The U.S. SST prototype commercial airliner under development from 1967 to 1971 employed redundant flight-critical control systems as an essential part of the airplane's airworthiness. The flight control system electronics were analog for the flight-critical stability augmentation functions and digital for the automatic flight control functions. The digital system, through an automated preflight test function, also served to establish the integrity of the flight-critical elements. The SST program was terminated before these systems became operational. This study deals with the mechanization of redundant electronic systems. Specifically, the study evaluates analog and digital electronic designs for implementing a triplex fail-operational flight-critical control system. The primary subjects studied were analog and digital systems' multiple failure fail-operational capabilities and preflight integrity check requirements. This document describes the systems evaluated during the study. (Author)
Redundant Flight-Critical Control System Evaluation. Analog and Digital Systems Descriptions
1974
137 pages
Report
Keine Angabe
Englisch
Aircraft , Avionics , Flight control systems , Supersonic transports , Electronic equipment , Redundant components , Display systems , Analog computers , Digital computers , Navigational aids , Navigation computers , Aviation safety , Automatic , Flight paths , Aerodynamic stability , Handling , Fail safe , Memory devices , Ground support equipment , Algorithms , SST technology follow on program
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