Development of a Component Head Injury Criteria (HIC ... - FAA
Development of a Component Head Injury Criteria (HIC ... - FAA
Development of a Component Head Injury Criteria (HIC ... - FAA
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<strong>HIC</strong><br />
3500<br />
3000<br />
2500<br />
2000<br />
1500<br />
y = 4.8541x<br />
R 2 = 0.9806<br />
y = 4.7295x<br />
R 2 = 0.9928<br />
NHCT<br />
FSST<br />
1000<br />
500<br />
0<br />
0 100 200 300 400 500 600 700<br />
Stiffness(lb/in)<br />
Figure 33. The <strong>HIC</strong> Correlation for FSST and NHCT MADYMO Models With an Impact Angle<br />
<strong>of</strong> 40 Degrees<br />
6.4.3 Panel Stiffness and <strong>HIC</strong> at an Impact Angle <strong>of</strong> 53 Degrees.<br />
Figure 34 shows the relationship between the panel stiffness and <strong>HIC</strong> value for the NHCT and<br />
the FSST at an impact angle <strong>of</strong> 53 degrees. The <strong>HIC</strong> values for the NHCT and the FSST were<br />
calculated using the coefficients derived in MADYMO (equations 7 and 8).<br />
where: K = Stiffness <strong>of</strong> the panel (lb/in.)<br />
<strong>HIC</strong> NHCT = 2.91 K (7)<br />
<strong>HIC</strong> FSST = 2.24 K (8)<br />
<strong>HIC</strong><br />
NHCT<br />
2000<br />
FSST<br />
1800<br />
1600<br />
y = 2.919x<br />
R 2 = 0.9864<br />
1400<br />
1200<br />
1000<br />
y = 2.2488x<br />
R 2 = 0.9911<br />
800<br />
600<br />
400<br />
200<br />
0<br />
0 100 200 300 400 500 600 700<br />
Stiffness(lb/in)<br />
Figure 34. The <strong>HIC</strong> Correlation for FSST and NHCT MADYMO Models With an Impact<br />
Angle <strong>of</strong> 53 Degrees<br />
24
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