A wing of an aircraft that includes a wing leading edge, a wing trailing edge, and a wing surface defined by a wing upper surface and a wing lower surface is described herein. The wing extends from the wing root to the wingtip, and the wingtip has a wingtip chord. A winglet extends from the wingtip and has a winglet leading edge, a winglet trailing edge, a winglet inboard surface, a winglet outboard surface, a winglet root having a winglet root chord, and a winglet tip. A flow fence is disposed on the wing surface inboard from the winglet and overlapping with the winglet. The flow fence is adapted to delay and/or prevent airflow separation on the winglet inboard surface at high angle of sideslip, increasing lateral stability and linearizing aircraft behavior at high angle of sideslip.

A wing of an aircraft that includes a wing leading edge, a wing trailing edge, and a wing surface defined by a wing upper surface and a wing lower surface is described herein. The wing extends from the wing root to the wingtip, and the wingtip has a wingtip chord. A winglet extends from the wingtip and has a winglet leading edge, a winglet trailing edge, a winglet inboard surface, a winglet outboard surface, a winglet root having a winglet root chord, and a winglet tip. A flow fence is disposed on the wing surface inboard from the winglet and overlapping with the winglet. The flow fence is adapted to delay and/or prevent airflow separation on the winglet inboard surface at high angle of sideslip, increasing lateral stability and linearizing aircraft behavior at high angle of sideslip.

An aircraft assembly is disclosed having a wing tip device connected to a wing tip of a wing by a first connector, a second connector, and a third connector. The wing tip device includes a front device spar and a rear device spar. The first connector is associated with the rear device spar. The second connector is spaced apart in a chordwise direction forward of the first connector, and the third connector is spaced apart in a chordwise direction rearward of the first connector. The third connector includes a spigot mounting formation.

An aircraft assembly is disclosed having a wing tip device connected to a wing tip of a wing by a first connector, a second connector, and a third connector. The wing tip device includes a front device spar and a rear device spar. The first connector is associated with the rear device spar. The second connector is spaced apart in a chordwise direction forward of the first connector, and the third connector is spaced apart in a chordwise direction rearward of the first connector. The third connector includes a spigot mounting formation.

A technique of operating an unmanned aerial vehicle (UAV) adapted for a package delivery mission includes: powering distributed propulsion units during takeoff and landing segments of the package delivery mission and idling at least a portion of the distributed propulsion units while powering a pair of outboard propulsion units during a cruise segment of the package delivery mission. The distributed propulsion units are mounted below fixed wings of the UAV and have first propellers mounted fore of the fixed wings. The outboard propulsion units are each mounted to a corresponding one of the fixed wings outboard of the distributed propulsion units. The outboard propulsion units include outboard propellers having a larger diameter than the first propellers.

A technique of operating an unmanned aerial vehicle (UAV) adapted for a package delivery mission includes: powering distributed propulsion units during takeoff and landing segments of the package delivery mission and idling at least a portion of the distributed propulsion units while powering a pair of outboard propulsion units during a cruise segment of the package delivery mission. The distributed propulsion units are mounted below fixed wings of the UAV and have first propellers mounted fore of the fixed wings. The outboard propulsion units are each mounted to a corresponding one of the fixed wings outboard of the distributed propulsion units. The outboard propulsion units include outboard propellers having a larger diameter than the first propellers.

In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of a wing of an aircraft and form part of a top surface of the wing when in a first closed position, and a second deflector configured to couple to the shaft and form part of a bottom surface of the wing when in a second closed position. The first deflector and the second deflector may be configured to be positioned proximate to the tip of the wing. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of a wing of an aircraft and form part of a top surface of the wing when in a first closed position, and a second deflector configured to couple to the shaft and form part of a bottom surface of the wing when in a second closed position. The first deflector and the second deflector may be configured to be positioned proximate to the tip of the wing. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

A vertical takeoff and landing (VTOL) aircraft, configured to transport passengers and/or cargo, uses propellers during vertical flight and wings during forward flight to generate lift. The VTOL aircraft includes a front wing and a rear wing connected by inboard booms. The rear wing may include a wingtip boom attached to each free end of the wing. A propeller may be attached to each inboard boom and each wingtip boom. The propellers attached to the inboard booms may be stacked propellers including at least two co-rotating propellers. The aircraft can also include a cruise propeller attached to the tail region of the fuselage, where the cruise propeller is configured to rotate in a plane approximately perpendicular to the fuselage to generate thrust during forward flight.

A vertical takeoff and landing (VTOL) aircraft, configured to transport passengers and/or cargo, uses propellers during vertical flight and wings during forward flight to generate lift. The VTOL aircraft includes a front wing and a rear wing connected by inboard booms. The rear wing may include a wingtip boom attached to each free end of the wing. A propeller may be attached to each inboard boom and each wingtip boom. The propellers attached to the inboard booms may be stacked propellers including at least two co-rotating propellers. The aircraft can also include a cruise propeller attached to the tail region of the fuselage, where the cruise propeller is configured to rotate in a plane approximately perpendicular to the fuselage to generate thrust during forward flight.