The Method of Fault Tolerance Evaluation of Reconfigurable Navigation System

Abstract

The method of research and evaluation of fault tolerance of the navigation system of a passenger aircraft is described. The system should have a very high reliability, provided under the influence of such external factors as factors of electromagnetic, thermal and mechanical nature. The method uses structural reconfiguration aimed at increasing reliability by increasing fault tolerance, when the required function continues to be performed despite the appearance of failures in some components of the system. To confirm the reliability indicators, computer modeling of physical processes occurring in the avionics design is used.