Abstract: A transverse flux electrical machine for coupling to a rotating shaft of a propulsor of an aircraft is provided. The transverse flux electrical machine includes a rotor having a plurality of circumferentially distributed permanent magnets that form a number, NP, of rotor poles, wherein the rotor poles have a pole pitch angle, P?, equal to 2? divided by the number of rotor poles, NP. The transverse flux electrical machine further includes a stator having a plurality of current-carrying coils configured to interact with the rotor poles of the rotor to produce a torque. The transverse flux electrical machine further includes an air gap separating the rotor from the stator by an air gap distance, GAir, wherein a machine parameter, , defined as: =P?×GAir is less than 100 micro radian-meters.

Abstract: An electrical machine for integration into a vehicle frame structure is provided. The vehicle frame structure includes a structural wall that at least partially encloses an inner volume. The electrical machine includes a rotor with a rotor shaft. The rotor shaft is rotatable around a rotational axis, and is connectable to a propulsor for transferring torque to or from a fluid. The electrical machine includes a first bearing unit configured to hold the rotor shaft in a rotatable manner and a second bearing unit configured to hold the rotor shaft in a rotatable manner. The first bearing unit is releasably attachable to a first wall region of the structural wall, and the second bearing unit is releasably attachable to a second wall region of the structural wall. The first wall region and the second wall region are spaced apart with respect to the rotational axis.

Abstract: The invention relates to a synchronous machine which is excited by permanent magnets and has a stator (2) and a rotor (1) which rotates adjacent to the stator (2) about a longitudinal axis (3). The rotor (1) comprises a number of surface magnets which are disposed along the circumference of the rotor (1). The surface magnets are designed as Halbach arrays (4), each of which comprises tangential segments (PM1, PM4, PM5, PM8), in which the magnetisation direction (M) is oriented predominantly in the circumferential direction, and normal segments (PM2, PM3, PM6, PM7), in which the magnetisation direction (M) is oriented predominantly in the radial direction or counter to the radial direction, and in the field of the stator (2) the tangential segments (PM1, PM14, PM5, PM8) are subjected to a radially inwardly directed force (?Fn) and the normal segments (PM2, PM3, PM6, PM7) are subjected to a radially outwardly directed force (+Fn).

Abstract: A transverse flux electrical machine for coupling to a rotating shaft of a propulsor of an aircraft is provided. The transverse flux electrical machine includes a rotor having a plurality of circumferentially distributed permanent magnets that form a number, NP, of rotor poles, wherein the rotor poles have a pole pitch angle, P?, equal to 2? divided by the number of rotor poles, NP. The transverse flux electrical machine further includes a stator having a plurality of current-carrying coils configured to interact with the rotor poles of the rotor to produce a torque. The transverse flux electrical machine further includes an air gap separating the rotor from the stator by an air gap distance, GAir, wherein a machine parameter, ?, defined as: ?=P?×GAir is less than 100 micro radian-meters.

Abstract: An electrical machine for an aircraft electrical power system includes a stator having current-carrying coils and flux guiding stator iron defining one or more stator slots that house the current-carrying coils. The electrical machine further includes a rotor having a plurality of permanent magnets configured to interact with the stator to produce a torque. The electrical machine has an active parts mass, mact, which is a cumulated mass of components of the electrical machine that contribute to producing the torque. The electrical machine is configured to produce a peak rated torque, ?peak. The electrical machine has a slot current density, Jslot,peak, when producing the peak rated torque, ?peak. A value of a machine parameter, ?, defined as: ?=?peak/(mact×Jslot,peak) is greater than or equal to 5 ?Nm3 kg?1A?1.

Abstract: A vertical take-off and landing (VTOL) aircraft includes at least one electrical propulsion unit (EPU). An EPU of the at least one EPU includes a propeller or a fan and a transverse flux electric motor. The electric motor includes a stator having coils configured to carry current and a rotor arranged to interact with the stator, such that a torque for driving rotation of the propeller or the fan is generated. The rotor is configured to supply a flow of air to the coils, such that heat is removed from the coils. The coils are directly exposed to the flow of air, such that heat is exchanged directly from the coils to the flow of air. Each coil includes an effective cooling surface area directly exposed to the flow of air. An effective cooling surface area is at least 20% of a total surface area of the respective coil.

Abstract: A vertical take-off and landing (VTOL) aircraft includes at least one electrical propulsion unit (EPU). An EPU of the at least one EPU includes a propeller or a fan and a transverse flux electric motor. The electric motor includes a stator having coils configured to carry current and a rotor arranged to interact with the stator, such that a torque for driving rotation of the propeller or the fan is generated. The rotor is configured to supply a flow of air to the coils, such that heat is removed from the coils. The coils are directly exposed to the flow of air, such that heat is exchanged directly from the coils to the flow of air. Each coil includes an effective cooling surface area directly exposed to the flow of air. An effective cooling surface area is at least 20% of a total surface area of the respective coil.

Abstract: An air guidance device for a vertical take-off and landing aircraft is provided. A nacelle device with a drive device is connected via a pylon device to a wing of the vertical take-off and landing aircraft and is pivotable by a pivoting device, about an axis of rotation between a first position, such as a propulsion position, and a second position, such as a lift position, relative to the pylon device. A first inlet opening of the air guidance device is arranged on the pylon device in a region in which air conveyed by the drive device in the second position impinges on the pylon device and/or in a region of maximum propeller-generated pressure.

Abstract: A transverse flux electric motor includes a stator including coils configured to carry current and a rotor arranged to interact with the stator. The rotor is configured to produce a torque for driving rotation of the rotor. The transverse flux electric motor has an active parts mass, mact, equal to a cumulated mass of components of the transverse flux electric motor that contribute to the production of the torque. The transverse flux electric motor has an active parts torque density, ?act, defined as a peak rated torque, ?peak, divided by the active parts mass, mact. The transverse flux electric motor has a power factor equal to cos(?), wherein ? is a steady-state phase difference between a stator coil current and a stator coil voltage, and wherein the transverse flux electric motor has a machine parameter ? that is greater than or equal to 65 Nmkg?1, where ? equals ?act/cos(?).

Abstract: A vertical take-off and landing (VTOL) aircraft is provided. The VTOL aircraft includes at least one electrical propulsion unit (EPU), wherein an EPU of the at least one EPU includes a propeller or a fan. The EPU further includes an electric motor including a stator having insulated coils for carrying current and a rotor arranged to interact with the stator, such that a torque for driving rotation of the propeller or the fan is produced.

Abstract: An electric machine includes at least one stator having at least one individual-tooth winding carrier that has at least one spacer configured to space apart turns of an individual-tooth winding mounted on the individual-tooth winding carrier. A hybrid electric aircraft has an electric machine of this kind.

Abstract: An electrical power system for an aircraft includes a DC:AC power electronics converter and a transverse flux electrical machine. The transverse flux electrical machine includes a rotor that is coupleable to a rotating shaft of a propulsor of the aircraft, wherein the rotor includes a plurality of permanent magnets defining a number, NP, of evenly distributed rotor poles. The transverse flux electrical machine further includes a stator arranged to interact with the rotor, such that a torque is produced. The stator includes a plurality of coils.

Abstract: An electrical propulsion unit (EPU) for a vertical take-off and landing (VTOL) aircraft is provided. The EPU includes a propeller or a fan and an electric motor. The electric motor includes a stator comprising coils configured to carry current and a rotor arranged to interact with the stator. The rotor is configured to generate a torque for driving rotation of the propeller or the fan. The coils of the stator have a cumulated conductor volume Vconductor The stator, the rotor, or the stator and the rotor include a flux guiding iron material configured to guide magnetic flux generated by the coils of the stator, wherein the flux guiding iron material has a cumulated iron volume Viron, and wherein the electric motor has a machine parameter ? that is greater than or equal to 0.25, ? being defined as: ?=Vconductor/Viron.

Abstract: A stator pole for a stator of a transverse flux machine is provided. The stator includes a stator winding arranged in a winding space, and the winding space being formed circumferentially in a circumferential direction in relation to an axis of rotation of a rotor. The stator pole has a body element made of a ferromagnetic material, which has at least one pole head which, in the installation position, may be arranged opposite the one rotor, and a magnetic return path region, which may be arranged facing away from the one rotor, wherein a number of the pole heads of the stator pole correspond to a number of the rotors. The stator pole is configured to occupy only a portion of a circumference of the winding space in the circumferential direction, and the magnetic return path region has a curved shape which adjoins the at least one pole head, as a result of which the magnetic return path region is designed to define the winding space in part transversely to the circumferential direction.

Abstract: The invention relates to an electric machine with a protection against inter-turn short circuits, comprising a rotor with one or more permanent magnets and a stator which comprises a plurality of stator poles that are concentrically arranged about the rotor and a plurality of grooves that space the stator poles apart in the circumferential direction, wherein a yoke is arranged in each groove, said yoke forming a bridge-like connection between the stator poles in the circumferential direction, and at least one yoke winding is arranged on each yoke, said yoke winding forming an electric coil. The coil axis direction corresponds to the circumferential direction, and each pair of adjacent yoke windings surrounds a stator pole.

Abstract: An electric machine includes at least one stator having at least one individual-tooth winding carrier that has at least one spacer configured to space apart turns of an individual-tooth winding mounted on the individual-tooth winding carrier. A hybrid electric aircraft has an electric machine of this kind.

Abstract: A stator pole for a stator of a transverse flux machine is provided. The stator includes a stator winding arranged in a winding space, and the winding space being formed circumferentially in a circumferential direction in relation to an axis of rotation of a rotor. The stator pole has a body element made of a ferromagnetic material, which has at least one pole head which, in the installation position, may be arranged opposite the one rotor, and a magnetic return path region, which may be arranged facing away from the one rotor, wherein a number of the pole heads of the stator pole correspond to a number of the rotors. The stator pole is configured to occupy only a portion of a circumference of the winding space in the circumferential direction, and the magnetic return path region has a curved shape which adjoins the at least one pole head, as a result of which the magnetic return path region is designed to define the winding space in part transversely to the circumferential direction.

Abstract: A stator pole for a stator of a transverse flux machine is provided. The stator includes a stator winding arranged in a winding space, and the winding space being formed circumferentially in a circumferential direction in relation to an axis of rotation of a rotor. The stator pole has a body element made of a ferromagnetic material, which has at least one pole head which, in the installation position, may be arranged opposite the one rotor, and a magnetic return path region, which may be arranged facing away from the one rotor, wherein a number of the pole heads of the stator pole correspond to a number of the rotors. The stator pole is configured to occupy only a portion of a circumference of the winding space in the circumferential direction, and the magnetic return path region has a curved shape which adjoins the at least one pole head, as a result of which the magnetic return path region is designed to define the winding space in part transversely to the circumferential direction.

Abstract: An electric machine includes at least one stator having at least one individual-tooth winding carrier that has at least one spacer configured to space apart turns of an individual-tooth winding mounted on the individual-tooth winding carrier. A hybrid electric aircraft has an electric machine of this kind.

Abstract: A stator pole for a stator of a transverse flux machine is provided. The stator includes a stator winding arranged in a winding space, and the winding space being formed circumferentially in a circumferential direction in relation to an axis of rotation of a rotor. The stator pole has a body element made of a ferromagnetic material, which has at least one pole head which, in the installation position, may be arranged opposite the one rotor, and a magnetic return path region, which may be arranged facing away from the one rotor, wherein a number of the pole heads of the stator pole correspond to a number of the rotors. The stator pole is configured to occupy only a portion of a circumference of the winding space in the circumferential direction, and the magnetic return path region has a curved shape which adjoins the at least one pole head, as a result of which the magnetic return path region is designed to define the winding space in part transversely to the circumferential direction.