Abstract: An actuator for aviation applications, in particular for adjusting rotor blades in a helicopter, may include an electromechanical drive assembly connected to an output drive via a downstream transmission, where the drive assembly is divided into sub-drives that can be operated independently, and where at least two sub-drives are spatially separated from one another in that the transmission is placed between these sub-drives. The transmission may include at least two harmonic gearings coupled to one another by at least one first coupling element, where a first harmonic gearing is located inside a non-rotating first housing, where a second harmonic gearing is located inside a rotating second housing, and where the second housing is connected to the output drive.

Abstract: An actuator for aviation applications, in particular for adjusting rotor blades in a helicopter, may include an electromechanical drive assembly connected to an output drive via a downstream transmission, where the drive assembly is divided into sub-drives that can be operated independently, and where at least two sub-drives are spatially separated from one another in that the transmission is placed between these sub-drives. The transmission may include at least two harmonic gearings coupled to one another by at least one first coupling element, where a first harmonic gearing is located inside a non-rotating first housing, where a second harmonic gearing is located inside a rotating second housing, and where the second housing is connected to the output drive.

Abstract: The discovery concerns a rotor hub cover for a helicopter, whereby the rotor hub cover has been constructed as a rotational body with a dome-shaped cover and the rotor hub cover has performance and control electronic components, characterized by the arrangement of the performance electronic components and the control electronic components on a surface of the internal side or the dome-shaped cover.

Abstract: The discovery concerns a rotor hub cover for a helicopter, whereby the rotor hub cover has been constructed as a rotational body with a dome-shaped cover and the rotor hub cover has performance and control electronic components, characterized by the arrangement of the performance electronic components and the control electronic components on a surface of the internal side or the dome-shaped cover.

Abstract: The present disclosure provides a rotor blade control device for a helicopter. The rotor blade control device may include a swash plate disk with a non-rotating component coupled to the helicopter. At least three actuators may be arranged around a rotor shaft axis of the helicopter, and a coupling element may be located between each actuator and the non-rotating component. The coupling element can be adjusted to change the position of a crosspoint at the non-rotating component of the swash plate disk alongside the rotor shaft axis in order to adjust the rotor blades. The actuators may be arranged onto the non-rotating component and may be able to pivot around a respective swivel axis. A radial distance of the first crosspoint to the rotor shaft axis may change with the swivel movement of an actuator around the swivel axis.

Abstract: Rotor blade control device for a helicopter, consisting of a swash plate disk, the swash plate disk consisting of a non-rotating part of the swash plate disk, which is stationary stationarily coupled to the helicopter, a rotating part of the swash plate disk, at least three actuators which are arranged around a rotor shaft axis of the helicopter, a coupling element between actuator and the non-rotating part of the swash plate disk. The coupling element can be adjusted in its tilt, in order to change the position of the crosspoint at the non-rotating part of the swash plate disk alongside the rotor shaft axis by means of the actuator through a control shaft, in order to adjust the rotor blades. Here, the coupling element is made up in a rigid way, and the actuators are arranged onto the stationary component being able to pivot around a respective swivel axis.

Abstract: An electro-mechanical linear actuator unit comprising an actuator housing that accommodates at least two electric drives, each of which, when actuated by a control device, sets an associated drive of a respective spindle drive into rotation for adjusting linear movement of the associated spindle drive in order to produce relative linear adjustment of a control rod. The two electric drives are located in the actuator housing in such manner that relative adjustment can be produced by simultaneous actuation of the two electric drives, as the sum of the adjustment movements of the associated spindle drives, or by actuating a single electric drive, as the adjustment movement of the associated spindle drive. A respective brake is provided, in an area of each of the two electric drives, which can be selectively actuated by the control device to then prevent the adjustment movement of the respective associated spindle drive.

Abstract: An electro-mechanical linear actuator unit comprising an actuator housing that accommodates at least two electric drives, each of which, when actuated by a control device, sets an associated drive of a respective spindle drive into rotation for adjusting linear movement of the associated spindle drive in order to produce relative linear adjustment of a control rod. The two electric drives are located in the actuator housing in such manner that relative adjustment can be produced by simultaneous actuation of the two electric drives, as the sum of the adjustment movements of the associated spindle drives, or by actuating a single electric drive, as the adjustment movement of the associated spindle drive. A respective brake is provided, in an area of each of the two electric drives, which can be selectively actuated by the control device to then prevent the adjustment movement of the respective associated spindle drive.

Abstract: A helicopter with rotor blades rotatably connected to a rotor head. The rotor head is non-rotatably connected with a rotor mast (1) pivoted in a transmission housing and driven by a transmission via at least one driving mechanism. A pitch of the rotor blades, relative to a plane of rotation of the rotor blades, is controlled via a swash plate, control rods (12) and via individual actuators (9) allocated to each individual rotor blade. The control rods (12) and the actuators (9) are mounted in the rotor mast (1) and the rotor head and those components act, via a mixing lever (11) and a control rod (8), upon a pivoted arm (7) which adjusts the pitch of the rotor blade. The control devices of the rotor blades do not interfere with the air flow, are affected only to a limited extent by centrifugal forces and additional stresses, and are also protected against influences of the weather.