26 July 2004 Design and testing of a servotab-actuated trailing-edge flap for rotor vibration suppression
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Abstract
A servo-tab mechanism was designed for a full-scale rotor blade section, and tested in an open-jet wind tunnel. The intent was to use aerodynamic forces and moments to amplify the stroke and force provided by a compact piezoelectric bender actuator. The design was constrained by the stroke-force characteristics of the piezoceramic benders previously developed for model scale applications. The flap chord was chosen as 25% of the blade chord, and the tab chord was 5% of the blade chord. The flap response to the aerodynamic moment generated by the servotab was predicted using blade element momentum and thin airfoil theory. Testing in an open-jet wind tunnel explored the response of the flap in both steady and oscillating tab conditions.
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Jaye Falls, Inderjit Chopra, "Design and testing of a servotab-actuated trailing-edge flap for rotor vibration suppression", Proc. SPIE 5390, Smart Structures and Materials 2004: Smart Structures and Integrated Systems, (26 July 2004); doi: 10.1117/12.539989; https://doi.org/10.1117/12.539989
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KEYWORDS
Actuators

Aerodynamics

Aluminum

Foam

Dielectric polarization

Sensors

Servomechanisms

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