| 摘要 |
FIELD: engines and pumps.SUBSTANCE: invention relates to aircraft applications, in particular to electric systems of aircrafts. The aircraft engine contains the stator, the main shaft, the transmission gear, the first and second electric devices, supported the first and second rotors respectively, the control unit, the first and second armature windings, supported by the first and second rotors respectively. The transmission gear converts the rotation of the main shaft into the rotation of the first and second rotors in different directions. The control unit induces DC current in the first excitation winding. The first and second armature windings are connected to the first and second electric devices. The first excitation winding is located between the first armature winding and the second armature winding in one position of the main shaft.EFFECT: decrease of mass-dimensional parameters of devices, supported by the aircraft engine rotor is achieved.7 cl, 7 dwg |
