Boundary Element Methods for Damage Tolerance Design of Aircraft Structures

Booknews

Dual boundary element formulations are presented for damage tolerance analysis of aircraft stiffened panels and repair patches. Bonded, integral, and mechanically fastened stiffeners are considered, as are riveted and bonded repairs consisting of single or double patches. Formulations allow for crack propagation analysis to be performed with virtually no re-meshing between crack extension increments. Looks into the viability of interactive computer programs for damage tolerance design, and develops an object-oriented interactive system for design of stiffened panels. Annotation c. by Book News, Inc., Portland, Or.