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The philosopy followed to satisfy design requirements for aircraft structures is discussed. An approach is described which has been successfully used to generate boron/epoxy design allowables data on the basis of 90 percent probability of survival with a confidence of 95 percent (MIL-HDBK-5 B basis). This approach results in design strength data which include not only the variations in material properties but also any inadequacies in theoretical methods for strength prediction. Results of tests on full scale components and subcomponents are compared with theoretical predictions using these design allowables data.
composite materials, boron, epoxy resins, laminates, orthotropism, aircraft structures, structural members, fatigue (materials), static tests, fatigue tests, ultimate strength, design
Head, Grumman Aerospace Corporation, Bethpage, N.Y.