Higher Harmonic Control Simulation with Actuators Designed by the Physics-Based Approach

A higher harmonic control simulation along with actuators designed by the physics-based approach is attempted in this paper. The object rotorcraft used in the simulation is UH-60A Black Hawk and a multibody dynamics analysis program DYMORE is used for the simulation. The three actuators are located upon the non-rotating swashplate, and represented by the prismatic joints. Pitch angles of the rotor blades are adjusted by the combination of linear motion of the actuators. The rotor system is verified by the comparison against the references via the modal and trim analysis. The response of the fuselage is reflected regarding its entire hardware by the order reduction according to Herting's method. The fuselage is finally modeled as the beam element. A higher harmonic control with the transformation from the harmonic coefficients to the displacements of the servo actuators is to be simulated. By LQG based algorithm that is proposed by the authors, the vibration reduction capability of the present control algorithm will be verified.