Aircraft propulsion unit including at least one turbojet engine and a nacelle
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United States of America Patent
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Oct 3, 2017
Issued Date -
N/A
app pub date -
Jan 28, 2014
filing date -
Jul 29, 2011
priority date (Note) -
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Abstract
The present disclosure relates to a nacelle for a dual-flow turbojet engine includes a cold airstream having a non-constant cross-section over the periphery of the nacelle, such that at least one flap is radially offset with respect to the central axis of the turbojet engine, relative to the adjacent flaps. The system for driving the radially offset flaps is suitable for ensuring that the kinematics of the flaps are offset relative to the kinematics of the flaps mounted along the remainder of the periphery of the airstream.
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