'American Institute of Aeronautics and Astronautics (AIAA)'
Doi
Abstract
The use of electrified on-board systems is increasingly more required to reduce aircraft
complexity, polluting emissions, and its life cycle cost. However, the more and all-electric
aircraft configurations are still uncommon in the civil aviation context and their certifiability
has yet to be proven in some aircraft segments. The aim of the present paper is to define a
multidisciplinary design problem which includes some disciplines pertaining to the
certification domain. In particular, the study is focused on the preliminary design of a 19
passengers small regional turboprop aircraft. Different on-board systems architectures with
increasing electrification levels are considered. These architectures imply the use of bleedless
technologies including electrified ice protection and environmental control systems. The use
of electric actuators for secondary surfaces and landing gear are also considered. The aircraft design, which includes aerodynamic, structural, systems and propulsion domains, is then
assessed by some certification disciplines. In particular, minimum performance, external noise
and safety assessments are included in the workflow giving some insights on the aircraft
certifiability. The results show a reduction of 3% of MTOM and 3% of fuel mass depending
on the systems architecture selected. From the certification side, the design has proven to be
certifiable and the margins with the certification constraint can be controlled to improve the
overall design