Abstract
The paper is concerned with development of geodesic composite fuselage structure whose stiffness and strength are provided by a system of ribs made of unidirectional carbon-epoxy composite materials by continuous wet filament winding. Design and weight efficiency of the geodesic structures are discussed along with the efficiency of traditional composite stringer structures. Results of design, analysis and fabrication of a full-scale 4m diameter fuselage section are presented.
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