| 摘要 |
According to the present invention, the vertical take-off, forward and backward movement, rotation, and the turning left and right of an aircraft are adjusted by changing the rotation speeds of blades 2, 17, 23, 24 and the angle between an engine and the ground. Complicated total torque adjusting and cyclic variable pitch devices of a helicopter are removed by replacing the same with a newly invented total torque adjusting device; because the blade cannot be rotated by 360 degrees with a conventional total torque adjusting device. Since the waving of the blade is not required, a seesaw and a fully hinged structure for advancing and lagging are not required. |
