<p>This paper introduces a unified rotor modeling approach integrated into the Helicopter Trim, Linearization, and Simulation flight dynamic model, previously developed by the authors, to handle diverse hinge types in rotorcraft configurations. By leveraging rigid-body kinematics, this method simplifies the representation of hinges, such as gimbals, see-saw, pre-cone, pre-sweep, droop, flap, lag, and pitch, enabling sequential breakdown of rotor dynamics into interconnected subsystems. This facilitates flexible modeling without extensive reconfiguration, addressing challenges in coaxial and tilt-rotor aircraft. The proposed approach is validated through trim analyses on two exemplar rotorcraft: the XH-59A coaxial helicopter and the XV-15 tilt-rotor. For the XH-59A, the effects of control phase angles and lift offset are examined, incorporating inflow interference and differential controls to optimize performance across forward speeds up to 300 knots, including scheduling for minimum power. For the XV-15, influences of flap deflection and pylon tilt angles are analyzed, considering control mixing between helicopter and airplane modes to ensure adequate force/moment generation and control margins during transition flight. Results demonstrate the model's efficacy in predicting scheduling strategies for enhanced efficiency and stability. Limitations, such as the omission of aeroelastic effects, are noted, with future work planned to incorporate these for broader applicability in urban air mobility and high-speed rotorcraft design.</p>