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UID:8@aero.iisc.ac.in
DTSTART:20240313T140000Z
DTEND:20240313T150000Z
DTSTAMP:20240322T042526Z
URL:https://aero.iisc.ac.in/events/test-event/
SUMMARY:Thesis Colloquium
DESCRIPTION:\n\n\n\n\n\n\nAsymptotic Modelling of Carbon Nanotube (CNT) and
  CNT-reinforced composite structures using strain gradient formulations\n&
 nbsp\;\n\n\nResearch Supervisor: Dineshkumar Harursampath\n\nThesis Abstra
 ct\n\nCarbon nanotubes (CNTs) have garnered attention for their remarkable
  mechanical\, thermal\, and electrical properties\, making them valuable i
 n various applications. CNTs are particularly advantageous in aerospace st
 ructures as reinforcements in polymer matrix composites\, enhancing struct
 ural strength while reducing weight. Furthermore\, they offer the potentia
 l for multifunctionality\, integrating structural\, thermal\, and electric
 al functionalities within components like wings. However\, accurately mode
 lling CNT behaviour poses challenges\, especially considering their applic
 ation in larger-scale aerospace structures. While accurate\, molecular dyn
 amics and molecular structural mechanics are computationally intensive and
  limited in length scale. In this context\, the present research proposes 
 reduced-order continuum structural models using the Variational Asymptotic
  Method (VAM) to study CNT and its composite structures while incorporatin
 g length scale effects using strain-gradient formulations.\n\nUsing VAM\, 
 single-walled CNTs (SWCNTs) were first analysed by considering them as str
 aight\, hollow\, circular tubes in a local continuum framework. This tube 
 model accounts for the geometrically nonlinear behaviour of standalone CNT
  when subjected to bending and buckling loads. Cross-sectional ovalisation
  leading to nonlinear bending and buckling behaviour has been studied. Com
 bined loading cases of bending and compression and torsion and compression
  and bending and torsion have been examined. The study aims to provide ins
 ights into the 3-D nonlinear deformation behaviour of SWCNTs\, offering a 
 more efficient approach for evaluating CNTs in aerospace composite applica
 tions.\n\nIn the next step\, recognising the significance of the structure
 's small size (such as used in MEMS\, NEMS\, and sensors)\, the non-classi
 cal theories\, such as the Modified Strain Gradient Theory\, which account
  for the size effect in the material\, have been employed to develop a pio
 neering beam and plate models tailored for CNT-reinforced composite struct
 ures. Emphasising the critical nature of size effects\, characterised by l
 ength scale parameters\, this study delves into the nuances of the length 
 scale effects in nanoscale structures. To develop the asymptotically-corre
 ct strain-gradient beam model\, a prismatic beam with a rectangular cross 
 section has been considered to derive zeroth-order and subsequent higher-o
 rder models while capturing the strain-gradient effects. Notably\, this wo
 rk is the first application of non-classical theories in developing VAM-ba
 sed beam models. Different orders for length scale parameters have been co
 nsidered\, and the validity of each choice is scrutinised\, followed by gu
 idance on the appropriate choice of the length scale parameters.\n\nFollow
 ing the development of the strain-gradient beam model\, a modified strain 
 gradient theory-based plate model has also been developed using VAM\, whic
 h is again a first-of-its-kind work in the context of VAM and reduced-orde
 r structural models. Using the variational methods\, fourth-order ordinary
  differential equations were obtained for the non-classical case\, and sim
 ilarly\, an additional set of boundary conditions (non-classical) were als
 o derived. The warping solutions and the plate stiffnesses are obtained by
  solving these governing differential equations and boundary conditions. I
 t was noted that the material length scale parameters appear only in the b
 ending and twist stiffness terms. Further\, the classical results can be d
 erived by setting the material length scale parameters as zero. Zeroth- an
 d first-order approximations have been derived\, followed by detailed vali
 dation of the results with literature for bending and buckling load cases.
  Parametric studies involving variations in thickness and plate width have
  been conducted to assess their influence on mechanical behaviour. The dev
 eloped plate model is then applied to CNT-reinforced composites\, and thei
 r bending and buckling studies have been carried out. The parametric studi
 es have also considered evaluating all influencing parameters like CNT vol
 ume fraction\, material length scale parameter\, plate thickness and width
 .\n\nFull Meeting Link: https://teams.microsoft.com/l/meetup-join/19%3ame
 eting_ZWY1NmM0MGItODQ5ZS00ZmE4LTk5YjMtYWMyMGQ3ZGE1ODlh%40thread.v2/0?conte
 xt=%7b%22Tid%22%3a%226f15cd97-f6a7-41e3-b2c5-ad4193976476%22%2c%22Oid%22%3
 a%22eb59112f-967f-4f24-8739-385858c5592e%22%7d\n\n\n\nVenue: STC Seminar H
 all\, 1st Floor\, Dept of Aerospace Engineering\n\n\n\n\n\n\n
CATEGORIES:Thesis Colloquium
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