Dynamic buckling optimization of laminated aircraft conical shells with hybrid nanocomposite martial-Reference-Cited by-同舟云学术

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Dynamic buckling optimization of laminated aircraft conical shells with hybrid nanocomposite martial

Published:2020-03 Issue: Volume:98 Page:105656
ISSN:1270-9638
Container-title:Aerospace Science and Technology
language:en
Short-container-title:Aerospace Science and Technology

Author:

Kolahchi Reza,Zhu Shun-Peng,Keshtegar Behrooz,Trung Nguyen-Thoi

Funder

National Natural Science Foundation of China

Sichuan Provincial Key Research and Development Program

Nanjing University of Aeronautics and Astronautics

Ministry of Industry and Information Technology

Ton Duc Thang University

Duy Tan University

Publisher

Elsevier BV

Subject

Aerospace Engineering

Reference42 articles.

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2. Sandwich structured composites for aeronautics: methods of manufacturing affecting some mechanical properties;Krzyżak;Int. J. Aerosp. Eng.,2016

3. A general nonlinear global-local theory for bending and buckling analyses of imperfect cylindrical laminated and sandwich shells under thermomechanical loads;Shariyat;Meccanica,2012

4. A finite element model based on coupled refined high-order global-local theory for static analysis of electromechanical embedded shear-mode piezoelectric sandwich composite beams with various widths;Beheshti-Aval;Thin-Walled Struct.,2013

5. Active vibration control of a sandwich plate by non-collocated positive position feedback;Ferrari;J. Sound Vib.,2015

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