Under-flap stiffener for aircraft
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United States of America Patent
Stats
-
Aug 18, 2015
Grant Date -
May 31, 2012
app pub date -
Mar 15, 2010
filing date -
Mar 19, 2009
priority date (Note) -
In Force
status (Latency Note)
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Abstract
An assembly of longitudinal structural stiffeners for an aircraft including, in a front portion of the fuselage, a windscreen that is slightly recessed relative to the airplane nose, and a fuselage portion extending in alignment with the airplane nose up to the base of the windscreen. The stiffeners include a bending-resistance main plane and are arranged under the flap and connected to the fuselage along a force transfer line. For one or more of the stiffeners, the bending resistance main plane substantially coincides, at at least a certain number of points of the fuselage force transfer line, with the plane predetermined by the local normal to the fuselage surface and the longitudinal axis of the airplane. A method is also provided for calculating the shape of the stiffeners.
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