Multi-model combined satellite orbit and attitude control system

Abstract

The utility model relates to the technical field of satellite orbit attitude control, and discloses a multi-model combined satellite orbit and attitude control system which comprises a control system chassis, an adjusting wheel is rotatably arranged in the control system chassis, an adjusting disc is fixed at the bottom end of the adjusting wheel, and the adjusting disc is connected with the control system chassis. A first servo motor is fixed to the top face of the control system chassis, the adjusting wheel is arranged in the control system chassis in a sliding and rotating mode, the first servo motor drives the adjusting wheel to rotate, the adjusting wheel drives the adjusting disc to move, and therefore the adjusting disc drives the first balancing weight to move; meanwhile, by adjusting the number of the first balancing weights and the number of the second balancing weights on the balancing weight disc and the adjusting disc, the weight of the balancing weights can be flexibly adjusted, and the problems that the moving angle of the balancing weights in the control system is fixed and single, and the inclination angle of a satellite cannot be adjusted more finely and attitude control cannot be achieved are solved.

Description

Technical Field

[0001] This utility model application relates to the field of satellite orbit and attitude control technology, specifically a multi-model combined satellite orbit and attitude control system. Background Technology

[0002] Satellite orbital attitude control refers to adjusting a satellite's trajectory and orientation in space through dynamics and control technologies to meet mission requirements. Orbital control involves the operation of the propulsion system, which changes the satellite's position, velocity, or orbital parameters. Attitude control, on the other hand, uses reaction wheels, thrusters, or magnetic torquers to stabilize or adjust the satellite's orientation relative to the Earth, the Sun, or other reference directions, ensuring precise payload orientation. Together, they ensure the satellite's positioning accuracy, energy acquisition, communication links, and mission execution. It is one of the core technologies of spacecraft and is widely used in remote sensing, communication, navigation, and other fields.

[0003] Patent No. CN218332379U describes a multi-model combined satellite orbit and attitude control system. Through the interaction of a counterweight, pointer, movable rod, and air box, the system allows for convenient rotation of the motor output, which in turn drives the lead screw via a bevel gear set. This enables the counterweight to slide on the movable rod, providing counterweight on the worktable and causing it to deflect. Air jets from nozzles then control the worktable smoothly, facilitating better training and control.

[0004] The counterweight in the control system of the aforementioned patent has a relatively fixed and singular movement angle, which makes it impossible to adjust the tilt angle and attitude control of the satellite more precisely. Summary of the Invention

[0005] To address the issue that the counterweight's movement angle in the control system of the aforementioned patent is relatively fixed and singular, making it impossible to more precisely adjust the satellite's tilt angle and attitude control, this utility model provides a multi-model combined satellite orbit and attitude control system to solve the above problems.

[0006] To achieve the above objectives, this utility model provides the following technical solution:

[0007] A multi-model combined satellite orbit and attitude control system includes a control system chassis. An adjustment wheel is rotatably mounted inside the control system chassis. An adjustment disk is fixed to the bottom end of the adjustment wheel. A first servo motor is fixed to the top surface of the control system chassis. A transmission gear is fixed to the output end of the first servo motor and meshes with the adjustment wheel. Several first counterweights are slidably mounted on the bottom end of the adjustment disk. The first counterweights are fixedly connected to the adjustment disk by first fixing bolts. A gyroscope sensor is fixed in the center of the control system chassis.

[0008] Furthermore, a counterweight plate is fixed to the top surface of the control system chassis away from the first servo motor, and a plurality of second counterweight blocks are slidably arranged on the counterweight plate, each of the second counterweight blocks being fixedly connected to the counterweight plate by a second fixing bolt.

[0009] Furthermore, two fixed plates are symmetrically fixed at the bottom of the control system chassis, and two other fixed plates are symmetrically fixed at the bottom of the control system chassis away from the first counterweight. Each fixed plate is rotatably connected to a sprocket. A connecting rod is fixed between the two sprockets at the same end, and the two sprockets on the same side are connected by a transmission chain. A third counterweight is fixed at the bottom of the transmission chain. A second servo motor is fixed near the middle of the bottom of the control system chassis, and the output end of the second servo motor is fixedly connected to a sprocket.

[0010] Furthermore, the bottom of the adjustment disc is fixed with a fixed threaded post that matches the position of the first counterweight, and the sum of the masses of the first counterweights matches the mass of the first servo motor.

[0011] Furthermore, the first servo motor, gyroscope sensor, and counterweight are located on the same plane, and the sum of the masses of several second counterweights matches the mass of the first servo motor.

[0012] Furthermore, the mass of the third counterweight is matched with the mass of the first servo motor, and another counterweight with the same mass as the second servo motor is fixed to a third counterweight located away from the second servo motor.

[0013] Compared with the prior art, the beneficial effects of this utility model are:

[0014] 1. In this utility model, an adjustment wheel is slidably rotated inside the control system chassis, and the adjustment wheel is driven to rotate by a first servo motor, which causes the adjustment wheel to move the adjustment disk, thereby causing the adjustment disk to move the first counterweight. At the same time, by adjusting the number of the first and second counterweights on the counterweight disk and the adjustment disk, the weight of the counterweight can be flexibly adjusted, which solves the problem that the movement angle of the counterweight in the control system of the above-mentioned patent is relatively fixed and single, and cannot more precisely adjust the tilt angle and attitude control of the satellite.

[0015] 2. In this utility model, a fixed plate is set at the middle of the bottom end of the control system chassis, and a second servo motor is set on one side of the fixed plate to drive the sprocket to rotate, thereby causing the sprocket to drive the transmission chain to move. At this time, the transmission chain can drive the third counterweight to move. By changing the position of the third counterweight at the bottom end of the control system chassis, the center change at the bottom end of the control system chassis is changed, thereby increasing the adjustment space. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a three-dimensional structural schematic diagram according to an embodiment of the present application;

[0018] Figure 2 yes Figure 1 The above-view three-dimensional structural diagram is shown in the embodiment.

[0019] Figure 3 yes Figure 1 The diagram shown is a three-dimensional representation of the structure after opening in the embodiment shown.

[0020] Figure 4 yes Figure 1 A three-dimensional structural diagram of the third counterweight component in the embodiment shown.

[0021] The meanings of the reference numerals in the diagram are as follows: 1. Control system chassis; 2. Adjusting wheel; 3. First servo motor; 4. Adjusting disc; 5. First counterweight; 6. First fixing bolt; 7. Counterweight disc; 8. Second counterweight; 9. Second fixing bolt; 10. Fixing plate; 11. Sprocket; 12. Connecting rod; 13. Transmission chain; 14. Third counterweight; 15. Second servo motor; 16. Gyroscope sensor; 17. Transmission gear. Detailed Implementation

[0022] To make the purpose, features, and advantages of this application more apparent and understandable, the technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments described below are only some embodiments of this application, and not all embodiments. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0023] Reference Figure 1 , Figure 2 , Figure 3 and Figure 4A multi-model combined satellite orbit and attitude control system includes a control system chassis 1. An adjustment wheel 2 is rotatably mounted inside the control system chassis 1. An adjustment disk 4 is fixed to the bottom end of the adjustment wheel 2. A first servo motor 3 is fixed to the top surface of the control system chassis 1. A transmission gear 17 is fixed to the output end of the first servo motor 3. The transmission gear 17 is meshed with the adjustment wheel 2. Several first counterweights 5 are slidably mounted on the bottom end of the adjustment disk 4. The first counterweights 5 are fixedly connected to the adjustment disk 4 by first fixing bolts 6. A gyroscope sensor 16 is fixed in the middle of the control system chassis 1, making the movement range of the first counterweights 5 more flexible.

[0024] Specifically, the bottom of the adjustment plate 4 is fixed with a fixed threaded post that matches the position of the first counterweight 5. The sum of the masses of several first counterweights 5 matches the mass of the first servo motor 3, so that the center of gravity of the control system chassis 1 is located at the center of the control system chassis 1.

[0025] As an optimization solution, such as Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, a counterweight plate 7 is fixed to the top surface of the control system chassis 1 at the end away from the first servo motor 3. Several second counterweight blocks 8 are slidably arranged on the counterweight plate 7. Each second counterweight block 8 is fixedly connected to the counterweight plate 7 by a second fixing bolt 9. The positions of the first servo motor 3, the gyroscope sensor 16 and the counterweight plate 7 are located on the same plane. The sum of the masses of the several second counterweight blocks 8 is matched with the mass of the first servo motor 3, so that the masses of the second counterweight blocks 8 and the first servo motor 3 are balanced.

[0026] Specifically, two fixed plates 10 are symmetrically fixed at the bottom of the control system chassis 1. Two other fixed plates 10 are symmetrically fixed at the bottom of the control system chassis 1 away from the first counterweight 5. Each fixed plate 10 is rotatably connected to a sprocket 11. A connecting rod 12 is fixed between the two sprockets 11 at the same end. The two sprockets 11 on the same side are connected by a transmission chain 13. A third counterweight 14 is fixed at the bottom of the transmission chain 13. A second servo motor 15 is fixed near the middle of the bottom of the control system chassis 1. The output end of the second servo motor 15 is fixedly connected to a sprocket 11. The mass of the third counterweight 14 matches the mass of the first servo motor 3. Another counterweight with the same mass as the second servo motor 15 is fixed to the third counterweight 14 away from the second servo motor 15, thereby raising the control system chassis 1 to adjust the angle.

[0027] Working principle: By fixing the small satellite to the control system chassis 1, and selecting a second counterweight 8 of corresponding weight to be placed on the counterweight plate 7 according to the weight of the first servo motor 3, and fixing the second counterweight 8 to the counterweight plate 7 with the second fixing bolt 9, the weight between the two ends of the control system chassis 1 and the second counterweight 8 is balanced. At the same time, according to the weight and positional relationship between the first servo motor 3, the second counterweight 8, the third counterweight 14, and the first counterweight 5, a corresponding number of first counterweights 5 are placed at the adjustment plate 4, and fixed to the adjustment plate 4 with the first fixing bolt 6. At this time, the third counterweight 14 and the first counterweight 5 are both perpendicular to the first servo motor 3 and the counterweight plate 7, so that the center of gravity of the control system chassis 1 is located at... At the center of the control system chassis 1, when the gyroscope sensor 16 detects that the control system chassis 1 is tilted, it starts the first servo motor 3, which drives the transmission gear 17 to rotate. At the same time, the transmission gear 17 drives the adjusting wheel 2 to rotate, which in turn drives the first counterweight 5 to move. This causes the center of gravity on one side of the control system chassis 1 to shift and adjust the attitude of the control system chassis 1. Simultaneously, it starts the second servo motor 15, which drives the sprocket 11 to rotate. This causes the sprocket 11 to drive the transmission chain 13 to move, which in turn drives the third counterweight 14 to move. This causes the center of gravity on the other side of the control system chassis 1 to change as well. The attitude of the control system chassis 1 is then adjusted according to the detection data of the gyroscope sensor 16.

[0028] It will be apparent to those skilled in the art that this application is not limited to the details of the exemplary embodiments described above, and that this application can be implemented in other specific forms without departing from the spirit or essential characteristics of this application. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this application is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of the equivalent elements of the claims are intended to be included within this application. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0029] The above-described 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 of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application.

Claims

1. A multi-model combined satellite orbit and attitude control system, comprising a control system chassis (1), characterized in that: The control system chassis (1) is equipped with an adjustment wheel (2) that rotates inside. An adjustment disk (4) is fixed at the bottom of the adjustment wheel (2). A first servo motor (3) is fixed on the top surface of the control system chassis (1). A transmission gear (17) is fixed at the output end of the first servo motor (3). The transmission gear (17) meshes with the adjustment wheel (2). Several first counterweights (5) are slidably arranged at the bottom of the adjustment disk (4). The first counterweights (5) are fixedly connected to the adjustment disk (4) by first fixing bolts (6). A gyroscope sensor (16) is fixed in the middle of the inside of the control system chassis (1).

2. The satellite orbit and attitude control system with multi-model combination according to claim 1, characterized in that: The control system chassis (1) has a counterweight plate (7) fixed at one end of its top surface away from the first servo motor (3). Several second counterweight blocks (8) are slidably arranged on the counterweight plate (7). Each second counterweight block (8) is fixedly connected to the counterweight plate (7) by a second fixing bolt (9).

3. The satellite orbit and attitude control system with multi-model combination according to claim 1, characterized in that: The control system chassis (1) has two fixed plates (10) symmetrically fixed at the bottom end. The control system chassis (1) has two other fixed plates (10) symmetrically fixed at the end away from the first counterweight (5). Each fixed plate (10) is rotatably connected to a sprocket (11). A connecting rod (12) is fixed between the two sprockets (11) at the same end. The two sprockets (11) on the same side are connected by a transmission chain (13). A third counterweight (14) is fixed at the bottom end of the transmission chain (13). A second servo motor (15) is fixed near the middle of the bottom end of the control system chassis (1). The output end of the second servo motor (15) is fixedly connected to a sprocket (11).

4. A satellite orbit and attitude control system with multiple model combinations according to claim 1, characterized in that: The bottom of the adjustment plate (4) is fixed with a fixed threaded column that matches the position of the first counterweight (5), and the sum of the masses of several first counterweights (5) matches the mass of the first servo motor (3).

5. A satellite orbit and attitude control system with multiple model combinations according to claim 2, characterized in that: The first servo motor (3), gyroscope sensor (16) and counterweight disk (7) are located on the same plane, and the sum of the masses of several second counterweight blocks (8) matches the mass of the first servo motor (3).

6. A satellite orbit and attitude control system with multiple model combinations according to claim 3, characterized in that: The mass of the third counterweight (14) is matched with the mass of the first servo motor (3), and a third counterweight (14) away from the second servo motor (15) is fixed with another counterweight of the same mass as the second servo motor (15).

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