Department of the Air Force Report, 1996

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Figure 30 shows the percentage of malfunction-tum impacts in 5° sectors for no
breakup, and for breakup qa.'s of 20,000, 10,000, and 5,000 deg-lb/ft'\ The three
breakup qa's produced impact distributions that were surprisingly similar, possibly
due to the vehicle's higher acceleration. Theoretical Mode-5 impact distributions are
also plotted in the figure for B= 1,000 and best-fit values of A. This value of B was
chosen since it is currently used by-RTI in making launch-area risk studies for
45 SW/SE. For all except the no-breakup case, values of A were found that produced
good fits between the malfunction-tum and Mode-5 impact distributions in the sectors
from ±60° to ±180°.
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Angle From Flight Path (deg)
Figure 30. LLVl Simulation Results with B = 1,000
9/10/96
70
RTI