A device for controlling the steering of a satellite platform
By combining components such as central control circuit board, gear disk and motor speed reduction mechanism, all-round attitude control of the satellite platform is achieved, solving the problems of complex structure and heavy weight in the existing technology, reducing energy consumption and cost, and improving application flexibility.
Patent Information
- Application Number
- CN202111630046.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2021-12-29
- Publication Date
- 2025-08-26
- Estimated Expiration
- 2041-12-29
AI Technical Summary
The attitude control mechanism of the existing satellite platform is complex in structure and heavy in weight, and requires a jet control system to achieve all-round movement, resulting in increased energy consumption and cost.
A device for controlling the steering of the satellite platform is adopted, including a central control circuit board, a gear disc, a motor speed reduction mechanism, a rotary power supply mechanism, an attitude transmitting unit, a signal receiving unit and a control unit, and the 360-degree rotation and attitude control of the satellite platform are realized through the combined movement of the motor and the flywheel.
It realizes all-round attitude control with simple structure, light weight and convenient use, reduces energy consumption, reduces aerospace launch costs, and improves application flexibility.
Smart Images
Figure CN114261541B_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of satellite auxiliary equipment, in particular to a device for controlling the steering of a satellite platform. Background Art
[0002] A satellite platform is a platform equipped with various detection and communication equipment, solar panels, and other equipment. To ensure the satellite's attitude control while orbiting the Earth, a controller for controlling flight direction is installed on the satellite platform. Existing controllers generally include jet or flywheel inertial control mechanisms, among others. Although jet control of satellite flight attitude is effective, it consumes energy carried by the platform. Therefore, after the required energy is used up, the satellite will no longer be able to adjust its flight attitude. In addition, the jet control mechanism (the probe on the central control circuit board detects the satellite platform's attitude and then controls the direction of gas ejection from the relevant nozzles) requires nozzles to be installed in all directions of the satellite platform and connected to the jet mechanism separately. This makes the overall equipment more complex. The increased weight and increased cost of space launches also have certain application limitations.
[0003] Current flywheel inertial control mechanisms, also known as wheel control systems, use the inertial wheel as the primary actuator for attitude control. This control is primarily achieved by generating a reaction torque from flywheel acceleration. Typically, these systems only control the satellite's pitch and other attitudes (probes on the central control circuit board detect the satellite platform's attitude and then control the wheel control system's operation). However, horizontal and vertical roll (rotation) control requires the use of a jet control system. Consequently, the complex and heavy jet control mechanism presents practical limitations. Therefore, a simple, easy-to-use device capable of controlling the steering of a satellite platform in all directions is highly desirable. Summary of the Invention
[0004] In order to overcome the drawbacks of the directional control mechanisms used in existing satellite platforms as described in the background, the present invention provides a device for controlling the steering of a satellite platform that has a simple and compact structure, is light in weight, and is easy to use. Under the joint action of the relevant factors in application, the flywheel can rotate 360 degrees along the X-axis and the Y-axis, thereby generating directional forces in all directions, driving the entire device and the onboard equipment to move to the required azimuth angle, and providing strong technical support for the normal operation of the satellite.
[0005] The technical solution adopted by the present invention to solve its technical problem is:
[0006] A device for controlling the steering of a satellite platform, comprising a central control circuit board, a gear plate, a motor reduction mechanism, a gear, a fixed plate, a connecting plate, an outer shell, and a motor of the satellite platform, wherein the signal output end of the central control circuit board is electrically connected to the power input end of the motor and the motor reduction mechanism respectively; the device is characterized in that it also has a rotating power supply mechanism, a posture sending unit, a signal receiving unit and a control unit; the posture sending unit, the signal receiving unit and the control unit are application software installed on the central control circuit board; the gear plate is installed in front of the fixed plate, the side of the connecting plate is installed with a bearing, the inner ring of the bearing is installed with a shaft, the shell side of the motor reduction mechanism is installed on one side of the inner shell, the connecting plate is installed in the outer shell, the power output shaft of the motor reduction mechanism and one end of the shaft are installed together, and the other end of the shaft and one side end of the fixed plate are installed together; a flywheel is installed under the power output shaft of the motor; the rotating power supply mechanism includes a sleeve, Bearing A, electromagnetic coil, annular armature, the lower end of the sleeve is installed on the upper end of the motor housing, there are at least two bearings A, respectively installed at the upper and lower ends of the sleeve, the outer ring of the lower end bearing A and the inner side of the sleeve, and the inner ring and the outer end of the power output shaft are insulated, there is an opening at the bottom of the side end of the sleeve, and the wire connected to the outer ring of the lower end bearing is led outward from the opening, the electromagnetic coil is installed on the upper end of the power output shaft, an upper shaft is sleeved inside the inner ring of the upper end bearing A, the gear is installed on the upper shaft, and the upper end of the armature is installed at the lower end of the upper shaft and located in the sleeve; the wire connected to the inner ring of the lower end bearing A, the upper end of the power output shaft and the two power input ends of the electromagnetic coil are electrically connected respectively, and the outer shell is installed at the middle of the lower end of the satellite platform; the attitude sending unit can send satellite platform attitude data to the ground receiving station, and the signal receiving unit can receive the command signal sent by the ground station, and then the control unit controls the working mode of the motor and the motor reduction mechanism respectively.
[0007] Furthermore, the control unit itself can also automatically control the attitude of the satellite platform based on the output subunit function of the attitude sending unit.
[0008] Furthermore, the outer diameters of the electromagnetic coil and the armature are smaller than the inner diameter of the sleeve, and there is a distance between the upper end of the electromagnetic coil and the lower end of the armature.
[0009] Furthermore, the motor reduction mechanism shown has a limit switch inside; the control unit controls the working mode of the motor reduction mechanism so that it does not rotate more than 360 degrees in the circumferential direction.
[0010] Furthermore, one of the negative power output terminals of the main control circuit board is connected to the negative power input terminal of the electromagnetic coil via the connecting plate, the fixing plate, the power output shaft of the motor.
[0011] Furthermore, the attitude sending unit can collect data detected by various satellite attitude detectors carried by the satellite platform, and transmit the signal remotely through its supporting data sending circuit.
[0012] Furthermore, when the control unit controls the working mode of the motor and the motor reduction mechanism, it will detect the attitude data of the satellite platform in real time. When the platform attitude data reaches a preset value, the control unit will no longer control the working mode of the motor and the motor reduction mechanism.
[0013] Furthermore, after the attitude sending unit sends the satellite platform attitude data and the ground station related application receives the data, the ground station personnel can cut off the output subunit to control the attitude of the satellite platform.
[0014] The beneficial effects of the present invention are as follows: the present invention has a simple and compact structure, is lightweight, and is easy to use. In application, the attitude of the satellite platform can be automatically controlled under the action of the output subunit, and the attitude of the satellite platform can be controlled by sending instructions through ground personnel as needed, making it more convenient and flexible to use. In the present invention, the motor reduction mechanism can drive the motor and its connected components to rotate 360 degrees vertically to any angle, and the motor can drive the flywheel to rotate horizontally to any angle. In this way, the flywheel driven by the electric mechanism located at different angles can cause the satellite platform to be rotated to the corresponding attitude by the reaction force. The present invention provides strong technical support for the normal operation of the satellite. Based on the above, the present invention has good application prospects. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] The present invention will be further described below with reference to the accompanying drawings and embodiments.
[0016] Figure 1 It is a schematic diagram of the overall structure of the present invention.
[0017] Figure 2 、 3 It is a schematic diagram of the local structure of the present invention. DETAILED DESCRIPTION
[0018] Figure 1 、 23, a device for controlling the steering of a satellite platform, including a satellite platform central control circuit board (not shown), a hollow annular gear plate 2, a motor 32 and a motor reduction mechanism 31, a bevel gear 4, a fixing plate 5, an outer shell 6, and a connecting plate 17. The signal output terminal of the satellite platform central control circuit board and the power input terminals of the motor 32 and the motor reduction mechanism 31 are respectively connected via wires (and connected to the power input terminal of the electromagnetic coil 13 via wires); the device also has a rotating power supply mechanism, a posture sending unit, a signal receiving unit, and a control unit; the posture sending unit, the signal receiving unit, and the control unit are application software installed on the central control circuit board; The gear disc 2 is mounted on the front of the fixed plate 5, and there is an axial hole in the middle of the left side of the connecting plate 17, in which a bearing 8 is mounted, and a shaft rod 7 is tightly sleeved in the inner ring of the bearing 8. The right rear end of the shell of the motor reduction mechanism 31 is mounted in the middle of the right end of the outer shell 6 through a screw nut, and the upper and lower parts of the connecting plate 17 are mounted on the upper and lower sides of the middle of the outer shell 6. The power output shaft of the motor reduction mechanism 31 is welded to the right rear end of the shaft rod 7, and the left front end of the shaft rod 7 is welded to the middle of the right end of the fixed plate 5; a circular flywheel 8 is welded under the lower power output shaft of the motor 32 (the power output shaft passes through the shell of the motor); the rotating power supply mechanism includes a sleeve 11 , bearing 12, annular electromagnetic coil 13, annular armature 14, the lower end of the sleeve 11 is welded to the middle of the upper end of the outer shell of the motor 32 and the upper end power output shaft of the motor 32 is located in the sleeve 11, there are two bearings, which are respectively installed at the upper and lower ends of the sleeve 11, and annular insulating sleeves are tightly installed between the outer ring of the lower end bearing 12 and the inner side of the sleeve 11, and between the inner ring and the outer end of the power output shaft of the motor 32. There is an opening on the left side of the lower end of the sleeve 11, and a wire 15 is welded to the outer ring of the lower end bearing. The wire 15 is led out through the opening of the sleeve and connected to one of the positive power output terminals of the central control circuit board through a wire. The electromagnetic coil 13 is installed on the motor 32. At the upper end of the force output shaft, an upper shaft 16 is tightly sleeved in the inner ring of the upper end bearing 12, the middle part of the bevel gear 4 is installed on the upper shaft 16 and is located outside the sleeve, and the upper end of the armature 14 is installed at the lower end of the upper shaft 16 and is located inside the sleeve; the wires connected to the inner ring of the lower end bearing 12, the upper end of the power output shaft of the motor 32 and the two power input ends of the electromagnetic coil 13 are respectively connected by wires, and the outer shell 6 is installed in the middle of the lower end of the satellite platform 1; the attitude sending unit can send the satellite platform attitude data to the ground receiving station, and the signal receiving unit can receive the command signal sent by the ground station, and then the control unit controls the working mode of the two sets of motor reduction mechanisms respectively.
[0019] Figure 1 、 2As shown in Figures 3 and 4, the control unit itself, based on the output subunit of the attitude transmission unit, can also automatically control the attitude of the satellite platform. The outer diameter of the electromagnetic coil 13 and the armature 14 is 1 mm smaller than the inner diameter of the sleeve 11. The upper end of the electromagnetic coil 13 and the lower end of the armature 14 are separated by a small distance (0.2 mm). The motor reduction mechanism 31 has an internal limit switch. If the motor reduction mechanism 31 rotates approximately 360 degrees in one direction, it will lose power and will only be re-energized when power is supplied in the reverse direction. The control unit controls the operation of the first motor reduction mechanism to prevent it from exceeding 360 degrees in the circumferential direction. One of the negative power output terminals of the main control circuit board is connected to the negative power input terminal of the electromagnetic coil 13 via the connecting plate 17, the fixing plate 5, and the power output of the motor 32. The attitude transmission unit can collect data detected by various satellite attitude sensors on the satellite platform and transmit the signals remotely through its supporting transmission equipment. When the control unit controls the operation of the motor reduction mechanism, it monitors the satellite platform's attitude data in real time. When the platform attitude data reaches a preset value, the control unit no longer controls the motor reduction mechanism and the motor operation mode. After the attitude sending unit sends the satellite platform attitude data and the ground station related applications receive the data, the ground station personnel can cut off the output subunit to control the attitude of the satellite platform.
[0020] Figure 1 、 2As shown in Figure 3, the present invention has a simple and compact structure, is light in weight and easy to use. In application, the control unit itself can automatically control the attitude of the satellite platform 1 based on the output subunit of the attitude sending unit. When the satellite platform 1 has an attitude deviation in the vertical or horizontal direction, the control unit can output power to the motor reduction mechanism and the power input end of the motor respectively. The motor reduction mechanism 31 can drive the motor and the fixing plate to rotate to any angle in the vertical direction (Y axis), and the motor 32 can drive the flywheel 9 to rotate to any angle in the horizontal direction (X axis). Since the flywheel is in rotation, the satellite platform can be rotated to the corresponding attitude (for example, the flywheel 9 is in the reverse direction) under the inertia of the motor driving the flywheel 9 at different angles. If the flywheel is located at the lower end and rotates clockwise for a period of time, the satellite platform will drive the onboard equipment to rotate horizontally counterclockwise by a certain angle to change the satellite platform's attitude. If the flywheel is located at the lower end and rotates counterclockwise for a period of time, the satellite platform will drive the onboard equipment to rotate horizontally clockwise by a certain angle to change the satellite platform's attitude. For example, if the flywheel is located at the left end and rotates clockwise for a period of time, the satellite platform will drive the onboard equipment to rotate vertically counterclockwise by a certain angle to change the satellite platform's attitude. If the flywheel is located at the left end and rotates counterclockwise for a period of time, the satellite platform will drive the onboard equipment to rotate vertically clockwise by a certain angle to change the satellite platform's attitude. In the present invention, when the control unit controls the working mode of the motor and the motor reduction mechanism, it will detect the attitude data of the satellite platform in real time. When the platform attitude data reaches a preset value, the control unit will no longer control the working mode of the motor and the motor reduction mechanism, thus ensuring effective adjustment of the satellite platform's attitude. In the present invention, when the control unit controls the motor reduction mechanism 31 to be powered on, according to the different polarities of the positive and negative power output by the control unit, the motor reduction mechanism 31 will drive the fixed plate 5, the motor 32, the rotating power supply mechanism, etc. to rotate clockwise or counterclockwise to the corresponding angle. When the control unit energizes motor 32, it drives the flywheel clockwise or counterclockwise, depending on the polarity of the input power, generating inertial counterforces in different directions. When the control unit energizes motor 32 and electromagnetic coil 13, the strong magnetic force generated by electromagnetic coil 13 acts on the armature at the lower end of upper shaft 16. This causes motor 32, via the power output shaft, to rotate electromagnetic coil 13, which in turn engages the armature (made of steel), driving bevel gear 4 clockwise or counterclockwise. Consequently, as the motor's power output shaft rotates clockwise or counterclockwise, the motor 32 and flywheel rotate horizontally along gear plate 2, via bevel gear 4, counterclockwise or clockwise to the appropriate angle, thereby changing the satellite platform's attitude.In the present invention, when the power output shaft of the motor 32 rotates along the bearing (copper material) 12 at the lower end of the sleeve 11, the outer ring of the bearing does not rotate, thus ensuring that the positive power supply output by the control unit enters the positive power input end of the electromagnetic coil 13 through the wire connected to the outer ring of the bearing 12, the bearing balls, and the inner ring of the bearing, and the negative power input end of the electromagnetic coil and the negative power output end of the control unit are connected through the power output shaft of the motor 32 and the fixed plate 5, the outer shell 6, etc.; through the above, the present invention can effectively ensure the power supply of the electromagnetic coil, and can also ensure that the electromagnetic coil drives the umbrella gear to rotate through the armature.
[0021] Figure 1 、 2 As shown in Figures 3 and 4, in the present invention, the attitude sending unit can collect data detected by various satellite attitude detectors carried by the satellite platform and transmit the signal remotely through its supporting output sending circuit. After receiving the data, the ground base station can manually control the attitude of the satellite platform 1 as needed. After the ground personnel issue an instruction through the application software in the PC, the output subunit cuts off the automatic control of the satellite platform's attitude. Then, the ground personnel, in conjunction with the attitude sending unit, can collect attitude data detected by various satellite attitude detectors carried by the satellite platform and issue corresponding instructions. The signal receiving unit receives the instruction signal sent by the ground station and can control the working mode of the motor and the motor reduction mechanism respectively through the control unit, thereby achieving the purpose of controlling the attitude of the satellite platform 1. The present invention provides strong technical support for the normal operation of satellites.
[0022] The basic principles and main features of the present invention and the advantages of the present invention are shown and described above. It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above and that the present invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the present invention. Therefore, the embodiments should be regarded in all respects as illustrative and non-restrictive. The scope of the present invention is defined by the appended claims rather than the foregoing description, and all changes that come within the meaning and range of equivalents of the claims are intended to be included therein.
[0023] In addition, it should be understood that although this specification is described in terms of implementation methods, the implementation methods do not only include an independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in the embodiments can also be appropriately combined to form other implementation methods that can be understood by those skilled in the art.
Claims
1. A device for controlling the steering of a satellite platform, comprising a central control circuit board, a gear plate, a motor reduction mechanism, a gear, a fixing plate, a connecting plate, an outer shell, and a motor of the satellite platform, wherein the signal output terminal of the central control circuit board is electrically connected to the power input terminal of the motor and the motor reduction mechanism; characterized in that It also has a rotating power supply mechanism, a posture sending unit, a signal receiving unit and a control unit; the posture sending unit, the signal receiving unit and the control unit are application software installed on the central control circuit board; the gear plate is installed in front of the fixed plate, the side of the connecting plate is installed with a bearing, the inner ring of the bearing is installed with a shaft, the side of the shell of the motor reduction mechanism is installed on one side of the inner shell, the connecting plate is installed in the outer shell, the power output shaft of the motor reduction mechanism and one end of the shaft are installed together, and the other end of the shaft and one side of the fixed plate are installed together; a flywheel is installed under the power output shaft of the motor; the rotating power supply mechanism includes a sleeve, a bearing A, an electromagnetic coil, and an annular armature. The lower end of the sleeve is installed on the upper end of the motor shell, and there are at least two bearings A, which are installed in the upper and lower parts of the sleeve respectively. The end, the outer ring of the lower end bearing A and the inner side of the sleeve, and the inner ring and the outer end of the power output shaft are insulated. There is an opening at the bottom of the side end of the sleeve, and the wire connected to the outer ring of the lower end bearing is led out from the opening. The electromagnetic coil is installed at the upper end of the power output shaft, and an upper shaft rod is sleeved in the inner ring of the upper end bearing A. The gear is installed on the upper shaft rod, and the upper end of the armature is installed at the lower end of the upper shaft rod and is located in the sleeve; the wire connected to the inner ring of the lower end bearing A, the upper end of the power output shaft and the two power input ends of the electromagnetic coil are electrically connected respectively, and the outer shell is installed at the middle of the lower end of the satellite platform; the attitude sending unit can send satellite platform attitude data to the ground receiving station, and the signal receiving unit can receive the command signal sent by the ground station, and then the control unit controls the working mode of the motor and the motor reduction mechanism respectively.
2. The device for controlling the steering of a satellite platform according to claim 1, characterized in that: The control unit itself can also automatically control the attitude of the satellite platform based on the output sub-unit function of the attitude sending unit.
3. The device for controlling the steering of a satellite platform according to claim 1, characterized in that: The outer diameters of the electromagnetic coil and the armature are smaller than the inner diameter of the sleeve, and there is a distance between the upper end of the electromagnetic coil and the lower end of the armature.
4. The device for controlling the steering of a satellite platform according to claim 1, characterized in that: The motor reduction mechanism is internally provided with a limit switch; the control unit controls the working mode of the motor reduction mechanism so that the motor reduction mechanism does not rotate more than 360 degrees in the circumferential direction.
5. The device for controlling the steering of a satellite platform according to claim 1, characterized in that: One of the negative power output terminals of the main control circuit board is connected to the negative power input terminal of the electromagnetic coil via the connecting plate, the fixing plate, the power output shaft of the motor.
6. The device for controlling the steering of a satellite platform according to claim 1, characterized in that: The attitude sending unit can collect data detected by various satellite attitude detectors carried by the satellite platform, and transmit the signal remotely through its supporting data sending circuit.
7. The device for controlling the steering of a satellite platform according to claim 1, characterized in that: When the control unit controls the working mode of the motor and the motor reduction mechanism, it will detect the attitude data of the satellite platform in real time. When the platform attitude data reaches a preset value, the control unit will no longer control the working mode of the motor and the motor reduction mechanism.
8. The device for controlling the steering of a satellite platform according to claim 1, characterized in that: After the attitude sending unit sends the satellite platform attitude data and the ground station related applications receive the data, the ground station personnel can cut off the output subunit to control the attitude of the satellite platform.
Citation Information
Patent Citations
Uniaxial quick maneuverable spacecraft flywheel configuration and optimization method thereof
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