An analytical investigation was carried out for composite rotor blades with straight and swept tips to determine aeroelastic stability, response and loads in forward flight. Nonlinear equations were derived using Hamilton's principle. Composite blades with two-cell, soft-in-plane, hingeless configuration were analyzed. Results obtained from numerical calculations demonstrate the influence of composite ply orientation, tip sweep and anhedral on antrium, hub loads, blade response and stability.

C. Venkatesan

Department of Mechanical Engineering

IIT Jodhpur

Kuo-An Yuan

Peretz Friedmann P.

&ldquo;IIT Jodhpur is committed to impart quality education to facilitate the creation of qualified, competent and responsible human resources to meet the emerging technological challenges of the world. It is working towards creating an equitable learning platform that is positive, accessible and effective in the face of the modern societal and scientific advancements.

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Journal	Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Publisher	AIAA, New York, NY, United States
ISSN	02734508