Satellite three-axis integrated reaction flywheel module
By using a satellite three-axis integrated reaction flywheel module, which employs a single motor to drive multiple flywheel switching and a 45-degree oblique mounting structure, the single-axis failure and redundant design problems of traditional satellite reaction flywheel systems are solved, achieving attitude control with high reliability, low energy consumption and convenient maintenance.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- SHANGHAI ZHONGCHEN XINWEI AEROSPACE TECHNOLOGY CO LTD
- Filing Date
- 2025-07-18
- Publication Date
- 2026-06-26
AI Technical Summary
Traditional satellite reaction flywheel systems suffer from single-axis failure risk, high cost and low reliability due to redundant design, and low utilization of computing resources, which affect the reliability and lifespan of satellite attitude control systems.
It adopts a satellite three-axis integrated reaction flywheel module, including a base module, a magnetless motor, a harmonic reducer, a wheel, and a square truncated pyramid. It switches between multiple flywheels by driving a single motor, and utilizes a 45-degree inclined flywheel structure and quick-release interface design, with integrated heat pipe heat dissipation, to achieve modularity and convenient maintenance.
It improves system reliability and lifespan, reduces control coupling, lowers energy consumption, facilitates on-orbit maintenance and replacement, and improves heat dissipation efficiency.
Smart Images
Figure CN224409632U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of satellite attitude control technology, and more specifically, to a satellite three-axis integrated reaction flywheel module. Background Technology
[0002] Satellite attitude control is a core technology system for spacecraft operation in orbit, and its control accuracy directly determines the effectiveness of missions such as Earth communication and space observation. Modern three-axis stabilized satellites generally use reaction wheels as the main actuators, achieving sub-arcsecond pointing accuracy through angular momentum exchange.
[0003] However, traditional flywheel systems face three major technical bottlenecks:
[0004] Firstly, the single-axis independent reaction flywheel architecture has the risk of single-point failure. Failure of a flywheel on one axis will lead to momentum saturation or attitude instability. According to statistics from the European Space Agency, about 23% of satellite anomalies are caused by single-axis failure of the actuator.
[0005] Secondly, the existing 1:1 corresponding drive circuit design requires a single satellite to be equipped with 4 dedicated control boards (including redundancy), which significantly increases the system weight and manufacturing cost.
[0006] Thirdly, the distributed architecture results in redundant computing resources. The utilization rate of the FPGA logic unit of the single-axis independent reaction flywheel is less than 40%, and the task load rate of the multi-core CPU is less than 30%. These technical bottlenecks have led to high costs and low reliability of the satellite attitude control system, seriously affecting the service life of the satellite.
[0007] With the rapid development of commercial spaceflight, the market has placed increasingly stringent demands on satellite attitude control components, including multi-dimensional performance standards such as low cost, high reliability, modularity, and long lifespan. As a key core component for attitude control, the traditional design of the satellite reaction wheel urgently needs innovation and improvement in this context.
[0008] Current reaction flywheel designs have many limitations in meeting the high-frequency launches and diverse mission requirements of commercial spaceflight, such as insufficient anti-interference capabilities and poor stable operation performance in complex orbital environments. Therefore, it is essential to further enhance the design of reaction flywheels by focusing on material selection, structural optimization, and control algorithm upgrades. This will align with the continuous iterative advancements in commercial spaceflight technology, providing robust and reliable attitude control guarantees for the long-term stable operation and precise mission execution of satellites in orbit, and propelling the space industry to new heights.
[0009] The preceding description is intended to provide general background information and does not necessarily constitute prior art. Utility Model Content
[0010] The purpose of this invention is to provide a satellite three-axis integrated reaction flywheel module that is more energy-efficient than traditional three-motor systems, reduces control coupling, facilitates on-orbit maintenance or replacement, improves heat dissipation efficiency, and extends flywheel life.
[0011] This utility model provides a satellite three-axis integrated reaction flywheel module, including a base module, a magnetless motor, a harmonic reducer, a wheel, a square truncated pyramid, and a reaction flywheel. A circular groove is provided in the center of the top of the base module, and the wheel is rotatably connected to the circular groove. Teeth are provided on the circumference of the wheel. The magnetless motor is connected to the side of the base module, and the output shaft of the magnetless motor is connected to the teeth of the wheel through the harmonic reducer to drive the wheel to rotate. The square truncated pyramid is connected to the top of the wheel, and quick-release interfaces are provided on all four sides of the square truncated pyramid. The reaction flywheel is connected to the side of the square truncated pyramid through the quick-release interfaces.
[0012] Using the above technical solution, during assembly, the non-magnetic motor is mounted on the side milled plane of the base module via a flange; the wheel and the non-magnetic motor shaft adopt an H7 / g6 transition fit, and the axial direction is limited by an E-type snap ring; the bottom surface of the square truncated pyramid is coated with silicone rubber and bonded to the wheel, and then fastened with 4×M4 screws; the reaction flywheel is embedded in the locating pin (2mm in diameter) on the side of the square truncated pyramid, and the screws are tightened twice in a cross sequence.
[0013] Furthermore, the interior of the regular square truncated pyramid is hollow with an opening at the top, and each side of the regular square truncated pyramid forms a 45-degree angle with the top of the wheel. The reaction flywheel is vertically connected to the center position of the side of the regular square truncated pyramid.
[0014] Furthermore, the axes of the four reaction flywheels intersect at a single point.
[0015] Furthermore, the four edges of the bottom surface of the regular square pyramid are provided with outwardly extending bosses, and the bosses are provided with mounting interfaces, through which the regular square pyramid is connected to the wheel.
[0016] Furthermore, the centerline of the square frustum coincides with the centerline of the wheel.
[0017] Furthermore, the reduction ratio of the harmonic reducer is 50:1.
[0018] This utility model provides a satellite three-axis integrated reaction flywheel module, which can switch between single motor and multiple flywheels. Only one non-magnetic motor is needed to drive the wheel, which can switch the working state of four reaction flywheels, making it more energy-efficient than the traditional three-motor system. The optimized 45-degree angled flywheel and the square truncated pyramid structure make the flywheel axis naturally aligned with the three axes of the satellite during rotation, reducing control coupling. The quick-release interface design on the side of the square truncated pyramid and the reaction flywheel fixed with anti-loosening screws facilitate on-orbit maintenance or replacement. The hollow upper opening design inside the square truncated pyramid and the integrated heat pipe inside improve heat dissipation efficiency and extend the life of the flywheel. Attached Figure Description
[0019] Figure 1 A schematic diagram of the structure of the satellite triaxial integrated reaction flywheel module provided in this embodiment of the utility model.
[0020] Figure 2 for Figure 1 A schematic diagram of the structure of the harmonic reducer and the wheel in the three-axis integrated reaction flywheel module of Zhongwei Satellite.
[0021] Figure 3 for Figure 1 A plan view of the square truncated pyramid of the three-axis integrated reaction flywheel module of Zhongwei Satellite.
[0022] Figure 4 for Figure 1 A schematic diagram of the square truncated pyramid structure of the three-axis integrated reaction flywheel module of Zhongwei Satellite.
[0023] Figure 5 for Figure 1 A top-view schematic diagram of the three-axis integrated reaction flywheel module of Zhongwei Satellite.
[0024] Figure 6 for Figure 1 A cross-sectional schematic diagram of the three-axis integrated reaction flywheel module of Zhongwei Satellite.
[0025] Figure 7 This is a schematic diagram of the flywheel mounting architecture of a traditional three-motor system.
[0026] Figure 8 for Figure 1 A schematic diagram of the flywheel installation orientation of the Zhongwei satellite three-axis integrated reaction flywheel module.
[0027] The reference numerals and components involved in the accompanying drawings are shown below:
[0028] 1. Base module; 11. Circular groove; 2. Magnetless motor.
[0029] 3. Harmonic reducer; 4. Wheel; 41. Gears
[0030] 5. Regular square pyramid 51. Quick-release interface 52. Boss
[0031] 53. Installation interface 6. Reaction flywheel Detailed Implementation
[0032] The specific embodiments of this utility model will be described in further detail below with reference to the accompanying drawings and examples. The following examples are used to illustrate this utility model, but are not intended to limit its scope.
[0033] The terms "first," "second," "third," "fourth," etc., used in the specification and claims of this utility model are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence.
[0034] Example 1
[0035] Figure 1 This is a structural schematic diagram of the satellite three-axis integrated reaction flywheel module provided in an embodiment of the present invention. Figure 2 for Figure 1 A schematic diagram of the structure of the harmonic reducer and the wheel in the three-axis integrated reaction flywheel module of Zhongwei Satellite. Figure 3 for Figure 1 A plan view of the square truncated pyramid of the Zhongweixing three-axis integrated reaction flywheel module. Please refer to... Figure 1 , Figure 2 , Figure 3 The satellite triaxial integrated reaction flywheel module provided in this embodiment includes a base module 1, a magnetless motor 2, a harmonic reducer 3, a wheel 4, a square truncated pyramid 5, and a reaction flywheel 6. A circular groove 11 is provided in the center of the top of the base module 1, and the wheel 4 is rotatably connected to the circular groove 11. Teeth 41 are provided on the circumference of the wheel 4. The magnetless motor 2 is connected to the side of the base module 1, and the output shaft of the magnetless motor 2 is connected to the teeth 41 of the wheel 4 through the harmonic reducer 3, thereby driving the wheel 4 to rotate. The reduction ratio of the harmonic reducer 3 is 50:1. The square truncated pyramid 5 is connected to the top of the wheel 4, and quick-release interfaces 51 are provided on all four sides of the square truncated pyramid 5. The reaction flywheel 6 is connected to the side of the square truncated pyramid 5 through the quick-release interfaces 51.
[0036] Figure 4 for Figure 1 A schematic diagram of the square truncated pyramid structure of the Zhongwei Satellite three-axis integrated reaction flywheel module. Figure 5 for Figure 1 A top-view schematic diagram of the Zhongweixing three-axis integrated reaction flywheel module. Figure 6 for Figure 1 A cross-sectional schematic diagram of the Zhongweixing three-axis integrated reaction flywheel module. Please refer to... Figure 4 , Figure 5 , Figure 6 The square truncated pyramid 5 of this invention is hollow inside with an open top. Each side of the square truncated pyramid 5 forms a 45-degree angle with the top of the wheel 4. The reaction flywheel 6 is vertically connected to the center of the side of the square truncated pyramid 5. Furthermore, the axes of the four reaction flywheels 6 intersect at a single point. The centerline of the square truncated pyramid 5 coincides with the centerline of the wheel 4. Furthermore, the four edges of the bottom surface of the square truncated pyramid 5 are provided with outwardly extending bosses 52. The bosses 52 are provided with mounting interfaces 53, through which the square truncated pyramid 5 is connected to the wheel 4.
[0037] It should be noted that the base module 1 is a square aluminum alloy frame; the advantage of the magnetless motor 2 is that it avoids the risk of permanent magnets falling off during high-speed rotation, making it more suitable for high-speed flywheel operation and reducing maintenance costs; the four reaction flywheels 6 of this utility model module are controlled by a common magnetless motor 2. When one flywheel fails, the magnetless motor can be started to switch to another flywheel in a clockwise / counterclockwise direction; the wheel 4 is a titanium alloy disc, connected to the shaft of the magnetless motor 2 through a harmonic reducer 3 (reduction ratio 50:1), with an axial clearance of <0.01mm; the wheel 4 is controlled by the magnetless motor 2. The core is to drive the flywheel to store / release kinetic energy through the generation and regulation of electromagnetic torque. Its advantages are high speed, reliability, low maintenance and adaptability. The square truncated pyramid 5 is made of carbon fiber with a 45-degree slope on all four sides. The bottom surface has a boss 52 on the four sides, and the boss 52 has a reserved mounting interface 53 (M4 threaded hole). The inside of the square truncated pyramid 5 is a hollow shape like a small square truncated pyramid. The center of the four faces inside the square truncated pyramid 5 has a quick-release interface 51 for connecting with the reaction flywheel 6. The quick-release interface 51 fixes the reaction flywheel 6 to the center of the four faces outside the square truncated pyramid 5 with four screws.
[0038] Assembly process of this utility model:
[0039] The non-magnetic motor 2 is mounted on the side milled plane of the base module 1 via a flange; the wheel 4 and the shaft of the non-magnetic motor 2 adopt an H7 / g6 transition fit, and the axial direction is limited by an E-type snap ring; the bottom surface of the square truncated pyramid 5 is coated with silicone rubber and bonded to the wheel 4, and then fastened with 4×M4 screws; the reaction flywheel 6 is embedded in the positioning pin (diameter 2mm) on the side of the square truncated pyramid 5, and the screws are tightened twice in a cross sequence;
[0040] This utility model's reaction flywheel module features single-motor multi-flywheel switching. Only one non-magnetic motor 2 drives the wheel 4 to switch the working states of the four reaction flywheels 6, making it more energy-efficient than traditional three-motor systems. The optimized 45-degree angled flywheel design and the truncated square prism 5 structure ensure that the flywheel axis naturally aligns with the satellite's three axes during rotation, reducing control coupling. The quick-release interface 51 on the side of the truncated square prism 5 allows the reaction flywheels 6 to be secured with anti-loosening screws, facilitating on-orbit maintenance or replacement. The hollow interior and open upper end of the truncated square prism 5 integrate heat pipes, improving heat dissipation efficiency and extending flywheel life.
[0041] Example 2
[0042] Figure 7 This is a schematic diagram of a traditional three-motor system with a flywheel mounting architecture. Figure 8 for Figure 1 A schematic diagram showing the flywheel installation orientation of the Zhongweixing three-axis integrated reaction flywheel module. Please refer to... Figure 7 , Figure 8 In this embodiment, the four reaction flywheels 6 are named flywheel A, flywheel B, flywheel C, and flywheel D, respectively. The bottom surfaces of flywheels A, B, C, and D are respectively... Figure 8 The corresponding arrows are perpendicular, and the arrows lie in the plane formed by any two axes, with the perpendicular component of this plane forming a 45-degree angle with both axes. Each flywheel is installed at the center of the plane formed by the X, Y, and Z axes (e.g., ...). Figure 8 (As shown).
[0043] Figure 7 In traditional three-motor systems with a flywheel-mounted architecture, the angular momentum of the three flywheels is equal to the angular momentum of their respective axes. If one flywheel fails, the angular momentum of that axis becomes zero. This utility model's integrated three-axis variable-reaction flywheel module avoids the inconvenience of a single flywheel failure paralyzing the entire device. Because all four reaction flywheels 6 have angular momentum components on each of the three axes, it prevents the situation where the angular momentum of a certain axis becomes zero due to the malfunction of one or more reaction flywheels 6. The principle is as follows:
[0044] Angular momentum is an important physical quantity describing the rotational motion of a reaction flywheel. The direction of angular momentum is perpendicular to the mounting surface, and its basic formula is:
[0045] H = J * ω, where H represents angular momentum (unit: kg·m) 2 / s or N·m·s);
[0046] J represents the moment of inertia (unit: kg·m) 2 );
[0047] ω represents angular velocity (unit: rad / s);
[0048] The components of the angular momentum of any flywheel along the three axes can be calculated using the following formulas. For example, the angular momentum components of the reaction flywheel A along the three axes are shown in the following formulas:
[0049] H ZA =H A *cos45°;
[0050] H XA =H A *cos45°+tan 45°;
[0051] H YA =H A *cos45°+sin 2 45°;
[0052] The same logic applies to the other three reaction flywheels. Therefore, the sum of the angular momentum of the four flywheels on the three axes can be derived, as shown in the following formula:
[0053] H Z =H ZA +H ZB +H ZC +H ZD ;
[0054] H X =H XA +H XB +H XC +H XD ;
[0055] H Y =H YA +H YB +H YC +H YD .
[0056] As can be seen from the above description, the advantages of this utility model are:
[0057] 1. The satellite three-axis integrated reaction flywheel module of this utility model can switch between single motor and multiple flywheels. Only one non-magnetic motor is needed to drive the wheel to switch the working state of four reaction flywheels, which is more energy-efficient than the traditional three-motor system.
[0058] 2. The satellite three-axis integrated reaction flywheel module of this utility model features a 45-degree angled flywheel optimization and a regular square truncated pyramid structure that allows the flywheel axis to naturally align with the three axes of the satellite during rotation, reducing control coupling.
[0059] 3. The satellite triaxial integrated reaction flywheel module of this utility model has a quick-release interface design on the side of the square truncated pyramid, and the reaction flywheel is fixed by anti-loosening screws, which facilitates on-orbit maintenance or replacement.
[0060] 4. The satellite three-axis integrated reaction flywheel module of this utility model has a hollow upper opening design inside the square truncated pyramid, and the heat pipe is integrated inside the square truncated pyramid to improve heat dissipation efficiency and extend the life of the flywheel.
[0061] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the protection scope of the claims.
Claims
1. A satellite three-axis integrated reaction flywheel module, characterized in that, It includes a base module (1), a non-magnetic motor (2), a harmonic reducer (3), a wheel (4), a square truncated pyramid (5), and a reaction flywheel (6); The base module (1) has a circular groove (11) in the middle, and the wheel (4) is rotatably connected in the circular groove (11). The wheel (4) has teeth (41) on its circumference. The non-magnetic motor (2) is connected to the side of the base module (1). The output shaft of the non-magnetic motor (2) is connected to the teeth (41) of the wheel (4) through the harmonic reducer (3) to drive the wheel (4) to rotate. The regular square truncated pyramid (5) is connected to the top of the wheel (4). The four sides of the regular square truncated pyramid (5) are provided with quick-release interfaces (51). The reaction flywheel (6) is connected to the side of the regular square truncated pyramid (5) through the quick-release interfaces (51).
2. The satellite three-axis integrated reaction flywheel module according to claim 1, characterized in that, The regular square truncated pyramid (5) is hollow inside with an opening at the top. Each side of the regular square truncated pyramid (5) forms a 45-degree angle with the top of the wheel (4). The reaction flywheel (6) is vertically connected to the center of the side of the regular square truncated pyramid (5).
3. The satellite three-axis integrated reaction flywheel module according to claim 2, characterized in that, The axes of the four reaction flywheels (6) intersect at a single point.
4. The satellite three-axis integrated reaction flywheel module according to claim 1, characterized in that, The four sides of the bottom surface of the regular square truncated pyramid (5) are provided with outwardly extending bosses (52), and the bosses (52) are provided with mounting interfaces (53). The regular square truncated pyramid (5) is connected to the wheel (4) through the mounting interfaces (53).
5. The satellite three-axis integrated reaction flywheel module according to claim 1, characterized in that, The centerline of the square truncated pyramid (5) coincides with the centerline of the wheel (4).
6. The satellite three-axis integrated reaction flywheel (6) module according to claim 1, characterized in that, The reduction ratio of the harmonic reducer (3) is 50:1.