Torque driving device for spacecraft

Abstract

The invention discloses a spacecraft torque driving device which comprises SPM-1-1A, a mechanism mounting disc and a first mechanism connecting flange are coaxially connected to the SPM-1-1A, the first mechanism connecting flange is arranged above the mechanism mounting disc, the first mechanism connecting flange is an output end, and the second mechanism connecting flange is an output end. The end, away from the first mechanism connecting flange, of the SPM-1-1A is coaxially connected with a second mechanism connecting flange. The invention belongs to the technical field of mechanical measurement, and particularly relates to a spacecraft torque driving device. The dynamic torque sensor is started through SPM-1-1A, meanwhile, the magnetic powder brake is used for driving the axial gear of the coupler to rotate, the dynamic torque sensor is used for reducing the rotating speed ratio of the brake, the dynamic torque sensor is driven to rotate again, and the driving mechanism is connected with the flange plane of the second flange. According to the invention, the SPM-1-1A is driven to rotate, so that a mechanism connecting flange I fixed with the SPM-1-1A is driven, the SPM-1-1A is concentric with a coupler and a dynamic torque sensor in the longitudinal horizontal shaft system direction, the transmission consumption of output torque due to friction can be reduced due to the longitudinal axial arrangement of an integral output system, vector change of torque output is carried out on a spacecraft at high precision, and the torque output precision of the spacecraft is improved. And high-efficiency driving of the spacecraft is realized.

Description

Technical Field

[0001] The present invention belongs to the technical field of mechanical metrology, and specifically refers to a torque driving device for a spacecraft. Background Art

[0002] In the field of space engineering, the design, manufacturing, testing, and maintenance of spacecraft face extremely stringent technical challenges. Spacecraft need to withstand extreme environments and complex mechanical loads in space. The torque control accuracy of the connection and assembly of its components directly determines the structural integrity, flight safety, and upper limit of system performance. When traditional torque control technologies face the complex working conditions of spacecraft, it is difficult to balance high precision, high reliability, and low energy consumption. The torque transmission loss caused by friction will result in torque output deviation, and it cannot meet the precise requirements of space missions for the vector change of torque output. With the development of space technology towards deep space exploration, high-resolution remote sensing, etc., higher requirements are put forward for the accuracy, stability, and efficiency of the torque driving system. The existing driving devices have limitations in structural layout and power transmission, unable to achieve optimal arrangement in the longitudinal and axial directions, and it is difficult to ensure the concentricity between components, resulting in system response lag and large energy loss, seriously restricting the overall performance of the spacecraft. In this context, the research and development of a new type of spacecraft torque driving device has become the key to breaking through the technical bottleneck. There is an urgent need to develop a driving device that can effectively reduce friction loss and achieve high-precision torque output vector change through innovative design and technology integration, so as to meet the growing technical needs of space engineering and provide a solid guarantee for the safe and reliable operation of spacecraft and the improvement of manufacturing and maintenance efficiency. Summary of the Invention

[0003] In view of the above situation, in order to overcome the defects of the prior art, the present invention provides a torque driving device for a spacecraft, effectively solving the problem that the precise concentricity between components in the current market is not achieved, the longitudinal and axial layouts are unreasonable, resulting in a large amount of energy loss due to friction during the torque transmission process, and the output torque accuracy is low, unable to meet the requirements of the spacecraft for high-precision torque output vector change. Secondly, in terms of torque control, the prior art lacks an effective collaborative adjustment mechanism. When power components such as magnetic particle brakes are operating, it is easy to affect the output stability due to friction, resulting in large errors in testing and practical applications, and it is difficult to ensure the accuracy and reliability of the spacecraft driving process.

[0004] The technical solution adopted by the present invention is as follows: The present invention proposes a spacecraft torque drive device, including SPM-1-1A, on which a mechanism mounting disk and a mechanism connecting flange 1 are coaxially connected, the mechanism connecting flange 1 is arranged above the mechanism mounting disk, the mechanism connecting flange 1 is the output end, and the end of the SPM-1-1A away from the mechanism connecting flange 1 is coaxially connected to a mechanism connecting flange 2, and a coupling is coaxially fixedly installed on the mechanism connecting flange 1, and the coupling is used to transmit mechanical motion. Two groups of couplings are provided, and both are arranged at the upper and lower ends of a dynamic torque sensor. Under the synergistic effect of the couplings at both ends, the dynamic torque sensor can capture the real-time dynamic change trend of the torque parameter during the rotation of the equipment, a torque sensor mounting platform is provided on one side of the dynamic torque sensor, and an optical platform is connected to the torque sensor mounting platform away from the dynamic torque sensor. The coupling at the upper end of the dynamic torque sensor is coaxially installed with a torque test disk, and the torque test disk is coaxially installed with a magnetic powder brake, and the magnetic powder brake is arranged above the torque test disk.

[0005] Furthermore, the torque sensor mounting platform fixes the optical platform, and a dynamic torque bracket is fixedly connected to a side of the optical platform away from the torque sensor mounting platform.

[0006] Furthermore, a base is installed on one side of the magnetic powder brake, and the base is connected to the optical platform for fixation; the end of the magnetic powder brake away from the torque measuring disk is connected to a connecting shaft; a mechanism connecting flange 2 is provided at the connection between the connecting shaft and the magnetic powder brake; the end of the connecting shaft away from the magnetic powder brake is connected to an encoder bracket 1 and an encoder bracket 2; the ends of the bracket 1 and the encoder bracket 2 away from the connecting shaft are both connected to the optical platform.

[0007] Furthermore, the mechanism connection flange 1 is rotated in the outer cavity of the mechanism mounting disk through a coupling, and the mechanism connection flange 1 is positioned on the coupling through 8 groups of positioning holes evenly distributed on the outer ring to output the transmission torque vector.

[0008] Furthermore, the coupling is rotatably connected to the torque test disk through a bearing, the magnetic powder brake is threadedly connected to the optical platform through a threaded sleeve, the outer ring of the torque test disk is provided with a groove, and the inner cavity of the mechanism mounting disk is provided with a limit groove, and the limit groove is based on the hook lock principle to achieve connection and positioning with the test end weight. When the magnetic powder brake is started and drives the torque test disk to rotate, a vector relationship is formed between the coupling and the dynamic torque sensor through axial transmission, and the dynamic torque sensor transmits a signal and transmits the information to SPM-1-1A.

[0009] The beneficial effects achieved by the present invention with the above structure are as follows: This solution proposes a torque drive device for a spacecraft. The magnetic powder brake is used to start and drive the torque test disk to rotate. Through axial transmission, a vector relationship is formed between the coupling and the dynamic torque sensor. The dynamic torque sensor transmits signals and transfers the information to the SPM-1-1A for coherent adjustment, thereby avoiding errors caused by friction when rotating the magnetic powder brake during the test, ensuring the accuracy of the experimental test, and achieving high-efficiency drive of the spacecraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 FIG. is a sectional view of a torque drive device for a spacecraft proposed by the present invention.

[0011] Among them, 1. First encoder bracket; 2. Second encoder bracket; 3. Connecting shaft; 4. Magnetic powder brake; 5. Torque test disk; 6. Coupling; 7. Dynamic torque sensor; 8. Second mechanism connection flange; 9. Optical platform; 10. First mechanism connection flange; 11. Mechanism mounting plate; 12. SPM-1-1A; 13. Torque sensor mounting table.

[0012] The drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation to the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0013] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0014] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", etc. indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0015] Such as Figure 1As shown in the figure, the present invention proposes a torque drive device for a spacecraft, including SPM-1-1A12. SPM-1-1A12 serves as the core drive unit of the device. It adopts a high-performance servo motor and has the capabilities of high-precision speed control and stable torque output. A mechanism mounting plate 11 and a first mechanism connection flange 10 are coaxially connected to the SPM-1-1A12. The mechanism mounting plate 11 provides a stable mounting foundation for the device. It is made of high-strength aluminum alloy and has good rigidity and lightweight characteristics. The first mechanism connection flange 10 is arranged above the mechanism mounting plate 11 and serves as the output end of the device for connecting external spacecraft components. Its surface is specially treated to enhance wear resistance and corrosion resistance. At one end of the SPM-1-1A12 away from the first mechanism connection flange 10, a second mechanism connection flange 8 is coaxially connected. The second mechanism connection flange 8 is used to connect power input or other auxiliary equipment to achieve power transmission and the expansion function of the device. A coupling 6 is coaxially and fixedly installed on the first mechanism connection flange 10. The coupling 6 is made of a high-elasticity material and has good shock absorption and the ability to compensate for the relative displacement of two shafts, and is used to transmit mechanical motion. Two sets of the couplings 6 are provided and are both arranged at the upper and lower ends of the dynamic torque sensor 7, ensuring the stability and accuracy of torque transmission. The dynamic torque sensor 7 adopts a high-precision strain gauge sensor. Under the cooperative action of the two couplings 6 at both ends, it can capture the real-time dynamic change trend of torque parameters during the rotation of the device in real time and accurately, and can quickly respond to small changes in torque. On one side of the dynamic torque sensor 7, there is a torque sensing mounting platform 13. The torque sensing mounting platform 13 is made of high-strength engineering plastic and has good insulation and shock absorption performance, and is used to fix the dynamic torque sensor 7 to ensure the stability of its installation. On the side of the torque sensing mounting platform 13 away from the dynamic torque sensor 7, an optical platform 9 is connected. The optical platform 9 has extremely high flatness and stability and provides a high-precision installation reference surface for the entire device. A torque test disc 5 is coaxially installed on the coupling 6 at the upper end of the dynamic torque sensor 7. The surface of the torque test disc 5 is specially processed and has high-precision flatness and roughness, and is used to accurately measure torque. A magnetic powder brake 4 is coaxially installed on the torque test disc 5. The magnetic powder brake 4 serves as a load device and can accurately control the magnitude of the loaded torque. The magnetic powder brake 4 is arranged above the torque test disc 5, facilitating installation and maintenance.

[0016] The torque sensing mounting platform 13 fixes the optical platform 9 through multiple high-strength bolts to ensure the reliability of the connection. On the side of the optical platform 9 away from the torque sensing mounting platform 13, a dynamic torque bracket is fixedly connected. The dynamic torque bracket is made of steel structure and has good rigidity, and is used to support and fix the optical platform 9 to ensure the stability of the entire device during operation.

[0017] On one side of the magnetic powder brake 4, there is a base installed. The base is made of cast iron and has good shock absorption performance. It is fixed to the optical platform 9 through bolt connection. At one end of the magnetic powder brake 4 away from the torque test disc 5, there is a connecting shaft 3 connected. The connecting shaft 3 is made of high-strength alloy steel and has sufficient strength and stiffness. At the connection between the connecting shaft 3 and the magnetic powder brake 4, there is a mechanism connection flange two 8 for realizing reliable connection and power transmission between the two. At one end of the connecting shaft 3 away from the magnetic powder brake 4, there are an encoder bracket one 1 and an encoder bracket two 2 connected. The encoder bracket one 1 and the encoder bracket two 2 are used to install an encoder to accurately measure the rotation speed and angle of the connecting shaft 3. One end of the bracket one 1 and the encoder bracket two 2 away from the connecting shaft 3 are both connected to the optical platform 9, ensuring the stability of the encoder installation and the accuracy of measurement.

[0018] The mechanism connection flange one 10 rotates in the outer cavity of the mechanism installation disc 11 through a coupling 6. The inner wall of the outer cavity of the mechanism installation disc 11 is precision machined and cooperates with the coupling 6 to ensure the smoothness of rotation. The mechanism connection flange one 10 is positioned on the coupling 6 through 8 groups of positioning holes evenly distributed on the outer ring to output and transmit the torque vector, ensuring the accuracy of torque transmission and facilitating installation and disassembly at the same time.

[0019] The coupling 6 is rotationally connected to the torque test disc 5 through a bearing. The bearing is a high-precision rolling bearing with a low friction coefficient and high rotational accuracy, ensuring the smooth rotation of the torque test disc 5. The magnetic powder brake 4 is threadedly connected to the optical platform 9 through a threaded sleeve, facilitating the installation and adjustment of the magnetic powder brake 4. There are grooves on the outer ring of the torque test disc 5, which is convenient for torque measurement and calibration. There is a limiting groove opened in the inner cavity of the mechanism installation disc 11. Based on the hook lock principle, the limiting groove realizes the connection and positioning with the test end weight. By adding weights of different weights, different load conditions can be simulated to test the performance of the device. When the magnetic powder brake 4 starts and drives the torque test disc 5 to rotate, through axial transmission, a vector relationship is formed between the coupling 6 and the dynamic torque sensor 7. The dynamic torque sensor 7 transmits a signal and transfers the information to the SPM-1-1A 12. The SPM-1-1A 12 adjusts the output torque of the motor in real time according to the received torque signal to realize closed-loop control and ensure the stable operation of the device.

[0020] It should be noted that, in this text, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, such that a process, method, article or device comprising a series of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article or device.

[0021] Although the embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

[0022] The above description of the present invention and its embodiments is not restrictive. What is shown in the drawings is only one of the embodiments of the present invention, and the actual structure is not limited thereto. Generally speaking, if those of ordinary skill in the art are inspired by it and, without departing from the gist of the present invention, design similar structural modes and embodiments to this technical solution without creative efforts, they shall fall within the protection scope of the present invention.

Claims

1. A spacecraft torque drive device, characterized in that: It includes SPM-1-1A(12), on which a mechanism mounting disc(11) and a first mechanism connection flange(10) are coaxially connected. The first mechanism connection flange(10) is arranged above the mechanism mounting disc(11). The first mechanism connection flange(10) is the output end. One end of the SPM-1-1A(12) far from the first mechanism connection flange(10) is coaxially connected to a second mechanism connection flange(8). A coupling(6) is coaxially and fixedly installed on the first mechanism connection flange(10). The coupling(6) is used to transmit mechanical motion. There are two groups of couplings(6), and they are both arranged at the upper and lower ends of the dynamic torque sensor(7). Under the cooperative action of the two end couplings(6), the dynamic torque sensor(7) can capture the real-time dynamic change trend of the torque parameter during the rotation of the equipment. A torque sensing mounting platform(13) is arranged on one side of the dynamic torque sensor(7). One side of the torque sensing mounting platform(13) far from the dynamic torque sensor(7) is connected to an optical platform(9). A torque test disc(5) is coaxially installed on the coupling(6) at the upper end of the dynamic torque sensor(7). A magnetic powder brake(4) is coaxially installed on the torque test disc(5). The magnetic powder brake(4) is arranged above the torque test disc(5).

2. The torque drive device for a spacecraft according to claim 1, characterized in that: The torque sensing mounting platform(13) fixes the optical platform(9). A dynamic torque bracket is fixedly connected to one side of the optical platform(9) far from the torque sensing mounting platform(13).

3. A spacecraft torque drive device according to claim 2, characterized in that: A base is installed on one side of the magnetic powder brake(4). The base is connected to the optical platform(9) for fixation. One end of the magnetic powder brake(4) far from the torque measurement disc(6) is connected to a connecting shaft(3). A second mechanism connection flange(8) is arranged at the connection between the connecting shaft(3) and the magnetic powder brake(4). One end of the connecting shaft(3) far from the magnetic powder brake(4) is connected to a first encoder bracket(1) and a second encoder bracket(2). One ends of the first encoder bracket(1) and the second encoder bracket(2) far from the connecting shaft(3) are both connected to the optical platform(9).

4. A spacecraft torque drive device according to claim 1, characterized in that: The first mechanism connection flange(10) rotates in the outer cavity of the mechanism mounting disc(11) through the coupling(6). The first mechanism connection flange(10) is positioned on the coupling(6) through 8 groups of uniformly distributed positioning holes on the outer ring to output and transmit the torque vector.

5. A spacecraft torque drive device according to claim 1, characterized in that: The coupling(6) is rotationally connected to the torque test disc(5) through a bearing. The magnetic powder brake(4) is threadedly connected to the optical platform(9) through a threaded sleeve. A groove is arranged on the outer ring of the torque test disc(5). A limit groove is opened in the inner cavity of the mechanism mounting disc(11). Based on the hook lock principle, the limit groove realizes the connection and positioning with the test end weight. When the magnetic powder brake(4) starts and drives the torque test disc(5) to rotate, through axial transmission, a vector relationship is formed between the coupling(6) and the dynamic torque sensor(7). The dynamic torque sensor(7) transmits a signal and transmits the information to the SPM-1-1A(12).

Images