1. The load-relief system for the Saturn VIVoyager configuration was able to l i m i t the bending moments for a given wind disturbance and thus increase the probability of not encountering a wind disturbance which would cause structural failure. Figure 11 depicts the marked advantage of the load relief controller over the Apollo attitude controller for the Voyager missions during the 1970's launch periods,
2. ,2865 + 1 I S" + 4.1659 + 146 S" + 7.525 + 13.45 &I ,255 + 1 S + 140.35 + 1463 l^i ,167s + 1
3. 1972 1974 i976 1978