Blade sailing phenomenon modeling for feedback control

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.

[1]  Mayuresh J. Patil,et al.  Nonlinear Dynamics and Control of Integrally Actuated Helicopter Blades , 2005 .

[2]  Edward C. Smith,et al.  Analysis And Control Of The Transient Shipboard Engagement Behavior Of Rotor Systems , 1999 .

[3]  C. Fletcher.  Computational Galerkin Methods , 1983 .

[4]  David A. Peters,et al.  A State-Space Airloads Theory for Flexible Airfoils , 2006 .

[5]  Mohammad Riazi.  Control-centric Modelling and Nonlinear Control of the Blade Sailing Phenomenon , 2012 .

[6]  Edward C. Smith,et al.  Aeroelastic Analysis of Transient Blade Dynamics During Shipboard Engage/Disengage Operations , 1998 .

[7]  D. Peters,et al.  Finite state induced flow models. I - Two-dimensional thin airfoil , 1995 .

[8]  David A. Peters,et al.  Finite state induced flow models. II - Three-dimensional rotor disk , 1995 .

[9]  S Newman,et al.  The phenomenon of helicopter rotor blade sailing , 1999 .

[10]  Carlos E. S. Cesnik,et al.  Vibratory loads reduction testing of the NASA/Army/MIT active twist rotor , 2001 .

[11]  Simon Newman.  The safety of shipborne helicopter operation , 2004 .

[12]  S. J. Newman,et al.  The verification of a theoretical helicopter rotor blade sailing method by means of windtunnel testing , 1995, The Aeronautical Journal (1968).

[13]  Dewey H. Hodges,et al.  Nonlinear Composite Beam Theory , 2006 .

[14]  Dewey H. Hodges,et al.  Flight Dynamics of Highly Flexible Flying Wings , 2006 .

[15]  Dewey H. Hodges,et al.  Geometrically Exact, Intrinsic Theory for Dynamics of Curved and Twisted Anisotropic Beams , 2004 .

[16]  Alanna Wall,et al.  A discrete approach to modelling helicopter blade sailing , 2009 .

[17]  F. Khouli.  Modelling and attenuation feasibility of the aeroelastic response of active helicopter rotor systems during the engagement/disengagement phase of maritime operation , 2009 .

[18]  Andrade,et al.  Individual Blade Root Control of Helicopter Blade Sailing for Articulated Shipboard Rotors , 2009 .

[19]  Hao,et al.  Modeling and Simulation of Rotor Engagement and Disengagement During Shipboard Operations , 2004 .

[20]  Edward C. Smith,et al.  Validation and Application of a Transient Aeroelastic Analysis for Shipboard Engage/Disengage Operations. , 1996 .

[21]  Olivier A. Bauchau,et al.  Multibody Modeling of Engage and Disengage Operations of Helicopter Rotors , 2001 .

[22]  Jonathan Allen Keller,et al.  Analysis and Control of the Transient Aeroelastic Response of Rotors During Shipboard Engagement and Disengagement Operations , 2001 .

[23]  Olivier A. Bauchau,et al.  Modeling rotorcraft dynamics with finite element multibody procedures , 2001 .