A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

A chine spoiler system enhances aircraft wing stall recovery characteristics while optimizing a maximum lift coefficient (CLMAX) of an aft-swept wing on an aircraft having an engine nacelle mounted below the wing. The system includes a chine located on a surface of the nacelle; the chine is configured to generate a vortex at high angles of attack. The vortex passes over an upper surface of the wing, favorably influencing inboard wing aerodynamics to delay airflow separation from the wing, in advance of a stall. The vortex increases CLMAX, but also creates a nose-up pitching moment on an aft-swept wing, which degrades stall recovery. A chine spoiler system module is configured to render the chine ineffective at predetermined wing flap configurations and angles of attack (typically post CLMAX) to balance the objectives of achieving high pre-stall CLMAX, while providing a nose-down pitching moment increment for improved stall recovery.

A chine spoiler system enhances aircraft wing stall recovery characteristics while optimizing a maximum lift coefficient (CLMAX) of an aft-swept wing on an aircraft having an engine nacelle mounted below the wing. The system includes a chine located on a surface of the nacelle; the chine is configured to generate a vortex at high angles of attack. The vortex passes over an upper surface of the wing, favorably influencing inboard wing aerodynamics to delay airflow separation from the wing, in advance of a stall. The vortex increases CLMAX, but also creates a nose-up pitching moment on an aft-swept wing, which degrades stall recovery. A chine spoiler system module is configured to render the chine ineffective at predetermined wing flap configurations and angles of attack (typically post CLMAX) to balance the objectives of achieving high pre-stall CLMAX, while providing a nose-down pitching moment increment for improved stall recovery.

Aircraft nacelles having adjustable chines are described. An example apparatus includes a multi-segment chine having a first segment and a second segment. The first segment is fixedly coupled to a nacelle. The second segment is rotatable relative to the first segment about an axis of rotation. The axis of rotation is substantially perpendicular to a local area of an outer surface of the nacelle.

Aircraft nacelles having adjustable chines are described. An example apparatus includes a multi-segment chine having a first segment and a second segment. The first segment is fixedly coupled to a nacelle. The second segment is rotatable relative to the first segment about an axis of rotation. The axis of rotation is substantially perpendicular to a local area of an outer surface of the nacelle.

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.

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.

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 translatable relative to the nacelle along the fore-aft direction. The first segment includes one or more first airflow openings. The second segment is fixedly coupled to the nacelle. The second segment is oriented along the fore-aft direction. The second segment includes one or more second airflow openings. The second segment is substantially coplanar with the first segment. Translation of the first segment adjusts the transverse alignment of the first airflow openings with the second airflow openings to vary an allowable airflow through the multi-segment chine.

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 translatable relative to the nacelle along the fore-aft direction. The first segment includes one or more first airflow openings. The second segment is fixedly coupled to the nacelle. The second segment is oriented along the fore-aft direction. The second segment includes one or more second airflow openings. The second segment is substantially coplanar with the first segment. Translation of the first segment adjusts the transverse alignment of the first airflow openings with the second airflow openings to vary an allowable airflow through the multi-segment chine.

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 oriented along a fore-aft direction. The first segment is translatable relative to the nacelle along the fore-aft direction. The multi-segment chine further includes a second segment oriented along the fore-aft direction. The second segment is substantially coplanar with the first segment.