On-orbit wireless light transmission device

Abstract

The utility model relates to the technical field of wireless transmission, in particular to an on-orbit wireless optical transmission device which moves upwards in a cargo package mode and comprises a first on-orbit wireless optical transmission device and a second on-orbit wireless optical transmission device. The use modes of the first in-orbit wireless light transmission device and the second in-orbit wireless light transmission device are adjusted, signal wireless connection between a single cabin body and / or different cabin bodies is achieved, and the first in-orbit wireless light transmission device is autonomously installed on a load adapter controlled outside the cabin through a mechanical arm; and the second in-orbit wireless light transmission device is mounted by using a handrail on the cabin wall as a mounting and fixing interface. By applying the device, the problems that the newly added extravehicular load information link optical fiber is insufficient, and the existing extravehicular optical fiber cannot be used due to failure can be solved; the device can be used independently or in a combined mode, application scenes are diversified, on-orbit replacement is supported, the robustness of an information link of the whole system can be improved, and long-life use of the system is guaranteed.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of wireless transmission, in particular to an on-orbit wireless optical transmission device. BACKGROUND

[0002] Space stations and other space infrastructure adopt the mode of on-orbit assembly and splicing of multiple cabin sections to obtain larger structural space and more installation positions to meet the simultaneous on-orbit use of multiple load devices, and a large number of power supply and information cables are laid on the inner and outer surfaces of the cabin to realize the interconnection and intercommunication between devices. Currently, the cables are installed on the ground and launched into orbit with the cabin, and have the same service life as the cabin.

[0003] However, the current cable installation method has the following problems: on the one hand, the extravehicular cable is basically laid below the metal radiator, which also makes it difficult to troubleshoot and determine the fault point when information transmission problems occur, and it is not easy to maintain and replace, so once the information connection cable fails, the device cannot work; on the other hand, each cabin is assembled into a large multi-cabin section structure through node docking, and the interconnection cables between each cabin need to pass through the node cabin during on-orbit work, and the inner and outer cables of the node cabin are fixed in the protective plate and cannot be maintained and replaced on orbit, and once damaged, the information cannot be exchanged between single cabins; on the other hand, with the application and expansion of space stations, various new loads need to be continuously installed outside the cabin. Since the previously laid optical cable resources have been fixed and bound to the existing load devices, the newly installed load cannot transmit load information to the cabin for processing through the existing optical fiber.

[0004] Therefore, how to provide an on-orbit wireless optical transmission device that can be installed on orbit to realize signal connection between different cabins when signal failure occurs between each cabin section of an on-orbit space station and other multi-cabin spacecraft becomes a technical problem that needs to be solved at present. SUMMARY

[0005] The embodiments of the present application provide an on-orbit wireless optical transmission device to solve the problem of failure to interconnect and intercommunicate or failure of single-cabin device information link to be connected, or failure of newly added load to be newly laid optical cable, between each cabin section of an on-orbit space station and other multi-cabin spacecraft.

[0006] In a first aspect of the embodiments of the present application, an on-orbit wireless optical transmission device is provided, which is uplink by a cargo bag mode, and includes a first on-orbit wireless optical transmission device and a second on-orbit wireless optical transmission device. By adjusting the use mode of the first on-orbit wireless optical transmission device and the second on-orbit wireless optical transmission device, signal wireless connection between a single cabin and / or different cabins is realized, wherein

[0007] The first on-orbit wireless optical transmission device is installed on a load adapter controlled by a mechanical arm outside the cabin;

[0008] The second on-orbit wireless optical transmission device is installed by using a handrail on a cabin wall as a mounting fixed interface.

[0009] The application provides an on-orbit wireless optical transmission device, which is uploaded in a cargo bag mode and comprises a first on-orbit wireless optical transmission device and a second on-orbit wireless optical transmission device. By adjusting the use modes of the first on-orbit wireless optical transmission device and the second on-orbit wireless optical transmission device, the signal wireless connection between a single cabin and / or different cabins is realized. The first on-orbit wireless optical transmission device is autonomously mounted on a load adapter controlled outside the cabin by a mechanical arm. The second on-orbit wireless optical transmission device is installed by using a handrail on a cabin wall as a mounting fixed interface.

[0010] The on-orbit wireless optical transmission device provided by the application can solve the problems of insufficient optical fiber of a newly added extravehicular load information link and the problem that an existing extravehicular optical fiber cannot be used due to failure. The on-orbit wireless optical transmission device provided by the application has two types, wherein the first on-orbit wireless optical transmission device is corresponding to autonomous installation by a mechanical arm, and the second on-orbit wireless optical transmission device is corresponding to installation by an astronaut. The two types of devices can be used alone or in combination, and the application scenarios are various. The on-orbit wireless optical transmission device supports on-orbit replacement, can improve the robustness of the whole system information link, and ensures the long-life use of the system. In addition, the on-orbit installation is a regular action, and the required resource requirement is less, so the on-orbit installation can be combined with other extravehicular tasks to be executed.

[0011] The above description is only a summary of the technical solutions of the application. In order to more clearly understand the technical means of the application, the application can be implemented according to the content of the specification, and in order to make the above and other purposes, characteristics and advantages of the application more obvious and easy to understand, the following specific embodiments of the application are described. BRIEF DESCRIPTION OF DRAWINGS

[0012] Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The accompanying drawings are included to provide a description of the preferred embodiments and are not meant to limit the present application. Moreover, the same reference numerals in different drawings represent the same or similar components. In the drawings:

[0013] Figure 1 FIG. 1 is a structural schematic diagram of a first on-orbit wireless optical transmission device in an on-orbit wireless optical transmission device provided by an embodiment of the application;

[0014] Figure 2 FIG. 2 is a structural schematic diagram of a second on-orbit wireless optical transmission device in an on-orbit wireless optical transmission device provided by an embodiment of the application;

[0015] Figure 3A schematic diagram of the interface structure for installing and fixing a second on-orbit wireless optical transmission device to a space station handrail, provided in an embodiment of this application;

[0016] Figure 4 A schematic diagram of a connector socket and cable structure in an on-orbit wireless optical transmission device provided in this application embodiment;

[0017] Figure 5 A schematic diagram of the installation layout for the first and third faults in an on-orbit wireless optical transmission method provided in an embodiment of this application;

[0018] Figure 6 A schematic diagram of the installation layout for a second fault in an on-orbit wireless optical transmission method provided in an embodiment of this application;

[0019] Figure 7 A schematic diagram of the installation layout for a fourth fault in an on-orbit wireless optical transmission method provided in an embodiment of this application;

[0020] Among them, the optical antenna system-1; tracking system-2; power supply system-3; installation and operation interface-4; installation and fixing device-5; connector socket and cable-6; connector socket #1-61; connector socket #2-62; closed loop cable 1-63; connector socket #3-64; connector socket #4-65; closed loop cable 2-66. Detailed Implementation

[0021] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

[0022] See Figures 1-2 , Figure 1 This is a schematic diagram of the structure of the first on-orbit wireless optical transmission device in an embodiment of this application; Figure 2 This is a schematic diagram of the structure of a second on-orbit wireless optical transmission device provided in an embodiment of this application.

[0023] like Figure 1 and Figure 2As shown, the on-orbit wireless optical transmission device, transported via cargo packages, includes a first on-orbit wireless optical transmission device (Type A below) and a second on-orbit wireless optical transmission device (Type B below). By adjusting the usage modes of the first and second on-orbit wireless optical transmission devices, wireless signal connections can be achieved between a single cabin and / or different cabins. The first on-orbit wireless optical transmission device is autonomously installed by a robotic arm onto an externally controlled load adapter; the second on-orbit wireless optical transmission device is installed using a handrail on the cabin wall as a mounting interface.

[0024] In this embodiment of the application, the usage modes include a first usage mode, a second usage mode, a third usage mode, and a fourth usage mode, wherein the first usage mode and the second usage mode are used to realize wireless signal connection of a single cabin; and the third usage mode and the fourth usage mode are used to realize wireless signal connection of different cabins.

[0025] In practical applications, the on-orbit wireless optical transmission device includes two types, A and B, which are transported via cargo packages. Type A is autonomously installed by a robotic arm onto an empty payload adapter outside the cabin; Type B is installed by astronauts outside the cabin, using handrails on the cabin wall as the installation and fixing interface. The AB and BB usage modes can realize wireless signal connection between devices in a single cabin, while the AA and ABBA usage modes can realize wireless signal connection between different cabins.

[0026] In this embodiment of the application, the on-orbit wireless optical transmission device includes: an optical system 1, a tracking system 2, a power supply system 3, an installation and operation interface 4, an installation and fixing device 5, a connector socket, and a cable 6.

[0027] The optical antenna system 1 is used for signal communication and to receive and transmit space laser signals, that is, it mainly completes communication and the reception and transmission of space laser signals.

[0028] The tracking and aiming system 2 is used to automatically track, locate, and control the orientation of the space laser signal, so that the orbital motion platform can achieve real-time alignment with the space laser signal during the motion process; on the other hand, the tracking and aiming system 2 uses the method of camera spot position detection and rear optical path fast reflection mirror to adjust the beam direction to automatically track, locate, and control the orientation of the space laser signal.

[0029] The power supply system 3 is used to provide power to the on-orbit wireless optical transmission device. The first on-orbit wireless optical transmission device is directly powered by the cabin platform through the mounting and fixing device 5. The second on-orbit wireless optical transmission device is powered by a solar panel power supply system, which includes a solar panel uplink locking device and an energy storage battery module.

[0030] The installation operation interface 4 is used to provide a corresponding installation operation interface 4 for installing the first on-orbit wireless optical transmission device and the second on-orbit wireless optical transmission device. The installation operation interface 4 includes a first installation operation interface and a second installation operation interface. The first installation operation interface is a robotic arm capture interface, used to provide an operation interface for the first on-orbit wireless optical transmission device. The second installation operation interface is a handrail, used to provide an operation interface for the second on-orbit wireless optical transmission device. In addition, the second installation fixing device can also be used to connect two independent second on-orbit wireless optical transmission devices.

[0031] The mounting and fixing device 5 includes a first mounting and fixing device and a second mounting and fixing device. The first mounting and fixing device uses an adapter interface for autonomous mounting and fixing of the first on-orbit wireless optical transmission device by a robotic arm. The second mounting and fixing device uses a screw connection interface with an external handrail for mounting and fixing of the second on-orbit wireless optical transmission device via a user terminal (which could be an astronaut) outside the spacecraft. This interface can also be used to fix one Type B device to another. See also... Figure 3 , Figure 3 This is a schematic diagram of the interface structure for installing and fixing an on-orbit wireless optical transmission device to a space station handrail, as provided in an embodiment of this application.

[0032] The connector sockets and cables 6 include four identical rectangular connector sockets for information communication between the on-orbit wireless optical transmission device and the external equipment. The connector sockets can form two sets of cables: the first connector socket and the second connector socket fix the first closed-loop cable, and the third connector socket and the fourth connector socket fix the second closed-loop cable.

[0033] In this embodiment, the first connector socket and the third connector socket are used to connect the on-orbit wireless optical transmission device and the external equipment; the second connector socket is used to fix the cable plug; and the fourth connector socket is used to fix the cable socket.

[0034] In practical applications, the connector socket mainly consists of four rectangular connector sockets (#1, #2, #3, and #4), primarily used for communication of information and control signals between this device and external equipment. The four connector sockets are divided into two pathways: connector sockets #1 and #2 (62) secure closed-loop cables 1-63, connector socket #1 (61) facilitates communication between this device and external equipment, and connector socket #2 (62) is used only for securing the cable plug; connector sockets #3 (64) and #4 (65) secure closed-loop cables 2-66, connector socket #3 (64) facilitates communication between this device and other equipment, and connector socket #4 (65) is used only for securing the cable socket. See also... Figure 4 , Figure 4 This is a schematic diagram of the connector socket and cable structure in an on-orbit wireless optical transmission device provided in an embodiment of this application.

[0035] The on-orbit wireless optical transmission device provided in this application can solve the problems of insufficient fiber optic links for new extravehicular payloads and the inability to use existing extravehicular optical fibers due to malfunctions. The on-orbit wireless optical transmission device provided in this application is of two types: the first type is for autonomous installation by a robotic arm, and the second type is for installation by astronauts. These two types of devices can be used individually or in combination, and are applicable in various scenarios. They also support on-orbit replacement, which can improve the robustness of the information link of the entire system and ensure the long service life of the system. In addition, on-orbit installation is a routine operation with low resource requirements and can be performed in conjunction with other extravehicular activities.

[0036] Based on the above-mentioned device, this application also provides an on-orbit wireless optical transmission method, which specifically includes the following steps: determining the fault type of the on-orbit wireless optical transmission device; determining the maintenance method based on the fault type; and establishing an information link.

[0037] It should be noted that the types of faults mentioned here include, but are not limited to: the first fault, namely cable fault; the second fault, namely the addition of a non-adapter interface and no cabin entry information interface device; the third fault, namely the information link between the two cabins is not working; and the fourth fault, namely the addition of a non-adapter interface and no cabin entry information interface device in both cabins.

[0038] Accordingly, this application provides four embodiments, which can be found in the following examples. Figures 5-7 ,in, Figure 5 A schematic diagram of the installation layout for the first and third faults in an on-orbit wireless optical transmission method provided in an embodiment of this application; Figure 6 A schematic diagram of the installation layout for a second fault in an on-orbit wireless optical transmission method provided in an embodiment of this application; Figure 7 This is a schematic diagram of the installation layout for a fourth fault in an on-orbit wireless optical transmission method provided in an embodiment of this application.

[0039] Example 1: The first fault is the cable fault.

[0040] In this embodiment of the application, determining the repair method and establishing an information link based on the fault type includes:

[0041] The first on-orbit wireless optical transmission device, which is grasped by the robotic arm and exits the cargo airlock, is autonomously installed on the external load adapter and sends a first fault command to the first on-orbit wireless optical transmission device, wherein the first on-orbit wireless optical transmission device is installed on the cargo slide.

[0042] After the first on-orbit wireless optical transmission device receives the first fault command, it controls the telescopic mechanism to rise to the target working height and controls the tracking and aiming system 2 to enter the search state.

[0043] When the tracking system 2 detects a target faulty device, a second on-orbit wireless optical transmission device is installed on the external handrail within a preset range of the target faulty device. The connector for transmitting information on the target faulty device is plugged into the socket of the second on-orbit wireless optical transmission device to establish an information path.

[0044] Using an external power tool, the solar array of the second on-orbit wireless optical transmission device is automatically deployed, and the tracking system of the second on-orbit wireless optical transmission device is controlled to enter the search state. After the second on-orbit wireless optical transmission device and the first on-orbit wireless optical transmission device are detected and mutually captured, a wireless optical path is established, and control information enters the cabin through the payload adapter of the first on-orbit wireless optical transmission device. The solar array is used to power the second on-orbit wireless optical transmission device.

[0045] In practical applications, when a fault occurs in the information cable of a device in a single compartment, preventing the signal from entering the compartment, the following method can be adopted: Device A is installed on the cargo slide and exits the compartment via the cargo airlock. A robotic arm grasps it and autonomously installs it onto the external payload adapter. Device A receives a command and raises its telescopic mechanism to the working height, and the tracking system enters search mode. Then, the astronaut carries Device B out of the compartment and installs it on the external handrail near the faulty device. The astronaut manually unplugs the connector transmitting information from the faulty device and plugs it into the connector socket of Device B, establishing an information path. Then, using an external power tool, the locking screws on the solar panels of Device B are loosened, causing the solar panels to automatically deploy and provide power to Device B. Device B's tracking system also begins autonomous searching. Once the tracking systems of Device A and Device B mutually acquire each other, a wireless optical path is established, and finally, the information enters the compartment through the payload adapter on Device A.

[0046] Example 2: The second fault is the addition of a non-adapter interface and a device without an entry information interface.

[0047] In this embodiment of the application, determining the repair method and establishing an information link based on the fault type further includes:

[0048] After the new equipment is installed, the type of the on-orbit wireless optical transmission device is determined according to the installation location of the new equipment;

[0049] After the on-orbit wireless optical transmission device is installed, connect the connector socket of the on-orbit wireless optical transmission device to the cabin information interface connector to establish an information link.

[0050] In another embodiment of this application, a selection principle is also provided. Specifically, determining the type of the on-orbit wireless optical transmission device based on the installation location of the new device includes: determining a first on-orbit wireless optical transmission device in response to detecting the presence of a controlled payload adapter near the new device; and determining a second on-orbit wireless optical transmission device in response to detecting the absence of a payload adapter near the new device.

[0051] In practical applications, when adding new non-adapter interface or no cabin information interface equipment, the following method can be adopted: After the new equipment is installed, determine whether to select type A or type B based on its installation location. The selection principle is: if there is an unused load adapter near the new equipment, select type A; if there is no load adapter nearby, use type B.

[0052] After installing the wireless optical transmission device near the new equipment, the astronauts unplug the cable plug from connector socket 62 (No. 2) on the transmission device and plug it into the pre-installed connector socket on the new equipment to establish an information link. The astronauts then carry the Type B device and install it near the extravehicular equipment (which has a cross-vehicle interface). The astronauts unplug the cross-vehicle information interface connector from the onboard equipment and then unplug the connectors of the closed-loop cables 1-63 on connector socket 62 (No. 2) on the Type B device and connect them to the cross-vehicle information interface connector to establish an information link. The steps and methods for establishing a wireless communication link between the Type A device and the Type B device are the same as in Example 1.

[0053] Example 3: The third fault is that the information link between the two cabins is not working.

[0054] In this embodiment of the application, determining the repair method and establishing an information link based on the fault type further includes:

[0055] The robotic arm grabs the first on-orbit wireless optical transmission device 1 and device 2, which exit the cargo airlock, and autonomously installs them on the external load adapters of different compartments. The first on-orbit wireless optical transmission device 1 and device 2 are installed on the cargo slide in two separate steps.

[0056] After receiving the third fault command, the first on-orbit wireless optical transmission device 1 and device 2 control the telescopic mechanism to rise to the target working height, and control the tracking and aiming system 1 and tracking and aiming system 2 of the device 1 and device 2 to enter the search state respectively.

[0057] After the tracking and aiming systems 1 and 2 detect that the device 1 and the device 2 have captured each other, a wireless optical path is established, and the information is transmitted into the cabin through the payload adapter on the first on-orbit wireless optical transmission device.

[0058] In practical applications, the following method can be adopted when the information link between the two compartments is not connected: Type A device 1 and Type A device 2 are installed on the cargo slide in two separate steps and exit the cargo airlock. The robotic arm grabs and autonomously installs them on the external load adapters of different compartments. Type A devices 1 and 2 receive instructions to raise the telescopic mechanism to the working height. The tracking systems of both devices are in search mode. After Type A devices 1 and 2 capture each other, a wireless optical path is established. Finally, the information enters the compartment through the load adapter on the Type A device.

[0059] Example 4: The fourth fault is that both cabins have newly added non-compatible interfaces and no cabin entry information interface equipment.

[0060] It should be noted that the selection principles for the first on-orbit wireless optical transmission device and the second on-orbit wireless optical transmission device are as described in Embodiment 2.

[0061] When both cabins have newly added non-adapter interfaces and no cabin entry information interface equipment, the following methods can be adopted:

[0062] The selection principle for type A or type B is the same as in Example 2;

[0063] After installing the wireless optical transmission device near the new equipment in cabin 2, the astronauts unplugged the closed-loop cables 1-63 from connector socket 62 on the transmission device and plugged them into the pre-installed connector socket on the new equipment to establish an information link; the steps for installing the transmission device near the new equipment in cabin 1 are the same as those for cabin 2.

[0064] The astronauts carry two Type B devices (defined as a and b) out of the cabin. Device a is installed on the handrail near the external equipment (with a cross-vehicle interface) in Module 1, and device b is fixed to the handrail of device a. The astronauts unplug the cross-vehicle information interface connector from the external equipment. Then, they unplug the connectors of closed-loop cables 1-63 on connector socket 62 of device a and connect them to the cross-vehicle information interface of the external equipment. Next, they unplug the connectors of closed-loop cables 2-66 on connector socket 64 of device a and closed-loop cables 1-63 on connector socket 62 of device b, respectively, and close the connection to establish an information link. At this time, the newly added equipment in Module 1 and Module 2 establishes an information link through the pathways of devices a and b, completing the entry of external information into the cabin.

[0065] The on-orbit wireless optical transmission method provided in this application can solve the problems of insufficient fiber optic links for new extravehicular payloads and the inability to use existing extravehicular optical fibers due to malfunctions. The on-orbit wireless optical transmission device provided in this application is of two types: the first on-orbit wireless optical transmission device is for autonomous installation by a robotic arm, and the second on-orbit wireless optical transmission device is for installation by astronauts. These two types of devices can be used individually or in combination, and have diverse application scenarios. They also support on-orbit replacement, which can improve the robustness of the information link of the entire system and ensure the long service life of the system. In addition, on-orbit installation is a routine operation with low resource requirements and can be performed in conjunction with other extravehicular activities.

[0066] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to interchangeably. Each embodiment focuses on its differences from other embodiments. In particular, the on-orbit wireless optical transmission device is basically similar to the on-orbit wireless optical transmission method embodiments, so the description is relatively simple; relevant parts can be referred to in the description of the on-orbit wireless optical transmission method embodiments.

[0067] It should be noted that the above description describes specific embodiments of this specification. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recorded in the claims can be performed in a different order than that shown in the embodiments and still achieve the desired results. Furthermore, the processes depicted in the drawings do not necessarily require a specific or sequential order to achieve the desired results. In some embodiments, multitasking and parallel processing are also possible or may be advantageous. Secondly, those skilled in the art should also understand that the embodiments described in the specification are preferred embodiments, and the actions and modules involved are not necessarily essential to the embodiments of this specification.

[0068] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions of other embodiments.

[0069] The preferred embodiments disclosed above are merely illustrative of this specification. The optional embodiments do not exhaustively describe all details, nor do they limit the invention to the specific implementations described. Clearly, many modifications and variations can be made based on the embodiments described herein. These embodiments are selected and specifically described in this specification to better explain the principles and practical applications of the embodiments, thereby enabling those skilled in the art to better understand and utilize this specification. This specification is limited only by the claims and their full scope and equivalents.

Claims

1. An on-orbit wireless optical transmission device, characterized by comprising: The in-orbit wireless optical transmission device transmits data in a package mode, and includes a first in-orbit wireless optical transmission device and a second in-orbit wireless optical transmission device, and the signal wireless connection between a single cabin and / or different cabins is realized by adjusting the use modes of the first in-orbit wireless optical transmission device and the second in-orbit wireless optical transmission device, wherein The first in-orbit wireless optical transmission device is autonomously installed on a load adapter controlled by an extravehicular arm. The second in-orbit wireless optical transmission device is installed by using a handrail on a cabin wall as a mounting fixed interface.

2. The on-orbit wireless optical transmission device according to claim 1, wherein The use modes include a first use mode, a second use mode, a third use mode and a fourth use mode, wherein The first use mode and the second use mode are used to realize the signal wireless connection of a single cabin. The third use mode and the fourth use mode are used to realize the signal wireless connection of different cabins.

3. The on-orbit wireless optical transmission device according to any one of claims 1-2, wherein, The in-orbit wireless optical transmission device includes an optical antenna system, a tracking system, a power supply system, a mounting operation interface, a mounting fixing device, a connector socket and a cable, wherein The optical antenna system is used for signal communication and receives a transmitted space laser signal. The tracking system is used for automatic tracking, positioning and azimuth control of the space laser signal, so as to realize real-time alignment of the space laser signal during the movement of an orbital motion platform. The power supply system is used for providing power for the in-orbit wireless optical transmission device, wherein the first in-orbit wireless optical transmission device is directly powered by a cabin platform through a mounting fixing device, and the second in-orbit wireless optical transmission device is powered by a solar wing power supply system, wherein the solar wing power supply system includes a solar wing uplink locking device and an energy storage battery module. The mounting operation interface includes a first mounting operation interface and a second mounting operation interface, the first mounting operation interface is a mechanical arm capture interface, and is used for providing an operation interface for the first in-orbit wireless optical transmission device, and the second mounting operation interface is a handrail, and is used for providing an operation interface for the second in-orbit wireless optical transmission device. The mounting fixing device includes a first mounting fixing device and a second mounting fixing device, wherein the first mounting fixing device adopts an adapter form interface, and autonomously installs and fixes the first in-orbit wireless optical transmission device by a mechanical arm, and the second mounting fixing device adopts a form interface of screw connection with an extravehicular handrail, and installs and fixes the second in-orbit wireless optical transmission device by a user end out-of-cabin installation. The connector socket and the cable include four same rectangular connector sockets, and are used for information communication between the in-orbit wireless optical transmission device and extravehicular equipment, wherein the connector sockets can constitute two groups of cables, a first connector socket and a second connector socket fix a first closed loop cable, and a third connector socket and a fourth connector socket fix a second closed loop cable.

4. The on-orbit wireless optical transmission device according to claim 3, wherein The tracking system adopts a mode of camera spot position detection and rear optical path quick mirror adjustment of beam pointing to automatically track, position and azimuth control the space laser signal.

5. The on-orbit wireless optical transmission device according to claim 3, wherein The second mounting fixing device can also be used to connect two independent second on-orbit wireless optical transmission devices.

6. The on-orbit wireless optical transmission device according to claim 3, wherein The first connector socket and the third connector socket are used to connect the on-orbit wireless optical transmission device and the extravehicular device. The second connector socket is used to fix the cable plug. The fourth connector socket is used to fix the cable socket.

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