| 摘要 |
The present invention provides a rotor assembly for helicopter vehicles for providing an easy way of controlling pitch, roll and lift of the aircraft by respective servo actuators. The rotor assembly has a rotor shaft and at least two rotor blades coupled to a rotor head which in turn is connected to the rotor shaft. The rotor assembly further comprises a non-rotating swash plate through which centre the rotor shaft runs, being adjusted to tilt around its entire radial axis. A respective pitch hinge for each rotor blade connecting said respective rotor blade to the rotor head is provided, wherein a hinge axis which the pitch hinge rotates around is generally parallel to and is positioned in front of the longitudinal centre axis of the respective rotor blade in the rotational direction. A respective guide member for each rotor blade is connected to an inner blade tip. The inner blade tip is positioned in front of the hinge axis in the rotational direction, and the guide member is adjusted to follow an upper surface of the non-rotating swash plate when the rotor assembly rotates. One or more forces, e.g. a magnetic and/or an aerodynamic force, are applied on the rotor blades being sufficiently strong to create a valve effect on the pitch hinge pressing the guide members downwards against the non-rotating swash plate, whereby movements of the non-rotating swash plate are transferred to blade pitch movements of the rotor blades. |
