Design and experimental testing of an induced-shear piezoelectric actuator for rotor blade trailing edge flaps

Louis R. Centolanza, Edward Smith

Research output: Contribution to journalConference article

9 Scopus citations

Abstract

A new actuator design for helicopter trailing edge flaps is presented. The new actuator incorporates an induced-shear piezoelectric tube as the driving element. The tube actuator is used in conjunction with a hinge amplification mechanism to generate a useful combination of flap deflection and hinge moment. A finite element model of the actuator tube and trailing edge flap is used to compare the performance of the new tube actuator to bender and stack piezoelectric actuators. Experimental bench top testing of a full scale tube actuator flap system was conducted to validate the analysis. Hinge moments that corresponded to various rotor speeds were applied to the actuator using mechanical springs. The analytical modeling revealed that the tube actuator produced 6° of flap motion at 2000 RPM for Mach scaled blades. For a full scale blade design, the tube actuator can deflect a 12 inch flap 2.5°, at a rotation speed of 400 RPM for an electric field of 4 kV/cm. The experimental testing found that for an applied electric field of 3 kV/cm, the tube actuator deflected a representative full scale 12 inch flap 2.8 degrees at 0 RPM and 1.4 degrees for a hinge moment simulating a 400 RPM condition. The percent error between the predicted and experimental flap deflections ranged from 4% (low RPM) to 12.5% (large RPM).

All Science Journal Classification (ASJC) codes

  • Architecture
  • Materials Science(all)
  • Aerospace Engineering
  • Mechanics of Materials
  • Mechanical Engineering

Fingerprint Dive into the research topics of 'Design and experimental testing of an induced-shear piezoelectric actuator for rotor blade trailing edge flaps'. Together they form a unique fingerprint.

  • Cite this