CN219192571U - Compact primary and secondary star structure - Google Patents

Abstract

The utility model provides a compact primary-secondary star structure, which comprises: the device comprises a female star (500) and a child star (300), wherein the female star (500) comprises a female star bearing cylinder (502) on the outer side surface, a female star top plate (503) is connected above the female star bearing cylinder (502), and a female star bottom plate (501) is connected below the female star bearing cylinder (502); the outer side surface of the female satellite bearing cylinder (502) is connected with a plurality of sub satellites (300), and each sub satellite (300) is connected to the female satellite bearing cylinder (502) through a separating mechanism (400). The satellite has the advantages of compact structure, high space utilization rate, low structural weight ratio, low mounting height of the sub-satellites (300), simple and efficient force transmission path, contribution to optimizing the carrying mechanical environment of the sub-satellites (300), fan-shaped expansion of the mutual distance of the sub-satellites (300) along the separation direction, and low risk of collision of the sub-satellites (300) during separation.

Description

Compact primary and secondary star structure

Technical Field

The utility model mainly relates to the technical field of satellite structures, in particular to a compact primary-secondary satellite structure.

Background

With the continuous progress of the aerospace technology, the traditional mode of launching one satellite at a time by using one rocket cannot meet the requirement of diversified tasks, and multi-satellite launching can obtain more benefits at a lower cost, so that the method represents a new state of satellite development.

The multi-star comprises primary and secondary stars, and a connection and separation device is generally adopted between the primary and secondary stars, and is a device which is fixed on the primary star and used for connecting and releasing microsatellites (secondary stars). After the primary and secondary satellites are transmitted, the primary and secondary satellite connection and separation device takes the primary satellites as a load platform, and the microsatellite is transmitted out at a proper time and orbit position so as to execute specific tasks such as accompanying observation. The common primary and secondary satellite configurations in the domestic and foreign satellite configurations are provided with a frame panel type, a plate frame type or a bearing cylinder type and the like, the satellite structure generally comprises a main bearing structure such as a bearing partition plate or a bearing cylinder and the like and a secondary bearing structure such as an auxiliary partition plate or a cabin sealing plate and the like, the structural complexity is high, the structural weight occupies a large part in the whole satellite weight, and the force transmission path of each single-machine device on the satellite is complex.

The existing primary-secondary star configuration is more in the situation of carrying and transmitting, the primary star and the secondary star are independently designed, the secondary star carries one or more secondary stars according to carrying and transmitting allowance and available enveloping space, the primary star and the secondary star are connected in series or in parallel simply, the primary star and the secondary star lack of overall design, the secondary star adopts more traditional configuration, the auxiliary structure is more, the structure weight is large, the force transmission path of the secondary star is complex, the mechanical environment is worse, and the mechanical performance requirement on the secondary star is higher.

Disclosure of Invention

The technical problem to be solved by the utility model is to provide a compact primary-secondary star structure, which has the advantages of compact satellite structure, high space utilization rate, low structural weight ratio, low mounting height of the secondary star, simple and efficient force transmission path, contribution to optimizing the carrying mechanical environment of the secondary star, fan-shaped expansion of the mutual distance of the secondary star along the separation direction, and low risk of mutual collision of separation of the secondary star.

In order to solve the above technical problems, the present utility model provides a compact primary-secondary star structure, including: the device comprises a mother star and a child star, wherein the mother star comprises a mother star bearing cylinder on the outer side surface, a mother star top plate is connected above the mother star bearing cylinder, and a mother star bottom plate is connected below the mother star bearing cylinder; the outer side surface of the parent satellite bearing cylinder is connected with a plurality of child satellites, and each child satellite is connected to the parent satellite bearing cylinder through a separator mechanism.

Optionally, an interface embedded part is arranged on the outer side surface of the female satellite bearing cylinder, and the interface embedded part is used for connecting the separating mechanism.

Optionally, the structure form of the female star bearing cylinder is a honeycomb plate.

Optionally, the honeycomb panel skin is made of carbon fiber or aluminum alloy.

Optionally, the female star bearing cylinder is in the shape of a round table, an inverted round table or a cylinder.

Optionally, a first frame embedded part is arranged below the female satellite bearing cylinder, the outer side of the first frame embedded part is used for being in butt joint with the carrier rocket adapter, and the inner side of the first frame embedded part is connected with the female satellite bottom plate.

Optionally, a second frame embedded part is arranged above the female star bearing cylinder, and the second frame embedded part is connected with the female star top plate.

Optionally, a body-mounted sailboard is arranged, the body-mounted sailboard is mounted on the mother star roof, and a solar cell array is adhered to the upper surface of the body-mounted sailboard.

Optionally, the body-mounted sailboard is mounted on the parent star top plate through a heat insulation gasket.

Optionally, the number of the son stars is 6, and the son stars are uniformly distributed on the outer side surface of the parent star bearing cylinder.

Compared with the prior art, the utility model has the following advantages: a female star bearing cylinder is arranged on the outer side surface of the female star, a female star top plate is connected above the female star bearing cylinder, and a female star bottom plate is connected below the female star bearing cylinder; the outer side surface of the parent satellite bearing cylinder is connected with a plurality of child satellites, each child satellite is connected to the parent satellite bearing cylinder through a separating mechanism, the parent satellite bearing cylinder is of a main structure and a cabin sealing structure, the space utilization rate is high, the structural weight ratio is low, the mounting height of the child satellites is low, the force transmission path is concise and efficient, the carrying mechanical environment of the child satellites is facilitated to be optimized, the mutual distance between the child satellites is enlarged in a fan shape along the separating direction, and the risk of mutual collision of the child satellite separation is low.

Drawings

The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiments of the application and together with the description serve to explain the principles of the application. In the accompanying drawings:

FIG. 1 is a schematic diagram of a conventional satellite architecture;

FIG. 2 is a schematic diagram of a compact primary-secondary star structure according to an embodiment of the present utility model;

FIG. 3 is an exploded view of a compact primary-secondary star structure in accordance with one embodiment of the present utility model;

FIG. 4 is a cross-sectional view of the primary structure of a parent star in an embodiment of the utility model.

The marks in the figure respectively represent:

100-a traditional primary-secondary star structure;

101-top plate; 102, a cabin sealing plate; 103-diaphragm plates; 104-a bottom plate; 105-adapter; 106, a force bearing cylinder; 107-vertical partition plates;

200-solar cell arrays;

300-son star;

400-separating mechanism;

500-parent star; 501-a mother star baseboard; 502-a female star force bearing cylinder; 503-a mother star roof; 504-body-mounted sailboards; 505-insulating spacers;

5021-first frame burial; 5022-honeycomb panel; 5023-interface burial; 5024-second frame buries.

Detailed Description

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are used in the description of the embodiments will be briefly described below. It is apparent that the drawings in the following description are only some examples or embodiments of the present application, and it is obvious to those skilled in the art that the present application may be applied to other similar situations according to the drawings without inventive effort. Unless otherwise apparent from the context of the language or otherwise specified, like reference numerals in the figures refer to like structures or operations.

As used in this application and in the claims, the terms "a," "an," "the," and/or "the" are not specific to the singular, but may include the plural, unless the context clearly dictates otherwise. In general, the terms "comprises" and "comprising" merely indicate that the steps and elements are explicitly identified, and they do not constitute an exclusive list, as other steps or elements may be included in a method or apparatus.

The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present application unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.

In the description of the present application, it should be understood that, where azimuth terms such as "front, rear, upper, lower, left, right", "transverse, vertical, horizontal", and "top, bottom", etc., indicate azimuth or positional relationships generally based on those shown in the drawings, only for convenience of description and simplification of the description, these azimuth terms do not indicate and imply that the apparatus or elements referred to must have a specific azimuth or be constructed and operated in a specific azimuth, and thus should not be construed as limiting the scope of protection of the present application; the orientation word "inner and outer" refers to inner and outer relative to the contour of the respective component itself.

Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

In addition, the terms "first", "second", etc. are used to define the components, and are merely for convenience of distinguishing the corresponding components, and unless otherwise stated, the terms have no special meaning, and thus should not be construed as limiting the scope of the present application. Furthermore, although terms used in the present application are selected from publicly known and commonly used terms, some terms mentioned in the specification of the present application may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein. Furthermore, it is required that the present application be understood, not simply by the actual terms used but by the meaning of each term lying within.

Fig. 1 is a schematic view of a conventional satellite structure, as shown in fig. 1, in which the conventional satellite structure 100 adopts a more plate-shaped design, such as a top plate 101 above, a bottom plate 104 below, and an adapter 105, and in addition, the conventional satellite structure 100 further has components such as a cabin sealing plate 102, a diaphragm 103, and a vertical diaphragm 107, so that the overall structure is complex, and the weight of the structure is relatively high in the whole satellite.

Example 1

Fig. 2 is a schematic diagram of a compact primary-secondary star structure according to an embodiment of the present utility model, and fig. 3 is an exploded view of a compact primary-secondary star structure according to an embodiment of the present utility model, referring to fig. 2 and 3, the compact primary-secondary star structure of the present embodiment mainly includes a primary star 500 and a secondary star 300, wherein the primary star 500 includes a primary star bearing cylinder 502 on an outer side, a primary star top plate 503 is connected above the primary star bearing cylinder 502, and a primary star bottom plate 501 is connected below the primary star bearing cylinder 502. The outer side of the female satellite bearing cylinder 502 is connected to a plurality of sub-satellites 300, each sub-satellite 300 being connected to the female satellite bearing cylinder 502 by a separation mechanism 400.

In this embodiment, the female star 500 includes a female star bearing cylinder 502 on the outer side, and a plurality of sub-stars 300 are connected to the outer side of the female star bearing cylinder 502, the space occupied by the female star 500 is limited within the range of the female star bearing cylinder 502, and the sub-stars 300 are tightly attached around the female star bearing cylinder 502, so that the space occupied by the whole structure of the sub-female star is reduced, and the layout of the sub-female star is more compact.

By adopting the satellite structure, the propulsion storage tank can be arranged on the mother satellite bottom plate 501, each platform single machine can be arranged on the lower surface of the mother satellite top plate 503, the space utilization rate in the satellite is high, no complex partition plate structure is arranged in the satellite, a carrier rocket adapter docking interface is arranged below the mother satellite bearing cylinder 502, no satellite adapter parts are required to be independently designed, the single machine transmission path is short, and the weight of the whole satellite structure is relatively low, so that the satellite launching cost can be saved.

In this embodiment, the sub-satellites 300 are distributed around the parent satellite 500, so that mutual interference between the sub-satellites 300 can be reduced. In addition, the sub-star 300 is hung on the mother star 500 in a side manner instead of being in butt joint with the mother star 500 at the bottom of the sub-star 300, and the layout manner is beneficial to reducing the mass center height of the sub-star 300 relative to the mounting surface, improving the fundamental frequency of the sub-star, avoiding the fundamental frequency of the sub-star 300 within 100Hz, and further reducing the mechanical response level of the sub-star 300.

In some embodiments, the outer side of the female satellite carrier 502 is provided with an interface burial 5023, the interface burial 5023 being used to connect the disconnect mechanism 400. The embedded parts 5023 provide support or connection function for the subsequent structure or equipment installation, so that other structures or equipment are more convenient and simpler to install. The interface embedded part 5023 is arranged on the outer side surface of the female star bearing cylinder 502, and the position of the separating mechanism 400 is reserved in advance, so that smooth installation of the separating mechanism 400 is facilitated, the equipment installation time is saved, the equipment installation efficiency is improved, and a better installation effect is achieved.

In some embodiments, the female satellite carrier 502 is configured as a honeycomb panel 5022. The honeycomb panel can achieve higher overall structural rigidity of the satellite at lower weight cost. Further, the honeycomb plate 5022 skin may be made of carbon fiber or aluminum alloy, that is, the honeycomb plate 5022 may be a carbon fiber skin honeycomb plate or an aluminum alloy skin honeycomb plate. It will be appreciated by those skilled in the art that the structural form of the female satellite bearing cylinder 502 may be selected according to practical situations, for example, considering structural strength, manufacturing difficulty, cost input and other factors, and may be selected in a pure metal form or other composite material forms, which are not listed herein.

In some embodiments, the female satellite bearing cartridge 502 is shaped as a truncated cone, inverted truncated cone, or cylinder. For example, the female star bearing cylinder 502 shown in fig. 2 is in the shape of an inverted truncated cone, and has a larger top circular area and a smaller bottom circular area. The shape of the female star bearing cylinder 502 may be a truncated cone shape, the top circle area is smaller and the bottom circle area is larger, and the female star bearing cylinder 502 has different upper and lower areas and is generally influenced by factors such as structural design of the female star 500 and actual installation conditions of equipment. It can be appreciated that when the top circular area and the bottom circular area are the same, the shape of the female satellite bearing cylinder 502 in this embodiment is a cylindrical shape.

The shapes of the round table, the cylinder and the like are the whole appearance of the female star bearing cylinder 502, and the outer side surface of the female star bearing cylinder 502 can be a smooth curved surface or can be formed by splicing a plurality of planes. The advantage of the smooth curved surface is that the sub-stars 300 can be reasonably arranged according to the number and interval requirements of the sub-stars 300, and the outer side surface formed by splicing planes is that one sub-star 300 is arranged on one plane of the outer side surfaces in most cases, so that the outer side surface of the parent satellite bearing cylinder 502 has a plurality of planes in design, and the number of the sub-stars 300 is generally equal to the number of the planes.

Illustratively, if the outer side surface of the parent satellite bearing cylinder 502 is formed by splicing 4 planes, 4 sub-satellites 300 may be arranged, if the outer side surface of the parent satellite bearing cylinder 502 is formed by splicing 8 planes, 8 sub-satellites 300 may be arranged, and of course, the relationship between the number of the planes and the number of the sub-satellites 300 is only a general case, and other sub-satellite 300 arrangement situations may be provided in combination with performance characteristics of the sub-satellites 300, task requirements and interval requirements between the sub-satellites 300, which are not described herein.

In some embodiments, a first frame buried piece 5021 is disposed below the female satellite bearing cylinder 502, an outer side of the first frame buried piece 5021 is used for docking a carrier rocket adapter, and an inner side of the first frame buried piece 5021 is connected with the female satellite bottom plate 501. Illustratively, the first frame embedded part 5021 may be made of an aluminum alloy.

Fig. 4 is a main structural cross-section of a female satellite in an embodiment of the present utility model, referring to fig. 4, a first frame embedded part 5021 is provided below a female satellite bearing cylinder 502, a lower end surface of the first frame embedded part 5021 has an inner side and an outer side, a carrier rocket adapter docking interface is reserved at the outer side of the first frame embedded part 5021, and the inner side of the first frame embedded part 5021 can be used for installing a female satellite bottom plate 501, that is, the female satellite bottom plate 501 is installed at the inner side of the first frame embedded part 5021 through a fastener. The frame embedded part structure is adopted, so that the installation of the female satellite bottom plate 501 and the butt joint of the carrier rocket adapter are simpler and more convenient, and the assembly time is saved.

Further, a second frame embedded part 5024 is disposed above the female star bearing cylinder 502, and the second frame embedded part 5024 is connected with the female star top plate 503. Illustratively, the second frame embedded part 5024 may be made of an aluminum alloy, a magnesium alloy or other materials, which are not listed here. The female top plate 503 may be mounted by fasteners to the second frame burial 5024 above the female force bearing cartridge 502.

In this embodiment, the first frame embedded part 5021, the honeycomb panel 5022, the interface embedded part 5023 and the second frame embedded part 5024 may be independent components, and may be used independently when the primary and secondary stars are installed, or the first frame embedded part 5021, the honeycomb panel 5022, the interface embedded part 5023 and the second frame embedded part 5024 may be set or preset as an integral component. For example, the first frame embedded part 5021, the interface embedded part 5023 and the second frame embedded part 5024 can be glued with the honeycomb plate 5022 into a whole through a J47 series adhesive, and the integral structure is beneficial to improving the strength of the primary-secondary star structure, so that the satellite safety and the performance stability are guaranteed.

In some embodiments, a body-mounted windsurfing board 504 may also be disposed on the mother star roof 503 in this embodiment. The body-mounted sailboard 504 is mounted on the mother star roof 503, and the solar cell array 200 is adhered to the upper surface of the body-mounted sailboard 504, and the solar cell array 200 is an important power generation component, and can provide energy for the son-mother star. In this embodiment, to keep the compactness of the primary-secondary star structure, the plane of the solar cell array 200 is similar to the shape of the primary-secondary star top plate 503, and the size is equal to or the solar cell array 200 is slightly larger than the primary-secondary star top plate 503, so that it is appropriate to just cover the secondary star 300.

In some embodiments, body windsurfing board 504 is mounted to parent star top board 503 via insulation spacers 505. In this embodiment, the heat insulation spacer 505 may be a glass fiber reinforced plastic heat insulation spacer, and the body-mounted sailboard 504 is installed on the outer side of the top plate 501 of the parent star, and the parent star 500 can form a shielding for the child star 300 in the sun-oriented state by the body-mounted sailboard 504, so as to provide a good stable thermal environment for the child star 300, so that the child star 300 can exert stable performance.

In some embodiments, the number of the sub-stars 300 may be 6, and the 6 sub-stars 300 are uniformly distributed on the outer side surface of the parent satellite carrier 502. In the rocket launching stage, 6 sub-stars 300 are respectively hung on a parent-satellite bearing cylinder 502 through a separating mechanism 400 (a small separating mechanism), and when the sub-parent stars enter the orbit, if the on-orbit sub-stars 300 need to independently execute tasks, the separating mechanism 400 is unlocked, and the sub-stars 300 are separated along the normal direction of the installation surface.

In this embodiment, 6 sub-stars 300 are uniformly hung on the outer side of the parent-satellite bearing cylinder 502 along the circumferential direction, and can be separated along the normal direction of the mounting surface, the cross overlapping area between the sub-stars 300 in the separation direction is less, the mutual spacing is fan-shaped, and the separation safety between the sub-stars 300 is high. In addition, 6 son stars 300 are uniformly and laterally hung on the outer side of the mother star bearing cylinder 502 in the circumferential direction, the mounting height of the son stars 300 is low, the longitudinal mass center height of the combined body is low, the vibration response of the son stars 300 in the satellite transmitting stage is reduced, and the mother star structure of the embodiment provides a good mechanical environment for the son stars 300.

The above-mentioned mother-son star structure and working process of the present embodiment are described in detail by the mother-son star structure of 6 son stars 300 to reveal the technical advantages of the mother-son star structure of the present embodiment, it is easy to think that the number of son stars 300 in the present embodiment may depend on specific tasks or requirements, and the number of son stars 300 listed in the present embodiment is not limited specifically.

In the compact primary-secondary star structure provided by the embodiment, task requirements of the primary star 300 and the secondary star 500 are comprehensively considered, structural design is comprehensively carried out, a primary star bearing cylinder 502 is arranged on the outer side surface of the primary star 500, a primary star top plate 503 is connected above the primary star bearing cylinder 502, and a primary star bottom plate 501 is connected below the primary star bearing cylinder 502; the outer side of the female satellite bearing cylinder 502 is connected to a plurality of sub-satellites 300, each sub-satellite 300 being connected to the female satellite bearing cylinder 502 by a separation mechanism 400. It can be seen that the main bearing structure of the mother star is integrated with the auxiliary bearing structure, the main bearing structure uses the main bearing cylinder 502 of the mother star, and has the functions of bearing and cabin sealing, the satellite configuration is compact, the space utilization rate in the cabin is high, the weight ratio of the structure is low, the installation mode of the uniform side hanging of the son star 300 in the circumferential direction has higher separation safety, and meanwhile, the mass center height of the son star 300 and the mother star 500 is reduced, and the overall mechanical properties of the son star 300 and the mother star 500 are optimized.

While the basic concepts have been described above, it will be apparent to those skilled in the art that the above disclosure is by way of example only and is not intended to be limiting. Although not explicitly described herein, various modifications, improvements, and adaptations of the present application may occur to one skilled in the art. Such modifications, improvements, and modifications are intended to be suggested within this application, and are therefore within the spirit and scope of the exemplary embodiments of this application.

Meanwhile, the present application uses specific words to describe embodiments of the present application. Reference to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic is associated with at least one embodiment of the present application. Thus, it should be emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various positions in this specification are not necessarily referring to the same embodiment. Furthermore, certain features, structures, or characteristics of one or more embodiments of the present application may be combined as suitable.

Likewise, it should be noted that in order to simplify the presentation disclosed herein and thereby aid in understanding one or more inventive embodiments, various features are sometimes grouped together in a single embodiment, figure, or description thereof. This method of disclosure, however, is not intended to imply that more features than are presented in the claims are required for the subject application. Indeed, less than all of the features of a single embodiment disclosed above.

In some embodiments, numbers describing the components, number of attributes are used, it being understood that such numbers being used in the description of embodiments are modified in some examples by the modifier "about," approximately, "or" substantially. Unless otherwise indicated, "about," "approximately," or "substantially" indicate that the number allows for a 20% variation. Accordingly, in some embodiments, numerical parameters set forth in the specification and claims are approximations that may vary depending upon the desired properties sought to be obtained by the individual embodiments. In some embodiments, the numerical parameters should take into account the specified significant digits and employ a method for preserving the general number of digits. Although the numerical ranges and parameters set forth herein are approximations that may be employed in some embodiments to confirm the breadth of the range, in particular embodiments, the setting of such numerical values is as precise as possible.

While the present application has been described with reference to the present specific embodiments, those of ordinary skill in the art will recognize that the above embodiments are for illustrative purposes only, and that various equivalent changes or substitutions can be made without departing from the spirit of the present application, and therefore, all changes and modifications to the embodiments described above are intended to be within the scope of the claims of the present application.

Claims (10)

1. A compact primary-secondary star structure, comprising: the novel satellite comprises a parent satellite (500) and a child satellite (300), wherein the parent satellite (500) comprises a parent satellite bearing cylinder (502) on the outer side surface, a parent satellite top plate (503) is connected above the parent satellite bearing cylinder (502), and a parent satellite bottom plate (501) is connected below the parent satellite bearing cylinder (502);

the outer side surface of the parent satellite bearing cylinder (502) is connected with a plurality of child satellites (300), and each child satellite (300) is connected to the parent satellite bearing cylinder (502) through a separating mechanism (400).

2. The compact primary-secondary star structure of claim 1, wherein an interface buried piece (5023) is arranged on the outer side surface of the primary star force bearing cylinder (502), and the interface buried piece (5023) is used for connecting the separation mechanism (400).

3. The compact primary-secondary star structure of claim 1, wherein the primary star-bearing cylinder (502) is in the form of a honeycomb plate (5022).

4. A compact primary-secondary star structure according to claim 3, characterized in that the honeycomb panel (5022) skin is made of carbon fibre or aluminium alloy.

5. The compact primary-secondary star structure of claim 1, wherein said primary star-bearing cylinder (502) is in the shape of a truncated cone, inverted cone or cylinder.

6. The compact primary-secondary star structure of claim 1, wherein a first frame embedded part (5021) is arranged below the primary star bearing cylinder (502), the outer side of the first frame embedded part (5021) is used for docking a carrier rocket adapter, and the inner side of the first frame embedded part (5021) is connected with the primary star base plate (501).

7. The compact primary-secondary star structure of claim 1, wherein a second frame embedded part (5024) is arranged above the primary star bearing cylinder (502), and the second frame embedded part (5024) is connected with the primary star top plate (503).

8. The compact primary-secondary star structure of claim 1, further comprising a body-mounted sailboard (504), wherein the body-mounted sailboard (504) is mounted on the primary-star top plate (503), and a solar cell array (200) is adhered to an upper surface of the body-mounted sailboard (504).

9. The compact parent-child star structure according to claim 8, wherein the body mounted windsurfing board (504) is mounted on the parent-child star top board (503) through a heat insulation spacer (505).

10. The compact primary-secondary star structure according to claim 1, wherein the number of the secondary stars (300) is 6, and the secondary stars (300) are uniformly distributed on the outer side surface of the primary star bearing cylinder (502).

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