Distributed trailing edge actuation systems and methods for aircraft

An aircraft comprising:

• a wing;
• a flap coupled to the wing, the flap movable between a stowed position and a deployed position;
• and
• a distributed trailing edge (DTE) actuation system including:
• a flap actuator coupled to the wing to move the flap, the flap actuator including an integrated hydraulic powered actuator and electric powered actuator, the flap actuator operable in a hydraulic powered mode in which the hydraulic powered actuator is activated to move the flap, an electric powered mode in which the electric powered actuator is activated to move the flap, and a hybrid mode in which the hydraulic powered actuator and the electric powered actuator are activated simultaneously to move the flap, wherein the flap actuator is a rotary actuator including a crank arm, the crank arm coupled to the flap via a linkage assembly, and wherein the wing includes a support bracket, the hydraulic powered actuator and the electric powered actuator disposed on opposite sides of the support bracket.

A method comprising:

• determining an engine of an aircraft has failed, wherein failure of the engine causes a reduction in hydraulic power in an aircraft hydraulic system, the aircraft including:
• a wing;
• a flap coupled to the wing, the flap moveable between a stowed position and a deployed position;
• and
• a flap actuator coupled to the wing to move the flap relative to a trailing edge of the wing, the flap actuator including an integrated hydraulic powered actuator and electric powered actuator, the flap actuator operable in a hydraulic powered mode in which the hydraulic powered actuator is activated to move the flap, an electric powered mode in which the electric powered actuator is activated to move the flap, and a hybrid mode in which the hydraulic powered actuator and the electric powered actuator are activated simultaneously to move the flap, wherein the flap actuator is a rotary actuator including a crank arm, the crank arm coupled to the flap via a linkage assembly, and wherein the wing includes a support bracket, the hydraulic powered actuator and the electric powered actuator disposed on opposite sides of the support bracket;
• and
• in response to determining the engine has failed, operating the flap actuator in the hybrid mode in which the hydraulic powered actuator and the electric powered actuator are activated simultaneously to move the flap.