The utility model discloses a lightweight
permanent magnet synchronous motor for an
electric aircraft. An electromagnetic structure in the motor comprises a
stator iron core, an armature winding, a permanent
magnet, a rotor
magnet yoke and a rotor bracket, the
stator iron core is of an annular columnar structure,
stator grooves penetrating through the axial direction are evenly formed in the end face of the stator iron core in the circumferential direction, and armature windings are arranged in the stator grooves. A rotor
magnet yoke is arranged to be of an annular thin-wall structure, a plurality of pole permanent magnets which are sequentially connected are evenly pasted to the outer ring wall face of the rotor magnet yoke in the circumferential direction, and an excitation
assembly of an annular columnar structure is formed by the pole permanent magnets. The rotor magnet yoke and the permanent magnets of each pole adhered to the outer side wall of the rotor magnet yoke are mounted on the inner side of the stator iron core through the rotor bracket, and the permanent magnets of each pole and the inner side wall of the stator iron core form an annular thin-wall gap, so that the rotor magnet yoke, the permanent magnets of each pole and the rotor bracket rotate relative to the stator iron core; the permanent magnet of each pole is of a segmented structure and is divided into four segments which are arranged in a
central symmetry mode, and the four segments comprise the two
samarium cobalt permanent magnets located in the middle and the two
neodymium iron
boron permanent magnets located on the two sides. According to the technical scheme of the utility model, the problem that as most of the existing
aviation permanent magnet synchronous motors adopt high-speed and high-electromagnetic-load design, the temperature rise of the motors is too high, and the stable operation of the motors is greatly threatened is solved.