In this paper, a reduced control-centric model of a particular behavior associated with maritime helicopter rotor systems, known as Blade Sailing Phenomenon (BSP), is developed. BSP is a transient aeroelastic phenomenon described by the large undesired flapping motion of the helicopter rotor blades during low rotor speeds. The developed model utilizes the Unified Airloads Model to capture the aerodynamic loads, the Intrinsic Nonlinear Beam Model to capture the structural behavior of the blade, and the Integrally Actuated Twist (IAT) for actuation. The governing partial-differential equations of motion together with the blade structural displacements as the output of interest are then discretized in the space domain using the Galerkin Spectral Discretization Method. The resultant nonlinear ordinary-differential equations are in the standard form of nonlinear systems that is highly desirable for designing a feedback controller to counter the BSP.

Additional Metadata
Persistent URL dx.doi.org/10.2514/6.2013-1715
Conference 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Citation
Riazi, M. (Mohammad), Afagh, F, & Langlois, R.G. (2013). Blade Sailing Phenomenon modeling for feedback control. In 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. doi:10.2514/6.2013-1715