Induced-shear piezoelectric actuators for rotor blade trailing edge flaps and active tips

Louis R. Centolanza, Edward C. Smith, Anthony Morris

Research output: Contribution to conferencePaper

6 Scopus citations

Abstract

One of the most promising active control solutions being investigated to solve the rotorcraft vibration problem is an active trailing edge flap and/or active blade tip. In the present work, induced-shear piezoelectric tube actuators are used in conjunction with simple lever/cusp hinge amplification devices to generate useful combinations of trailing edge flap and blade tip deflections and hinge moments. A finite element model of the actuator tube and trailing edge flap (including aerodynamic and inertial loading) was used to guide the design of the actuator/flap system. Both a Mach scale induced shear tube actuator flap system and a Mach scale induced shear blade tip system were fabricated. Experimental bench top testing was conducted to validate the analysis. In experimental testing at an applied electric field of 4 kV/cm of a Mach scale induced shear tube actuator, a 1.5 inch long flap was deflected +/- 12° in a no-load condition and +/- 8.5° for a hinge moment simulating a rotor speed of 2000 RPM. The percent error between the predicted and experimental flap deflections ranged from 2% (low RPM) to 8% (large RPM). In addition, a 10% radius blade tip (3.6 inches) was deflected +/-3.15° and +/- 2.50° for hinge moments that simulated the 0 and 2000 RPM rotor speed conditions.

Original languageEnglish (US)
DOIs
StatePublished - Jan 1 2001
Event19th AIAA Applied Aerodynamics Conference 2001 - Anaheim, CA, United States
Duration: Jun 11 2001Jun 14 2001

Other

Other19th AIAA Applied Aerodynamics Conference 2001
CountryUnited States
CityAnaheim, CA
Period6/11/016/14/01

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Mechanical Engineering

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