Manned spacecraft in-cabin test load interface support system

Abstract

The invention relates to the field of aerospace information processing, in particular to a manned spacecraft in-cabin test load interface support system, comprising an instruction forwarding module which communicates with a test load and a spacecraft platform through a 1553B bus network and is used for receiving a bus instruction from the spacecraft platform and forwarding the bus instruction to the test load; the state acquisition module communicates with the test load and the spacecraft platform through a 1553B bus network and is used for acquiring working state information of the test load and forwarding the working state information to the spacecraft platform; and the high-speed data transmission module communicates with the test load through a wireless network, communicates with the spacecraft platform through a high-speed data line, and is used for receiving the test data of the test load and forwarding the test data to the spacecraft platform. According to the invention, a standardized information support interface can be provided for the test load, interface standardization is realized, the wiring scale of the manned spacecraft can be reduced, and the layout flexibility of the test load and the space utilization rate of the manned spacecraft are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of space information processing technology, and in particular to a manned spacecraft cabin test load interface support system. BACKGROUND

[0002] During the on-orbit operation of manned spacecraft, a variety of space science and technology tests such as material science, fluid physics, and life science can be carried out by taking full advantage of the special environment in space, such as microgravity, high vacuum, and strong radiation. These tests are usually completed by various types of test loads, and the normal operation of the test loads depends on the mechanical installation, power supply support, information interaction, and thermal control management interfaces provided by the spacecraft platform.

[0003] In terms of information support, the spacecraft platform needs to provide instruction control, state monitoring, and test data transmission functions for the test loads. Under the traditional mode, the spacecraft platform usually configures a dedicated instruction cable, state acquisition cable, and high-speed data cable for each test load. This "one load one interface" design mode results in a large number of cables, significant weight increase, occupation of valuable carrying resources, and also increases the complexity and integration difficulty of the spacecraft system.

[0004] In addition, due to the differences in information interface types, communication protocols, and electrical characteristics of different test loads, the spacecraft platform often needs to develop information support interfaces for each test load, resulting in non-uniform platform technology status, increasing the system development risk and cost. On the other hand, the non-standardization of the interface also limits the interchangeability and layout flexibility between test loads, making some scientific tests unable to be implemented due to interface incompatibility or wiring limitations. SUMMARY

[0005] The present application aims to provide a manned spacecraft cabin test load interface support system to solve the problems of a large number of cables, heavy weight, non-standard interfaces, and poor load interchangeability of the spacecraft platform.

[0006] To achieve the above-mentioned purpose, the technical solution of the present application is as follows: A manned spacecraft cabin test load interface support system, comprising: An instruction forwarding module, which communicates with the test load and the spacecraft platform through a 1553B bus network, and is used to receive bus instructions from the spacecraft platform and forward them to the test load; A state acquisition module, which communicates with the test load and the spacecraft platform through a 1553B bus network, and is used to acquire the working state information of the test load and forward it to the spacecraft platform; The high-speed data transmission module communicates with the test load through a wireless network and communicates with the spacecraft platform through a high-speed data line, and is used for receiving test data of the test load and forwarding the test data to the spacecraft platform.

[0007] Further, the 1553B bus network comprises a primary 1553B bus cable, a secondary 1553B bus cable, a bus controller and a remote terminal; wherein, The bus controller is arranged on the spacecraft platform, the command forwarding module and the state acquisition module respectively, and the remote terminal is arranged on the command forwarding module, the state acquisition module and the test load respectively; The remote terminal arranged on the command forwarding module is connected with the bus controller arranged on the spacecraft platform through the primary 1553B bus cable, and the bus controller arranged on the command forwarding module is connected with the remote terminal arranged on each test load through the secondary 1553B bus cable; The remote terminal arranged on the state acquisition module is connected with the bus controller arranged on the spacecraft platform through the primary 1553B bus cable, and the bus controller arranged on the state acquisition module is connected with the remote terminal arranged on each test load through the secondary 1553B bus cable.

[0008] Further, the command forwarding module comprises: The command receiving module is arranged with the remote terminal and communicates with the bus controller arranged on the spacecraft platform through the primary 1553B bus communication protocol, and is used for screening and receiving the bus command sent by the spacecraft platform to each test load; The command analysis module is used for analyzing the bus command received by the command receiving module to obtain the command type and the destination address; The secondary bus forwarding module is arranged with the bus controller and communicates with the remote terminal arranged on each test load through the secondary 1553B bus communication protocol, and is used for packaging and forwarding the command type and the destination address analyzed by the command analysis module to the corresponding test load according to the secondary 1553B bus communication format.

[0009] Further, the state acquisition module comprises: The secondary bus state receiving module is arranged with the bus controller and communicates with the remote terminal arranged on each test load through the secondary 1553B bus communication protocol, and is used for initiating a state acquisition process to each test load and receiving the working state information of each test load; The data packaging module is used for packaging the working state information of each test load received by the secondary bus state receiving module according to a predetermined format; The main bus sending module is configured with a remote terminal and communicates with a bus controller configured on the spacecraft platform through a level 1553B bus communication protocol, and is used for responding to a state acquisition request of the spacecraft platform and sending working state information of each test payload after being packed by the data packing module to the spacecraft platform.

[0010] Further, the high-speed data transmission module comprises: The wireless network interface module is used for providing a wireless network communication interface for each test payload and receiving test data of each test payload according to a wireless network communication protocol. The data conversion module is used for unpacking and format converting the test data of each test payload received by the wireless network interface module. The high-speed communication module is used for communicating with the spacecraft platform through a high-speed data line and sending the test data of each test payload converted by the data conversion module to the spacecraft platform.

[0011] Further, the wireless network interface module comprises a Wi-Fi signal transceiving device, an antenna and a wireless network card, the wireless network card is configured on each test payload to realize the wireless network communication interface of each test payload, the Wi-Fi signal transceiving device is connected with the antenna and receives the test data of each test payload through the antenna.

[0012] Compared with the prior art, the application can achieve the following beneficial effects: The application standardizes the design of the manned spacecraft test payload interface support system, controls and acquires states of the test payload by using the 1553B bus communication, and transmits high-speed data of the test payload by using the wireless network, thereby reducing the number of cables laid for the test payload by the spacecraft platform, reducing the total weight, saving the valuable carrying resources, ensuring the consistency of the spacecraft technology state and the interface interchangeability of different test payloads, and effectively reducing the development cost of the spacecraft platform and the test payload and shortening the development cycle. BRIEF DESCRIPTION OF DRAWINGS

[0013] The drawings constituting a part of the application are used to provide further understanding of the application, the schematic embodiments of the application and the description thereof are used to explain the application, and do not constitute improper limitation on the application. In the drawings: Figure 1 The logic structure schematic diagram of the manned spacecraft cabin test payload interface support system described in the embodiments of the application; Figure 2 The logic structure schematic diagram of the instruction forwarding module described in the embodiments of the application; Figure 3 The logic structure schematic diagram of the state acquisition module described in the embodiments of the application; Figure 4 Fig. 1 is a schematic diagram of the logical structure of the high-speed data transmission module according to the embodiment of the present application.

[0014] Legend of reference signs: instruction forwarding module 1, instruction receiving module 11, instruction parsing module 12, secondary bus forwarding module 13, state acquisition module 2, secondary bus state receiving module 21, data packaging module 22, main bus sending module 23, high-speed data transmission module 3, wireless network interface module 31, data conversion module 32, high-speed communication module 33, spacecraft platform 4, test load 5. DETAILED DESCRIPTION

[0015] In order to make the purpose, technical scheme and advantages of the present application more clear, the present application is further described in detail below in combination with the drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application, and do not constitute a limitation on the present application.

[0016] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict.

[0017] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second" and the like are only for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features limited by "first", "second" and the like can explicitly or implicitly include one or more of the features. In the description of the present application, unless otherwise specified, the meaning of "a plurality of" is two or more.

[0018] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood through specific circumstances.

[0019] This invention provides an interface support system for test payloads inside a manned spacecraft. It utilizes 1553B bus technology to complete the command control and status acquisition of the test payloads by the spacecraft platform, and uses a wireless network to complete the transmission of test data generated by the test payloads by the spacecraft platform. Each test payload only needs a bus interface and a wireless network interface to carry out space experiments. The interface adopts a standardized design, which can effectively keep the technical status of the manned spacecraft consistent, and various test payloads can be interchanged.

[0020] The invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0021] like Figure 1 As shown, the manned spacecraft in-cabin test payload interface support system includes a command forwarding module 1, a status acquisition module 2, and a high-speed data transmission module 3. The command forwarding module 1 communicates with the spacecraft platform 4 and each test payload 5 via a 1553B bus network. The command forwarding module 1 receives bus commands and status information requests from the spacecraft platform 4, forwards the bus commands to the corresponding test payload 5, and forwards the status information requests to the status acquisition module 2. The status acquisition module 2 communicates with the spacecraft platform 4 and each test payload 5 via a 1553B bus network. The status acquisition module 2 collects the working status information of each test payload 5 in real time and forwards the working status information of the test payload 5 to the spacecraft platform 4 when a status information request is received. The high-speed data transmission module 3 communicates with each test payload 5 via a wireless network and with the spacecraft platform 4 via a high-speed data line (using the Ethernet communication protocol). The high-speed data transmission module 3 receives the test data from each test payload 5 and forwards it to the spacecraft platform 4.

[0022] When test payload 5 conducts tests in orbit, it requires the manned spacecraft's in-cabin test payload interface support system to provide various information interface support. Test payload 5 often has multiple operating modes, and mode switching needs to be performed as needed during in-orbit testing. The switching control command is issued by spacecraft platform 4. To complete this mode switching function, the manned spacecraft's in-cabin test payload interface support system needs to be configured with command forwarding module 1.

[0023] When test payload 5 is operating in orbit, its operational status needs to be monitored by ground personnel to determine whether the test is proceeding normally. The operational status of test payload 5 is collected by spacecraft platform 4 and transmitted to the ground via a communication link. To accomplish this status acquisition function, the manned spacecraft's in-cabin test payload interface support system needs to be equipped with a status acquisition module 2.

[0024] The test load 5 will generate a large amount of test data in the on-orbit test, and the test data needs to be sent to the ground for analysis, so as to serve as the basis for judging whether the test achieves the expected results. The test data has the characteristics of large quantity and high rate, and needs to be transmitted by the special high-speed data link of the spacecraft platform 4. In order to complete the high-speed transmission function, the high-speed data transmission module 3 needs to be configured in the test load interface support system in the manned spacecraft cabin.

[0025] The 1553B bus network includes a primary 1553B bus cable, a secondary 1553B bus cable, a bus controller (BC) and a remote terminal (RT); wherein the bus controller is configured on the spacecraft platform 4, the command forwarding module 1 and the state acquisition module 2 respectively, and the remote terminal is configured on the command forwarding module 1, the state acquisition module 2 and the test load 5 respectively; the remote terminal configured on the command forwarding module 1 is connected with the bus controller configured on the spacecraft platform 4 through the primary 1553B bus cable, and the bus controller configured on the command forwarding module 1 is connected with the remote terminal configured on each test load 5 through the secondary 1553B bus cable; the remote terminal configured on the state acquisition module 2 is connected with the bus controller configured on the spacecraft platform 4 through the primary 1553B bus cable, and the bus controller configured on the state acquisition module 2 is connected with the remote terminal configured on each test load 5 through the secondary 1553B bus cable.

[0026] The spacecraft platform 4, as the superior of the command forwarding module 1, is configured with the bus controller, and sends the bus command and the state acquisition request to the command forwarding module 1 through the primary 1553B bus cable.

[0027] The command forwarding module 1, as the subordinate of the spacecraft platform 4, is configured with the remote terminal for communication with the spacecraft platform 4, and is used for receiving the bus command and the state acquisition request issued by the spacecraft platform 4. The command forwarding module 1, as the superior of the test load 5, is configured with the bus controller for communication with the test load 5, and is used for forwarding the bus command and the state acquisition request to the test load 5.

[0028] The test load 5, as the subordinate of the command forwarding module 1, is configured with the remote terminal, and is used for receiving the bus command and the state acquisition request forwarded by the command forwarding module 1.

[0029] As shown in Figure 2 The command forwarding module 1 includes a command receiving module 11, a command analysis module 12 and a secondary bus forwarding module 13.

[0030] The instruction receiving module 11 is configured to connect with the bus controller of the spacecraft platform 4 through a first 1553B bus cable, that is, the instruction receiving module 11 communicates with the spacecraft platform 4 through a first 1553B bus communication protocol, and the instruction receiving module 11 is configured to receive the state collection request and screen and receive the bus instruction sent by the spacecraft platform 4 to each test load 5. The instruction receiving module 11 determines whether the instruction is a bus instruction sent to the test load 5 by analyzing the address information in the instruction.

[0031] The instruction analysis module 12 is configured to analyze the bus instruction received by the instruction receiving module 11 to obtain the instruction type and the destination address. The instruction analysis module 12 locates and analyzes the instruction type field and the destination address field in the bus instruction to identify the category of the bus instruction and the destination device of the bus instruction.

[0032] The second bus forwarding module 13 is configured to connect with the remote terminal of each test load 5 through a second 1553B bus cable, that is, the second bus forwarding module 13 communicates with each test load 5 through a second 1553B bus communication protocol, and the second bus forwarding module 13 is configured to forward the instruction type and the destination address analyzed by the instruction analysis module 12 to the corresponding test load 5 in a second 1553B bus communication format. Meanwhile, the second bus forwarding module 13 forwards the state collection request to the state collection module 2.

[0033] As shown in Figure 3 The state collection module 2 includes a second bus state receiving module 21, a data packaging module 22, and a main bus sending module 23.

[0034] The second bus state receiving module 21 is configured to connect with the remote terminal of each test load 5 through a second 1553B bus cable, that is, the second bus state receiving module 21 communicates with the remote terminal of each test load 5 through a second 1553B bus communication protocol, and the second bus state receiving module 21 is configured to initiate the state collection process to each test load 5 in real time and receive the working state information of each test load 5 in real time, and send the working state information of each test load 5 to the data packaging module 22 when the state collection request is received.

[0035] The data packaging module 22 is configured to package the working state information of each test load 5 sent by the second bus state receiving module 21 in a first 1553B bus communication format.

[0036] The main bus sending module 23 is configured to connect with the bus controller of the spacecraft platform 4 through the first 1553B bus, that is, the main bus sending module 23 communicates with the spacecraft platform 4 through the first 1553B bus communication protocol, and the main bus sending module 23 is used for sending the working state information of each test payload 5 packaged by the data packaging module 22 to the spacecraft platform 4 in response to the state acquisition request of the spacecraft platform 4.

[0037] The high-speed data transmission module 3 comprises a wireless network interface module 31, a data conversion module 32 and a high-speed communication module 33; the wireless network interface module 31 is used for providing a wireless network communication interface for each test payload 5 and receiving test data generated by each test payload 5 according to a wireless network communication protocol; the data conversion module 32 is used for unpacking and format-converting the test data generated by each test payload 5 received by the wireless network interface module 31; and the high-speed communication module 33 is used for communicating with the spacecraft platform 4 through a high-speed data line and sending the test data of each test payload 5 converted by the data conversion module 32 to the spacecraft platform 4.

[0038] The wireless network interface module 31 comprises a Wi-Fi signal transceiver device, an antenna and a wireless network card, the wireless network card is configured on each test payload 5 to realize the wireless network communication interface of each test payload 5, the Wi-Fi signal transceiver device and the antenna are configured on the high-speed data transmission module 3, the Wi-Fi signal transceiver device is connected with the antenna, and the Wi-Fi signal transceiver device receives the test data generated by each test payload 5 through the antenna.

[0039] Compared with the prior art, the manned spacecraft cabin test payload interface support system provided by the embodiment of the application can achieve the following beneficial effects: (1) The number and weight of cables are significantly reduced By using the 1553B bus to realize the instruction control and state acquisition of the test payload and using the wireless network to realize the transmission of the test data generated by the test payload, the manned spacecraft cabin test payload interface support system greatly reduces the number and total weight of the traditional point-to-point cable layout, saves the valuable spacecraft carrying resources, and improves the launch efficiency.

[0040] (2) The interface standardization is realized, and the load interchangeability is improved The manned spacecraft cabin test payload interface support system provides a unified bus interface and wireless network interface for all test payloads, realizes the standardized design of the information interface, enhances the interchangeability and compatibility between different test payloads, facilitates the on-orbit replacement and upgrade, and expands the flexibility of the test task.

[0041] (3) The system architecture is simplified, and the layout freedom is improved Since it no longer relies on a large number of dedicated cables, the installation location of test loads is no longer limited by the wiring path, which improves the utilization of cabin space and the flexibility of test layout, and is conducive to carrying out more types and more complex space science experiments.

[0042] (4) Flexible parameter adaptation and expanded application scenarios: The threshold requirements of the solid-state power controller can be "customized and modified", supporting the adjustment of parameters such as monitoring cycle and number of times exceeding the threshold according to different loads and test requirements. Whether it is spacecraft load testing or ground simulation verification, it can be flexibly adapted to enhance the universality of design and engineering practicality.

[0043] (5) Improve data transmission efficiency and reliability The wireless network supports real-time transmission of test data, meets the requirements for on-orbit processing and downlink of large-capacity, high-speed test data, ensures the integrity and timeliness of test data, and provides reliable support for ground analysis.

[0044] (6) Enhance system scalability and adaptability Modular design (such as command forwarding, status acquisition, and high-speed transmission modules) facilitates system function expansion and upgrades, adapts to the access requirements of new test payloads in the future, and has good engineering applicability and foresight.

[0045] It should be understood that the various forms of processes shown above can be used to reorder, add, or delete steps. For example, the steps described in this invention disclosure can be executed in parallel, sequentially, or in different orders, as long as the desired result of the technical solution disclosed in this invention can be achieved, and this is not limited herein.

[0046] The specific embodiments described above do not constitute a limitation on the scope of protection of this invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations, and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this invention should be included within the scope of protection of this invention.

Claims

1. A manned spacecraft cabin test load interface support system, characterized by, Comprise: instruction forwarding module, instruction forwarding module through 1553B bus network and test load, spacecraft platform communication, for receiving bus instruction and state acquisition request from spacecraft platform and forwarding to test load; state acquisition module, state acquisition module through 1553B bus network and test load, spacecraft platform communication, for collecting test load working state information and forwarding to spacecraft platform; High-speed data transmission module, high-speed data transmission module through wireless network and test load communication, and through high-speed data line and spacecraft platform communication, for receiving test data of test load and forwarding to spacecraft platform.

2. The test load interface support system for use in a manned spacecraft cabin according to claim 1, wherein, 1553B bus network includes a 1553B bus cable, two 1553B bus cable, bus controller and remote terminal; wherein, bus controller is arranged on spacecraft platform, instruction forwarding module and state acquisition module, respectively, and remote terminal is arranged on instruction forwarding module, state acquisition module and test load, respectively; The remote terminal configured by the instruction forwarding module is connected with the bus controller arranged on the spacecraft platform through the first 1553B bus cable, and the bus controller configured by the instruction forwarding module is connected with the remote terminal arranged on each test load through the second 1553B bus cable; The remote terminal configured by the state acquisition module is connected with the bus controller arranged on the spacecraft platform through the first 1553B bus cable, and the bus controller configured by the state acquisition module is connected with the remote terminal arranged on each test load through the second 1553B bus cable.

3. The test load interface support system for use in a manned spacecraft cabin according to claim 2, wherein, The instruction forwarding module comprises: instruction receiving module, configured with remote terminal and communicating with bus controller arranged on spacecraft platform through first 1553B bus communication protocol, for screening and receiving bus instruction and state acquisition request sent by spacecraft platform to each test load; instruction analysis module, for analyzing bus instruction received by instruction receiving module, obtaining instruction type and destination address; Second bus forwarding module, configured with bus controller and communicating with remote terminal arranged on each test load through second 1553B bus communication protocol, for packing and forwarding instruction type and destination address analyzed by instruction analysis module to corresponding test load according to second 1553B bus communication format.

4. The test load interface support system for use in a manned spacecraft cabin according to claim 2, wherein, The state acquisition module comprises: Second bus state receiving module, configured with bus controller and communicating with remote terminal arranged on each test load through second 1553B bus communication protocol, for initiating state acquisition process to each test load and receiving working state information of each test load; Data packing module, for packing working state information of each test load received by second bus state receiving module according to predetermined format; Main bus sending module, configured with remote terminal and communicating with bus controller arranged on spacecraft platform through first 1553B bus communication protocol, for responding to state acquisition request of spacecraft platform and sending working state information of each test load packed by data packing module to spacecraft platform.

5. The test load interface support system for use in a manned spacecraft cabin according to claim 1, wherein, High-speed data transmission module comprises: a wireless network interface module configured to provide a wireless network communication interface for each test load and receive test data generated by each test load according to a wireless network communication protocol; a data conversion module configured to unpack and convert the test data generated by each test load received by the wireless network interface module; a high-speed communication module configured to communicate with the spacecraft platform through a high-speed data line and transmit the test data of each test load converted by the data conversion module to the spacecraft platform.

6. The test load interface support system for use in a manned spacecraft cabin according to claim 5, wherein, The wireless network interface module includes a Wi-Fi signal transceiver, an antenna, and a wireless network card. The wireless network card is arranged on each test load to provide a wireless network communication interface for each test load. The Wi-Fi signal transceiver is connected to the antenna and receives the test data generated by each test load through the antenna.

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