An aircraft flight control system advantageously is provided with a control rod which is spline-connected to a bearing assembly so as to permit simultaneous independent longitudinal and rotational movements of the control rod while isolating such movements from one another (e.g., so as to allow operative interconnection to an aircraft's aileron and elevator control surfaces). Thus, the control rod 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. The control rod is splined operatively to the bearing assembly so as to allow for independent simultaneous longitudinal and rotational movements of the control rod relative to the longitudinal axis thereof to thereby allow the command inputs to be transferred to the aircraft's respective flight control surfaces.

 
Web www.patentalert.com

< Auxiliary wing and flap assembly for an aircraft

< Translating active Gurney flap to alleviate aircraft wake vortex hazard

> Fastener

> Hybrid fiberglass composite structures and methods of forming the same

~ 00616