| 摘要 |
<p>The present invention relates to an aircraft (1) comprising a rotor blade (2) and turboshaft engines (11, 12, 13) for driving the rotor blade (2). The aircraft comprises two identical main engines (11, 12) and a second engine (13). Each main engine is able to be operated with at least one specific rating related to main power (maxTOP, OEIcont). The second engine (13) is able to be operated with at least one specific rating by transferring second power (maxTOP′, OEIcont′) which is proportional to the corresponding main power (maxTOP, OEIcont) when a proportional coefficient (k) of 0.5 or less is applied. The aircraft allows each main engine (11, 12) to be continuously operated during flight and includes a control system (20) for driving the rotor blade by using the second engine (13) as a supplement during at least one preset certain state of flight.</p> |
