Abstract: Described herein are methods of diagnosing systemic sclerosis (SSc) involving the detection of anti-vinculin antibodies. Also described herein are methods of selecting treatment of subjects diagnosed with systemic sclerosis (SSc), and methods of treating systemic sclerosis (SSc).

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: Described herein are methods of diagnosing systemic sclerosis (SSc) involving the detection of anti-vinculin antibodies. Also described herein are methods of selecting treatment of subjects diagnosed with systemic sclerosis (SSc), and methods of treating systemic sclerosis (SSc).

Abstract: The invention relates to a system for the data transfer and processing for the controlling of a rotor blade actuator, the system comprising: an adjusting device (2) that is arranged within the rotating system (10) of the helicopter, which is configured to provide at least one first rotor blade actuator (1); a first control system (3) that is arranged within the rotating system and that is coupled via signals (11) to the adjusting device (2); a first sensor (4) that is arranged within the rotating system (10) which is designed to detect at least one first control variable of the rotor blade actuator (1) in the time domain and to transmit this control variable in the time domain to the first control system (3) via a second signal-based coupling (12); wherein the first control system (3) is configured to receive the first control variable via the signal-based coupling (12), to determine at least one first control value in the time domain by using the received control variable in the time domain and by using a

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 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 system for the data transfer and processing for the controlling of a rotor blade actuator, the system comprising: an adjusting device (2) that is arranged within the rotating system (10) of the helicopter, which is configured to provide at least one first rotor blade actuator (1); a first control system (3) that is arranged within the rotating system and that is coupled via signals (11) to the adjusting device (2); a first sensor (4) that is arranged within the rotating system (10) which is designed to detect at least one first control variable of the rotor blade actuator (1) in the time domain and to transmit this control variable in the time domain to the first control system (3) via a second signal-based coupling (12); wherein the first control system (3) is configured to receive the first control variable via the signal-based coupling (12), to determine at least one first control value in the time domain by using the received control variable in the time domain and by using a

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 method of controlling rotor pitch in a helicopter comprising the steps of: generating at least one blade dynamics signal representing at least one dynamic force acting on at least one of a rotor blade rotating assembly and a helicopter non-rotating assembly, the rotor blade rotating assembly including a plurality of rotor blades and a pitch actuator for each rotor blade; extracting information representing the at least one dynamic force; generating a dynamic force compensation output representing a compensation for at least a portion of the at least one dynamic force; receiving flight control signals directing flight of the helicopter from flight controls of the helicopter; generating from the flight control signals and the dynamic force compensation output a compensated pitch control signal for each blade of the rotor blade rotating assembly, and providing a compensated pitch control signal to compensate for a portion of the at least one dynamic force.

Abstract: A method of controlling rotor pitch in a helicopter comprising the steps of: generating at least one blade dynamics signal representing at least one dynamic force acting on at least one of a rotor blade rotating assembly and a helicopter non-rotating assembly, the rotor blade rotating assembly including a plurality of rotor blades and a pitch actuator for each rotor blade; extracting information representing the at least one dynamic force; generating a dynamic force compensation output representing a compensation for at least a portion of the at least one dynamic force; receiving flight control signals directing flight of the helicopter from flight controls of the helicopter; generating from the flight control signals and the dynamic force compensation output a compensated pitch control signal for each blade of the rotor blade rotating assembly, and providing a compensated pitch control signal to compensate for a portion of the at least one dynamic force.

Abstract: Controlling the pitch of individual rotor blades of a helicopter to reduce control loads, vibration and noise in or from the rotating rotor control elements. The system generates blade dynamics signals representing dynamic forces acting on either or both of the rotating and non-rotating elements of the helicopter, including rotor blades of a rotating assembly. The system extracts information representing at least one dynamic force, generates a dynamic force compensation output that represents a compensation for the dynamic force, and generates, from flight control signals and the dynamic force compensation output, a compensated pitch actuator control signal for each rotor blade wherein the compensation factor of the pitch control signal compensates for the dynamic force.

Abstract: Controlling the pitch of individual rotor blades of a helicopter to reduce control loads, vibration and noise in or from the rotating rotor control elements. The system generates blade dynamics signals representing dynamic forces acting on either or both of the rotating and non-rotating elements of the helicopter, including rotor blades of a rotating assembly. The system extracts information representing at least one dynamic force, generates a dynamic force compensation output that represents a compensation for the dynamic force, and generates, from flight control signals and the dynamic force compensation output, a compensated pitch actuator control signal for each rotor blade wherein the compensation factor of the pitch control signal compensates for the dynamic force.