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.

Aircraft nacelles having adjustable chines are described. An example apparatus includes a chine coupled to a nacelle. The chine is oriented along a fore-aft direction. The chine is translatable relative to the nacelle along the fore-aft direction.

Aircraft nacelles having adjustable chines are described. An example apparatus includes a chine coupled to a nacelle. The chine is oriented along a fore-aft direction. The chine is translatable relative to the nacelle along the fore-aft direction.

A variable area fan nozzle actuation (VAFN) system is disclosed. The VAFN system may include an electrohydrostatic actuator (EHA) arranged to translate a VAFN panel relative to a translating sleeve. An electrical coupling may extend between a translating sleeve associated with the VAFN system and the fixed structure. The electrical coupling may be movable so that as the translating sleeve and fixed structure move relative to each other, power may be provided to the EHA by a wiring harness extending across the space between the translating sleeve and the fixed structure and connecting the EHA to an EHA power source.

A variable area fan nozzle actuation (VAFN) system is disclosed. The VAFN system may include an electrohydrostatic actuator (EHA) arranged to translate a VAFN panel relative to a translating sleeve. An electrical coupling may extend between a translating sleeve associated with the VAFN system and the fixed structure. The electrical coupling may be movable so that as the translating sleeve and fixed structure move relative to each other, power may be provided to the EHA by a wiring harness extending across the space between the translating sleeve and the fixed structure and connecting the EHA to an EHA power source.

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 device is provided for attenuating the vortex wake created in the zone behind an aircraft, the aircraft having at least one wing and an afterbody having a strong upward asymmetrical reduction of section of the rear fuselage. The device is positioned downstream of the wing of the aircraft symmetrically relative to the longitudinal plane of the aircraft. The device includes vortex-generating aerodynamic appendages capable of being deployed between a folded-down position in which the aerodynamic appendages are folded down substantially in the direction of the fuselage, capable of switching from a folded-down position in which they are folded down substantially in the direction of the fuselage, and a deployed position calculated to generate vortex structures having an intensity and a trajectory which modify the local pressure field in order to interact with the vortex wake to attenuate it and separate the upsweep vortices from the longitudinal plane of the aircraft.

A device is provided for attenuating the vortex wake created in the zone behind an aircraft, the aircraft having at least one wing and an afterbody having a strong upward asymmetrical reduction of section of the rear fuselage. The device is positioned downstream of the wing of the aircraft symmetrically relative to the longitudinal plane of the aircraft. The device includes vortex-generating aerodynamic appendages capable of being deployed between a folded-down position in which the aerodynamic appendages are folded down substantially in the direction of the fuselage, capable of switching from a folded-down position in which they are folded down substantially in the direction of the fuselage, and a deployed position calculated to generate vortex structures having an intensity and a trajectory which modify the local pressure field in order to interact with the vortex wake to attenuate it and separate the upsweep vortices from the longitudinal plane of the aircraft.

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.