Development of a Component Head Injury Criteria (HIC ... - FAA

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The input pulse for all the simulations used the standard triangular Federal Aviation Administration (FAA) 16-g, 180-ms pulse as shown in figure 27. Figure 28 shows the MADYMO lap belt properties, while figure 29 shows the properties of the seat cushion. Acc'g' 18 16 14 12 10 8 6 4 2 0 0 0.02 0.04 0.06 0.08 0.1 0.12 0.14 0.16 0.18 0.2 Time(Sec) Figure 27. MADYMO Simulation Input Pulse 600 500 Force (N) 400 300 200 Hysteresis model = "1" Hysteresis slope= 1.00000E+06 100 load unload 0 0 0.01 0.02 0.03 0.04 0.05 Displacement (m) Figure 28. MADYMO Lap Belt Load Deflection Properties Force (N) p 2000 load 1800 unload 1600 1400 Hysteresis Model="1" 1200 Hysteresis slope = 6.00000E+06 1000 800 600 400 200 0 0 0.002 0.004 0.006 0.008 0.01 0.012 0.014 Displacement (m) Figure 29. Seat Cushion Load Deflection Properties 20
Figure 30 shows the MADYMO model simulation sequence. The results of the parametric study are shown in table 8. 1 2 3 Figure 30. Simulation of the FSST With ETHAFOAM Panel Table 8. The FSST Simulation Results of Panel Stiffness and Impact Angles Stiffness (lb/in.) Impact Angle 50 100 150 200 300 400 500 600 31 HIC (deg) HIC window 40 HIC (deg) HIC window 53 HIC (deg) HIC window 4 5 6 210 [Δt=15ms] 160 [Δt=15ms] 120 [Δt=15ms] 435 [Δt=15ms] 340 [Δt=15ms] 228 [Δt=15ms] 6.3.2 Parametric Study With NHCT. 721 [Δt=9ms] 670 [Δt=11ms] 387 [Δt=15ms] 968 [Δt=10ms] 1044 [Δt=13ms] 503 [Δt=15ms] 1619 [Δt=11ms] 1491 [Δt=11ms] 721 [Δt=13ms] 2111 [Δt=9ms] 1931 [Δt=11ms] 916 [Δt=13ms] 2616 [Δt=8ms] 2377 [Δt=9ms] 1112 [Δt=11ms] 3114 [Δt=15ms] 2771 [Δt=8ms] 1293 [Δt=9ms] As was the case for the FSST, a parametric study was carried out for the NHCT MADYMO model. The NHCT model was validated using NHCT test 01057-82. The panel was given the same load deflection curve as that used in the simulation of previous sled tests. The simulation sequence is shown in figure 31. A series of simulations was conducted with similar panel properties and head impact angles as used for the previous sled test to study the effect of these factors on the HIC value. Moving the panel closer to or away from the tester changed the impact angle. The data from these tests are listed in table 9. 21
Page 1 and 2: DOT/FAA/AR-06/47 Air Traffic Organi
Page 3 and 4: 1. Report No. 2. Government Accessi
Page 5 and 6: TABLE OF CONTENTS Page EXECUTIVE SU
Page 7 and 8: LIST OF FIGURES Figure Page 1 Desig
Page 9 and 10: 45 Simulation Sequence of Foam Defo
Page 11 and 12: LIST OF SYMBOLS AND ACRONYMS ATD c.
Page 13 and 14: 1. INTRODUCTION. One of the problem
Page 15 and 16: distribution was obtained by optimi
Page 17 and 18: 4. MODIFICATION OF THE NHCT. Since
Page 19 and 20: Figure 8. Pressure Sensor Once the
Page 21 and 22: Table 1. Test Results of FSST 96288
Page 23 and 24: Table 3. Test Results of NHCT Tests
Page 25 and 26: From the above data plots and the r
Page 27 and 28: Test 01057-82 conducted at NIAR was
Page 29 and 30: Figure 20. MADYMO Model Setup for F
Page 31: 6.3 PARAMETRIC STUDY OF IMPACT SURF
Page 35 and 36: 3500 3000 y = 5.5408x R 2 = 0.9801
Page 37 and 38: The equations obtained can be used
Page 39 and 40: Table 10. Results of the FSST and N
Page 41 and 42: 8.1 RAW TEST DATA. The raw data use
Page 43 and 44: Figure 41. MADYMO Model Developed f
Page 45 and 46: 1 2 3 4 5 6 Figure 45. Simulation S
Page 47 and 48: 1 2 3 4 5 6 Figure 48. Simulation S
Page 49 and 50: Table 15. Comparison of HIC Results
Page 51 and 52: when the actuator is firing. This r
Page 53 and 54: Table 17. Comparison of FSST Result
Page 55: 6. Gurdjian, E.S., Roberts, V.L. an

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