This report presents a detailed description of the flightworthy graphite fiber reinforced composite aircraft primary structural assemblies program. The following tasks were completed: Component selection and preliminary design; materials development; test and quality control procedures development; design allowables and criteria; design allowables testing; and analysis procedure assessment and definition. Demonstration items selected were the F-5A supersonic fighter main landing gear strut door, speed brake, wing leading edge flap, wing trailing edge flap, horizontal stabilizer, and vertical stabilizer main spar. (P.S.-PL)
Flightworthy Graphite Fiber Reinforced Composite Aircraft Primary Structural Assemblies. Volume I. Tasks 1 Through 5
1972
484 pages
Report
No indication
English
Aircraft , Composite Materials , Airframes , Composite materials , Carbon fibers , Reinforcing materials , Aerodynamic control surfaces , Fuselages , Epoxy resins , Graphite , Steel , Quality control , Stabilizers(Horizontal tail surface) , Aluminum alloys , Filament wound construction , Sandwich construction , Honeycomb cores , Laminates , Mechanical properties , Supersonic aircraft , Jet fighters , Leading edge flaps , Landing gear doors , Ammunition damage , Air brake flaps , Flaps(Control surfaces) , Manufacturing , F-5a aircraft , F-5 aircraft
Graphite-Fiber-Reinforced Glass-Matrix Composite
NTRS | 1982
|European Patent Office | 2024
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