The feasibility of performing the automated optimum design of airplane wing structures at preliminary design stages, with consideration of the taxing stress developed, is studied. During actual programming, we need to adjust the order in which different interval parameters are considered in any specific equation. The purpose of truncation is to make reasonable modifications to the output range before applying it to the next interval operation. This truncation approach can give reasonable predictions for the solution even when the widths of their starting points or the interval ranges of other influencing parameters are quite large. The optimization results obtained with the interval analysis are found to be in good agreement with those obtained with the deterministic approach. The interval analysis is expected to be more realistic and, hence, should be used in the optimum design of the airplane wing structure.
ASJC Scopus subject areas
- Aerospace Engineering