The study is concerned with the application of super component design techniques to a representative nonelectronic flight control component, and evaluation of the reliability improvement attained by means of tests performed on groups of standard and super units. The representative component used was a cold gas, proportional mode reaction controller for space vehicle attitude control applications. Three super controllers and four standard controllers were fabricated, and were tested according to a plan which simulated, as far as was practical, a mission profile. The test results tended to show the super units had advantages over the standard units in regard to specific failure modes. However, no statistically significant difference in life characteristics between the two groups was demonstrated. This is attributed to the combination of the small numbers of samples in the test groups, and the relatively low magnitude improvement in life characteristics actually attained. Author
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