Download complete journal in PDF form - Academy Publish

PARAMETRIC STUDY OF SANDWICH PANEL BUCKLING IN COMPOSITE WIND TURBINE BLADES
Shicong Miao, Steven Donaldson, and Elias Toubia
the result is approximately 9.6% maximum decrease in buckling strain.
For core material Q5, the shear modulus is the same as Q4 but up to
28.6% decrease in material elastic modulus. The result is only
maximum 3.3% decreased in buckling strain. The results indicate that
in sandwich buckling resistance, the core transverse shear modulus is a
major characteristic aspect, while the material elastic modulus has
negligible effect on the critical strain level.The trends are almost
constant when the core shear modulus increases. Critical buckling
strains are proportional with the increase in core thickness. As such,
core thickness is another major aspect in sandwich buckling
resistance.The results are expanded in Figure 10 to include additional
face sheet layer combinations.
Figure 9. Critical buckling strain versus core transverse shear modulus in 20, 30, 40mm core. 1 facing layer. Flat-section sandwich panel.
Critical buckling strain ε (%)
0.9
0.8
0.7
0.6
0.5
0.4
0.3
0.2
0.1
0
M
1
M
1
M
1
M
2
M
2
M
2
Q1
Q1
Q1
1 facing
M
M
M
20 40 60 80 100 120 140 160 180 200 220 240
Transverse shear modulus
Q5
Q2 Q3 Q4
Q3
Q3
Q5
Q4
Q5
Q4
M
4
M
4
M
4
40m
30mm
20mm
Figure 10. Critical buckling strain versus core transverse shear modulus in 20, 30, 40mm core. All 5 facing layers. Flat panel. 1m width
Critical buckling strain ε (%)
1
0.9
0.8
0.7
0.6
0.5
0.4
0.3
0.2
40mm
30mm
20mm
5 layer
4 layer
3 layer
2 layer
1 layer
5 layer
4 layer
3 layer
2 layer
1 layer
5 layer
4 layer
3 layer
2 layer
1 layer
0.1
0
20 70 120 170 220
Transverse shear modulus (Mpa)
AcademyPublish.org – Journal of Engineering and Technology Vol.2, No.2 10