| 发明名称 |
Aerofoil for an aircraft, and an aircraft |
| 摘要 |
An aerofoil for an aircraft includes an engine, a first lift body, and a second lift body which is arranged behind the first lift body in the direction of flow of the aerofoil. The second lift body is pivotable relative to the first lift body between a cruising flight position in which both lift bodies together define an elongate and substantially continuous cross section of the aerofoil in the direction of flow, and a take-off/landing position in which the second lift body is angled downwards relative to the first lift body in order to increase a lift of the aerofoil. |
| 申请公布号 |
US2016311522(A1) |
申请公布日期 |
2016.10.27 |
| 申请号 |
US201615135624 |
申请日期 |
2016.04.22 |
| 申请人 |
Lilium GmbH |
发明人 |
Wiegand Daniel |
| 分类号 |
B64C9/20;B64C29/00;B64C9/34;B64D27/26 |
主分类号 |
B64C9/20 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. An aerofoil for an aircraft, comprising a first lift body, a second lift body which is arranged behind the first lift body in a direction of flow of the aerofoil, the second lift body being pivotable relative to the first lift body between a cruising flight position in which both lift bodies together define an elongate and substantially continuous cross section of the aerofoil in the direction of flow, and a take-off/landing position in which the second lift body is angled downwards relative to the first lift body in order to increase a lift of the aerofoil, and an engine is arranged on the second lift body. |
| 地址 |
Gilching DE |
