Hyperstatic satellite dynamic and static partition multi-stage vibration isolation configuration
By adopting a multi-level vibration isolation configuration with dynamic and static partitioning of the ultra-quiet satellite, and using modular design and multi-level vibration isolation technology, the problem of the impact of satellite micro-vibration on the main payload is solved, providing a quiet working environment and meeting the performance requirements of the main payload.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-10
- Publication Date
- 2026-04-10
AI Technical Summary
Existing satellite configuration designs cannot effectively reduce the impact of micro-vibrations on the main payload. In particular, as satellite functions improve, the sensitivity of the main payload to micro-disturbances of the platform and the main payload increases, resulting in larger micro-vibration disturbances that affect the normal operation of the main payload.
The system adopts a multi-level vibration isolation configuration with dynamic and static partitioning of the ultra-quiet satellite. The platform and main load are partitioned through modular design. Flexible and rigid connection devices are used in combination with vibration isolators to achieve multi-level vibration isolation and reduce the transmission of micro-vibrations. This includes arranging large flexible deployable equipment outside the platform module and arranging micro-vibration source equipment inside. After entering orbit, the rigid connection is unlocked, and only the flexible connection is retained.
It achieves multi-level vibration isolation for micro-vibrations, reduces the impact of platform micro-vibrations on the main load, provides a quiet working environment, ensures the performance indicators of the main load, and provides movement space for large flexible equipment.
Smart Images
Figure CN121822855A_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of satellite configuration design technology, and in particular relates to a multi-level vibration isolation configuration for an ultra-quiet satellite with dynamic and static partitioning. Background Technology
[0002] As satellite performance improves, satellite payloads, especially those of remote sensing satellites, become more sensitive to micro-disturbances (vibrations with accelerations in the mg range or below are generally referred to as micro-vibrations) in the satellite platform and its own moving components. Simultaneously, due to these improved performance, the size and scale of platform actuators are increasing, leading to even greater micro-vibration disturbances. Furthermore, large flexible components and mechanisms on the satellite, due to their low frequencies and mechanical movements, will also cause disturbances to the payload. Therefore, there is an urgent need to design a new satellite configuration to provide a "quiet" operating environment for the satellite payload. Summary of the Invention
[0003] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a multi-level vibration isolation configuration for ultra-quiet satellites with dynamic and static partitioning. It implements modular design for dynamic and static partitioning and multi-level vibration isolation design for micro-vibration disturbance sources, providing a "quiet" working environment for the payload and ensuring the performance indicators of the payload.
[0004] To address the aforementioned technical problems, this invention discloses a multi-level vibration isolation configuration for an ultra-quiet satellite, comprising: a platform module, a main payload module, and isolators A, a flexible connection device, a rigid connection unlocking device, and isolator B. The platform module and the main payload module are connected via the flexible connection device and the rigid connection unlocking device. A large, flexible, deployable device is arranged on the outer surface of the platform module. A platform micro-vibration source device is arranged inside the platform module and connected to it via isolator A. A main payload module micro-vibration source device is arranged inside the main payload module and connected to it via isolator B.
[0005] In the above-mentioned multi-level vibration isolation configuration of the ultra-quiet satellite with dynamic and static partitioning, after the satellite enters orbit, the rigid connection unlocking device is unlocked, creating a gap at the connection between the platform module and the main payload module, and only the flexible connection device plays a connecting role.
[0006] In the aforementioned multi-level vibration isolation configuration of the ultra-quiet satellite with dynamic and static partitions, during satellite launch, the large flexible deployable device retracts and presses against the outer surface of the platform module; after the satellite enters orbit, the large flexible deployable device unlocks and deploys.
[0007] In the aforementioned multi-level vibration isolation configuration of the ultra-quiet satellite with dynamic and static partitioning, the rigid connection unlocking device includes: an upper flange, a segmented pad, a lower flange, a pyrotechnic connecting bolt, a storage spring A, a storage spring B, and a storage spring C; wherein, the upper flange is connected to the main load module, the lower flange is connected to the platform module, the segmented pad is arranged between the upper flange and the lower flange, and the upper flange and the lower flange are connected as a whole by the pyrotechnic connecting bolt; the storage spring A is sleeved on the outside of the segmented pad; one end of the storage spring B is connected to the lower surface of the segmented pad, and the other end is connected to the lower flange; one end of the storage spring C is connected to the pyrotechnic connecting bolt, and the other end is connected to the platform module.
[0008] In the above-mentioned multi-level vibration isolation configuration of the ultra-quiet satellite dynamic and static partition, the segmented pad has a segmented structure with gaps between each segment to ensure that it can be folded inward laterally.
[0009] In the aforementioned multi-level vibration isolation configuration of the ultra-quiet satellite with dynamic and static partitioning, the working principle of the rigid connection unlocking device is as follows: After the satellite enters orbit, the pyrotechnic connection bolts are unlocked and disconnected, releasing the constraints on the upper flange, the segmented gasket, and the lower flange; the segmented gasket moves laterally inward under the action of the storage spring A, and then moves downward under the action of the storage spring B, finally being stored in the lower flange; at the same time, the disconnected part of the pyrotechnic connection bolt moves downward under the action of the storage spring C; finally, a gap is generated at the connection between the platform module and the main load module, and only the flexible connection device plays a connecting role.
[0010] The present invention has the following advantages: (1) This invention discloses a multi-level vibration isolation configuration for a super-quiet satellite with dynamic and static partitioning. It adopts a modular partitioning configuration design and realizes the connection between the satellite platform and the main payload through a rigid connection + flexible connection method. After the satellite enters orbit, the rigid connection is unlocked, and only the flexible connection plays a connecting role, thereby reducing the impact of platform micro-vibration on the operation of the main payload.
[0011] (2) This invention discloses a multi-level vibration isolation configuration for dynamic and static partitioning of an ultra-quiet satellite. For the micro-vibration source of the platform, on the basis of direct passive vibration isolation of the source, it further combines the technical approach of "flexible connection between the main load module and the platform module" to carry out secondary vibration isolation, so as to minimize the impact of its micro-vibration on the operation of the main load.
[0012] (3) The present invention discloses a multi-level vibration isolation configuration for dynamic and static partitioning of an ultra-quiet satellite, which arranges large flexible deployable equipment on the outer surface of the platform module to increase its micro-vibration transmission path and reduce its impact on the main load.
[0013] (4) This invention discloses a multi-level vibration isolation configuration for a super-quiet satellite with dynamic and static partitions. It provides vibration isolation for the micro-vibration sources inside the main load to reduce the impact of micro-vibration on its own operation.
[0014] (5) The present invention discloses a multi-level vibration isolation configuration for dynamic and static partitioning of an ultra-quiet satellite. After the rigid connection unlocking device is unlocked, a gap can be formed between the platform module and the main load module, realizing a contactless connection between the platform module and the main load module (except for the flexible connection), avoiding the transmission of micro-vibrations through structural contact, and providing motion space for the flexible connection device with active adjustment of direction function. Attached Figure Description
[0015] Figure 1 This is a structural schematic diagram of a multi-level vibration isolation configuration for an ultra-quiet satellite with dynamic and static partitioning, as described in an embodiment of the present invention. Figure 2 This is a structural schematic diagram of a rigid connection unlocking device (before unlocking) in an embodiment of the present invention; Figure 3 This is a schematic diagram of the structure of a rigid connection unlocking device (after unlocking) in an embodiment of the present invention. Detailed Implementation
[0016] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments disclosed in the present invention will be described in further detail below with reference to the accompanying drawings.
[0017] Reference Figure 1 In this embodiment, the ultra-quiet satellite dynamic and static partition multi-level vibration isolation configuration includes: platform module 1, main load module 2, through vibration isolator A8, flexible connection device 9, rigid connection unlocking device 10 and vibration isolator B11.
[0018] The satellite adopts a modular configuration, divided into a platform module 1 and a main payload module 2. Platform module 1 and main payload module 2 are connected via a flexible connection device 9 and a rigid connection unlocking device 10. After the satellite enters orbit, the rigid connection unlocking device 10 unlocks, creating a gap at the connection between platform module 1 and main payload module 2, with only the flexible connection device 9 serving as the connection. Large, flexible, deployable equipment that may cause micro-vibrations is placed on the outer surface of platform module 1. Platform micro-vibration source equipment 6, which may cause micro-vibrations, is placed inside platform module 1 and connected to it via vibration isolator A8 to reduce the transmission of micro-vibrations from platform micro-vibration source equipment 6 to platform module 1. Main payload module micro-vibration source equipment 7 is placed inside main payload module 2 and connected to it via vibration isolator B11 to reduce the transmission of micro-vibrations from main payload module micro-vibration source equipment 7 to main payload module 2.
[0019] In this embodiment, during satellite launch, the large flexible deployable device folds up and is pressed tightly against the outer surface of platform module 1; after the satellite enters orbit, the large flexible deployable device is unlocked and deployed. The large flexible deployable device includes, but is not limited to, solar panels 3, antenna A4, and antenna B5; solar panels 3 are arranged on the outer surface of platform module 1, located on the ±Y side, folded and pressed tightly during satellite launch, and unlocked and deployed in the ±Y direction after entering orbit; antennas A4 and B5 are arranged on the outer surface of platform module 1, located on the ±X side, in a pressed-tight state during satellite launch, and unlocked and deployed in the ±Z direction after entering orbit.
[0020] In this embodiment, the platform micro-vibration source device 6 is centrally located inside the platform module 1. The platform micro-vibration source device 6 includes, but is not limited to, control moment gyroscopes, momentum wheels, etc. For example, a satellite may be equipped with six control moment gyroscopes, arranged in a typical pentagonal pyramidal configuration. These gyroscopes are centrally mounted inside the platform module 1 via vibration isolators A. The micro-vibrations generated by the control moment gyroscopes are attenuated by vibration isolators A, significantly reducing the micro-vibrations transmitted to the platform module 1.
[0021] In this embodiment, the micro-vibration source device 7 of the main load module includes, but is not limited to, an infrared refrigerator, etc. The infrared refrigerator is usually located near the infrared detector, and the high-frequency micro-vibration it generates will have a serious impact on the imaging of the infrared detector. Micro-vibration isolation is required. It is installed inside the main load module 2 through a vibration isolator B. After the micro-vibration generated by the infrared refrigerator is attenuated by the vibration isolator B, the micro-vibration transmitted to the main load module 2 is greatly reduced, which meets the imaging requirements of the infrared detector.
[0022] In this embodiment, as Figure 2 As shown, the rigid connection unlocking device 10 mainly includes: an upper flange 12, a segmented pad 13, a lower flange 14, a pyrotechnic connection bolt 15, a storage spring A16, a storage spring B17, and a storage spring C18. The upper flange 12 is connected to the main load module 2, and the lower flange 14 is connected to the platform module 1. The segmented pad 13 is arranged between the upper flange 14 and the lower flange 14, and the upper flange 12 and the lower flange 14 are connected as a whole by the pyrotechnic connection bolt 15, used to bear the gravity of the main load during satellite launch and ground phases. The segmented pad 13 has a segmented structure with gaps between each segment to ensure lateral inward storage. The storage spring A16 is fitted onto the outside of the segmented pad 13. One end of the storage spring B17 is connected to the lower surface of the segmented pad 13, and the other end is connected to the lower flange 14. One end of the storage spring C18 is connected to the pyrotechnic connection bolt 15, and the other end is connected to the platform module 1.
[0023] Furthermore, the working principle of the rigid connection unlocking device 10 is as follows: After the satellite enters orbit, the pyrotechnic connection bolt 15 is unlocked and disconnected, releasing the constraints on the upper flange 12, the segmented gasket 13, and the lower flange 14; the segmented gasket 13 moves laterally inward under the action of the storage spring A16, and then moves downward under the action of the storage spring B17, finally being stored in the lower flange 14; at the same time, the disconnected part of the pyrotechnic connection bolt moves downward under the action of the storage spring C18; finally, a gap is generated at the connection between the platform module 1 and the main load module 2, and only the flexible connection device 9 plays a connecting role, such as... Figure 3 As shown.
[0024] In this embodiment, the electrical connection (such as power, signal, data, etc.) between platform module 1 and main load module 2 can be made using either wireless or wired connectors. The electrical connection (such as power, signal, etc.) between platform micro-vibration source device 6 and platform module 1 can also be made using either wireless or wired connectors.
[0025] Based on the above embodiments, the following detailed description will be provided using an optical satellite as an example.
[0026] For a specific optical satellite, it is divided into two main modules: the satellite platform and the optical camera. The satellite platform serves as the platform module, and the optical camera as the main payload module. Furthermore, an ultra-quiet platform is selected as the flexible connection device. Therefore: The satellite platform and the optical camera are connected via an ultra-quiet platform and a rigid connection unlocking device. During launch, the rigid connection unlocking device is locked, bearing the weight of the optical camera, while the ultra-quiet platform does not bear this weight. After the optical satellite enters orbit, the rigid connection unlocking device unlocks, creating an unlocking gap, at which point the ultra-quiet platform becomes the connecting element. In addition to its micro-vibration isolation function, which isolates micro-vibrations generated by the satellite platform and minimizes their impact on the optical camera's imaging, the ultra-quiet platform also possesses active, rapid, and high-precision attitude adjustment capabilities, improving the satellite's attitude readjustment and stability. Due to the ultra-quiet platform's strong micro-vibration isolation and active control capabilities, the electrical connection between the satellite platform and the optical camera can be wired.
[0027] Furthermore, for optical satellites, the specific source of micro-vibration on the platform refers to the control moment gyroscope. Since the control moment gyroscope generates relatively strong micro-vibrations, secondary micro-vibration isolation is required. This involves connecting the control moment gyroscope to the satellite platform via a vibration isolator to minimize the transmission of its micro-vibrations. Because the control moment gyroscope has relatively few electrical connection cables and the impact of micro-vibration transmission is acceptable, a wired connection can be used between the control moment gyroscope and the satellite platform.
[0028] Furthermore, for optical satellites, large flexible deployable equipment specifically includes: solar panels and antennas, etc.; wherein, the solar panels and antennas are arranged on the outer surface of the satellite platform; when the optical satellite is launched, the solar panels and antennas are retracted and pressed against the outer surface of the satellite platform; after the optical satellite enters orbit, the solar panels and antennas are unlocked and deployed.
[0029] As shown above, the micro-vibrations of the control moment gyroscope after vibration isolation, as well as the micro-vibrations generated by the unlocking and deployment of the solar array and antenna, will be attenuated again after passing through the ultra-quiet platform, and the impact on the imaging of the optical camera is acceptable.
[0030] Furthermore, for optical satellites, the micro-vibration source equipment of the main payload module specifically refers to the infrared camera cooler. The infrared camera cooler is a strong micro-vibration source, and its micro-vibration will have a significant impact on the imaging of the optical camera. The infrared camera cooler is required to be placed near the infrared detector of the optical camera. Therefore, it is connected to the optical camera through vibration isolator B to reduce the impact of the infrared camera cooler on the micro-vibration imaging of the optical camera.
[0031] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.
[0032] The contents not described in detail in this specification are common knowledge to those skilled in the art.
Claims
1. A multi-level vibration isolation configuration for ultra-quiet satellites with dynamic and static partitioning, characterized in that, include: Platform module (1), main load module (2), and vibration isolator A (8), flexible connection device (9), rigid connection unlocking device (10) and vibration isolator B (11); wherein, platform module (1) and main load module (2) are connected by flexible connection device (9) and rigid connection unlocking device (10); large flexible deployable equipment is arranged on the outer surface of platform module (1); platform micro vibration source device (6) is arranged inside platform module (1) and connected to platform module (1) through vibration isolator A (8); main load module micro vibration source device (7) is arranged inside main load module (2) and connected to main load module (2) through vibration isolator B (11).
2. The multi-level vibration isolation configuration for ultra-quiet satellites with dynamic and static partitioning according to claim 1, characterized in that, After the satellite enters orbit, the rigid connection unlocking device (10) is unlocked, creating a gap at the connection between the platform module (1) and the main payload module (2), and only the flexible connection device (9) serves as the connection.
3. The multi-level vibration isolation configuration for ultra-quiet satellites with dynamic and static partitioning according to claim 1, characterized in that, When the satellite is launched, the large flexible deployable device is retracted and pressed against the outer surface of the platform module (1); after the satellite enters orbit, the large flexible deployable device is unlocked and deployed.
4. The multi-level vibration isolation configuration for ultra-quiet satellites with dynamic and static partitioning according to claim 1, characterized in that, The rigid connection unlocking device (10) includes: an upper flange (12), a split-type pad (13), a lower flange (14), a flame-connecting bolt (15), a storage spring A (16), a storage spring B (17), and a storage spring C (18); wherein, the upper flange (12) is connected to the main load module (2), the lower flange (14) is connected to the platform module (1), the split-type pad (13) is arranged between the upper flange (14) and the lower flange (14), and the upper flange (12) and the lower flange (14) are connected to each other by the flame-connecting bolt (15) to form an integral whole; the storage spring A (16) is sleeved on the outside of the split-type pad (13); one end of the storage spring B (17) is connected to the lower surface of the split-type pad (13), and the other end is connected to the lower flange (14); one end of the storage spring C (18) is connected to the flame-connecting bolt (15), and the other end is connected to the platform module (1).
5. The multi-level vibration isolation configuration for ultra-quiet satellites with dynamic and static partitioning according to claim 4, characterized in that, The segmented pad (13) has a segmented structure with gaps between each segment to ensure that it can be stored horizontally inward.
6. The multi-level vibration isolation configuration for ultra-quiet satellites with dynamic and static partitioning according to claim 4, characterized in that, The working principle of the rigid connection unlocking device (10) is as follows: After the satellite enters orbit, the pyrotechnic connection bolt (15) is unlocked and disconnected, releasing the constraints on the upper flange (12), the split-type pad (13), and the lower flange (14); the split-type pad (13) moves laterally inward under the action of the storage spring A (16), and then moves downward under the action of the storage spring B (17), and finally is stored in the lower flange (14); at the same time, the disconnected part of the pyrotechnic connection bolt moves downward under the action of the storage spring C (18); finally, a gap is generated at the connection between the platform module (1) and the main load module (2), and only the flexible connection device (9) plays a connecting role.