Patent ID: 7789341

Claim:
A rotary wing aircraft comprising: a non-rotating structural backbone, a first rotor system coupled to the non-rotating structural backbone, the first rotor system including first rotor blades supported by a first rotor shaft for rotation about an axis of rotation, a first blade pitch controller coupled to the backbone, and a first motor fixed to the non-rotating structural backbone, a second rotor system coupled to the non-rotating structural backbone, the second rotor system including second rotor blades supported by a second rotor shaft for rotation about the axis of rotation, a second blade pitch controller coupled to the non-rotating structural backbone, and a second motor fixed to the non-rotating structural backbone, and wherein the first rotor shaft and second rotor shaft are positioned to lie in axially spaced apart relation to one another along the axis of rotation; wherein at least one of the first and second blade pitch controllers includes cyclic movement control of the rotor blades; and wherein the first rotor blades are positioned to lie in spaced-apart relation to the second rotor blades and the first and second motors are positioned to lie in spaced-apart relation to one another to locate the first and second rotor blades therebetween.