Table 2. Predicted Failure Probabilities for Representative Configurations
                                         Filter Technic ue                    Sample
             Flight      Equal      Index     Expon.     Expon.      Expon Failures
  Vehicle Phase         Weight      Count F =0.99 F = 0.98 F = 0.97            /Total
  Atlas      0         0          0          0          0          0         0/7
             0-1       0.0256       0.0253     0.0245    0.0219      0.0186     4/156
             0-2       0.0449       0.0385     0.0387    0.0313      0.0243     7/156
             0-3       0.0769       0.0715     0.0714    0.0643      0.0568     12/156
             0-4       0.0833       0.0811     0.0801    0.0740      0.0663     13/156
             0-5*      0.1090       0.1100     0.1078    0~1019      0.0929     17/156
  Delta      0         0            0          0         0           0          0/125
             0-1       0.0160     . 0.0126     0.0134    0.0104      0.0075     2/125
             0-2       0.0160       0.0126     0.0134    0.0104      0.0075     2/125
             0-3       0.0160       0.0126    ·o.0134    0.0104      0.0075     2/125
             0-4       0.0160       0.0126     0.0134    0.0104      0.0075     2/125
             0-5*      0.0640       0.0447     0.0535    0.0469      0.0442     8/125
  Titan      0         0.0306       0.0210     0.0225    0.0292      0.0352     3/98
             0-1       0.0234       0.0305     0.0314    0.0403      0.0470     4/171
             0-2       0.0409       0.0496     0.0514    0.0642      0.0750     7/171
             0-3       0.0526      0.0581      0.0597    0.0689      0.0773     9/171
             0-4       0.0526      0.0581      0.0597    0.0689      0.0773     9/171
             0-5*      0.1111      0.1167      0.1188    0.1284      0.1358     19/171
  * Includes response mode 'NA'
It is apparent from the data in Table 2 that estimates of future vehicle reliability depend
on the filtering (i.e., weighting) technique applied. Since there are many ways to
perform the filtering, all generally producing slightly different results, the choice of
method to use in deriving empirical failure probabilities cannot be totally objective.
Subjective decisions must also be made about which past configurations to consider as
representative of future vehicles, which flight tests to include_ in the sample, how to
weight the individual flights, and, in unusual cases, whether to consider a flight a
success or a failure, and to which flight phase to attribute a failure. Except for data
weighting (i.e., choice of filter), these decisions were made for Atlas, Delta, and Titan
before computing the failure probabilities shown in Table 2.                    •

For Atlas and Delta, it can be seen from Table 2 that the predicted failure probabilities
computed. with the exponential filter decrease as the value of F decreases. Since a
decreasing F means more emphasis on recent data and less emphasis on the old, the
launch reliability for these vehicles is apparently improving. The reverse seems to be
true for Titan, suggesting either that Titan reliability is not improving or, possibly, that
improvements that have been or are being made to the vehicle are not yet fully
reflected in the test· results. For Atlas and Delta, the computed failure probabilities
based on equal weighting are higher than for all other filters, and the predicted failure


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