An aerothermoelastic analysis framework with reduced-order modeling applied to composite panels in hypersonic flows. (April 2020)

• Record Type: Journal Article
• Authors: Huang, Daning; Friedmann, Peretz P.
• Is Part Of: Journal of fluids and structures. Volume 94(2019)
• Publication Date: 2020-04
• Subjects: Panel flutter -- Fluid–thermal-structure interaction -- Hypersonic aerothermoelasticity -- Reduced-order modeling -- Linearized stability analysis; Fluid-structure interaction -- Periodicals; Fluid mechanics -- Periodicals; Structural dynamics -- Periodicals; Structural analysis (Engineering) -- Periodicals; 620.106
• DOI: 10.1016/j.jfluidstructs.2020.102927
• Languages: English
• ISSNs: 0889-9746

Abstract

Abstract: This study describes the enhancement of a computational framework for aerothermoelasticity using novel model order reduction techniques and efficient coupling schemes. First, the fluid solver for hypersonic aerothermodynamics is accelerated using a reduced order model. The flexibility of the reduced order model is enhanced using a novel correction and scaling technique, which accounts for non-uniform temperature distribution, varying flight conditions and geometrical scales using analytical pointwise models. Secondly, based on the reduced order model, a tightly-coupled scheme and linearized stability analysis are developed for fast aerothermoelastic simulation of extended flight time and automatic identification of aerothermoelastic instabilities, respectively. The enhanced framework is accelerated by a factor of 1 0 4 so that near-real-time aerothermoelastic simulation is achieved. Finally, using the enhanced framework, the aerothermoelastic response of a generic skin panel is studied emphasizing the effect of flow orientation angle and material orthotropicity on the aerothermoelastic stability boundary. It is found that a combination of flow orientation angle and material orientation can significantly extend the aerothermoelastic stability boundary, i.e. the time elapsed before the onset of structural failure. Highlights: Aerothermoelastic response of a 3D stiffened skin panel in hypersonic flow is studied. Near-real-time high-fidelity hypersonic aerothermoelastic simulation is achieved. Aerothermoelastic instability is effectively identified using a linearized approach. Snap-through does not necessarily cause the unstable response of a skin panel. Orientations of flow and stiffeners impact the aerothermoelastic stability boundary.