The F-111 (EF-111A) horizontal stabilizer leading edge was selected as the baseline component to demonstrate the superior supportability characteristics of composites. The production component is a full-depth aluminum honeycomb sandwich construction that has historically shown in-service supportability programs. The composite leading edge (22.4 sq ft in plan area) was designed as a form, fit and function replacement for the existing aircraft. Because of the aircraft's leading edge high service temperature (317 F) and humidity environment (83 percent relative humidity), skins and stiffening members were designed of graphite/bismaleimide (Gr/BMI). At equivalent weight, acquisition and life cycle cost savings of 13 and 45 percent respectively were projected, for the composite leading edge over the existing aluminum honeycomb sandwich assembly.
Development of a Graphite/Bismaleimide Leading Edge for the F-111 (EF-111A) Horizontal Stabilizer
1988
9 pages
Report
Keine Angabe
Englisch
Aircraft , Engineering Materials , Composite Materials , Bismaleimide , F-111 aircraft , Fiber composites , Leading edges , Resin matrix composites , Stabilizers (Fluid dynamics) , Aluminum , Cost reduction , High temperature , Honeycomb structures , Humidity , Life cycle costs , Sandwich structures , Stiffening
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