Accession Number : ADA300871

Title :   Application Study of Filamentary Composites in a Commercial Jet Aircraft Fuselage.

Descriptive Note : Final rept. Oct 71-Jun 72,

Corporate Author : BOEING CO SEATTLE WA

Personal Author(s) : Johnson, R. W. ; June, R. R.

PDF Url : ADA300871

Report Date : JUN 1972

Pagination or Media Count : 130

Abstract : A study of applications of filamentary composite materials to aircraft fuselage structure was performed. General design criteria were established and material studies conducted using the 727-200 forebody as the primary structural component. Three design approaches to the use of composites were investigated: concept 1, uniaxial reinforcement of metal structure; concept 2, uniaxial and biaxial reinforcement of metal structure; and concept 3, an all- composite design. Materials application studies for all three concepts were conducted on fuselage shell panels, keel beam, floor beams, floor panels, body frames, fail-safe straps, and window frames. Cost benefit studies were conducted and developmental program costs estimated, also for all three concepts. On the basis of weight savings, cost effectiveness, developmental program costs, and potential for early application on commercial aircraft, the concept 1 design is recommended for a 5-year flight service evaluation program.

Descriptors :   *COMPOSITE MATERIALS, *FUSELAGES, *FILAMENTS, METALS, AIRCRAFT, COMMERCIAL AIRCRAFT, COST EFFECTIVENESS, COST ANALYSIS, MATERIALS, FLOORS, PANELS, BEAMS(STRUCTURAL), SHELLS(STRUCTURAL FORMS), COSTS, WINDOWS, AXES, STRAPS, FRAMES, BIAXIAL STRESSES, DESIGN CRITERIA, WEIGHT REDUCTION, JET AIRCRAFT, FAIL SAFE.

Subject Categories : Aircraft
      Laminates and Composite Materials

Distribution Statement : APPROVED FOR PUBLIC RELEASE