Accession Number : ADA325855
Title : Design and Test of a Boron-Aluminum High Temperature Wing.
Descriptive Note : Final rept.,
Corporate Author : NAVAL AIR DEVELOPMENT CENTER WARMINSTER PA AIRCRAFT AND CREW SYSTEMS TECHNOLO GY DIRECTORATE
Personal Author(s) : Richey, R. J., Jr. ; Hess, T. E.
PDF Url : ADA325855
Report Date : 31 MAY 1979
Pagination or Media Count : 101
Abstract : The feasibility of utilizing the high buckling stability characteristics of boron-aluminum advanced composite material in a simple, low cost sparrib skin construction for a thin airfoil structure was investigated for high temperature application up to 589 deg K. The design concept developed consists of boron-aluminum skins, to carry the primary bending and torsion loads, mechanically fastened to a light gage steel substructure, which resists transverse shear and stabilizes the skins. The viability of the concept depends on whether this stabilization of the skin material can be accomplished with a practical number and spacing of substructure elements. A weight saving of one third in comparison to the production article is projected in this boron-aluminum version of the BYM-34E wing. A major wing subcomponent was fabricated and static tested to validate the structural adequacy of the overall design.
Descriptors : *COMPOSITE MATERIALS, *HIGH TEMPERATURE, *STRUCTURES, *FABRICATION, *BUCKLING, *WINGS, *AIRCRAFT DESIGN, SHEAR PROPERTIES, STABILITY, ALUMINUM ALLOYS, LOW COSTS, BENDING, AIRFOILS, STEEL, WEIGHT REDUCTION, TORSION, STATIC TESTS, TRANSVERSE, BORON ALLOYS.
Subject Categories : Aircraft
Properties of Metals and Alloys
Couplers, Fasteners, and Joints
Distribution Statement : APPROVED FOR PUBLIC RELEASE