Patent ID: 6170779
Filing Date: 2001-01-09
Classification: B64C

Abstract:
A rotor/wing apparatus for a rotor/wing aircraft comprising:a rotor hub rotatable about an azimuthal axis;a first rotor blade attached to and extending radially outward from said rotor hub, said first rotor blade being pivotable about a first pitch axis extending substantially radially outward from said azimuthal axis;a second rotor blade attached to and extending radially outward from said rotor hub, said second rotor blade being pivotable about a second pitch axis extending substantially radially outward from said azimuthal axis;a first pitch link having a first upper end and a first lower end, said first upper end being attached to said first rotor blade eccentric of said first pitch axis, said first pitch link being moveable in a direction substantially parallel to said azimuthal axis to cause said first rotor blade to pivot about said first pivot axis;a second pitch link having a second upper end and a second lower end, said second upper end being attached to said second rotor blade eccentric of said second pitch axis, said second pitch link being moveable in a direction substantially parallel to said azimuthal axis to cause said second rotor blade to pivot about said second pitch axis; anda locking link having a proximal end, said proximal end including a link engaging surface, said locking link being moveable to a first position in which said link engaging surface engages one of said first and second lower ends to constrain said one of said first and second lower ends against movement parallel to said azimuthal axis, said locking link being further moveable to a second position in which said proximal end moves in a radial direction relative to said azimuthal axis to disengage said link engaging surface from said one of said first and second lower ends.