This paper proposes to use laminate damage modelling capabilities, together with global aircraft level modelling methods, to create a multi-fidelity simulation framework. The framework will enable the early evaluation of composite wing panel damage response and residual strength within its representative in-service structural environment. The framework is developed on the principles of Simulation Intent, utilising the concepts of cellular modelling to efficiently define and construct analysis models for key structural features, and equivalencing to intelligently and automatically map the different representation of the features in the aircraft GFEM and the higher fidelity local stiffened panel design domain model. Example output demonstrates the capability of the modelling framework to evaluate skin laminate residual strength within the global wing structure, and inform the structural design process with more representative laminate maximum allowable stress data.
|Number of pages||10|
|Publication status||Published - 2018|
|Event||RAS 6th Aircraft Structural Design Conference - Bristol, United Kingdom|
Duration: 09 Oct 2018 → 11 Oct 2018
|Conference||RAS 6th Aircraft Structural Design Conference|
|Period||09/10/2018 → 11/10/2018|
Student thesis: Doctoral Thesis › Doctor of PhilosophyFile