side edge of the central star body.
As an alternative, six regular hexagonal edge stars are included in the plurality of edge stars; when the plate-shaped satellite group structure is projected to the plane of the cross section of the central star body, one side edge of one regular hexagon edge star body is coincided with one side edge of the central star body.
Further, the thickness of the edge star is the same as the thickness of the center star.
Furthermore, the central connecting piece is a central connecting cylinder, the first connecting piece is a first connecting cylinder, and the second connecting piece is a second connecting cylinder; the central connecting cylinders are arranged at six corners of the central star body, and the first connecting cylinders are arranged at two corners of the edge star body adjacent to the central star body; the second connecting cylinder is arranged at a corner adjacent to the corner provided with the first connecting cylinder; in the thickness direction of the plate-shaped satellite group structure, the central connecting cylinder is opposite to the first connecting cylinder, and the second connecting cylinder of one edge star is opposite to the second connecting cylinder of the other edge star.
Furthermore, three of the six regular hexagonal edge stars are first edge stars, and the other three are second edge stars; the height of the central connecting cylinder is not greater than the thickness of the central star body, the height of the first connecting cylinder and the height of the second connecting cylinder are not greater than the thickness of the edge star bodies, one of the two adjacent edge star bodies is a first edge star body, and the other one of the two adjacent edge star bodies is a second edge star body; the central connecting cylinder is positioned at the bottom of the central star body, and the first connecting cylinder and the second connecting cylinder on the first edge star body are both positioned at the upper part of the first edge star body; the first connector barrel of the second edge star is located in the middle of the second edge star and the second connector barrel of the second edge star is located at the bottom of the second edge star.
Further, third connecting members are arranged on the first edge star body and the second edge star body, the third connecting members on the first edge star body are arranged on the side edge of the first edge star body opposite to the central star body, and the third connecting members on the second edge star body are arranged on the side edge of the second edge star body opposite to the central star body.
Further, the third connecting piece is a third connecting cylinder; the height of the central connecting cylinder is equal to the sum of the heights of the two first connecting cylinders, the sum of the heights of the two second connecting cylinders and the height of the third connecting cylinder, the height of the third connecting cylinder is respectively greater than the thickness of the first edge star and the thickness of the second edge star, and the top end of the third connecting cylinder and the bottom end of the third connecting cylinder protrude out of the edge star;
the top surface of the first connecting cylinder of the first edge star and the top surface of the second connecting cylinder of the first edge star are both in the same plane with the top surface of the third connecting cylinder; the bottom surface of the second connecting cylinder of the second edge star and the bottom surface of the central connecting cylinder are both in the same plane with the bottom surface of the third connecting cylinder.
As an alternative, the plurality of edge stars further include a third edge star, the third edge star is an isosceles triangle, and one third edge star is sandwiched between the first edge star and the second edge star which are adjacently disposed.
It is to be understood that both the foregoing general description and the following detailed description are for purposes of illustration and description and are not necessarily restrictive of the disclosure. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate the subject matter of the disclosure. Together, the description and drawings serve to explain the principles of the disclosure.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic structural diagram of a slab satellite according to a first embodiment of the present invention;
fig. 2 is a schematic structural diagram of a slab satellite according to a second embodiment of the present invention;
fig. 3 is a schematic structural view of a central star in the slab satellite shown in fig. 2;
FIG. 4 is a schematic diagram of a first edge star of the plate satellite shown in FIG. 2;
FIG. 5 is a schematic diagram of a second edge star in the slate satellite shown in FIG. 2;
fig. 6 is a schematic structural view illustrating a plurality of stacked platy satellites shown in fig. 2;
fig. 7 is a schematic structural diagram of a plate satellite according to a third embodiment of the present invention.
Icon: 10-a central star; 20-edge stars; 30-a central connecting cylinder; 40-a first connecting cylinder; 50-a second connector barrel; 60-a third connector barrel; 21-a first edge star; 22-a second edge star; 23-a third edge star; 01-plate satellite group structure.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention.
The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention.
All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1 to 7, the present invention provides a plate-shaped satellite group structure 01, which includes a central star 10 (the central star 10 is arranged in a plate shape) and a plurality of edge stars 20 (the edge stars 20 are arranged in a plate shape), wherein the cross section of the central star 10 (the plane perpendicular to the thickness direction of the central star 10) is a polygon with the number of sides N being greater than or equal to five, and the edge stars 20 are sequentially connected end to end and are surrounded around the central star 10; when the plate-shaped satellite group structure 01 is projected to the plane where the cross section of the central star body 10 is located, two adjacent edge star bodies 20 share one side edge; the central star body 10 is provided with a central connecting piece, and the edge star body 20 is provided with a first connecting piece and a second connecting piece; the first connector is connected to the center connector and the second connector on one edge star 20 is connected to the second connector on the other edge star 20.
In this embodiment, the central star 10 is disposed in a polygon, and the number N of the polygon sides is greater than or equal to five, that is, the central star 10 is at least a pentagon, an obtuse angle exists at an inner angle of the central star 10, and a plurality of edge stars 20 surround the central star 10; when the plate-shaped satellite group structure 01 is projected onto the plane where the cross section of the central star 10 is located, two adjacent edge stars 20 share one side edge, that is, in the two adjacent edge stars 20, the side edge of one edge star 20 is the same as the corresponding side plate of the other edge star 20 in length and is abutted against each other, and the central star 10 is surrounded by the plurality of edge stars 20; compared with a rectangular plate-shaped satellite placed on a circular fairing, the polygonal central star 10 is adopted in the embodiment, and the edge stars 20 can occupy blank positions between the sides of the rectangle and the circle, so that the space of the circular fairing can be fully utilized, and the utilization rate of the circular fairing is improved.
In the process of stacking a plurality of plate-shaped satellite group structures 01 together, connecting the center connection with the first connection piece through the pressing and releasing device and connecting a plurality of second connection pieces, the connection of the center star body 10 and the edge star body 20 and the connection of the edge star body 20 and the edge star body 20 in the same plate-shaped satellite group structure 01 are realized, and the connection of the multilayer plate-shaped satellite group structures 01 is also realized. After the plurality of fixed plate-shaped satellite group structures 01 are placed on a fairing and then launched to a preset orbit by a rocket, the pressing and releasing assembly releases the plurality of plate-shaped satellite group structures 01 and releases the edge star 20 and the center star 10 in the plate-shaped satellite group structures 01 on the same layer. The compression release device can adopt a structure which is conventional in the field, and the central connecting piece, the first connecting piece and the second connecting piece are arranged into a structure which is matched with the compression release device.
For example: the pressing and releasing device comprises a pressing rope, the central connecting piece is a central connecting cylinder 30 extending along the thickness direction of the central star body 10, the first connecting piece is a first connecting cylinder 40 extending along the thickness direction of the edge star body 20, and the second connecting piece is a second connecting cylinder 50 extending along the thickness direction of the edge star body 20; in the thickness direction of the plate-shaped satellite group structure 01, the hole of the central connecting cylinder 30 is opposite to the hole of the first connecting cylinder 40, and a pressing rope sequentially penetrates through the corresponding central connecting cylinder 30 and the first connecting cylinder 40 of the multi-layer plate-shaped satellite group structure 01 from bottom to top or from top to bottom; similarly, the pressing rope sequentially penetrates through the corresponding second connecting cylinders 50 of the multilayer plate-shaped satellite group structures 01 from bottom to top or from top to bottom, so that the connection between the edge stars 20 and the edge stars 20 in the same plate-shaped satellite group structure 01 is realized, and the connection between a plurality of plate-shaped satellite group structures 01 is also realized.
Wherein, the central star 10 is preferably polygonal, such as: a regular pentagon, a regular heptagon, or a regular octagon, etc. The regular polygon is adopted to facilitate processing and manufacturing.
As an alternative, the cross section of the central star 10 is a regular hexagon, in this embodiment, the central star 10 is a regular hexagon, so that the plurality of edge stars 20 are conveniently arranged around the central star 10 to be equally divided by 360 degrees, and the processing and manufacturing are convenient. When bearing a lateral force, the central star 10 is arranged in a regular hexagon, which can disperse the force and help to improve the stability of the stacked structure.
The structure of three plate-shaped satellite group structures 01 is listed below based on the central star 10 as a regular hexagon:
the first embodiment is as follows:
as shown in fig. 1, the cross section of the edge star 20 is isosceles trapezoid, and the number of the edge stars 20 is six; when the plate-shaped satellite group structure 01 is projected onto the plane where the cross section of the central star 10 is located, the short side (the upper base of the isosceles trapezoid) of the edge star 20 coincides with one side of the central star 10, that is, the sides of the regular hexagon are the upper bases of six isosceles trapezoids respectively.
The second embodiment:
as shown in fig. 2-6, six regular hexagonal edge stars 20 are included in the plurality of edge stars 20; when the plate-shaped satellite group structure 01 is projected onto the plane of the cross section of the central star 10, one side of one regular hexagonal edge star 20 coincides with one side of the central star 10, that is, six sides of the regular hexagon of the central star 10 coincide with one side of the hexagons of the six edge stars 20, respectively. The side of the edge star 20 opposite the center star 10 can be closer to the inner wall of the circular fairing, further improving the utilization of the fairing.
Wherein the thickness of the edge star 20 may be different from the thickness of the central star 10, in which case the plate-like satellite group structure 01 is not flat.
As an alternative solution, the thickness of the edge star 20 is the same as that of the central star 10, in this embodiment, the cross section of the edge star 20 is the same as that of the central star 10, and the thickness of the edge star 20 is the same as that of the central star 10, so that the two have the same specification and structure, and are convenient to process and manufacture; the surface of the plate-shaped satellite group structure 01 is smooth, the structure is compact, the plate-shaped satellite group structures 01 can be stacked conveniently, and the space utilization rate of the fairing is further improved.
On the basis of any of the above embodiments, further, the edge star 20 is further provided with a third connecting member, the third connecting member is disposed on the side of the edge star 20 opposite to the central star 10, and the optional third connecting member is disposed at the center of the side, so as to ensure the stability of connection. The third connector may be a third connector barrel 60 extending through the thickness of the edge star 20. The third connector barrel 60 may be the same compression application device as the central connector barrel 30, the first connector barrel 40 and the second connector barrel 50.
In this embodiment, set up the third connecting piece and can improve the connection stability who compresses tightly release. The number of the compaction points is 18, the number of the stars is 7, the ratio of the compaction points to the stars is about 2.6, and the utilization rate of the compaction applying device is high.
As shown in fig. 2 to 5, further, based on the above embodiment, the central connection tube 30 is disposed at each of six corners of the central star 10, and the first connection tubes 40 are disposed at two corners of the edge star 20 adjacent to the central star 10; the second connecting cylinder 50 is disposed at a corner adjacent to the corner where the first connecting cylinder 40 is disposed; in the thickness direction of the plate-like satellite group structure 01 (also, the thickness direction of the center star 10, the thickness direction of the edge star 20, and the height direction of the cowling), the center connecting cylinder 30 faces the first connecting cylinder 40, and the second connecting cylinder 50 of one edge star 20 faces the second connecting cylinder 50 of the other edge star 20. In this embodiment, the central connecting cylinder 30 is disposed at the connection position of the central star 10, and the first connecting cylinder 40 and the second connecting cylinder 50 are disposed at the corners of the edge star 20, so that on one hand, the installation is convenient, on the other hand, the connection position between the edge star 20 and between the edge star 20 and the central star 10 can be closer, so that the plate-shaped satellite group structure 01 is more compact, and on the other hand, the connection can be more stable.
For the same central connecting cylinder 30, in the thickness direction of the plate-shaped satellite group structure 01, the first connecting cylinders 40 on the two edge stars 20 are opposite to the central connecting cylinder 30, namely the central connecting cylinder 30, one first connecting cylinder 40 and the other first connecting cylinder 40 are stacked; two second connector barrels 50 are stacked. The location of the central connector barrel 30, the first connector barrel 40 and the second connector barrel 50 may be set as desired.
Alternatively, as shown in fig. 3-5, three of the six regular hexagonal edge stars 20 are first edge stars 21, and the other three are second edge stars 22; the height of the central connecting cylinder 30 is not more than the thickness of the central star body 10, the height of the first connecting cylinder 40 and the height of the second connecting cylinder 50 are not more than the thickness of the edge star bodies 20, one of the two adjacent edge star bodies 20 is a first edge star body 21, the other one is a second edge star body 22, namely the first edge star body 21 and the second edge star body 22 are alternately arranged one by one; the central connecting cylinder 30 is located at the bottom of the central star 10, and the first connecting cylinder 40 and the second connecting cylinder 50 on the first edge star 21 are both located at the upper part of the first edge star 21, so that the intermediate connecting cylinder is sandwiched between the two first connecting cylinders 40; the first connector barrel 40 of the second edge star 22 is located at the center of the second edge star 22 and the second connector barrel 50 of the second edge star 22 is located at the bottom of the second edge star 22.
Optionally, the third connector is a third connector barrel 60; the height of the central connecting cylinder 30 and the sum of the heights of the two first connecting cylinders 40, the sum of the heights of the two second connecting cylinders 50 and the height of the third connecting cylinder 60 are equal, the height of the third connecting cylinder 60 is greater than the thickness of the edge star 20, and the top end of the third connecting cylinder 60 and the bottom end of the third connecting cylinder 60 both protrude out of the edge star 20; the top surface of the first connector barrel 40 of the first edge star 21 and the top surface of the second connector barrel 50 of the first edge star 21 are both in the same plane as the top surface of the third connector barrel 60; the bottom surface of the second connector barrel 50 of the second edge star 22 and the bottom surface of the central connector barrel 30 are both coplanar with the bottom surface of the third connector barrel 60.
When a plurality of plate-shaped satellite group structures 01 are stacked, in the adjacent two layers of plate-shaped satellite group structures 01, the central connecting cylinder 30 of the upper plate-shaped satellite group structure 01 abuts against the first connecting cylinder 40 of the first edge star 21 in the lower plate-shaped satellite group structure 01, the second connecting cylinder 50 of the second edge star 22 in the upper plate-shaped satellite group structure 01 abuts against the second connecting cylinder 50 of the first edge star 21 in the lower plate-shaped satellite group structure 01, the third connecting cylinder 60 of the upper plate-shaped satellite group structure 01 abuts against the third connecting cylinder 60 of the lower plate-shaped satellite group structure 01, gaps can exist between each star in the upper plate-shaped satellite group structure 01 and each star in the lower plate-shaped satellite group structure 01, collision between the upper layer star and the lower layer star in the conveying process is avoided, and satellites can be protected.
Optionally, the height of the second connecting cylinder 50 is half of the thickness of the edge star 20 (the thickness of the central star 10 is the same as that of the edge star 20), and the height of the first connecting cylinder 40 and the height of the central connecting cylinder 30 are both one third of the thickness of the edge star 20 (the thickness of the central star 10 is the same as that of the edge star 20).
Example three:
this embodiment may include all the technical features of the second embodiment.
As shown in fig. 7, the plurality of edge stars 20 further includes a third edge star 23, the third edge star 23 is an isosceles triangle, and one third edge star 23 is sandwiched between two adjacent regular hexagonal edge stars. Namely, an isosceles triangle edge star is filled in the gap between two adjacent edge stars 20, so that the utilization rate of the circular fairing is further improved.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and these modifications or substitutions do not depart from the spirit of the corresponding technical solutions of the embodiments of the present invention. In the description provided herein, numerous specific details are set forth. It is understood, however, that embodiments of the invention may be practiced without these specific details. In some instances, well-known methods, structures and techniques have not been shown in detail in order not to obscure an understanding of this description. Moreover, those of skill in the art will appreciate that while some embodiments herein include some features included in other embodiments, not others, combinations of features of different embodiments are meant to be within the scope of the invention and form different embodiments.
Claims (10)
1. A plate-like satellite group structure, comprising: the star-shaped light source comprises a central star body and a plurality of edge star bodies, wherein the cross section of the central star body is a polygon with the number of sides N being more than or equal to five, and the edge star bodies are sequentially arranged around the central star body in an end-to-end manner; when the plate-shaped satellite group structure is projected to a plane where the cross section of the central star is located, two adjacent edge stars share one side edge;
the central star body is provided with a central connecting piece, and the edge star body is provided with a first connecting piece and a second connecting piece; the first connecting piece is connected with the central connecting piece, and the second connecting piece on one edge star body is connected with the second connecting piece on the other edge star body.
2. The panel satellite group structure of claim 1, wherein the cross-section of the central star is a regular hexagon.
3. The panel-shaped satellite group structure according to claim 2, wherein the cross section of the edge stars is in the shape of an isosceles trapezoid, and the number of the edge stars is six; when the plate-shaped satellite group structure is projected to the plane of the cross section of the central star body, the short side of the edge star body is superposed with one side edge of the central star body.
4. The panel satellite constellation structure of claim 2, wherein said plurality of edge stars comprises six regular hexagonal edge stars; when the plate-shaped satellite group structure is projected to the plane of the cross section of the central star body, one side of one regular hexagonal edge star body is coincided with one side of the central star body.
5. The platy satellite group structure according to claim 4, wherein the thickness of the edge stars is the same as the thickness of the center star.
6. The panel satellite group structure according to claim 5, wherein said central connection member is a central connection cylinder, said first connection member is a first connection cylinder, and said second connection member is a second connection cylinder;
the central connecting cylinders are arranged at six corners of the central star body, and the first connecting cylinders are arranged at two corners of the edge star body, which are adjacent to the central star body; the second connecting cylinder is arranged at a corner adjacent to the corner provided with the first connecting cylinder; in the thickness direction of the plate-shaped satellite group structure, the central connecting cylinder is opposite to the first connecting cylinder, and the second connecting cylinder of one edge star is opposite to the second connecting cylinder of the other edge star.
7. The panel satellite group structure of claim 6, wherein three of said six regular hexagonal edge stars are first edge stars and the other three are second edge stars; the height of the central connecting cylinder is not greater than the thickness of the central star body, the height of the first connecting cylinder and the height of the second connecting cylinder are not greater than the thickness of the edge star bodies, one of the two adjacent regular hexagon edge star bodies is a first edge star body, and the other one of the two adjacent regular hexagon edge star bodies is a second edge star body;
the central connecting cylinder is positioned at the bottom of the central star body, and the first connecting cylinder and the second connecting cylinder on the first edge star body are both positioned at the upper part of the first edge star body; the first connector barrel of the second edge star is located in the middle of the second edge star and the second connector barrel of the second edge star is located at the bottom of the second edge star.
8. The slate satellite group structure of claim 7, wherein a third connector is disposed on each of said first edge star and said second edge star, said third connector on said first edge star being disposed on an opposite side of said first edge star from said center star, said third connector on said second edge star being disposed on an opposite side of said second edge star from said center star.
9. The panel-like satellite group structure according to claim 8, wherein said third connector is a third connector barrel; the height of the central connecting cylinder is equal to the sum of the heights of the two first connecting cylinders, the sum of the heights of the two second connecting cylinders and the height of the third connecting cylinder, the height of the third connecting cylinder is greater than the thickness of the first edge star and greater than the thickness of the second edge star, and the top end of the third connecting cylinder and the bottom end of the third connecting cylinder protrude out of the edge star;
the top surface of the first connecting cylinder of the first edge star and the top surface of the second connecting cylinder of the first edge star are both in the same plane with the top surface of the third connecting cylinder; the bottom surface of the second connecting cylinder of the second edge star and the bottom surface of the central connecting cylinder are both in the same plane with the bottom surface of the third connecting cylinder.
10. The panel-shaped satellite group structure according to any one of claims 7 to 9, wherein the plurality of edge stars further comprises a third edge star, the third edge star is an isosceles triangle, and one third edge star is sandwiched between the first edge star and the second edge star which are adjacently arranged.
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| US5411226A (en) * | 1993-10-13 | 1995-05-02 | Martin Marietta Corporation | Spacecraft adapter and dispenser |
| US9718566B2 (en) * | 2015-04-30 | 2017-08-01 | Worldvu Satellites Limited | Stackable satellites and method of stacking same |
| IL258729B (en) * | 2018-04-16 | 2021-12-01 | Israel Aerospace Ind Ltd | Nano-satellite |
| FR3082509B1 (en) * | 2018-06-14 | 2022-03-11 | Thales Sa | METHOD FOR FITTING A PLURALITY OF SPACESHIPS UNDER THE CAP OF A LAUNCHER WITHOUT STRUCTURAL DISTRIBUTOR AND ASSEMBLY RESULTING FROM SUCH A METHOD |
| CN112591144B (en) * | 2020-12-28 | 2023-07-07 | 中国科学院微小卫星创新研究院 | Laminated satellite array configuration and transmitting method thereof |
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