The reduction of mission fuel mass due to new aircraft system technologies can be amplified by consideration of its coherences in aircraft design. The quantitative impact has shown to be highly sensitive to design parameters of the aircraft, such as design mass, maximum speed or service ceiling. For specific aircraft design parameters, resizing the wing area with respect to a new mission fuel mass showed a considerable effect in an example calculation. It is evident that the potential benefit of wing area changes is highly linked to the mass and drag sensitivities to the wing area. Due to the simple applied mass and drag approximation models in this paper, the results can diverge significantly for other cases. It seems to be essential to replace these general approximations with mass and drag models linked to the particular reference aircraft in each case. A general quantitative statement on the impact of fuel consumption caused by aircraft systems on aircraft design can not be given, as this process may be dominated by other considerations in each specific case. Nevertheless, especially for long-range missions, the presented coherences can become considerable under certain conditions, and the extension of the simulation model has shown a huge potential for further studies.
Consideration of fuel consumption caused by aircraft systems in aircraft design
Berücksichtigung des durch die Flugzeugsysteme verursachten Kraftstoffverbrauches im Luftfahrzeugentwurf
2006
10 Seiten, 9 Bilder, 4 Tabellen, 4 Quellen
Conference paper
English
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