Aircraft nacelles having adjustable chines
AssigneeThe Boeing Company
InventorsPaul M. Vijgen, Adam M. Clark, Connie Phung, Miles Anthony Robinson
Life of this patent
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Abstract
Aircraft nacelles having adjustable chines are described. An example apparatus includes a multi-segment chine coupled to a nacelle. The multi-segment chine includes a first segment and a second segment. The first segment is oriented along a fore-aft direction. The first segment is rotatable relative to the nacelle about an axis of rotation. The axis of rotation is substantially perpendicular to a plane of the first segment defined by an outer mold line of the first segment. The second segment is fixedly coupled to the nacelle. The second segment is oriented along the fore-aft direction. The second segment is substantially coplanar with the first segment.
Claims20
An apparatus, comprising:
- a nacelle of an aircraft engine;
- and
- a multi-segment chine coupled to the nacelle, the multi-segment chine including a first segment and a second segment respectively located on the nacelle, the first segment oriented along a fore-aft direction, the first segment rotatable between a deployed position and a stowed position relative to the nacelle, the stowed position angularly displaced from the deployed position, the rotation of the first segment being about an axis of rotation substantially perpendicular to a plane of the first segment defined by an outer mold line of the first segment, the second segment fixedly coupled to the nacelle such that the second segment is stationary relative to the nacelle, the second segment extending outwardly from an outer surface of the nacelle, the second segment oriented along the fore-aft direction, the second segment substantially coplanar with the first segment, wherein a portion of the first segment extends outwardly from the outer surface of the nacelle when the first segment is in the deployed position, and the portion of the first segment is retracted inwardly from the outer surface of the nacelle when the first segment is in the stowed position.
A method, comprising:
- rotating a first segment of a multi-segment chine coupled to a nacelle of an aircraft engine relative to a second segment of the multi-segment chine, the first segment oriented along a fore-aft direction, the first segment rotatable between a deployed position and a stowed position relative to the nacelle, the stowed position angularly displaced from the deployed position, the rotation of the first segment being about an axis of rotation substantially perpendicular to a plane of the first segment defined by an outer mold line of the first segment, the second segment fixedly coupled to the nacelle such that the second segment is stationary relative to the nacelle, the second segment extending outwardly from an outer surface of the nacelle, the second segment oriented along the fore-aft direction, the second segment substantially coplanar with the first segment, the first segment and the second segment respectively located on the nacelle, wherein a portion of the first segment extends outwardly from the outer surface of the nacelle when the first segment is in the deployed position, and the portion of the first segment is retracted inwardly from the outer surface of the nacelle when the first segment is in the stowed position.
An aircraft, comprising:
- a fuselage;
- a wing coupled to and extending outwardly from the fuselage;
- a nacelle of an engine, the nacelle coupled to the wing via a pylon extending downwardly from the wing, the nacelle located below the wing and spaced apart from the fuselage;
- and
- a multi-segment chine coupled to the nacelle, the multi-segment chine including a leading segment and a trailing segment respectively located on the nacelle, the leading segment oriented along a fore-aft direction, the leading segment rotatable relative to the nacelle about an axis of rotation, the axis of rotation substantially perpendicular to a plane of the leading segment defined by an outer mold line of the leading segment, the trailing segment fixedly coupled to the nacelle such that the trailing segment is stationary relative to the nacelle, the trailing segment extending outwardly from an outer surface of the nacelle, the trailing segment oriented along the fore-aft direction, the trailing segment substantially coplanar with the leading segment.
Dependencies are inferred from the claim text.