Universal satellite configuration suitable for various loads

Abstract

The invention provides a universal satellite configuration suitable for various loads. The universal satellite configuration comprises a platform cabin, a universal thermal control information structure plate and a satellite load, the platform cabin is provided with a universal thermal control information structural plate, and the satellite load is connected to the universal thermal control information structural plate; pre-embedded holes, pre-embedded buses and thermal control assemblies which are used for adapting to different types of satellite loads are arranged on the universal thermal control information structural plate. The flexible design idea is adopted, different load function modules can be selected and matched according to actual needs, the same satellite platform cabin can be met by configuring the universal thermal control information structural plate, adaptation to different loads is achieved, and batch production of the platform cabin is facilitated.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft, and in particular to a universal satellite configuration suitable for multiple types of payloads. Background Art

[0002] In order to meet the needs of long-term integrated remote sensing applications, it is necessary to have comprehensive analysis of detection elements, detection methods, payloads, satellite platforms, etc. to meet the construction of a system-efficient remote sensing satellite cloud network. Cloud network satellite payload types and satellite quantity requirements are numerous, and currently independent satellite platforms are often designed specifically for different payloads, which is not conducive to future mass production needs. Therefore, it is necessary to design a universal satellite platform that is suitable for a variety of payloads.

[0003] Compared with existing patents:

[0004] The application number is CN202310926825.5, and the name is "A multifunctional satellite configuration". This patent adopts a controllable separation installation of solar panels and satellite body to avoid the failure or damage of a single solar panel affecting the operation of the satellite body, and improve the flexibility and reliability of the satellite system. This application mainly proposes a satellite configuration based on a universal satellite platform and a rapid installation design of multiple types of payloads to meet the mass design and production needs of satellites.

[0005] The application number is CN202211094854.1, and the name is "An open-type satellite configuration with integrated payload structure". The patent adopts an open-type isosceles trapezoidal main structure to integrate the payload structure and platform structure, reduce the structural weight, and provide a large assembly operation space and high test flexibility, meeting the requirements of satellite constellation automated assembly production and batch testing. Different from the platform-payload integrated satellite configuration designed in the patent, the universal satellite configuration for multiple types of payloads proposed in this application consists of three parts: a satellite platform, a universal thermal control information structure board, and a satellite payload.

[0006] The application number is CN202311481138.3, and the name is "A high storage ratio modular satellite configuration". This patent independently designs the satellite main module and the payload expansion module to meet the functional design requirements of different types of satellites. Through the high storage ratio design, multiple satellites can be launched with one rocket, and a large area of ​​ground antenna array can be obtained by deploying in orbit. Compared with this patent, this application proposes a flexible satellite design, but this application pays more attention to the universalization of payload interfaces and the flexible satellite configuration design of payload selection. It uses a universal thermal control information structure board to connect the platform and the payload, providing physical conditions for plug-and-play of multiple payloads. Summary of the invention

[0007] In view of the defects in the prior art, an object of the present invention is to provide a universal satellite configuration suitable for multiple types of payloads.

[0008] A universal satellite configuration applicable to multiple types of payloads provided by the present invention includes: a platform cabin, a universal thermal control information structure board, and a satellite payload;

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

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

[0011] Preferably, the embedded hole comprises: a sliding fixed guide rail and an embedded block moving along the sliding fixed guide rail;

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

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

[0014] The two ends of the guide rail groove along the depth direction are provided with limiting structures, and the limiting structures are arranged along the two sides of the end surface shape of the guide rail groove;

[0015] The opposing sides of the limiting structures on both sides are arranged in a wave shape and form a plurality of circular connected shapes as a whole.

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

[0017] Cylindrical bosses are provided at both ends of the fastening threaded column, and grooves are provided on the circumferential side of the cylindrical bosses for accommodating two semicircular movable limiting bodies. When the movable limiting bodies are fully accommodated in the cylindrical bosses, the outer circumferential side of the movable limiting bodies does not protrude from the circumferential side of the cylindrical bosses.

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

[0019] The cylindrical boss and the movable limiting body are located in 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 rail groove.

[0020] Preferably, a threaded hole connected to the fastening threaded column is provided in the middle of the end surface of the cylindrical boss, and the load screw is inserted into the cylindrical boss through the threaded hole and pushes the outer peripheral side of the movable limiter to the outer peripheral side of the protruding cylindrical boss;

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

[0022] Preferably, a slot hole having a diameter smaller than that of the load screw is provided on one side of the movable limiting body close to the center of the circle.

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

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

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

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

[0027] A graphene thermal conductive film is provided on the side of the universal thermal control information structure plate facing the satellite payload, and one end of the embedded heat pipe extends to one side of the graphene thermal conductive film, and the other end extends to a side close to the platform cabin.

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

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

[0030] 2. This application can meet the mechanical connection of multiple types of loads and single machine sizes through the embedded hole array and cross sliding fixed guide rail, and has stronger load adaptability. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

[0033] Figure 2 It is a schematic diagram of the structure of the universal thermal control information structure board;

[0034] Figure 3 Schematic diagram of the embedded hole structure;

[0035] Figure 4 It is a schematic diagram of the sliding fixed guide rail structure;

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

[0037] Figure 6 This is a schematic diagram of the embedded hole being unlocked;

[0038] Figure 7 This is a schematic diagram of the locking state of the embedded hole;

[0039] As shown in the figure:

[0040]

[0041] DETAILED DESCRIPTION

[0042] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

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

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

[0045] like Figure 3-5As shown, the embedded hole 21 includes: a sliding fixed guide rail 211 and an 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 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 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 limiting structures 2111 are provided at both ends of the guide rail groove 2112 in the depth direction, and the limiting structures 2111 are arranged along both sides of the end surface shape of the guide rail groove 2112; the two sides of the limiting structures 2111 facing each other are provided in a wavy shape and the whole constitutes a plurality of circular connected shapes, which is similar to the shape of a candied haws. The embedded block 212 includes: a fastening threaded column 2121, a movable limiting body 2122 and a cylindrical boss 2123; the fastening threaded column 2121 is provided with cylindrical bosses 2123 at both ends, and the cylindrical bosses 2123 are provided with grooves on the periphery thereof for accommodating two semicircular 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 column 2121 is provided along the depth direction of the guide groove 2112 (i.e., Figure 1 The fastening threaded column 2121 allows movement along the end face shape direction of the guide groove 2112 (i.e., the cross direction); the cylindrical boss 2123 and the movable limiting body 2122 are located in the limiting structure 2111, and the diameter of the cylindrical boss 2123 is smaller than the width of the circular connection part of the limiting structure 2111, and the diameter of the cylindrical boss 2123 is larger than the width of the guide groove 2112. A threaded hole 21211 connected to the fastening threaded column 2121 is set in the middle of the end face of the cylindrical boss 2123. The load screw 31 is inserted into the cylindrical boss 2123 through the threaded hole 21211 and pushes the outer peripheral side of the movable limiting body 2122 to the outer peripheral side 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 point of the limiting structure 2111, and the embedded block 212 is limited along the end face shape direction of the guide rail groove 2112.

[0046] In one embodiment, a slot hole having a diameter smaller than that of the load screw 31 is provided on one side of the movable limiting body 2122 close to the center of the circle, so as to facilitate the load screw 31 to push out the movable limiting bodies 2122 on both sides.

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

[0048] In one embodiment, a plurality of guide rail grooves 2112 are provided 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 cabin 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 embedded bus 22 of the universal thermal control information structure board 2 is connected with multiple electrical connectors of different types of satellite payloads 3. The embedded block 212 of the 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 embedded block 212, the movable limiter 2122 is pushed out, and the embedded block 212 is limited 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 transmits it to the heat dissipation surface of the platform cabin 1 through the 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 a satellite payload 3. The universal thermal control information structure board 2 mainly provides flexible mechanical, electrical and thermal interfaces to achieve the loading 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 is composed of a pre-embedded bus 22, a pre-embedded hole 21 and a thermal control component 23. The pre-embedded bus 22 is composed of pre-embedded electrical connectors of different models to achieve flexible electrical connection configuration; the pre-embedded hole 21 realizes a flexible mechanical interface configuration; the thermal control component 23 is composed of a graphene thermal conductive film 231 and a pre-embedded heat pipe 232, wherein the graphene thermal conductive film 231 is laid flat on the load installation surface of the universal thermal control information structure board 2, and has the ability to evenly conduct heat on the entire board surface. The pre-embedded heat pipe 232 is evenly installed inside the universal thermal control information structure board 2, pulling the heat of the graphene thermal conductive film 231 to the heat dissipation surface of the platform cabin 1, playing a role of flexible thermal control.

[0055] like Figure 3-5As shown, the embedded hole 21 is composed of a sliding fixed guide rail 211 and an embedded block 212, wherein the sliding fixed guide rail 211 adopts a cross-shaped configuration to provide a space for the embedded block 212 to move and adjust on two axes; the embedded block 212 is installed on the guide 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 is composed of a limiting structure 2111 and a guide groove 2112, wherein the limiting structure 2111 is set to 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 groove 2112, which can ensure that multiple positions in the guide groove 2112 have a fixed limiting function. The guide groove 2112 is a hollow cross-shaped structure, which allows the fastening threaded column 2121 to move arbitrarily in the guide groove 2112. The embedded block 212 is composed of a fastening threaded column 2121 and a movable limiting body 2122. The fastening threaded column 2121 is provided with a threaded hole 21211 for connecting with the load screw 31. There are cylindrical bosses 2123 at both ends of the fastening threaded column 2121, which can play a role of upper and lower restrictions after the sliding fixed guide rail 211 is installed. The cylindrical boss 2123 has a hollow structure inside for installing the movable limiting body 2122. The movable limiting body 2122 is a combination of a semicircle and a cube. The radius of the semicircle is consistent with the cylindrical boss 2123. A semicircular slot is provided at the center end of the cylindrical boss 2123, which is installed in the hollow structure of the cylindrical boss. Inside a cylindrical boss 2123, there are two movable limiting bodies 2122 for use.

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

[0057] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0058] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A universal satellite configuration suitable for multiple types of payloads, characterized in that: include: A platform cabin (1), a universal thermal control information structure board (2), and a satellite payload (3); A universal thermal control information structure board (2) is arranged on the platform cabin (1), and the satellite payload (3) is connected to the universal thermal control information structure board (2); The universal thermal control information structure plate (2) is provided with pre-buried holes (21) for adapting to different types of satellite payloads (3), a pre-buried bus (22) and a thermal control component (23).

2. The universal satellite configuration applicable to multiple types of payloads according to claim 1, characterized in that: The embedded hole (21) comprises: a sliding fixed guide rail (211) and an embedded block (212) moving along the sliding fixed guide rail (211); The sliding fixed guide rail (211) is provided with a limiting structure (2111), and the 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 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).

3. The universal satellite configuration applicable to multiple types of payloads according to claim 2, characterized in that: The sliding fixed guide rail (211) comprises: 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 along both sides of the end surface shape of the guide rail groove (2112); The two sides of the limiting structures (2111) facing each other are arranged in a wave shape and form a plurality of circular connected shapes as a whole.

4. The universal satellite configuration applicable to multiple types of payloads according to claim 3, characterized in that: The embedded block (212) comprises: a fastening threaded column (2121), a movable limiting body (2122) and a cylindrical boss (2123); The fastening threaded column (2121) is provided with cylindrical bosses (2123) at both ends, and the cylindrical bosses (2123) are provided with grooves on the circumferential side for accommodating two semicircular movable limiting bodies (2122). When the movable limiting bodies (2122) are completely accommodated in the cylindrical bosses (2123), the outer circumferential side of the movable limiting bodies (2122) does not protrude from the circumferential side of the cylindrical bosses (2123).

5. The universal satellite configuration applicable to multiple types of payloads according to claim 4, characterized in that: The fastening threaded column (2121) is installed in the guide rail groove (2112) along the depth direction of the guide rail groove (2112), and the fastening threaded column (2121) is allowed to move along the end surface shape direction of the guide rail groove (2112); 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 point of the limiting structure (2111); and the diameter of the cylindrical boss (2123) is larger than the width of the guide rail groove (2112).

6. The universal satellite configuration applicable to multiple types of payloads according to claim 4, characterized in that: A threaded hole (21211) connected to the fastening threaded column (2121) is provided in the middle of the end surface of the cylindrical boss (2123); the load screw (31) is inserted into the cylindrical boss (2123) through the threaded hole (21211) and pushes the outer peripheral side of the movable limiting body (2122) to the outer peripheral side of the protruding cylindrical boss (2123); When the movable limiting body (2122) is ejected, the maximum diameter formed by the two movable limiting bodies (2122) is greater than the width of the circular connection point of the limiting structure (2111), and the embedded block (212) is limited along the end surface shape direction of the guide rail groove (2112).

7. The universal satellite configuration applicable to multiple types of payloads according to claim 4, characterized in that: The movable limiting body (2122) is provided with a slot hole having a diameter smaller than that of the load screw (31) on one side close to the center of the circle.

8. The universal satellite configuration applicable to multiple types of payloads according to claim 3, characterized in that: The end surface shape of the guide rail groove (2112) is set to be a cross shape or an X shape; The guide rail grooves (2112) are provided in plurality and arranged in an array.

9. The universal satellite configuration applicable to multiple types of payloads according to claim 1, characterized in that: The electrical connectors of a plurality of different types of satellite payloads (3) are connected via the pre-buried bus (22).

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

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