阅读说明：本技术 一种卫星太阳翼 (Satellite solar wing ) 是由 陈绍杰 薛鹏飞 高乙栋 鞠松琦 连红奎 孙萌 于 2021-11-05 设计创作，主要内容包括：本发明涉及航天设备技术领域,具体而言,涉及一种卫星太阳翼。卫星太阳翼包括天线基板、散热板和充电模组；所述充电模组设置在所述散热板的一侧,所述天线基板贴设在所述散热板的另一侧。本发明实施例的有益效果是：通过将充电模组和天线基板进行层叠设置,减小了卫星太阳翼的体积,通过在充电模组靠近天线基板的一侧设置散热板,保证了在减小卫星太阳翼的体积后的散热效率。(The invention relates to the technical field of space equipment, in particular to a satellite solar wing. The satellite solar wing comprises an antenna substrate, a heat dissipation plate and a charging module; the charging module is arranged on one side of the heat dissipation plate, and the antenna substrate is attached to the other side of the heat dissipation plate. The embodiment of the invention has the beneficial effects that: through carrying out range upon range of setting with the module that charges and antenna substrate, reduced satellite solar wing's volume, set up the heating panel through the one side that the module that charges is close to antenna substrate, guaranteed the radiating efficiency after reducing satellite solar wing's volume.)

1. A satellite solar wing is characterized by comprising an antenna substrate, a heat dissipation plate and a charging module;

the charging module is arranged on one side of the heat dissipation plate, and the antenna substrate is attached to the other side of the heat dissipation plate.

2. The satellite solar wing according to claim 1, wherein a plurality of groups of the charging modules are stacked, and adjacent charging modules are stacked through a rotating structure.

3. The satellite solar wing according to claim 1, wherein a heat dissipation coating is sprayed on an edge of a surface where the charging module and the heat dissipation plate are attached.

4. The satellite solar wing according to claim 1, characterized in that an insulating film is provided between the charging module and the heat dissipation plate.

5. The satellite solar wing according to claim 1, wherein the charging module comprises a battery assembly and a base frame, the array of battery assemblies being disposed on the base frame.

6. The satellite solar wing according to claim 5, wherein the base frame is rotatably connected to the heat dissipation plate by a rotating structure.

7. The satellite solar wing according to claim 5, wherein a heat conducting device is connected to the battery assembly, and the heat conducting device is connected to the heat dissipation plate.

8. The satellite solar wing according to claim 5, wherein the base frame is a frame structure or a connection substrate.

9. The satellite solar wing according to claim 1, wherein the antenna substrate, the heat dissipation plate, and the charging module are aligned.

10. The satellite solar wing according to claim 1, wherein the heat dissipation plate is an aluminum plate.

Technical Field

The invention relates to the technical field of space equipment, in particular to a satellite solar wing.

Background

In the prior art, the charging modules of the satellite solar wing are arranged on the left side and the right side of the antenna, and are unfolded from the left side and the right side of the antenna when in use, so that the solar irradiation area is increased, and the purpose of solar charging is achieved.

The existing satellite solar wing needs to be unfolded with the antenna first in the whole using process so as to enable the charging module to be unfolded for charging, the whole structure is complex, and after the whole satellite solar wing is unfolded, the occupied space of the whole satellite solar wing is enlarged, and the accident situation is easily caused.

Disclosure of Invention

The invention aims to provide a satellite solar wing which does not unfold an antenna when solar charging is carried out, occupies a small space and has a simple structure.

The embodiment of the invention is realized by the following steps:

the invention provides a satellite solar wing, which comprises an antenna substrate, a heat dissipation plate and a charging module, wherein the heat dissipation plate is arranged on the antenna substrate;

the charging module is arranged on one side of the heat dissipation plate, and the antenna substrate is attached to the other side of the heat dissipation plate.

In an optional embodiment, a plurality of groups of the charging modules are stacked, and adjacent charging modules are stacked through a rotating structure.

In an optional embodiment, heat dissipation coating is sprayed at the edge of the abutting surface of the charging module and the heat dissipation plate.

In an alternative embodiment, an insulating film is disposed between the charging module and the heat dissipation plate.

In an alternative embodiment, the charging module includes a battery assembly and a base frame, and the array of battery assemblies is disposed on the base frame.

In an alternative embodiment, the base frame and the heat dissipation plate are rotatably connected through a rotating structure.

In an alternative embodiment, a heat conducting device is connected to the battery assembly, and the heat conducting device is connected to the heat dissipation plate.

In an alternative embodiment, the base frame is a frame structure or a connection substrate.

In an alternative embodiment, the antenna substrate, the heat dissipation plate, and the charging module are aligned.

In an alternative embodiment, the heat dissipation plate is an aluminum plate.

The embodiment of the invention has the beneficial effects that:

through carrying out range upon range of setting with the module that charges and antenna substrate, reduced satellite solar wing's volume, set up the heating panel through the one side that the module that charges is close to antenna substrate, guaranteed the radiating efficiency after reducing satellite solar wing's volume.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

Fig. 1 is a schematic structural diagram of a satellite solar wing according to an embodiment of the present invention;

fig. 2 is a schematic perspective view of a satellite solar wing according to an embodiment of the present invention;

fig. 3 is a schematic view of a heat dissipation method of a satellite solar wing according to an embodiment of the present invention;

fig. 4 is a schematic unfolding view of a satellite solar wing according to an embodiment of the present invention.

Icon: 1-a charging module; 2-a heat sink; 3-an antenna substrate; 4-an insulating film; 5-a battery assembly; 6-base frame; 7-heat dissipation coating.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious 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, 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 derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

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 or the orientations or positional relationships that the products of the present invention are conventionally placed in use, and are only used for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements 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," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.

Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not imply that the components are required to be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly and may, for example, be 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.

Some embodiments of the invention are described in detail below with reference to the accompanying drawings. The embodiments described below and the features of the embodiments can be combined with each other without conflict.

The invention provides a satellite solar wing, as shown in fig. 1 and 2, comprising an antenna substrate 3, a heat dissipation plate 2 and a charging module 1; the charging module 1 is disposed on one side of the heat dissipation plate 2, and the antenna substrate 3 is attached to the other side of the heat dissipation plate 2.

In the present embodiment, the antenna substrate 3 is used for mounting an antenna, or an antenna position, that is, the antenna substrate 3.

Specifically, in the present embodiment, the antenna, the heat dissipation plate 2, and the charging module 1 are stacked in this order.

That is to say, after the antenna substrate 3 and the charging module 1 are stacked, the contact area between the charging module 1 and the outside is reduced, the corresponding heat dissipation area is reduced, and further, the charging module 1 may be damaged due to insufficient heat dissipation, which may affect the service life of the charging module 1.

For solving the above problem, in this embodiment, set up heating panel 2 between module 1 and the antenna substrate 3 charges, be connected with module 1 charges through heating panel 2, will charge produced heat direction heating panel 2 of module 1 in the in-process of charging and discharging to give off in the external environment through heating panel 2, in order to reach and carry out radiating purpose for module 1 charges.

In an alternative embodiment, as shown in fig. 4, a plurality of sets of charging modules 1 are stacked, and adjacent charging modules 1 are stacked through a rotating structure.

Specifically, in this embodiment, the multiunit is charged module 1 and is carried out range upon range of setting back, and it can reduce holistic occupation space, and when required electric quantity increases, can realize the expansion of multiunit charging module 1 through rotating-structure, and then increase with the area of directly projecting of sun, improve charge efficiency.

More specifically, in this embodiment, the rotating-structure setting is at the relative both ends of the module 1 that charges, through rotating in proper order, realizes opening of the module 1 that charges, finally shows the effect of a tiling, has increased the effect with the direct sunlight.

Specifically, in the present embodiment, the rotation structure may be arranged in various ways, such as a shaft rotation structure or a ball rotation structure, as long as the rotation between the adjacent charging modules 1 can be realized.

In this embodiment, the quantity of adjacent two rotational structure between the module 1 that charges is one or more, and the stationarity of the module 1 when rotating can more effectually be charged in the setting of a plurality of rotational structure, assurance.

Specifically, in this embodiment, for rotating the connection between two adjacent charging modules 1, for realizing the stability after rotating, still need two adjacent charging modules 1 to set up location structure between, fix a position two charging modules 1 after rotating, guarantee its stability after rotating.

In this embodiment, the number of the positioning structures between two adjacent charging modules 1 may be one, or may be multiple, as long as the positioning accuracy between two adjacent charging modules 1 and the stability after positioning can be ensured.

In an alternative embodiment, as shown in fig. 3, a heat dissipation coating 7 is sprayed on the edge of the surface where the charging module 1 and the heat dissipation plate 2 are attached.

The heat dissipation coating is a heat insulation waterproof coating capable of radiating heat of an object, the temperature resistance range is minus 50-600 ℃, the coating is directly coated on the surface of the object to be cooled, the heat on the coated object can be automatically radiated to the atmospheric space by the radiation heat dissipation cooling coating with the infrared wavelength of 8-13.5 microns, the surface and internal temperature of the object is reduced, and the heat dissipation cooling is obvious.

Through the setting of heat dissipation coating 7, the radiating efficiency of charging module 1 and heating panel 2 has been increased. Simultaneously, thermal coating 7 has better heat conductivity, and thermal conductivity between module 1 and the heating panel 2 that charges is increased through the thermal coating 7 of spraying, and then has increased the heat conductivility between module 1 and the heating panel 2 that charges, can realize the heat dissipation cooling to the module 1 that charges fast.

It is to be noted that, in the present embodiment, the heat dissipation efficiency is increased by spraying the heat dissipation paint 7 between the charging module 1 and the heat dissipation plate 2, but the method of increasing the heat dissipation efficiency is not limited to this method, and may be other methods capable of increasing the heat dissipation efficiency.

In an alternative embodiment, an insulating film 4 is provided between the charging module 1 and the heat dissipation plate 2.

The function of the charging module 1 is to convert solar energy into electric energy, and in the whole conversion process, not only can generate large heat, but also can have leakage of current, and further can damage other components such as the radiating plate 2 or the antenna substrate 3.

In order to solve the above problem, in the present embodiment, the insulating film 4 is disposed between the charging module 1 and the heat dissipation plate 2, so as to prevent the charging module 1 from leaking electricity and affecting the heat dissipation plate 2, and even the antenna.

The insulating film 4 is a thin film capable of ensuring good electrical insulation. Such films should have a very high resistivity (higher than 10)¹⁰Ω · cm) and breakdown field strength, while the electronic structure is characterized by a large forbidden band width and requires a material with low dielectric loss for high-frequency insulation.

The insulating film 4 is classified into inorganic and organic.

Inorganic insulators are commonly referred to as dielectrics and are commonly used as silicon oxide, silicon nitride, aluminum oxide, aluminum nitride; the organic insulating film 4 is made of polyimide, polyethylene, polyvinylidene fluoride, or polytetrafluoroethylene.

It is noted that both inorganic and organic insulators generally have the ability to polarize under the influence of an external electric field. When used as the electrical insulating film 4, a low dielectric constant is required to reduce dielectric loss.

Specifically, in the present embodiment, the insulating film 4 may be provided on the charging module 1 or on the heat dissipation plate 2.

In an alternative embodiment, the charging module 1 includes a battery assembly 5 and a base frame 6, and the battery assembly 5 is arranged in an array on the base frame 6.

In the present embodiment, after the battery modules 5 are arranged in an array on the base frame 6, the overall stability of the battery modules 5 can be ensured.

Specifically, in this embodiment, the array manner of the battery modules 5 on the base frame 6 may be a rectangular array as shown in fig. 2, or may be a circular array or other arrays, which only needs to realize the positioning and installation of the battery modules 5 by arranging the battery modules 5, and ensure the charging effect of the battery modules 5.

In an alternative embodiment, the base frame 6 and the heat dissipation plate 2 are rotatably connected by a rotating structure.

Specifically, in this embodiment, the base frame 6 and the heat dissipation plate 2 are also rotatably connected through a rotating structure, so that the heat dissipation plate 2 and the charging module 1 are unfolded.

Specifically, in the present embodiment, one end of the rotating structure is connected to the end of the frame, and the other end is connected to the middle or end of the heat dissipation plate 2, so that the charging module 1 can start to be unfolded at the end or middle of the heat dissipation plate 2.

The rotating structure between the base frame 6 and the heat dissipation plate 2 and the rotating structure between the charging modules 1 can be the same or different; specifically, the number of the organic acid compounds may be the same or different.

In this embodiment, a positioning structure is also provided between the base frame 6 and the heat dissipation plate 2 to ensure the positioning of the base frame 6 after rotation.

The positioning structure between the base frame 6 and the heat dissipation plate 2 and the positioning structure between the adjacent charging modules 1 may be the same or different, as long as the positioning function between the base frame 6 and the heat dissipation plate 2 can be realized.

In an alternative embodiment, a heat conducting device is connected to the battery pack 5, and the heat conducting device is connected to the heat sink 2.

Specifically, in this embodiment, since the battery assembly 5 rotates along with the base frame 6, and further in order to ensure the heat dissipation performance of the battery assembly 5, a heat conduction device is connected to the battery assembly 5, the heat generated by the battery assembly 5 is guided to the heat dissipation plate 2 through the heat conduction device, and the heat dissipation of the battery assembly 5 is performed through the heat dissipation plate 2.

Specifically, in this embodiment, the heat conducting device may be a heat exchanging pipeline, or may be a metal rod or other device capable of conducting heat, as long as the heat on the battery assembly 5 can be conducted to the heat dissipation plate 2, and the heat dissipation function is realized through the heat dissipation plate 2.

In the present embodiment, the heat conducting device is disposed on the base frame 6, and the heat conducting device is fixed by the base frame 6.

In an alternative embodiment, the base frame 6 is a frame structure or a connection substrate.

In this embodiment, the base frame 6 may be a frame structure as shown in fig. 2, so that the outer surface of the battery assembly 5 has a larger contact area with the outside, and thus has better heat dissipation performance.

In this embodiment, the base frame 6 may be formed by disposing all of the battery modules 5 on a single connecting substrate, and connecting the battery modules into a whole through the connecting substrate. With this arrangement, the stability and strength of the battery assembly 5 on the base frame 6 can be increased.

In an alternative embodiment, the antenna substrate 3, the heat dissipation plate 2, and the charging module 1 are aligned.

In this embodiment, the antenna substrate 3, the heat dissipation plate 2, and the charging module 1 are stacked, and are aligned on each periphery, so that the space utilization rate can be improved to the maximum extent.

It should be noted that the antenna substrate 3, the heat dissipation plate 2 and the charging module 1 may be aligned, or may be protruded from any end according to actual requirements.

Since the charging modules 1 are rotatably connected to the heat dissipation plate 2 and the adjacent charging modules 1 are rotatably connected to each other, the rotating structure may protrude in the stacked structure, resulting in a misaligned arrangement.

In an alternative embodiment, the heat dissipation plate 2 is an aluminum plate.

Specifically, because aluminium has better heat conductivility, use aluminum plate with the material of heating panel 2, can effectual assurance heat conductivity, guaranteed the heat dissipation of the module that charges 1.

It should be noted that, in the present embodiment, the heat dissipation plate 2 is an aluminum plate, but it is not limited to the aluminum plate, and it may be made of other materials as long as it has good thermal conductivity and can dissipate heat of the charging module 1.

The embodiment of the invention has the beneficial effects that:

through carrying out range upon range of setting with module 1 and the antenna substrate 3 that charges, reduced the volume of satellite solar wing, set up heating panel 2 through the one side that is close to antenna substrate 3 at module 1 that charges, guaranteed the radiating efficiency after reducing the volume of satellite solar wing.

The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.