In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of an aircraft. The first deflector may form part of a top surface of the aircraft when in a first closed position. The apparatus may further include a second deflector configured to couple to the shaft and form part of a bottom surface of the aircraft when in a second closed position. The first deflector and the second deflector may be configured to be positioned at a junction of a body of the aircraft and a wing of the aircraft. 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 an aircraft. The first deflector may form part of a top surface of the aircraft when in a first closed position. The apparatus may further include a second deflector configured to couple to the shaft and form part of a bottom surface of the aircraft when in a second closed position. The first deflector and the second deflector may be configured to be positioned at a junction of a body of the aircraft and a wing of the aircraft. 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.

This disclosure provides construction variants of a cruise miniflap of an aircraft wing that is added to trailing edge flap of an aircraft wing and can be used for improving the aerodynamic properties of an aircraft. In the rear edge of the cruise miniflap there is a cavity with a height of up to 1% of the wing chord.

This disclosure provides construction variants of a cruise miniflap of an aircraft wing that is added to trailing edge flap of an aircraft wing and can be used for improving the aerodynamic properties of an aircraft. In the rear edge of the cruise miniflap there is a cavity with a height of up to 1% of the wing chord.

A vortex generator control system for a controlling an aircraft vortex generator arrangement comprising a controller configured to receive one or more deploy or retract command signals from a flight control unit and further configured to send one or more command signals to a fluid control valve, a fluid pressure sensor configured to sense one or more pressure values from an actuator of the vortex generator arrangement and to signal the pressure value(s) to the controller, wherein the fluid control valve is configured to control fluid transfer between the actuator and a reservoir in response to a command signal from the controller.

A vortex generator control system for a controlling an aircraft vortex generator arrangement comprising a controller configured to receive one or more deploy or retract command signals from a flight control unit and further configured to send one or more command signals to a fluid control valve, a fluid pressure sensor configured to sense one or more pressure values from an actuator of the vortex generator arrangement and to signal the pressure value(s) to the controller, wherein the fluid control valve is configured to control fluid transfer between the actuator and a reservoir in response to a command signal from the controller.

A vortex generator arrangement comprising a section that defines an opening to a corresponding cavity, an aircraft airflow modification device disposed within the cavity, and at least one fluidic muscle actuator arrangement coupled to the airflow modification device.

Wing structure that includes slat-cove fillers configured to reduce leading-edge slat noise on aircraft, such as transport aircraft.

Wing structure that includes slat-cove fillers configured to reduce leading-edge slat noise on aircraft, such as transport aircraft.

Underwing-mounted trailing edge flaps for wings of aircraft are disclosed. A flap pivotally coupled to the wing is movable between a stowed position located along a lower surface of the wing and a deployed position located rearward of a trailing edge of the wing. The flap includes a first edge, a second edge located opposite the first edge, a first surface extending between the first edge and the second edge, and a second surface located opposite the first surface and extending between the first edge and the second edge. The first edge is located rearward of the second edge when the flap is in the stowed position, and forward of the second edge when the flap is in the deployed position. A bullnose pivotally coupled to the flap at a location along the first edge pivots relative to the flap as the flap moves between the stowed and deployed positions.