Systems and methods are described herein to implement transverse momentum injection at low frequencies to directly modify large-scale eddies in a turbulent boundary layer on a surface of an object. A set of transverse momentum injection actuators may be positioned on the surface of the object to affect large-scale eddies in the turbulent boundary layer. The system may include a controller to selectively actuate the transverse momentum injection actuators with an actuation pattern to affect the large-scale eddies to modify the drag, fluid mixing, heat transfer, and/or other interactions of the fluid flow with the surface. In various embodiments, the transverse momentum injection actuators may be operated at frequencies less than 10,000 Hertz.

Aircraft pitch control systems and methods are disclosed. An aircraft pitch control system (28) comprises a movable horizontal stabilizer (24) and an elevator (26) movably coupled to the horizontal stabilizer. The elevator is electronically geared to the horizontal stabilizer.

Systems and methods for controlling a fixed-wing aircraft during flight are disclosed. The aircraft comprises first and second flight control surfaces of different types. The method comprises determining that a pilot command of the first flight control surface will excite a structural flexible mode of the aircraft and then executing the pilot command of the first flight control surface in conjunction with a command of the second flight control surface to mitigate the effect of the excitation of the structural flexible mode of the aircraft.

A control surface actuation mechanism for moving a control surface relative to a fixed aerofoil portion of an aircraft is disclosed including an articulating support, a sliding member on the articulating support and coupled to the control surface, the sliding member arranged to slide relative to the articulating support, a track with a path for attachment on the fixed aerofoil portion, and a rigid connecting element connected to the first track and to the sliding member. The first end of the first rigid connecting element is configured to move passively along the path, as the sliding member is driven to slide relative to the articulating support by an actuator.

A control surface actuation mechanism for moving a control surface relative to a fixed aerofoil portion of an aircraft is disclosed including an articulating support, a sliding member on the articulating support and coupled to the control surface, the sliding member arranged to slide relative to the articulating support, a track with a path for attachment on the fixed aerofoil portion, and a rigid connecting element connected to the first track and to the sliding member. The first end of the first rigid connecting element is configured to move passively along the path, as the sliding member is driven to slide relative to the articulating support by an actuator.

A drone-type air mobility vehicle includes a body, a plurality of rotors, and a plurality of rotor arms configured to connect the plurality of rotors to the body. The drone-type air mobility vehicle further includes: a plurality of air flaps provided in the rotor arms, respectively, and configured to be deployed downwards with the respect to the respective rotor arms by gas injected into the air flaps; and a controller configured to determine whether the rotors are abnormal, based on a yaw rate of the mobility vehicle and state information of the rotors, and the controller configured to determine whether to deploy the air flaps according to a result of the determination on whether the rotors are abnormal.

A drone-type air mobility vehicle includes a body, a plurality of rotors, and a plurality of rotor arms configured to connect the plurality of rotors to the body. The drone-type air mobility vehicle further includes: a plurality of air flaps provided in the rotor arms, respectively, and configured to be deployed downwards with the respect to the respective rotor arms by gas injected into the air flaps; and a controller configured to determine whether the rotors are abnormal, based on a yaw rate of the mobility vehicle and state information of the rotors, and the controller configured to determine whether to deploy the air flaps according to a result of the determination on whether the rotors are abnormal.

A wing for an aircraft is disclosed including a main wing and a trailing edge high lift assembly movably arranged at a trailing edge of the main wing, the trailing edge high lift assembly having a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position. The connection assembly includes an actuator unit for moving the flap between the retracted position and the at least one extended position. The flap includes a leading edge part and a trailing edge part mounted to the leading edge part in a manner pivotable about a pivot axis.

A wing for an aircraft is disclosed including a main wing and a trailing edge high lift assembly movably arranged at a trailing edge of the main wing, the trailing edge high lift assembly having a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position. The connection assembly includes an actuator unit for moving the flap between the retracted position and the at least one extended position. The flap includes a leading edge part and a trailing edge part mounted to the leading edge part in a manner pivotable about a pivot axis.

A wingless compact aircraft, with a limited footprint and no exposed high-speed moving parts. The aircraft can takeoff and land vertically, can fly at high-speed and even cruise on land and water in one of the preferred embodiments.