Flap actuation systems for aircraft

An aircraft wing comprising:

• a fixed wing portion;
• a flap;
• a first flap actuation system coupled to the fixed wing portion to move the flap relative to the fixed wing portion between a stowed position and a deployed position, the first flap actuation system including:
• a first fixed beam coupled to and extending downward from the fixed wing portion;
• a first rocking lever plate pivotably coupled to the first fixed beam via a first coupling, the first coupling forming a first hingeline, the first rocking lever plate coupled to a forward end of a flap bracket disposed on a bottom side of the flap, the first rocking lever plate to be rotated relative to the first fixed beam via a rotary actuator;
• and
• a flap link coupled between the first rocking lever plate and an aft end of the flap bracket, the first fixed beam, the first rocking lever plate, the flap bracket, and the flap link oriented generally streamwise;
• and
• a second flap actuation system to move the flap between the stowed position and the deployed position, the second flap actuation system including:
• a second fixed beam coupled to an extending downward from the fixed wing portion;
• and
• a second rocking lever plate pivotably coupled to the second fixed beam via a second coupling, the second coupling forming a second hingeline, wherein the second hingeline is offset from and non-parallel to the first hingeline.

A flap actuation system comprising:

• a fixed beam coupled to and extending downward from a fixed wing portion of a wing of an aircraft;
• a rocking lever plate pivotably coupled to the fixed beam via a first coupling, the rocking lever plate coupled to a forward end of a flap bracket disposed on a bottom side of a flap of the wing;
• a linear actuator having an output shaft;
• a connecting arm coupled between the output shaft and the rocking lever plate, the connecting arm coupled to the rocking lever plate via a second coupling that is spaced apart from the first coupling;
• and
• a flap link coupled between the rocking lever plate and an aft end of the flap bracket, such that actuation of the output shaft pivots the rocking lever plate to move the flap between a stowed position and a deployed position relative to the fixed wing portion, wherein the flap link and the rocking lever plate are coupled via a third coupling, the flap link and the flap bracket are coupled via a fourth coupling, and the third and fourth couplings form rotational axes that are oriented in a direction that is perpendicular to a direction of rotational axes of the first and second couplings.