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.

Braking systems for aircraft are disclosed. An example braking system includes a fan cowl having a leading edge and a trailing edge. The braking system includes a hinge assembly coupled between the leading edge and a fan cage of an aircraft engine to enable the fan cowl to move between a stowed position and a deployed position. An actuator is coupled to the leading edge of the fan cowl, and the actuator is to move the fan cowl via the hinge from the stowed position to the deployed position in a direction away from the aircraft engine and toward a fore end of the aircraft to provide an air brake during a braking event.

Braking systems for aircraft are disclosed. An example braking system includes a fan cowl having a leading edge and a trailing edge. The braking system includes a hinge assembly coupled between the leading edge and a fan cage of an aircraft engine to enable the fan cowl to move between a stowed position and a deployed position. An actuator is coupled to the leading edge of the fan cowl, and the actuator is to move the fan cowl via the hinge from the stowed position to the deployed position in a direction away from the aircraft engine and toward a fore end of the aircraft to provide an air brake during a braking event.

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 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 bell-mouth scoop assembly includes an actuator comprising a plurality of hinge members configured to rotate in unison about a respective hinge axis of rotation from a first stowed position to a second deployed position and at least one linkage arm extending outwardly from at least one of the plurality of hinge members. The bell-mouth scoop assembly further comprises a bell-mouth panel comprising a panel longitudinal centerline and pivotably coupled to each linkage arm, in the first stowed position the bell-mouth panel (configured to conform to an outer surface of the with the panel longitudinal centerline aligned about a circumference of the flow discharge nozzle, in the second deployed position the bell-mouth panel configured to extend away from the outer surface of the flow discharge nozzle with the longitudinal centerline aligned parallelly with the nozzle centerline.

A bell-mouth scoop assembly includes an actuator comprising a plurality of hinge members configured to rotate in unison about a respective hinge axis of rotation from a first stowed position to a second deployed position and at least one linkage arm extending outwardly from at least one of the plurality of hinge members. The bell-mouth scoop assembly further comprises a bell-mouth panel comprising a panel longitudinal centerline and pivotably coupled to each linkage arm, in the first stowed position the bell-mouth panel (configured to conform to an outer surface of the with the panel longitudinal centerline aligned about a circumference of the flow discharge nozzle, in the second deployed position the bell-mouth panel configured to extend away from the outer surface of the flow discharge nozzle with the longitudinal centerline aligned parallelly with the nozzle centerline.

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.