| 摘要 |
The rotor consists of several groups of blades fixed to a slanting carrier in parallel position with a certain distance between them like the wing of a bird diminishing the rotor diameter, and the effect of torque and the unsymmetry, giving greater stability, and enabling higher peripheral speed whereby the flow at the backward-turning blade does not cease. The carrier of each blade group is connected by flapping hinges to the outside ring of the hub relatively large in relation to blade length. By turning the blade group the angle of incidence of blades is changed. The blade groups are periodically and collectively controlled by y control device based on a hydraulic system which is installed along the rotor shaft. A control wheel allows radial turning of the whole control device making it possible to control the helicopter in longitudinal and lateral sense. Compensation of torque and of the unsymmetry of rotor during forward flight is brought about by a long and large-surface rotor airfoil with counterweight which is installed variably and with opposite direction of rotation on top of main rotor through a differential gear in the rotor head. This airfoil is stopped during forward flight by the flow of drive wind, so that the helicopter shows an unsymmetric airfoil giving a lift by which the unsymmetry of the stream of rotor is eliminated. Compensation of torque and of the unsymmetry of rotor works automatically without special control. The blade group rotor, blade control and torque compensation are a compact unit propelled by an engine which is installed in the fuselage before the pilot. |
