Thin-Plate Splines for Thick Composite Plate Analysis

Author(s):  
António J.M. Ferreira
2021 ◽  
Vol 8 (1) ◽  
pp. 1-12
Author(s):  
Ashok Magar ◽  
Achchhe Lal

Abstract This paper presents the solution of stress distribution around elliptical cutout in an infinite laminated composite plate. Analysis is done for in plane loading under hygrothermal environment. The formulation to obtain stresses around elliptical hole is based on Muskhelishvili’s complex variable method. The effect of fibre angle, type of in plane loading, volume fraction of fibre, change in temperature, fibre materials, stacking sequence and environmental conditions on stress distribution around elliptical hole is presented. The study revealed, these factors have significant effect on stress concentration in hygrothermal environment and stress concentration changes are significant with change in temperature.


2011 ◽  
Vol 52 ◽  
pp. 518 ◽  
Author(s):  
Bishnu P. Lamichhane ◽  
Stephen Roberts ◽  
Linda Stals

2014 ◽  
Vol 57 (8) ◽  
pp. 1532-1540 ◽  
Author(s):  
XingWu Zhang ◽  
XueFeng Chen ◽  
ZhiBo Yang ◽  
ZhongJie Shen

2014 ◽  
Vol 1 (S1) ◽  
Author(s):  
Lynn Frohwein ◽  
Verena Hoerr ◽  
Cornelius Faber ◽  
Klaus Schäfers

2013 ◽  
Vol 446-447 ◽  
pp. 597-601
Author(s):  
H. Haidzir ◽  
Dayang Laila Majid ◽  
A.S.M. Rafie ◽  
M.Y. Harmin

In any flutter prediction analysis, modal testing is necessary because flutter, a resonant like vibration occurs at a flutter frequency and adopts a mode shape akin to its structural natural modes. Modal testing can be performed computationally with knowledge of the mechanical properties of the structure. In the present work, computational modal analysis is first performed on a cantilevered hybrid composite thin plate and validated experimentally. Then, the computational procedure is demonstrated on a composite hollow wing model of same material. The concept of hollow wing is explored due to the superior mechanical properties of carbon/kevlar composite plate. It is observed that the natural frequencies of the hollow wing model are higher than thin plate due to stiffer configuration. A breathing mode was also observed at mode 4 for the hollow wing.


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