Patent ID: 7740207
Filing Date: 2010-06-22
Classification: B64C,Y10T

Abstract:
1. An aircraft flight control system comprising: a control rod which is moveable in longitudinal and rotational directions relative to a longitudinal axis of the control rod in response to pitch and roll command inputs, respectively, a torque tube assembly for connection to pitch control surfaces of the aircraft; and a rotatable bearing assembly for connection to aileron control surfaces of the aircraft, wherein the bearing assembly has an outer fixed position bearing member and a rotatable inner bearing member coaxially positioned with the outer bearing member, the inner bearing member being coupled operatively to the outer bearing member to allow for rotational movements of the inner bearing member relative to the longitudinal axis of the control rod, and wherein the control rod and the inner bearing assembly collectively define opposed races and include an axially aligned series of spherical bearings positioned within the opposed races to operatively spline-connect the control rod to the inner bearing assembly so as to allow for independent simultaneous longitudinal and rotational movements of the control rod relative to the longitudinal axis thereof such that longitudinal movements of the control rod are isolated from the bearing member but rotational movements of the control rod are transferred to the bearing member to cause rotation thereof and thereby allow operation of the aileron control surfaces, an articulated linkage operatively connecting the control rod to the torque tube assembly so that roll command inputs to the control rod are isolated from the torque tube assembly but pitch command inputs to the control rod are transferred by the articulated linkage to the torque tube assembly, wherein the articulated linkage comprises: