| 摘要 |
The invention relates to an electrical system (310) for an aircraft, comprising: a first main generator (314a) connected to at least one load via a first bus; a second main generator (314b) connected to at least one load via a second bus; a first and a second auxiliary generator (316a,316b) associated with the first and second buses, the auxiliary generators being driven by a common prime mover (326). |
