Examination of data on weight of various structural elements fabricated in graphite composites, and application of this data to study of weight of X-22A V/STOL aircraft; it is shown that over 30% of weight of current aluminum structure could be saved, resulting in 100% increase in payload; studies include such elements as tension members, stiffened and unstiffened compression panels, shear panels, sandwich panels, columns, beams, torque tubes, etc; potential failure modes such as buckling, fiber tensile strength, resin shear strength, fiber resin bond strength, and resin strain limitations are considered.
Application of graphite fiber composites to airframe structures
SAE -- Paper
SAE Meeting ; 1968 Plastics
1968
12 pages
Aufsatz (Konferenz)
Englisch
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The Application of Graphite Fiber Composites to Airframe Structures
SAE Technical Papers | 1968
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