A flap actuation mechanism incorporates a coupler rod eccentrically supported at an aft end and at a forward end. The coupler rod is configured to translate from an aft position to a forward position. An inboard crank arm is coupled to the rotary actuator and engaged to the aft end of the coupler rod. The inboard crank is configured rotate responsive to rotation of the rotary actuator thereby inducing translation of the coupler rod. An outboard crank arm engaged to a forward end of the coupler rod and is configured to rotate responsive to translation of the coupler rod. A flap drive arm is attached to the outboard crank arm and is configured to rotate with the outboard crank arm from a stowed position to a deployed position responsive to translation of the coupler rod from the aft position to the forward position.

A method for controlling a control surface multirod actuator arrangement and the arrangement including: a first and a second multirod actuator configured to move or clamp around a first set of piston rods; a third multirod actuator configured to move or clamp around a second set of piston rods; a control unit configured to control motion of the first set of piston rods in a first motion mode and to control motion of the second set of piston rods in a second motion mode. Steps are moving at least one piston rod of first set of piston rods and/or clamping in parked position at least one piston rod of the second set of piston rods.

A method for controlling a control surface multirod actuator arrangement and the arrangement including: a first and a second multirod actuator configured to move or clamp around a first set of piston rods; a third multirod actuator configured to move or clamp around a second set of piston rods; a control unit configured to control motion of the first set of piston rods in a first motion mode and to control motion of the second set of piston rods in a second motion mode. Steps are moving at least one piston rod of first set of piston rods and/or clamping in parked position at least one piston rod of the second set of piston rods.

Linkage assemblies for moving tabs on control surfaces of aircraft are disclosed herein. An example aircraft includes a wing including a fixed wing portion and a trailing edge control surface. The trailing edge control surface includes a fore panel rotatably coupled to the fixed wing portion and an aft panel rotatably coupled to the fore panel. The wing also includes a linkage assembly including a rocking lever rotatably coupled to a bottom side of the fore panel, a trailing edge link having a first end rotatably coupled to the fixed wing portion and a second end rotatably coupled to the rocking lever, and an aft panel link having a first end rotatably coupled to the rocking lever and a second end rotatably coupled to a bottom side of the aft panel.

Linkage assemblies for moving tabs on control surfaces of aircraft are disclosed herein. An example aircraft includes a wing including a fixed wing portion and a trailing edge control surface. The trailing edge control surface includes a fore panel rotatably coupled to the fixed wing portion and an aft panel rotatably coupled to the fore panel. The wing also includes a linkage assembly including a rocking lever rotatably coupled to a bottom side of the fore panel, a trailing edge link having a first end rotatably coupled to the fixed wing portion and a second end rotatably coupled to the rocking lever, and an aft panel link having a first end rotatably coupled to the rocking lever and a second end rotatably coupled to a bottom side of the aft panel.

A system for an aircraft wing including a power drive unit (101), a first actuator (104C) for actuating a first aerodynamic device (103), a second actuator (104A) for actuating a second aerodynamic device (102), a first drive path (109B) configured to operate between the power drive unit (101) and the first actuator (104C), a second drive path (109A) operably connecting the power drive unit (101) and the second actuator (104A), the first drive path (109B) including a lost motion device (108A), the lost motion device (108A) being configured to selectively operably connect the power drive unit (101) to the first actuator (104C) and selectively operably disconnect the power drive unit (101) from the first actuator (104C).

A high-lift device includes a flap disposed at a leading edge of a wing, and configured to be retracted in the lower surface and extended toward of the leading edge; a first rotary shaft and a second rotary shaft, the axial direction of the rotary shafts being disposed along the spanwise direction of the wing, respectively; a first link mechanism connected to the first rotary shaft and the flap; and a second link mechanism connected to the second rotary shaft and the flap. When the first link mechanism is driven with the first rotary shaft, the flap is retracted in the lower surface of the leading edge or is extended toward the front of the leading edge. When the second link mechanism is driven with the second rotary shaft, the position or the angle of the flap moved by the first link mechanism is changed.

A high-lift device includes a flap disposed at a leading edge of a wing, and configured to be retracted in the lower surface and extended toward of the leading edge; a first rotary shaft and a second rotary shaft, the axial direction of the rotary shafts being disposed along the spanwise direction of the wing, respectively; a first link mechanism connected to the first rotary shaft and the flap; and a second link mechanism connected to the second rotary shaft and the flap. When the first link mechanism is driven with the first rotary shaft, the flap is retracted in the lower surface of the leading edge or is extended toward the front of the leading edge. When the second link mechanism is driven with the second rotary shaft, the position or the angle of the flap moved by the first link mechanism is changed.

A wing, a method of controlling lift on a wing, and a system to produce lift on a wing are provided. The wing may include a fore-element, an aft-element, a pivotable linkage that operatively connects the aft-element leading edge to the fore-element trailing edge in a span-wise direction, and an actuator. The actuator may deflect the aft-element through a predetermined deflection angle about the pivotable linkage relative to the fore-element within less than or equal to two convective periods. The method may include deflecting a span-wise flap through the deflection angle in less than or equal to two convective periods to produce high lift. The system may include a sensor to detect an input and a controller to deflect the span-wise flap of the wing by the deflection angle in not more than two convective periods based on the received input signal.

A wing, a method of controlling lift on a wing, and a system to produce lift on a wing are provided. The wing may include a fore-element, an aft-element, a pivotable linkage that operatively connects the aft-element leading edge to the fore-element trailing edge in a span-wise direction, and an actuator. The actuator may deflect the aft-element through a predetermined deflection angle about the pivotable linkage relative to the fore-element within less than or equal to two convective periods. The method may include deflecting a span-wise flap through the deflection angle in less than or equal to two convective periods to produce high lift. The system may include a sensor to detect an input and a controller to deflect the span-wise flap of the wing by the deflection angle in not more than two convective periods based on the received input signal.