Patent ID: 6062508
Filing Date: 2000-05-16
Classification: B64C

Abstract:
A lift rotor assembly for a compound aircraft having a fuselage, comprising:(a) at least one circular disk structure with a plurality of bladelets spaced peripherally thereabout;(b) a drive shaft coupled to a power source at a first end for rotating said drive shaft at low torque;(c) a hub coupled to each circular disk structure, wherein each said hub is located concentrically about said drive shaft;(d) a gear drive coupled to a second end of said drive shaft opposite said fist drive drive shaft end;(e) a first gear coupled to said gear drive and the hub for the circular disk structure located adjacent to said gear drive; and(f) a gear reduction apparatus associated with said gear drive and said first gear, wherein the low torque of said first drive shaft end is translated into high torque for the operation of said first gear and rotation of said adjacently located circular disk structure.