Individual blade control system for rotorcraft

A blade pitch control system, comprising a plurality of serially stacked swashplate assemblies, one respective swashplate assembly for each of a corresponding plurality of blades of a rotor system and each respective swashplate assembly of the plurality of swashplate assemblies including concentric, ring-shaped non-rotating and rotating sections, an associated output pitch link coupled to its rotating section and an associated input pitch link coupled to its non-rotating section, the non-rotating and rotating sections of each respective swashplate assembly including pass through holes to accommodate respective input pitch links and output pitch links of adjacent ones of the stacked swashplate assemblies;

• and a plurality of actuators, each respective one of the plurality of actuators coupled to a respective input pitch link of a respective one of the stacked swashplate assemblies.