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Proceedings Paper

Feasibility study to build a smart rotor: trailing edge flap actuation
Author(s): Dhananjay K. Samak; Inderjit Chopra
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Paper Abstract

This paper presents an experimental study on the development of a Froude scale helicopter rotor blade with trailing edge flap as a vibration reduction device actuated by piezoelectric crystals. A fixed wing model with NACA 0012 airfoil, 3.0 inch blade chord and 20% trailing edge flap is fabricated and tested in the open-jet tunnel to determine the dynamic flap response at various blade angles of attack and excitation frequencies. The results show that for a given velocity, flap response does not change appreciably with the excitation frequency and the blade angle of attack.

Paper Details

Date Published: 8 September 1993
PDF: 13 pages
Proc. SPIE 1917, Smart Structures and Materials 1993: Smart Structures and Intelligent Systems, (8 September 1993); doi: 10.1117/12.152762
Show Author Affiliations
Dhananjay K. Samak, Univ. of Maryland/College Park (United States)
Inderjit Chopra, Univ. of Maryland/College Park (United States)

Published in SPIE Proceedings Vol. 1917:
Smart Structures and Materials 1993: Smart Structures and Intelligent Systems
Nesbitt W. Hagood; Gareth J. Knowles, Editor(s)

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