Patent ID: 6719244
Filing Date: 2004-04-13
Classification: B64C,B64D

Abstract:
A system for controlling the attitude of an aircraft about an axis in flight, said aircraft comprising two spinning lift or propulsion devices which are counter-rotating, and said system comprising means for tilting the spin axes of said devices such that components of their tilting can essentially be equally and simultaneously towards or away from one another and by an amount and rate dictated by the operator, and the tilting of said devices using said components, thereby generating unbalanced torque-induced and gyroscopic moments which act on the aircraft about an axis essentially perpendicular to the tilt axes of said components, said moments collectively being functions of said amount and rate of said tilting components, and said moments effecting control of the aircraft about said perpendicular axis, wherein while in horizontal and vertical flight substantially all attitude control about said perpendicular axis is by the tilting of the spin axes.