| 摘要 |
<p>A rotor control system which includes a blade (10) fitted to a main rotor shaft (1) in such a fashion that the pitch angle is variable, a flap (20) fitted to the rear edge side of the blade (10) in such a fashion that the pitch angle is variable, a first link mechanism for controlling the pitch angle of the blade (10) and a second link mechanism for controlling the pitch angle of the flap (20). The first link mechanism includes a swash plate (14) comprising a rotation portion (12) connected to the blade (10) by a link mechanism and a control portion (13) undergoing displacement in accordance with the operation quantity. The second link mechanism includes a swash plate (31) comprising a rotation portion (29) connected to the flap (20) by a link mechanism and a control portion (30) undergoing displacement by actuators (36a and 26b), and a harmonic controller (37). According to this construction, a flap driving mechanism capable of exploiting effectively the flap performance can be accomplished, and the noise and vibration of a helicopter can be reduced.</p> |
