[PPT] - laminate stacking sequences Nomie Fedon Terence Macquart, Paul PowerPoint Presentation

SLIDE 1

Optimisation of composite laminate stacking sequences

Noémie Fedon

Terence Macquart, Paul Weaver, Alberto Pirrera

CDT conference

16 April 2019

SLIDE 2

Design of blended composite laminates

2

Noémie Fedon

Optimisation of composite laminate stacking sequences

[ϴ1, ϴ2, ϴ3, ϴ4] Lightweight structures

Aims

Discrete design variables
Highly non-linear and non-convex
bjective and constraints functions
Many design variables

Difficulties

Discrepancy in the multi-level optimisation

SLIDE 3

Novel optimiser to design the plies’ fibre orientations

3

[45, 90, -45, ?, …, ?] Noémie Fedon

Optimisation of composite laminate stacking sequences

Target lamination parameters Boundary of the lamination parameter design space

ξ1 ξ3

0°

45°

45° 90° 0° 0° 45° 90°

45°

45° 90° 0° 45° 90° -45°

45°

SLIDE 4

Design of a benchmark 18-panel structure

4

Nx = -700 Ny = -400 Nx = -375 Ny = -360 Nx = -1100 Ny = -600 Nx = -900 Ny = -400 Nx = -375 Ny = -525 Nx = -400 Ny = -320 Nx = -270 Ny = -325 Nx = -305 Ny = -360 Nx = -300 Ny = -610 Nx = -330 Ny = -330 Nx = -320 Ny = -180 Nx = -190 Ny = -205 Nx = -300 Ny = -410 Nx = -815 Ny = -1000 Nx = -250 Ny = -200 Nx = -290 Ny = -195 Nx = -210 Ny = -100 Nx = -600 Ny = -480 18 in. 20 in. 24 in. 12 in. Load intensities in lbf/in (x 1751.1 for N/m)

Noémie Fedon

Optimisation of composite laminate stacking sequences

Weight: 28.8 kg
Execution time: 10 min

SLIDE 5

Conclusion and future work

5

Noémie Fedon

Optimisation of composite laminate stacking sequences

Multi-level optimisation to account for load redistribution

Interaction between the levels of optimisation

2 - stacking sequence design 1 - stiffness and thickness optimisation

Upper skin Ply counts Thickness in mm Lower skin

SLIDE 6

Design of blended composite laminate structures

noemie.fedon@bristol.ac.uk

SLIDE 7

Novel technique to design blended structures

7

Panel 1 Panel 2 Panel 3 Panel 4 Group 1 Group 2 Group 3

Sub-division of the optimisation problem Noémie Fedon

Optimisation of composite laminate stacking sequences

0°

45°

45° 90° 0° 0° 45° 90°

45°

45° 90° 0° 45° 90° -45°

45°

0°

45°

45° 90° 0° 0° 45° 90°

45°

45° 90° 0° 45° 90° -45°

45°

0°

45°

45° 90° 0° 0° 45° 90°

45°

45° 90° 0° 45° 90° -45°

45°

SLIDE 8

Design of a benchmark 18-panel structure

8

Nx = -700 Ny = -400 Nx = -375 Ny = -360 Nx = -1100 Ny = -600 Nx = -900 Ny = -400 Nx = -375 Ny = -525 Nx = -400 Ny = -320 Nx = -270 Ny = -325 Nx = -305 Ny = -360 Nx = -300 Ny = -610 Nx = -330 Ny = -330 Nx = -320 Ny = -180 Nx = -190 Ny = -205 Nx = -300 Ny = -410 Nx = -815 Ny = -1000 Nx = -250 Ny = -200 Nx = -290 Ny = -195 Nx = -210 Ny = -100 Nx = -600 Ny = -480 18 in. 20 in. 24 in. 12 in. Load intensities in lbf/in (x 1751.1 for N/m)

Results

Weight similar than in

the literature

Design obtained less

than an hour

Many laminate design

guidelines can be considered: symmetry, balance, contiguity, disorientation, 10% rule, ply drop spacing and stacking Initial thickness distribution from individual panel

ptimisations

Multi-panel structure

ptimisation

Addition of a ply to the most critical panel if the buckling constraints are not all satisfied Method Noémie Fedon

Optimisation of composite laminate stacking sequences

SLIDE 9

Design of composite laminates

9

Noémie Fedon

Optimisation of composite laminate stacking sequences

[ϴ1, ϴ2, ϴ3, ϴ4] Lightweight structures

Objective

Discrete design variables
Many design and manufacturing guidelines

MN = Number of possible stacking sequences N = Number of plies For single-panel

ptimisation with a

fixed number of plies

Highly non-convex objective function
Many design variables