Control for helicopter having dual rigid rotors

摘要

A control for a helicopter having dual, coaxial, counterrotating rigid rotors which varies the cyclic control phase angle of each rotor in flight as a function of vehicle forward speed to thereby control the coupling of lateral cyclic pitch with longitudinal cyclic pitch so as to introduce differential cyclic pitch inputs which automatically produce aerodynamic moments in each rotor to minimize maneuver generated gyroscopic precession moments, which also produce optimum lateral lift vector displacement for all flight speeds.