For sealing at the transition between high-lift devices and fairings, a shutter assembly can be installed in a high-lift system, thereby forming the shutter arrangement. The shutter assembly includes the shutter panel and possibly the driving member. The shutter assembly can be installed in the high-lift system, to form any embodiment of the shutter arrangement. The shutter arrangement covers the trunnion opening and is moveable in correspondence with the movement of the high-lift device in a continuous and strictly monotone manner.

A rotary actuator assembly for moving a first relatively movable part relative to a second relatively movable part. The assembly includes a rotary actuator having a plurality of circumferential earth members for attachment to one of the first and the second relatively movable parts and a plurality of circumferential output members for attachment to the other of the first and second relatively movable parts. At least the plurality of circumferential earth members or the plurality of circumferential output members is provided with radially outwardly extending locking features around their circumference configured to be received in a mounting sleeve having complementary locking features to engage with the radially outwardly extending locking features.

An adjustable length crank arm includes a first component having a longitudinal length, a second component coupled to the first component, the second component having a longitudinal length. A total length of the crank arm can be adjusted by changing an amount of longitudinal overlap that exists between the first component and the second component. The adjustable length crank arm can include a first wedge and a second wedge and at least a portion of each of the first wedge and the second wedge is longitudinally captured between the first component and the second component.

A simple, safe, and inexpensive flight control system in an aircraft. An anti-torque system for a rotary-wing aircraft has an airfoil with a first surface extending from a first trailing edge and a leading edge, and a second surface extending from a second trailing edge to join the first surface at the leading edge. The airfoil has a first moveable deflector panel pivotally coupled to the first trailing edge, and a second moveable deflector panel pivotally coupled to the second trailing edge. Means are provided to pivot the deflector panels in unison about their respective pivot axes to alter the direction of travel of the airflow downstream of the pivot axes over the surfaces of the deflector panels, thereby producing a lift in a direction perpendicular to the airflow to counteract the torque applied on the aircraft. The flight control system may be arranged within a fixed-wing aircraft.

In one or more embodiments, a method for providing continuously variable feel forces for an aircraft comprises sensing, by each of at least one sensor associated with at least one aircraft control, a force sensor value. The method further comprises determining a net force value by using the force sensor value for each of at least one sensor. Also, the method comprises comparing the net force value to a desired breakout force. In addition, the method comprises determining whether the net force value exceeds the desired breakout force. Additionally, the method comprises determining an adjusted force value by using the desired breakout force and the net force value, when the net force value exceeds the desired breakout force. Also, the method comprises determining an actuator torque command based on the adjusted force value. Further, the method comprises commanding an autopilot actuator with the actuator torque command to apply torque.

A rotary actuator mounting system configured to attach a rotary actuator to and between two relatively moveable parts, the rotary actuator being attached to a first of the two relatively moveable parts and to a second of the relatively moveable parts such that operation of the actuator causes one of the first and second relatively movable parts to rotate relative to the other of the first and second relatively movable parts about an axis of the rotary actuator. The system includes a compliant attachment component connecting the actuator to the first relatively moveable part, the compliant attachment component having a first end attached to the first movable part and a second end attached to the actuator, and wherein at least one of the first and the second end is in the form of a ball bearing arranged to be received in a complementary socket on the actuator and/or the first movable part.

A rotary actuator mounting system configured to attach a rotary actuator to and between two relatively moveable parts, the rotary actuator being attached to a first of the two relatively moveable parts and to a second of the relatively moveable parts such that operation of the actuator causes one of the first and second relatively movable parts to rotate relative to the other of the first and second relatively movable parts about an axis of the rotary actuator. The system includes a compliant attachment component connecting the actuator to the first relatively moveable part, the compliant attachment component having a first end attached to the first movable part and a second end attached to the actuator, and wherein at least one of the first and the second end is in the form of a ball bearing arranged to be received in a complementary socket on the actuator and/or the first movable part.

Example flap actuation systems and related methods are disclosed herein. An example control surface actuation system includes processor circuitry to cause a first actuator to generate an output to operatively couple the first actuator to a first drive arm; cause a second actuator to generate an output to operatively couple the second actuator to a second drive arm; cause the first actuator and the second actuator to move a control surface when the first actuator and the second actuator are in an operative state; detect the first actuator as in a failed state; and in response to the first actuator being in the failed state, cause first actuator to refrain from generating the output to disrupt the operative coupling between the first actuator and the first drive arm; and cause the second actuator to move the control surface via the first drive arm and the second drive arm.

Installation of powered actuators in the leading edge of a control surface in order to have a better weight distribution. The systems described herein propose an actuation system with a static ground structure used to move a control surface of an aircraft. The actuation system, and the ground structure are aligned with the center of rotation of the control surface, providing the aircraft with flutter suppression. This proposal is an approach to use the actuator in a place favorable to the mass balancing and reducing or even dismissing the usage of mass balancing, saving weight and cost.

Installation of powered actuators in the leading edge of a control surface in order to have a better weight distribution. The systems described herein propose an actuation system with a static ground structure used to move a control surface of an aircraft. The actuation system, and the ground structure are aligned with the center of rotation of the control surface, providing the aircraft with flutter suppression. This proposal is an approach to use the actuator in a place favorable to the mass balancing and reducing or even dismissing the usage of mass balancing, saving weight and cost.