NASA NTRS · 19790009409
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 discussed.
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Sobieszczanski-Sobieski, J.. 1979-02-01. An integrated computer procedure for sizing composite airframe structures. https://ntrs.nasa.gov/citations/19790009409
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