Patent ID: 9555878
Date: 2017-01-31
CPC Classifications: B64C

Claim:
1. A rotor blade control device for a helicopter comprising a swash plate disk, the swash plate disk comprising: a non-rotating part of the swash plate disk; at least three actuators which are arranged around a rotor shaft axis of the helicopter, each of the at least three actuators connected to a stationary component in relation to the helicopter; and a coupling element between each of the at least three actuators and the non-rotating part of the swash plate disk, wherein each of the at least three actuators comprises a control shaft, which can be twisted around a control axis, and the coupling element is connected to the control shaft in a torque-proof way at a first crosspoint being located on the control axis, and to the non-rotating part of the swash plate disk at a second crosspoint in a flexible way, so that by means of a twisting of the control shaft the second crosspoint is moved at least alongside the non-rotating part of the swash plate disk via the coupling element, wherein the control shafts of each of the at least three actuators can be twisted at a certain adjustment angle respectively, independent of each other, according to a desired tilt or movement of the non-rotating part of swash plate disk, so that the second crosspoint at the non-rotating part of the swash plate disk takes a defined point in space, wherein the coupling element, which can be swiveled in all directions around the second crosspoint, is made up in a rigid way, and each of the at least three actuators is arranged onto the stationary component, being able to pivot around a respective swivel axis, and that the first crosspoint having a radial distance to the swivel axis, and wherein the control axis and the swivel axis are arranged in such a way toward each other, and a radial distance of the first crosspoint to the rotor shaft axis changes with the swivel movement of each of the at least three actuators around the swivel axis.