K. Seywald, A. Wildschek, F. Holzapfel

DOI Number: N/A

Conference number: IFASD-2015-068

This article deals with different methods for modeling the free-flying flexible aircraft and compares the obtained models for aircraft response simulations. A direct time domain approach which is composed of a free flying finite element structure coupled to an unsteady potential flow method was implemented. This method is used to investigate the impact of fixed-axis and mean-axis boundary conditions. Furthermore the impact of quasisteady and unsteady aerodynamic modeling to the aircraft response is investigated. A modal truncation method is introduced which is based on the significance of modes in characteristic loadcases. Moreover a fast time capable reduced order model is generated from the original model allowing fast time simulations with similar accuracy.

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In Categories: 2. IFASD 2015, Aeroelastic Response & Stability
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