Abstract: An aerodynamic surface for an aircraft, comprising a torsion box, a movable control surface, and a central element, the torsion box comprising a rear spar, upper and lower covers, and the movable control surface comprising a leading edge, a front spar, a hinge line, a beam having a first end and a second end, and a counterweight attached to the second end of the beam. The first end of the beam is attached to the front spar, and the second end is projected beyond at least the hinge line so that the counterweight is arranged between the upper and lower covers extending from the rear spar of the torsion box towards the movable control surface.

Abstract: A power take off unit includes an input gear, an output gear, and an intermediary gear that cooperate to transfer power from a rotational power source to an operating target. The power take off unit has a control module that biases the intermediary gear relative to the input gear and the output gear to reduce gear rattle vibrations associated with intermeshed tooth looseness.

Abstract: A power take off unit includes an input gear, an output gear, and an intermediary gear that cooperate to transfer power from a rotational power source to an operating target. The power take off unit has a control module that biases the intermediary gear relative to the input gear and the output gear to reduce gear rattle vibrations associated with intermeshed tooth looseness.

Abstract: The invention concerns a device for a adjustable flap adjustably mounted on a main wing surface of an aeroplane wing, in particular, a landing flap, with at least one adjustment unit for purposes of adjustment of the adjustable flap, which has an actuator arranged, or that can be arranged, on the main wing surface, and has a kinematic adjustment mechanism running between the actuator and the adjustable flap, wherein the adjustable flap is mechanically coupled with the actuator via the kinematic adjustment mechanism. At least one damping unit for purposes of damping a dynamic loading effected by the adjustable flap on the adjustment unit, which can occur as a result of a critical malfunction event occurring in the region of the adjustable flap, is arranged, or can be arranged, between the main wing surface and the adjustable flap.

Abstract: A method and device for detecting oscillatory faults relating to an aircraft airfoil slaving chain. The device includes units that count the number of overshoots of a threshold value by the current value of a quantity related to the positional slaving of an airfoil. Oscillatory fault is detected based on the number of overshoots of the threshold value being greater than the current value by a predetermined number.

Abstract: Disclosed is a method of detecting at least one oscillatory fault in at least one positional slaving chain for at least one airfoil of an aircraft. The method involves estimating a reference position of the airfoil in the absence of a fault, and calculating a residual value based on the difference between the estimated reference position and the actual position measured by at least one sensor. The calculated residual value is compared with at least one predetermined threshold value to determine the number of successive and alternating overshoots of the predetermined threshold value by the residual value, and oscillatory fault is determined based on the determined number.

Abstract: The Tail Load Monitoring System detects faulty low frequency (e.g. those in the range from 0.1 to 1 Hz) oscillatory conditions caused by Flight Control System malfunctions while the aircraft is in air by means of a continuous assessment of the estimated tail load behavior and data processing. Both estimation and data processing activities are provided by a dedicated architecture featuring a tail load estimation module, a band-pass filter and three independent paths that continuously monitor nuisance fault detection events avoidance, catastrophic events avoidance (addressing a limit load criterion), and structural damage avoidance (addressing fatigue life criteria).

Abstract: A support assembly for deployment and retraction of an aero surface from an aircraft is disclosed. The assembly comprises a guide track, a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is rotatable relative to the carriage about multiple axes, and a control arm having one end coupled to the primary support arm and a second end pivotably attachable to a fixed support forming part of the structure of the aircraft. The assembly being configured such that, when the carriage is driven along the guide track, the control arm causes the primary support arm to pivot about said multiple axes to deploy and/or retract an aero surface pivotally attached to an opposite end of the primary support member along an arcuate path.

Abstract: Circuits and methods for use on a mobile platform including a flight control system, a structure, an aerodynamic surface, and an actuator operatively coupled to the surface to control the surface. The circuit includes a first and a second input, a summing element, and an output. The first input accepts commands from the flight control system while the second input accepts a vibration signal from the structure. The summing element communicates with the inputs and sums the signal and the command. In turn, the summing element controls the actuator with the summed signal and command.

Abstract: Apparatus and methods for hybrid actuation and suppressing vibration are disclosed. In one embodiment, a hybrid actuator includes a first actuator and a second actuator linked to move a component a combined actuation distance. The first actuator may include a hydraulic piston, and the second actuator may include a piezo-electric actuator. In another embodiment, the first actuator is activated within a first frequency range, and the second actuator is activated within a second frequency range. In another aspect, a method is provided combining a first actuation movement and a second actuation movement. In another embodiment, a system is provided for suppressing movement of a component including a combination of actuators. In a further embodiment, an aircraft is provided with hybrid motion suppression including a first actuator and a second actuator linked to activate a control surface.

Abstract: Circuits and methods for use on a mobile platform including a flight control system, a structure, an aerodynamic surface, and an actuator operatively coupled to the surface to control the surface. The circuit includes a first and a second input, a summing element, and an output. The first input accepts commands from the flight control system while the second input accepts a vibration signal from the structure. The summing element communicates with the inputs and sums the signal and the command. In turn, the summing element controls the actuator with the summed signal and command.

Abstract: Apparatus and methods for hybrid actuation and suppressing vibration are disclosed. In one embodiment, a hybrid actuator includes a first actuator and a second actuator linked to move a component a combined actuation distance. The first actuator may include a hydraulic piston, and the second actuator may include a piezo-electric actuator. In another embodiment, the first actuator is activated within a first frequency range, and the second actuator is activated within a second frequency range. In another aspect, a method is provided combining a first actuation movement and a second actuation movement. In another embodiment, a system is provided for suppressing movement of a component including a combination of actuators. In a further embodiment, an aircraft is provided with hybrid motion suppression including a first actuator and a second actuator linked to activate a control surface.

Abstract: Servocontrolled aerodynamic control surfaces, such as the direction rudder (1) of an airplane, are equipped with servoactuators (5). The bearing supports (3) of the rotation axis (2) or hinged axis give rise to the formation of free play for the manufacturing tolerances, that will be more pronounced with the wear of the bearings or joint elements. The mechanism (8) in question includes an elastic element (10) fixed to the structure (4) wherein the control surface (1) is jointed, connected rigidly to an articulated connecting rod (12) having a following roller (13) of a cam (9) integral to the control surface (1). The cam (9) profile produces a continuous nonlinear, angular deformation, of the elastic element in order to determine a force torque on the control surface (1) that is maximum in the neutral position of the control surface and manages to be eliminated in the extreme side deviations.