Abstract: A method for determining a state of a component in a high lift system of an aircraft comprises the steps of extending at least one high lift surface, which is coupled with two drive struts, wherein at least one of the two drive struts is a load sensing drive strut, to a first extended position, acquiring a first load sensed by a load sensing drive strut associated with the at least one high lift surface at a first flight state having a first speed, comparing the first load with a known nominal load for the first extended position and the first flight state under consideration of a predetermined threshold, and producing an alarm signal in case the acquired load differs from the nominal load including the predetermined threshold.

Abstract: A method for determining a state of a component in a high lift system of an aircraft is proposed, the high lift system comprising a central power control unit for providing rotational power by means of a transmission shaft; and drive stations coupled with the power control unit and movable high lift surfaces.

Abstract: A method for determining a state of a component in a high lift system of an aircraft comprises the steps of extending at least one high lift surface, which is coupled with two drive struts, wherein at least one of the two drive struts is a load sensing drive strut, to a first extended position, acquiring a first load sensed by a load sensing drive strut associated with the at least one high lift surface at a first flight state having a first speed, comparing the first load with a known nominal load for the first extended position and the first flight state under consideration of a predetermined threshold, and producing an alarm signal in case the acquired load differs from the nominal load including the predetermined threshold.

Abstract: A method for generating hydraulic power in an aircraft, the aircraft having a drive system comprising at least one transmission shaft connected to a power control unit, the power control unit having an electric motor and a hydraulic displacement machine connected to a differential gear unit for driving a common output shaft. The method includes switching the hydraulic displacement machine into a pump mode, arresting the output shaft, rotating the electric motor such that the hydraulic displacement machine is driven due to the arrested output shaft and supplying the fluid flow into a hydraulic system. A drive system of an aircraft may thereby be used for either moving control surfaces or for generating hydraulic power in an aircraft. This hydraulic power may be used to cover hydraulic load peaks during aircraft operation or to power hydraulic devices without the need of additional hydraulic power generation components.

Abstract: A method for determining a state of a component in a high lift system of an aircraft, the high lift system including a central power control unit for providing rotational power by a transmission shaft; and drive stations coupled with the power control unit and movable high lift surfaces, includes acquiring in an extended position in flight a first position of a first position pick-off unit coupled with the component, mechanically coupled with a high lift surface, and coupled with a drive station; acquiring in flight a second position of a second position pick-off unit arranged in or at the central power control unit in the extended position; determining a deviation between a first measure based on the first position and a second measure based on the second position; determining, whether the deviation exceeds a predetermined threshold; and if so, generating a signal indicating an abnormal state of the component.

Abstract: A method for determining a state of a component in a high lift system of an aircraft is proposed, the high lift system comprising a central power control unit for providing rotational power by means of a transmission shaft; and drive stations coupled with the power control unit and movable high lift surfaces.

Abstract: An arresting apparatus for arresting a rotational motion of two components relative to each other is provided. The arresting apparatus includes a first arresting means having a longitudinal axis and at least one first engaging element, and a second arresting means having an opening and at least one second engaging element. In a first mode of operation, the first arresting means extends through a first section of the opening of the second arresting means such that it is freely rotatable and the first engaging element and the second engaging element are distanced from each other. In a second mode of operation, the first arresting means is misaligned and extends through a second section of the opening of the second arresting means such that the first engaging element and the second engaging element engage and arrest the first arresting means relative to the second arresting means.

Abstract: A wing of an aircraft or spacecraft, the wing including at least a movable flow body, the wing including a movable support member, which is connected to the flow body, for rotating the flow body on the wing, the wing including a flow body control element, the flow body control element being fixed to the wing in a first point and the support member in a second point, the two points of the flow body control element and of the support member forming an axis, the flow body control element being formed at a predetermined angle to the axis and the flow body control element guiding the flow body in a predetermined plane about this axis.

Abstract: A method for generating hydraulic power in an aircraft, the aircraft having a drive system comprising at least one transmission shaft connected to a power control unit, the power control unit having an electric motor and a hydraulic displacement machine connected to a differential gear unit for driving a common output shaft. The method includes switching the hydraulic displacement machine into a pump mode, arresting the output shaft, rotating the electric motor such that the hydraulic displacement machine is driven due to the arrested output shaft and supplying the fluid flow into a hydraulic system. A drive system of an aircraft may thereby be used for either moving control surfaces or for generating hydraulic power in an aircraft. This hydraulic power may be used to cover hydraulic load peaks during aircraft operation or to power hydraulic devices without the need of additional hydraulic power generation components.

Abstract: A method for generating hydraulic power in an aircraft, the aircraft having a drive system comprising at least one transmission shaft connected to a power control unit, the power control unit having an electric motor and a hydraulic displacement machine connected to a differential gear unit for driving a common output shaft. The method includes switching the hydraulic displacement machine into a pump mode, arresting the output shaft, rotating the electric motor such that the hydraulic displacement machine is driven due to the arrested output shaft and supplying the fluid flow into a hydraulic system. A drive system of an aircraft may thereby be used for either moving control surfaces or for generating hydraulic power in an aircraft. This hydraulic power may be used to cover hydraulic load peaks during aircraft operation or to power hydraulic devices without the need of additional hydraulic power generation components.

Abstract: An arresting apparatus for arresting a rotational motion of two components relative to each other is provided. The arresting apparatus includes a first arresting means having a longitudinal axis and at least one first engaging element, and a second arresting means having an opening and at least one second engaging element. In a first mode of operation, the first arresting means extends through a first section of the opening of the second arresting means such that it is freely rotatable and the first engaging element and the second engaging element are distanced from each other. In a second mode of operation, the first arresting means is misaligned and extends through a second section of the opening of the second arresting means such that the first engaging element and the second engaging element engage and arrest the first arresting means relative to the second arresting means.

Abstract: A monitoring device is disclosed for an actuation system of an aircraft for monitoring a guiding device of a regulating flap with a load sensor. An actuation system with the monitoring device and a method for reconfiguring such an actuation system are disclosed. The monitoring device includes an interface to the load sensor and an interface to a driving device for adjusting the regulating flap. The monitoring device can determine or receive in-flight information actively signaling a predefined flight attitude and/or a predefined operational state of the aircraft. The monitoring device can compare a load value corresponding to a sensor value acquired by the load sensor and a limiting value corresponding to a minimum operational load for the predefined flight attitude and/or the predefined operational state of the aircraft and a monitoring function. The monitoring function can assign a fault mode to the regulating flap.

Abstract: A method for actuating at least one positioning flap on each wing of an aircraft, which positioning flap is actuated by at least two flap coupling devices each including a flap actuator device, where at least on one flap actuator device for each positioning flap a brake mechanism is arranged by means of whose actuation an adjustment state of the respective flap actuator device can be locked, including the steps of: actuating each brake mechanism of a positioning flap individually, subsequently actuating the flap actuator device by means of the drive motor, in the case of a change in the adjustment state of the positioning flap by a predetermined extent, terminating actuation of the positioning flap concerned, and a system for implementing the method.

Abstract: A monitoring device is disclosed for an actuation system of an aircraft for monitoring a guiding device of a regulating flap with a load sensor. An actuation system with the monitoring device and a method for reconfiguring such an actuation system are disclosed. The monitoring device includes an interface to the load sensor and an interface to a driving device for adjusting the regulating flap. The monitoring device can determine or receive in-flight information actively signaling a predefined flight attitude and/or a predefined operational state of the aircraft. The monitoring device can compare a load value corresponding to a sensor value acquired by the load sensor and a limiting value corresponding to a minimum operational load for the predefined flight attitude and/or the predefined operational state of the aircraft and a monitoring function. The monitoring function can assign a fault mode to the regulating flap.

Abstract: A method for generating hydraulic power in an aircraft, the aircraft having a drive system comprising at least one transmission shaft connected to a power control unit, the power control unit having an electric motor and a hydraulic displacement machine connected to a differential gear unit for driving a common output shaft. The method includes switching the hydraulic displacement machine into a pump mode, arresting the output shaft, rotating the electric motor such that the hydraulic displacement machine is driven due to the arrested output shaft and supplying the fluid flow into a hydraulic system. A drive system of an aircraft may thereby be used for either moving control surfaces or for generating hydraulic power in an aircraft. This hydraulic power may be used to cover hydraulic load peaks during aircraft operation or to power hydraulic devices without the need of additional hydraulic power generation components.

Abstract: A monitoring device is disclosed for an actuation system of an aircraft for monitoring a guiding device of a regulating flap with a load sensor. An actuation system with the monitoring device and a method for reconfiguring such an actuation system are disclosed. The monitoring device includes an interface to the load sensor and an interface to a driving device for adjusting the regulating flap. The monitoring device can determine or receive in-flight information actively signaling a predefined flight attitude and/or a predefined operational state of the aircraft. The monitoring device can compare a load value corresponding to a sensor value acquired by the load sensor and a limiting value corresponding to a minimum operational load for the predefined flight attitude and/or the predefined operational state of the aircraft and a monitoring function. The monitoring function can assign a fault mode to the regulating flap.

Abstract: An actuator having two or more interconnected movement components, wherein the movement components are designed as linear actuators with substantially coaxial longitudinal axes or longitudinal axes that are parallel to each other and that are interconnected in longitudinal direction such that their linear movements are superimposed on one another, and such that at least one of the linear actuators can be stopped at one or several predetermined positions.

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 wing of an aircraft or spacecraft, the wing including at least a movable flow body, the wing including a movable support member, which is connected to the flow body, for rotating the flow body on the wing, the wing including a flow body control element, the flow body control element being fixed to the wing in a first point and the support member in a second point, the two points of the flow body control element and of the support member forming an axis, the flow body control element being formed at a predetermined angle to the axis and the flow body control element guiding the flow body in a predetermined plane about this axis.

Abstract: A lift-augmenting leading edge flap for a carrying wing of an aircraft, wherein the flap comprises an essentially rigid main body which makes a transition from the first side to the second side of the wing the flap being adjustable by a retention- and actuation mechanism coupled between the flap and wing box, between a first, retracted, position and a second, extended, position, wherein the first transition region of the flap is slidable to rest in each position essentially free of any gap, against the first skin of the wing box or against the wing end cover, in relation to the wing end cover.