Attitude control integrated structure based on 1U size

Abstract

The utility model discloses an attitude control integrated structure based on 1U size, and relates to the technical field of satellite structures. Comprising a structure unit, an attitude control subsystem, an attitude monitoring subsystem, a data processing subsystem, a data transmission communication subsystem and a power supply subsystem, the structure of the unit is a hollow hexahedron structure formed by a front mounting plate, a rear mounting plate, a left mounting plate, a right mounting plate, an upper mounting plate and a lower mounting plate, and the six mounting plates are all hollow structures. The front installation plate, the left installation plate and the lower installation plate form a first integrated installation plate, the upper installation plate and the right installation plate form a second integrated installation plate, and the first integrated installation plate, the second integrated installation plate and the rear installation plate are connected through bolts. The attitude monitoring subsystem, the attitude control subsystem, the data processing subsystem, the data transmission communication subsystem and the power supply subsystem are all attached to the unit structure. The satellite attitude control system is simple in structure, low in cost and capable of adapting to integrated attitude control of most satellites.

Description

Technical Field

[0001] The utility model relates to the technical field of satellite structures, and in particular to an attitude control integrated structure based on a 1U size. Background Art

[0002] A satellite is a natural celestial body that orbits a planet in a closed, periodic orbit. Artificial satellites are also generally referred to as satellites. An artificial satellite is an unmanned spacecraft orbiting the Earth. It is a "man-made satellite" created by humans, primarily launched into a predetermined orbit by rockets or other vehicles, orbiting the Earth or other planets for exploration or scientific research. With the development of aerospace technology, satellites have shifted from a single type to a diversified type. With the increasing diversification of user needs, micro- and nano-satellites are gradually entering the aerospace market. Micro- and nano-satellites, with their light weight, small size, short development cycle, low cost, and ability to be launched in large numbers at once, have broad application prospects in many fields.

[0003] A satellite attitude control system is a system used to precisely control and stabilize the satellite's attitude. A satellite's attitude refers to its orientation and position relative to a reference frame (such as the Earth or the Sun) while in orbit. A satellite attitude control system primarily consists of two subsystems: 1. The attitude determination subsystem, which uses information measured by onboard attitude sensors and, after appropriate processing, determines the attitude of a coordinate system fixed to the satellite relative to a reference frame in space. Attitude sensors typically include gyroscopes, star sensors, and sun sensors. 2. The attitude control subsystem, which uses the information provided by the attitude determination subsystem to generate control torques to adjust and stabilize the satellite's attitude. Control torques are typically generated by actuators such as flywheels and magnetic torquers. Currently, satellite attitude control systems primarily utilize a separate installation method, which is time-consuming and requires specialized equipment structural design, resulting in high development time and costs.

[0004] Therefore, it is necessary to design an integrated, low-cost, and highly applicable attitude control structure. Utility Model Content

[0005] The technical problem to be solved by the utility model is to provide an attitude control integrated structure based on 1U size, which has a simple structure and low cost and can adapt to the integrated attitude control of most satellites.

[0006] In order to solve the above technical problems, the technical solution adopted by the present invention is: a 1U-sized attitude control integrated structure, including an attitude control subsystem, an attitude monitoring subsystem, a data processing subsystem, a data transmission and communication subsystem, and a power supply subsystem; the attitude control subsystem includes a flywheel system and a magnetic torquer, and the flywheel system includes a motor, a flywheel, and a motor bracket; the attitude monitoring subsystem includes an accelerometer, a magnetometer, a gyroscope, and a sun sensor; the data processing subsystem includes a logic operation processing all-in-one machine; the data transmission and communication subsystem includes a data transmission all-in-one machine; and the power supply subsystem includes a power management all-in-one machine. It also includes a unit structure, which is a hollow hexahedron structure composed of a front mounting plate, a rear mounting plate, a left mounting plate, a right mounting plate, an upper mounting plate, and a lower mounting plate. The six mounting plates are all hollow structures. The front mounting plate, the left mounting plate, and the lower mounting plate constitute a first integrated mounting plate, and the upper mounting plate and the right mounting plate constitute a second integrated mounting plate. The first integrated mounting plate, the second integrated mounting plate, and the rear mounting plate are connected to each other by bolts to form a hollow hexahedron structure. The attitude monitoring subsystem, the attitude control subsystem, the data processing subsystem, the digital communication subsystem, and the power supply subsystem are all attached and installed on the hollow hexahedron structure.

[0007] Preferably, the motor bracket includes a fixed disc and a hollow cylindrical connecting portion with a accommodating cavity. The fixed disc and the cylindrical connecting portion are coaxial and superimposed. Four T-shaped connecting portions are extended outward from the outer edge of the fixed disc. The flywheel is a cylindrical hollow structure.

[0008] Preferably, the three inner side surfaces of the first integrated mounting plate are each provided with an inner concave plane, and the three inner concave planes are perpendicular to each other and are provided at the center of each inner side surface.

[0009] Preferably, there are three flywheel systems, which are fixedly connected to the three inner side surfaces of the first integrated mounting plate by bolts.

[0010] Preferably, there are three magnetic torquers, namely an X-direction magnetic torquer, a Y-direction magnetic torquer, and a Z-direction magnetic torquer, and the three magnetic torquers are respectively mounted on the inner side surfaces of the upper mounting plate, the rear mounting plate, and the right mounting plate.

[0011] Preferably, the accelerometer is mounted on the inner side of the rear mounting plate, the magnetometer is mounted on the inner side of the right mounting plate, the gyroscope is mounted on the inner side of the rear mounting plate, the sun sensor is mounted on the outer side of the upper mounting plate, the logic operation processing all-in-one machine and the data transmission all-in-one machine are both mounted on the inner side of the right mounting plate, and the power management all-in-one machine is mounted on the inner side of the upper mounting plate.

[0012] The beneficial effects of adopting the above technical solution are:

[0013] 1. In the present invention, the five subsystems are all installed on the unit structure to form an integrated attitude control module, which can adapt to the structures of different satellites.

[0014] 2. The integrated design enables quick replacement of attitude control systems and quick maintenance within the effective space, which is convenient and fast.

[0015] 3. The two integrated mounting plates in the present invention can be processed in one piece so that their processing accuracy is controlled within ±0.01mm, the verticality of adjacent surfaces is 0.05mm, and the flatness is 0.02mm. This can effectively reduce the assembly error of the satellite attitude monitoring equipment, thereby reducing the monitoring error of the equipment, improving the monitoring accuracy, and maintaining the stability of satellite attitude control. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is an exploded diagram of the attitude control system assembly;

[0017] Figure 2 is a structural schematic diagram of the flywheel system installed on the first integrated mounting plate;

[0018] Figure 3 It is a structural diagram of the gyroscope and accelerometer installed on the upper mounting plate;

[0019] Figure 4 is a schematic diagram of device installation on the inner side of the second integrated mounting plate;

[0020] Figure 5 is a schematic diagram of device installation on the outer side of the second integrated mounting plate;

[0021] Figure 6 It is a structural diagram of the unit structure;

[0022] In the figure: 1. First integrated mounting plate; 2. Second integrated mounting plate; 3. Rear mounting plate; 4. Flywheel; 5. Motor; 6. Motor bracket; 7. X-axis magnetic torquer; 8. Y-axis magnetic torquer; 9. Z-axis magnetic torquer; 10. Sun sensor; 11. Gyroscope; 12. Accelerometer; 13. Magnetometer; 14. Logic operation all-in-one machine; 15. Data transmission all-in-one machine; 16. Power management all-in-one machine. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of this application to clearly and completely describe the technical solutions in the embodiments of this application. Obviously, the embodiments described are only part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0024] The integrated attitude control structure includes five subsystems: the attitude control subsystem, the attitude monitoring subsystem, the data processing subsystem, the data transmission and communication subsystem, and the power supply subsystem. These five subsystems are installed on the unit structure. The attitude control subsystem includes the flywheel system and the magnetic torquer. The attitude monitoring subsystem includes an accelerometer 12, a magnetometer 13, a gyroscope 11, and a sun sensor 10. The data processing subsystem includes an integrated logic processing unit 14; the data transmission and communication subsystem includes an integrated data transmission unit 15; and the power supply subsystem includes an integrated power management unit 16.

[0025] The unit structure is the primary load-bearing framework for the entire CubeSat system. Made of Al6061 aluminum alloy with an oxidized surface, the unit structure's envelope dimensions are limited to 100mm × 100mm × 100mm. The mounting plates must fit tightly together, with an allowable assembly tolerance of 0.01mm to 0.04mm. The attitude monitoring subsystem, attitude control subsystem, data processing subsystem, data transmission and communication subsystem, and power supply subsystem are all attached to the unit structure.

[0026] like Figure 1 and Figure 6 As shown, the unit structure is a hollow hexahedron structure consisting of a front mounting plate, a rear mounting plate 3, a left mounting plate, a right mounting plate, an upper mounting plate, and a lower mounting plate. All six mounting plates are hollow structures. The front mounting plate, the left mounting plate, and the lower mounting plate constitute the first integrated mounting plate 1, and the upper mounting plate and the right mounting plate constitute the second integrated mounting plate 2. The first integrated mounting plate 1, the second integrated mounting plate 2, and the rear mounting plate 3 are connected to each other by bolts to form a hollow hexahedron structure. The first integrated mounting plate 1 and the second integrated mounting plate 2 are both integrally connected and processed using milling. The processing accuracy is ±0.01mm, the verticality of adjacent surfaces is 0.05mm, the flatness is 0.02mm, and the surface roughness is Ra3.2. This not only ensures the error during satellite assembly, but also maintains the stability of satellite attitude control.

[0027] like Figure 2As shown, there are three flywheel systems, each bolted to the three inner side surfaces of the first integrated mounting plate 1. Each flywheel system includes a motor 5, a flywheel 4, and a motor bracket 6. The motor bracket 6 comprises a fixed disc and a hollow cylindrical connecting portion with a receiving cavity. The fixed disc and cylindrical connecting portion are coaxial and stacked, with four T-shaped connecting portions extending outward from the outer edge of the fixed disc. The T-shaped connecting portions are connected to the first integrated mounting plate 1 via bolts. The motor 5 is bolted to the receiving cavity of the cylindrical connecting portion of the motor bracket 6, and the flywheel 4 is also bolted to the motor 5. The flywheel 4 is a hollow cylindrical structure with an outer diameter of 75 mm and an inner diameter of 16.5 mm. It is made of aluminum alloy Al6061 and has an oxidized surface. Concave surfaces are provided on each of the three inner side surfaces of the first integrated mounting plate 1. The three concave surfaces are perpendicular to each other and located at the center of each inner side surface. When installed, the flywheel 4 fits neatly into the space between the concave surfaces and the fixed disc of the motor bracket 6. The assembly clearance between the flywheel 4 and the first integrated mounting plate 1 is 1 mm, and the allowable assembly error is controlled within 0.01 mm to 0.04 mm.

[0028] There are three magnetic torquers, namely X-direction magnetic torquer 7, Y-direction magnetic torquer 8, and Z-direction magnetic torquer 9. The three magnetic torquers are respectively mounted on the inner side surfaces of the upper mounting plate, the rear mounting plate 3, and the right mounting plate.

[0029] The accelerometer 12 is mounted on the inner side of the rear mounting plate 3, the magnetometer 13 is mounted on the inner side of the right mounting plate, the gyroscope 11 is mounted on the inner side of the rear mounting plate 3, the sun sensor 10 is mounted on the outer side of the upper mounting plate, the logic operation processing all-in-one 14 and the data transmission all-in-one 15 are both mounted on the inner side of the right mounting plate, and the power management all-in-one 16 is mounted on the inner side of the upper mounting plate.

[0030] In the satellite system module, the accelerometer 12, gyroscope 11, magnetorentrigger, and sun sensor 10 are connected to the integrated logic operation and processing unit 14. During satellite operation, the sun sensor 10 locates the sun's position to monitor the satellite's attitude and orbit. The accelerometer 12 monitors the satellite's angular acceleration, and the gyroscope 11 monitors the satellite's angular velocity. The integrated logic operation and processing unit 14 receives and analyzes the monitoring data from the sun sensor 10, accelerometer 12, and gyroscope 11. After analyzing the data, the integrated logic operation and processing unit 14 uses the flywheel system to adjust the satellite's attitude and orbit based on the satellite's attitude state and mission requirements. Simultaneously, the integrated logic operation and processing unit 14 synchronously transmits the data to the integrated data transmission unit 15, which sends the data to a ground receiver for easy recording and subsequent inspection. The integrated power management unit 16 provides power to the satellite's components. The power management integrated machine 16 needs to supply power to the motor 5, X-direction magnetic torquer 7, Y-direction magnetic torquer 8, Z-direction magnetic torquer 9, sun sensor 10, gyroscope 11, accelerometer 12, magnetometer 13, logic operation processing integrated machine 14, and data transmission integrated machine 15 respectively to ensure the normal operation of the satellite.

[0031] The above are only preferred specific implementation methods of the present invention, but the protection scope of the present invention is not limited to them. Any technician familiar with the technical field can make equivalent replacements or changes based on the technical solution and utility model concept of the present invention within the technical scope disclosed by the present invention, and they should be covered by the protection scope of the present invention.

Claims

1. A 1U-sized integrated attitude control structure, comprising an attitude control subsystem, an attitude monitoring subsystem, a data processing subsystem, a data transmission and communication subsystem, and a power supply subsystem; the attitude control subsystem comprises a flywheel system and a magnetic torquer, the flywheel system comprises a motor, a flywheel, and a motor bracket; the attitude monitoring subsystem comprises an accelerometer, a magnetometer, a gyroscope, and a sun sensor; the data processing subsystem comprises a logic operation processing all-in-one machine; the data transmission and communication subsystem comprises a data transmission all-in-one machine; the power supply subsystem comprises a power management all-in-one machine; and the invention is characterized in that: It also includes a unit structure, which is a hollow hexahedron structure composed of a front mounting plate, a rear mounting plate, a left mounting plate, a right mounting plate, an upper mounting plate, and a lower mounting plate. The six mounting plates are all hollow structures. The front mounting plate, the left mounting plate, and the lower mounting plate constitute a first integrated mounting plate, and the upper mounting plate and the right mounting plate constitute a second integrated mounting plate. The first integrated mounting plate, the second integrated mounting plate, and the rear mounting plate are connected to each other by bolts to form a hollow hexahedron structure. The attitude monitoring subsystem, the attitude control subsystem, the data processing subsystem, the digital communication subsystem, and the power supply subsystem are all attached and installed on the hollow hexahedron structure.

2. The 1U-sized integrated posture control structure according to claim 1, characterized in that: The motor bracket includes a fixed disc and a hollow cylindrical connecting portion with a accommodating cavity. The fixed disc and the cylindrical connecting portion are coaxial and superimposed. Four T-shaped connecting portions are extended outward from the outer edge of the fixed disc. The flywheel is a cylindrical hollow structure.

3. The 1U-sized integrated posture control structure according to claim 1, characterized in that: The three inner side surfaces of the first integrated mounting plate are all provided with inner concave planes, and the three inner concave planes are perpendicular to each other and are provided at the center of the respective inner side surfaces.

4. The 1U-sized integrated posture control structure according to claim 1, characterized in that: There are three flywheel systems, which are fixedly connected to the three inner side surfaces of the first integrated mounting plate by bolts.

5. The 1U-sized integrated posture control structure according to claim 1, characterized in that: There are three magnetic torquers, namely, an X-direction magnetic torquer, a Y-direction magnetic torquer, and a Z-direction magnetic torquer. The three magnetic torquers are respectively mounted on the inner side surfaces of the upper mounting plate, the rear mounting plate, and the right mounting plate.

6. The 1U-sized integrated posture control structure according to claim 1, characterized in that: The accelerometer is mounted on the inner side of the rear mounting plate, the magnetometer is mounted on the inner side of the right mounting plate, the gyroscope is mounted on the inner side of the rear mounting plate, the sun sensor is mounted on the outer side of the upper mounting plate, the logic operation processing all-in-one machine and the data transmission all-in-one machine are both mounted on the inner side of the right mounting plate, and the power management all-in-one machine is mounted on the inner side of the upper mounting plate.

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