A wing for an aircraft, comprising a main wing and a slat assembly with a slat and a connection assembly with a slat track. The front end of the slat track is mounted to the slat, and the rear end and/or the intermediate portion of the slat track are mounted to the main wing by a roller or slide bearing. The slat track is movable along the track longitudinal axis. The connection assembly includes a drive unit. The drive unit includes a rotary actuator mounted to the main wing and having at least one drive arm rotatably driven about a rotation axis and drivingly engaging the slat track, and one of the drive arm and the slat track has at least one groove and the other one of the drive arm and the slat track comprises at least one spigot drivingly engaging the groove.

A wing for an aircraft, comprising a main wing and a slat assembly with a slat and a connection assembly with a slat track. The front end of the slat track is mounted to the slat, and the rear end and/or the intermediate portion of the slat track are mounted to the main wing by a roller or slide bearing. The slat track is movable along the track longitudinal axis. The connection assembly includes a drive unit. The drive unit includes a rotary actuator mounted to the main wing and having at least one drive arm rotatably driven about a rotation axis and drivingly engaging the slat track, and one of the drive arm and the slat track has at least one groove and the other one of the drive arm and the slat track comprises at least one spigot drivingly engaging the groove.

Robotic wings for an aerial drone include a plurality of armwing structures, each comprising a plurality of rigid members connected together by flexible living hinges in a single monolithic structure. Wing membranes are supported by the armwing structures. A drive mechanism is connected to the armwing structures for articulating the armwing structures. A motor is connected to the drive mechanism for actuating the drive mechanism to move the armwing structures through a series of wingbeats wherein the armwing structures expand in a downstroke and retract in an upstroke to move the wing membranes in a flapping motion.

Robotic wings for an aerial drone include a plurality of armwing structures, each comprising a plurality of rigid members connected together by flexible living hinges in a single monolithic structure. Wing membranes are supported by the armwing structures. A drive mechanism is connected to the armwing structures for articulating the armwing structures. A motor is connected to the drive mechanism for actuating the drive mechanism to move the armwing structures through a series of wingbeats wherein the armwing structures expand in a downstroke and retract in an upstroke to move the wing membranes in a flapping motion.

Example aircraft spoiler actuation systems and related methods are disclosed herein. An example spoiler actuation system includes a rotary actuator, a first output shaft coupled to the rotary actuator, a second output shaft coupled to the rotary actuator, the first output shaft opposite the second output shaft, a first actuator rod coupled to the spoiler at a first location, and a second actuator rod coupled to the spoiler at a second location, the second location spaced apart from the first location. The rotary actuator is operatively coupled to the first actuator rod via the first output shaft and to the second actuator rod via the second output shaft to cause the spoiler to move between one of a stowed position and a raised position or the stowed position and a drooped position.

Described is a mechanical transmission (T) comprising a containment structure (1) housing a roto-translational element (2), extending along an axis of rotation (X) and comprising a first and a second threaded portion (3, 4), a rotary element (5) connected or connectable to a drive unit to define a mechanical power input unit and equipped with a first thread (8) designed to engage rotatably with the first threaded portion (3) to the roto-translational element in such a way as to define a first threaded connection, a fixed guide (9) having a second thread (14) designed to engage with the second threaded portion (4) of the roto-translational element (2) in such a way as to define a second threaded connection, and a translating element (10), translating along the axis (X) and defining a power output unit. The translating element (10) is connected to the roto-translational element (2) for translating at the same linear speed as the roto-translational element (2). The roto-translational element (2) is thus simultaneously coupled to the rotary element (5) and to the fixed guide (9) respectively by means of the first and second threaded connections. These connections have different pitches in such a way as to vary the angular speed between the roto-translational element (2) and the rotary element (5).

Described is a mechanical transmission (T) comprising a containment structure (1) housing a roto-translational element (2), extending along an axis of rotation (X) and comprising a first and a second threaded portion (3, 4), a rotary element (5) connected or connectable to a drive unit to define a mechanical power input unit and equipped with a first thread (8) designed to engage rotatably with the first threaded portion (3) to the roto-translational element in such a way as to define a first threaded connection, a fixed guide (9) having a second thread (14) designed to engage with the second threaded portion (4) of the roto-translational element (2) in such a way as to define a second threaded connection, and a translating element (10), translating along the axis (X) and defining a power output unit. The translating element (10) is connected to the roto-translational element (2) for translating at the same linear speed as the roto-translational element (2). The roto-translational element (2) is thus simultaneously coupled to the rotary element (5) and to the fixed guide (9) respectively by means of the first and second threaded connections. These connections have different pitches in such a way as to vary the angular speed between the roto-translational element (2) and the rotary element (5).

Various flight control components can be operated through gearbox driven rotary actuators. In the event of a jam occurring the gearbox, the gearbox can be decoupled from a surrounding support housing to enable free-trailing or limited motion relative to the support housing. The motion may or may not be damped. Decoupling the gearbox enables the flight control component to move to a neutral or non-interfering position even when user control over the component has been lost.

A wing for an aircraft including a wing tip section with an inboard section, a fairing in which an opening connecting an exterior of the fairing and an interior of the fairing is formed and which is mounted to the inboard section of the wing tip section, a movable device arranged in the exterior of the fairing, a connecting assembly movably connecting the movable device to the wing tip section such that the movable device is movable between a retracted position and at least one extended position, and a drive mechanism. The connecting assembly includes an actuating element, which extends through the opening and includes a first section, which is arranged in the interior of the fairing and is drivingly coupled to the drive mechanism, and a second section, which is arranged in the exterior of the fairing and coupled to the movable device.

A wing for an aircraft including a wing tip section with an inboard section, a fairing in which an opening connecting an exterior of the fairing and an interior of the fairing is formed and which is mounted to the inboard section of the wing tip section, a movable device arranged in the exterior of the fairing, a connecting assembly movably connecting the movable device to the wing tip section such that the movable device is movable between a retracted position and at least one extended position, and a drive mechanism. The connecting assembly includes an actuating element, which extends through the opening and includes a first section, which is arranged in the interior of the fairing and is drivingly coupled to the drive mechanism, and a second section, which is arranged in the exterior of the fairing and coupled to the movable device.