A low-orbit small satellite fault-tolerant system and method

Abstract

The invention discloses a low-orbit small satellite fault-tolerant system and method. The system comprises a storage component interface, first, second and third processors arranged in parallel, first, second and third logic judgment modules arranged in parallel, and a peripheral interface. The three processors can be set as master, slave, or cold standby, respectively. The master and slave process the data and instructions accessed by the storage unit interface, and the cold standby machine does not work. Each logic judging module is communicatively connected with two of the first, second andthird processors. The output results of the two processors can be compared respectively, and one output signal can be selected to output to the peripheral interface and the data storage unit according to the comparison results, or the remaining another processor can be started. The method is based on the system, wherein the two processors are simultaneously operated and the output signals are compared, and the third processor is started for output comparison when the comparison fails to pass, and the output is finally determined, thereby solving the problems of insufficient fault detection capability of the host computer and low reliability of the output results in the prior art.

Description

technical field [0001] The invention belongs to the technical field of processor fault tolerance, and in particular relates to a low-orbit small satellite fault-tolerant system and method. Background technique [0002] For micro-satellites operating in orbit, processors mostly use high-tech such as micro-nano and micro-electromechanical systems. Due to the high sensitivity of processors to cosmic rays and alpha particles, transient errors will occur; due to small defects, such as high-temperature, low-pressure Specific situations such as certain situations will lead to intermittent failures of the processor; the processor is the control core of the entire satellite system, so it is necessary to design a fault-tolerant processor, and a multi-core redundant design solution is usually used to solve this problem. [0003] Chinese invention patent CN201210103767 discloses an FPGA-based soft-core fault-tolerant spaceborne computer solution, which consists of dual-redundant soft-co...

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Problems solved by technology

[0005] Aiming at the above defects or improvement needs of the prior art, the present invention provides a low-orbit small satellite fault-tolerant system and method, the purpose of which is to use multiple identical processors, so that two of them can work simultaneously and perform output comparison and When the comparison fails, start another processor for output comparison, and finally decide the output, thereby solving the problems of insufficient host fault detection capability and low reliability of output results in the prior art

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