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Proceedings Paper

Design and static testing of a trailing-edge flap actuator with piezostacks for a rotor blade
Author(s): Taeoh Lee; Inderjit Chopra
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Paper Abstract

This paper presents the development of an actuator for a trailing edge flap on a full-scale helicopter rotor blade using a high performance piezoelectric stack device. The actuator was designed and constructed using two identical piezostacks that were selected among commercially available actuators through a systematic testing. To calculate the aerodynamic requirement of the flap actuator, an analytical model was formulated using quasi-steady aerodynamics. A new amplification device utilizing double-lever mechanism was designed and fabricated. An amplification factor of 19.4 and the constant response covering up to 8/rev were obtained experimentally under non-rotating condition. It was shown that the present flap actuator is capable of achieving the required flap deflection to actively control rotor vibration.

Paper Details

Date Published: 27 July 1998
PDF: 12 pages
Proc. SPIE 3329, Smart Structures and Materials 1998: Smart Structures and Integrated Systems, (27 July 1998); doi: 10.1117/12.316903
Show Author Affiliations
Taeoh Lee, Univ. of Maryland/College Park (United States)
Inderjit Chopra, Univ. of Maryland/College Park (United States)

Published in SPIE Proceedings Vol. 3329:
Smart Structures and Materials 1998: Smart Structures and Integrated Systems
Mark E. Regelbrugge, Editor(s)

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