Integrated satellite attitude control system

Abstract

The utility model discloses an integrated satellite attitude control system, and relates to the technical field of satellite structures. Comprising a main body support, star sensors, a terahertz sensor, a mechanical gyroscope, a hydraulic device and a connecting rod, the support is of an octahedral hollow structure, three star sensor supports are rotationally connected to the top of the support, the three star sensors are fixedly connected to the three star sensor supports respectively and located at the three corners of an equilateral triangle respectively, and the three star sensors are connected with the hydraulic device. The three star sensors are installed on the main body support, the sensor is fixedly connected to the outer top surface of the main body support and located in the center of the three star sensors, the mechanical gyroscope is installed on the inner top surface of the main body support and located in the center of the three star sensors, the hydraulic device is fixedly connected to the inner bottom surface of the main body support, and the top end of a hydraulic rod of the hydraulic device is rotationally connected with the bottom ends of the three connecting rods respectively. And the top end of each connecting rod is rotationally connected with a star sensor bracket. The star sensor is simple in structure, small in occupied space and capable of effectively saving installation space, and the installation angle of the star sensor is adjustable.

Description

Technical Field

[0001] The utility model relates to the technical field of satellite structures, in particular to an integrated satellite attitude control system. Background Art

[0002] At present, with the development of aerospace technology, micro-satellites have become a hot topic in the current aerospace research field. The attitude control system is one of the key subsystems of the spacecraft. It is mainly used to provide control force and control torque for the attitude stability and control of various spacecraft during the flight process, ensuring that the aircraft has good stability and operability during the flight.

[0003] The attitude control system includes attitude sensors, attitude control actuators, computers or controllers. At present, attitude sensors mainly include star sensors, time sensors, and gyroscopes. The attitude control actuators are mainly provided with control force and control torque by flywheel mechanisms. Since the current attitude control system layout occupies a large space area and the installation angle of star sensors cannot be changed, this will lead to problems such as increased satellite size, inconvenient transportation, and complex observation.

[0004] Therefore, it is necessary to design an integrated control system structure with a simple structure, small footprint, and the ability to change the installation angle of the star sensor. Utility Model Content

[0005] The technical problem to be solved by the utility model is to provide an integrated satellite attitude control system with a simple structure, small space occupation, and the ability to effectively save installation space and an adjustable star sensor installation angle.

[0006] In order to solve the above technical problems, the technical solution adopted by the utility model is: an integrated satellite attitude control system, including a main body bracket, a star sensor, a time sensor, a mechanical gyroscope, a hydraulic device, and a connecting rod. The main body bracket is an octahedral hollow structure, and three star sensor brackets are rotatably connected to the top of the main body bracket. The three star sensors are respectively fixedly connected to the three star sensor brackets, and the three star sensors are respectively located at the three corners of an equilateral triangle. The time sensor is fixedly connected to the outer top surface of the main body bracket and is located at the center of the three star sensors. The mechanical gyroscope is installed on the inner top surface of the main body bracket and is located at the center of the three star sensors. The hydraulic device is fixedly connected to the inner bottom surface of the main body bracket. The top end of the hydraulic rod of the hydraulic device is rotatably connected to the bottom end of the three connecting rods, and the top end of each connecting rod is rotatably connected to a star sensor bracket.

[0007] Preferably, the top of the main bracket is a regular triangular prism structure, and the three star sensor brackets are all trapezoidal plate structures, which are respectively located on the three sides of the regular triangular prism. The lower base of each trapezoidal plate is rotatably connected to the main bracket through a hinge, and the star sensor is fixedly connected to the center of the upper top surface of the regular triangular prism structure.

[0008] Preferably, two lifting ears are provided on the bottom surface of each star sensor bracket, the first rotating shaft passes through the two lifting ears, and the top end of the connecting rod is arranged between the two lifting ears and is rotatably connected to the first rotating shaft.

[0009] Preferably, three pairs of lifting ears are provided at the top of the hydraulic rod, and the three second rotating shafts pass through the three pairs of lifting ears respectively. A connecting rod is provided between each pair of lifting ears, and the second rotating shaft is rotatably connected to the connecting rod, and the angle between each two second rotating shafts is 120°.

[0010] Preferably, the ear plates of each two adjacent pairs of lifting ears are connected together to form three corner structures with an included angle of 120°.

[0011] The beneficial effects of adopting the above technical solution are:

[0012] 1. The three star sensors are installed in a triangle shape on the main bracket. Only one hydraulic device is used to adjust the angles of the three star sensors at the same time. The overall structure is very simple and occupies little space, which can effectively save space.

[0013] 2. The three star sensors, the Taimin sensor and the mechanical gyroscope are all installed on the main bracket. Through this integrated design, the attitude control system is unified, which greatly simplifies the layout of the circuit and effectively reduces the development cost.

[0014] 3. The hydraulic device can be used to change the angle of the star sensor bracket, thereby changing the angle of the star sensor, which can make the satellite attitude control more flexible and greatly shorten the satellite observation time. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is the overall structural diagram of the control system;

[0016] Figure 2 It is a schematic diagram of the overall structure after the main frame is removed from the bottom plate;

[0017] Figure 3 This is a schematic diagram of the structure when viewed from above after the bottom plate of the main frame is removed;

[0018] Figure 4 It is a schematic diagram of the structure of the hydraulic device;

[0019] In the figure: 1. Star-sensing device; 12. Star-sensing device bracket; 2. Taimin; 3. Mechanical gyroscope; 4. Main frame; 5. Hydraulic device; 51. Hydraulic rod; 6. Connecting rod; 7. Hinge. DETAILED DESCRIPTION

[0020] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0021] like Figure 1-3 As shown, the integrated satellite attitude control system includes a main support 4, three star sensors 1, a Taimin 2, a mechanical gyroscope 3, a hydraulic device 5, and three connecting rods 6. The main support 4 is an octahedral hollow structure, and the top is a regular triangular prism structure. The star-sensing support 12 is a trapezoidal plate, and the trapezoidal plate is installed on the side of the regular triangular prism. The lower bottom of the trapezoidal plate is rotatably connected to the main support 4 through a hinge 7. The star sensor 1 is fixedly connected to the star-sensing support 12 by bolts. The Taimin 2 is fixedly connected to the center position of the upper top surface of the regular triangular prism structure, which is also located exactly at the center of the three star sensors 1.

[0022] The mechanical gyroscope 3 is mounted on the inner top surface of the main support 4, just below the Taimin 2 and at the center of the three Xingmin 1. The hydraulic device 5 can be a hydraulic cylinder, which is fixedly connected to the center of the inner bottom surface of the main support 4. The top of the hydraulic rod 51 of the hydraulic device 5 is rotatably connected to the bottom ends of the three connecting rods 6 respectively.

[0023] In one embodiment of the hydraulic rod 51, three pairs of lifting ears are arranged at the top of the hydraulic rod 51, and three second rotating shafts pass through the three pairs of lifting ears respectively, a connecting rod 6 is arranged between each pair of lifting ears, and the second rotating shaft is rotatably connected to the connecting rod 6. The angle between the three second rotating shafts is 120°.

[0024] like Figure 4 As shown, another embodiment of the hydraulic rod 51 is provided with three pairs of lifting ears at the top of the hydraulic rod 51, and the ear plates of each two adjacent pairs of lifting ears are connected together to form three corner structures with an angle of 120°. This design makes the structure more compact and reduces the space occupied.

[0025] The top end of each connecting rod 6 is rotatably connected to a star-sensing bracket 12. Specifically, two lifting ears are provided on the bottom surface of each star-sensing bracket 12, the first rotating shaft passes through the two lifting ears, and the top end of the connecting rod 6 is arranged between the two lifting ears and rotatably connected to the first rotating shaft.

[0026] There are four mounting holes on Taimin 2, Xingmin 1 and mechanical gyroscope 3. It is necessary to determine the installation accuracy of the attitude control equipment to ensure the accuracy of the equipment's observation data.

[0027] Adjustment of the star-sensing observation angle: the main bracket 4 is installed on the satellite structure, and the field of view angles of the star-sensing device 1 and the star-sensing device 2 are not blocked. During the operation of the satellite, if the observation angle of the star-sensing device 1 needs to be changed, the hydraulic device 5 is operated, and the hydraulic rod 51 extends vertically upward. The hydraulic rod 51 drives the connecting rod 6 to move, so that the star-sensing mounting plate 12 is flipped, thereby achieving the change of the observation angle of the star-sensing device 1.

[0028] The above are only preferred specific implementation methods of the utility model, but the protection scope of the utility model is not limited to this. Any technician familiar with the technical field within the technical scope disclosed by the utility model, who makes equivalent replacements or changes based on the technical scheme and utility model concept of the utility model, should be covered by the protection scope of the utility model.

Claims

1. An integrated satellite attitude control system, characterized in that: The invention comprises a main frame (4), a star sensor (1), a time sensor (2), a mechanical gyroscope (3), a hydraulic device (5), and a connecting rod (6). The main frame (4) is an octahedral hollow structure. Three star sensor frames (12) are rotatably connected to the top of the main frame (4). The three star sensors (1) are respectively fixedly connected to the three star sensor frames (12). The three star sensors (1) are respectively located at three corners of an equilateral triangle. The time sensor (2) is fixedly connected to the outer top surface of the main frame (4) and is located at the center of the three star sensors (1). The mechanical gyroscope (3) is installed on the inner top surface of the main frame (4) and is located at the center of the three star sensors (1). The hydraulic device (5) is fixedly connected to the inner bottom surface of the main frame (4). The top end of a hydraulic rod (51) of the hydraulic device (5) is rotatably connected to the bottom end of the three connecting rods (6). The top end of each connecting rod (6) is rotatably connected to a star sensor frame (12).

2. The integrated satellite attitude control system according to claim 1, characterized in that: The top of the main support (4) is a regular triangular prism structure, and the three star sensor supports (12) are all trapezoidal plate structures, which are respectively located on the three sides of the regular triangular prism. The lower base of each trapezoidal plate is rotatably connected to the main support (4) through a hinge (7), and the star sensor (1) is fixedly connected to the center of the upper top surface of the regular triangular prism structure.

3. The integrated satellite attitude control system according to claim 2, characterized in that: Two lifting ears are provided on the bottom surface of each star sensor bracket (12), the first rotating shaft passes through the two lifting ears, and the top end of the connecting rod (6) is arranged between the two lifting ears and is rotatably connected to the first rotating shaft.

4. The integrated satellite attitude control system according to claim 2, characterized in that: The top end of the hydraulic rod is provided with three pairs of lifting ears, and the three second rotating shafts pass through the three pairs of lifting ears respectively. A connecting rod (6) is provided between each pair of lifting ears, and the second rotating shafts are rotatably connected to the connecting rod (6), and the angle between each two second rotating shafts is 120 degrees.

5. The integrated satellite attitude control system according to claim 4, characterized in that: The ear plates of each two adjacent pairs of lifting ears are connected together to form three corner structures with an included angle of 120°.

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