Abstract: An improved transmission for transferring torque. First and second gears are each configured for integral, rigid attachment to first and second torque-bearing bodies, respectively. A third gears is disposed in simultaneous meshing engagement with the first and second gears such that said first and second gears are disposed in substantial co-axial orientation. The gears are configured such that rotation of a first of the three gears relative to a second of the three gears causes rotation of the remaining third gear via the various meshing engagements to thereby accomplish a transfer of torque from the first gear to the third gear.

Abstract: A helicopter including a driven rotor assembly provided with a hub having oscillatable rotor blades extending outwardly therefrom and axially spaced portions of the hub having outer peripheral portions of a pair of annular flexible and elastic supporting diaphragms anchored relative thereto. Inner peripheral portions of the diaphragms are deflected and stretched toward each other and anchored to a supporting flange carried by a central rotary drive shaft of the rotor assembly. A sleeve is longitudinally shiftably mounted on the shaft below the rotor assembly and supports, through the utilization of a flexible and resilient diaphragm, a larger sleeve structure therefrom for universal angular displacement of the sleeve structure relative to the sleeve. The sleeve structure includes control arms operatively connected to the rotor blades for oscillation of the latter in response to axial shifting of the sleeve structure relative to the sleeve.

Abstract: A helicopter having a small diameter and fast rotating upper horizontally disposed conventional airplane propeller and a large diameter slower and counter-rotating large diameter bladed rotor equipped with variable pitch blades is provided and the bladed rotor is mounted in such a manner that its plane of rotation may be readily adjustably canted in all directions relative to the axis of rotation of the small diameter upper airplane-type propeller. Further, the blades of the rotor may be simultaneously adjusted in pitch and a single manually shiftable control is provided for selectively simultaneously or independently canting the plane of rotation of the rotor blades and varying the pitch of the rotor blades.