Optimal design of fighter aircraft wing panels laminates under multi-load case environment by ply-drop and ply-migrations-Reference-Cited by-同舟云学术

Optimal design of fighter aircraft wing panels laminates under multi-load case environment by ply-drop and ply-migrations

Published:2019-01 Issue: Volume:207 Page:909-922
ISSN:0263-8223
Container-title:Composite Structures
language:en
Short-container-title:Composite Structures

Author:

Shrivastava Sachin,Mohite P.M.,Limaye M.D.

Publisher

Elsevier BV

Subject

Civil and Structural Engineering,Ceramics and Composites

Reference29 articles.

1. Design and optimization of a composite canard control surface of an advanced fighter aircraft under static loading;Shrivastava;Curved Layered Struct,2015

2. Robust design optimisation of advance hybrid (fiber metal) composite structures;Lee;Compos Struct,2013

3. Multi-objective robust optimisation of unidirectional carbon/glass fibre reinforced hybrid composites under flexural loading;Kalantari;Compos Struct,2016

4. Maximum stiffness and minimum weight optimization of laminated composite beams using continuous fiber angles;Blasques;Struct Multidisc Optim,2011

5. Multi-objective multi-laminate design and optimization of a carbon fibre composite wing torsion box using evolutionary algorithm;Shrivastava;Compos Struct,2018

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