| 摘要 |
Supplemental power systems for aircraft are described. One example is a power conversion system (340) for an electrical power system in an aircraft having a first generator (336) and a second generator (338) is described. The power conversion system includes a first branch (402), a second branch (404), and a selector (424). The first branch has a first input, a first power converter, and a first output configured for coupling to an aircraft electrical distribution system. The second branch includes a second input, a second power converter, and a second output configured for coupling to the aircraft electrical distribution system. The selector is coupled between the first branch and the second branch. The selector is configured to selectively connect the first generator to the first branch or to the first and second branches. The selector is also configured to selectively connect the second generator to the second branch or the first and second branches. |
