Lighting power supply controller and anti-vibration base used in manned spacecraft cabin

Abstract

The utility model discloses a lighting power supply controller used in a manned spacecraft cabin and an anti-vibration base, the lighting power supply controller comprises a controller housing, and a power supply module and a signal communication module which are arranged in the controller housing, the power supply module is provided with a spectrum adjusting circuit, and high color rendering spectrum output is realized by mixing white light and yellow light; the signal communication module comprises a wireless signal amplifying and transmitting circuit, mounting lugs are respectively arranged on the controller shell, mounting through holes are formed in the mounting lugs, anti-vibration bases with axial and radial buffering are mounted on the mounting through holes, and connecting interfaces are formed in the two sides of the controller shell. The utility model aims to provide the lighting power supply controller and the vibration-proof base for the manned spacecraft cabin, which integrate high-color-rendering spectrum output, low-flicker eye protection design and vibration-proof structure optimization, and on the basis of meeting the requirements of high-color-rendering and low-flicker eye protection of lighting in the cabin, high-efficiency power supply, reliable communication and excellent vibration-proof capability are realized; and a safe and comfortable lighting environment is provided for astronauts.

Description

Technical Field

[0001] This utility model relates to the field of spacecraft lighting accessories, and in particular to a power controller and vibration-resistant base for lighting inside a manned spacecraft cabin. Background Technology

[0002] In the design and operation of manned spacecraft, the stability of the cabin environment is crucial to the work and life of astronauts. In particular, the health and comfort of astronauts are often among the primary considerations in the design. As a vital component of the cabin, the lighting system must not only meet basic lighting needs but also consider the long-term use by astronauts. When astronauts work for extended periods inside the spacecraft, facing artificial light sources, especially LED lighting, insufficient color rendering index or excessive flicker can cause eye discomfort, fatigue, and even affect visual health. Therefore, to avoid eye fatigue and vision impairment, the spacecraft's lighting system must provide a spectrum with high color rendering index and high color saturation. This not only more closely resembles natural light but also reduces the strain on the eyes from prolonged illumination. Furthermore, the stability of the light source is also key to eye-care design; avoiding flicker is an effective way to reduce eye fatigue. Therefore, the lighting power controller should adopt a low flicker index design, complying with electronic eye protection standards to ensure the stability of the lighting source and provide a comfortable visual environment for astronauts, thereby reducing eye strain.

[0003] To meet these requirements, the power controller of the lighting system must remain stable to ensure the normal operation of the lighting equipment. In spacecraft, the lighting power controller is not only responsible for providing stable power to the lighting equipment but also for coordinating the transmission of signals from various lighting devices to ensure the system's normal operation. However, during different phases of spacecraft operation, the lighting power controller may face significant vibrations, which can affect its stability and functionality. During rocket launch, the strong thrust and acceleration generated by the engine cause severe vibrations in the spacecraft, which can significantly impact on cabin equipment, including the lighting power controller, potentially affecting its normal operation. During orbit insertion and orbit adjustment phases, the spacecraft's acceleration and vibrations can also adversely affect the lighting power controller. If these vibrations accumulate over a long period, they may further affect the operational stability of the lighting power controller, causing it to malfunction.

[0004] Therefore, the design of the lighting power controller in the spacecraft cabin must fully consider the impact of these vibration sources and adopt effective anti-vibration design to ensure that the lighting power controller can work stably under different working conditions, thereby ensuring the safety and comfort of astronauts. Utility Model Content

[0005] The purpose of this invention is to provide a power controller and vibration-resistant base for manned spacecraft cabin lighting that can avoid problems such as unstable power supply, unreliable signal transmission, and insufficient eye protection performance of the light source in high vibration environments.

[0006] To achieve the above objectives, this utility model adopts the following solution: a power controller for lighting inside a manned spacecraft cabin, comprising a rectangular controller housing; a power supply module disposed within the controller housing for supplying power to the lighting equipment, the power supply module having a spectral adjustment circuit capable of achieving a high color rendering spectrum output by mixing white light and yellow light, the spectrum having high color saturation, and its DC power supply having an FPF flicker index as low as .%, meeting electronic eye protection standards; a signal communication module is provided within the controller housing, the signal communication module including a wireless signal amplification and transmission circuit for enhancing signal transmission effect; wherein, the signal communication module communicates with the power supply module via an internal cable. The electrical module is electrically connected to achieve signal transmission and power supply coordination. Multiple mounting ears are provided on both sides of the controller housing, each with a through mounting hole. Connection interfaces are located on both sides of the controller housing. These interfaces are used to insert external cable connectors, and their inner ends are electrically connected to the power supply module via internal cables. This allows for external power and signal access on one side, while the other side outputs high color rendering index (CRI) spectrum power and signals to the controlled cabin lighting equipment. An indicator light, electrically connected to the signal communication module, is provided on the controller housing to indicate signal status, enabling rapid system status assessment and improved troubleshooting efficiency.

[0007] In the above solution, the controller housing provides external protection, shielding the internal circuitry from mechanical damage and environmental influences. The power supply module, equipped with spectral adjustment capabilities, outputs a high color rendering index (CRI) light source to meet the long-term lighting needs within the spacecraft cabin, reducing visual fatigue and improving personnel comfort. The signal communication module is linked to the power supply module via cables, unifying power supply and communication functions, supporting remote control and status monitoring, and facilitating maintenance management and integration with intelligent control systems.

[0008] In a preferred embodiment of this invention, the controller housing is divided into a large circuit compartment and a small circuit compartment by a partition, clearly defining the layout area of ​​each functional module and reducing mutual interference. The power supply module is installed in the large circuit compartment, and the signal communication module is installed in the small circuit compartment.

[0009] As a preferred embodiment of this utility model, a notch is provided on the partition, and the cable electrically connecting the signal communication module and the power supply module passes through the notch.

[0010] In a preferred embodiment of this invention, the partition is made of a thermally conductive material and has an electromagnetic shielding coating on its surface to isolate heat and electromagnetic interference between different circuit compartments. The use of a thermally conductive material and the addition of an electromagnetic shielding coating not only dissipates heat but also shields against electromagnetic interference, effectively improving system stability and preventing heat or electromagnetic signal interference between the power supply module and the signal module. This design is suitable for spacecraft applications in complex electromagnetic environments.

[0011] As a preferred embodiment of this utility model, the connection interface is a waterproof connector with a needle. The connection interface not only provides power input and output to the power supply module, but also enables data interaction with external control equipment to achieve remote control of the power supply module and the signal communication module and synchronous control of signal transmission.

[0012] This utility model also provides a vibration-damping base solution, comprising: a rectangular cubic upper body; a lower base plate movably fastened to the bottom of the upper body; an axial elastic buffer for providing axial buffering is provided between the upper body and the lower base plate, the upper body and the lower base plate are connected by the axial elastic buffer to form a vibration-damping base structure, which can reduce axial vibration impact from the outside; a swing cavity is provided inside the upper body, the top of the swing cavity penetrating the top of the upper body; a connector is movably installed in the swing cavity, the connector can move back and forth towards the inner wall of the swing cavity, supporting multi-directional buffering function; radial buffers for providing radial buffering are respectively provided between the connector and the inner wall of the swing cavity to absorb vibration energy; the connector is respectively connected to the mounting ears of the manned spacecraft cabin lighting power controller as described above by screws. This solution provides axial and radial dual buffering, improves impact resistance, and reduces the risk of vibration damage to the circuit board and connector.

[0013] As a further embodiment of this utility model, the axial elastic buffer includes multiple stud holes that pass through the bottom of the swing cavity. A connecting bolt is movably inserted into each stud hole. The insertion end of the connecting bolt passes through the stud hole and is threaded together with the lower seat plate. A first return spring is sleeved on each of the connecting bolts. The two ends of the first return spring abut against the bottom surface of the upper seat body and the top surface of the lower seat plate, respectively, to prevent frequent vibration from causing equipment misalignment or damage.

[0014] As a further embodiment of this utility model, the swing cavity is rectangular, with a sliding guide rail at its bottom. The sliding guide rail is arranged parallel to the inner wall of the adjacent swing cavity. The radial buffer includes sliding plates disposed on one side of the four inner walls of the swing cavity, with the bottom of each sliding plate slidably inserted into the corresponding sliding guide rail. Multiple connecting rods are disposed on the outer circumference of the connector, each extending towards one of the four inner walls of the corresponding swing cavity, arranged in a cross shape and fixed to the outer circumference of the connector, with its outer end fixedly connected to the sliding plate. A second return spring, sleeved on the connecting rod and located between the sliding plate and the connector, provides an elastic return force. The sliding guide rail and sliding plate work together to ensure the sliding stability of the connector, and the second return spring provides a return force, providing a flexible movement and recovery structure, further improving the controller's shock and vibration resistance.

[0015] In a preferred embodiment of this utility model, the connector has a threaded connection hole in the center for connecting with a bolt passing through the mounting ear. After the bolt passes through the mounting through hole on the mounting ear, it is inserted into the threaded connection hole, and the two are fixed together by the threaded connection.

[0016] In a preferred embodiment of this invention, a rubber cover is provided over the upper housing, and an opening coaxial with and communicating with the threaded connection hole is provided on the top of the rubber cover. The rubber cover provides dustproof, waterproof, and additional cushioning protection, enhancing the overall protective capability of the equipment, extending its service life, and simplifying installation and maintenance.

[0017] In summary, the advantages of this invention compared to existing technologies are as follows: This invention, by adopting a rectangular controller housing structure and internally housing a power supply module and a signal communication module, realizes an integrated high color rendering index (CRI) spectral output, low flicker eye protection design, and vibration-resistant structural optimization lighting power controller for manned spacecraft cabins. The power supply module achieves high CRI and low flicker index lighting output through a spectral adjustment circuit, effectively reducing astronaut eye fatigue and meeting electronic eye protection standards. The signal communication module is equipped with wireless signal amplification and transmission circuits, ensuring the stability of data transmission and remote control. The controller housing is internally divided into a large circuit compartment and a small circuit compartment, which isolates heat and electromagnetic interference, improving the operational stability and reliability of the circuit modules. Furthermore, thermally conductive materials and electromagnetic shielding coatings further optimize anti-interference performance. The connection interface adopts a machined waterproof connector design, which not only enhances the device's sealing and protection capabilities but also supports power supply and data interaction functions, enabling remote control and status monitoring of the power supply module and communication module.

[0018] In addition, to cope with the strong vibrations generated during spacecraft launch and orbit adjustment, the power controller for the lighting inside the manned spacecraft adopts a vibration-resistant base design. It provides multi-directional buffering through axial and radial elastic buffers to further absorb and disperse vibration impact forces, maintaining the structural stability of the equipment and the integrity of the circuit connections. The buffer design uses first and second return springs to achieve elastic restoring force, combined with sliding guide rails and sliding plate structures to effectively reduce vibration transmission, thereby ensuring the controller can still operate normally under severe vibration environments.

[0019] Furthermore, the addition of a rubber outer cover not only improves the stability of the equipment installation but also enhances its protective performance and vibration resistance, ensuring the long-term stable operation of the power controller for manned spacecraft cabin lighting during space missions. The overall solution, while meeting the requirements for high color rendering and low flicker for eye protection in cabin lighting, achieves efficient power supply, reliable communication, and excellent vibration resistance, providing astronauts with a safe and comfortable lighting environment while improving the durability and adaptability of the equipment, thus ensuring the smooth implementation of space missions. Attached Figure Description

[0020] Figure 1 This is a perspective view of the present invention.

[0021] Figure 2 This is a perspective view of the internal structure of the controller housing in this utility model.

[0022] Figure 3 This is a separate exploded view of the power controller for the cabin lighting of a manned spacecraft according to this utility model.

[0023] Figure 4 This is a perspective view of the controller housing mounted on the vibration-resistant base in this utility model.

[0024] Figure 5 This is an exploded view of the overall structure of the power controller for lighting inside a manned spacecraft and the vibration-resistant base of this utility model.

[0025] Figure 6 for Figure 5 A magnified view of point A in the middle.

[0026] Figure 7 for Figure 5 A magnified view of point B in the middle.

[0027] Figure 8 This is a perspective view of the vibration-resistant base in this utility model.

[0028] Figure 9 This is one of the exploded views of the vibration-resistant base in this utility model.

[0029] Figure 10 for Figure 9 A magnified view of point C in the middle.

[0030] Figure 11 This is the second exploded view of the vibration-resistant base in this utility model, as well as an enlarged view of a local area in the figure.

[0031] Figure 12 This is the third exploded view of the vibration-resistant base in this utility model.

[0032] Figure 13 This is one of the cross-sectional views of the vibration-resistant base in this utility model.

[0033] Figure 14 This is the second cross-sectional view of the vibration-resistant base of this utility model, as well as an enlarged view of a local area in the figure.

[0034] Explanation of reference numerals in the attached drawings: 1. Controller housing; 2. Power supply module; 3. Signal communication module; 4. Connection interface; 5. Upper base; 6. Lower base plate; 7. Connector; 8. Radial buffer; 9. Rubber cover; 11. Mounting ear; 12. Mounting through hole; 13. Partition; 14. Large circuit compartment; 15. Small circuit compartment; 16. Notch; 17. Wire clamp; 18. Bottom shell; 19. Top cover; 31. Indicator light; 51. Swing cavity; 52. Sliding guide rail; 60. Axial elastic buffer; 61. Stud hole; 62. Connecting bolt; 63. First return spring; 71. Threaded connection hole; 72. Swing rod; 73. Ball head; 74. Spherical groove; 81. Sliding plate; 82. Connecting rod; 83. Second return spring; 91. Clearance opening; 811. Guide plate. Detailed Implementation

[0035] The following detailed description provides various embodiments or examples for implementing this utility model. Of course, these are merely embodiments or examples and are not intended to be limiting. Additionally, repeated reference numerals, such as repeated numbers and / or letters, may be used in different embodiments. These repetitions are for the purpose of simple and clear description of this utility model and do not represent a specific relationship between the different embodiments and / or structures discussed.

[0036] Furthermore, spatial terms may be used, such as "below," "lower," "from the inside out," "above," "upper," and similar terms. These relational terms are used to facilitate the description of the relationship between some elements or features in the drawings and other elements or features. These spatial relational terms include different orientations of the device in use or operation, as well as the orientations described in the drawings. The device may be rotated 90 degrees or otherwise to different orientations, and the spatially related adjectives used therein can be interpreted in the same way. Therefore, they should not be construed as limiting the present invention. The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined with "first" or "second" may explicitly or implicitly include one or more of that feature.

[0037] The present invention will be further described below with reference to the accompanying drawings and specific embodiments: Figures 1 to 5 The diagram illustrates a power controller for lighting inside a manned spacecraft cabin, comprising: a rectangular controller housing 1, consisting of a hollow bottom shell 18 and a top cover 19, made of high-strength, impact-resistant metal or engineering plastic to meet the durability and safety requirements of equipment inside the spacecraft cabin; the controller housing 1 is divided into a large circuit compartment 14 and a small circuit compartment 15 by a partition 13. A power supply module 2 is installed in the large circuit compartment 14, which provides stable power to the lighting equipment. The power supply module 2 integrates a spectral adjustment circuit, which intelligently adjusts the mixing ratio of white and yellow light to output a spectrum with high color rendering and high color saturation. Simultaneously, it employs a DC power supply design, reducing the FPF flicker index to 0.01%, meeting electronic eye protection standards, effectively reducing visual fatigue caused by prolonged use, and improving the comfort of the astronauts' working and living environment.

[0038] The small circuit compartment 15 houses a signal communication module 3, which integrates wireless signal amplification and transmission circuits to enhance signal transmission and ensure stable signal communication even in complex compartment environments. A notch 16 is provided in the partition 13, through which the power supply module 2 and the signal communication module 3 are electrically connected, enabling coordinated signal transmission and power supply to ensure the stability and reliability of the control system. It should be noted that the partition 13 is made of thermally conductive material and has an electromagnetic shielding coating on its surface to isolate heat and electromagnetic interference between different circuit compartments. After the cable connecting the power supply module 2 and the signal communication module 3 passes through the notch 16, a wire clamp 17 is used to press and secure the cable within the notch 16.

[0039] The controller housing 1 has multiple mounting ears 11 on both sides, and each mounting ear 11 has a through mounting hole 12, which makes it easy to reliably fix the controller to the equipment bracket inside the cabin using screws or other fasteners, further improving the convenience and firmness of installation.

[0040] Connection interfaces 4 are arranged on both sides of the controller housing 1, which facilitate the insertion and connection of external cable connectors. One connection interface 4 is used to connect external power and signal input, while the other connection interface 4 transmits the high color rendering spectrum power and signal output from the power supply module 2 to the cabin lighting equipment through internal cables, thereby ensuring efficient coordination of power and signal transmission.

[0041] In addition, to further improve the efficiency of system status monitoring and maintenance, an indicator light 31 is installed on the controller housing 1. The indicator light 31 is electrically connected to the signal communication module 3 and is used to display the signal transmission status in real time. By observing the flashing or on / off state of the indicator light 31, the operator can quickly determine the system operating status, which helps to improve the efficiency of fault diagnosis and troubleshooting and ensures the smooth progress of space missions.

[0042] In addition, such as Figures 4 to 14 The illustration shows an embodiment of an anti-vibration base according to this utility model, comprising: an upper seat body 5 in the shape of a rectangular cube and a lower seat plate 6 movably fastened to the bottom of the upper seat body 5. An axial elastic buffer member 60 is provided between the upper seat body 5 and the lower seat plate 6 to provide axial buffering. The axial elastic buffer member 60 connects the upper seat body 5 and the lower seat plate 6 to form an anti-vibration base structure, which can significantly reduce axial vibration impact from the outside and improve the overall impact resistance. The upper seat body 5 has a rectangular cube structure and is made entirely of high-strength material, possessing good rigidity and impact resistance. It has an internal swing cavity 51, within which a connecting member 7 is movably installed, capable of moving back and forth towards the inner walls of the swing cavity 51 to support multi-directional buffering. Radial buffer members 8 are respectively provided between the connecting member 7 and the inner walls of the swing cavity 51 to absorb vibration energy. The space of the swing cavity 51 can accommodate and guide the movement of the connecting member 7, while providing installation space for the radial buffer members 8. The upper seat 5 has a through-hole at the top, allowing the connector 7 to be freely installed and adjusted. The lower seat plate 6 is made of a high-toughness material to ensure it is not easily deformed under vibration and impact, and its surface is treated with an anti-slip coating to enhance the fixing effect. The top center of each connector 7 is connected to the respective mounting ears 11 of the manned spacecraft cabin lighting power controller as described above, via screws. This design provides axial and radial dual buffering, improving impact resistance and reducing the risk of vibration damage to the circuit board and connectors.

[0043] The axial elastic buffer 60 specifically includes multiple stud holes 61 penetrating the bottom of the swing cavity 51. A connecting bolt 62 is movably inserted into each stud hole 61. The connecting bolt 62 connects the upper seat body 5 and the lower seat plate 6. Specifically, the insertion end of the connecting bolt 62 passes through the stud hole 61 and is threadedly connected to the lower seat plate 6. Furthermore, a first return spring 63 is fitted onto each of the connecting bolts 62, with its two ends abutting against the bottom surface of the upper seat body 5 and the top surface of the lower seat plate 6, respectively, generating an elastic return force to effectively prevent misalignment or damage to the equipment caused by frequent vibration.

[0044] It should be noted that the swing cavity 51 has a rectangular structure, and its bottom is provided with a sliding guide rail 52. The sliding guide rail 52 is arranged parallel to the inner wall of the adjacent swing cavity 51 to limit the sliding trajectory of the connecting piece 7 during radial movement and improve sliding stability. The outer wall of the connecting piece 7 is provided with multiple connecting rods 82 for connecting the radial buffer 8. The radial buffer 8 includes a sliding plate 81 and a second return spring 83. The four sliding plates 81 are respectively set on one side of the four inner walls of the swing cavity 51 and can be slidably inserted into the corresponding sliding guide rail 52. The bottom end of the sliding plate 81 is restricted to slide within the sliding guide rail 52 by two upper and lower spaced guide plates 811 to ensure sliding stability. The connecting rods 82 are arranged in a cross shape and fixed on the circumferential outer wall of the connecting piece 7. The outer end of each connecting rod 82 extends toward the inner wall of the corresponding swing cavity 51. Its outer end is movably connected to the sliding plate 81 to ensure that the connecting piece 7 moves synchronously, that is, the connecting rod 82 can extend and retract relative to the sliding plate 81. The second return spring 83 is sleeved on the connecting rod 82 and located between the sliding plate 81 and the connecting piece 7. It provides elastic return force to ensure that the vibration is absorbed and the initial position is quickly restored.

[0045] Furthermore, the connector 7 has a threaded connection hole 71 in the center for connection with a bolt passing through the mounting ear 11. The bolt passes through the mounting through holes 12 on the mounting ear 11 and is then inserted into the threaded connection hole 71, and the two are fixed together by the threaded connection to ensure structural stability. To prevent the connector 7 from being subjected to strong compressive force from the mounting ear 11, which could cause the connecting rod 82 to bend and thus fail to provide radial buffering, a swing rod 72 is provided between the connector 7 and the bottom of the swing cavity 51. The swing rod 72 has round ball heads 73 at both ends, and spherical grooves 74 are fixed to the center of the bottom of the connector 7 and the center of the bottom wall of the swing cavity 51, respectively. The ball heads 73 are movably embedded in their corresponding spherical grooves 74. In this way, the swing rod 72 provides axial support when the connector 7 sinks into the bottom of the swing cavity 51, and also swings with the connector 7 as it moves back and forth within the swing cavity 51.

[0046] The upper body 5 is covered by a rubber cover 9, and the top of the rubber cover 9 has a clearance opening 91 that is coaxial with and communicates with the threaded connection hole 71. The rubber cover 9 provides dustproof, waterproof, and additional cushioning protection. In summary, this embodiment, through a dual axial and radial cushioning structure combined with a return spring and sliding guide rail design, effectively reduces the risk of vibration damage to the circuit board and connection interfaces of the manned spacecraft cabin lighting power controller. The overall structure is robust, easy to install and maintain, and suitable for ensuring the long-term stable operation of the manned spacecraft cabin lighting power controller during space missions.

[0047] The foregoing has shown and described the basic principles and main features of this utility model, as well as its advantages. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of this utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed utility model. The scope of protection of this utility model is defined by the appended claims and their equivalents.

Claims

1. A power controller for cabin lighting in a manned spacecraft, characterized in that, include: Controller housing (1); The power supply module (2) is installed inside the controller housing (1) for powering the lighting equipment and has a spectrum adjustment circuit that can achieve high color rendering spectrum output by mixing white light and yellow light. The spectrum has high color saturation and its DC power supply FPF flicker index is as low as 0.01% to meet the electronic eye protection standard. The signal communication module (3) is located inside the controller housing (1). The signal communication module (3) includes a wireless signal amplification and transmission circuit to enhance the signal transmission effect. The signal communication module (3) is electrically connected to the power supply module (2) via an internal cable to achieve signal transmission and power supply coordination. Multiple mounting ears (11) are respectively disposed on both sides of the controller housing (1), and the mounting ears (11) are provided with through mounting holes (12). Connection interfaces (4) are respectively set on both sides of the controller housing (1) for inserting external cable connectors. The inner ends of the connection interfaces (4) are electrically connected to the power supply module (2) through internal cables. An indicator light (31) is installed on the controller housing (1) and electrically connected to the signal communication module (3) to indicate the signal status.

2. The power controller for cabin lighting in a manned spacecraft according to claim 1, characterized in that, The controller housing (1) is divided into a large circuit compartment (14) and a small circuit compartment (15) by a partition (13). The power supply module (2) is installed in the large circuit compartment (14), and the signal communication module (3) is installed in the small circuit compartment (15).

3. The power controller for cabin lighting in a manned spacecraft according to claim 2, characterized in that, A notch (16) is provided on the partition (13), and the cable connecting the signal communication module (3) and the power supply module (2) passes through the notch (16).

4. The power controller for cabin lighting in a manned spacecraft according to claim 3, characterized in that, The partition (13) is made of thermally conductive material and has an electromagnetic shielding coating on its surface to isolate heat and electromagnetic interference between different circuit compartments.

5. The power controller for cabin lighting in a manned spacecraft according to claim 1, characterized in that, The connection interface (4) is a waterproof connector for machine pins. The connection interface (4) can not only provide power input and output to the power supply module (2), but also interact with external control devices to realize remote control of the power supply module (2) and the signal communication module (3).

6. A vibration-damping base, characterized in that, include: Upper body (5); The lower seat plate (6) is movably fastened to the bottom of the upper seat body (5); An axial elastic buffer (60) is disposed between the upper seat (5) and the lower seat plate (6) to provide axial buffering; A swing cavity (51) is disposed inside the upper seat (5), and the top of the swing cavity (51) penetrates the top of the upper seat (5); The connector (7) is movably installed in the swing cavity (51) and can move back and forth towards the inner wall of the swing cavity (51); Radial buffers (8) are respectively disposed between the connector (7) and the inner walls of the swing cavity (51) to provide radial buffering; The connector (7) is connected by screws to each mounting lug (11) of the manned spacecraft cabin lighting power controller as described in any one of claims 1 to 5.

7. The vibration-damping base according to claim 6, characterized in that, The axial elastic buffer (60) includes a plurality of stud holes (61) that pass through the bottom of the swing cavity (51). A connecting bolt (62) is movably inserted in each stud hole (61). The insertion end of the connecting bolt (62) passes through the stud hole (61) and is threaded together with the lower seat plate (6). A first return spring (63) is sleeved on each of the connecting bolts (62). The two ends of the first return spring (63) abut against the bottom surface of the upper seat body (5) and the top surface of the lower seat plate (6), respectively.

8. The vibration-damping base according to claim 6, characterized in that, The swing cavity (51) is rectangular, and a sliding guide rail (52) is provided at its bottom. The sliding guide rail (52) is arranged parallel to the inner wall of the adjacent swing cavity (51). The radial buffer (8) includes: Sliding plates (81) are set on one side of the four inner walls of the swing cavity (51), and the bottom of each sliding plate (81) can be slidably inserted into the corresponding sliding guide rail (52); Multiple connecting rods (82) are provided on the outer circumference of the connector (7). Each connecting rod (82) extends toward the four inner walls of the corresponding swing cavity (51) and is fixed on the outer circumference of the connector (7) in a cross shape. Its outer end is movably connected to the sliding plate (81). The second return spring (83), sleeved on the connecting rod (82), is located between the sliding plate (81) and the connecting member (7) and is used to provide elastic return force.

9. The vibration-damping base according to claim 6, characterized in that, The connector (7) has a threaded connection hole (71) in the center, which is used to connect with the bolt passing through the mounting ear (11). After the bolt passes through the mounting through hole (12) on the mounting ear (11) in sequence, it is inserted into the threaded connection hole (71) and the two are fixed together by the threaded connection.

10. The vibration-damping base according to claim 9, characterized in that, A rubber cover (9) is provided on the upper body (5), and a clearance opening (91) is provided on the top of the rubber cover (9) that is coaxial with and connected to the threaded connection hole (71).

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