This work is a development of previous work where improvements on the computational models, both aerodynamic and structural, have been introduced. This paper presents the work done in designing a morphing wing concept for a small experimental unmanned aerial vehicle (UAV), in order to improve the vehicle's performance over its intended speed range. The wing is designed with a multidisciplinary design optimization tool where an aerodynamic shape optimization code coupled with a structural morphing model is used to obtain a set of optimal wing shapes for minimum drag at different flight speeds. The optimization procedure is described as well as structural modelling. The aerodynamic shape optimization code, which uses a viscous 2-dimensional panel method formulation coupled with a non-linear lifting-line algorithm and a sequential quadratic programming (SQP) optimization algorithm, is suitable for preliminary wing design optimization tasks. The morphing concept, based on changes in wing planform shape and wing section shape achieved by extending spars and telescopic ribs, is explained in detail. Comparisons between initial wing performance, optimal morphing wing performance and the performance of the wing obtained from the coupled aerodynamic-structural solution are presented. Estimates for the performance enhancements achieved by the UAV when fitted with this new morphing wing are also presented. Some conclusions on this concept are addressed with comments on the benefits and drawbacks of the morphing mechanism design. Observations from wind tunnel testing of a simplified morphing wing prototype are discussed.
Optimization of a morphing wing based on coupled aerodynamic and structural constraints
Optimierung eines veränderbaren Tragflügels auf Basis gekoppelter aerodynamischer und struktureller Randbedingungen
2007
27 Seiten, 29 Quellen
Conference paper
English
Optimization of a Morphing Wing Based on Coupled Aerodynamic and Structural Constraints
Online Contents | 2009
|British Library Conference Proceedings | 2007
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