초록 ▼

This invention is concerned with helicopter rotor control systems which hitherto have tended to comprise complex assemblies which are costly to manufacture and maintain and which are vulnerable to external damage. A helicopter rotor is disclosed in which each of a plurality of radially extending rot

This invention is concerned with helicopter rotor control systems which hitherto have tended to comprise complex assemblies which are costly to manufacture and maintain and which are vulnerable to external damage. A helicopter rotor is disclosed in which each of a plurality of radially extending rotor blades is attached to the outer end of an individual spindle 19 having its inner end protruding into the interior of a hollow rotor hub structure 12 and supported by bearing means 21 arranged to permit rotational movement of the spindle 19 about its axis. A pitch control lever 22 is attached to the inner end of each spindle 19 and is articulated, through a universal joint, to the upper end of an individual connecting rod 38, 39, 40 and 41, the lower ends of the connecting rods being attached to a common housing 42 having independently rotatable means for connection to helicopter flying controls.

대표청구항 ▼

A helicopter rotor including a hollow rotor hub arranged for rotation about an axis and a plurality of rotor blades extending radially of said axis, means attaching each blade to the outer end of an individual spindle, each said individual spindle having its inner end protruding into the interior of

A helicopter rotor including a hollow rotor hub arranged for rotation about an axis and a plurality of rotor blades extending radially of said axis, means attaching each blade to the outer end of an individual spindle, each said individual spindle having its inner end protruding into the interior of the hollow rotor hub and supported by bearing means within the hub arranged to permit rotational movement of the spindle about its axis to change the pitch of its associated blade, a respective pitch control lever coupled to the inner end of each said spindle, a plurality of connecting rods each articulated at its upper end, through a universal joint, to a respective one of said pitch control levers, the lower end of the connecting rods being attached to a common housing having independently rotatable means for connection to helicopter flying controls, one of said connecting rods being fixedly attached to said common housing, and the remaining connecting rods being attached to said common housing through universal joints.