This paper presents the design, dynamical model, and experimental investigation of an articulated rotor that affords cyclic pitch authority in small unmanned air vehicle rotorcraft without requiring either a mechanical swashplate or blade pitch actuators. An offset flap hinge coincident with a skew lag-pitch hinge is used to impose a positive lag-pitch coupling on one rotor blade and a complementary negative lag-pitch coupling on the other. The motor torque driving the propeller is electronically modulated to excite a lead-lag motion with controlled rotational phase and amplitude; the ensuing once-per-revolution variation in blade pitch obtains the conventional control response and flapping character of fully actuated cyclic systems. The governing nondimensional lag-flap equations including a nonconstant speed hub are shown. The experimentally measured motor torque, the hub speed variation, the cyclic blade lag-pitch response, and the cyclic blade flapping response are compared with model predictions.