Cubesat attitude control support assembly and cubesat attitude control system

Abstract

The invention relates to the technical field of spaceflight, in particular to a cubesat attitude control support assembly and a cubesat attitude control system.The cubesat attitude control support assembly comprises a first support and a second support, and the first support comprises a first base plate and a first mounting plate perpendicularly fixed to the first base plate; the first support comprises a first substrate, the second support comprises a second substrate parallel to the first substrate, the first mounting plate is fixedly connected with the second support so as to form an attitude control assembly accommodating space between the first substrate and the second substrate, and the first substrate, the first mounting plate and the second substrate are all used for mounting attitude control assemblies. The invention aims to provide a cubesat attitude control bracket assembly and a cubesat attitude control system aiming at at least one technical problem related in the background technology.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a cubical satellite attitude control support assembly and a cubical satellite attitude control system. BACKGROUND

[0002] The attitude control system of a spacecraft is the key component to ensure the spacecraft to keep stable and accurately point to a specific direction in space. The attitude control subsystem is composed of three parts: measurement components, execution components and controller modules. The measurement components include digital sun sensors, magnetometers, MEMS gyroscopes and star sensors; the execution components include reaction flywheels and magnetic torque devices; the controller modules include on-board computers and their application software.

[0003] The working principle of the attitude control subsystem is to collect the measurement signals of various measurement components and the orbit measurement information provided by the GPS receiver, combine the outputs of other systems, design control signals according to the controller module, and then issue control instructions to the execution components to generate corresponding control torques.

[0004] The cubical satellite adopts commercial off-the-shelf components and standard, modular design, with low cost, high functional density and short development cycle, which provides the possibility for more people to carry out scientific research and technology development. The cubical satellite is a micro-nano satellite adopting international standard, with U (Unit) as the basic unit, and the volume of 1U is 10cmx10cmx10cm. According to the needs of the task, the cubical satellite can be expanded to 2U (10cmx10cmx20cm), 3U, even 16U or larger.

[0005] Due to the regular volume and limited space of the cubical satellite, higher requirements are put forward for the installation of the single machine inside and outside the satellite, which makes it an urgent problem to reduce the space occupied by the attitude control system on the cubical satellite. SUMMARY

[0006] The present application aims to solve at least one technical problem involved in the background art, and provides a cubical satellite attitude control support assembly and a cubical satellite attitude control system.

[0007] In order to achieve the above-mentioned purpose, the present application adopts the following technical solutions: One aspect of the present application provides a cubical satellite attitude control support assembly, comprising a first support and a second support, the first support comprising a first base plate and a first mounting plate fixed vertically to the first base plate, the second support comprising a second base plate arranged parallel to the first base plate, the first mounting plate being fixedly connected with the second support to form an attitude control assembly accommodating space between the first base plate and the second base plate, the first base plate, the first mounting plate and the second base plate being used for mounting attitude control assemblies.

[0008] Optionally, the second support comprises a second mounting plate, the second mounting plate is fixed perpendicularly to the second base plate, the second mounting plate is arranged parallel to the first mounting plate, and the end of the second mounting plate away from the second base plate is detachably fixed to the end of the first mounting plate away from the first base plate, and the second mounting plate is used for mounting the attitude control assembly.

[0009] The technical scheme has the beneficial effects that: in this way, the size of the attitude control assembly accommodating space is expanded in the direction perpendicular to the first mounting plate, the first mounting plate and the second mounting plate can both mount the attitude control assembly, the attitude control assembly can be distributed in multiple layers in the attitude control assembly accommodating space, and the space occupied by the attitude control assembly on the cubic star can be reduced better than when the attitude control assembly is fixed on the surface of the cubic star.

[0010] Optionally, a first L-shaped positioning groove is formed on the first mounting plate, the first L-shaped positioning groove is arranged close to the second mounting plate, and a positioning protrusion is arranged on the second mounting plate, and the positioning protrusion is positioned and matched with the first L-shaped positioning groove.

[0011] The technical scheme has the beneficial effects that: in this way, when the first mounting plate and the second mounting plate are connected, the first L-shaped positioning groove and the positioning protrusion can be positioned first, and the assembly efficiency of the cubic star attitude control support assembly is improved.

[0012] Optionally, the first support further comprises a third mounting plate, the first base plate, the first mounting plate and the third mounting plate are connected perpendicularly in pairs, and the third mounting plate is used for mounting the attitude control assembly.

[0013] The technical scheme has the beneficial effects that: by arranging the third mounting plate, more mounting positions can be provided for the attitude control assembly, the attitude control assembly can be arranged concentratedly in the attitude control assembly accommodating space, and the space occupied by the attitude control assembly on the cubic star can be reduced.

[0014] Optionally, the cubic star attitude control support assembly further comprises a star sensor support, one end of the star sensor support is fixed to the second base plate, and the other end of the star sensor support is fixed to the end of the third mounting plate away from the first base plate.

[0015] The technical scheme has the beneficial effects that: that is, the star sensor support is used for mounting the star sensor, by arranging the star sensor support to mount the star sensor specially, the structure of the star sensor can be arranged purposefully, and the volume of the attitude control system integrated by the cubic star attitude control support assembly and the space occupied on the cubic star can be reduced.

[0016] Optionally, the attitude control component accommodating space comprises a first accommodating space, a second accommodating space and a third accommodating space, the first accommodating space and the second accommodating space are respectively located on two sides of the first mounting plate in a direction perpendicular to the first mounting plate, and the first accommodating space and the third accommodating space are respectively located on two sides of the second mounting plate in a direction perpendicular to the second mounting plate.

[0017] The technical scheme has the beneficial effects that: in this way, the two sides of the first mounting plate, the two sides of the second mounting plate and the two sides of the third mounting plate can be used for mounting and accommodating the attitude control component, the mounting and accommodating capacity of the attitude control support component of the cubic star for the attitude control component is improved, and thus the space occupied by the attitude control component on the cubic star is reduced.

[0018] Optionally, the star sensor support is provided with a mounting surface and a through hole, the mounting surface is inclined relative to a first direction, the mounting surface is arranged to face the first accommodating space, the through hole penetrates the star sensor support in a direction perpendicular to the mounting surface, and the first direction is perpendicular to the third mounting plate.

[0019] The technical scheme has the beneficial effects that: in this way, the star sensor can extend into the through hole and be mounted on the mounting surface.

[0020] Optionally, a second L-shaped positioning groove is arranged at the top end of the star sensor support, the groove opening of the second L-shaped positioning groove is arranged to face the third accommodating space, and the bottom end of the third mounting plate is matched with the second L-shaped positioning groove.

[0021] The technical scheme has the beneficial effects that: in this way, when the star sensor support is fixedly connected with the third mounting plate, the positioning between the star sensor support and the third mounting plate can be realized by matching the third mounting plate with the second L-shaped positioning groove, and thus the cubic star attitude control support component is facilitated to be assembled.

[0022] Optionally, the cubic star attitude control support component provided in the application further comprises a cable support, the cable support comprises an L-shaped plate and a plurality of cable mounting seats which are detachably mounted on the L-shaped plate, the cable mounting seats are distributed in the extension direction of the L-shaped plate to clamp the cable between the cable mounting seats 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.

[0023] The technical scheme has the beneficial effects that: in this way, the lines of each instrument can be fixed on the cable support, and the lines of each instrument in the attitude control component are facilitated to be arranged more reasonably.

[0024] Another aspect of the present application provides a CubeSat attitude control system comprising an attitude control assembly and the CubeSat attitude control bracket assembly provided by the present application, The attitude control assembly comprises a star sensor, a gyroscope, a first flywheel, a second flywheel, a third flywheel, a magnetometer and a magnetic torque device, The second bracket comprises a second mounting plate, the first bracket further comprises a third mounting plate, the CubeSat attitude control bracket assembly further comprises a star sensor bracket and a cable bracket, the attitude control assembly accommodating space comprises a first accommodating space, a second accommodating space and a third accommodating space, The star sensor and the first flywheel are both located in the first accommodating space, the star sensor is mounted on the star sensor bracket, and the first flywheel is fixed on the first base plate, The magnetometer, the second flywheel and the gyroscope are all located in the second accommodating space, the magnetometer is fixed on the first mounting plate, the second flywheel and the gyroscope are both mounted on the second mounting plate, and the arrangement direction of the second flywheel and the gyroscope is parallel to the second mounting plate and the second base plate, The third flywheel is located in the third accommodating space, and the third flywheel is mounted on the third mounting plate, The magnetic torque device is mounted on the first base plate, and the magnetic torque device is located on the side of the first base plate away from the first accommodating space.

[0025] The technical scheme provided by the present application can achieve at least one of the following beneficial effects: The CubeSat attitude control bracket assembly and the CubeSat attitude control system provided by the present application can effectively reduce the space occupied by the attitude control assembly on the CubeSat.

[0026] The additional technical features and advantages of the present application will be more apparent in the following description, or can be understood by the specific practice of the present application. BRIEF DESCRIPTION OF DRAWINGS

[0027] In order to more clearly illustrate the technical scheme of the specific embodiments of the present application, the following will briefly introduce the drawings needed to be used in the description of the specific embodiments. Obviously, the drawings in the following description are some embodiments of the present application, and those skilled in the art can obtain other drawings according to these drawings without creating any creative labor.

[0028] Figure 1A perspective view of one embodiment of a cubic satellite attitude control system provided by an embodiment of the present application from one angle; Figure 2 A perspective view of one embodiment of a cubic satellite attitude control system provided by an embodiment of the present application from another angle; Figure 3 An exploded view of one embodiment of a cubic satellite attitude control system provided by an embodiment of the present application; Figure 4 An exploded view of one embodiment of a cubic satellite attitude control support assembly provided by an embodiment of the present application; Figure 5 A perspective view of one embodiment of a second support provided by an embodiment of the present application; Figure 6 A perspective view of one embodiment of a first support provided by an embodiment of the present application from one angle; Figure 7 A perspective view of one embodiment of a first support provided by an embodiment of the present application from another angle; Figure 8 A perspective view of one embodiment of a star sensor support provided by an embodiment of the present application from one angle; Figure 9 A perspective view of one embodiment of a star sensor support provided by an embodiment of the present application from another angle; Figure 10 An exploded view of one embodiment of a cable support provided by an embodiment of the present application; Figure 11 An exploded view of one embodiment of a cubic satellite attitude control support assembly provided by an embodiment of the present application; Figure 12 An exploded view of one embodiment of a cubic satellite attitude control system provided by an embodiment of the present application; Figure 13 A partial view of one embodiment of a cubic satellite attitude control system provided by an embodiment of the present application; Figure 14 A partial view of one embodiment of a cubic satellite attitude control system provided by an embodiment of the present application; Figure 15 A partial view of one embodiment of a cubic satellite attitude control system provided by an embodiment of the present application; Figure 16 A perspective view of one embodiment of a cubic satellite attitude control system provided by an embodiment of the present application from a third angle; Figure 17Fig. 4 is a perspective view of a fourth angle of an embodiment of a cubic satellite attitude control system provided by the present application.

[0029] Reference signs: 1, cubic satellite attitude control support assembly; 2, star sensor; 3, gyroscope; 4, first flywheel; 5, magnetometer; 6, magnetic torque device; 11, second support; 12, first support; 13, star sensor support; 14, cable support; 15, cable mounting seat; 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, first flywheel interface; 122, magnetic torque device interface; 123, third flywheel interface; 124, second mounting plate interface; 125, cable support interface; 126, star sensor support 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 support interface; 133, third mounting plate interface; 141, connecting interface; 142, mounting seat interface. DETAILED DESCRIPTION

[0030] The technical solutions of the present application will be described clearly and completely below in conjunction with the drawings. Obviously, the described embodiments are only some of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0031] In the description of the present application, it should be noted that the orientations or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", "third" are only for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0032] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the communication inside two elements. For those skilled in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0033] As Figures 1 to 17 shown in the drawings, one aspect of the present application provides a cubical satellite attitude control support assembly 1, comprising a first support 12 and a second support 11, the first support 12 comprising a first base plate 129 and a first mounting plate 12b fixed perpendicularly to the first base plate 129, the second support 11 comprising a second base plate 116 arranged in parallel with the first base plate 129, the first mounting plate 12b being fixedly connected with the second support 11 to form an attitude control assembly accommodating space between the first base plate 129 and the second base plate 116, the first base plate 129, the first mounting plate 12b and the second base plate 116 all being used for mounting attitude control assemblies.

[0034] The cubical satellite attitude control support assembly 1 provided by the present application, in use, concentrates the attitude control assemblies in the attitude control assembly accommodating space formed between the first base plate 129 and the second base plate 116, and then fixes the cubical satellite attitude control support assembly 1 and the attitude control assemblies mounted on the cubical satellite attitude control support assembly 1 as a whole on the cubical satellite, the first base plate 129, the second base plate 116 and the first mounting plate 12b are all used for mounting attitude control assemblies, which can effectively reduce the space occupied by the attitude control assemblies on the cubical satellite, compared with dispersing the attitude control assemblies around the cubical satellite; and the attitude control system is an integral whole integrated by the attitude control assemblies and the cubical satellite attitude control support assembly 1, which can simplify the interface with the satellite, compared with independently mounting each component of the attitude control assemblies on the cubical satellite and mounting the above integral whole on the cubical satellite.

[0035] Optionally, the second support 11 comprises a second mounting plate 118, the second mounting plate 118 being fixed perpendicularly to the second base plate 116, the second mounting plate 118 being arranged in parallel with the first mounting plate 12b, and the end of the second mounting plate 118 away from the second base plate 116 being detachably fixed to the end of the first mounting plate 12b away from the first base plate 129, the second mounting plate 118 being used for mounting the attitude control assemblies. In this way, the size of the attitude control assembly accommodating space is expanded in the direction perpendicular to the first mounting plate 12b, so that the first mounting plate 12b and the second mounting plate 118 can both mount attitude control assemblies, and the attitude control assemblies can be distributed in multiple layers in the attitude control assembly accommodating space, which can better reduce the space occupied by the attitude control assemblies on the cubical satellite, compared with fixing the attitude control assemblies on the surface of the cubical satellite respectively.

[0036] Optionally, a first L-shaped positioning groove is formed on the first mounting plate 12b, the first L-shaped positioning groove is arranged close to the second mounting plate 118, a positioning protrusion is arranged on the second mounting plate 118, and the positioning protrusion is positioned and matched with the first L-shaped positioning groove. In this way, when the first mounting plate 12b is connected with the second mounting plate 118, the first L-shaped positioning groove and the positioning protrusion can be positioned first, and then the assembly efficiency of the cubic star attitude control support assembly 1 is improved. Preferably, a first mounting plate interface 115 is formed on the positioning protrusion of the second mounting plate 118, 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 with the second mounting plate interface 124 through a bolt, and the connection between the first mounting plate 12b and the second mounting plate 118 is realized.

[0037] Optionally, the first support 12 further comprises a third mounting plate, the first base plate 129, the first mounting plate 12b and the third mounting plate 12a are connected with each other in pairs, and the third mounting plate 12a is used for mounting an attitude control assembly. By arranging the third mounting plate 12a, more mounting positions can be provided for the attitude control assembly, the attitude control assembly can be arranged in the attitude control assembly containing space in a concentrated manner, and then the space occupied by the attitude control assembly on the cubic star is reduced.

[0038] Optionally, the cubic star attitude control support assembly 1 provided in the embodiment of the application further comprises a star sensor support 13, one end of the star sensor support 13 is fixed to the second base plate 116, and the other end of the star sensor support 13 is fixed to one end of the third mounting plate 12a away from the first base plate 129. That is, the star sensor support 13 is used for mounting a star sensor 2, by arranging the star sensor support 13 to specially mount the star sensor 2, the structure of the star sensor 2 can be arranged in a targeted manner, and then the attitude control system integrated by the cubic star attitude control support assembly 1 can reduce the volume and the space occupied on the cubic star.

[0039] Optionally, the attitude control assembly containing space comprises a first containing space, a second containing space and a third containing space, the first containing space and the second containing space are respectively located on two sides of the first mounting plate 12b in a direction perpendicular to the first mounting plate 12b, and the first containing space and the third containing space are respectively located on two sides of the second mounting plate 118 in a direction perpendicular to the second mounting plate 118. In this way, the two sides of the first mounting plate 12b, the two sides of the second mounting plate 118 and the two sides of the third mounting plate 12a can be used for mounting and containing the attitude control assembly, the mounting and containing capacity of the cubic star attitude control support assembly 1 for the attitude control assembly is improved, and then the space occupied by the attitude control assembly on the cubic star is reduced.

[0040] Optionally, the star sensor support 13 is provided with a mounting surface and a through hole, the mounting surface is inclined relative to the first direction, the mounting surface faces the first accommodating space, the through hole penetrates the star sensor support 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 be inserted into the through hole and mounted on the mounting surface.

[0041] Optionally, the star sensor support 13 is provided with a second L-shaped positioning groove at a top end, the groove opening of the second L-shaped positioning groove faces the third accommodating space, and the bottom end of the third mounting plate 12a is matched with the second L-shaped positioning groove. In this way, when the star sensor support 13 is fixedly connected with the third mounting plate 12a, the positioning between the star sensor support 13 and the third mounting plate 12a can be realized by matching the third mounting plate 12a with the second L-shaped positioning groove, thereby facilitating the assembly of the cubic star attitude control support assembly 1. Preferably, a second support 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, and the fixed connection between the star sensor support 13 and the third mounting plate 12a is realized by connecting the second support interface 132 with the through hole through a bolt.

[0042] Optionally, the cubic star attitude control support assembly 1 provided by the embodiment of the application further comprises a cable support 14, the cable support 14 comprises 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 extension 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 lines of each instrument can be fixed on the cable support 14, and the lines of each instrument in the attitude control assembly can be arranged more reasonably. Preferably, a mounting portion is arranged at each end of the L-shaped plate, a through hole is formed on the mounting portion, a threaded hole is arranged on the first mounting plate 12b and the third mounting plate 12a, and the through holes on the mounting portions at the two ends of the L-shaped plate are connected with the threaded holes on the first mounting plate 12b and the third mounting plate 12a through bolts, respectively. The cable mounting seat 15 is preferably plate-shaped.

[0043] As Figures 1 to 3 , and Figures 12 to 17 Another aspect of the application provides a cubic star attitude control system, comprising an attitude control assembly and the cubic star attitude control support assembly 1 provided by the embodiment of the application, The attitude control assembly comprises 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 device 6. The second support 11 comprises a second mounting plate 118, the first support 12 further comprises a third mounting plate 12a, the cubic star attitude control support assembly 1 further comprises a star sensor support 13 and a cable support 14, the attitude control assembly containing space comprises a first containing space, a second containing space and a third containing space, The star sensor 2 and the first flywheel 4 are located in the first containing space, the star sensor 2 is mounted on the star sensor support 13, and the first flywheel 4 is fixed on the first base plate 129, The magnetometer 5, the second flywheel 16 and the gyroscope 3 are located in the second containing space, the magnetometer 5 is fixed on the first mounting plate 12b, the second flywheel 16 and the gyroscope 3 are mounted on the second mounting plate 118, and the arrangement direction of the second flywheel 16 and the gyroscope 3 is parallel to the second mounting plate 118 and the second base plate 116, The third flywheel 17 is located in the third containing space, and the third flywheel 17 is mounted on the third mounting plate 12a, The magnetic torque meter 6 is mounted on the first base plate 129, and the magnetic torque meter 6 is located on the side of the first base plate 129 away from the first containing space.

[0044] In the embodiment of the application, the gyroscope 3 is preferably a MEMS gyroscope.

[0045] The cubic star attitude control support assembly 1 provided by the application, when in use, concentrates the attitude control assembly in the attitude control assembly containing space formed between the first base plate 129 and the second base plate 116, and then fixes the cubic star attitude control support assembly 1 and the attitude control assembly mounted on the cubic star attitude control support assembly 1 as a whole on the cubic star, the first base plate 129, the second base plate 116 and the first mounting plate 12b are used to mount the attitude control assembly, which can effectively reduce the space occupied by the attitude control assembly on the cubic star, compared with dispersing the attitude control assembly around the cubic star; and the attitude control system is an integral whole obtained by integrating the attitude control assembly and the cubic star attitude control support assembly 1, which can simplify the interface with the satellite, compared with independently mounting each component in the attitude control assembly on the cubic star and mounting the above integral whole on the cubic star.

[0046] The cubical satellite attitude control system provided in the application adopts the cubical satellite attitude control support assembly 1 provided in the application, the internal layout of the whole cubical satellite attitude control system is reasonable, and the occupied space on the cubical satellite is reduced; the measuring components and the executing components of the whole cubical satellite attitude control system are connected to the satellite as a whole high-integration module, the attitude control subsystem is assembled and tested on the ground, and then is installed on the satellite body as a whole, so that the interface with the satellite is simplified; the cubical satellite attitude control support assembly 1 as the main force bearing structure is integrally machined from aluminum alloy, satisfies the installation of various instruments and guarantees the transmission of internal and external forces of the assembly, the support is internally distributed with lightening holes and reinforcing ribs, and the support is provided with a wiring path at a reasonable position to facilitate the line connection of various instruments.

[0047] In the embodiment of the application, preferably, the first flywheel 4, the second flywheel 16 and the third flywheel 17 are orthogonally installed and coincide with the X direction, the Y direction and the Z direction of the whole satellite respectively; all the devices except the magnetic torque device 6 are located in the maximum outer envelope of the cubical satellite attitude control support assembly 1, and the cubical satellite attitude control support assembly 1 plays a certain protection role on the attitude control assembly. The devices on the attitude control assembly module are installed compactly, the shape is relatively regular, and the regular space in the satellite is occupied.

[0048] In the embodiments of the present application, preferably, the second support 11 is in a T-shaped structure as a whole, and the second support 11 is provided with a plurality of external interfaces, the second substrate 116 is provided with four satellite interfaces which are arranged at opposite angles and are used for docking with satellites, the star sensor support 13 is formed with a star sensor interface 112, the second mounting plate 118 is provided with a second flywheel interface 113, the second mounting plate 118 is provided with a gyro interface 114, and the first mounting plate interface 115 is formed on the positioning protrusion of the second mounting plate 118; the first support 12 is composed of a first substrate 129, a first mounting plate 12b and a third mounting plate 12a which are perpendicular to each other, the first support 12 is in a structure with large rigidity, the inner surface of the first substrate 129 is provided with a first flywheel interface 121, and the outer side is provided with a magnetic torque device interface 122, the first mounting plate 12b is provided with a magnetometer interface 128, and the outer side of the third mounting plate 12a is provided with a third flywheel interface 123, a cable support interface 125, a star sensor support interface 126 and a satellite docking interface 127; the star sensor support 13 is in a closed frame structure, the installation surface is at a specific angle required by attitude control analysis, the star sensor support 13 is provided with a star sensor interface 131 on the top and a second support interface 132 at the bottom, and the star sensor support 13 is provided with a third mounting plate interface 133 at the top end; the L-shaped plate is formed by bending a sheet metal part, and both ends are provided with a connecting interface 141, and the L-shaped plate is provided with a plurality of mounting seat interfaces 142, and the cable mounting seat 15 is detachably mounted on the mounting seat interfaces 142; the cubic satellite attitude control support assembly 1 is connected with the satellite externally, and is mainly connected through eight screws, four second external interfaces 111 on the second support 11 and four first external interfaces 127 on the first support 12; the cubic satellite attitude control system provided by the present application is assembled as follows: firstly, the second support 11, the star sensor support 13 and the star sensor 2 are assembled into one body, and the first support 12 and the first flywheel 4 are assembled into one body; then, the second support 11, the first support 12 and the star sensor support 13 are assembled into one body, and the gyro 3, the second flywheel 16, the third flywheel 17, the magnetometer 5 and the magnetic torque device 6 are mounted at the corresponding positions peripherally; finally, the cable support 14 and the cable mounting seat 15 are mounted.

[0049] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present application, but not to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: the technical solutions recorded in the foregoing embodiments can still be modified, or some or all of the technical features can be replaced equivalently; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application.

Claims

1. A CubeSat attitude control boom assembly, characterized by, The first support includes a first base plate and a first mounting plate fixed perpendicularly to the first base plate, and the second support includes a second base plate arranged in parallel with the first base plate, and the first mounting plate is fixedly connected with the second support to form a pose control component accommodating space between the first base plate and the second base plate, and the first base plate, the first mounting plate and the second base plate are used for mounting the pose control component.

2. The cubesat attitude control mount assembly of claim 1, wherein, The second support includes a second mounting plate fixed perpendicularly to the second base plate, and the second mounting plate is arranged in parallel with the first mounting plate, and 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, and the second mounting plate is used for mounting the pose control component.

3. The cubesat attitude control mount assembly of claim 2, wherein, A first L-shaped positioning groove is formed on the first mounting plate, and the first L-shaped positioning groove is arranged close to the second mounting plate, and a positioning protrusion is arranged on the second mounting plate, and the positioning protrusion is positioned and matched with the first L-shaped positioning groove.

4. The cubesat attitude control mount assembly of claim 2, wherein, The first support further includes a third mounting plate, and the first base plate, the first mounting plate and the third mounting plate are connected perpendicularly to each other, and the third mounting plate is used for mounting the pose control component.

5. The cubesat attitude control mount assembly of claim 4, wherein, A star sensor support is further included, and one end of the star sensor support is fixed to the second base plate, and the other end of the star sensor support is fixed to one end of the third mounting plate away from the first base plate.

6. The cubesat attitude control mount assembly of claim 5, wherein, The pose control component accommodating space includes a first accommodating space, a second accommodating space and a third accommodating space, and the first accommodating space and the second accommodating space are respectively located on two sides of the first mounting plate in a direction perpendicular to the first mounting plate, and the first accommodating space and the third accommodating space are respectively located on two sides of the second mounting plate in a direction perpendicular to the second mounting plate.

7. The cubesat attitude control mount assembly of claim 6, wherein, An installation surface and a through hole are formed on the star sensor support, the installation surface is inclined relative to a first direction, the installation surface is arranged to face the first accommodating space, the through hole penetrates the star sensor support in a direction perpendicular to the installation surface, and the first direction is arranged perpendicularly to the third mounting plate.

8. The cubesat attitude control mount assembly of claim 7, wherein, A second L-shaped positioning groove is arranged at a top end of the star sensor support, and a groove opening of the second L-shaped positioning groove is arranged to face the third accommodating space, and a bottom end of the third mounting plate is matched with the second L-shaped positioning groove.

9. The cubesat attitude control mount assembly of any of claims 4-8, wherein, A cable support is further included, and the cable support includes an L-shaped plate and a plurality of cable mounting seats detachably mounted on the L-shaped plate, and the cable mounting seats are distributed in an extension direction of the L-shaped plate to clamp cables between the cable mounting seats and the L-shaped plate, one end of the L-shaped plate is fixed to one end of the first mounting plate away from the third mounting plate, and the other end of the L-shaped plate is fixed to one end of the third mounting plate away from the first mounting plate.

10. A cubic star attitude control system characterized by, The pose control component includes a star sensor, a gyroscope, a first flywheel, a second flywheel, a third flywheel, a magnetometer and a magnetic torque device, ​ The second support includes a second mounting plate, the first support further includes a third mounting plate, the cubic star attitude control support assembly further includes a star sensor support and a cable support, the attitude control assembly containing space includes a first containing space, a second containing space and a third containing space, The star sensor and the first flywheel are located in the first containing space, the star sensor is mounted on the star sensor support, and the first flywheel is fixed on the first base plate, The magnetometer, the second flywheel and the gyroscope are located in the second containing space, the magnetometer is fixed on the first mounting plate, the second flywheel and the gyroscope are mounted on the second mounting plate, and the arrangement directions of the second flywheel and the gyroscope are parallel to the second mounting plate and the second base plate, The third flywheel is located in the third containing space, and the third flywheel is mounted on the third mounting plate, The magnetic torque meter is mounted on the first base plate, and the magnetic torque meter is located on the side of the first base plate away from the first containing space.

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