PITCH BIAS ACTUATOR SYSTEM FOR HELICOPTER LONGITUDINAL CYCLIC PITCH

摘要

A bias actuator, such as an extensible link (31), in the longitudinal cyclic pitch channel of a helicopter is provided with inputs as a function of airspeed multiplied inversely with collective pitch, and as a function of the rate of change of collective pitch stick (42) position, so as to enforce positive angle of attack and speed stability and positive static pitch trim gradient and to decouple collective pitch from the longitudinal cyclic pitch channel at cruise airspeeds, the invention, inter alia, adverse control effects of tail stabilizer surfaces at cruise speeds. A pair of indicators (53, 55) display bias commands and actual bias responses.