| 摘要 |
An electrical network for an aircraft. The aircraft includes at least one variable pitch propulsor 50. The electrical network includes a wound field synchronous AC electrical generator 56 having a wound rotor (128, fig. 4) driven by an internal combustion engine, such as a gas turbine engine (10, fig 2). The network further includes a voltage regulator 102 configured to regulate output voltage of the electrical generator 56 by regulating rotor winding magnetic field strength, and a synchronous AC drive motor 106 coupled to a respective variable pitch propulsor 50 and provided with power from the output of the electrical generator 56. The aircraft may comprise two gas turbine engines each coupled to a plurality of propellers 50. |
