Architecture options estimate for the near-medium-haul aircraft control system by the reliability, mass and power consumption criteria

Current trends in increasing fuel efficiency and improving aircrafts flight characteristics place engineers before task of reducing the weight of onboard systems and decreasing power consumption with preserving required degree of reliability. In part of aircraft control system, the main stream is the actuators usage with power supply. In this article, three architecture options of the power part of the aircraft control system with different electrification levels are considered. The considered options of the power part of the control system are estimated by three criteria: reliability, mass, power consumption. The selected criteria allow for the preliminary conclusion about the prospects one or another aircraft control system architecture.