Blade Design for Reduced Helicopter Vibration-Reference-Cited by-同舟云学术

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Blade Design for Reduced Helicopter Vibration

Published:1983-07-01 Issue:3 Volume:28 Page:33-41
ISSN:2161-6027
Container-title:Journal of the American Helicopter Society
language:en
Short-container-title:j am helicopter soc

Author:

Blackwell R. H.¹

Affiliation:

1. Aircraft Development, Sikorsky Aircraft Division, United Technologies Corporation, Stratford, Conn.

Publisher

American Helicopter Society

Cited by 21 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Tendon-inerter-damper helicopter blade augmentation for improved dynamic performance;Journal of Sound and Vibration;2023-03

2. Experimental modal analysis of a rotating tendon-loaded helicopter blade demonstrator;Mechanical Systems and Signal Processing;2022-10

3. Effects of blade configuration parameters on helicopter rotor structural dynamics and whirl tower loads;The Aeronautical Journal;2016-02

4. Design optimization of slender elastic beam with initial twist using genetic algorithms and finite element analysis;Journal of Mechanical Science and Technology;2014-05

5. A Study of Elastic Coupling to the Wind Turbine Blade by Combined Analytical and Finite Element Beam Model;Journal of Composite Materials;2010-05-19

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