Cubesat attitude control bracket assembly and cubesat attitude control system

Abstract

This application relates to the field of aerospace technology, specifically to a cubic star attitude control bracket assembly and a cubic star attitude control system. The assembly includes a first bracket and a second bracket. The first bracket includes a first substrate and a first mounting plate vertically fixed to the first substrate. The second bracket includes a second substrate disposed parallel to the first substrate. The first mounting plate is fixedly connected to the second bracket to form an attitude control component accommodating space between the first substrate and the second substrate. The first substrate, the first mounting plate, and the second substrate are all used to mount the attitude control component. The purpose of this application is to address at least one technical problem mentioned in the background art by providing a cubic star attitude control bracket assembly and a cubic star attitude control system.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and more specifically, to a cubic star attitude control bracket assembly and a cubic star attitude control system. Background Technology

[0002] The attitude control system of a spacecraft is a crucial component ensuring its stability and precise orientation in space. The attitude control subsystem consists of three parts: measurement components, actuation components, and a controller module. Measurement components include digital sun sensors, magnetometers, MEMS gyroscopes, and star sensors; actuation components include reaction wheels and magnetic torque converters; and the controller module includes the onboard computer and its application software.

[0003] The attitude control subsystem works by collecting measurement signals from various measuring components and track measurement information provided by the GPS receiver, combining them with the outputs of other systems, designing control signals according to the controller module, and then sending control commands to the actuators to generate corresponding control torques.

[0004] CubeSats utilize commercially available components and standard, modular designs, resulting in low cost, high functional density, and short development cycles, making scientific research and technological development possible for more people. CubeSats are micro-nano satellites that adopt internationally accepted standards. The basic unit for CubeSats is U (Unit), with 1U having a volume of 10cm × 10cm × 10cm. Depending on mission requirements, CubeSats can be expanded to 2U (10cm × 10cm × 20cm), 3U, or even 16U or larger.

[0005] Due to the regular shape and limited space of CubeSats, higher requirements are placed on the installation of individual units inside and outside the satellite. This makes it urgent to solve the problem of how to reduce the space occupied by the attitude control system on the CubeSat. Summary of the Invention

[0006] The purpose of this application is to provide a cubic star attitude control bracket assembly and a cubic star attitude control system in response to at least one of the technical problems involved in the background art.

[0007] To achieve the above objectives, this application adopts the following technical solution:

[0008] One aspect of this application provides a cubic star attitude control support assembly, including a first support and a second support. The first support includes a first substrate and a first mounting plate vertically fixed to the first substrate. The second support includes a second substrate disposed parallel to the first substrate. The first mounting plate is fixedly connected to the second support to form an attitude control component receiving space between the first substrate and the second substrate. The first substrate, the first mounting plate, and the second substrate are all used to mount the attitude control component.

[0009] Optionally, the second bracket includes a second mounting plate, which is vertically fixed to the second base plate and disposed parallel to the first mounting plate. One end of the second mounting plate away from the second base plate is detachably fixed to one end of the first mounting plate away from the first base plate. The second mounting plate is used to mount the attitude control component.

[0010] The beneficial effects of this technical solution are as follows: In this way, the size of the attitude control component accommodating space is expanded in the direction perpendicular to the first mounting plate, so that both the first mounting plate and the second mounting plate can be used to install the attitude control component. The attitude control component can be distributed in multiple layers in the attitude control component accommodating space, which can better reduce the space occupied by the attitude control component on the CubeSat compared to fixing the attitude control component separately to the surface of the CubeSat.

[0011] Optionally, a first L-shaped positioning groove is formed on the first mounting plate, the first L-shaped positioning groove is disposed close to the second mounting plate, and a positioning protrusion is provided on the second mounting plate, the positioning protrusion being positioned and engaged with the first L-shaped positioning groove.

[0012] The beneficial effect of this technical solution is that, when connecting the first mounting plate and the second mounting plate, positioning can be achieved first through the first L-shaped positioning groove and the positioning protrusion, thereby improving the assembly efficiency of the cubic star attitude control bracket assembly.

[0013] Optionally, the first bracket further includes a third mounting plate, wherein the first base plate, the first mounting plate and the third mounting plate are perpendicularly connected to each other, and the third mounting plate is used to mount the attitude control component.

[0014] The beneficial effects of this technical solution are: by setting a third mounting plate, more installation positions can be provided for the attitude control components, making it easier for the attitude control components to be centrally arranged in the attitude control component housing space, thereby reducing the space occupied by the attitude control components on the CubeSat.

[0015] Optionally, the cubic star attitude control bracket assembly provided in this application further includes a star-sensor bracket, one end of which is fixed to the second substrate, and the other end of which is fixed to the end of the third mounting plate away from the first substrate.

[0016] The beneficial effects of this technical solution are as follows: that is, the star sensor bracket is used to install the star sensor. By setting up the star sensor bracket to install the star sensor, it is convenient to make targeted arrangements for the structure of the star sensor. In turn, it is convenient to reduce the size and space occupied on the CubeSat by integrating the attitude control system with the cubic star attitude control bracket assembly.

[0017] Optionally, the attitude control component accommodating space includes a first accommodating space, a second accommodating space, and a third accommodating space. In a direction perpendicular to the first mounting plate, the first accommodating space and the second accommodating space are respectively located on both sides of the first mounting plate, and in a direction perpendicular to the second mounting plate, the first accommodating space and the third accommodating space are respectively located on both sides of the second mounting plate.

[0018] The beneficial effects of this technical solution are as follows: In this way, both sides of the first mounting plate, both sides of the second mounting plate, and both sides of the third mounting plate can be used to install and accommodate the attitude control components, thereby improving the installation and accommodation capacity of the CubeSat attitude control support assembly for the attitude control components, and thus reducing the space occupied by the attitude control components on the CubeSat.

[0019] Optionally, the star sensor bracket has a mounting surface and a through hole. The mounting surface is inclined relative to a first direction and faces the first accommodating space. The through hole penetrates the star sensor bracket in a direction perpendicular to the mounting surface. The first direction is perpendicular to the third mounting plate.

[0020] The beneficial effect of this technical solution is that the star sensor can be inserted into the through hole and installed on the mounting surface.

[0021] Optionally, a second L-shaped positioning groove is provided at the top of the star sensor bracket, the opening of the second L-shaped positioning groove is facing the third receiving space, and the bottom end of the third mounting plate cooperates with the second L-shaped positioning groove.

[0022] The beneficial effect of this technical solution is that, when the star sensor bracket is fixedly connected to the third mounting plate, the positioning between the star sensor bracket and the third mounting plate can be achieved by the cooperation of the third mounting plate and the second L-shaped positioning groove, which facilitates the assembly of the cubic star attitude control bracket assembly.

[0023] Optionally, the cubic star attitude control bracket assembly provided in this application further includes a cable bracket, the cable bracket including an L-shaped plate and a plurality of cable mounting seats detachably mounted on the L-shaped plate, each of the cable mounting seats being distributed in the extending direction of the L-shaped plate to clamp the cable between the cable mounting seat and the L-shaped plate, one end of the L-shaped plate being fixed to the end of the first mounting plate away from the third mounting plate, and the other end of the L-shaped plate being fixed to the end of the third mounting plate away from the first mounting plate.

[0024] The beneficial effect of this technical solution is that it allows the wiring of each instrument to be fixed on the cable bracket, which facilitates a more reasonable arrangement of the wiring of each instrument in the attitude control component.

[0025] Another aspect of this application provides a cubic star attitude control system including an attitude control component and the cubic star attitude control support component provided in this application.

[0026] The attitude control component includes a star sensor, a gyroscope, a first flywheel, a second flywheel, a third flywheel, a magnetometer, and a magnetic torque converter.

[0027] The second bracket includes a second mounting plate, and the first bracket further includes a third mounting plate. The cubic star attitude control bracket assembly also includes a star sensor bracket and a cable bracket. The attitude control component accommodating space includes a first accommodating space, a second accommodating space, and a third accommodating space.

[0028] Both the star sensor and the first flywheel are located within the first accommodating space. The star sensor is mounted on the star sensor bracket, and the first flywheel is fixed to the first substrate.

[0029] The magnetometer, the second flywheel, and the gyroscope are all located within the second accommodating space. The magnetometer is fixed to the first mounting plate, and the second flywheel and gyroscope are both mounted on the second mounting plate. The arrangement direction of the second flywheel and the gyroscope is parallel to both the second mounting plate and the second base plate.

[0030] The third flywheel is located in the third receiving space and is mounted on the third mounting plate.

[0031] The magnetic torque device is mounted on the first substrate, and the magnetic torque device is located on the side of the first substrate opposite to the first accommodating space.

[0032] The technical solution provided in this application can achieve at least one of the following beneficial effects:

[0033] The cubic star attitude control bracket assembly and cubic star attitude control system provided in this application, when in use, have the attitude control components centrally installed in the attitude control component accommodating space formed between the first substrate and the second substrate. Then, the cubic star attitude control bracket assembly and the attitude control components installed on the cubic star attitude control bracket assembly are fixed as a whole on the cubic star. The first substrate, the second substrate, and the first mounting plate are all used to install the attitude control components. Compared with dispersing the attitude control components around the cubic star, it can effectively reduce the space occupied by the attitude control components on the cubic star.

[0034] The additional technical features and advantages of this application will become more apparent from the following description or from practical application. Attached Figure Description

[0035] To more clearly illustrate the technical solutions of the specific embodiments of this application, the accompanying drawings used in the description of the specific embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0036] Figure 1 A three-dimensional structural diagram of one angle of an embodiment of the cubic star attitude control system provided in this application;

[0037] Figure 2 A three-dimensional structural schematic diagram from another angle of one embodiment of the cubic star attitude control system provided in this application;

[0038] Figure 3 An exploded structural diagram of one embodiment of the cubic star attitude control system provided in this application;

[0039] Figure 4 An exploded structural diagram of one embodiment of the cubic star attitude control support assembly provided in this application;

[0040] Figure 5 A three-dimensional structural schematic diagram of one embodiment of the second support provided in this application;

[0041] Figure 6 A three-dimensional structural diagram of one angle of an embodiment of the first support provided in this application;

[0042] Figure 7 A three-dimensional structural schematic diagram from another angle of one embodiment of the first support provided in this application;

[0043] Figure 8 A three-dimensional structural diagram of one embodiment of the star-sensor bracket provided in this application.

[0044] Figure 9 A three-dimensional structural schematic diagram from another angle of one embodiment of the star-sensor bracket provided in this application;

[0045] Figure 10 An exploded structural diagram of one embodiment of the cable bracket provided in this application;

[0046] Figure 11 An exploded structural diagram of one embodiment of the cubic star attitude control support assembly provided in this application;

[0047] Figure 12 An exploded structural diagram of one embodiment of the cubic star attitude control system provided in this application;

[0048] Figure 13 A partial structural schematic diagram of one embodiment of the cubic star attitude control system provided in this application;

[0049] Figure 14 A partial structural schematic diagram of one embodiment of the cubic star attitude control system provided in this application;

[0050] Figure 15 A partial structural schematic diagram of one embodiment of the cubic star attitude control system provided in this application;

[0051] Figure 16 A three-dimensional structural schematic diagram of a third angle of an embodiment of the cubic star attitude control system provided in this application;

[0052] Figure 17 This is a three-dimensional structural diagram of a fourth angle of one embodiment of the cubic star attitude control system provided in this application.

[0053] Figure label:

[0054] 1. Cubic star attitude control bracket assembly; 2. Star sensor; 3. Gyroscope; 4. First flywheel; 5. Magnetometer; 6. Magnetic torque generator; 11. Second bracket; 12. First bracket; 13. Star sensor bracket; 14. Cable bracket; 15. Cable mounting base; 16. Second flywheel; 17. Third flywheel; 111. Second external interface; 112. Star sensor interface; 113. Second flywheel interface; 114. Gyroscope interface; 115. First mounting plate interface; 116. Second base plate; 121 121. First flywheel interface; 122. Magnetic torquer interface; 123. Third flywheel interface; 124. Second mounting plate interface; 125. Cable bracket interface; 126. Star sensor bracket interface; 127. Satellite docking interface; 128. Magnetometer interface; 129. First base plate; 12a. Third mounting plate; 12b. First mounting plate; 131. Star sensor interface; 132. Second bracket interface; 133. Third mounting plate interface; 141. Connection interface; 142. Mounting base interface. Detailed Implementation

[0055] The technical solutions of this application will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0056] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used 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. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0057] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0058] like Figures 1 to 17 As shown, one aspect of this application provides a cubic star attitude control support assembly 1, including a first support 12 and a second support 11. The first support 12 includes a first substrate 129 and a first mounting plate 12b vertically fixed to the first substrate 129. The second support 11 includes a second substrate 116 arranged parallel to the first substrate 129. The first mounting plate 12b is fixedly connected to the second support 11 to form an attitude control component receiving space between the first substrate 129 and the second substrate 116. The first substrate 129, the first mounting plate 12b, and the second substrate 116 are all used to mount attitude control components.

[0059] The CubeSat attitude control support assembly 1 provided in this application, when in use, centrally installs the attitude control components within the attitude control component accommodating space formed between the first substrate 129 and the second substrate 116. Then, the CubeSat attitude control support assembly 1 and the attitude control components installed on the CubeSat attitude control support assembly 1 are fixed as a whole on the CubeSat. The first substrate 129, the second substrate 116, and the first mounting plate 12b are all used to install the attitude control components. Compared with dispersing the attitude control components around the CubeSat, this can effectively reduce the space occupied by the attitude control components on the CubeSat. Furthermore, the attitude control system is an integrated whole formed by the attitude control components and the CubeSat attitude control support assembly 1. Compared with installing each component of the attitude control components independently on the CubeSat, installing the above-mentioned whole on the CubeSat simplifies the interface with the satellite.

[0060] Optionally, the second bracket 11 includes a second mounting plate 118, which is vertically fixed to the second substrate 116 and parallel to the first mounting plate 12b. One end of the second mounting plate 118 away from the second substrate 116 is detachably fixed to the end of the first mounting plate 12b away from the first substrate 129. The second mounting plate 118 is used to mount the attitude control component. This expands the size of the attitude control component accommodating space in the direction perpendicular to the first mounting plate 12b, allowing both the first mounting plate 12b and the second mounting plate 118 to mount the attitude control component. The attitude control component can be distributed in multiple layers within the accommodating space, which better reduces the space occupied by the attitude control component on the CubeSat compared to fixing the attitude control component separately to the CubeSat surface.

[0061] Optionally, a first L-shaped positioning groove is formed on the first mounting plate 12b, and the first L-shaped positioning groove is located close to the second mounting plate 118. A positioning protrusion is provided on the second mounting plate 118, and the positioning protrusion engages with the first L-shaped positioning groove. In this way, when connecting the first mounting plate 12b and the second mounting plate 118, positioning can be performed first through the first L-shaped positioning groove and the positioning protrusion, thereby improving the assembly efficiency of the cubic star attitude control bracket assembly 1. Preferably, a first mounting plate interface 115 is formed on the positioning protrusion of the second mounting plate 118, and a second mounting plate interface 124 is formed on the inner wall of the first L-shaped positioning groove. The first mounting plate interface 115 is connected to the second mounting plate interface 124 by bolts, thereby realizing the connection between the first mounting plate 12b and the second mounting plate 118.

[0062] Optionally, the first bracket 12 further includes a third mounting plate. The first base plate 129, the first mounting plate 12b, and the third mounting plate 12a are perpendicularly connected to each other in pairs. The third mounting plate 12a is used to mount the attitude control components. By setting the third mounting plate 12a, more mounting positions can be provided for the attitude control components, making it easier to centrally arrange the attitude control components in the attitude control component accommodating space, thereby reducing the space occupied by the attitude control components on the CubeSat.

[0063] Optionally, the cubic star attitude control bracket assembly 1 provided in this application embodiment further includes a star sensor bracket 13. One end of the star sensor bracket 13 is fixed to the second substrate 116, and the other end of the star sensor bracket 13 is fixed to the end of the third mounting plate 12a away from the first substrate 129. That is, the star sensor bracket 13 is used to install the star sensor 2. By setting the star sensor bracket 13 specifically to install the star sensor 2, it is convenient to make targeted arrangements for the structure of the star sensor 2, thereby facilitating the reduction of the size and space occupied on the cubic star by integrating the attitude control system of the cubic star attitude control bracket assembly 1 into one unit.

[0064] Optionally, the attitude control component accommodating space includes a first accommodating space, a second accommodating space, and a third accommodating space. The first and second accommodating spaces are located on opposite sides of the first mounting plate 12b in a direction perpendicular to the first mounting plate 12b, and on opposite sides of the second mounting plate 118 in a direction perpendicular to the second mounting plate 118. Thus, both sides of the first mounting plate 12b, both sides of the second mounting plate 118, and both sides of the third mounting plate 12a can be used to install and accommodate the attitude control component, improving the CubeSat attitude control support assembly 1's ability to install and accommodate the attitude control component, thereby reducing the space occupied by the attitude control component on the CubeSat.

[0065] Optionally, the star sensor bracket 13 has a mounting surface and a through hole. The mounting surface is inclined relative to a first direction and faces the first receiving space. The through hole penetrates the star sensor bracket 13 in a direction perpendicular to the mounting surface, and the first direction is perpendicular to the third mounting plate 12a. In this way, the star sensor 2 can extend into the through hole and be mounted on the mounting surface.

[0066] Optionally, a second L-shaped positioning groove is provided at the top of the star-sensor bracket 13, with the opening of the second L-shaped positioning groove facing the third receiving space. The bottom end of the third mounting plate 12a mates with the second L-shaped positioning groove. Thus, when the star-sensor bracket 13 and the third mounting plate 12a are fixedly connected, the positioning between the star-sensor bracket 13 and the third mounting plate 12a can be achieved by the engagement of the third mounting plate 12a with the second L-shaped positioning groove, thereby facilitating the assembly of the cubic star attitude control bracket assembly 1. Preferably, a second bracket interface 132 is formed on the groove wall of the second L-shaped positioning groove, and a through hole is formed on the third mounting plate 12a. A bolt is passed through the through hole and connected to the second bracket interface 132 to achieve a fixed connection between the star-sensor bracket 13 and the third mounting plate 12a.

[0067] Optionally, the cubic star attitude control support assembly 1 provided in this application embodiment further includes a cable bracket 14. The cable bracket 14 includes an L-shaped plate and a plurality of cable mounting seats 15 detachably mounted on the L-shaped plate. Each cable mounting seat 15 is distributed in the extending direction of the L-shaped plate to clamp the cable between the cable mounting seat 15 and the L-shaped plate. One end of the L-shaped plate is fixed to the end of the first mounting plate 12b away from the third mounting plate 12a, and the other end of the L-shaped plate is fixed to the end of the third mounting plate 12a away from the first mounting plate 12b. In this way, the wiring of each instrument can be fixed on the cable bracket 14, which facilitates a more reasonable arrangement of the wiring of each instrument in the attitude control assembly. Preferably, mounting portions are provided at both ends of the L-shaped plate, and through holes are formed in the mounting portions. Threaded holes are provided on both the first mounting plate 12b and the third mounting plate 12a. The through holes on the mounting portions at both ends of the L-shaped plate are connected to the threaded holes on the first mounting plate 12b and the threaded holes on the third mounting plate 12a respectively by bolts. The cable mounting base 15 is preferably plate-shaped.

[0068] like Figures 1 to 3 ,as well as Figures 12 to 17 Another aspect of this application provides a cubic star attitude control system, including an attitude control component and a cubic star attitude control support assembly 1 provided in the embodiments of this application.

[0069] The attitude control assembly includes a star sensor 2, a gyroscope 3, a first flywheel 4, a second flywheel 16, a third flywheel 17, a magnetometer 5, and a magnetic torque converter 6.

[0070] The second bracket 11 includes a second mounting plate 118, and the first bracket 12 also includes a third mounting plate 12a. The cubic star attitude control bracket assembly 1 also includes a star sensor bracket 13 and a cable bracket 14. The attitude control assembly accommodating space includes a first accommodating space, a second accommodating space, and a third accommodating space.

[0071] Both the star sensor 2 and the first flywheel 4 are located within the first accommodating space. The star sensor 2 is mounted on the star sensor bracket 13, and the first flywheel 4 is fixed to the first substrate 129.

[0072] The magnetometer 5, the second flywheel 16, and the gyroscope 3 are all located within the second accommodating space. The magnetometer 5 is fixed to the first mounting plate 12b, and the second flywheel 16 and the gyroscope 3 are both mounted on the second mounting plate 118. The arrangement direction of the second flywheel 16 and the gyroscope 3 is parallel to both the second mounting plate 118 and the second base plate 116.

[0073] The third flywheel 17 is located in the third receiving space and is mounted on the third mounting plate 12a.

[0074] The magnetic torque device 6 is mounted on the first substrate 129, and the magnetic torque device 6 is located on the side of the first substrate 129 opposite to the first accommodating space.

[0075] In this embodiment, the gyroscope 3 is preferably a MEMS gyroscope.

[0076] The CubeSat attitude control support assembly 1 provided in this application, when in use, centrally installs the attitude control components within the attitude control component accommodating space formed between the first substrate 129 and the second substrate 116. Then, the CubeSat attitude control support assembly 1 and the attitude control components installed on the CubeSat attitude control support assembly 1 are fixed as a whole on the CubeSat. The first substrate 129, the second substrate 116, and the first mounting plate 12b are all used to install the attitude control components. Compared with dispersing the attitude control components around the CubeSat, this can effectively reduce the space occupied by the attitude control components on the CubeSat. Furthermore, the attitude control system is an integrated whole formed by the attitude control components and the CubeSat attitude control support assembly 1. Compared with installing each component of the attitude control components independently on the CubeSat, installing the above-mentioned whole on the CubeSat simplifies the interface with the satellite.

[0077] The cubic star attitude control system provided in this application adopts the cubic star attitude control bracket assembly 1 provided in this application. The internal layout of the entire cubic star attitude control system is reasonable, reducing the space occupied on the CubeSat. The measurement and execution components of the entire cubic star attitude control system are integrated as a whole module and interface with the satellite. The attitude control subsystem is assembled and tested on the ground and then installed as a whole on the satellite, simplifying the interface with the satellite. The cubic star attitude control bracket assembly 1, as the main load-bearing structure, is integrally machined from aluminum alloy, which meets the installation requirements of various instruments and ensures the transmission of internal and external forces of the components. The bracket has weight-reducing holes and reinforcing ribs distributed inside, and wiring paths are left in reasonable positions on the bracket to facilitate the wiring connection of various instruments.

[0078] In this embodiment, preferably, the first flywheel 4, the second flywheel 16, and the third flywheel 17 are orthogonally installed, coinciding with the X, Y, and Z directions of the entire satellite, respectively. Except for the magnetic torque device 6, all other equipment is located within the maximum outer envelope of the cubic star attitude control support assembly 1, which provides some protection for the attitude control assembly. The equipment on the attitude control assembly module is compactly installed, has a relatively regular shape, and occupies a relatively regular space within the satellite.

[0079] In this embodiment, preferably, the second bracket 11 has a T-shaped structure. The second bracket 11 has multiple external interfaces. The second base plate 116 has four diagonally distributed satellite interfaces for docking with satellites. The star sensor bracket 13 has a star sensor interface 112. The second mounting plate 118 has a second flywheel interface 113 and a gyroscope interface 114. A first mounting plate interface 115 is formed on the positioning protrusion of the second mounting plate 118. The first bracket 12 is composed of mutually perpendicular... The first base plate 129, the first mounting plate 12b, and the third mounting plate 12a constitute a structure with high rigidity. The inner surface of the first base plate 129 is provided with a first flywheel interface 121, and the outer surface is provided with a magnetic torque converter interface 122. The first mounting plate 12b is provided with a magnetometer interface 128. The outer surface of the third mounting plate 12a is provided with a third flywheel interface 123, a cable bracket interface 125, a star-sensor bracket interface 126, and a satellite docking interface 127. The star-sensor bracket 13 is a closed frame structure with a mounting surface angle of... The angle is the specific angle required after attitude control analysis. It has a star sensor interface 131 at the top, a second bracket interface 132 at the bottom, and a third mounting plate interface 133 at the top of the star sensor bracket 13. The L-shaped plate is formed by bending sheet metal, with connection interfaces 141 at both ends. Multiple mounting base interfaces 142 are provided on the L-shaped plate, and cable mounting bases 15 are detachably installed on the mounting base interfaces 142. The cubic star attitude control bracket assembly 1 is externally connected to the satellite, mainly through 8 screws, and has second external interfaces on the 4 second brackets 11. The first external interface 127 on the 111 and the four first brackets 12; the cubic star attitude control system provided in this application, during assembly, firstly assembles the second bracket 11, the star sensor bracket 13 and the star sensor 2 into one unit, and assembles the first bracket 12 and the first flywheel 4 into one unit, then assembles the second bracket 11, the first bracket 12 and the star sensor bracket 13 into one unit, and installs the gyroscope 3, the second flywheel 16, the third flywheel 17, the magnetometer 5 and the magnetic torque device 6 in the corresponding positions on the periphery; finally, the cable bracket 14 and the cable mounting base 15 are installed.

[0080] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application.

Claims

1. A cubic star attitude control bracket assembly, characterized in that, The system includes a first support and a second support. The first support includes a first substrate and a first mounting plate that is vertically fixed to the first substrate. The second support includes a second substrate that is parallel to the first substrate. The first mounting plate is fixedly connected to the second support to form a space for accommodating the attitude control component between the first substrate and the second substrate. The first substrate, the first mounting plate, and the second substrate are all used to mount the attitude control component. The second bracket includes a second mounting plate, which is vertically fixed to the second base plate and is arranged parallel to the first mounting plate. One end of the second mounting plate away from the second base plate is detachably fixed to one end of the first mounting plate away from the first base plate. The second mounting plate is used to mount the attitude control component. A first L-shaped positioning groove is formed on the first mounting plate, and the first L-shaped positioning groove is located close to the second mounting plate. A positioning protrusion is provided on the second mounting plate, and the positioning protrusion is positioned and engaged with the first L-shaped positioning groove.

2. The cubic star attitude control support assembly according to claim 1, characterized in that, The first bracket also includes a third mounting plate. The first base plate, the first mounting plate and the third mounting plate are perpendicularly connected to each other. The third mounting plate is used to mount the attitude control component.

3. The cubic star attitude control support assembly according to claim 2, characterized in that, It also includes a star-sensor bracket, one end of which is fixed to the second substrate, and the other end of which is fixed to the end of the third mounting plate away from the first substrate.

4. The cubic star attitude control support assembly according to claim 3, characterized in that, The attitude control component accommodating space includes a first accommodating space, a second accommodating space, and a third accommodating space. In a direction perpendicular to the first mounting plate, the first accommodating space and the second accommodating space are respectively located on both sides of the first mounting plate. In a direction perpendicular to the second mounting plate, the first accommodating space and the third accommodating space are respectively located on both sides of the second mounting plate.

5. The cubic star attitude control support assembly according to claim 4, characterized in that, The star sensor bracket has a mounting surface and a through hole. The mounting surface is inclined relative to a first direction and faces the first accommodating space. The through hole penetrates the star sensor bracket in a direction perpendicular to the mounting surface. The first direction is perpendicular to the third mounting plate.

6. The cubic star attitude control support assembly according to claim 5, characterized in that, A second L-shaped positioning groove is provided at the top of the star sensor bracket, the opening of the second L-shaped positioning groove faces the third receiving space, and the bottom end of the third mounting plate cooperates with the second L-shaped positioning groove.

7. The cubic star attitude control support assembly according to any one of claims 2 to 6, characterized in that, It also includes a cable bracket, which includes an L-shaped plate and a plurality of cable mounting seats detachably mounted on the L-shaped plate. Each of the cable mounting seats is distributed in the extension direction of the L-shaped plate to clamp the cable between the cable mounting seat and the L-shaped plate. One end of the L-shaped plate is fixed to the end of the first mounting plate away from the third mounting plate, and the other end of the L-shaped plate is fixed to the end of the third mounting plate away from the first mounting plate.

8. A cubic star attitude control system, characterized in that, Includes an attitude control component and a cubic star attitude control support assembly as described in any one of claims 1 to 7. The attitude control component includes a star sensor, a gyroscope, a first flywheel, a second flywheel, a third flywheel, a magnetometer, and a magnetic torque converter. The second bracket includes a second mounting plate, and the first bracket further includes a third mounting plate. The cubic star attitude control bracket assembly also includes a star sensor bracket and a cable bracket. The attitude control component accommodating space includes a first accommodating space, a second accommodating space, and a third accommodating space. Both the star sensor and the first flywheel are located within the first accommodating space. The star sensor is mounted on the star sensor bracket, and the first flywheel is fixed to the first substrate. The magnetometer, the second flywheel, and the gyroscope are all located within the second accommodating space. The magnetometer is fixed to the first mounting plate, and the second flywheel and gyroscope are both mounted on the second mounting plate. The arrangement direction of the second flywheel and the gyroscope is parallel to both the second mounting plate and the second base plate. The third flywheel is located in the third receiving space and is mounted on the third mounting plate. The magnetic torque device is mounted on the first substrate, and the magnetic torque device is located on the side of the first substrate opposite to the first accommodating space.

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