Information system framework design method of spacecraft assembly

An architecture design and information system technology, applied in the field of information system architecture design of spacecraft assemblies, can solve problems such as difficulty in unified management, and achieve the effects of ensuring smooth progress, reducing data confusion, and reducing difficulty

Inactive Publication Date: 2018-08-24
BEIJING SPACE TECH RES & TEST CENT
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Problems solved by technology

[0003] The purpose of the present invention is to provide an information system architecture design method for a spacecraft assembly,

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  • Information system framework design method of spacecraft assembly
  • Information system framework design method of spacecraft assembly
  • Information system framework design method of spacecraft assembly

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Embodiment approach

[0039] According to an embodiment of the present invention, step S1 includes:

[0040] S11. Design the platform bus system 1 in each spacecraft, and the docking bus system 2 of each platform bus system 1 after connecting each spacecraft as a composite body;

[0041] Such as figure 2 As shown, according to an embodiment of the present invention, two spacecrafts, a docking spacecraft and a target spacecraft, are connected to form a combined body. In this embodiment, the platform bus system 1 adopts a 1553B bus system. Docking bus system 2 adopts 1553B bus system. In this embodiment, there is a platform bus system 1 in both the docking spacecraft and the target spacecraft.

[0042] Combine figure 2 with image 3 As shown, in the docking spacecraft, the platform bus system 1 is connected to different sub-systems, such as data management sub-system, instrument and lighting sub-system, environmental control sub-system, crew sub-system thermal control sub-system, measurement control and...

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Abstract

The invention relates to an information system framework design method of a spacecraft assembly. The method comprises the steps of S1, designing an information transmission link of each spacecraft, thus allowing the information transmission link to communicate with one another after the spacecrafts are connected to form the assembly; and S2, designing a remote measurement and remote control link of each spacecraft based on the information transmission links, thus allowing the remote measurement and remote control links to communicate with one another after the spacecrafts are connected to formthe assembly. Through building the physical connection path for each spacecraft, the message interaction paths are built among the spacecrafts. Via a platform bus system in each spacecraft, communication and data exchange requirements of each spacecraft under an independent flying state are met. Meanwhile, via a butt-joint bus system and a data transceiving bus system, the platform bus systems inthe spacecrafts are connected with one another, and the information networking of the assembly is achieved. Via the abovementioned settings, the condition that the information transmission links, constructed based on the abovementioned system, of the assembly is applied to sharing and unified control of data information of the spacecraft assembly can be ensured.

Description

Technical field [0001] The invention relates to an information system architecture design method, in particular to an information system architecture design method of a spacecraft assembly. Background technique [0002] The spacecraft information system, as an important functional system to support spacecraft’s missions in orbit, uses technologies such as bus, network, and radio frequency communication to complete the information management between various internal functional units, as well as the communication management with external systems such as the ground, to ensure aerospace The healthy and stable operation of the device supports the completion of various tasks. Due to the different mission requirements of different spacecraft, the design of the information system is also different. When two or more spacecraft complete the space rendezvous and docking, a composite spacecraft is formed, referred to as a composite. For composite spacecraft that are rigidly connected in sp...

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Application Information

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IPC IPC(8): H04L12/40
CPCH04L12/40006H04L12/40052H04L2012/4028
Inventor 梁克杨宏刘宏泰南洪涛李光日王玮高延超孙犇陈瑞勋
Owner BEIJING SPACE TECH RES & TEST CENT
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