Multiscale Reduced-Order Modeling of a Titanium Skin Panel Subjected to Thermomechanical Loading

Abstract

This paper presents the formulation, implementation, calibration, and application of a multiscale reduced-order model to simulate a titanium panel structure subjected to thermomechanical loading associated with high-speed flight. The formulation is based on the eigenstrain-based reduced-order homogenization model and further considers thermal strain as well as temperature-dependent material properties and evolution laws. The material microstructure (i.e., at the scale of a polycrystalline representative volume element) and underlying microstructural mechanisms are directly incorporated and fully coupled with a structural analysis, concurrently probing the response at the structural scale and the material microscale. The proposed approach was fully calibrated using a series of uniaxial tension tests of Ti-6242S at a wide range of temperatures and two different strain rates. The calibrated model is then adopted to study the response of a generic aircraft skin panel subjected to thermomechanical loading associated with high-speed flight. The analysis focuses on demonstrating the capability of the model to predict not only the structural scale response, but also simultaneously the microscale response, and it further studies the effects of temperature and texture on the response.