Self-correcting redundancy switching mechanism for spacecraft system and verification method thereof

A technology of redundant switching and verification methods, applied in the field of verification of self-correcting redundant switching mechanisms, can solve the problems of reduced long-term battery life, long failure time, and inability to cover, to simplify design investment, improve diagnostic accuracy, Great realism

CN101628628AInactive Publication Date: 2010-01-20BEIHANG UNIV
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Patent Information

Authority / Receiving Office
CN · China
Current Assignee / Owner
Publication Date
2010-01-20
Estimated Expiration
Not applicable · inactive patent

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Abstract

The invention discloses a self-correcting redundancy switching mechanism for a spacecraft system and a verification method thereof. The invention adds the redundancy switching mechanism with the feature of self-correcting into the spacecraft system and provides the verification method thereof. The subsystems of the each spacecraft are communicated by a 1553B bus, and are respectively communicatedwith a ground monitor and control system by an Ethernet communication module. The ground monitor and control system immediately detects the fault state of the spacecraft system, and injects fault as well as a control instruction, thereby being capable of significantly improving the high efficiency and the safety of the redundancy switching mechanism of a complex system. By accumulating and optimizing expert opinions, the invention can reduce unnecessary backup switch, has significant research meaning for improving the long-time endurance capability, can immediately switch the fault of a key sensitive part, prevents from an uncontrolled state, and guarantees the safe operation of the system. The method has significant meaning for realizing the reliability research of a spacecraft autonomous intelligent control system.
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Description

technical field

[0001] The invention belongs to the fields of aerospace, intelligent control and computer information processing, and particularly relates to a self-correctable redundant switching mechanism and a verification method of the self-correcting redundant switching mechanism that can realize system real-time fault injection. Background technique

[0002] With the development of space technology, the functions and structures of spacecraft are becoming more and more complex, and it is more and more difficult for such a large and complex system to operate exactly as the designer intended. The complexity of the space environment leads to many uncertain factors, and the possibility of hardware and software failure of the spacecraft increases with the complexity of the system. In order to ensure the smooth completion of the mission, the backup redundancy mechanism of the spacecraft system is to solve this problem. important way. The multi-redundancy mechanism of the spa...

Examples

Embodiment

[0069] The verification method provided by the present invention is described by taking the temperature control system 3 as an example.

[0070] The temperature control system 3 is composed of two subsystems: one is the main system A, and the other is the backup system B. The main system A and the backup system B are respectively composed of a control computer and a set of instruments (such as heaters and other equipment) for control and detection. Firstly, the self-redundant switching mechanism provided by the present invention is set in the temperature control system 3, such as Figure 5 shown, and then verify the self-redundant switching mechanism of the subsystem. The specific method is as follows:

[0071] Step 1. Inject the fault.

[0072] The ground monitoring system 7 uses manual methods to select from the fault source database: such as figure 2 As shown, it is assumed that the failure of the cooler A_4 in the main system A of the temperature control system 3 is a ...