B. Aigner, F. Peter, E. Stumpf, B. Hauber, D. Metzler

A major objective of civil aviation is the progressive electrification of aircraft systems in order to enhance reliability while reducing operating costs at the same time. An aircraft's flight control system is considered as one of the identified key technologies to reach this goal. In this paper an approach for a novel flight control system architecture aiming towards a more electric aircraft is introduced and analyzed. The implemented concept consists of one hydraulic and two electrical systems (2E1H architecture) as power supply for the flight control system of a civil transport aircraft, which targets to represent a feasible medium term approach. The focus is put on the assessment of the impact on direct operating costs (DOC) compared to a traditional flight control architecture with exclusively hydraulically powered flight controls. In addition to the monetary analysis, a preliminary system safety assessment with emphasis on roll control is carried out to ensure the fulfillment of required safety standards. The Airbus A320 aircraft, which is currently equipped with three hydraulic power supply circuits (3H architecture) for flight controls, serves as the reference case for the analyses. The presented concept was developed in a cooperation project between the Institute of Aerospace Systems (ILR) of RWTH Aachen University and Liebherr-Aerospace Lindenberg GmbH.

Deutscher Luft- und Raumfahrtkongress 2016, Braunschweig

Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2016

Conference Paper

englisch

21,0 x 29,7 cm, 11 Seiten

urn:nbn:de:101:1-201611183234

aircraft systems, technology assessment

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18.11.2016