U. Kling, F. Peter, M. Hornung, R. Springmann, F. Thielecke

In the scope of the AdVanced Aircraft CONfiguration (AVACON) research project the potential of unconventional landing gear configurations is one of the research questions. The AVACON research baseline aircraft has been defined by the German Aerospace Center (DLR) and implements a selection of technologies for an entry into service in the year 2028. From the research baseline, innovative configurations will be derived and analyzed. Especially by further increasing the bypass ratio of the engines to reduce emissions and fuel burn. Therefore, a central aspect of AVACON is the integration of high bypass ratio engines with large nacelle diameters. It is planned to analyze configurations with over wing positioned nacelles. This offers the potential to integrate unconventional landing gear designs, for example a body landing gear. AVACON contains a dedicated work package in which Bauhaus Luftfahrt e.V. and the Hamburg University of Technology are cooperating with industry support to assess possible landing gear configurations. Several landing gear requirements are taken into account in the AVACON landing gear work package. Configurational requirements comprise the take-off rotation, tipping, turnover angle, ground mobility, nacelle clearance and wing tip clearance. Furthermore, the landing and taxiing shocks have to be absorbed by the landing gear. The structure of the landing gear has to be dimensioned accordingly. The Certification Specification (CS25) specifies load cases, which the landing gear structure has to withstand. These load cases are used as to estimate the forces, which are applied on the landing gear. A preliminary sizing loop using structural simulation is established to size the main structural component of the landing gear according to these load cases. After the design of the landing gear structure, a preliminary kinematics analysis is carried out with special regards on the actuation of the landing gear. This paper presents the application of this process on the research baseline. The preliminary sizing of the main structural components and conceptualizing of the kinematics is demonstrated. The system off-takes necessary for the actuation, which are an input for the sizing of the system architecture, are estimated using the dimensions and weights of the landing gear design.

Deutscher Luft- und Raumfahrtkongress 2018, Friedrichshafen

Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2022

Conference Paper

englisch

21,0 x 29,7 cm, 8 Seiten

urn:nbn:de:101:1-2022092113303870890928

10.25967/480198

AVACON, Landing gear

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Kling, U.; Peter, F.; et al. (2022): Landing Gear Design and Assessment Methodology in the AVACON Project. Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V.. (Text). https://doi.org/10.25967/480198. urn:nbn:de:101:1-2022092113303870890928.

21.09.2022