Rapid Prediction of Worst Case Gust Loads Following Structural Modification

An approach to reduce the computational effort required to determine the worst-case gust loads for aircraft is described, specifically when structural modifications are included as part of the design process. The Sherman–Morrison–Woodbury formula is employed to determine the gust response of the modified structure using a reanalysis approach and to undertake an efficient modal reanalysis. The approach is demonstrated successfully using a simple wing and full-scale aircraft finite-element models to determine the worst-case “1 − cosine” gust following structural
modification. Savings of about56%were achieved for gust-response computations and 50%for the modal reanalysis.