Abstract
The initiation of flight testing of aircraft structures utilizing advanced composite materials in January of 1967 marks a major milestone in the development of this new material concept. Specific developments in the boron fiber-reinforced plastic tape systems leading to this accomplishment will be discussed, together with design, analysis, and fabrication techniques. Composite test results emphasize the need for fiber spacing control and matrix toughness. Data through the 420°F temperature range demonstrate the advantages of this material over other materials Analytical procedures for predicting laminate stiffness and yield strength have demonstrated satisfactory results with an assumed yield surface theory. A digital program has been written to aid the designer in selecting the minimum weight laminate for a given point load or stiffness requirement. The flight test component design features and static test results will be discussed.
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