Aircraft wings, aircraft, and related methods. Aircraft wings include a spoiler constructed substantially of a monolithic structural body with an upper side that defines a portion of an airfoil surface of an aircraft wing. The monolithic structural body further includes a lower side, opposite the upper side, that includes a plurality of stiffening ribs that define a plurality of open voids. Methods of constructing a spoiler for an aircraft wing include forming a monolithic structural body of the spoiler.

Aircraft wings, aircraft, and related methods. Aircraft wings include a spoiler constructed substantially of a monolithic structural body with an upper side that defines a portion of an airfoil surface of an aircraft wing. The monolithic structural body further includes a lower side, opposite the upper side, that includes a plurality of stiffening ribs that define a plurality of open voids. Methods of constructing a spoiler for an aircraft wing include forming a monolithic structural body of the spoiler.

A wing leading edge architecture designed to enable laminar flow on passenger jets or other aircraft. The embodiments disclosed herein comprise a metallic fixed leading edge skin panel that is bonded to internal support structure without fasteners except for limited fastening along side edge portions adjacent to side edge portions of adjacent leading edge skin panels and along an aft edge portion overlapping a wing skin. In addition, the embodiments disclosed herein integrate a low-drag bleed-air anti-icing (i.e., vent) system and a Krueger flap assembly (e.g., a two-position, high-height, variable-camber Krueger flap assembly).

A wing leading edge architecture designed to enable laminar flow on passenger jets or other aircraft. The embodiments disclosed herein comprise a metallic fixed leading edge skin panel that is bonded to internal support structure without fasteners except for limited fastening along side edge portions adjacent to side edge portions of adjacent leading edge skin panels and along an aft edge portion overlapping a wing skin. In addition, the embodiments disclosed herein integrate a low-drag bleed-air anti-icing (i.e., vent) system and a Krueger flap assembly (e.g., a two-position, high-height, variable-camber Krueger flap assembly).

A variable camber Krueger flap deployment linkage mechanism is presented. A first linkage assembly couples a flap assembly and an airfoil, and comprising a first drive arm, a first drive link, and a support arm. A second linkage assembly couples the flap assembly and the first drive arm, and comprises a drive transfer arm, a middle connection segment, and a bullnose link.

A variable camber Krueger flap deployment linkage mechanism is presented. A first linkage assembly couples a flap assembly and an airfoil, and comprising a first drive arm, a first drive link, and a support arm. A second linkage assembly couples the flap assembly and the first drive arm, and comprises a drive transfer arm, a middle connection segment, and a bullnose link.

Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use.

A gust alleviating aircraft wing includes a gust alleviating wing portion on the wing. The wing portion can have a leading edge, a trailing edge, and a downwardly sloping upper surface therebetween. At least one air passageway can extend through the wing portion from the leading edge to a rear or downstream location on the downwardly sloping upper surface of the wing portion. At least one spoiler can be on the upper surface of the wing portion at the rear location for selectively movably covering and uncovering an exit location of the at least one passageway. Opening the at least one passageway is capable of diverting air flow through the at least one passageway and the wing portion for counteracting upward lift caused by a gust of wind.

A gust alleviating aircraft wing includes a gust alleviating wing portion on the wing. The wing portion can have a leading edge, a trailing edge, and a downwardly sloping upper surface therebetween. At least one air passageway can extend through the wing portion from the leading edge to a rear or downstream location on the downwardly sloping upper surface of the wing portion. At least one spoiler can be on the upper surface of the wing portion at the rear location for selectively movably covering and uncovering an exit location of the at least one passageway. Opening the at least one passageway is capable of diverting air flow through the at least one passageway and the wing portion for counteracting upward lift caused by a gust of wind.

A fixed-wing aircraft at least includes at least one vortex generator movable through an outer surface of the aircraft between a retracted state and a fully extended state by at least one electric motor, the at least one electric motor being exclusively adapted to actuate this at least one vortex generator, and including an electronic control unit adapted to control operation of the at least one electric motor for actuation of the at least one vortex generator.