Design Optimization of Airframe in Aircraft Fuselage Structure under Static Loading Conditions

Authors: Sowmya R, Sreenivasa R, Kallesh S S

DOI: https://doi.org/10.17605/OSF.IO/4HYZG

Short DOI: https://doi.org/ggrs9b

Country: India

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Abstract: The fuselage is one of the main component in any aircraft and its function is to hold all parts together and carries passengers. This fuselage part experience a different loads like static, fatigue, dynamic, buckling during landing, flying and take-off conditions. Now a day’s aircraft undergo different type of failure modes, due to improper design, pilot error, weather conditions etc. In the present work, fuselage component with airframes can be optimized in design in order to check which design of airframes in fuselage structure can withstand static loading conditions with minimum deflection and minimum induced stress. The result shows that fuselage component with airframes containing three vertical truss members under roof can able to withstand static loading conditions with minimum deflection, fuselage component with airframes containing two inclined and one vertical truss member located at centre under roof can able to withstand static loading conditions with minimum induced stress and fuselage component with airframes don’t containing any truss members under roof cannot able to withstand static loading conditions.

Keywords: Fuselage, airframe, truss members, static loads.

Paper Id: 218

Published On: 2016-10-24

Published In: Volume 4, Issue 5, September-October 2016

Cite This: Design Optimization of Airframe in Aircraft Fuselage Structure under Static Loading Conditions - Sowmya R, Sreenivasa R, Kallesh S S - IJIRMPS Volume 4, Issue 5, September-October 2016. DOI 10.17605/OSF.IO/4HYZG

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