Javon C. Farao, Arnaud G. Malan, Francesco Gambioli
DOI Number: N/A
Conference number: IFASD-2017-064
This study details the development of a computational full aircraft model (FAM) to assess the non-linear response of an aircraft during an aerodynamic gust. A FAM comprises numerous components viz., the structure, aerodynamics and inertial loads. The focus of this study is to implement a geometrically non-linear reduced-order model (ROM) for the wing and assess its aeroelastic response against standard linear approaches. The NASA common research model (CRM) wing is modeled by three-dimensional Timoshenko beam elements in both the linear and non-linear regime. Linear responses are derived from standard linear modal analysis procedures. The geometrically non-linear beam element ROM is solved via quadratic mode shape components in the modal domain. These components are extracted from linear mode shapes in a novel approach for elastic beam elements. A representative gust load is applied to the structure and the responses are compared to the linear approach. It was found that QMS modal methodology offers improved accuracy by retaining the overall wing length even when loading produces a vertical displacement of 35% with respect to wing span. The extension caused by linear modeling exceeds 14%, while the QMS approach reduces it to less than 3%.