Synthesis of structure of the onboard passive redundant subsystem with due consideration of the established tolerances

Abstract

The goal of this article is to select optimal parameters of various structures of the passive redundant subsystems of flying vehicles (hereinafter to be referred to as the “the aircraft”) with due consideration of the established tolerances in respect of decrease in output parameters of these subsystems in the cases of failure of the aircraft components (in accordance with the required failure-free operation). It was demonstrated that synthesis of such structure is based on the solving the two-objective optimisation problem, which can be reduced to the one-criterion problem with the help of various methods. Authors of this article have selected the linear convolution method. Due to the absence of information on quantitative values of the prescribed tolerances and on the required failure-free operation of actual subsystems, authors have performed calculations of relevant dependences within the wide range of the realisable tolerances of the first and second levels. Authors have investigated influence of values of the required failure-free operation and values of tolerances upon the optimal structure of the passive redundancy subsystems of the aircraft.