Chapter 10: Altstädt, V.: Testing of Composite Materials. In: Grellmann, W., Seidler, S. (Eds.): Polymer Testing. Carl Hanser Verlag, Munich (2013) 2

Chapter 10: Altstädt, V.: Testing of Composite Materials. In: Grellmann, W., Seidler, S. (Eds.): Polymer Testing. Carl Hanser Verlag, Munich (2013) 2. Edition

Fig.: 10.1

relative costs

70 %

13 %

14 %

3 %

component tests

part componenttests

detail tests

coupontests

plastic zone

resin

matrix

fiber

8-10 µm

ba

0 200 400 600 800 1000 resin G (J m )Ic

-2

com

posi

te G

Ic

(J

m-2)

100

200

300

400

500

0

1:1


Fig.: 10.2

0 500 1000 1500

400

300

200

100

0

standard carbon-fiber

IM carbon-fiber

laminate fracture toughness G (J m )IIc-2

resi

dua

l com

pres

sive

str

engt

haf

ter

impa

ct (

MP

a)


Fig.: 10.3

0+45

[0/+45/90/-45]S

90

-45

-45

90

+45

0


Fig.: 10.4

specimen

plate

test

tensile compression shear flexure

laminating

winding ring

0°-ring

90°-tube

tube

plat

e


Fig.: 10.5

cap strip

adhesive layer

specimen


Fig.: 10.6


Fig.: 10.7

linear analysis planar analysis

a b


Fig.: 10.8

fiber orientation in the cap strip

150

50

45°

cap strip

1

50250

clamping devices

15

45°


Fig.: 10.9

150

50

2010


Fig.: 10.10

cap stripclamping devices

25

150

50

250

center holes(optional)

2–1

0


Fig.: 10.11

25

136

50

250

center holes(optional)

2–1

0


Fig.: 10.12

specimen

brittle failure with smooth fracture surface

brittle failure with brush-like fracture surface


Fig.: 10.13

A

B

CD

80

60

40

20

00 0.1 0.2 0.3 0.4 0.5 0.6

(%)

0.05 % – 0.25 %

secant line

(M

Pa)


Fig.: 10.14


Fig.: 10.15

failure

buckling

shear failure

in-plane failurecaused by longitudinalcrack formation

brooming


Fig.: 10.16

175

150

125

100

75

50

25

00 1 2 3 4 5 6

g/h

EP/CF

A

B

CB

(MP

a)


Fig.: 10.17

strength modulus load application by the frontface of the specimen

5

60

70

80

1

1212

80

2 dcba


Fig.: 10.18

ba c


Fig.: 10.19

load application by four-point bending

cover layer 1

honeycomb

cover layer 2

F/2

compression failure

d1

d2

F/2 d < d1 2


Fig.: 10.20


Fig.: 10.21


Fig.: 10.22

6.4

3.2

L = 8d

= 26.

4

v = 1.25 mm min v = 1 mm min

25Ld

= 4

[0]

[ 45]

16

8+

3.2 6

L = 1020

6

d =

210

6

Ld

= 5

[0]

[ 45]

16

8+

ba


Fig.: 10.23

-1 -1

45° -45° 10°

45° 10°+

off-axis tensile test Iosipescu shear test two-rail three-railshear test shear test


Fig.: 10.24

150

45°

cap strip

50250

clamping devices

25

45°

specimen

x

ystrain gauge

x

45

45


Fig.: 10.25

determination of G12

12 ’ = 0.0112

’’ = 0.05

12 ’

12

12 ’’

(MP

a)12


Fig.: 10.26

150

45°

cap strip

50250

clamping device

25

45°

specimen

x

y

strain gauge rosette

x

10°

3 2

1


Fig.: 10.27

F

45°straingauge

+

44.576.2

152

.4

R 8

ba


Fig.: 10.28

tensile or compressionloading

center beam slipsthrough the guide

strain gauge

ba


Fig.: 10.29

ba

F

movable

adjustable jaw

rigid

strain gauge

base plate

shear plane

90°

76.2

19

d=12.7

wChapter 10: Altstädt, V.: Testing of Composite Materials. In: Grellmann, W., Seidler, S. (Eds.): Polymer Testing. Carl Hanser Verlag, Munich (2013) 2. Edition

Fig.: 10.30

F/2 F/2

F/2 F/2


Fig.: 10.31

50 50125

10

50

1.7–

3.5


Fig.: 10.32


Fig.: 10.33

mode Iplane crack opening

mode IIin-plane shear

mode IIIout-of-plane shear


Fig.: 10.34

glued loading blocks

3–5

mma = 50 mm

B = 2

0 m

m

dist

ance

10

mm

hinge bands

225 mm


Fig.: 10.35

a1

a2

A

150

100

50

00 20 40 60 80 100

v (mm)L

F (

N)


Fig.: 10.36

a

2d

F

0 1 2 3 4 5 6 7


Fig.: 10.37

a

L L

0 1 2 3 42d


Fig.: 10.38

4ENF-specimen

base plate

aL

0 1 2


Fig.: 10.39

a

2d 0 1 2 3 4 5 6 7 8 9 10

L

F


Fig.: 10.40

2d

cF

rotation center

0 1 2 3 4 5 6 7 8 9 10

aL L

back gaugeand stirrup


Fig.: 10.41

shear layer

clamping layer

F

a

L

BF

d2

d1


Fig.: 10.42

-30/90

x

38 38250


Fig.: 10.43

specimenwith hole

F

F

ba


Fig.: 10.44

peel arm(thickness d)

clamped arm of the laminate

peel angle

peel load F

laminate (width B)

ba


Fig.: 10.45

peel load F

peel arm 1

peel arm 2

specimen(width B)

ba


Fig.: 10.46

rigid layer

flexible layer

ba


Fig.: 10.47

impact

500 µm


Fig.: 10.48

1500

1000

500

00 2 4 6 8 10

A (Nm)H

EP/CF

BMI/CF

A

(m

m

)s

2


Fig.: 10.49

strain gauges

127

76.2

impactposition

ba


Fig.: 10.50

EP/CF

BMI/CF

0 2 4 6 8 10

A (Nm)H

0

100

200

300

400

500

(MP

a)M


Fig.: 10.51

0

100

200

300

400

500

(MP

a)M

EP/CF

BMI/CF

A (mm2)s

0 500 1000 1500


Fig.: 10.52

Documents

Chapter 10: Altstädt, V.: Testing of Composite Materials. In: Grellmann, W., Seidler, S. (Eds.): Polymer Testing. Carl Hanser Verlag, Munich (2013) 2