Abstract: An aviation propulsion system for an aircraft with two engines, comprising respectively a connecting shaft which is rotatably drivable in rotation by one of the engines, wherein mutually facing ends of both connecting shafts are connected to each other or are connectable to each other in a rotatably drivable manner. Both connecting shafts are connected via their mutually facing ends in a rotatably drivable manner to one of the mutually facing ends of the connecting shafts via a openable coupling.

Abstract: A method for monitoring a gearbox in an aircraft. The gearbox comprises at least one gearbox section with at least one measuring area. A first and a second electrical contact are arranged in the measuring area at a spacing from one another. A magnetic field is generated in the gearbox section. The magnetic field is adapted to move at least one ferromagnetic particle arranged in the gearbox section towards the measuring area, so that a bridge produced from one or more of the ferromagnetic particles is formed between the two electrical contacts. A measured value is generated based on an electrical parameter between the two electrical contacts. A measure of the criticality of a flight operation is determined on the basis of the measured value.

Abstract: A torsional moment acting on a component in a drive train of an aircraft may be determined using at least one sensor, where the determined torsional moment is used for adjusting at least one adjustable damping element located in or on the component and/or for regulating a torsional stiffness in the torque-conducting component. As a result, the torsional load in the component may be reduced.

Abstract: The invention relates to a belt drive assembly for a drive train of a helicopter, comprising a drive shaft that can be functionally connected to a crankshaft of a drive machine of the helicopter, wherein the drive shaft is functionally connected to a belt disk via a torsional vibration damper, wherein the belt disk can rotate via a bearing mechanism on a bearing shaft connected to the drive shaft for conjoint rotation therewith, wherein the belt disk can receive a belt that is functionally connected to a rotor system of the helicopter.

Abstract: A torsional moment acting on a component in a drive train of an aircraft may be determined using at least one sensor, where the determined torsional moment is used for adjusting at least one adjustable damping element located in or on the component and/or for regulating a torsional stiffness in the torque-conducting component. As a result, the torsional load in the component may be reduced.

Abstract: The invention relates to a belt drive assembly for a drive train of a helicopter, comprising a drive shaft that can be functionally connected to a crankshaft of a drive machine of the helicopter, wherein the drive shaft is functionally connected to a belt disk via a torsional vibration damper, wherein the belt disk can rotate via a bearing mechanism on a bearing shaft connected to the drive shaft for conjoint rotation therewith, wherein the belt disk can receive a belt that is functionally connected to a rotor system of the helicopter.

Abstract: A gear transmission system (20) comprising at least a first cylindrical gear (21) and a second cylindrical gear (22). Each of the first and the second cylindrical gears (21, 22) comprise a plurality of teeth (23, 26). The teeth (23) of the first cylindrical gear (21) having a first tooth flank (24) for contacting a first tooth flank (27) of the teeth (26) of the second cylindrical gear (22) according to a predefined first contact line (30). The first tooth flanks (24, 27) of the teeth (23, 26) of each of the first and second cylindrical gears (21, 22) have a tooth shape and tooth properties determined by the predefined first contact line (30).

Abstract: A gear transmission system (20) comprising at least a first cylindrical gear (21) and a second cylindrical gear (22). Each of the first and the second cylindrical gears (21, 22) comprise a plurality of teeth (23, 26). The teeth (23) of the first cylindrical gear (21) having a first tooth flank (24) for contacting a first tooth flank (27) of the teeth (26) of the second cylindrical gear (22) according to a predefined first contact line (30). The first tooth flanks (24, 27) of the teeth (23, 26) of each of the first and second cylindrical gears (21, 22) have a tooth shape and tooth properties determined by the predefined first contact line (30).