An Integrated Computer Procedure for Sizing Composite Airframe Structures.

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.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1979
Accession Number
ADA304390

Entities

People

  • Jaroslaw Sobieszczanski-sobieski

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Airplanes
  • Algorithms
  • Aspect Ratio
  • Composite Materials
  • Computations
  • Computer Programs
  • Computers
  • Finite Element Analysis
  • Heuristic Methods
  • Materials
  • Mathematical Programming
  • Optimization
  • Orientation (Direction)

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Structural Health Monitoring of Composite Structures.
  • Systems Analysis and Design