Abstract: A flow actuator module having a support device, a flow actuator mounted on the support device to be movable between a retracted position and a deployed position and which has an actuation portion and a flow plate rigidly connected to the actuation portion, an electrical coil arranged on the support device, and an armature on the actuation portion of the flow actuator and which has a magnetizable metal material. The flow actuator, in the retracted position, can be fixed in a positionally static manner relative to the support device by the armature by generation of an electrical current flow through the coil. A flow body system having a flow actuator module of the type, and an aircraft, are also disclosed.

Abstract: An aircraft includes an electromechanical actuator and a decoupling device. A form-fit between a drive element and a linkage point outside of the actuator element can be reversibly decoupled and recoupled. The decoupling device allows the actuator element to run freely in the event of a malfunction, which effectively prevents a jam.

Abstract: A reversible decoupling device is connected to an electromechanical actuator. The reversible decoupling device has an energy storage element configured to store the energy required for a decoupling in the decoupling device. The decoupling device can be re-coupled again after a completed test run so that the decoupling functionality can be easily tested.

Abstract: A pneumatic decoupling device for an electromechanical actuator, in particular, for flight applications includes a pressure accumulator housing for storing a compressed gas, which can be released to a decoupling mechanism of an electromechanical actuator for separating the drive components, so that in the event of a decoupling the electromechanical actuator runs totally freely.

Abstract: A high lift system for an aircraft, which extends and retracts the landing flaps of the aircraft in a fully electric manner. In this context, a fully electric drive is used, comprising an electric motor having an internal redundancy, in such a way that the electric motor is configured as a fault-tolerant electric motor. It may thus be possible to do without a coupling gear unit in the electric motor.

Abstract: A reversible decoupling device is connected to an electromechanical actuator. The reversible decoupling device has an energy storage element configured to store the energy required for a decoupling in the decoupling device. The decoupling device can be re-coupled again after a completed test run so that the decoupling functionality can be easily tested.

Abstract: An aircraft includes an electromechanical actuator and a decoupling device. A form-fit between a drive element and a linkage point outside of the actuator element can be reversibly decoupled and recoupled. The decoupling device allows the actuator element to run freely in the event of a malfunction, which effectively prevents a jam.

Abstract: A pneumatic decoupling device for an electromechanical actuator, in particular, for flight applications includes a pressure accumulator housing for storing a compressed gas, which can be released to a decoupling mechanism of an electromechanical actuator for separating the drive components, so that in the event of a decoupling the electromechanical actuator runs totally freely.

Abstract: A detection and control device is provided for detecting a motor fault of an electric motor with star point topology, with an evaluation unit, a control unit, and a return unit. The return unit is configured for returning a star point potential of the electric motor to the evaluation unit, the evaluation unit is configured for evaluating the star point potential and the control unit is designed for passivating a motor fault on the basis of the evaluation. The function of the return unit and of the evaluation unit may also be assumed by control lines and by the control unit.

Abstract: A high lift system for an aircraft, which extends and retracts the landing flaps of the aircraft in a fully electric manner. In this context, a fully electric drive is used, comprising an electric motor having an internal redundancy, in such a way that the electric motor is configured as a fault-tolerant electric motor. It may thus be possible to do without a coupling gear unit in the electric motor.

Abstract: A method and a device for fault detection in the load path of a spindle actuator which is provided for actuating a high-lift flap of an aircraft, wherein the spindle actuator has a redundant load path which is formed by a spindle and a secondary connection which are connected rotationally fixedly to one another on the driven side and are coupled to the surface to be actuated and which are assigned separate load paths on the drive side, whereof the primary load path contains a primary spindle which is driven by a motor and can be fixed in its rotational movement by a primary brake, and the secondary load path contains the secondary inner connection, which is arranged concentrically in the primary spindle, which can be fixed in its rotational movement by a secondary brake, in which output signals representing the turning position of the spindle are detected and evaluated.

Abstract: A detection and control device is provided for detecting a motor fault of an electric motor with star point topology, with an evaluation unit, a control unit, and a return unit. The return unit is configured for returning a star point potential of the electric motor to the evaluation unit, the evaluation unit is configured for evaluating the star point potential and the control unit is designed for passivating a motor fault on the basis of the evaluation. The function of the return unit and of the evaluation unit may also be assumed by control lines and by the control unit.

Abstract: A method and a device for fault detection in the load path of a spindle actuator which is provided for actuating an aerodynamically active surface, in particular a high-lift flap of an aircraft, wherein the spindle actuator has a redundant load path which is formed by a spindle and a secondary connection which are connected rotationally fixedly to one another on the driven side and are coupled to the surface to be actuated and which are assigned separate load paths on the drive side, whereof the primary load path contains a primary spindle which is driven by a motor and can be fixed in its rotational movement by a primary brake, and the secondary load path contains the secondary inner connection, which is in particular arranged concentrically in the primary spindle, which can be fixed in its rotational movement by a secondary brake, in which output signals representing the turning position of the spindle, which are generated by means of at least one turning position sensor which is coupled to the primary spin