GALCIT Colloquium

Friday March 10, 2017 3:00 PM

A Virtual Platform for Future Manufacturing and Certification of Aerostructures

Speaker: Tony Waas, Aeronautics and Astronautics, University of Washington
Location: Guggenheim 133 (Lees-Kubota Lecture Hall)

The current practice of designing composite airframe structures relies on extensive testing, coupled to a bottom-up, pyramidal building block approach, to ensure structural integrity and damage tolerance. Reducing the number of tests can lead to a substantial decrease in total design cost of many vehicles. Cost reduction is enabled by developing high fidelity computational models which can provide valuable information regarding the performance of a structure up to and including failure. This activity, which is now a major area of research falls under the broad umbrella of "virtual" testing, and includes parallel activities such as ICME (integrated computational materials science and engineering), and "digital twin" (the process of creating a high fidelity computational model of individual aircraft, to integrate computation of structural deflections and temperatures in response to flight conditions, with a depository of local damage evolution so that the "state" of the vehicle is updated and current at any given time). With a view towards addressing future, robotically manufactured aerospace structures, this talk will address elements of ICME, to analyze the effect of the curing process on the in-service performance of fiber reinforced composite structures. A polymer curing model based on the notion of polymer networks that are continuously formed in a body of changing shape due to changes in temperature, chemistry and external loads is used in conjunction with multiple fiber representative volume elements (RVE) to assess the strength of the RVE when subjected to mechanical loads after virtual curing. Nonlinear material response, including damage and failure, is incorporated in conjunction with the mesh-objective crack band model. It is shown that significant stresses can develop during cure, and depending on the cure cycle, the matrix material can be subjected to damage prior to insertion in service. The notions of composite strength are re-examined in light of the results obtained.  Examples from continuous fiber reinforced polymer matrix composites and textile composites will be presented.

Series GALCIT Colloquium Series

Contact: Mallory Neet