Accession Number : ADA298560

Title :   Improvements in Design Oriented Equivalent Plate Modeling of Wing Structures,

Descriptive Note : Master's thesis,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

Personal Author(s) : Borchert, Robert Q.

PDF Url : ADA298560

Report Date : MAR 1995

Pagination or Media Count : 177

Abstract : Improvements in equivalent plate modeling of aircraft wings are presented. Formulations for wing mass, stiffness, and loads using Classical Plate Theory and First Order Shear Deformation Plate Theory are given in a general manner allowing versatility in the selection of displacement Ritz polynomials. A new technique for approximating the stiffness of an array of spar webs with the stiffness of an equivalent sandwich core is developed. A formulation allowing wing zones modeled with Classical Plate Theory and First Order Shear Deformation Plate Theory to be used together is also presented. Numerical tests were performed to verify the validity of the new formulations. Tests of a thick, high aspect ratio wing showed that selecting low order Ritz polynomials for the linear in-plane displacements of a symmetric wing can lead to a significant reduction in model order while retaining acceptable accuracy. Additional tests of the thick, high aspect ratio wing and a typical supersonic transport wing showed that an array of spar webs may be accurately replaced by an equivalent core leading to substantial savings in computation time. (MM)

Descriptors :   *AERODYNAMIC CONFIGURATIONS, *STIFFNESS, *WINGS, *SUPERSONIC TRANSPORT AIRCRAFT, CORES, MASS, DEFORMATION, DISPLACEMENT, THESES, EIGENVALUES, COMPOSITE STRUCTURES, STRAIN(MECHANICS), SYMMETRY, VECTOR ANALYSIS, DESIGN CRITERIA, SKIN(STRUCTURAL), ASPECT RATIO, SANDWICH CONSTRUCTION, RIBS, WEB BEAMS.

Subject Categories : Aerodynamics
      Transport Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE