Satellite reaction flywheel module

Abstract

The present invention provides a satellite reaction flywheel module, comprising a shell, a flexible support part and a locking support part, wherein the shell has a space for accommodating at least two groups of flywheel assemblies, the flexible support part is arranged inside the shell and the number of the flexible support parts is the same as the number of the flywheel assemblies, each flexible support part is connected to the shell and the end of each flexible support part has a center ring, each center ring is connected to a flywheel assembly, the locking support part comprises a locking member and a compression release ring of the same number as the flywheel assembly, each compression release ring is connected to a flywheel assembly through a corresponding connecting section, and the locking member makes each compression release ring in a compression state before working. The flywheel module of the present invention is lightweight and low-cost, reduces the installation time of the flywheel assembly, and can also meet the rapid deployment requirements of giant constellations.

Description

Technical Field

[0001] The present invention mainly relates to the technical field of satellite attitude control, and in particular to a satellite reaction flywheel module. Background Art

[0002] Satellite attitude control is a key technology to ensure that satellites fly in a predetermined attitude and orbit. It involves the orientation and rotation control of satellites. Satellite attitude control systems usually include three main parts: sensors, central computers, and actuators, which are responsible for signal measurement, signal processing, and control command execution. The key to satellite attitude control lies in accurate measurement and fast response. For example, communication satellites need to maintain a stable connection between the antenna and the ground base station, while scientific exploration satellites need to accurately align with the observation target. These tasks require satellite attitude control systems to provide high-precision and high-stability control.

[0003] With the development of technology, satellite attitude control systems are also constantly innovating. For example, magnetic torquers that use the earth's magnetic field to adjust attitude, or jet thrusters that use tiny thrusters for precise control, all play an important role in improving the performance and accuracy of satellite attitude control. At the same time, with the advancement of microelectronics technology, the size and weight of satellite attitude control systems are also constantly decreasing, which makes it possible to develop miniaturized satellites.

[0004] There are many methods for attitude control of orbiting satellites, such as spin stabilization and three-axis stabilization. The active three-axis attitude control system actuators are divided into two types: jet control and flywheel control. Other actuators are basically auxiliary devices such as magnetic torquers. Flywheel control uses the angular momentum stored in the flywheel to exchange angular momentum with the aircraft. It has the characteristics of low fuel consumption, high control accuracy, no environmental pollution, and long life. It has obvious advantages over other attitude control methods. In recent years, the accelerated development of civil aerospace requires lightweight, miniaturized, low-cost, integrated efficiency and high performance of satellite payloads. As a universal payload, the reaction flywheel has an even more urgent need for optimized design. Summary of the invention

[0005] The technical problem to be solved by the present invention is to provide a satellite reaction flywheel module which is lightweight and low-cost, reduces the installation time of the flywheel assembly, and can also meet the needs of rapid deployment of giant constellations.

[0006] In order to solve the above technical problems, the present invention provides a satellite reaction flywheel module, comprising: a shell, the interior of the shell having a space for accommodating at least two groups of flywheel assemblies; a flexible support portion, the flexible support portion is arranged inside the shell and the number of the flexible support portions is the same as the number of the flywheel assemblies, each of the flexible support portions is connected to the shell and the end of each of the flexible support portions has a center ring, and each of the center rings is connected to one of the flywheel assemblies; a locking support portion, the locking support portion includes a locking member and a compression release ring with the same number as the flywheel assemblies, each of the compression release rings is connected to one of the flywheel assemblies through a corresponding connecting section; the locking member enables each of the compression release rings to be in a compression state before working.

[0007] Optionally, the shell and the flexible support portion are an integrated component formed by 3D printing.

[0008] Optionally, the flexible support portion comprises a plurality of spokes, one end of the plurality of spokes is connected to the shell, and the other end of the plurality of spokes is connected to the central ring.

[0009] Optionally, in each of the flywheel assemblies, spokes corresponding to different flywheel assemblies have different cross-sections.

[0010] Optionally, in each of the flywheel assemblies, spokes corresponding to different flywheel assemblies have different topological configurations.

[0011] Optionally, the locking member includes a hot knife assembly and a rope used in conjunction with the hot knife assembly, wherein the rope causes each of the compression release rings to be in a compression state before operation.

[0012] Optionally, a base and a pressure cover are further provided inside the shell, wherein the base is located below all the compression and release rings, and the pressure cover is located above all the compression and release rings; one end of the rope is connected to the base, and the other end is connected to the pressure cover.

[0013] Optionally, the housing further comprises a first cover plate, and the first cover plate is used to seal a corresponding housing opening at the flywheel assembly.

[0014] Optionally, the housing further comprises a second cover plate, and the second cover plate is used to seal a corresponding housing opening at a location other than the flywheel assembly.

[0015] Optionally, two adjacent compression and release rings are in contact with each other via a limiting structure, and the limiting structure enables each compression and release ring to be in a coaxial position.

[0016] Optionally, in two adjacent compression and release rings, the compression and release ring located on the upper side has a protruding section located on the inner side, and the compression and release ring located on the lower side has a recessed section located on the inner side, and the protruding section and the recessed section constitute the limiting structure.

[0017] Compared with the prior art, the present invention has the following advantages: a space for accommodating at least two groups of flywheel assemblies is provided inside the shell, a flexible support portion is arranged inside the shell and the number of the flexible support portions is the same as the number of the flywheel assemblies, each flexible support portion is connected to the shell and the end of each flexible support portion has a center ring, each center ring is connected to a flywheel assembly, a locking support portion includes a locking member and a compression release ring which is the same in number as the flywheel assemblies, each compression release ring is connected to a flywheel assembly through a corresponding connecting section, the locking member puts each compression release ring in a compression state before working, and a plurality of independent flywheel assemblies are replaced by a set of modules to achieve the purpose of lightweight and low cost, reduce the installation time of the flywheel, and meet the needs of rapid deployment of giant constellations. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings are included to provide a further understanding of the present application. They are included and constitute a part of the present application. The accompanying drawings illustrate embodiments of the present application and together with the present specification serve to explain the principles of the present application. In the accompanying drawings:

[0019] Figure 1 It is a schematic diagram of the overall structure of a satellite reaction flywheel module according to an embodiment of the present invention;

[0020] Figure 2 It is a schematic diagram of the internal structure of a satellite reaction flywheel module according to an embodiment of the present invention;

[0021] Figure 3 It is a schematic structural diagram of a housing and a flexible support portion in a satellite reaction flywheel module according to an embodiment of the present invention;

[0022] Figure 4 It is a schematic diagram of the positional relationship between the flywheel components in a satellite reaction flywheel module according to an embodiment of the present invention;

[0023] Figure 5 It is a structural schematic diagram of a satellite reaction flywheel module having a first cover plate according to an embodiment of the present invention;

[0024] Figure 6 It is a structural schematic diagram of a satellite reaction flywheel module having a first cover plate and a second cover plate according to an embodiment of the present invention;

[0025] Figure 7 It is a cross-sectional schematic diagram of a locking support portion and related components in a satellite reaction flywheel module according to an embodiment of the present invention;

[0026] Figure 8It is a schematic diagram of a limiting structure in one embodiment of the present invention.

[0027] In the figure:

[0028] 110 - housing, 111 - first cover plate, 112 - second cover plate;

[0029] 120-flexible support portion, 121-center ring, 122-spokes;

[0030] 130-flywheel assembly;

[0031] 140-locking support portion, 141-compression release ring, 142-locking member, 143-connecting section;

[0032] 1421-hot knife assembly, 1422-rope;

[0033] 150-base;

[0034] 160- gland;

[0035] 170 - limiting structure, 171 - protruding section, 172 - recessed section. DETAILED DESCRIPTION

[0036] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for the description of the embodiments. Obviously, the drawings described below are only some examples or embodiments of the present application. For ordinary technicians in this field, the present application can also be applied to other similar scenarios based on these drawings without creative work. Unless it is obvious from the language environment or otherwise explained, the same reference numerals in the figures represent the same structure or operation.

[0037] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0038] refer to Figure 1~Figure 4As shown, the satellite reaction flywheel module of this embodiment mainly includes a shell 110, a flexible support portion 120 and a locking support portion 140. The shell 110 has a space for accommodating at least two groups of flywheel assemblies 130. The flexible support portion 120 is arranged inside the shell 110 and the number of the flexible support portions 120 is the same as the number of the flywheel assemblies 130. Each flexible support portion 120 is connected to the shell 110 and the end of each flexible support portion 120 has a center ring 121, and each center ring 121 is connected to a flywheel assembly 130. The locking support portion 120 includes a locking member 142 and a compression release ring 141 with the same number as the flywheel assembly 130. Each compression release ring 141 is connected to a flywheel assembly 130 through a corresponding connecting section 143. The locking member 142 puts each compression release ring 141 in a compression state before working.

[0039] The attitude control of a satellite is generally performed by installing multiple reaction flywheel assemblies 130. This method requires a large installation space, makes the overall mass of the satellite heavier, the cost higher, and takes a long time to integrate and install. It also requires a separately designed vibration isolation system and cannot meet the requirements of lightweight, low-cost and rapid deployment of future giant constellations.

[0040] In this embodiment, all flywheel assemblies 130 are placed in a housing 110, and each flywheel assembly 130 is installed centrally. In addition, multiple flywheel assemblies 130 can be uniformly coordinated and controlled through an integrated control drive assembly, thereby improving the integration of the flywheel module and reducing the investment cost. Before the satellite is launched, the locking member 142 in the locking support portion 120 applies a pre-tightening force to put each compression release ring 141 in a compressed state. After the satellite is launched into orbit, the ground sends a remote control command to unlock the locking member 142, then the pre-tightening force between each compression release ring 141 is released, and the rigid connection between the flywheel assembly 130 and the locking support portion 140 is released, and is only supported by the flexible support portion 120. A gap is generated between the unlocked compression release rings 141 to achieve micro-vibration isolation. Then, the satellite reaction flywheel module works normally to achieve satellite in-orbit attitude control.

[0041] In one example, the housing 110 and the flexible support portion 120 are an integrated component formed by 3D printing.

[0042] 3D printing is a manufacturing method that builds an object by adding materials layer by layer. It allows the digital model to be converted into a physical object through computer-aided design software. Its core principle is to add materials layer by layer to convert the digital design into a physical object. 3D printing brings many advantages to the manufacture of satellite devices, such as reducing costs, increasing production speed, and making the design more flexible. For example, 3D printing can produce lightweight structures such as lattice structures, which helps to reduce the weight of satellites, thereby reducing launch costs. 3D printing can realize the integrated manufacturing of structures, reduce the number of parts, simplify the assembly process, and improve the reliability of satellites. In this embodiment, the housing 110 and the flexible support portion 120 are combined into a whole by 3D printing, and the bonding force between the housing 110 and the flexible support portion 120 is improved, which is equivalent to the flywheel assembly 130 being directly installed on the housing 110, and the structure is more stable, and the satellite reaction flywheel module has a longer life in orbit. Of course, 3D printing can also be used to print other components of the satellite reaction flywheel module of this embodiment, such as the locking support portion 140, etc., which will not be repeated here.

[0043] In an example, the flexible support portion 120 includes a plurality of spokes 122 , one end of the plurality of spokes 122 is connected to the housing 110 , and the other end of the plurality of spokes 122 is connected to the central ring 121 .

[0044] Using spokes 122 as connecting parts between the shell 110 and the center ring 121 (or the flywheel assembly 130) can reduce the weight of the satellite reaction flywheel module, which means reducing the amount of material used, thereby reducing the launch cost. Spokes 122 usually have better mechanical properties, such as higher bending and torsion resistance, to meet the needs of satellites operating in harsh environments. If combined with 3D printing technology, using spokes 122 as connecting parts, more complex structures can be designed.

[0045] In one example, in each flywheel assembly 130, the spokes 122 corresponding to different flywheel assemblies 130 have different cross-sections. Furthermore, the spokes 122 corresponding to different flywheel assemblies 130 have different topological configurations.

[0046] In this embodiment, by changing the cross-section and topological configuration of the spokes 122 of different flywheel assemblies 130, the support frequencies of different flywheel assemblies 130 are different to avoid resonance caused by the same local frequency. Different cross-sections can be different shapes of the cross-sections or different sizes of the cross-sections. Different topological configurations can be different numbers of spokes 122 in each flywheel assembly 130 or different connection positions of each spoke 122. Thanks to 3D printing technology, the complex structure of these spokes 122 is also relatively easy to achieve, and the specific structure of the spokes will not be further described here.

[0047] In one example, the locking member 142 includes a hot knife assembly 1421 and a rope 1422 used in conjunction with the hot knife assembly 1421 , and the rope 1422 puts each compression release ring 141 in a compressed state before operation.

[0048] The hot knife assembly 1421 converts electrical energy into thermal energy, melts the high-strength rope 1422 to achieve unlocking, and has the characteristics of small impact, electromagnetic insensitivity, reusability and low cost. The core component of the hot knife assembly 1421 is the hot knife, which is composed of an electric heating element. The element can quickly heat up after power is turned on, heating and melting the rope 1422. In this embodiment, after the satellite is launched into orbit, the ground sends a remote control command, and the hot knife assembly 1421 melts the high-strength rope 1422, the preload between the compression release rings 141 is released, and the rigid connection between the flywheel assembly 130 and the locking support part 140 is released, and it is only supported by the flexible support part 120.

[0049] In one example, a base 150 and a pressure cover 160 are also provided inside the shell 110. The base 150 is located below all the compression and release rings 141, and the pressure cover 160 is located above all the compression and release rings 141. One end of the rope 1422 is connected to the base 150, and the other end is connected to the pressure cover 160.

[0050] refer to Figure 7 As shown, the pressure cover 160 is installed above all the compression release rings 141, the base 150 is installed below all the compression release rings 141, the lower part of the rope 1422 is connected to the base 150, and the upper part of the rope 1422 is connected to the pressure cover 160. After the connection is made in the above manner, all the compression release rings 141 are compressed together. When the hot knife assembly 1421 is powered on, the upper part of the rope 1422 is heated and melted, and the rope 1422 is disconnected from the pressure cover 160, and the pre-tightening force between the compression release rings 141 can be released.

[0051] In one example, the housing 110 further includes a first cover plate 111, which is used to seal the housing opening corresponding to the flywheel assembly 130. Further, the housing 110 further includes a second cover plate 112, which is used to seal the housing opening corresponding to the non-flywheel assembly 1230.

[0052] refer to Figure 5 and Figure 6 As shown, based on the shell 110 , the first cover plate 111 and the second cover plate 112 can be connected to the shell 110 by brazing, so that the shell 110 forms an internal sealed space to ensure the working environment of the flywheel assembly 130 .

[0053] In one example, two adjacent compression release rings 141 are in contact with each other through a limiting structure 170, and the limiting structure 170 makes each compression release ring 141 in a coaxial position. Further, among the two adjacent compression release rings 141, the compression release ring 141 located at the top has a protruding section 171 located at the inside, and the compression release ring 141 located at the bottom has a recessed section 172 located at the inside, and the protruding section 171 and the recessed section 172 form the limiting structure 170.

[0054] refer to Figure 8 As shown, since the clamping release ring 141 located below has a recessed section 172, the protruding section 171 is confined in the recessed section 172. This limiting structure 170 can also be called a conical stop, thereby preventing the clamping release ring 141 from shaking laterally and keeping each clamping release ring 141 in a coaxial position.

[0055] Taking the satellite reaction flywheel module with four flywheel assemblies 130 as an example, the locking support part 140 includes four compression release rings 141 with conical stoppers from top to bottom, each compression release ring 141 is connected to a corresponding connecting section 143, and each connecting section 143 is connected to a flywheel assembly 130. The compression release ring 141 is integrally formed by 3D printing to reduce the number of parts. After the satellite enters orbit, the compression release ring 141 is released, and there is a gap between each compression release ring 141, which decouples the connection between the flywheel assemblies 130 and realizes the micro-vibration isolation function of the flexible support part 120. The flywheel assembly 130 is usually composed of a flywheel body, a drive motor, a bearing assembly, etc. The bearing assembly plays a supporting role, and the drive motor provides power for the rotation of the flywheel body. The flywheel body rotates to output torque and angular momentum to provide drive for satellite attitude control.

[0056] In this embodiment, the integrated control drive assembly can be designed as one-to-four, that is, the power supply and control parts of the four drive controllers are integrated, and one controller controls four drivers at the same time to drive four flywheel assemblies 130, which is low-cost and highly integrated. The integrated control drive assembly can be connected to the inside of the housing 110 by screws without affecting other components.

[0057] In summary, the satellite reaction flywheel module of this embodiment adopts an integrated modular design, and the relevant components can be formed by 3D printing to minimize the number of parts and controllers. One set of flywheel modules replaces the functions of multiple flywheel assemblies 130, achieving lightweight and low cost, reducing the installation time of the flywheel, and meeting the needs of rapid deployment of giant constellations. The method of locking before entering orbit and releasing after entering orbit is adopted to reduce the support stiffness requirements of the flywheel assembly 130, making the satellite lighter, and realizing flexible support of the flywheel assembly 130, meeting the needs of micro-vibration isolation of the flywheel assembly 130 during rotation, and reducing the impact on other loads on the satellite. A heterogeneous support structure can be used to support the flywheel assembly 130, and the staggered frequency design of the flexible support portion 120 can be realized by changing the topological configuration of the flexible support portion 120, etc., to avoid resonance during the rotation of the flywheel assembly 130.

[0058] The basic concepts have been described above. Obviously, for those skilled in the art, the above invention disclosure is only used as an example and does not constitute a limitation of the present application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements and amendments to the present application. Such modifications, improvements and amendments are suggested in the present application, so such modifications, improvements and amendments still belong to the spirit and scope of the exemplary embodiments of the present application.

[0059] At the same time, the present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or more in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0060] Although the present application has been described with reference to the current specific embodiments, ordinary technicians in this technical field should recognize that the above embodiments are only used to illustrate the present application, and various equivalent changes or substitutions may be made without departing from the spirit of the present application. Therefore, as long as the changes and modifications to the above embodiments are within the essential spirit of the present application, they will fall within the scope of the claims of the present application.

Claims

1. A satellite reaction flywheel module, characterized in that: include: A housing, wherein the housing has a space for accommodating at least two flywheel assemblies; A flexible support portion, wherein the flexible support portion is disposed inside the housing and the number of the flexible support portions is the same as the number of the flywheel assemblies, each of the flexible support portions is connected to the housing and the end of each of the flexible support portions has a center ring, and each of the center rings is connected to one of the flywheel assemblies; The locking support portion includes a locking member and a number of compression release rings equal to the number of the flywheel assemblies, each of the compression release rings being connected to one of the flywheel assemblies via a corresponding connecting section; the locking member causes each of the compression release rings to be in a compression state before operation.

2. The satellite reaction flywheel module according to claim 1, characterized in that: The shell and the flexible support portion are an integrated component formed by 3D printing.

3. The satellite reaction flywheel module according to claim 1, characterized in that: The flexible support portion includes a plurality of spokes, one end of the plurality of spokes is connected to the housing, and the other end of the plurality of spokes is connected to the central ring.

4. The satellite reaction flywheel module according to claim 3, characterized in that: In each of the flywheel assemblies, spokes corresponding to different flywheel assemblies have different cross-sections.

5. The satellite reaction flywheel module according to claim 3, characterized in that: In each of the flywheel assemblies, spokes corresponding to different flywheel assemblies have different topological configurations.

6. The satellite reaction flywheel module according to claim 1, characterized in that: The locking member comprises a hot knife assembly and a rope used in conjunction with the hot knife assembly, wherein the rope enables each of the compression release rings to be in a compression state before operation.

7. The satellite reaction flywheel module according to claim 6, characterized in that: A base and a pressure cover are also provided inside the shell, wherein the base is located below all the compression and release rings, and the pressure cover is located above all the compression and release rings; one end of the rope is connected to the base, and the other end is connected to the pressure cover.

8. The satellite reaction flywheel module according to claim 1, characterized in that: The housing further comprises a first cover plate, and the first cover plate is used to seal a corresponding housing opening at the flywheel assembly.

9. The satellite reaction flywheel module according to claim 8, characterized in that: The housing further comprises a second cover plate, and the second cover plate is used for sealing a corresponding housing opening at a position other than the flywheel assembly.

10. The satellite reaction flywheel module according to claim 1, characterized in that: Two adjacent compression and release rings are in contact with each other via a limiting structure, and the limiting structure enables each compression and release ring to be in a coaxial position.

11. The satellite reaction flywheel module according to claim 10, characterized in that: In two adjacent compression and release rings, the compression and release ring located on the upper side has a protruding section located on the inner side, and the compression and release ring located on the lower side has a concave section located on the inner side, and the protruding section and the concave section constitute the limiting structure.

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