APPLICATION OF A ROTATIONAL-PROBABILITY ANALYSIS FOR DETERMINATION OF ULTIMATE DESIGN LOADS ON LARGE, FLEXIBLE, MILITARY AIRCRAFT
Rept. for Oct 1963-Mar 1964
SYSTEMS ENGINEERING GROUP WRIGHT-PATTERSON AFB OH
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Recent experiences with B-52 aircraft have indicated that the current structural design criteria are inadequate for large, flexible, military aircraft. A rational-probability analytical procedure was established to overcome this problem. This analysis determines ultimate loads for which the vehicle must be designed in order to achieve the specified acceptable failure rate due to structural overload. The basis for the analysis is the acceptable failure rate, the dynamic spectral analysis, and the spectral exceedance curves. By use of this analysis, mission and performance trade-offs can be established in terms of probability of failure due to structural overload. With some modification, it is believed that this type of analysis can, and should, be applied to all types of aircraft.