The drone according to the embodiment has a propeller, a first direct current motor, a power source, a second direct current motor, and a control unit. The first direct current motor drives the propellers. The power source supplies power to the first direct current motor. The second direct current motor has a rotating shaft that rotates in conjunction with the rotation of a rotating shaft of the first direct current motor. The control unit controls the first direct current motor. The second direct current motor charges the power source using the current output from the second direct current motor along with the rotation of a rotating shaft of the second direct current motor.

The drone according to the embodiment has a propeller, a first direct current motor, a power source, a second direct current motor, and a control unit. The first direct current motor drives the propellers. The power source supplies power to the first direct current motor. The second direct current motor has a rotating shaft that rotates in conjunction with the rotation of a rotating shaft of the first direct current motor. The control unit controls the first direct current motor. The second direct current motor charges the power source using the current output from the second direct current motor along with the rotation of a rotating shaft of the second direct current motor.

A brake disk defines an annular shape having a radially inner side and a radially outer side. The brake disk includes: a radially outer braking surface, the braking surface having a maximum operating temperature; a fusible material section radially inward from and connected to the braking surface. The fusible material has a maximum operating temperature, the fusible material section suitable for transmitting torque between the braking surface and a shaft. The maximum operating temperature of the braking surface is higher than the maximum operating temperature of the fusible material section. When the temperature of the fusible material section raises above the maximum operating temperature of the fusible material section, the fusible material section is configured to no longer transmit torque between the braking surface and the shaft.

A turboelectric distributed propulsion based on brushless doubly-fed machines (BDFMs) is provided, which minimizes power conversion, enhances mechanical reliability, and strengthens fault-tolerance capability of a DC-based propulsion system. A turboelectric distributed propulsion (TeDP) architecture using BDFMs for aviation applications, and a designed BDFM, inverter, and controller are provided. Simulations and systems are also provided.

A turboelectric distributed propulsion based on brushless doubly-fed machines (BDFMs) is provided, which minimizes power conversion, enhances mechanical reliability, and strengthens fault-tolerance capability of a DC-based propulsion system. A turboelectric distributed propulsion (TeDP) architecture using BDFMs for aviation applications, and a designed BDFM, inverter, and controller are provided. Simulations and systems are also provided.

The present disclosure relates to a winding for an electrical machine. The winding comprises at least one flat conductor having at least one turn to form the winding, and the at least one flat conductor comprises a substantially L-shaped, U-shaped or V-shaped cross-section. The present disclosure also relates to an electrical machine that includes the winding and an aircraft that includes the electrical machine.

The present disclosure relates to a winding for an electrical machine. The winding comprises at least one flat conductor having at least one turn to form the winding, and the at least one flat conductor comprises a substantially L-shaped, U-shaped or V-shaped cross-section. The present disclosure also relates to an electrical machine that includes the winding and an aircraft that includes the electrical machine.

Aircraft comprising a primary propeller driven in rotation by a motor, the motor having a first assembly and a second assembly movable in rotation relative to each other along an axis of rotation, the primary propeller being secured in rotation to one of said first assembly and second assembly, the first assembly and the second assembly being movable in translation relative to each other along a direction of translation defined by the axis of rotation, between a rest position and a service position, characterized in that said aircraft comprises a locking system, comprising a housing and an indexing element, the housing being formed in one among the first assembly and the second assembly, the indexing element being secured to the other among the first assembly and the second assembly, the locking system having an engaged configuration in which the indexing element is at least partially inserted into the housing.

Systems, methods, and apparatuses for an aerial vehicle (AV). The AV can include a frame structure comprising an upper frame, a lower frame, and bridges connecting the upper frame and the lower frame. The upper frame can include a housing for electrical components. The AV can include a duct extending from the upper frame to the lower frame. The AV can include a motor to rotate the propeller. The AV can include guides located between the bridges and the duct. A portion of the guides can include a non-linear path. The AV can include actuators. The AV can include flaps, coupled to the guides and the actuators, configured to protrude from the lower frame or retract into the frame structure. The flaps can curve along at least one of a horizontal axis or a vertical axis of the flaps. The flaps can overlap with each other when protruded.

Systems, methods, and apparatuses for an aerial vehicle (AV). The AV can include a frame structure comprising an upper frame, a lower frame, and bridges connecting the upper frame and the lower frame. The upper frame can include a housing for electrical components. The AV can include a duct extending from the upper frame to the lower frame. The AV can include a motor to rotate the propeller. The AV can include guides located between the bridges and the duct. A portion of the guides can include a non-linear path. The AV can include actuators. The AV can include flaps, coupled to the guides and the actuators, configured to protrude from the lower frame or retract into the frame structure. The flaps can curve along at least one of a horizontal axis or a vertical axis of the flaps. The flaps can overlap with each other when protruded.