| 摘要 |
The method involves determining a collective instruction pitch and a longitudinal cyclic instruction pitch such that an aircraft (1) i.e. hybrid helicopter, converges towards an optimized operation of a main rotor (3) at the time of a stabilized flight phase. A vertical behavior constant such as vertical speed, is preserved. A bearing pressure of one of a set of half-wings (11, 11') of the aircraft is adjusted so that a collective pitch of the blades of the main rotor is equal to the collective instruction pitch. An independent claim is also included for a control device. |
