Composite structure e.g. wing box, optimization draping method for aircraft, involves modifying variables to be optimized for model finite elements of structure, where variables include geometrical dimensions of elements

摘要

The method involves calculating efforts related to external loads for elementary zones of model finite elements of a composite structure, where computation results of characteristics of the external loads of the considered iterative configuration are incompatible for the elementary zone. Variables to be optimized for the model finite elements of the structure are modified, where the variables include geometrical dimensions of the elements. An independent claim is also included for a computer program product comprising a set of instructions to implement a method for optimizing draping of a composite structure.