The Effects of Aeroelastic Tailoring on Flight Dynamic Stability

Conference paper (2018)

Authors

M. Natella Aerospace Structures & Computational Mechanics - Aerospace Engineering
R. De Breuker Aerospace Structures & Computational Mechanics - Aerospace Engineering
Research Group
Aerospace Structures & Computational Mechanics (Aerospace Engineering) (TU Delft)
Copyright: © 2018 M. Natella, Xuerui Wang, R. De Breuker
DOI: https://doi.org/10.2514/6.2018-0191
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Published Date

2018

Language

English

Reuse Rights

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Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Aerospace Structures & Computational Mechanics

Abstract

This paper presents a unified framework for aeroelastic tailoring of free-flying aircraft with composite wings. A continuous-time state-space model is used to describe the flow. The 3D composite wing structures is condensed into a Timoshenko beam model by means of a cross-sectional modeler. The aerodynamic and structural models are closely coupled with the six degrees of freedom flight dynamic equations of motion in the state-space formulation. This paper refers to the clamped-wing aeroelastic tailoring as classic aeroelastic tailoring. Hence, the term aeroelastic tailoring will point at the novel approach that includes free-flying aeroelastic phenomena into the optimization process. The emphasis of the present paper is to show the effects of aeroelastic tailoring on body-freedom flutter and flight dynamic stability at large. The results of this paper will be used in the further development of aeroelastic tailoring practices for composite aircraft design.