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Proceedings Paper

Development of a piezoelectric actuator for trailing-edge flap control of rotor blades
Author(s): Friedrich K. Straub; Hieu T. Ngo; V. Anand; David B. Domzalski
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Paper Abstract

Piezoelectric actuator technology has now reached a level where macro-positioning applications in the context of smart structures can be considered. One application with high payoffs is vibration reduction, noise reduction, and performance improvements in helicopters. Integration of piezoelectric actuators in the rotor blade is attractive, since it attacks the problem at the source. The present paper covers the development of a piezoelectric actuator for trailing edge flap control on a 34-foot diameter helicopter main rotor. The design of an actuator using bi-axial stack columns, and its bench, shake, and spin testing are described. A series of enhancements lead to an improved version that, together with use of latest stack technology, meets the requirements. Next steps in this DARPA sponsored program are development of the actuator and full scale rotor system for wind tunnel testing in the NASA Ames 40 X 80 foot wind tunnel and flight testing on the MD Explorer.

Paper Details

Date Published: 9 June 1999
PDF: 12 pages
Proc. SPIE 3668, Smart Structures and Materials 1999: Smart Structures and Integrated Systems, (9 June 1999); doi: 10.1117/12.350692
Show Author Affiliations
Friedrich K. Straub, The Boeing Co. (United States)
Hieu T. Ngo, The Boeing Co. (United States)
V. Anand, The Boeing Co. (United States)
David B. Domzalski, The Boeing Co. (United States)

Published in SPIE Proceedings Vol. 3668:
Smart Structures and Materials 1999: Smart Structures and Integrated Systems
Norman M. Wereley, Editor(s)

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