Abstract
The possibility of imitation modeling of automatic recovery of a computer fault-tolerance system, whose elements have additional hardware and software redundancy in case successive failures, is considered on the base of a directed probabilistic graph whose tops correspond to possible states of the system, and the arcs between them determine the probabilities of transitions from one state to another, the arc length determines the random time of automatic recover, statistical characteristics of the recovery process are determined on the base of passage of the routes along the probabilistic graph from initial top to the final one.
Highlights
Fault-tolerance structures of avionics must provide a high level of automation at all stages of flight: at the route, automatic approach and landing on a III category ICAO, automatic control by a run after landing [1]
The quality of the such system can be estimated by the probability with which it guarantees automatic recovery in case of failure of individual elements, average recovery time of the functional modules and the system as a whole, by the number of failures of elements, which still maintain the functionality of the system unit, which is equivalent to the number of operational states of the system in case successive failures
In accordance with the strategy for the development and implementation of perspective fault-tolerance system of avionics it should be provided possible to delay the maintenance procedure until the aircraft returns to the main base, which in turn will allow for the implementation of the planned maintenance intervals
Summary
Fault-tolerance structures of avionics must provide a high level of automation at all stages of flight: at the route, automatic approach and landing on a III category ICAO, automatic control by a run after landing [1]. The quality of the such system can be estimated by the probability with which it guarantees automatic recovery in case of failure of individual elements, average recovery time of the functional modules and the system as a whole, by the number of failures of elements, which still maintain the functionality of the system unit (failure of the i-th multiplicity), which is equivalent to the number of operational states of the system in case successive failures. The number of such failures determines the survivability of the fault-tolerance system. In accordance with the requirements for faulttolerance structures of avionics it is necessary that all functions continue to be performed for 250 hours after the first failure with a confidence level of 0.99
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