Accession Number : ADA304390

Title :   An Integrated Computer Procedure for Sizing Composite Airframe Structures.

Descriptive Note : Technical paper,

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER

Personal Author(s) : Sobieszczanski-Sobieski, Jaroslaw

PDF Url : ADA304390

Report Date : FEB 1979

Pagination or Media Count : 45

Abstract : A computerized algorithm to generate cross-sectional dimensions and fiber orientations for composite airframe structures is described, and its application in a wing structural synthesis is established. The algorithm unifies computations of aeroelastic loads, stresses, and deflections, as well as optimal structural sizing and fiber orientations in an open-ended system of integrated computer programs. A finite-element analysis and a mathematical-optimization technique are the main components of the procedure. Design constraints include stress, strain, local buckling, and minimum gage. The algorithm is applied to evaluate a series of basic design alternatives such as types of construction, types of material, and manufacturing restrictions for the low-aspect-ratio wing of a large transport airplane. Included also is a review of the computational efficiency of the method.

Descriptors :   *COMPUTERIZED SIMULATION, *COMPUTER AIDED DESIGN, *COMPOSITE STRUCTURES, *AIRFRAMES, STRESSES, COMPUTER PROGRAMS, ALGORITHMS, FIBERS, INTEGRATED SYSTEMS, COMPUTATIONS, MANUFACTURING, SYNTHESIS, COMPUTERS, STRUCTURAL PROPERTIES, FINITE ELEMENT ANALYSIS, LOADS(FORCES), DEFLECTION, ORIENTATION(DIRECTION), EFFICIENCY, AEROELASTICITY, CROSS SECTIONS, BUCKLING, COMPUTER APPLICATIONS, WINGS, TRANSPORT AIRCRAFT.

Subject Categories : Aircraft
      Computer Programming and Software

Distribution Statement : APPROVED FOR PUBLIC RELEASE