A fuselage structure is described in which the skin is comprised of layers of a matrix fiber reinforced composite, with the stringers reinforced with the same composite material. The high strength to weight ratio of the composite, particularly at elevated temperatures, and its high modulus of elasticity, makes it desirable for use in airplane structures.
Fuselage Structure Using Advanced Technology Fiber Reinforced Composites
1978
9 pages
Report
Keine Angabe
Englisch
Government Inventions for Licensing , Composite Materials , Patents , Aircraft construction materials , Fiber reinforced composites , Fuselages , Laminates , Metal matrix composites , Borsic (Tradename) , Fiber orientation , Skin (Structural member) , Straps , Stringers , PAT-CL-244-119 , PAT-CL-244-123 , PAT-CL-244-132
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