Functional Reliability Support of Electronics Systems for Insuffisient Information about Operational Status this Units

Abstract

At the paper considered mathematical model of process appearance and accumulation of hidden faulty of electronic units. In reference to hypothetical electronic system of aircraft consists of five units receive the systems of equation. According to the systems of equation composition and construct two the graphs. One of them construct for avionics systems with constant structure in flight of aircraft. Another graph construct for avionics systems with changeable structure in flight of aircraft. Nodal points at left-hand upper angle of graphs (capital letter A) correspond to the facts of full in good working order of electronic system. Nodal points which mark capital letter D at right-hand lover angle of graphs correspond to the facts of full loss serviceability of electronic system. All the rest nodal points of graphs to represent intermediate condition (state). This intermediate state be discovered man-operator or automatic equipment of control (capital letter B 1 , B 2 , B 3 ) and latent disturbance (capital letter C 1 , C 2 ), either combination that or the other (capital letter at combination B 1 C 1 ; B 2 C 1 ). Arcs of graphs to represent intensity of transition system from a state to another, transition between states. Analysis of graphs demonstrate, what changeable structure avionics systems make it possible raise functional reliability of electronics systems. But considered mathematical model suitable only for production-type of avionics systems, which the remote past government test and experimental study of operation.