Spacecraft torque drive

Abstract

This invention discloses a spacecraft torque drive device, including an SPM-1-1A. A mechanism mounting plate and a mechanism connecting flange one are coaxially connected to the SPM-1-1A. The mechanism connecting flange one is located above the mechanism mounting plate and is an output end. A mechanism connecting flange two is coaxially connected to one end of the SPM-1-1A away from the mechanism connecting flange one. This invention belongs to the field of mechanical measurement technology, specifically referring to a spacecraft torque drive device. The invention activates a dynamic torque sensor via SPM-1-1A, simultaneously using a magnetic powder brake to drive the axial gear of the coupling to rotate. The dynamic torque sensor reduces the brake's speed ratio and then drives the dynamic torque sensor to rotate again. Through the flange plane of the drive mechanism connecting flange two, it drives the mechanism fixed to SPM-1-1A to connect flange one, ensuring that SPM-1-1A is concentric with the coupling and dynamic torque sensor in the longitudinal horizontal axis direction. The overall output system's longitudinal axial arrangement reduces torque loss due to friction, thus enabling high-precision vector changes in torque output for the spacecraft, achieving high-efficiency drive.

Description

Technical Field

[0001] This invention belongs to the field of mechanical measurement technology, specifically referring to a spacecraft torque drive device. Background Technology

[0002] In the field of aerospace engineering, the design, manufacturing, testing, and maintenance of spacecraft face extremely stringent technical challenges. Spacecraft must withstand extreme environments and complex mechanical loads in space, and the torque control precision of their component connections and assembly directly determines structural integrity, flight safety, and the upper limit of system performance. Traditional torque control technologies struggle to balance high precision, high reliability, and low energy consumption when facing the complex operating conditions of spacecraft. Friction-induced torque transmission losses cause torque output deviations, failing to meet the precise torque output vector changes required by space missions. As aerospace technology advances towards deep space exploration and high-resolution remote sensing, higher demands are placed on the precision, stability, and efficiency of torque drive systems. Existing drive devices have limitations in structural layout and power transmission, making it impossible to achieve optimized longitudinal axial arrangement and ensure concentricity between components. This results in system response lag, high energy loss, and severely restricts the overall performance of the spacecraft.

[0003] Against this backdrop, developing novel spacecraft torque drive devices has become crucial for overcoming technological bottlenecks. There is an urgent need to develop drive devices through innovative design and technology integration that can effectively reduce frictional losses and achieve high-precision torque output vector changes. This is essential to meet the growing technological demands of aerospace engineering and provide a solid guarantee for the safe and reliable operation of spacecraft and improved manufacturing and maintenance efficiency. Summary of the Invention

[0004] To address the aforementioned issues and overcome the shortcomings of existing technologies, this invention provides a spacecraft torque drive device. This device effectively solves the problems of insufficient concentricity between components and unreasonable longitudinal and axial layout, which lead to significant energy loss due to friction during torque transmission and low output torque accuracy, failing to meet the spacecraft's requirement for high-precision torque output vector changes. Furthermore, in terms of torque control, existing technologies lack effective coordinated adjustment mechanisms. Power components such as magnetic powder brakes are prone to output stability issues due to friction during operation, resulting in significant errors in testing and practical applications, making it difficult to guarantee the accuracy and reliability of the spacecraft's drive process.

[0005] The technical solution adopted by this invention is as follows: This invention proposes a spacecraft torque drive device, including an SPM-1-1A. A mechanism mounting plate and a mechanism connecting flange 1 are coaxially connected to the SPM-1-1A. The mechanism connecting flange 1 is located above the mechanism mounting plate and serves as the output end. A mechanism connecting flange 2 is coaxially connected to one end of the SPM-1-1A away from the mechanism connecting flange 1. A coupling is coaxially fixedly mounted on the mechanism connecting flange 1. The coupling is used to transmit mechanical motion. Two sets of couplings are provided, both arranged at the upper and lower ends of a dynamic torque sensor. Under the synergistic action of the couplings at both ends, the dynamic torque sensor can capture the real-time dynamic change trend of torque parameters during equipment rotation. A torque sensing mounting platform is provided on one side of the dynamic torque sensor. An optical platform is connected to the side of the torque sensing mounting platform away from the dynamic torque sensor. A torque testing plate is coaxially mounted on the coupling at the upper end of the dynamic torque sensor. A magnetic powder brake is coaxially mounted on the torque testing plate, and the magnetic powder brake is located above the torque testing plate.

[0006] Furthermore, the torque sensing mounting platform fixes the optical platform, and a dynamic torque bracket is fixedly connected to the side of the optical platform away from the torque sensing mounting platform.

[0007] Furthermore, a base is installed on one side of the magnetic powder brake, and the base is fixed to the optical platform. A connecting shaft is connected to the end of the magnetic powder brake away from the torque test disk. A second mechanism connecting flange is provided at the connection between the connecting shaft and the magnetic powder brake. An encoder bracket one and an encoder bracket two are connected to the end of the connecting shaft away from the magnetic powder brake. The ends of bracket one and encoder bracket two away from the connecting shaft are both connected to the optical platform.

[0008] Furthermore, the first mechanism connecting flange rotates in the outer cavity of the mechanism mounting plate via a coupling, and the first mechanism connecting flange is positioned on the coupling through eight sets of positioning holes evenly distributed on the outer ring to output and transmit torque vector.

[0009] Furthermore, the coupling is rotatably connected to the torque testing disk via bearings, and the magnetic powder brake is threadedly connected to the optical platform via a threaded sleeve. The outer ring of the torque testing disk is provided with a groove, and the inner cavity of the mechanism mounting disk is provided with a limiting groove. The limiting groove is based on the hook-lock principle to realize the connection and positioning with the weight at the testing end. When the magnetic powder brake is activated and drives the torque testing disk to rotate, a vector relationship is formed between the coupling and the dynamic torque sensor through axial transmission. The dynamic torque sensor transmits a signal and transmits the information to SPM-1-1A.

[0010] The beneficial effects of the present invention using the above structure are as follows: This solution proposes a spacecraft torque drive device, which uses a magnetic powder brake 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 a signal and transmits the information to the SPM-1-1A for continuous 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 driving of the spacecraft. Attached Figure Description

[0011] Figure 1 This is a cross-sectional view of a spacecraft torque drive device proposed in this invention.

[0012] Among them, 1. Encoder bracket one; 2. Encoder bracket two; 3. Connecting shaft; 4. Magnetic powder brake; 5. Torque test plate; 6. Coupling; 7. Dynamic torque sensor; 8. Mechanism connecting flange two; 9. Optical platform; 10. Mechanism connecting flange one; 11. Mechanism mounting plate; 12. SPM-1-1A; 13. Torque sensor mounting platform.

[0013] The accompanying drawings are provided to further illustrate the invention and form part of the specification. They are used together with the embodiments of the invention to explain the invention and do not constitute a limitation thereof. Detailed Implementation

[0014] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0015] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0016] like Figure 1As shown, this invention proposes a spacecraft torque drive device, including an SPM-1-1A12. The SPM-1-1A12 serves as the core drive unit of the device, employing a high-performance servo motor with high-precision speed control and stable torque output capability. A mechanism mounting plate 11 and a mechanism connecting flange 10 are coaxially connected to the SPM-1-1A12. The mechanism mounting plate 11 provides a stable mounting foundation for the device and is made of high-strength aluminum alloy, possessing excellent rigidity and lightweight characteristics. The mechanism connecting flange 10 is positioned above the mechanism mounting plate 11, serving as the output end of the device for connecting external spacecraft components. Its surface undergoes special treatment to enhance wear resistance and corrosion resistance. A second mechanism connecting flange 8 is coaxially connected to the end of the SPM-1-1A12 away from the first mechanism connecting flange 10. The second mechanism connecting flange 8 is used to connect power input or other auxiliary equipment, realizing power transmission and expanding the device's functionality. A coupling 6 is coaxially fixed on the connecting flange 10 of the mechanism. The coupling 6 is made of a highly elastic material, which has good shock absorption and the ability to compensate for the relative displacement of the two shafts, and is used to transmit mechanical motion. Two sets of couplings 6 are provided, and they are arranged at the upper and lower ends of the dynamic torque sensor 7 to ensure the stability and accuracy of torque transmission. The dynamic torque sensor 7 is a high-precision strain gauge sensor. With the synergistic effect of the couplings 6 at both ends, it can capture the real-time dynamic change trend of torque parameters during the rotation of the equipment in real time and accurately, and can quickly respond to small changes in torque. A torque sensing mounting platform 13 is provided on one side of the dynamic torque sensor 7. The torque sensing mounting platform 13 is made of high-strength engineering plastic, which has good insulation and shock absorption performance, and is used to fix the dynamic torque sensor 7 to ensure its installation stability. An optical platform 9 is connected to the side of the torque sensing mounting platform 13 away from the dynamic torque sensor 7. The optical platform 9 has extremely high flatness and stability, providing a high-precision installation reference surface for the entire device. The coupling 6 at the upper end of the dynamic torque sensor 7 is coaxially mounted with a torque testing disk 5. The surface of the torque testing disk 5 is specially processed to have high-precision flatness and roughness for accurate torque measurement. A magnetic powder brake 4 is coaxially mounted on the torque testing disk 5. The magnetic powder brake 4 serves as a load device, which can precisely control the magnitude of the applied torque. The magnetic powder brake 4 is positioned above the torque testing disk 5 for easy installation and maintenance.

[0017] The torque sensing mounting platform 13 secures the optical platform 9 using multiple high-strength bolts to ensure reliable connection. A dynamic torque bracket is fixedly connected to the side of the optical platform 9 furthest from the torque sensing mounting platform 13. This dynamic torque bracket, constructed of steel, provides excellent rigidity and supports and secures the optical platform 9, ensuring the stability of the entire device during operation.

[0018] A base made of cast iron is mounted on one side of the magnetic powder brake 4, providing excellent shock absorption. It is bolted to the optical platform 9 for fixation. A connecting shaft 3, made of high-strength alloy steel, is connected to the end of the magnetic powder brake 4 furthest from the torque testing disc 5. The connecting shaft 3 has sufficient strength and rigidity. A connecting flange 8 is provided at the connection point between the connecting shaft 3 and the magnetic powder brake 4 to ensure reliable connection and power transmission. Encoder bracket 1 and encoder bracket 2 are connected to the end of the connecting shaft 3 furthest from the magnetic powder brake 4. These brackets are used to mount encoders for accurate measurement of the rotational speed and angle of the connecting shaft 3. The ends of brackets 1 and 2 furthest from the connecting shaft 3 are both connected to the optical platform 9, ensuring the stability of the encoder installation and the accuracy of the measurement.

[0019] The connecting flange 10 rotates within the outer cavity of the mounting plate 11 via the coupling 6. The inner wall of the mounting plate 11 is precision-machined to fit with the coupling 6, ensuring smooth rotation. The connecting flange 10 is positioned on the coupling 6 via eight evenly distributed positioning holes on its outer ring, transmitting the torque vector and ensuring accurate torque transmission while facilitating installation and disassembly.

[0020] The coupling 6 is rotatably connected to the torque testing disk 5 via bearings. The bearings are high-precision rolling bearings with low friction coefficients and high rotational accuracy, ensuring the smooth rotation of the torque testing disk 5. The magnetic powder brake 4 is threadedly connected to the optical platform 9 via a threaded sleeve, facilitating its installation and adjustment. The outer ring of the torque testing disk 5 has grooves for convenient torque measurement and calibration. The inner cavity of the mounting disk 11 has a limiting groove based on a hook-lock principle, enabling connection and positioning with the test end weights. By adding weights of different weights, different load conditions can be simulated for performance testing of the device. When the magnetic powder brake 4 is activated and drives the torque testing disk 5 to rotate, a vector relationship is formed between the coupling 6 and the dynamic torque sensor 7 through axial transmission. The dynamic torque sensor 7 transmits a signal to the SPM-1-1A12. Based on the received torque signal, the SPM-1-1A12 adjusts the motor's output torque in real time, achieving closed-loop control and ensuring stable operation of the device.

[0021] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0022] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

[0023] The present invention and its embodiments have been described above. This description is not restrictive, and the accompanying drawings are only one embodiment of the present invention; the actual structure is not limited thereto. In conclusion, if those skilled in the art are inspired by this description and design similar structures and embodiments without departing from the spirit of the invention, such designs should fall within the protection scope of the present invention.

Claims

1. A spacecraft torque drive device, characterized in that: Includes SPM-1-1A(12), on which a mechanism mounting plate (11) and a mechanism connecting flange one (10) are coaxially connected. The mechanism connecting flange one (10) is located above the mechanism mounting plate (11) and is an output end. The end of the SPM-1-1A(12) away from the mechanism connecting flange one (10) is coaxially connected to a mechanism connecting flange two (8). A coupling (6) is coaxially fixed on the connecting flange (10) of the mechanism. The coupling (6) is used to transmit mechanical motion. There are two sets of couplings (6), which are arranged at the upper and lower ends of the dynamic torque sensor (7). Under the synergistic effect of the couplings (6) at both ends, the dynamic torque sensor (7) can capture the real-time dynamic change trend of torque parameters during the rotation of the equipment. A torque sensing mounting platform (13) is provided on one side of the dynamic torque sensor (7), and an optical platform (9) is connected to the side of the torque sensing mounting platform (13) away from the dynamic torque sensor (7). The coupling (6) at the upper end of the dynamic torque sensor (7) is coaxially mounted with a torque test disk (5), and a magnetic powder brake (4) is coaxially mounted on the torque test disk (5). The magnetic powder brake (4) is positioned above the torque test disk (5). The torque sensing mounting platform (13) fixes the optical platform (9), and a dynamic torque bracket is fixedly connected to the side of the optical platform (9) away from the torque sensing mounting platform (13). A base is installed on one side of the magnetic powder brake (4), and the base is fixed on the optical platform (9). A connecting shaft (3) is connected to the end of the magnetic powder brake (4) away from the torque test disk (5). A mechanism connecting flange (8) is provided at the connection between the connecting shaft (3) and the magnetic powder brake (4). An encoder bracket (1) and an encoder bracket (2) are connected to the end of the connecting shaft (3) away from the magnetic powder brake (4). The ends of the brackets (1) and the encoder brackets (2) away from the connecting shaft (3) are both connected to the optical platform (9). The first mechanism connecting flange (10) rotates in the outer cavity of the mechanism mounting plate (11) through the coupling (6). The first mechanism connecting flange (10) is positioned on the coupling (6) through 8 sets of positioning holes evenly distributed on the outer ring to output the torque vector. The coupling (6) is connected to the torque test disk (5) by bearing rotation. The magnetic powder brake (4) is connected to the optical platform (9) by threaded sleeve. The outer ring of the torque test disk (5) is provided with a groove. The inner cavity of the mechanism mounting disk (11) is provided with a limit groove. The limit groove is based on the hook lock principle to realize the connection and positioning with the test end weight. When the magnetic powder brake (4) is started and drives the torque test disk (5) to rotate, a vector relationship is formed between the coupling (6) and the dynamic torque sensor (7) through axial transmission. The dynamic torque sensor (7) transmits a signal and transmits the information to SPM-1-1A (12).

Images