Control system for rotary wing vehicle

摘要: A control system for a helicopter rotor has dual pitch changing mechanisms, one such mechanism the inboard ends of blades, and second servo flap an outboard station each blade. Conventional cyclic collective controls are provided in vehicle, mechanisms operate unison at moderate forward speeds, but function differentially higher speeds to cyclically twist blades according predetermined airspeed schedule so that advancing retreating twisted reduce increase, respectively, built-in negative torsionally resilient blades.