Structural features and approach employed in design of high-performance light aircraft stressed to 8 g limit loads; analytical design exercise shows feasibility of constructing primary airframe from fibrous composite materials; results of minimum weight analyses of fluted core and honeycomb core sandwich panels and their use in selection of final sandwich geometry; curves showing variation in elastic properties with changes in fiber orientation angle for typical basic laminate patterns employed in airframe components.
Design of aircraft utilizing fiberglass reinforced plastic primary structure
J Aircraft
Journal of Aircraft ; 3 , n 5
1966
7 pages
Article (Journal)
English
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