Abstract: A system for controlling an electromechanical actuator for setting a collective offset for a helicopter on a blade-specific basis, wherein the system comprises at least one actuator, the length and position of which can be adjusted electromechanically within a mechanically limited range, a power electronics that is configured to adjust the actuator by means of a servomotor in two directions, specifically toward a positive collective offset or toward a negative collective offset, and a first microelectronics system that is configured to control the power electronics such that positive and negative collective offsets can be set. The system also includes a second microelectronics system, which is configured to override the actuation of the first microelectronics system in order to act on the adjustment of the actuator, and by a first control line, which is configured to activate or deactivate the second microelectronics system through an external electrical signal.

Abstract: In one aspect, the present disclosure provides a system for reducing vibrations or stresses in a rotor blade system. The system may include at least three rotor blades configured to be rotated about a main rotor axis, where each of the three rotor blades may be adjusted by at least one electrically-adjustable control rod of a plurality of control rods. The plurality of control rods may include a first number of control rods forming a first group, and the plurality of control rods may include a second number of control rods forming a second group. A first circuit for may activate or deactivate the first group of control rods, and a second circuit may activate or deactivate the second group of control rods.

Abstract: A method for predicting vibrations in an aircraft comprising an active vibration reduction system includes estimating a first vibration amplitude or frequency resulting from adjustments by the active vibration reduction system and the respective sensitivities of the aircraft depending on the flying state using a statistical mathematical process, recording a second vibration amplitude or frequency by a sensor, generating a pseudo-vibration profile by combining the first and second vibration amplitudes or frequencies, comparing the pseudo-vibration profile with a predefined target vibration profile, and outputting a signal when a specific threshold value has been exceeded.

Abstract: In one aspect, the present disclosure provides a system for reducing vibrations or stresses in a rotor blade system. The system may include at least three rotor blades configured to be rotated about a main rotor axis, where each of the three rotor blades may be adjusted by at least one electrically-adjustable control rod of a plurality of control rods. The plurality of control rods may include a first number of control rods forming a first group, and the plurality of control rods may include a second number of control rods forming a second group. A first circuit for may activate or deactivate the first group of control rods, and a second circuit may activate or deactivate the second group of control rods.

Abstract: In one aspect, the present disclosure provides a system for reducing vibrations or stresses in a rotor blade system. The system may include at least three rotor blades configured to be rotated about a main rotor axis, where each of the three rotor blades may be adjusted by at least one electrically-adjustable control rod of a plurality of control rods. The plurality of control rods may include a first number of control rods forming a first group, and the plurality of control rods may include a second number of control rods forming a second group. A first circuit for may activate or deactivate the first group of control rods, and a second circuit may activate or deactivate the second group of control rods.

Abstract: A system for controlling an electromechanical actuator for setting a collective offset for a helicopter on a blade-specific basis, wherein the system comprises at least one actuator, the length and position of which can be adjusted electromechanically within a mechanically limited range, a power electronics that is configured to adjust the actuator by means of a servomotor in two directions, specifically toward a positive collective offset or toward a negative collective offset, and a first microelectronics system that is configured to control the power electronics such that positive and negative collective offsets can be set. The system also includes a second microelectronics system, which is configured to override the actuation of the first microelectronics system in order to act on the adjustment of the actuator, and by a first control line, which is configured to activate or deactivate the second microelectronics system through an external electrical signal.

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 invention relates to a method for predicting vibrations in an aircraft, wherein the aircraft comprises an active system for reducing main and/or tail rotor vibrations, in particular length-adjustable control rods and/or trim tabs, wherein the method comprises the steps: estimating a first amplitude or frequency, resulting from adjustments by the active system for actively reducing vibrations and the respective sensitivities of the aircraft depending on the flying state, by means of a statistical mathematical method in a first step 110 at a first point in time t1; recording a second amplitude or frequency by means of at least one sensor in a second step 120 at a second point in time t2; generating a pseudo-vibration profile by means of the first amplitude or frequency and the second vibrations in a third step 130 at a third point in time t3; comparing the pseudo-vibration profile with a predefined target vibration profile of the aircraft in a fourth step 140 at a fourth point in time t4; outputting a s

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: In one aspect, the present disclosure provides a system for reducing vibrations or stresses in a rotor blade system. The system may include at least three rotor blades configured to be rotated about a main rotor axis, where each of the three rotor blades may be adjusted by at least one electrically-adjustable control rod of a plurality of control rods. The plurality of control rods may include a first number of control rods forming a first group, and the plurality of control rods may include a second number of control rods forming a second group. A first circuit for may activate or deactivate the first group of control rods, and a second circuit may activate or deactivate the second group of control rods.

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.