Global ETD Search
Search theses and dissertations gathered from participating repositories worldwide. Every result links back to the library that holds it. No account is needed.
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Showing 1 to 11 of 11 for “"Wing weight"”.
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Principal Component Regression for Construction of Wing Weight Estimation Models
… documents the lessons learned from fitting the wing weight data of 41 subsonic transports by three types of interpolation methods---least polynomial interpolation, radial basis function interpolation, and Kriging interpolation. The objective of this thesis is to develop an automatic procedure of …
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Structural Optimization and Design of a Strut-Braced Wing Aircraft
… Optimization (MDO) by implementing truss-braced wing concepts in combination with other advanced technologies and novel design innovations. A considerable reduction in drag can be obtained by using a high aspect ratio wing with thin airfoil sections and tip-mounted engines. However, such wing …
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Integrated aerodynamic-structural wing design optimization
… design optimization of aircraft wings are investigated. These procedures include efficient methods for optimization and sensitivity calculations that are applied to two specific design examples. The first is a subsonic transport aircraft with a composite forwardswept wing. The …
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Fusion of correlated information in multifidelity aircraft design optimization
… involves the construction of three separate wing weight estimation models that simplify different aspects of the wing sizing problem, thereby creating a scenario where model fidelities are not confined to a rigid hierarchy. The second stage involves the establishment of a formal definition of …
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Optimum Spanloads Incorporating Wing Structural Considerations And Formation Flying
… drag optimum load distribution can produce wing weight savings that result in airplane performance benefits. For a group of aircraft flying in formation, non-elliptic lift distributions can give high induced drag reductions both for the formation and for each airplane. For single aircraft, a …
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Wing Optimization Technique Based on Vortex Lattice Theory
… optimizing the geometric parameters of a general wing with NACA 65-210 airfoil sections under a low speed aerodynamic regime. This will be completed by performing an aerodynamic analysis based on vortex lattice theory with the objective of satisfying a performance index function. This function …
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Sizing Tool for Quadrotor Biplane Tailsitter UAS
… enable its further development, including: a QBT weight model, preliminary sizing framework, and vehicle analysis tools. The preliminary sizing tool presented here shows the advantage afforded by QBT designs in missions with aggressive cruise requirements, such as offshore wind turbine …
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Multidisciplinary Design Optimization of a Strut-Braced Wing Aircraft
… (MDO) to investigate the use of truss-braced wing concepts in concert with other advanced technologies to obtain a significant improvement in the performance of transonic transport aircraft. The truss topology introduces several opportunities. A higher aspect ratio and decreased wing thickness …
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EBF3GLWingOpt: A Framework for Multidisciplinary Design Optimization of Wings Using SpaRibs
… optimization of generalized aircraft wing structure has been developed. The concept of curvilinear stiffening members (spars, ribs and stiffeners) has been applied in the optimization of a wing structure. A global wing optimization framework EBF3WingOpt, which integrates the static …
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Multidisciplinary Design Optimization of Low-Noise Transport Aircraft
… capable of optimizing both a cantilever wing and a Strut-Braced-Wing (SBW) aircraft was developed. The framework employs aircraft analysis codes previously developed at the Multidisciplinary Design and Analysis (MAD) Center at Virginia Tech (VT). These codes have been improved here to …
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Multidisciplinary Optimization and Damage Tolerance of Stiffened Structures
… structural optimization of a cantilever aircraft wing with curvilinear spars and ribs and stiffeners is described. The design concept of reinforcing the wing structure using curvilinear stiffening members has been explored due to the development of novel manufacturing technologies like …