Reactive spoilers for aircraft and associated methods. In one embodiment, a wing of an aircraft includes a leading edge, a trailing edge, and an upper surface and a lower surface between the leading edge and the trailing edge. The wing further includes a reactive spoiler disposed on the upper surface between the leading edge and the trailing edge. The reactive spoiler comprises one or more turbines configured to raise in relation to the upper surface into an airflow passing over the upper surface, and to reduce lift of a wing section behind the turbines. The turbines are configured to convert kinetic energy from the airflow into electrical energy.

The subject matter described herein relates to aircraft designs and more particularly to aircraft designs using tandem wings and a distributed propulsion system. The embodiments described enable synergies between aerodynamics, propulsion, structure, and stability/control. In one embodiment, the tandem wings include a first wing set and a second wing set, each having a wing span with a set of thrustors placed along the wing spans.

The subject matter described herein relates to aircraft designs and more particularly to aircraft designs using tandem wings and a distributed propulsion system. The embodiments described enable synergies between aerodynamics, propulsion, structure, and stability/control. In one embodiment, the tandem wings include a first wing set and a second wing set, each having a wing span with a set of thrustors placed along the wing spans.

An aircraft system includes a component configured to operate with a minimum power demand. The aircraft system also includes an auxiliary power unit including an engine. The auxiliary power unit is configured to power the component and to operate the engine in a plurality of operating modes including a power mode and a standby mode. The auxiliary power unit generates a first power output at least equal to the minimum power demand during the power mode. The auxiliary power unit generates a second power output less than the minimum power demand during the standby mode.

An aircraft system includes a component configured to operate with a minimum power demand. The aircraft system also includes an auxiliary power unit including an engine. The auxiliary power unit is configured to power the component and to operate the engine in a plurality of operating modes including a power mode and a standby mode. The auxiliary power unit generates a first power output at least equal to the minimum power demand during the power mode. The auxiliary power unit generates a second power output less than the minimum power demand during the standby mode.

An actuator arrangement for a fixed leading edge member of an aircraft wing. The fixed leading edge member has an inner cavity defined by the outer skin and ribs. The actuator arrangement comprises at least one geared rotary actuator which moves relative to the other parts along a circular arc section during extending and retracting of the high-lift device between a fully retracted position and a fully extended position. In the fully retracted position, the actuator is predominantly accommodated within the inner cavity and in the extended position the actuator is predominantly positioned outside the inner cavity, preferably protruding through a D-nose cut-out.

An actuator arrangement for a fixed leading edge member of an aircraft wing. The fixed leading edge member has an inner cavity defined by the outer skin and ribs. The actuator arrangement comprises at least one geared rotary actuator which moves relative to the other parts along a circular arc section during extending and retracting of the high-lift device between a fully retracted position and a fully extended position. In the fully retracted position, the actuator is predominantly accommodated within the inner cavity and in the extended position the actuator is predominantly positioned outside the inner cavity, preferably protruding through a D-nose cut-out.

Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.

Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.

A system and method for actuating one or more high-lift flight control surfaces of an aircraft are disclosed. The system comprises actuators operatively coupled between a driveline and one or more high-lift flight control surfaces associated with a wing of the aircraft. The actuators are configured to cause actuation of the one or more first high-lift flight control surfaces in response to being driven by the first driveline. Each actuator is associated with a no-back device configured to prevent an air load on the one or more high-lift flight control surfaces from driving the one or more high-lift flight control surfaces. The system also comprises a backup brake applicable to the driveline. The backup brake can be applied upon the identification of a developing unsafe condition such as an asymmetry condition between the flight control surfaces of each wing of the aircraft or an uncommanded movement the flight control surfaces.