Thermal control radiation sailboard special for spaceflight satellite

Abstract

The utility model discloses a thermal control radiation sailboard special for a spaceflight satellite. The thermal control radiation sailboard comprises a substrate and a liquid cooling heat dissipation assembly. The base plate comprises a frame, an upper sailboard and a lower sailboard are arranged at the upper end and the lower end of the frame, and multiple sets of fixing supports arranged at intervals are arranged in the frame. The liquid cooling heat dissipation assembly comprises a heat dissipation coil pipe which is located on the inner side of the frame and is bent in a snake shape and corresponds to the position between the upper cover plate and the lower cover plate. The sailboard adopts a double-layer structure, and a reasonable connecting and supporting structure is arranged in the sailboard, so that the sailboard can be stably mounted on a satellite, and good form and performance can be kept in a space environment; the heat dissipation coil pipes located in the frame are arranged on the upper sailboard and the lower sailboard to form a liquid cooling heat dissipation network, and heat generated in the satellite operation process can be efficiently dissipated by connecting the heat exchange pipelines to the heat dissipation coil pipes. The efficient and light-weight heat dissipation effect is achieved; the method is suitable for spaceflight satellites of various models, especially satellites with high heat consumption, and can effectively solve the heat control problem during the in-orbit operation period of the satellites.

Description

Technical Field

[0001] The utility model relates to the technical field of aerospace satellites, in particular to a thermal control radiation sailboard dedicated to aerospace satellites. Background Art

[0002] With the continuous development of aerospace technology, the thermal control problem of satellites during on-orbit operation has become increasingly important; although traditional thermal control methods such as thermal control coatings, thermal cladding and heat pipe technology have solved the heat dissipation problem of satellites to a certain extent, they are still insufficient when facing the complex and changeable space environment; especially for satellites with high heat consumption, traditional cooling systems often cannot meet the needs, and may increase the weight and complexity of the satellite, resulting in increased satellite launch costs. Utility Model Content

[0003] In response to the defects in the existing technology, the utility model proposes a thermal control radiation sail panel specially used for aerospace satellites, which can efficiently dissipate heat for the satellite and has a firm and stable overall structure, effectively solving the technical problems existing in the existing technology.

[0004] The technical solution adopted by the utility model is: a thermal control radiation sailboard specially used for aerospace satellites, comprising a base plate and a liquid cooling and heat dissipation component;

[0005] The base plate includes a frame, and an upper sail board and a lower sail board are provided at the upper and lower ends of the frame. A plurality of fixed brackets arranged at intervals are provided in the frame, and the fixed brackets include an upper bracket and a lower bracket arranged up and down. The upper bracket and the lower bracket are respectively fixed to the upper sail board and the lower sail board, and the upper bracket and the lower bracket are also fixedly connected to the end of the frame; the liquid cooling heat dissipation component includes a heat dissipation coil that is serpentinely bent and located between the upper cover plate and the lower cover plate corresponding to the inner side of the frame.

[0006] In this technical solution, the thermal control radiation sail panel adopts a double-layer structure. The upper sail panel and the lower sail panel are fixed by a frame and a fixed bracket built into the frame to ensure that the sail panel structure remains stable and firm; the heat dissipation coil located in the frame is arranged on the upper sail panel and the lower sail panel to form a liquid cooling network. The heat generated during the operation of the satellite can be connected to the heat dissipation coil through the heat exchange pipe for efficient heat dissipation; achieving efficient and lightweight heat dissipation effect to ensure the stable operation of the satellite.

[0007] Preferably, a reinforcing frame is provided on the inner side of the frame, a fixing opening is provided in the middle of the reinforcing frame, and the fixing opening is provided with a pressing pad and a pressing head that fix the upper sailboard and the lower sailboard and adapt to each other.

[0008] Preferably, a mounting head is provided on one outer side of the frame, and a liquid cooling joint connected to the input end and the output end of the heat dissipation coil is correspondingly provided on the mounting head.

[0009] Preferably, a clearance opening is provided between the upper bracket and the lower bracket for the heat dissipation coil to pass through.

[0010] Preferably, the outer surfaces of the frame, upper sailboard and lower sailboard are provided with a heat dissipation radiation coating.

[0011] The beneficial effects of the present invention are as follows: the sail panel of the present invention adopts a double-layer structure as a whole, and is equipped with a reasonable connection and support structure, which ensures that the sail panel can be stably installed on the satellite and maintains a good shape and performance in the space environment; the heat dissipation coils located in the frame are arranged on the upper sail panel and the lower sail panel to form a liquid cooling heat dissipation network, and the heat generated during the operation of the satellite can be connected to the heat dissipation coils through the heat exchange pipes for efficient heat dissipation, achieving efficient and lightweight heat dissipation effects; the present invention also coats the outer surface of the sail panel with a heat dissipation radiation coating, so that the sail panel has excellent reflection and radiation properties, and can quickly dissipate the absorbed heat into space in the form of infrared radiation, further improving the overall heat dissipation effect of the sail panel; the present invention is suitable for various types of aerospace satellites, especially satellites with high heat consumption, and can effectively solve their thermal control problems during on-orbit operation; it has high practical value. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly describes the drawings required for the specific embodiments or the description of the prior art. Similar elements or parts are generally identified by similar reference numerals throughout the drawings. Elements or parts in the drawings are not necessarily drawn to scale.

[0013] Figure 1 A three-dimensional diagram of a thermal control radiation sailboard dedicated to a space satellite provided in Example 1 of the present utility model;

[0014] Figure 2 This is a schematic diagram of the assembly of a thermal control radiation sailboard dedicated to a space satellite provided in the first embodiment of the present utility model.

[0015] In the accompanying drawings: frame 100, reinforcement frame 110, fixing port 111, upper sailboard 200, lower sailboard 300, upper bracket 400, lower bracket 500, heat dissipation coil 600, pressing pad 700, pressing head 800, installation head 900, connector 1000. DETAILED DESCRIPTION

[0016] The following embodiments of the technical solution of the present invention are described in detail with reference to the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present invention and are therefore only examples and are not intended to limit the scope of protection of the present invention.

[0017] It should be noted that, unless otherwise specified, the technical terms or scientific terms used in this application should have the common meanings understood by those skilled in the art to which this utility model belongs.

[0018] like Figure 1 and Figure 2 As shown, the first specific embodiment of the present invention provides a thermal control radiation sailboard dedicated to a space satellite. This type of sailboard has the characteristics of good heat dissipation effect and firm and stable structure, ensuring that the sailboard can operate stably and normally; it specifically includes a base plate and a liquid cooling heat dissipation component; wherein, the base plate includes a frame 100, and the upper and lower ends of the frame 100 are provided with an upper sailboard 200 and a lower sailboard 300, and the frame 100 is provided with a plurality of groups of fixed brackets arranged at intervals, and the fixed brackets include an upper bracket 400 and a lower bracket 500 arranged up and down, and the upper bracket 400 and the lower bracket 500 are respectively fixed to the upper sailboard 200 and the lower sailboard 300, and the upper bracket 400 and the lower bracket 500 are also fixedly connected to the end of the frame 100; the liquid cooling heat dissipation component includes a heat dissipation coil 600 located on the inner side of the frame 100 and corresponding to the upper cover plate and the lower cover plate and bent in a serpentine shape.

[0019] like Figure 1 and Figure 2 As shown, through the above-mentioned settings, the thermal control radiation sailboard provided in this embodiment adopts a double-layer structure, and the upper sailboard 200 and the lower sailboard 300 are fixed by the frame 100 and the fixed bracket built into the frame 100. There are multiple groups of fixed brackets, and each group of upper brackets 400 and lower brackets 500 can be fixed accordingly with the upper sailboard 200 and the lower sailboard 300 to ensure that the sailboard structure remains stable and firm; in order to achieve the requirements of firmness and lightweight, the frame 100 and the fixed bracket preferably use lightweight and high-strength alloy materials, which is beneficial to reducing the overall weight of the sailboard and reducing the launch cost of the satellite; when the sailboard is fixedly assembled with the frame 100 and the fixed component, the lightweight screw connector 1000 in the prior art is adopted, and the corresponding holes are opened according to the fixed position during production, which will not be repeated here.

[0020] like Figure 1 and Figure 2As shown, the heat dissipation coil 600 located within the frame 100 is arranged between the upper sailboard 200 and the lower sailboard 300 to form a liquid cooling heat dissipation network. The heat dissipation coil 600 can be connected to the heat dissipation pipeline of the satellite, and the heat generated during the operation of the satellite can be efficiently dissipated through the heat dissipation coil 600, achieving an efficient and lightweight heat dissipation effect and ensuring the stable operation of the satellite. In this embodiment, the heat dissipation coil 600 can be made of heat dissipation copper pipe, which has a better heat dissipation effect. In production applications, in order to improve the heat dissipation effect, in this embodiment, a heat dissipation radiation coating is provided on the surfaces of the frame 100, the upper sailboard 200, and the lower sailboard 300. The heat dissipation radiation coating uses the coating materials for heat dissipation in the existing technology, so that the overall sailboard has excellent reflection and radiation performance, and can quickly dissipate the absorbed heat into space in the form of infrared radiation, further improving the heat dissipation effect.

[0021] As Figure 1 and Figure 2 shown, in order to further improve the overall strength of the sailboard structure, in this embodiment, a strengthening framework 110 is provided inside the frame 100. A fixing port 111 is provided in the middle of the strengthening framework 110, and a pressing pad 700 and a pressing head 800 that are used to fix the upper sailboard 2 with the lower sailboard 300 and are mutually adapted are provided in the fixing port 111. The setting of the strengthening framework 110 makes the overall frame 100 in a "day" - shaped structure. The upper sailboard 200 and the lower sailboard 300 are further fixedly connected to the strengthening framework 110 through the pressing pad 700 and the pressing head 800, improving the overall stability.

[0022] As Figure 1 and Figure 2 shown, in actual applications, the entire sailboard needs to be installed on the satellite. For the convenience of connection, in this embodiment, a mounting head 900 is provided on one outer side of the frame 100, and liquid - cooling connectors corresponding to the input end and the output end of the heat dissipation coil 600 are provided on the mounting head 900. In this way, the entire sailboard structure can be installed through the mounting head 900, and the liquid - cooling connectors can be connected to the liquid - cooling pipeline. The coolant is transported to the heat dissipation pipe through a circulation pump, and by using the convection heat transfer principle of the circulating flow of the refrigerant, the heat of the liquid in the pipeline is effectively diffused and spread to the surface of the sailboard to implement efficient heat dissipation.

[0023] As Figure 1 and Figure 2 shown, since the heat dissipation coil 600 is located inside the frame 100, in order to avoid interference of the fixing bracket on the installation of the heat dissipation coil 600, in this embodiment, a让位口 (let - through hole) arranged at intervals is provided between the upper support 400 and the lower support 500 for the heat dissipation coil 600 to pass through. The heat dissipation coil 600 passes through the let - through hole and can be further fixed by a fixing bracket to ensure the stability of the installation of the heat dissipation structure.

[0024] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or make equivalent replacements for some or all of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present invention, and they should all be included in the scope of the claims and description of the present invention.

Claims

1. A thermal control radiation sailboard dedicated to a space satellite, characterized in that: Including base plate and liquid cooling heat dissipation components; The base plate comprises a frame (100), an upper sailboard (200) and a lower sailboard (300) are provided at the upper and lower ends of the frame (100), a plurality of fixed brackets arranged at intervals are provided in the frame (100), the fixed brackets comprising an upper bracket (400) and a lower bracket (500) arranged up and down, the upper bracket (400) and the lower bracket (500) being fixed to the upper sailboard (200) and the lower sailboard (300) respectively, and the upper bracket (400) and the lower bracket (500) are also fixedly connected to the end of the frame (100) and the frame (100); The liquid cooling heat dissipation component comprises a heat dissipation coil (600) located on the inner side of the frame (100) and corresponding to the upper cover plate and the lower cover plate and bent in a serpentine shape.

2. The thermal control radiation sailboard dedicated to a space satellite according to claim 1, characterized in that: A reinforcing frame (110) is provided on the inner side of the frame (100), a fixing opening (111) is provided in the middle of the reinforcing frame (110), and a pressing pad (700) and a pressing head (800) are provided in the fixing opening (111) for fixing the upper sailboard (200) and the lower sailboard (300) and matching with each other.

3. The thermal control radiation sailboard dedicated to a space satellite according to claim 1, characterized in that: A mounting head (900) is provided on one outer side of the frame (100), and a liquid cooling joint connected to the input end and the output end of the heat dissipation coil (600) is provided on the mounting head (900).

4. The thermal control radiation sailboard dedicated to a space satellite according to claim 1, characterized in that: A clearance opening for the heat dissipation coil (600) to pass through is provided between the upper bracket (400) and the lower bracket (500).

5. The thermal control radiation sailboard dedicated to a space satellite according to claim 1, characterized in that: The outer surfaces of the frame (100), the upper sailboard (200) and the lower sailboard (300) are provided with a heat dissipation radiation coating.

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