The Effects of Aeroelastic Tailoring on Flight Dynamic Stability

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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.
Original languageEnglish
Title of host publication2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc. (AIAA)
Number of pages16
ISBN (Electronic)978-1-62410-532-6
DOIs
Publication statusPublished - 2018
Event59th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference - Kissimmee, United States
Duration: 8 Jan 201812 Jan 2018
Conference number: 59
https://doi.org/10.2514/MSDM18

Conference

Conference59th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
CountryUnited States
CityKissimmee
Period8/01/1812/01/18
Internet address

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  • Cite this

    Natella, M., Wang, X., & De Breuker, R. (2018). The Effects of Aeroelastic Tailoring on Flight Dynamic Stability. In 2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference American Institute of Aeronautics and Astronautics Inc. (AIAA). https://doi.org/10.2514/6.2018-0191