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

Abstract

The invention discloses a manned spacecraft cabin lighting power supply controller and an anti-vibration base, the manned spacecraft cabin lighting power supply controller comprises a controller shell, and a power supply module and a signal communication module which are arranged in the controller shell, and the power supply module is provided with a spectrum adjusting circuit which can realize high color rendering spectrum output by mixing white light and yellow light; the signal communication module comprises a wireless signal amplifying and transmitting circuit, a plurality of 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 invention aims to provide the manned spacecraft in-cabin lighting power supply controller integrating high-color rendering spectrum output, low-flicker eye protection design and anti-vibration structure optimization, and the anti-vibration base, on the basis of meeting the in-cabin lighting high-color rendering and low-flicker eye protection requirements, realize efficient power supply, reliable communication and excellent anti-vibration capability, and improve the reliability of the in-cabin lighting power supply controller and the anti-vibration base of the manned spacecraft on the basis of meeting the in-cabin lighting high-color rendering and low-flicker eye protection requirements. And a safe and comfortable lighting environment is provided for astronauts.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft lighting accessories, and in particular to a lighting power controller and an anti-vibration base in a manned spacecraft cabin. Background Art

[0002] During the design and operation of manned spacecraft, the stability of the cabin environment is crucial to the work and life of astronauts. In particular, astronaut health and comfort are often among the primary design considerations. As a crucial component of the cabin, the lighting system must be designed not only to meet basic lighting requirements but also to accommodate long-term use by astronauts. Astronauts work for extended periods of time in spacecraft. When exposed to artificial light sources, particularly light-emitting diode (LED) lighting, insufficient spectral color rendering or excessive flicker can cause eye discomfort, fatigue, and even affect vision. Therefore, to prevent eye fatigue and vision loss, spacecraft lighting systems must provide a spectrum with high color rendering and color saturation. This not only closely resembles natural light but also reduces eye strain from prolonged exposure. Furthermore, light stability is crucial for eye protection, and avoiding flicker is an effective way to reduce eye fatigue. Therefore, lighting power controllers should adopt a low flicker index design that complies 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 achieve these requirements, the lighting system's power controller must remain stable to ensure the proper operation of the lighting equipment. Within a spacecraft, the lighting power controller not only provides stable power to the lighting equipment but also coordinates the transmission of signals between various lighting devices to ensure the proper functioning of the system. However, during various stages of a spacecraft's operation, the lighting power controller may be subject to significant vibrations, which can affect the controller's stability and functionality. During a rocket launch, the intense thrust and acceleration generated by the engines cause the spacecraft to experience severe vibrations. These vibrations can significantly impact the equipment within the cabin, including the lighting power controller, potentially impacting its proper operation. During orbit insertion and orbit adjustment, the acceleration and vibrations experienced by the spacecraft can also adversely affect the lighting power controller. If these vibrations accumulate over time, they can further impact the lighting power controller's operational stability, 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. Summary of the Invention

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

[0006] In order to achieve the above-mentioned purpose, the present invention adopts the following scheme: a manned spacecraft cabin lighting power controller, comprising a rectangular controller shell; a power supply module arranged in the controller shell and used to power the lighting equipment, the power supply module having a spectrum adjustment circuit capable of achieving high color rendering spectrum output by mixing white light and yellow light, the spectrum having high color saturation, and the FPF flicker index of its DC power supply is as low as .%, meeting the electronic eye protection standard; a signal communication module is provided in the controller shell, the signal communication module including a wireless signal amplification and transmission circuit for enhancing the signal transmission effect; wherein, the signal communication module is connected to the power supply module via an internal cable. The controller shell is electrically connected to the power supply module to realize the signal transmission and power supply coordination functions; a plurality of mounting ears are respectively provided on both sides of the controller shell, and each mounting ear is provided with a penetrating mounting through hole; connection interfaces are respectively provided on both sides of the controller shell, and the connection interfaces are used to insert external cable connectors, and the inner ends of the connection interfaces are electrically connected to the power supply module through internal cables to realize the access of external power supply and signals on one side and output high color rendering spectrum power supply and signals to the controlled cabin lighting equipment on the other side; an indicator light is provided on the controller shell, which is electrically connected to the signal communication module and is used to indicate the signal status, so as to quickly judge the system status and improve the troubleshooting efficiency.

[0007] In this solution, the controller housing provides external protection, safeguarding the internal circuitry from mechanical damage and environmental influences. The power supply module, equipped with spectral modulation and capable of outputting high-color rendering light, meets the long-term lighting requirements within the space capsule, reducing visual fatigue and improving crew comfort. The signal communication module, linked to the power supply module via cables, centrally manages power supply and communication functions, supports remote control and status monitoring, and facilitates maintenance management and intelligent control system integration.

[0008] As a preferred embodiment of the present invention, the controller housing is partitioned into a large circuit compartment and a small circuit compartment, clarifying 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 solution of the present invention, a gap is provided on the partition, and a cable electrically connected between the signal communication module and the power supply module passes through the gap.

[0010] As a preferred embodiment of the present invention, the partition is made of a thermally conductive material and coated with an electromagnetic shielding coating to isolate heat and electromagnetic interference between different circuit compartments. The use of thermally conductive material and the addition of an electromagnetic shielding coating both dissipates heat and shields electromagnetic interference, effectively improving system stability and preventing heat or electromagnetic signal interference between the power supply module and the signal module. This makes it suitable for spacecraft applications in complex electromagnetic environments.

[0011] As a preferred embodiment of the present invention, the connection interface is a waterproof connector with a needle. This connection interface not only provides power input and output for the power supply module, but also enables data exchange with external control devices to achieve remote control of the power supply module and signal communication module, as well as synchronous control of signal transmission.

[0012] The present invention also provides a solution for an anti-vibration base, comprising: an upper base in the shape of a rectangular cube; a lower base plate movably engaged with the bottom of the upper base; an axial elastic buffer for providing axial buffering disposed between the upper base and the lower base, the upper base and the lower base being connected by the axial elastic buffer to form an anti-vibration base structure that can reduce axial vibration impact from the outside; a swing cavity disposed within the upper base, the top of the swing cavity penetrating the top of the upper base; a connector movably mounted within the swing cavity, the connector being able to move back and forth toward the inner walls of the swing cavity, supporting a multi-directional buffering function; radial buffers for providing radial buffering to absorb vibration energy disposed between the connector and the inner walls of the swing cavity; the connectors being connected to the respective mounting ears of the above-mentioned manned spacecraft cabin lighting power controller via screws. This solution provides dual axial and radial buffering, improving impact resistance and reducing the risk of vibration damage to circuit boards and connectors.

[0013] As a further solution of the present invention, the axial elastic buffer includes a plurality of stud holes respectively passing through the bottom of the swing cavity, and a connecting bolt is movably inserted into each stud hole. The striking end of the connecting bolt passes through the stud hole and is threadedly connected to the lower seat plate. A first return spring is respectively sleeved on each of the connecting bolts, and the two ends of the first return spring respectively rest against the bottom surface of the upper seat body and the top surface of the lower seat plate to prevent frequent vibration from causing dislocation or damage to the equipment.

[0014] As a further embodiment of the present invention, the swing cavity is rectangular, and a sliding guide is provided at its bottom. The sliding guide is arranged parallel to the inner wall of the adjacent swing cavity. The radial buffer includes a sliding plate provided on one side of the four inner walls of the swing cavity, and the bottom of each sliding plate can be slidably inserted into the corresponding sliding guide. A plurality of connecting rods are provided on the outer circumferential wall of the connecting member, each extending toward the four inner walls of the corresponding swing cavity, and are arranged in a cross shape and fixed to the outer circumferential wall of the connecting member, with their outer ends fixedly connected to the sliding plate. A second return spring is provided on the connecting rod, located between the sliding plate and the connecting member, and is used to provide an elastic return force. The sliding guide is provided to cooperate with the sliding plate to ensure the sliding stability of the connecting member, and the return force is provided by the second return spring, providing a flexible movement and recovery structure, further improving the impact and vibration resistance of the controller.

[0015] As a preferred embodiment of the present invention, the connecting member is provided with a threaded hole in the center thereof for mating with a bolt passing through the mounting lug. The bolt passes through the mounting holes on the mounting lug and then into the threaded hole, whereupon the two are fixed together by a threaded connection.

[0016] As a preferred embodiment of the present invention, the upper housing is covered with a rubber cover, and an opening is provided at the top of the rubber cover, which is coaxial with and communicates with the threaded connection hole. The rubber cover provides dust and water resistance and provides additional cushioning protection, enhancing the overall protection capability of the device, extending its service life, and simplifying installation and maintenance operations.

[0017] In summary, the present invention has the following beneficial effects compared to the prior art: the present invention adopts a rectangular controller housing structure, and internally arranges a power supply module and a signal communication module to realize a manned spacecraft cabin lighting power controller that integrates high color rendering spectrum output, low flicker eye protection design, and anti-vibration structure optimization. The power supply module achieves high color rendering and low flicker index lighting output through a spectrum adjustment circuit, effectively reducing astronaut eye fatigue and meeting electronic eye protection standards; the signal communication module is equipped with a wireless signal amplification and transmission circuit to ensure the stability of data transmission and remote control. The interior of the controller housing is divided into a large circuit compartment and a small circuit compartment. Heat and electromagnetic interference are isolated by partitions, improving the working stability and reliability of the circuit module. At the same time, thermal conductive materials and electromagnetic shielding coatings are used to further optimize the anti-interference performance. The connection interface adopts a needle waterproof connector design, which not only enhances the sealing protection capability of the equipment, but also supports power supply and data interaction functions, realizing remote control and status monitoring of the power supply module and communication module.

[0018] Furthermore, to mitigate the intense vibrations generated during spacecraft launch and orbital adjustments, the cabin lighting power controller for manned spacecraft utilizes an anti-vibration mount solution. This solution utilizes axial and radial elastic buffers to provide multi-directional cushioning, further absorbing and dissipating vibration impact forces, maintaining the stability of the device structure and the integrity of the circuit connections. The buffer design utilizes first and second return springs to provide elastic restoring force. This, combined with the sliding guide and sliding plate structure, effectively reduces vibration transmission, ensuring the controller's continued operation even in severe vibration environments.

[0019] Furthermore, the provision of a rubber cover as an outer layer of protection not only enhances the device's installation stability but also further improves its protective performance and vibration resistance, ensuring the long-term stable operation of the cabin lighting power controller during manned spacecraft missions. The overall solution not only meets the requirements for high color rendering and low flicker eye protection for cabin lighting, but also achieves efficient power supply, reliable communication, and excellent vibration resistance, providing astronauts with a safe and comfortable lighting environment. It also improves the device's durability and adaptability, ensuring the smooth implementation of space missions. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a three-dimensional view of the present invention.

[0021] Figure 2 This is a three-dimensional view of the internal structure of the controller housing in the present invention.

[0022] Figure 3 This is a separate exploded view of the lighting power controller in the manned spacecraft cabin of the present invention.

[0023] Figure 4 This is a three-dimensional view of the controller housing installed on the anti-vibration base in the present invention.

[0024] Figure 5 This is an overall exploded view of the lighting power controller and anti-vibration base in the manned spacecraft cabin of the present invention.

[0025] Figure 6 for Figure 5 Magnified view at point A in the middle.

[0026] Figure 7 for Figure 5 Magnified view at point B.

[0027] Figure 8 It is a three-dimensional view of the anti-vibration base in the present invention.

[0028] Figure 9 This is one of the separate exploded views of the anti-vibration mount of the present invention.

[0029] Figure 10 for Figure 9 Magnified view at center C.

[0030] Figure 11 This is the second separate exploded view of the anti-vibration base in the present invention, and an enlarged view of a local area in the figure.

[0031] Figure 12 This is the third separate exploded view of the anti-vibration base in the present invention.

[0032] Figure 13 This is one of the cross-sectional views of the anti-vibration base in the present invention.

[0033] Figure 14 This is the second cross-sectional view of the anti-vibration base in the present invention, and an enlarged view of a local area in the figure.

[0034] Explanation of the accompanying drawings: 1. Controller housing; 2. Power supply module; 3. Signal communication module; 4. Connection interface; 5. Upper seat; 6. Lower seat 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 pressing piece; 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. Give way; 811. Guide plate. DETAILED DESCRIPTION

[0035] The following detailed description provides various embodiments or examples for implementing the present invention. These are, of course, merely examples and are not intended to be limiting. Furthermore, repeated reference numerals, such as repeated numbers and / or letters, may be used in different embodiments. Such repetition is for simplicity and clarity in describing the present invention and does not imply a specific relationship between the various embodiments and / or configurations discussed.

[0036] In addition, spatially related terms may be used, such as "below," "lower side," "from the inside out," "above," "upper side," and similar terms. These terms are used to facilitate the description of the relationship between one element or feature and another element or feature in the drawings. These spatially related terms include different orientations of the device in use or operation, as well as the orientations described in the drawings. The device may be turned to different orientations, rotated 90 degrees or other orientations, and the spatially related adjectives used therein may also be interpreted in the same way. Therefore, they cannot be understood as limiting the present invention. The terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of such features.

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

[0038] A signal communication module 3 is provided inside the small circuit cabin 15. The signal communication module 3 integrates a wireless signal amplification and transmission circuit, which can enhance the signal transmission effect and ensure that the signal communication capability is stable even in a complex cabin environment. A notch 16 is provided on the partition 13. The power supply module 2 and the signal communication module 3 are electrically connected to each other through a cable passing through the notch 16, so as to realize the coordinated work of signal transmission and power supply to ensure the stability and reliability of the control system function. It should be noted that the partition 13 is made of heat-conducting material and an electromagnetic shielding coating is provided on its surface to isolate the heat and electromagnetic interference of different circuit cabins. After the cable electrically connected between the power supply module 2 and the signal communication module 3 passes through the notch 16, a wire pressing piece 17 is used to press and fix the cable in the notch 16.

[0039] A plurality of mounting ears 11 are provided on both sides of the controller housing 1, and each mounting ear 11 is provided with a through-mounting hole 12, which facilitates the use of screws or other fasteners to reliably fix the controller to the equipment bracket in the cabin, further improving the convenience and firmness of installation.

[0040] Connector ports 4 are located on either side of the controller housing 1 to facilitate the insertion and connection of external cable connectors. One port 4 is used to connect to an external power source and signal input, while the other port 4 transmits the high-color rendering spectrum power and signals output by the power supply module 2 to the cabin lighting equipment via internal cables, ensuring efficient coordination of power and signal transmission.

[0041] To further enhance system status monitoring and maintenance efficiency, controller housing 1 is equipped with an indicator light 31, electrically connected to signal communication module 3, to display the real-time status of signal transmission. By observing the blinking or on / off state of indicator light 31, operators can quickly determine the system's operating status, improving fault diagnosis and troubleshooting efficiency and ensuring the smooth progress of space missions.

[0042] In addition, if Figures 4 to 14 The figure shows an embodiment of an anti-vibration mount according to the present invention, comprising an upper body 5 in the shape of a rectangular cube and a lower base plate 6 that flexibly engages the bottom of the upper body 5. An axial elastic buffer 60 is positioned between the upper body 5 and the lower base plate 6 to provide axial cushioning. The axial elastic buffer 60 connects the upper body 5 and the lower base plate 6 to form an anti-vibration base structure, significantly reducing external axial vibration impact and improving overall impact resistance. The upper body 5 is a rectangular cube constructed entirely of high-strength material, offering excellent rigidity and impact resistance. It contains a swing chamber 51, within which is mounted a connector 7 that can flexibly move back and forth toward the inner walls of the chamber 51, providing multi-directional cushioning. Radial buffers 8 are positioned between the connector 7 and the inner walls of the chamber 51 to absorb vibration energy. The space within the chamber 51 accommodates and guides the movement of the connector 7, while also providing mounting space for the radial buffer 8. The top of the upper base 5 is open, allowing for the connector 7 to be freely installed and adjusted. The lower base plate 6 is constructed of a highly resilient material, ensuring resistance to deformation when subjected to vibration and impact, and its surface is treated with an anti-slip finish to enhance securement. The top center of the connector 7 is screwed to the respective mounting ears 11 of the aforementioned manned spacecraft cabin lighting power controller. This solution provides dual axial and radial cushioning, enhancing impact resistance and reducing the risk of vibration damage to the circuit boards and connectors.

[0043] The axial elastic buffer 60 specifically includes multiple stud holes 61 extending through the bottom of the swing cavity 51. Each stud hole 61 movably supports a connecting bolt 62, which connects the upper base 5 and the lower base plate 6. Specifically, the insertion end of the connecting bolt 62 passes through the stud hole 61 and is threadedly connected to the lower base plate 6. Furthermore, a first return spring 63 is sleeved around each of the connecting bolts 62, with its ends resting against the bottom surface of the upper base 5 and the top surface of the lower base plate 6, generating an elastic return force that effectively prevents dislocation or damage to the equipment due to frequent vibration.

[0044] It should be noted that the swing cavity 51 is a rectangular structure with a sliding guide rail 52 at its bottom. The sliding guide rail 52 is arranged parallel to the inner wall of the adjacent swing cavity 51 and is used to limit the sliding trajectory of the connector 7 during radial movement and improve sliding stability. The outer wall of the connector 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 arranged 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 in the sliding guide rail 52 by two guide plates 811 spaced apart above and below to ensure sliding stability. The connecting rods 82 are arranged in a cross shape and fixed on the circumferential outer wall of the connector 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 synchronous movement of the connector 7, that is, the connecting rod 82 can be extended and retracted relative to the sliding plate 81. The second return spring 83 is sleeved on the connecting rod 82 and is located between the sliding plate 81 and the connecting member 7 to provide elastic return force to ensure that the initial position is quickly restored after vibration absorption.

[0045] In addition, the connector 7 is provided with a threaded connection hole 71 in the center for connecting with a bolt passing through the mounting ear 11. The bolts are sequentially inserted through the mounting holes 12 on the mounting ear 11 and then into the threaded connection hole 71. The two are then fixed together by a threaded connection to ensure structural stability. To ensure that the connector 7 is not subjected to strong squeezing forces from the mounting ear 11, which could cause the connecting rod 82 to bend and thus cause radial buffer failure, a swing rod 72 is provided between the connector 7 and the bottom of the swing cavity 51. The swing rod 72 has a circular ball head 73 at each end. 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, corresponding to the two ball heads 73. The ball heads 73 are movably embedded in the corresponding spherical grooves 74. In this way, the swing rod 72 can provide axial support when the connector 7 sinks into the bottom of the swing cavity 51, and can also swing with the connector 7 as the connector 7 moves back and forth within the swing cavity 51.

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

[0047] The basic principles, main features, and advantages of the present invention are shown and described above. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are merely illustrative of the principles of the present invention. Various changes and modifications may be made to the present invention without departing from the spirit and scope of the present invention. Such changes and modifications are intended to fall within the scope of the present invention. The scope of protection claimed in the present invention is defined by the appended claims and their equivalents.

Claims

1. A manned spacecraft cabin lighting power controller, characterized in that: include: Controller housing (1); A power supply module (2) is arranged in the controller housing (1) and is used to supply power to the lighting device, and has a spectrum 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 a FPF flicker index of a DC power supply as low as 0.01%, thereby meeting electronic eye protection standards; A signal communication module (3) is arranged in the controller housing (1), and the signal communication module (3) comprises a wireless signal amplification and transmission circuit for enhancing 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 functions; A plurality of mounting ears (11) are respectively arranged on two sides of the controller housing (1), and the mounting ears (11) are provided with penetrating mounting through holes (12); Connection interfaces (4) are respectively arranged on both sides of the controller housing (1) and are used to insert external cable connectors, and the inner ends of the connection interfaces (4) are respectively electrically connected to the power supply module (2) via internal cables; An indicator light (31) is arranged on the controller housing (1) and is electrically connected to the signal communication module (3) and is used to indicate a signal status.

2. The manned spacecraft cabin lighting power controller according to claim 1, characterized in that: The controller housing (1) is provided with a partition (13) to divide its internal space into a large circuit compartment (14) and a small circuit compartment (15); 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 manned spacecraft cabin lighting power controller according to claim 2, characterized in that: A notch (16) is provided on the partition (13), and a cable electrically connected between the signal communication module (3) and the power supply module (2) passes through the notch (16).

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

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

6. A vibration-resistant base, characterized in that: include: Upper seat body (5); A lower seat plate (6) movably buckled on the bottom of the upper seat body (5); An axial elastic buffer (60) is arranged between the upper seat body (5) and the lower seat plate (6) and is used to provide axial buffering; A swing cavity (51) is arranged inside the upper seat body (5), and the top of the swing cavity (51) passes through the top of the upper seat body (5); A connecting member (7) is movably mounted in the swing cavity (51) and is capable of moving back and forth toward the inner wall around the swing cavity (51); Radial buffers (8) are respectively arranged between the connecting member (7) and the inner walls around the swing cavity (51) and are used to provide radial buffering; The connecting member (7) is connected to each mounting ear (11) of the manned spacecraft cabin lighting power controller according to any one of claims 1 to 5 by means of screws.

7. The anti-vibration mount according to claim 6, characterized in that: The axial elastic buffer (60) comprises a plurality of stud holes (61) respectively penetrating the bottom of the swing cavity (51), and a connecting bolt (62) is movably inserted into each stud hole (61). The punching end of the connecting bolt (62) passes through the stud hole (61) and is threadedly connected to the lower seat plate (6). A first return spring (63) is sleeved on each of the connecting bolts (62), and two ends of the first return spring (63) respectively abut against the bottom surface of the upper seat body (5) and the top surface of the lower seat plate (6).

8. The anti-vibration mount according to claim 6, characterized in that: The swing cavity (51) is rectangular, and a sliding guide rail (52) is provided at the bottom thereof. The sliding guide rail (52) is arranged parallel to the inner wall of the adjacent swing cavity (51). The radial buffer (8) comprises: Sliding plates (81) are arranged on one side of 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); A plurality of connecting rods (82) are arranged on the outer circumferential wall of the connecting member (7), each connecting rod (82) extends in the direction of four inner walls of the corresponding swing cavity (51), and are arranged in a cross shape and fixed on the outer circumferential wall of the connecting member (7), and the outer ends of the connecting rods (82) are movably connected to the sliding plate (81); A 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 an elastic return force.

9. The anti-vibration mount according to claim 6, characterized in that: A threaded connection hole (71) is provided at the center of the connecting piece (7) for mating with a bolt passing through the mounting ear (11). The bolt passes through the mounting through hole (12) on the mounting ear (11) and is inserted into the threaded connection hole (71). The two are fixed together by threaded connection.

10. The anti-vibration mount according to claim 9, characterized in that: The upper seat body (5) is covered with a rubber cover (9), and a clearance opening (91) coaxial with and in communication with the threaded connection hole (71) is provided at the top of the rubber cover (9).

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