Abstract: An actuator for aviation may include an electromechanical drive unit connected with an output drive via a gearbox. The drive unit may have at least two partial drives that can be operated independently from one another. The gearbox may be located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.

Abstract: An actuator for aviation may include an electromechanical drive unit connected with an output drive via a gearbox. The drive unit may have at least two partial drives that can be operated independently from one another. The gearbox may be located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.

Abstract: The invention relates to a control rod for the adjusting of a helicopter rotor blade, wherein the control rod can be adjusted in longitudinal direction, comprising: at least one contact area element, at least one limit stop element, which is designed to limit the adjustability of the control rod in longitudinal direction to a specifiable adjusting range in interrelation with the at least one contact area element, wherein the limit stop element can be transferred from a first position to a second position, wherein the at least one stop element limits the adjustability of the control rod in the first position and enables the adjustability of the control rod beyond the specifiable adjusting range in the second position.

Abstract: An actuator for a rotor blade adjustment having an electromechanical drive unit may be connected with an output drive via a gearbox. The drive unit may have at least two partial drives that can be operated independently from one another. The gearbox may be located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.

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 invention relates to a control rod for the adjusting of a helicopter rotor blade, wherein the control rod can be adjusted in longitudinal direction, comprising: at least one contact area element, at least one limit stop element, which is designed to limit the adjustability of the control rod in longitudinal direction to a specifiable adjusting range in interrelation with the at least one contact area element, wherein the limit stop element can be transferred from a first position to a second position, wherein the at least one stop element limits the adjustability of the control rod in the first position and enables the adjustability of the control rod beyond the specifiable adjusting range in the second position.

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: A rotor blade control device for a helicopter, comprising a swash-ring, said swash-ring comprising a non-rotating component of the swash-ring, coupled in a non-rotatable manner to the helicopter, a rotating component of the swash-ring, at least three actuators disposed around a rotor shaft axis of the helicopter, a coupling means between the actuators and the non-rotating component of the swash-ring. The coupling means can be adjusted in terms of its pitch, for changing the position of a swash-ring coupling point on the non-rotating component of the swash-ring along the rotor shaft axis by the actuator, by means of a control shaft, in order to adjust the rotor blades.

Abstract: The present embodiments provide an actuator for a rotor blade adjustment having an electromechanical drive unit connected with an output drive via a gearbox. The drive unit may have at least two partial drives that can be operated independently from one another. The gearbox may be located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.

Abstract: A rotor blade control device for a helicopter, comprising a swash-ring, said swash-ring comprising a non-rotating component of the swash-ring, coupled in a non-rotatable manner to the helicopter, a rotating component of the swash-ring, at least three actuators disposed around a rotor shaft axis of the helicopter, a coupling means between the actuators and the non-rotating component of the swash-ring. The coupling means can be adjusted in terms of its pitch, for changing the position of a swash-ring coupling point on the non-rotating component of the swash-ring along the rotor shaft axis by the actuator, by means of a control shaft, in order to adjust the rotor blades.