214. NON LINEAR AEROELASTIC ANALYSIS OF JOINED WING CONFIGURATIONS

Department: Structural Engineering
Faculty Advisor(s): David Benson | Luciano Demasi
Award(s): Department Best Poster | Best Literature Review Award

Primary Student
Name: Rauno Cavallaro
Email: racavall@ucsd.edu
Phone: 619-594-3513
Grad Year: 2014

Abstract
The main objective of this research is the study of the aeroelastic behavior of unconventional configurations, with a major focus on joined wing vehicles. Civil transport aircraft of the future are requested to improve their performances and to achieve a significant reduction of Direct Operating Costs, noxious emissions and noise. The problem of reducing Direct Operative Costs will not be solved without a significant improvement of aircraft efficiency, which can be hardly obtained by an optimization of conventional aircraft. Hence, new non-conventional aircraft layouts configurations provide an attractive alternative. As pointed out by different leading aeronautical industries (such as Boeing, Lockheed Martin, Airbus, etc), one of these configurations is the joined wing. The main potential benefits range from a reduced induced drag to a more efficient structural design. Other interesting advantages are expected for the flight mechanics/dynamics behavior and capabilities, for engine integration possibilities, and for the operational impact. One of the most advanced and relatively unexplored fields is the aeroelasticity of joined wings airplanes. Nowadays, the aeroelastic response has not yet been well understood and, therefore, represents an interesting phenomenon to be further explored. The particular wing layout of joined wings is responsible for strong structural geometric non linearities, which are relevant even for small angles of attack and attached flows. More in detail, this research aims to analyze the static (divergence) and dynamic (flutter) aeroelastic instabilities and investigate the post-critical behavior with particular emphasis on the so called limit cycle oscillation (post-flutter analysis). The analysis will be conducted for realistic wing box configurations, represented with high fidelity structural models. Aeroelastic tailoring by means of composite materials will be also investigated.

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