Conceptual design and simulation validation based finite element optimisation for tubercle leading edge composite wing of an unmanned aerial vehicle-Reference-Cited by-同舟云学术

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Conceptual design and simulation validation based finite element optimisation for tubercle leading edge composite wing of an unmanned aerial vehicle

Published:2019-09 Issue:5 Volume:8 Page:4374-4386
ISSN:2238-7854
Container-title:Journal of Materials Research and Technology
language:en
Short-container-title:Journal of Materials Research and Technology

Author:

Basri Ernnie Illyani,Mustapha Faizal,Sultan Mohamed Thariq Hameed,Basri Adi Azriff,Abas Mohd Firdaus,Majid Mohd Shukry Abdul,Ahmad Kamarul Arifin

Publisher

Elsevier BV

Subject

Metals and Alloys,Surfaces, Coatings and Films,Biomaterials,Ceramics and Composites

Reference36 articles.

1. Finite element method: an overview;Mehta;IOSR J Dent Med Sci,2016

2. Finite element analysis of inter spar ribs of composite wing of light transport aircraft against Brazier load;James,2009

3. Active wing design with integrated flight control using piezoelectric macro fiber composites;Paradies;IOP Publ Smart Mater Struct,2009

4. Structural design of a UAV wing using finite element method;Mazhar,2010

5. Optimization of aircraft wing with composite material;Shabeer;Int J Innov Res Sci Eng Technol,2013

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