A lightweight structure for a laser-radio integrated communication payload for microsatellites

Abstract

This invention discloses a lightweight structure for a laser-radio integrated communication payload for microsatellites, belonging to the field of satellite payload lightweighting technology. The invention includes a mirror body and a substrate. Multiple honeycomb holes are evenly distributed on the back of the mirror body, and triangular ribs are provided at the intersections of these holes. A support ring is fitted to the outer edge of the mirror body, and three positioning holes and nine mounting holes are evenly distributed on the outer surface of the support ring. By evenly distributing hexagonal honeycomb holes on the back of the mirror body, the weight of the mirror body is significantly reduced. By using novel lightweight materials for the mirror body, substrate, and support, the thermal stability of the primary mirror structure is improved while maintaining structural rigidity. This reduces surface distortion while significantly compressing the weight of the primary mirror structure, achieving further optimization compared to traditional lightweighting solutions. This results in the optimization of the satellite payload structure for extreme lightweighting, ultra-stable thermal performance, and high dynamic rigidity.

Description

Technical Field

[0001] This invention relates to the field of lightweight satellite payload technology, specifically a lightweight structure for a laser-radio integrated communication payload for microsatellites. Background Technology

[0002] The lightweighting of satellite payloads requires comprehensive consideration of various factors, including functional integration, harsh space environment, extreme size and weight constraints, thermal management, vibration stability, and manufacturing process. It mainly includes lightweight structural platforms, lightweight optomechanical structures (such as lightweight mirror blanks), and lightweight integration of radio frequency antennas. In the optical system, traditional satellite primary mirrors are mostly made of solid mirror blanks, which are heavy and have poor thermal stability, thus affecting the performance and reliability of the optical system. Summary of the Invention

[0003] The purpose of this invention is to provide a lightweight structure for a laser-radio integrated communication payload for microsatellites. By using novel lightweight materials for the mirror body, substrate, and support, the structural rigidity is maintained while the thermal stability of the main mirror structure is improved. The weight of the main mirror structure is greatly reduced while reducing surface distortion, thus solving the problems of large main mirror weight and poor thermal stability.

[0004] This invention is achieved through the following technical solution: This invention relates to a lightweight structure for a laser-radio integrated communication payload for microsatellites, comprising a mirror body and a substrate. The back of the mirror body is uniformly provided with multiple honeycomb holes, and triangular ribs are provided at the intersections of the multiple honeycomb holes. A support ring is fitted to the outer edge of the mirror body, and the outer surface of the support ring is uniformly provided with three positioning holes and nine mounting holes.

[0005] Furthermore, the front surface of the mirror is an optical curved surface, the mirror is made of silicon carbide material through reaction sintering, and the front surface of the mirror is coated with a magnetron sputtered Au reflective film.

[0006] Furthermore, the thermal conductivity of the mirror body is 120 W / mK, and the coefficient of thermal expansion of the mirror body is 2.4 ppm / K.

[0007] Furthermore, the back of the mirror body is provided with a skin, which covers multiple honeycomb holes. The skin is made of reaction-bonded silicon carbide, and the honeycomb holes are regular hexagonal honeycomb cavities. Multiple honeycomb holes form a honeycomb array.

[0008] Furthermore, the diameter of the honeycomb-shaped through holes is between one-fifth and one-eighth of the lens body thickness, the wall thickness of the honeycomb holes is 0.8±0.5mm, and the depth of the honeycomb holes is 80% of the lens body thickness.

[0009] Furthermore, the support ring is equipped with four pairs of flexible hinges, and brackets are connected to the flexible hinges.

[0010] Furthermore, four connecting blocks are provided at the bottom of the substrate, and four pairs of brackets are rotatably connected to the four connecting blocks respectively.

[0011] Furthermore, the substrate is made of carbon fiber composite material, the support is an axial damping rod, the axial damping rod is filled with silicon-based damping adhesive, and the support and flexible hinge are both made of titanium alloy.

[0012] The present invention has the following beneficial effects: By uniformly opening hexagonal honeycomb holes on the back of the mirror body, the weight of the mirror body is significantly reduced. By using new lightweight materials for the mirror body, substrate, and support, the thermal stability of the primary mirror structure is improved while maintaining structural rigidity. The weight of the primary mirror structure is greatly reduced while minimizing surface distortion. This represents a further optimization compared to traditional lightweight solutions, providing a highly reliable and ultra-lightweight optical core component for microsatellite laser communication systems. It achieves the optimization of extreme lightweighting, ultra-stable thermal performance, and high dynamic rigidity of the satellite payload structure.

[0013] Of course, any product implementing this invention does not necessarily need to achieve all of the advantages described above at the same time. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of a lightweight structure.

[0015] Figure 2 This is a schematic diagram of the bottom of the lightweight structure.

[0016] Figure 3 This is a schematic diagram of the installation structure for a lightweight design.

[0017] Figure 4 This is a schematic diagram of the mirror body.

[0018] In the figure: 1. Mirror body; 101. Honeycomb hole; 102. Triangular rib; 103. Skin; 2. Support ring; 201. Positioning hole; 202. Mounting hole; 3. Base plate; 301. Connecting block; 4. Bracket; 401. Flexible hinge. Detailed Implementation

[0019] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] Please see Figure 1-4This invention provides a technical solution: a lightweight structure for a laser-radio integrated communication payload for microsatellites, comprising a mirror body 1 and a substrate 3. The front surface of the mirror body 1 is an optical curved surface. The mirror body 1 is made of silicon carbide material by reaction sintering, with a stiffness-to-weight ratio six times that of aluminum alloy and a thermal deformation coefficient only one-fifth that of microcrystalline glass. The front surface of the mirror body 1 is coated with a magnetron sputtered Au reflective film, which can improve the reflectivity of the mirror body 1. The thermal conductivity of the mirror body 1 is 120 W / mK, and the thermal expansion coefficient of the mirror body 1 is 2.4 ppm / K. Multiple honeycomb holes 101 are uniformly opened on the back of the mirror body 1, and triangular ribs 102 are provided at the intersection of the multiple honeycomb holes 101 to improve the strength of the honeycomb holes 101. A support ring 2 is fitted to the outer edge of the mirror body 1, and the outer surface of the support ring 2 is uniformly opened. There are three positioning holes 201 and nine mounting holes 202. The positioning pins installed in the three positioning holes 201 can bear the shear force of the mirror body. The bolts with disc springs installed in the nine mounting holes 202 provide axial preload and release thermal stress. The back of the mirror body 1 is provided with a skin 103, which covers multiple honeycomb holes 101. The skin 103 is made of reaction sintered silicon carbide material, which can resist gravity deformation. The honeycomb holes 101 are regular hexagonal honeycomb cavities. Multiple honeycomb holes 101 form a honeycomb hole array to achieve a significant weight reduction effect. The diameter of the honeycomb through holes 11 is between one-fifth and one-eighth of the thickness of the mirror body. The wall thickness of the honeycomb holes 101 is 0.8±0.05mm, and the hole depth of the honeycomb holes 101 is 80% of the thickness of the mirror body 1.

[0021] The support ring 2 is provided with four pairs of flexible hinges 401, and the flexible hinges 401 are connected to the brackets 4. The bottom of the base plate 3 is provided with four connecting blocks 301. The four pairs of brackets 4 are rotatably connected to the four connecting blocks 301 respectively. Two rotating slots are opened on the connecting blocks 301, and the rotating slots are fitted with shafts. The top of the bracket 4 is connected to the surface of the shaft, which can realize the rotation effect between the bracket and the connecting block. The base plate 3 is made of carbon fiber composite material, and the bracket 4 is an axial damping rod. The axial damping rod is filled with silicon-based damping glue, which can realize the vibration reduction effect on the mirror body 1. The bracket 4 and the flexible hinges 401 are both made of titanium alloy.

[0022] This invention significantly reduces the weight of the mirror body 1 by uniformly opening hexagonal honeycomb holes 101 on the back of the mirror body 1. By using novel lightweight materials for the mirror body 1, substrate 3, and support 4, the thermal stability of the primary mirror structure is improved while maintaining structural rigidity. The weight of the primary mirror structure is greatly reduced while minimizing surface distortion. This represents a further optimization compared to traditional lightweight solutions, providing a highly reliable and ultra-lightweight optical core component for microsatellite laser communication systems. It achieves the optimization of extreme lightweighting, ultra-stable thermal performance, and high dynamic rigidity of the satellite payload structure.

[0023] The preferred embodiments of the present invention disclosed above are merely illustrative of the invention. These preferred embodiments do not exhaustively describe all details, nor do they limit the invention to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the invention, thereby enabling those skilled in the art to better understand and utilize the invention. The invention is limited only by the claims and their full scope and equivalents.

Claims

1. A lightweight structure for a laser-radio integrated communication payload for microsatellites, comprising a mirror body (1), characterized in that: The back of the mirror body (1) is evenly provided with multiple honeycomb holes (101), and a triangular rib plate (102) is provided at the intersection of the multiple honeycomb holes (101). The outer edge of the mirror body (1) is fitted with a support ring (2), and the outer surface of the support ring (2) is evenly provided with three positioning holes (201) and nine mounting holes (202).

2. The lightweight structure of a laser-radio integrated communication payload for microsatellites according to claim 1, characterized in that, The front surface of the mirror body (1) is an optical curved surface. The mirror body (1) is made of silicon carbide material by reaction sintering. The front surface of the mirror body (1) is coated with a magnetron sputtered Au reflective film.

3. The lightweight structure of a laser-radio integrated communication payload for microsatellites according to claim 2, characterized in that, The thermal conductivity of the mirror body (1) is 120 W / mK, and the coefficient of thermal expansion of the mirror body (1) is 2.4 ppm / K.

4. The lightweight structure of a laser-radio integrated communication payload for microsatellites according to claim 3, characterized in that, The back of the mirror body (1) is provided with a skin (103), which covers a plurality of honeycomb holes (101). The skin (103) is made of reaction sintered silicon carbide material, and the honeycomb holes (101) are regular hexagonal honeycomb cavities. The plurality of honeycomb holes (101) form a honeycomb cavity array.

5. The lightweight structure of a laser-radio integrated communication payload for microsatellites according to claim 4, characterized in that, The diameter of the honeycomb through hole (11) is between one-fifth and one-eighth of the thickness of the mirror body, the wall thickness of the honeycomb hole (101) is 0.8±0.05mm, and the depth of the honeycomb hole (101) is eighty percent of the thickness of the mirror body (1).

6. The lightweight structure of a laser-radio integrated communication payload for microsatellites according to claims 1-5, characterized in that, The support ring (2) is provided with four pairs of flexible hinges (401), and the flexible hinges (401) are connected to the brackets (4).

7. The lightweight structure of a laser-radio integrated communication payload for microsatellites according to claim 6, characterized in that, It also includes a substrate (3), on the bottom of which are provided four connecting blocks (301), and four pairs of brackets (4) are rotatably connected to the four connecting blocks (301) respectively.

8. The lightweight structure of a laser-radio integrated communication payload for microsatellites according to claim 7, characterized in that, The substrate (3) is made of carbon fiber composite material, the bracket (4) is an axial damping rod, the axial damping rod is filled with silicon-based damping glue, and the bracket (4) and the flexible hinge (401) are both made of titanium alloy.

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