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Quickfire Presentations Bristol Composites Institute / NCC Joint Conference 21 st November 2019

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Page 1: QF full slide pack...LEUH )DLOXUH)LEUH .LQNLQJ0DWUL[ &UDFNLQJ 1XPHULFDO &KDUDFWHULVDWLRQ 8QLW &HOO 0RGHO U Q U ê Ý Ý Ù Ý 4 ê 4 r)DLOXUH 0RGHV'DPDJH /DZ ) Ø Ù Ù L ( : # Ù

Quickfire PresentationsBristol Composites Institute / NCC Joint Conference

21st November 2019

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Objective Hygro-thermal models Validation Application

• Hydrothermal dependant strength

𝜎 𝑇,𝑀 , 𝑡 = 𝑓(𝑇, 𝑇 𝑇⁄ , �̇�)

• Interface energy

• Similarly, moduli and in-plane shear models have been developed

• To numerically predict the effect of temperature and moisture on the mechanical degradation of composites

• To develop hygrothermal-dependant bulk matrix and interface property models

SBS- unidirectional [0]34

Transverse Tension [90]11 Cut-ply[(+45/90/-45/0)4 (0)]s

90/-45 interface

90/-45 interface

Room Temperature DRY

Room Temperature WET

Numerical modelling of the hygro-thermal effects of temperature and moisture on compositesGanapathi Ammasai Sengodan

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Fibre KinkingFibre Failure Matrix Cracking

Numerical Characterisation Unit Cell ModelEla

stic

Ten

sor

Est

imati

on

Dam

ag

e B

eh

avio

ur

𝜎

𝜀𝜀𝜀

𝜎

0

Damage LawFailure Modes

𝐺 = 𝐹(𝐴 )

Material ModelVoxelisationKinematic model

Initial cracks on the matrix pockets

damage

Transverse matrix cracks and shear induced damage

Strain [%]

yxShear angle, 𝜃

A numerical study of the effect of draping on the mechanical properties of 3D woven compositesIoannis Topalidis

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Micro-scale Analysis of CMCs

Micro-scale Analysis of CMCsRiccardo Manno

• Tool for the creation of CMCs microstructures and homogenisation of the physical properties:

Elastic

Thermal

Electrical

• User-Subroutines for interphase pull/push out behaviour and for matrix cracking:

Experiments Performed by R.M.G. De MeyereUniversity of Oxford

Push-out behaviourCohesive + Friction lawPush-out behaviourCohesive + Friction law

Damage InitiationChristensen Criterion

Damage ProgressionSmeared Crack Formulation

Damage ProgressionSmeared Crack Formulation

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Surrogate Modelling of Camber-Morphing Rotor Blades

Surrogate Modelling of Camber-Morphing Rotor BladesStephane Fournier

DISCRETE CONTROL SURFACE CAMBER-MORPHING AEROFOIL

FishBAC concept

max ΔCL > 1 max ΔCM > 0.2

Mach 0.6

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Skin Sample preparation & Materials Speckle pattern for Digital Image Correlation

Analytical model for granular jamming beamsDavid Brigido

Full-field of transversal strains

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WrapToR truss beams

SAMPE “Design and Make” 2019@EPSRC Future CompositesManufacturing Research Hub open day.With Dr Yian Zhao and Chris Hunt.

Christopher J.Hunt et al. 2019

3 points bending test

WrapToR truss beamsFrancescogiuseppe Morabito

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WrapToR truss beamsFrancescogiuseppe Morabito

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Pseudo-ductility in compression of thin-ply angle-ply laminatesXun Wu

Key challenge: to investigate gradual compressive failure of pseudo-ductile thin-ply angle-ply [±θn/0m]s laminates, via an indirect loading approaches.

Carbon fibre composites - stiff, strong, lightweight, but fail catastrophically, especially in compression

Metal CFRP

Compressive test method: premature failure, underestimated strength and large variability

Compressive non-linearity of angle-ply Fibre fragmentation of 0° plies Pseudo-ductility in compression

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1.Main Features of Tensegrity

1) Truss-like structure

2) Prestressed, self-equilibrated

3) Discontinuous compressive members

4) Continuous tensile members

Tensegrity Art Form

Tensegrity Super Ball Bot from

NASA

2.Tensegrity Form-Finding

Equilibrated Configuration

Topology of Tensegrity Tower

Form-Finding

Method

Case 1: Finite Tensegrity Tower

3.Tensegrity/Origami Structure Case 2: Infinite Tensegrity Tower

Topology of Infinite Tensegrity Tower

Origami Dual of Infinite Tensegrity Tower

Section of Infinite Tensegrity Tower

DualityDisplay

Self-equilibrated infinite tensegrity tessellations with a developable Origami dual.

Extract

Topology

Results

Tessellations for Tensegrity/Origami MetamaterialsKeyao Song

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Predicting Trans-laminar Fracture Using VCCT and In-situ CT ScansXiaoyang Sun

X. Sun, S. Takeda, M.R. Wisnom, X. Xu

In-situ CT scan & Virtual Crack Closure Technique (VCCT) are used to predict the failure propagation of the large stiffened panel.

(a) 0°

(c) -45°

(b) 90°

(d) 45°

7%accuracy vsexperiment

Predicting LARGE panels using small coupons is difficult, due to size effect.

R-curveDamage zone stateIn-situ CT scan

1 mm

25 mm

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Collaborative layup

“Best of both worlds”:

• Strength + Reliability of robot• Skill and dexterity of a human

Tactile sensing

• Real time detection of defects• Detecting ‘type’ of defects

Tactile sensing/collaborative layupMichael Elkington

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Project Summary

• Imperial College London are pursuing the incorporation of porous aerogels to boost the storage functions of composite laminates to create structural supercapacitors.

• Aerogels are stiff and brittle which presents a challenge for manufacturing of complex components.

• This project is investigating the formability and manufacturability of composites when divided into structural power and purely structural areas.

Forming simulationIdentify areas of high shear as a the ply is formed over the shape.

Segmenting multi- functional and structural areasAreas of high shear deformation and out of plane curvature are designated as purely structural. Areas of low deformation and curvature are designated for energy storage.

Manufacturing Composites with Structural and Energy Storage FunctionsMark Turk

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A Digital Image Correlation (DIC) technique for measuring Chemical Cure Shrinkage (CCS) evolutionJames McArdle

Results• Smallest spacing (largest

confinement) corresponded to highest measured strain (A>C>B>D)

• Peak strains concentrated at edges of confinements

Str

ain

A

CBD

Gelation window

Degree of cure (D.O.C)

Project Challenge• Measure process induced

strain as resin transitions from liquid polymer to glassy solid

A

0.5 mm

1.0 mm1.0 mm

B

CD

Experimental arrays

1.5 mm

DIC strain map

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Material variability

Process variability

Laminate Thickness

Requirements

MaterialVariability

ProcessVariability

Predicted Cured Ply Thickness

Tight dimensional tolerances

Laminate Thickness ControlKate Gongadze

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A. Burrows et al., Separ. Purif. Technol., 212 (2019), pp. 545-554.

Photoresponsive metal-organic framework composites for gas trappingHarina Amer Hamzah

Materials for sustainable energy applications

Photoresponsive metal-organic framework composites

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Thermo-responsive gas trapping in PW@TE7 composite

Maximum pressure up to 200 bar Temperature range 77-773 K High pressure CO2 and H2

Thermo-responsive gas trapping in paraffin wax coated activated carbon compositesPrasanth K Prabhakaran

100 µm

TE7 AC PW@TE7

100 µm

Paraffin wax (PW)

MeasurementsPreparation

Mechanism

I II III IV

Molten PW >55 ᵒC permeable to gases

Solid PW at 25 ᵒC physical barrier to gases

Solid PW at 25 ᵒC under vacuum Gas trapped

Molten PW >55 ᵒC Gas desorbed

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Questions?Please speak with presenters at their postersGanapathi Ammasai SengodanIoannis TopalidisRiccardo Manno Stephane FournierDavid Brigido Francescogiuseppe MorabitoXun WuKeyao SongXiaoyang SunMichael ElkingtonMark TurkJames McArdleKate Gongadze Harina Amer HamzahPrasanth Prabhakaran

[email protected]@[email protected]@[email protected]@[email protected]@[email protected]@[email protected]@[email protected]@[email protected]