Generalized satellite configuration suitable for multiple types of loads

Abstract

The application provides a universal satellite configuration suitable for multiple types of loads, comprising a platform cabin, a universal thermal control information structure plate and a satellite load; the universal thermal control information structure plate is arranged on the platform cabin, and the satellite load is connected to the universal thermal control information structure plate; the universal thermal control information structure plate is arranged with pre-buried holes, pre-buried buses and thermal control components for adapting different types of satellite loads. The application adopts a flexible design idea to select and match different load functional modules according to actual needs, and through the configuration of the universal thermal control information structure plate, the same satellite platform cabin can be satisfied, the adaptation of different loads can be realized, and the batch production of the platform cabin is facilitated.

Description

Technical Field

[0001] This invention relates to the field of spacecraft, and more specifically, to a universal satellite configuration applicable to a variety of payloads. Background Technology

[0002] To meet the long-term needs of integrated remote sensing applications, it is necessary to possess comprehensive analytical capabilities for detection elements, detection methods, payloads, and satellite platforms to satisfy the construction of a system-effective remote sensing satellite cloud network. The cloud network requires a large variety of satellite payloads and a large number of satellites, but currently, different payloads are often designed with separate, specific satellite platforms, which is not conducive to future mass production needs. Therefore, a universal satellite platform suitable for multiple payloads needs to be designed.

[0003] Compared with existing patents:

[0004] Application number CN202310926825.5, entitled "A Multifunctional Satellite Configuration," describes a satellite configuration where solar panels are controllably separated from the satellite body. This avoids the impact of single-panel failure or damage on satellite operation, improving the flexibility and reliability of the satellite system. This application primarily proposes a satellite configuration based on a universal satellite platform with a rapid installation design for multiple types of payloads to meet the needs of mass production of satellites.

[0005] Application number CN202211094854.1, entitled "An Integrated Open-Platform Satellite Configuration with Payload Structure," describes a patent that employs an open-platform isosceles trapezoidal main structure, integrating the payload structure and platform structure. This reduces structural weight, provides ample assembly and operation space, and offers high testing flexibility, meeting the requirements for automated assembly and mass testing of satellite constellations. Unlike the integrated platform-payload satellite configuration designed in that patent, this application proposes a universal satellite configuration for multiple payloads, consisting of a satellite platform, a universal thermal control information structure plate, and the satellite payload.

[0006] Application number CN202311481138.3, entitled "A High-Accommodation-Ratio Modular Satellite Configuration," independently designs the satellite main module and payload expansion module to meet the functional design requirements of different types of satellites. Through a high-accommodation-ratio design, it enables multi-satellite launches and achieves a large-area ground-pointing antenna array during on-orbit deployment. Compared to this patent, this application also proposes flexible satellite design; however, this application places greater emphasis on universal payload interfaces and flexible satellite configuration design for payload selection. It utilizes a universal thermal control information structure board to connect the platform and payload, providing the physical conditions for plug-and-play operation of multiple payloads. Summary of the Invention

[0007] In view of the shortcomings of the prior art, the purpose of this invention is to provide a universal satellite configuration applicable to multiple types of payloads.

[0008] According to the present invention, a generalized satellite configuration applicable to multiple types of payloads includes: a platform module, a generalized thermal control information structure plate, and a satellite payload;

[0009] A universal thermal control information structure board is installed on the platform cabin, and the satellite payload is connected to the universal thermal control information structure board;

[0010] The generalized thermal control information structure board is equipped with pre-embedded holes, pre-embedded buses, and thermal control components for adapting to different types of satellite payloads.

[0011] Preferably, the pre-embedded hole includes: a sliding fixed guide rail and a pre-embedded block that moves along the sliding fixed guide rail;

[0012] The sliding fixed guide rail is provided with a limit structure, and the pre-embedded block is provided with a movable limit body. When the load screw of the satellite payload is installed on the pre-embedded block, the load screw pushes out the movable limit body and interferes with the limit structure. When the load screw is removed, the movable limit body can be restored to a state where it does not interfere with the limit structure.

[0013] Preferably, the sliding fixed guide rail includes: a limiting structure and a guide rail groove;

[0014] The guide rail groove is provided with limiting structures at both ends along the depth direction, and the limiting structures are arranged along both sides of the end face shape of the guide rail groove.

[0015] The opposing side of the limiting structures on both sides is set in a wave shape and together they form a shape with multiple interconnected circles.

[0016] Preferably, the embedded block includes: a fastening threaded post, a movable limiting body, and a cylindrical boss;

[0017] The fastening threaded post has cylindrical bosses at both ends. The cylindrical bosses have grooves on their periphery to accommodate two semi-circular movable limiting bodies. When the movable limiting bodies are fully accommodated in the cylindrical bosses, the outer periphery of the movable limiting bodies does not protrude from the periphery of the cylindrical bosses.

[0018] Preferably, the fastening threaded post is installed in the guide rail groove along the depth direction of the guide rail groove, and the fastening threaded post is allowed to move along the shape direction of the end face of the guide rail groove;

[0019] The cylindrical boss, along with the movable limiting body, is located within the limiting structure. The diameter of the cylindrical boss is smaller than the width of the circular connecting part of the limiting structure, and the diameter of the cylindrical boss is larger than the width of the guide groove.

[0020] Preferably, a threaded hole is provided in the middle of the end face of the cylindrical boss, which is connected to the fastening threaded post. The load screw is inserted into the cylindrical boss through the threaded hole and pushes the outer peripheral side of the movable limiting body to the outer peripheral side of the protruding cylindrical boss.

[0021] When the movable limiting body is pushed out, the maximum diameter formed by the two movable limiting bodies is greater than the width of the circular connection of the limiting structure, and the embedded block is limited along the shape direction of the guide rail groove end face.

[0022] Preferably, the movable limiting body has a slot with a diameter smaller than that of the load screw on the side near the center.

[0023] Preferably, the end face shape of the guide rail groove is set to a cross shape or an X shape;

[0024] The guide rail grooves are provided in multiple ways and arranged in an array.

[0025] Preferably, electrical connectors for multiple different types of satellite payloads are connected via the pre-embedded bus.

[0026] Preferably, the thermal control component includes: a graphene thermally conductive film and a pre-embedded heat pipe;

[0027] The generalized thermal control information structure plate has a graphene thermal conductive film on the side facing the satellite payload. One end of the pre-embedded heat pipe extends to one side of the graphene thermal conductive film, and the other end extends to the side near the platform compartment.

[0028] Compared with the prior art, the present invention has the following beneficial effects:

[0029] 1. This application adopts a flexible design concept, which can select different payload functional modules according to actual needs. By configuring a universal thermal control information structure board, it can meet the needs of the same satellite platform cabin and achieve adaptation to different payloads, which is conducive to the mass production of platform cabins.

[0030] 2. This application, through the pre-embedded hole array and cross sliding fixed guide rail, can meet the mechanical connection of single machine size for various types of loads, and has stronger load adaptability. Attached Figure Description

[0031] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0032] Figure 1 This is a schematic diagram of the overall satellite configuration;

[0033] Figure 2 This is a schematic diagram of a generalized thermal control information structure board.

[0034] Figure 3 This is a schematic diagram of the pre-embedded hole structure;

[0035] Figure 4 Schematic diagram of a sliding fixed guide rail structure;

[0036] Figure 5 This is a schematic diagram of the embedded block structure;

[0037] Figure 6 This is a schematic diagram showing the pre-embedded hole in an unlocked state.

[0038] Figure 7 This is a schematic diagram showing the locked state of the pre-embedded hole;

[0039] As shown in the figure:

[0040]

[0041] Detailed Implementation

[0042] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0043] like Figure 1 As shown, this embodiment includes: a platform compartment 1, a universal thermal control information structure board 2, and a satellite payload 3; the universal thermal control information structure board 2 is installed on the platform compartment 1, and the satellite payload 3 is connected to the universal thermal control information structure board 2; the universal thermal control information structure board 2 is provided with pre-embedded holes 21, pre-embedded buses 22, and thermal control components 23 for adapting to different types of satellite payloads 3. Electrical connectors for multiple different types of satellite payloads 3 are connected through the pre-embedded buses 22.

[0044] like Figure 2 As shown, the thermal control component 23 includes: a graphene thermal conductive film 231 and a pre-embedded heat pipe 232; the generalized thermal control information structure plate 2 is provided with a graphene thermal conductive film 231 on the side facing the satellite payload 3, and one end of the pre-embedded heat pipe 232 extends to one side of the graphene thermal conductive film 231, and the other end extends to the side near the platform compartment 1.

[0045] like Figure 3-5As shown, the pre-embedded hole 21 includes: a sliding fixed guide rail 211 and a pre-embedded block 212 that moves along the sliding fixed guide rail 211; the sliding fixed guide rail 211 is provided with a limiting structure 2111, and the pre-embedded block 212 is provided with a movable limiting body 2122. When the load screw 31 of the satellite payload 3 is installed into the pre-embedded block 212, the load screw 31 pushes out the movable limiting body 2122 and interferes with the limiting structure 2111. When the load screw 31 is removed, the movable limiting body 2122 can be restored to a state where it does not interfere with the limiting structure 2111. Specifically, the sliding fixed guide rail 211 includes: a limiting structure 2111 and a guide rail groove 2112; the guide rail groove 2112 is provided with limiting structures 2111 at both ends along the depth direction, and the limiting structures 2111 are arranged on both sides of the end face shape of the guide rail groove 2112; the opposite side of the two limiting structures 2111 is set as a wave shape and forms multiple circular interconnected shapes, similar to the shape of a candied hawthorn. The embedded block 212 includes: a fastening threaded post 2121, a movable limiting body 2122, and a cylindrical boss 2123; the fastening threaded post 2121 has cylindrical bosses 2123 at both ends, and the cylindrical bosses 2123 have grooves on their circumferences to accommodate two semi-circular movable limiting bodies 2122. When the movable limiting bodies 2122 are completely accommodated in the cylindrical bosses 2123, the outer circumference of the movable limiting bodies 2122 does not protrude from the circumference of the cylindrical bosses 2123. The fastening threaded post 2121 is located along the depth direction of the guide groove 2112 (i.e., Figure 1 The threaded post 2121 is installed in the guide rail groove 2112 in the vertical direction. The threaded post 2121 is allowed to move along the shape direction of the end face of the guide rail groove 2112 (i.e., the cross direction). The cylindrical boss 2123, together with the movable limiting body 2122, is located in the limiting structure 2111. The diameter of the cylindrical boss 2123 is smaller than the width of the circular connection of the limiting structure 2111, and the diameter of the cylindrical boss 2123 is larger than the width of the guide rail groove 2112. A threaded hole 21211 is provided in the middle of the end face of the cylindrical boss 2123, which is connected to the fastening threaded post 2121. The load screw 31 is inserted into the cylindrical boss 2123 through the threaded hole 21211 and pushes the outer periphery of the movable limiting body 2122 to the outer periphery of the protruding cylindrical boss 2123. When the movable limiting body 2122 is pushed out, the maximum diameter formed by the two movable limiting bodies 2122 is greater than the width of the circular connection of the limiting structure 2111, and the embedded block 212 is limited along the shape direction of the end face of the guide groove 2112.

[0046] In one embodiment, the movable limiting body 2122 is provided with a slot with a diameter smaller than that of the load screw 31 on the side near the center, so that the load screw 31 can push out the movable limiting bodies 2122 on both sides.

[0047] In one embodiment, the end face shape of the guide rail groove 2112 is set to a cross shape or an X shape;

[0048] In one embodiment, the guide rail grooves 2112 are provided in multiple and arranged in an array.

[0049] Working principle:

[0050] Combination Figure 6-7 As shown, when the satellite payload 3 is installed on the platform compartment 1, the universal thermal control information structure board 2 of this embodiment can meet the installation requirements of different types of satellite payloads 3. The pre-embedded bus 22 of the universal thermal control information structure board 2 is connected to multiple electrical connectors of different types of satellite payloads 3. The pre-embedded block 212 of the pre-embedded hole 21 can move along the sliding fixed guide rail 211 to adapt to satellite payloads 3 of different sizes and shapes. When the load screw 31 of the satellite payload 3 is inserted into the pre-embedded block 212, the movable limit body 2122 is pushed out, thus realizing the limitation of the pre-embedded block 212 in the current position. The graphene thermal conductive film 231 of the thermal control component 23 absorbs the heat of the satellite payload 3 and transfers it to the heat dissipation surface of the platform compartment 1 through the pre-embedded heat pipe 232.

[0051] Example 2

[0052] Example 2 is a preferred example of Example 1.

[0053] like Figure 1 As shown, this embodiment mainly includes: a platform cabin 1, a universal thermal control information structure board 2, and satellite payloads 3. The universal thermal control information structure board 2 provides flexible mechanical, electrical, and thermal interfaces, enabling the mounting of different satellite payloads 3 on the same platform cabin 1.

[0054] like Figure 2 As shown, the universal thermal control information structure board 2 consists of a pre-embedded bus 22, pre-embedded holes 21, and a thermal control component 23. The pre-embedded bus 22 is composed of pre-embedded electrical connectors of different models, enabling flexible electrical connection configurations; the pre-embedded holes 21 enable flexible mechanical interface configurations; the thermal control component 23 consists of a graphene thermally conductive film 231 and pre-embedded heat pipes 232. The graphene thermally conductive film 231 is laid flat on the load-bearing surface of the universal thermal control information structure board 2, providing uniform heat conduction across the entire board surface. The pre-embedded heat pipes 232 are evenly installed inside the universal thermal control information structure board 2, drawing the heat from the graphene thermally conductive film 231 to the heat dissipation surface of the platform compartment 1, thus achieving flexible thermal control.

[0055] like Figure 3-5As shown, the pre-embedded hole 21 consists of a sliding fixed guide rail 211 and a pre-embedded block 212. The sliding fixed guide rail 211 adopts a cross-shaped configuration, providing space for the pre-embedded block 212 to move and adjust along two axes. The pre-embedded block 212 is installed on the guide rail groove 2112 of the sliding fixed guide rail 211 and is adjusted according to the installation port position of the satellite payload 3, providing a mechanical installation and fastening function for the satellite payload 3. The sliding fixed guide rail 211 consists of a limiting structure 2111 and a guide rail groove 2112. The limiting structure 2111 is set as a concave shape with the same diameter as the outer arc of the movable limiting body 2122, and is evenly distributed on both sides of the guide rail groove 2112, which can ensure that it has a fixing and limiting function at multiple positions within the guide rail groove 2112. The guide rail groove 2112 has a hollow cross-shaped structure, allowing the fastening threaded post 2121 to move arbitrarily within the guide rail groove 2112. The embedded block 212 consists of a fastening threaded post 2121 and a movable limiting body 2122. The fastening threaded post 2121 has threaded holes 21211 for connection with the load screw 31. Cylindrical bosses 2123 are located at both ends of the fastening threaded post 2121, which can limit the vertical movement of the sliding fixed guide rail 211 after installation. The cylindrical bosses 2123 have a hollow interior for installing the movable limiting bodies 2122. The movable limiting body 2122 has a combination of a semicircle and a cube. The radius of the semicircle is the same as that of the cylindrical boss 2123. A semicircular slot is provided at the center end of the cylindrical boss 2123, which fits into the hollow structure of the cylindrical boss. Two movable limiting bodies 2122 are used in conjunction within one cylindrical boss 2123.

[0056] like Figure 6-7 As shown, when the embedded block 212 is in the unlocked state, the two movable limiting bodies 2122 are close together, and the outer surface of the arc of the movable limiting body 2122 does not exceed the outer surface of the cylindrical boss 2123, so as not to interfere with the movement of the embedded block 212. When the embedded block 212 is in the locked state, the load screw 31 is tightened downward through the threaded hole 21211 and the slot between the two movable limiting bodies 2122. The column of the load screw 31 pushes the movable limiting body 2122 outward, so that the outer surface of the arc of the movable limiting body 2122 exceeds the outer surface of the cylindrical boss 2123 and abuts against the concave arc of the limiting structure 2221 of the sliding fixed guide rail 211, thereby restricting its movement.

[0057] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0058] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A universal satellite configuration applicable to multiple types of payloads, characterized in that, include: Platform cabin (1), universal thermal control information structure board (2), and satellite payload (3); A universal thermal control information structure plate (2) is installed on the platform cabin (1), and the satellite payload (3) is connected to the universal thermal control information structure plate (2); The generalized thermal control information structure board (2) is provided with pre-embedded holes (21), pre-embedded buses (22) and thermal control components (23) for adapting to different types of satellite payloads (3). The pre-embedded hole (21) includes: a sliding fixed guide rail (211) and a pre-embedded block (212) that moves along the sliding fixed guide rail (211). The sliding fixed guide rail (211) is provided with a limiting structure (2111), and the pre-embedded block (212) is provided with a movable limiting body (2122). When the load screw (31) of the satellite payload (3) is installed on the pre-embedded block (212), the load screw (31) pushes out the movable limiting body (2122) and interferes with the limiting structure (2111). When the load screw (31) is removed, the movable limiting body (2122) can be restored to a state that does not interfere with the limiting structure (2111). The sliding fixed guide rail (211) includes: a limiting structure (2111) and a guide rail groove (2112); The guide rail groove (2112) is provided with limiting structures (2111) at both ends along the depth direction, and the limiting structures (2111) are arranged on both sides of the end face shape of the guide rail groove (2112). The two limiting structures (2111) on opposite sides are set in a wave shape and together form a shape of multiple interconnected circles; The embedded block (212) includes: a fastening threaded post (2121), a movable limiting body (2122), and a cylindrical boss (2123). The fastening threaded post (2121) is provided with cylindrical bosses (2123) at both ends. The cylindrical bosses (2123) are provided with grooves on their periphery to accommodate two semi-circular movable limiting bodies (2122). When the movable limiting bodies (2122) are completely accommodated in the cylindrical bosses (2123), the outer periphery of the movable limiting bodies (2122) does not protrude from the periphery of the cylindrical bosses (2123). The fastening threaded post (2121) is installed in the guide rail groove (2112) along the depth direction of the guide rail groove (2112), and the fastening threaded post (2121) is allowed to move along the shape direction of the end face of the guide rail groove (2112); The cylindrical boss (2123) and the movable limiting body (2122) are located in the limiting structure (2111). The diameter of the cylindrical boss (2123) is smaller than the width of the circular connection of the limiting structure (2111), and the diameter of the cylindrical boss (2123) is larger than the width of the guide groove (2112). The cylindrical boss (2123) has a threaded hole (21211) in the middle of its end face that connects to the fastening threaded post (2121). The load screw (31) is inserted into the cylindrical boss (2123) through the threaded hole (21211) and pushes the outer periphery of the movable limiting body (2122) to the outer periphery of the protruding cylindrical boss (2123). When the movable limiting body (2122) is pushed out, the maximum diameter formed by the two movable limiting bodies (2122) is greater than the width of the circular connection of the limiting structure (2111), and the embedded block (212) is limited along the shape direction of the end face of the guide groove (2112); The movable limiting body (2122) has a slot with a diameter smaller than that of the load screw (31) on the side near the center; The end face shape of the guide rail groove (2112) is set to a cross shape or an X shape; The guide rail grooves (2112) are provided in multiple and arranged in an array.

2. The universal satellite configuration applicable to multiple payloads according to claim 1, characterized in that: Electrical connectors for multiple different types of satellite payloads (3) are connected via the pre-embedded bus (22).

3. The universal satellite configuration applicable to multiple payloads according to claim 1, characterized in that, The thermal control component (23) includes: a graphene thermal conductive film (231) and a pre-embedded heat pipe (232); The generalized thermal control information structure plate (2) is provided with a graphene thermal conductive film (231) on the side facing the satellite payload (3). One end of the pre-embedded heat pipe (232) extends to one side of the graphene thermal conductive film (231), and the other end extends to the side near the platform cabin (1).

Images