Abstract: A galvanically isolated DC/DC converter includes a first and a second side converter circuit coupled between a pair of first side DC terminals and a pair of second side DC terminals, respectively. The first side converter circuit has a first and a second switching element, each including a switch and a diode. When the DC/DC converter is in power transfer operation from the second side DC terminals to the first side DC terminals, the second side converter circuit alternates between two power transfer states. A conductive state of the diode of one of the first and second switching elements is the result of one of the two power transfer states. The first side converter circuit is controlled such that the switch of the respectively other of the first and second switching elements is closed for an adaptation interval before the one of the two power transfer states starts.

Abstract: A drive unit (16) for an aircraft running gear (2) having at least a first wheel (4) and a second wheel (6) on a common wheel axis (A) is characterized in that the drive unit (16) is drivingly coupleable to the first and second wheels (4, 6) such that a direction of longitudinal extension (C) of the drive unit (16) is in a plane orthogonal to the common wheel axis (A).

Abstract: A drive unit for an aircraft ground wheel associated with a brake unit for braking the ground wheel includes: a driving motor drivingly coupleable to the ground wheel; and a cooling system including at least a drive cooling unit configured to generate a drive cooling air stream for cooling the drive unit and a brake cooling unit configured to generate a brake cooling air stream by sucking in air from the brake unit. A method of controlling such drive unit in which the cooling system is driven by the driving motor of the drive unit includes: decoupling the driving motor from the ground wheel and increasing the rotational speed of the driving motor to increase the amount of generated drive cooling air, when an operating condition of the ground wheel and/or of the drive unit is switched from a propulsion mode to a non-propulsion mode.

Abstract: The invention relates to a method of producing a rotor (10) of an electric machine, the rotor (10) comprising a rotor body (14) adapted to be rotated about a rotor axis (A) as well as at least one rotor component (16) to be mounted to the rotor body (14), said method comprising the steps of: arranging the rotor component (16) on the rotor body (14) and winding a wire-like structure (20) around an outer circumference (12) of the rotor body having the rotor component (16) arranged thereon so as to form a bandage (18), with the wire-like structure (20) during winding thereof being held under an adjustable bias.

Abstract: A galvanically isolated DC/DC converter includes a first and a second side converter circuit coupled between a pair of first side DC terminals and a pair of second side DC terminals, respectively. The first side converter circuit has a first and a second switching element, each including a switch and a diode. When the DC/DC converter is in power transfer operation from the second side DC terminals to the first side DC terminals, the second side converter circuit alternates between two power transfer states. A conductive state of the diode of one of the first and second switching elements is the result of one of the two power transfer states. The first side converter circuit is controlled such that the switch of the respectively other of the first and second switching elements is closed for an adaptation interval before the one of the two power transfer states starts.

Abstract: A DC/AC converter includes a DC/DC conversion stage with galvanic isolation and a DC/AC conversion stage, wherein the DC/DC conversion stage comprises a pair of first side terminals providing or receiving a first DC voltage, a pair of second side terminals providing or receiving a second DC voltage and coupled to the DC/AC conversion stage, at least one first side converter circuit coupled between the pair of first side terminals, a series connection of a plurality of second side converter circuits coupled between the pair of second side terminals, and at least one transformer circuit coupling the plurality of second side converter circuits to the at least one first side converter circuit, wherein a connection point between two of the plurality of second side converter circuits is coupled to the DC/AC conversion stage and forms a neutral phase point thereof.

Abstract: A drive unit (16) for an aircraft running gear (2) having at least a first wheel (4) and a second wheel (6) on a common wheel axis (A), wherein the drive unit (16) is drivingly coupleable to at least one of the first and second wheels (4, 6), is characterized in that the drive unit (16) comprises at least one power output assembly (122, 124) for driving at least one of the first and second wheels (4, 6), with each of the at least one power output assembly (122, 124) comprising a power transmission chain (136) selectively engageable with a sprocket element (108, 110) coupled to one of the first and second wheels (4, 6).

Abstract: A galvanically isolated DC/DC converter includes at least one first side converter circuit coupled between a pair of first side DC terminals, and at least one second side converter circuit coupled between a pair of second side DC terminals. The second side converter circuit has at least a first and a second switching element, each including a switch and a diode connected in parallel. When the DC/DC converter is in power transfer operation from the pair of first side DC terminals to the pair of second side DC terminals, the diodes of the first and second switching elements are alternately in a conductive state, with each of the first and second switching elements being controlled such that a closed state of the respective switch extends beyond a transitioning of the diode of the same switching element from the conductive state to a blocking state.

Abstract: A drive system (DS) for a land craft comprises a machine system (M1, M2) for driving the land craft, the machine system comprising at least a first and a second electric machine (M1, M2) acting on a common drive shaft (S) for driving the land craft, and a control device (PE, PE1, PE2) which is adapted to control the machine system for operating in at least two rotating speed operation ranges (OR1, OR2) with different rotating speeds of the drive shaft (S). The first electric machine (Ml) is controlled to operate in both rotating speed operation ranges (OR1, OR2) to provide a first drive torque, and the second electric machine (M2) is controlled to operate in only one of the rotating speed operation ranges (OR1) to provide a second drive torque in addition to the first drive torque.

Abstract: A method of controlling an electric synchronous machine having a stator and a moving part includes operating the machine with a deceleration moment so that a speed of the moving part of the machine is reducing, monitoring the movement of the moving part of the machine, and, upon detection of a direction reversal or a speed of the moving part of approximately zero, transitioning to a holding mode by impressing at least one current pattern of string currents in the stator of the machine. The method also includes maintaining the current pattern until a stable equilibrium of moments between the external moment and a braking moment of the machine is established.

Abstract: A drive unit (16) for an aircraft running gear (2) having at least a first wheel (4) and a second wheel (6) on a common wheel axis (A) is characterized in that the drive unit (16) is drivingly coupleable to the first and second wheels (4, 6) such that a direction of longitudinal extension (C) of the drive unit (16) is in a plane orthogonal to the common wheel axis (A).

Abstract: A method of controlling an electric synchronous machine (2) having a stator and a moving part comprises the following steps: operating the machine (2) with a deceleration moment (MP) so that a moving part speed of the machine is reduced, monitoring the moving part movement of the machine, and upon detection of a direction reversal or a speed (v) of the moving part of approximately zero, a transition to a holding mode is effected, adjusting at least one electric supply variable (I; iu, iv, iw) of an electric stator system of the machine such that, at the beginning of the holding mode, an effective internal moment (MB) of the machine is formed that is reduced with respect to the deceleration moment (MP). The electric supply variable (I; iu, iv, iw) is adjusted in this manner until, with movement of the moving part and influence of an external moment (MA) acting on the machine, a stable equilibrium of moments between external moment (MA) and internal moment (MB) of the machine is established.