Effect of Piezoceramic Actuator Hysteresis on Helicopter Vibration and Noise Reduction

The objective of this studywas to assess the importance of actuator hysteresis on vibration and noise reduction in a rotorcraft equippedwith an actively controlledflap (ACF) system.Ahysteresismodel, based ona generalized formof the classical Preisach model, was developed using experimental data. The model displays good agreement with experimental data for inputs representative of those used for vibration and noise reduction in full-scale rotors. The hysteresis model has been incorporated into the AVINOR code to determine the effect of actuator hysteresis on vibration and noise reduction in both open and closed-loop modes of operation. It was found that the hysteresis level of a representative piezoceramic actuator does not produce a significant performance degradation of theACF system for vibration reduction under blade-vortex interaction (BVI) and dynamic stall conditions. For open-loop BVI noise control, the presence of hysteresis produces a significant effect on themaximumnoise reduction obtained using 2 per revolution (rev) and 5=rev harmonic inputs. For closed-loop BVI noise control, hysteresis introduces a substantial difference inflap deflection time histories; however, the overall noise reduction performance of theACF system is not affected because the controller compensates for actuator hysteresis.

[1]  Peretz Friedmann,et al.  A Comprehensive Survey of Individual Blade Control Emphasizing Recent Implementations , 2011 .

[2]  Kevin A. Snook,et al.  縦方向電界場中で曲げたPIN-PMN-PT単結晶の強度 , 2011 .

[3]  Bryan Glaz,et al.  The AVINOR Aeroelastic Simulation Code and its Application to Reduced Vibration Composite Rotor Blade Design , 2009 .

[4]  Hwan-Sik Yoon,et al.  A Hybrid Approach to Model Hysteretic Behavior of PZT Stack Actuators , 2009 .

[5]  Peter,et al.  Recent advances in Eurocopter's passive and active vibration control , 2008 .

[6]  Ranjan Ganguli,et al.  Dynamic hysteresis of piezoceramic stack actuators used in helicopter vibration control: experiments and simulations , 2007 .

[7]  Ranjan Ganguli,et al.  Effect of Piezoelectric Hysteresis on Helicopter Vibration Control Using Trailing-Edge Flaps , 2006 .

[8]  Philippe Leconte,et al.  Wind-tunnel tests of a helicopter rotor with active flaps , 2006 .

[9]  Dennis S. Bernstein,et al.  Higher-Harmonic-Control Algorithm for Helicopter Vibration Reduction Revisited , 2005 .

[10]  Inderjit Chopra,et al.  Closed-Loop Test of a Rotor with Individually Controlled Trailing-Edge Flaps for Vibration Reduction , 2005 .

[11]  Daniel G. Cole,et al.  High Performance ‘‘V-stack’’ Piezoelectric Actuator , 2004 .

[12]  Peretz P. Friedmann,et al.  Simultaneous Vibration and Noise Reduction in Rotorcraft Using Aeroelastic Simulation , 2004 .

[13]  Li Liu,et al.  Rotorcraft Vibration Reduction and Noise Prediction Using a Unified Aeroelastic Response Simulation , 2003 .

[14]  R. Ben Mrad,et al.  On the classical Preisach model for hysteresis in piezoceramic actuators , 2003 .

[15]  I. Mayergoyz.  Mathematical models of hysteresis and their applications , 2003 .

[16]  Peretz Friedmann,et al.  Reduction of Vibrations due to Dynamic Stall in Helicopters using an Actively Controlled Flap , 2002 .

[17]  Inderjit Chopra,et al.  Wind Tunnel Testing of a Smart Rotor Model with Trailing-Edge Flaps , 2002 .

[18]  Nagi G. Naganathan,et al.  Dynamic Preisach modelling of hysteresis for the piezoceramic actuator system , 2001 .

[19]  Peretz P. Friedmann,et al.  Application of a New Compressible Time Domain Aerodynamic Model to Vibration Reduction in Helicopters Using an Actively Controlled Flap , 2001 .

[20]  Inderjit Chopra,et al.  Status of Application of Smart Structures Technology to Rotorcraft Systems , 2000 .

[21]  Victor Giurgiutiu,et al.  Review of Smart-Materials Actuation Solutions for Aeroelastic and Vibration Control , 2000 .

[22]  Eric Frederick Prechtl,et al.  Design and implementation of a piezoelectric servo-flap actuation system for helicopter rotor individual blade control , 2000 .

[23]  Steven R. Hall,et al.  Preliminary testing of a Mach-scaled active rotor blade with a trailing-edge servo flap , 1999, Smart Structures.

[24]  Peretz P. Friedmann,et al.  Active Control Of BVI Induced Vibrations Using A Refined Aerodynamic Model And Experimental Correlation , 1999 .

[25]  Musa Jouaneh,et al.  Modeling hysteresis in piezoceramic actuators , 1995 .

[26]  Peretz P. Friedmann,et al.  Vibration reduction in rotorcraft using active control - A comparison of various approaches , 1995 .

[27]  Isaak D. Mayergoyz,et al.  Dynamic Preisach models of hysteresis , 1988 .