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Architecture of Distributed Control System for Gearbox-Free More Electric Turbofan Engine
Version 1
: Received: 1 September 2021 / Approved: 2 September 2021 / Online: 2 September 2021 (13:48:38 CEST)
A peer-reviewed article of this Preprint also exists.
Popov, V.; Yepifanov, S.; Kononykhyn, Y.; Tsaglov, A. Architecture of Distributed Control System for Gearbox-Free More Electric Turbofan Engine. Aerospace 2021, 8, 316. Popov, V.; Yepifanov, S.; Kononykhyn, Y.; Tsaglov, A. Architecture of Distributed Control System for Gearbox-Free More Electric Turbofan Engine. Aerospace 2021, 8, 316.
Abstract
The article presents development of the more electric turbofan engine in distributed architecture with a design thrust in the range from 3 to 7.5 and from 7.5 to 30 kN for small and medium-sized unmanned aerial vehicles. The engine subsystems are considered as separate smart modules with a built-in control system, exchanging data via a digital channel with the central engine control and diagnostics unit. The key smart engine units are combined in the following subsystems: starter and turbine generators, oil pumps, actuator of guide vanes, fuel pumps, fuel metering unit, control and diagnostic unit. All pumps and guide vane actuator are electrically driven. Control and monitoring signals are transmitted via a digital bus. Functional and reliability analysis, technical configuration design of each subsystem are presented. Based on analysis of the architecture of distributed control system for gearbox-free more electric engine, different configurations of described subsystems are proposed.
Keywords
unmanned aerial vehicle; more electric aircraft; turbofan engine; distributed control system
Subject
Engineering, Control and Systems Engineering
Copyright: This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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