Embedded satellite-borne fault-tolerant temperature control system and verification method thereof

Abstract

The invention discloses an embedded satellite-borne fault-tolerant temperature control system and a verification method thereof. The system comprises a satellite management computer, an on-satellite temperature control system and a ground monitoring and fault injection computer; the on-satellite temperature control system comprises a temperature control calculation host machine, a temperature control calculation standby machine and an environmental simulation computer; and the temperature control calculation host machine and the temperature control calculation standby machine are temperature control computers. The verification method comprises the following steps of: 1, initializing a file allocation; 2, initializing the system; 3, beginning simulation; 4, injecting and executing a fault; 5, processing redundant fault tolerance; 6, monitoring the ground and evaluating the fault; and 7, evaluating a fault model and a redundancy strategy of the temperature control system. The fault injection and the verification process of the whole running stage of the real satellite-borne temperature control system are completely realized; and the method is simple, convenient and reliable, and greatly reduces the test time and expense for the practical system.

Description

technical field [0001] The invention relates to an embedded spaceborne fault-tolerant temperature control system and a verification method thereof, belonging to the fields of aerospace, intelligent control and embedded computer information processing. Background technique [0002] The spaceborne system leaves the atmosphere, under the direct sunlight of strong sunlight, periodically enters the shadow of the earth or the moon, and is often in an environment of extreme cold and heat. If no measures are taken, the temperature will change greatly, which will seriously affect the normal operation of the on-board computer. At present, the spaceborne temperature control system is divided into passive temperature control and active temperature control. They are directly covered on the surface of the satellite (passive), or placed on the internal equipment components and servo systems of the satellite to adjust the flow of heat (active). This patent Involves active temperature contr...

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Problems solved by technology

[0007] Due to the long operating time in orbit, the spaceborne temperature control system is often subject to many interference factors such as space particle radiation, and the resulting failures will cause the software and hardware of the computer to fail.

Therefore, in order to achieve high reliability and high security, measures such as redundancy and fault tolerance need to be applied in the system. The correctness verification of the fault tolerance mechanism and design scheme has become an important link in the development of the onboard temperature control system. The failure rate is extremely low, and the failure time and process are difficult to predict. In addition, the cost of spacecraft system equipment is expensive, and the cost of equipment failure is high. How to simulate equipment failure in an effective way to verify and evaluate its redundant fault-tolerant mechanism, It has always been a difficult problem in the development process of the on-board temperature control system. According to the literature, there is no example at home and abroad of which fault injection method is used to verify the redundant fault-tolerant mechanism for the on-board temperature control system. Therefore, it is necessary to develop a low-cost , The simple and easy fault injection method for evaluating the reliability of the spaceborne computer system and its redundant fault-tolerant characteristics is of great significance and practical value

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