Development of a Graphite Horizontal Stabilizer.
Semi-annual interim technical rept. no. 4, 1 May-31 Oct 71,
DOUGLAS AIRCRAFT CO LONG BEACH CALIF
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The structural weights, stress-analysis results, and manufacturing methods are summarized for an A4 aircraft horizontal stabilizer utilizing Narmco 5206 graphite- epoxy laminates in the primary structure. The actual weight of the first unit produced was 178 pounds, a weight reduction of 30 in comparison to the equivalent metal structure. The finished structure weight was comprised of approximately 62 percent graphite-epoxy, 11 percent fiberglass-epoxy, 10, 8, and 5 percent, respectively, of aluminum, steel, and titanium alloys including attachments, and 4 percent adhesive and epoxy fillets. Results of a discrete element stress-analysis are presented for the three critical load conditions on the stabilizer. The discrete element model included recent design changes dimensions and elastic properties to the stabilizer and provisions for running asymmetric load cases. Buckling allowables are presented for actual skin panel thicknesses and margins-of-safety are summarized for all critical elements of the structure. Tooling, fabrication, and assembly procedures used during construction of the first stabilizer assembly and the second substructure assembly are discussed. Details of the discrete element model, internal stress distributions, incoming material and in-process test results including NDT, and fabrication procedures are contained in Appendices. Author-PL
- Attack and Fighter Aircraft
- Refractory Fibers
- Laminates and Composite Materials