Patent ID: 6227481
Filing Date: 2001-05-08
Classification: B64C,Y10T

Abstract:
An improved tilt rotor aircraft comprising:(a) an airframe;(b) a pair of wing members coupled to said airframe;(c) a pair of cooperating tilt rotor assemblies carried by said pair of wing members operate in a plurality of modes of operation, including at least:(1) an airplane mode of flight with said pair of cooperating tilt rotor assemblies establishing a rotor disk position substantially transverse to said airframe;(2) a helicopter mode of flight with said pair of cooperating tilt rotor assemblies establishing a rotor disk position substantially parallel with said airframe;(3) a transition mode of flight with said pair of cooperating tilt rotor assemblies moving between said airplane mode of flight and said helicopter mode of flight;(d) a flexible and elongated rotating shaft extending between said pair of cooperating tilt rotor assemblies;(e) a plurality of assemblies for generating at least one signal indicative of an amount of twist on said flexible and elongated shaft;(f) a controller for receiving said at least one signal and generating command signals;(g) a plurality of actuators for receiving said command signals and for compensating for said twist in said flexible and elongated shaft.