A data transmission system and method based on two-way confirmation
A technology of a data transmission system and a data transmission method, which is applied in the direction of error prevention/detection using a return channel, and can solve problems affecting the reliability and safety of spacecraft flight, aborting spacecraft, waste of manpower, material resources and financial resources, etc. Achieve the effect of avoiding test process suspension or operation failure, improving continuity, and data accuracy
Active Publication Date: 2017-11-28
BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST +1
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Problems solved by technology
If there is data loss, data variation or data delay in the data transmission link, the test process of the spacecraft will be suspended, and the flight reliability and safety of the spacecraft will be affected, which will cause a lot of waste of manpower, material resources and financial resources.
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[0043] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments.
[0044] Such as figure 1 As shown, a data transmission system based on two-way confirmation is composed of a data sending module and a data receiving and returning module. The data sending module is composed of a data generation module, a data transmission module, a data transmission 3-times retransmission module and a data comparison module; the data receiving and returning module is composed of a data receiving module, a data returning 3-times retransmitting module and a data returning module .
[0045] The data generation module of the data sending module generates data, and transmits the generated data to the data transmission module. At the same time, the data transmission module waits for a data receiving request from the data receiving module of the data receiving and returning module.
[0046] The data receiving module sends a data r...
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The invention belongs to the field of aerospace technology, and specifically discloses a data transmission system and method based on two-way confirmation. The system consists of a data sending module and a data receiving and returning module. The data sending module consists of a data generating module, a data 3-pass retransmission module and a data comparison module, the data receiving and returning module is composed of a data receiving module, a data returning 3-pass retransmitting module and a data returning module; the method includes: the data generation module transmits the generated data to Data transmission module, data transmission between the data transmission module and the data transmission module, data reception and return module for data reception and return, data comparison module compares the data transmitted by the data transmission module with the data returned by the data return module . The invention can tolerate faults in time and re-initiate data transmission to ensure the continuity and integrity of data transmission during the operation of the spacecraft, thereby ensuring the continuity, reliability and safety of the operation of the spacecraft.
Description
technical field [0001] The invention belongs to the technical field of aerospace reliability and data transmission, and in particular relates to a data transmission system and method based on two-way confirmation. Background technique [0002] With the continuous development of space technology, the functions and structures of spacecraft are becoming more and more complex. It is becoming more and more difficult for such a complex system to operate in the way expected by the designer. With the continuous increase of system functional modules, the mutual coupling of software and hardware Potential risks continue to increase, so reliable real-time parallel data transmission between modules is becoming more and more important for the reliable operation of spacecraft. Due to the intelligent requirements of the spacecraft at this stage, the system operation relies on the data interaction between the modules in the timing mode or command-response mode, in which the reliability and ...
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IPC IPC(8): H04L1/16
Inventor 窦小明杨飞吴晓蕊谭佳琳刘海东
Owner BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST