Spacecraft exposure test payload support platform

Abstract

The spacecraft exposure test load support platform belongs to the technical field of manned spacecraft platform, and adopts a classified centralized interface scheme, which can meet the power supply, information and heat control resource requirements of large-scale exposure test loads, can be well applied to different exposure test loads, and is better in platform reliability and advancement. Meanwhile, the exposure test load support platform is configured with a plurality of load stations, can support mechanical reliable connection of a plurality of exposure test loads through standardized load adapters, can provide power supply, information and heat control connection channels for each exposure test load, and supports on-orbit replacement of any exposure test load, so that the space application benefit of the platform is greatly improved.

Description

Technical Field

[0001] This invention relates to a spacecraft exposure test payload support platform, belonging to the field of manned spacecraft platform technology. Background Technology

[0002] One of the main tasks of large manned spacecraft is to continuously conduct large-scale space science and technology experiments. Large manned spacecraft typically have several scientific experiment cabinets inside the cabin and several exposed test platform payload positions outside the cabin. Through the cyclical use of scientific experiment cabinets and exposed test platforms, support and guarantee are provided for the continuous conduct of payload experiments in multiple disciplines such as space life science, microgravity science, aerospace medicine, and new aerospace technologies.

[0003] Compared with space laboratories and cargo spacecraft, large manned spacecraft exposure test payloads, represented by space stations, have some new characteristics as follows:

[0004] ① Replaceable test payloads: In order to support exposure tests in a cyclical manner, large manned spacecraft are designed with replaceable exposure test payloads outside the cabin. With the participation of astronauts, the payloads are taken care of by the space robotic arm to complete the extravehicular activity, on-orbit installation, and replacement.

[0005] ② Larger test payload scale: Large manned spacecraft have a dedicated exposure test platform outside the cabin, which can support dozens of exposure test payloads at the same time for carrying out multidisciplinary exposure test projects;

[0006] ③ More test data: After most of the exposed test loads start the test mission in orbit, they continue to work and generate a large amount of test data every day, which needs to be transmitted to the ground in a timely manner;

[0007] ④ Lagging development of test payloads: The establishment and development of replaceable exposure test payloads are relatively lagging. During the ground development phase of manned spacecraft, the manned spacecraft exposure test platform cannot be matched and verified with all exposure test payloads.

[0008] Therefore, given the characteristics of large manned spacecraft exposure test payloads—namely, their replaceability, larger scale, greater amount of test data, and delayed payload development—the payload support solutions adopted by space laboratories and cargo spacecraft are no longer sufficient to meet the needs of large manned spacecraft exposure test payloads. To better support the large-scale implementation of various exposure test projects for manned spacecraft, a reusable and highly reliable payload support platform needs to be designed to adapt to the application requirements of large manned spacecraft exposure test payloads. Summary of the Invention

[0009] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a spacecraft exposure test payload support platform that supports large manned spacecraft to carry out large-scale space science and technology experiments in extravehicular circulation in a replaceable, universal and standardized manner.

[0010] The technical solution of this invention is: a spacecraft exposure test payload support platform, comprising:

[0011] The exposure test platform includes a load station and a load adapter. The exposure test load is installed through the load station and connected to the exposure test load outside the chamber through the load adapter. It is used to provide various interfaces for the exposure test load, including mechanical installation interface, power supply interface, information interface, and thermal control fluid circuit interface.

[0012] The onboard equipment includes a payload management unit, an external payload management device, an external payload power distribution unit, a payload network switch, and a thermally controlled four-way valve. The payload management unit is used for centralized status data management and command control of the in-cabin scientific experimental cabinets and external exposure test payloads. The external payload management device, as an extension of the payload management unit, is used for centralized status data management and command control of several external exposure test payloads. The external payload power distribution unit is used for centralized power supply and power allocation for each exposure test payload. The payload network switch is used to provide multiple gigabit-rate network interfaces for each exposure test payload. The thermally controlled four-way valve is used to connect the exposure test payloads to the load fluid circuit of the exposure test platform.

[0013] Furthermore, the load adapter includes an active end and a passive end;

[0014] The passive end is installed on the exposure test platform and launched into orbit with the manned spacecraft.

[0015] The active end and the exposure test payload are transported to the manned spacecraft by a cargo spacecraft. Astronauts assemble the active end and the exposure test payload in orbit to form the exposure test payload assembly. Under the care of the space robotic arm, the exposure test payload assembly is ejected from the spacecraft. The installation of the exposure test payload on the designated payload position on the exposure test platform is completed by capturing and locking the active end and the passive end. When an exposure test payload completes its in-orbit mission, it is disassembled under the care of the space robotic arm by unlocking the active end and the passive end, thus releasing the payload position resources on the exposure test platform that it occupied.

[0016] Furthermore, the external load management device is provided in several units for accessing the 1553B bus of the exposed test load, and the number of 1553B bus terminals supported by the external load management device is 1 to 30.

[0017] Furthermore, the load network switch enables fiber optic access to the exposed test load by adding an optical splitter in the optical cable, with an access rate of not less than 1000Mbps.

[0018] Furthermore, depending on the maximum number of exposed test payloads, one or more external payload power distribution units are configured to provide centralized power to each exposed test payload; each external payload power distribution unit is designed with one 100V power input to receive 100V power from the manned spacecraft platform and centrally provide 20 relay-controlled 100V power outputs; the connection and disconnection of the 20 relay power outputs are controlled by sending commands through the exposed test payload management equipment.

[0019] Furthermore, each 100V power output is redundantly backed up at multiple points and on multiple lines, and the maximum power output of each output is set through the external load power distribution unit software.

[0020] Furthermore, based on the maximum number of exposure test loads, one load management unit and one or more external load management devices are configured to centrally manage and control the data of each exposure test load, and centrally manage the on-orbit status and control command data of each load.

[0021] Furthermore, the 1553B load bus network has two layers, including an internal 1553B bus inside the load chamber and an external 1553B bus outside the load chamber, connecting the load management unit, the external load management device, and each exposure test load. The internal 1553B bus inside the load chamber uses the load management unit as the bus controller BC terminal and the external load management device as the bus terminal RT terminal. The external 1553B bus outside the load chamber uses the external load management device as the bus controller BC terminal and the exposure test load as the bus terminal RT terminal.

[0022] Furthermore, the payload network switch provides fiber optic access interfaces for each exposed test payload. Each exposed test payload is connected to the payload network switch via optical cable, and accesses the manned spacecraft communication network through the payload network switch to build a payload test data network, realize network data exchange, and transmit payload space test data and experimental data.

[0023] Furthermore, the load adapter is equipped with an independent fluid circuit assembly. The active end is equipped with a cold plate and a fluid circuit disconnector. The cold plate is used to contact the heat dissipation surface of the exposed test load to remove the load heat. The passive end is equipped with a fluid circuit disconnector, which is connected to the active end fluid circuit disconnector and is used to connect to the external load fluid circuit of the manned spacecraft platform.

[0024] The advantages of this invention compared to the prior art are:

[0025] 1) The exposure test load support platform adopts a classified and centralized interface scheme, which can simultaneously meet the power supply, information, and thermal control resource requirements of large-scale exposure test loads. It is well-suited for different exposure test loads, and the platform has better reliability and advanced features.

[0026] 2) The platform supports the configuration of several load stations for the exposure test load. Through standardized load adapters, it can simultaneously support the mechanically reliable connection of multiple exposure test loads. It also provides power supply, information and thermal control connection channels for each exposure test load and supports the on-orbit replacement of any exposure test load, which greatly improves the space application efficiency of the platform.

[0027] 3) The load adapter interface is modularly designed according to functional categories such as installation interface, power supply interface, information interface, and thermal interface, with each functional module being independent of the others. The external interfaces of each functional module adopt a standardized design, with the same form and definition for the same type of interface. Specific exposure test loads can be selected according to their own needs, which greatly improves the versatility of the platform. Attached Figure Description

[0028] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0029] Figure 1 This is a schematic diagram of the power supply interface for the exposure test load involved in a specific embodiment of the present invention;

[0030] Figure 2 This is a schematic diagram of the exposure test load information interface (1553B bus interface) involved in a specific embodiment of the present invention;

[0031] Figure 3 This is a schematic diagram of the exposure test load information interface (fiber optic interface) involved in a specific embodiment of the present invention;

[0032] Figure 4 This is a schematic diagram illustrating the relative positions of the exposure test load and the load adapter as described in a specific embodiment of the present invention;

[0033] Figure 5 This is a schematic diagram of the load adapter and the power supply interface of the exposure test load involved in a specific embodiment of the present invention;

[0034] Figure 6 This is a schematic diagram of the load adapter and the interface for exposure test load information involved in a specific embodiment of the present invention;

[0035] Figure 7This is a schematic diagram of the load adapter and the thermal control interface of the exposure test load involved in a specific embodiment of the present invention. Detailed Implementation

[0036] To better understand the above technical solutions, the technical solutions of the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the embodiments of the present invention and the specific features in the embodiments are detailed descriptions of the technical solutions of the present invention, rather than limitations on the technical solutions of the present invention. In the absence of conflict, the embodiments of the present invention and the technical features in the embodiments can be combined with each other.

[0037] The following description, in conjunction with the accompanying drawings, provides a more detailed account of the spacecraft exposure test payload support platform provided in this embodiment of the invention. Specific implementation may include: a platform consisting of onboard equipment, an exposure test platform (including payload adapters), and related cables; several universal payload stations and standardized payload adapters configured on the exposure test platform; and a connection between the exposure test payload and the manned spacecraft exposure test platform established through the payload adapters. This provides support for the exposure test payload in terms of mechanical installation, 100V power supply, various information interfaces (including data transmission interfaces, inspection interfaces, etc.), and thermal control fluid circuits, among other interface resources. All supported exposure test payloads can be replaced in orbit.

[0038] The payload adapter consists of two parts: an active end and a passive end. The passive end of the payload adapter is installed on the manned spacecraft's exposure test platform and is launched into orbit with the manned spacecraft. The active end of the payload adapter and the exposure test payload are transported to the manned spacecraft by a cargo spacecraft. Astronauts assemble the active end of the payload adapter and the exposure test payload in orbit to form the exposure test payload assembly. Under the care of the space robotic arm, the exposure test payload assembly is ejected from the spacecraft. Through capture and locking between the active and passive ends of the payload adapter, the installation of the exposure test payload on the designated payload station on the exposure test platform is finally completed. When an exposure test payload completes its in-orbit mission, under the care of the space robotic arm, the exposure test payload is disassembled by unlocking between the active and passive ends of the payload adapter, releasing the payload station resources occupied on the exposure test platform.

[0039] The onboard equipment includes a load management unit, an external load management device, an external load power distribution unit, a load network switch, active and passive load adapter terminals, and a thermal control four-way valve. A categorized, centralized approach is adopted for power supply, command control, status monitoring, test data transmission, and active temperature control of the exposed test loads. The load management unit provides centralized status data management and command control for both the in-cabin scientific experimental cabinets and the external exposed test loads. The external load management device, as an extension of the load management unit, provides centralized status data management and command control for several external exposed test loads. The external load power distribution unit provides centralized power supply and power allocation for each exposed test load. The load network switch provides multiple gigabit-rate network interfaces for each exposed test load. The active and passive load adapter terminals provide reliable mechanical connections for each exposed test load and provide power, information, and thermal control transmission channels. The thermal control four-way valve connects the exposed test loads to the load fluid circuit of the exposed test platform.

[0040] In this invention, the manned spacecraft uses a payload adapter to support the on-orbit installation and reliable locking of the exposure test payload. The payload adapter interface includes the interface between the payload adapter and the exposure test payload, and the interface between the active and passive ends of the payload adapter. The payload adapter provides the necessary mechanical, electrical, and thermal interface support for the replaceable exposure test payload. The payload adapter interface is modularly designed according to functional categories such as installation interface, power supply interface, information interface, and thermal interface, with each functional module being independent. The external interfaces of each functional module adopt a standardized design; interfaces of the same type have the same form and definition, allowing the exposure test payload to select the appropriate interface according to its own needs.

[0041] In this invention, an external payload management device and a payload network switch are configured to support the information system of each exposure test payload. Each external payload management device can support the access of up to 30 exposure test payloads via the 1553B bus. By setting up a certain number of external payload management devices, the application of large-scale exposure test payloads can be supported simultaneously. The payload network switch achieves fiber optic access for large-scale exposure test payloads by adding an optical splitter to the optical cable, with an access rate of up to 1000Mbps.

[0042] In summary, this invention aims to provide a universal and advanced design for the manned spacecraft exposure test payload support platform. By configuring a payload adapter, the exposure test payload can be replaced in orbit, thereby enabling the payload workstations of the exposure test platform to be reused repeatedly, thus improving the universality, reliability, and advancement of the exposure test payload support platform.

[0043] In the solution provided in the embodiments of the present invention, a classified and centralized approach is adopted, with an architecture design that centrally supplies power to the external load power distribution unit, centrally manages and controls data and commands to the load management unit and external load management equipment, and centrally transmits test data through the load network switch. A universal, standardized, and replaceable load adapter is configured to enable the connection between the exposure test load and the exposure test platform, and all supported exposure test loads can be replaced on-orbit.

[0044] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0045] The exposure test payload support platform provides unified mechanical, power supply, information, and thermal control resource support for all exposure test payloads. It employs a categorized centralized processing strategy for the different resources required by the payloads, featuring an architecture design that centralizes power supply to the external payload power distribution unit, centralized data management and command control of the payload management unit and external payload management equipment, and centralized test data transmission via the payload network switch. It utilizes universal, standardized, and replaceable payload adapters to achieve connectivity between the exposure test payloads and the exposure test platform. The exposure test payload support platform consists of six types of core equipment (external payload power distribution unit, payload management unit, external payload management equipment, payload network switch, payload adapter, and thermal control four-way valve), a 1553B bus, power cables, and optical fibers, establishing a 100V power distribution, information management, data exchange, and thermal exchange hub between the manned spacecraft platform and each exposure test payload.

[0046] Centralized power supply for external load distribution units

[0047] Depending on the maximum number of exposed test payloads, one or more external payload power distribution units are configured to centrally power each exposed test payload. Each external payload power distribution unit is designed with one 100V power input, receiving 100V power from the manned spacecraft platform, and centrally providing 20 relay-controlled 100V power outputs. The connection and disconnection of these 20 power outputs are controlled by commands sent from the external payload management equipment, such as... Figure 1 As shown, each 100V power output adopts a multi-point, multi-line redundant backup design, and the maximum power output of each output is set through the external load power distribution unit software to ensure the reliability of the power output.

[0048] Centralized data management and control of payload management unit and external payload management equipment

[0049] Based on the maximum number of exposed test loads, one load management unit and one or more external load management devices are configured to centrally manage and control the data of each exposed test load, centrally managing the on-orbit status, control commands, and other data of each load. A two-layer load 1553B bus network is designed, including an internal 1553B bus within the load compartment and an external 1553B bus, connecting the load management unit, external load management devices, and each exposed test load. The internal 1553B bus within the load compartment uses the load management unit as the bus controller (BC end) and the external load management device as the bus terminal (RT end); the external 1553B bus uses the external load management device as the bus controller (BC end) and the exposed test load as the bus terminal (RT end), such as... Figure 2 As shown.

[0050] exist Figure 2 In this system, the payload management unit (RT) acts as the bus terminal (RT end) of the main 1553B bus of the manned spacecraft platform, communicating with the platform via the main 1553B bus network. The payload management unit also acts as the BC end, communicating with the external payload management equipment, which in turn communicates with each exposed test payload as the BC end. Each external payload management device can support up to 30 1553B bus terminal (RT) nodes: RT1 to RT30, with a maximum data transmission rate of 1 Mbps.

[0051] As can be seen, in this invention, the payload management unit interacts with the manned spacecraft platform externally, while the external payload management equipment interacts with each exposed test payload internally. This ensures that the exposed test payload information system and the manned spacecraft platform information system are independent of each other, providing two layers of physical isolation. When an exposed test payload experiences an information failure, a command can be sent to cut off the power to the faulty payload, thereby effectively protecting the information security of the manned spacecraft platform.

[0052] Centralized test data transmission of load network switch

[0053] The payload network switch provides fiber optic access interfaces for each exposure test payload. Each exposure test payload is connected to the payload network switch via fiber optic cable, and then connected to the manned spacecraft communication network through the payload network switch to construct a payload test data network (e.g., ...). Figure 3 As shown, network data exchange is achieved, and payload space test (experiment) data is downloaded.

[0054] The fiber optic interfaces configured on the load network switch support the Fiber Ethernet protocol (IEEE 802.3z) by default. With modifications to the load network switch software and fiber optic interface modules, it can also support the FC-AE-1553 and TTE communication protocols. Only one communication protocol can be selected between the load network switch and the exposure test payload at a time; both cannot be supported simultaneously. When using the Fiber Ethernet protocol (IEEE 802.3z), each fiber optic interface of the load network switch can provide a maximum data transmission rate of 1 Gbps for the exposure test payload. When using the FC-AE-1553 communication protocol, each fiber optic interface of the load network switch can provide a maximum data transmission rate of 4.25 Gbps for the exposure test payload. When using the TTE communication protocol, each fiber optic interface of the load network switch can provide a maximum data transmission rate of 1 Gbps for the exposure test payload.

[0055] Within the relay satellite's telemetry and control area, the start and stop of payload test data downlink are controlled by commands sent from the payload management unit. The maximum communication rate that the exposure test payload support platform can provide for simultaneous downlink data to each exposure test payload is limited by the relay satellite link rate.

[0056] Universal and standardized design of load adapter interfaces

[0057] The exposure test payload is supported by setting up a standard payload station and configuring a standard payload adapter on the manned spacecraft exposure test platform. With the participation of astronauts, the exposure test payload is launched outside the spacecraft under the care of the space robotic arm. The payload is captured, corrected and locked between the active and passive ends of the payload adapter. During the locking process, the power supply floating connector, optoelectronic floating connector and liquid circuit floating connector between the active and passive ends of the payload adapter are connected. Finally, the exposure test payload is installed on the designated payload station on the exposure test platform. Through the payload adapter, the power supply, information and liquid circuit connection between the manned spacecraft exposure test platform and the exposure test payload is realized.

[0058] The on-orbit disassembly process of the exposure test payload is the reverse of the installation process. After an exposure test payload completes its on-orbit test mission, the space robotic arm handles the unlocking and separation of the exposure test payload assembly from the passive end of the payload adapter. The exposure test payload assembly is then recovered into the manned spacecraft cabin, releasing the occupied payload adapter workstation for continued use in this exposure test project or other exposure test payload projects, thus realizing the recycling of resources on the manned spacecraft exposure test platform.

[0059] To simplify and standardize the various interfaces between the load adapter and the exposure test load, the load adapter interface is modularly designed according to functional categories such as installation interface, power supply interface, information interface, and thermal interface, with each functional module being independent of the others. The external interfaces of each functional module adopt a standardized design, with the same form and definition for the same type of interface, and specific exposure test loads can be selected according to their own needs.

[0060] like Figure 4 As shown, the mounting interface between the load adapter and the exposure test load adopts a universal design. Specifically, the mounting interface between the load adapter's active end and the exposure test load consists of four mounting lugs (numbered 1-4) on the upper surface of the active end, all on the same plane. Mounting hole 1 on the load adapter's active end is the R-point, and the other three mounting holes (numbered 2, 3, and 4) are positioned identically relative to the R-point on the main body, with all holes having the same diameter. This interface scheme standardizes the mechanical mounting interface between the load adapter's active end and the exposure test load, facilitating the use of standard mounting interface designs for the exposure test load and improving the load adapter's adaptability.

[0061] After the exposure test payload is installed, the manned spacecraft exposure test platform provides 100V power to the payload via the payload adapter to support the payload in carrying out the test mission. It also needs to supply power to the payload adapter for its own status monitoring. Figure 5 As shown, the load adapter and the exposure test load adopt a universal design with bidirectional differentiated power supply interfaces. That is, the load adapter has an internal power supply cable to provide a forward 100V power supply channel for the load, and the power supply capacity supports various specifications; the exposure test load provides a reverse 100V power supply to the active end control unit of the load adapter for the status inspection of the load adapter, and the exposure test load is equipped with a relay to control the power on and off of the load adapter.

[0062] The advantages of this power supply interface design are: ① More reliable and safer load power supply: The load adapter does not participate in the control of the load power supply, but only provides a power supply channel. The load power supply and the load adapter power supply paths are independent of each other. If the load experiences a power failure, it will not affect the space robotic arm's care operation of the load adapter; ② Better power supply efficiency: The exposed test load can select the appropriate power supply according to its own power demand. At the same time, the exposed test load only supplies power to the load adapter when it is being inspected, and does not supply power at other times, saving power resources; ③ Simpler power supply interface: The load adapter maintains a unified external power supply interface, which facilitates the universal design of the load interface and improves the adaptability of the load adapter.

[0063] After the exposure test payload is installed, the manned spacecraft exposure test platform provides an information interface to the payload via the payload adapter, supporting command control, status monitoring, and test data transmission of the payload, while also transmitting the payload adapter's own status. Figure 6 As shown, a general information interface design based on optoelectronic signal integration and inspection mode is adopted. That is, the load adapter is equipped with an optoelectronic connector to provide a transit information transmission channel for the load, including three types of transmission media: optical fiber, coaxial cable, and low frequency cable, which support optical interface, 1553B interface and remote control and telemetry interface respectively; the active end of the load adapter is equipped with an inspection interface, including active and passive inspection modes. In active mode, when the load adapter is powered on, the external load can obtain the complete status of the load adapter, including the hardware and software status of the electronic control unit, equipment temperature, etc. In passive mode, the load adapter does not need to be powered on for inspection, and the external load only collects the on-orbit temperature of the load adapter.

[0064] The advantages of this information interface design are: ① More comprehensive information interface: The load adapter provides diverse information interfaces for the exposed test load, including optical interface, 1553B interface, remote control interface, and telemetry interface. The exposed test load can select the appropriate information interface type according to its own power needs; ② More effective inspection interface: The exposed test load can perform active or passive inspection of the load adapter according to the inspection strategy. Under normal circumstances, passive inspection is mainly used. When necessary, the load adapter is powered on for inspection and active inspection is performed, reducing the frequency of power-on and power-off operations on the load adapter; ③ Simpler information interface: The load adapter has a unified external information interface, which facilitates the universal design of the load interface and improves the adaptability of the load adapter.

[0065] The load adapter provides a thermal interface for high-power exposure test loads, ensuring timely heat dissipation. For example... Figure 7 As shown, a general thermal interface design based on a cold plate and a liquid circuit disconnector is adopted, namely: the load adapter is configured with a relatively independent fluid circuit assembly, the active end is equipped with a cold plate and a liquid circuit disconnector (head), the cold plate is used to contact the heat dissipation surface of the exposed test load to remove the load heat, and the passive end is equipped with a liquid circuit disconnector (seat) connected to the active end liquid circuit disconnector (head) for accessing the external load fluid circuit of the manned spacecraft platform.

[0066] The advantages of this thermal interface design are: ① More independent thermal interface: The load adapter thermal control interface is a fluid loop assembly consisting of a cold plate and a fluid circuit disconnector, and its design is independent of the load adapter's own structure, electrical control unit, power supply, and information interface module; ② More reliable thermal interface: The load adapter fluid loop assembly is connected to the manned spacecraft's external load fluid loop through a four-way valve. When a working fluid leakage fault occurs in the load adapter fluid loop assembly, closing the four-way valve can isolate the fault without affecting platform safety; ③ Simpler thermal interface: The load adapter maintains a unified external thermal interface, which facilitates the universal design of the load interface and improves the adaptability of the load adapter.

[0067] Therefore, the exposure test payload support platform scheme of the present invention makes the manned spacecraft exposure test payload support platform more advanced and versatile, realizes the on-orbit replacement of exposure test payloads, can support the on-orbit application of multiple exposure test payloads at the same time, and improves the reliability and application benefits of the manned spacecraft platform.

[0068] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

[0069] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A spacecraft exposure test payload support platform, characterized in that, include: The exposure test platform includes a load station and a load adapter. The exposure test load is installed through the load station and connected to the exposure test load outside the chamber through the load adapter. It is used to provide various interfaces for the exposure test load, including mechanical installation interface, power supply interface, information interface, and thermal control fluid circuit interface. The onboard equipment includes a load management unit, an external load management device, an external load power distribution unit, a load network switch, and a thermally controlled four-way valve. The load management unit is used for centralized status data management and command control of the in-cabin scientific experimental cabinets and external exposure test loads. The external load management device, as an extension of the load management unit, is used for centralized status data management and command control of several external exposure test loads. The external load power distribution unit is used for centralized power supply and power allocation to each exposure test load. The load network switch provides multiple gigabit-rate network interfaces for each exposure test load. The thermally controlled four-way valve connects the exposure test loads to the load fluid circuit of the exposure test platform. The exposure test load support platform adopts a classified and centralized interface scheme, which classifies and centrally manages and provides power supply, information and thermal control resources through the on-device equipment. The load adapter includes an active end and a passive end; The passive end is installed on the exposure test platform and launched into orbit with the manned spacecraft. The active end and the exposure test payload are transported to the manned spacecraft by a cargo spacecraft. Astronauts assemble the active end and the exposure test payload in orbit to form the exposure test payload assembly. Under the care of the space robotic arm, the exposure test payload assembly is ejected from the spacecraft. The installation of the exposure test payload on the designated payload position on the exposure test platform is completed by capturing and locking the active end and the passive end. When an exposure test payload completes its in-orbit mission, it is disassembled under the care of the space robotic arm by unlocking the active end and the passive end, thus releasing the payload position resources on the exposure test platform that it occupied. Depending on the maximum number of exposed test payloads, one or more external payload power distribution units are configured to provide centralized power to each exposed test payload. Each external payload power distribution unit is designed with one 100V power input to receive 100V power from the manned spacecraft platform and centrally provide 20 relay-controlled 100V power outputs. The connection and disconnection of the 20 relay power outputs are controlled by sending commands through the exposed test payload management equipment. Each 100V power supply output is redundantly backed up at multiple points and on multiple lines, and the maximum power output of each output is set through the external load power distribution unit software. The 1553B bus network has two layers, including the 1553B internal bus inside the load chamber and the 1553B internal bus outside the load chamber, which connects the load management unit, the load management equipment outside the chamber and each exposure test load. The 1553B internal bus in the payload compartment uses the payload management unit as the bus controller BC terminal and the external payload management equipment as the bus terminal RT terminal. The 1553B external load cell bus uses the external load management equipment as the bus controller BC terminal and the exposed test load as the bus terminal RT terminal. The external load management device is provided in several units for accessing the 1553B bus of the exposed test load. The number of 1553B bus terminals supported by the external load management device is 1 to 30. The load network switch enables fiber optic access to the exposed test load by adding an optical splitter in the optical cable, with an access rate of not less than 1000Mbps; Based on the maximum number of exposed test loads, configure one load management unit and one or more external load management devices to centrally manage and control the data of each exposed test load, and centrally manage the on-orbit status and control command data of each load; The payload network switch provides fiber optic access interfaces for each exposed test payload. Each exposed test payload is connected to the payload network switch via optical cable. The payload network switch connects to the manned spacecraft communication network to build a payload test data network, realize network data exchange, and transmit payload space test data and experimental data. The load adapter is equipped with an independent fluid circuit assembly. The active end is equipped with a cold plate and a fluid circuit disconnector. The cold plate is used to contact the heat dissipation surface of the exposed test load to remove the load heat. The passive end is equipped with a fluid circuit disconnector, which is connected to the active end fluid circuit disconnector and is used to connect to the external load fluid circuit of the manned spacecraft platform.

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