All-electric Flight Control System and Landing Gear System Models for Power Assessment Studies
Year: 2014
Type: conference-paper
Abstract: The complete electrification of aircraft power systems entails \nthe implementation of smart logics for sharing the available \nenergy among the loads, and the design of these logics \nrequires the characterisation of the power absorption of each \non-board system as a function of mission phase and aircraft \noperating point, also taking into account the level of criticality of \nthe function implemented by the system itself. \nThe paper describes the models of the electro-mechanical \nsystems used for the landing gear extension/retraction and the \nflight control actuation of a regional aircraft, with the basic \nobjective of evaluating the power requests that have to be \nfulfilled both continuously and completely for these safetycritical \nequipments. \nThe Flight Control System (FCS) model is composed of both \nprimary and secondary flight controls. The Landing Gear \nSystem (LGS) model refers to the landing gear of a typical \nturboprop regional aircraft, with a single nose and two main \ngears. Both the landing gears (LGs) and the control surfaces \n(CSs) are driven by Electro-Mechanical Actuators (EMAs). All \nthe EMA models refer to actuators with a 3-phase synchronous \nbrushless motor and mechanical transmission. \nSimulation tests have been performed to assess the maximum \npower flows characterizing the systems, with reference to \nsevere operative conditions.
Source: HAL
Institution: University of Pisa
Language: English
Subfield: Aerospace Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: green
OpenAlex ID: W2795577341