Implementation of Structural Sizing Strategies for Morphing Wing Structures Using Common Toolsets

2008 ◽  
Author(s):  
Michael Skillen ◽  
William Crossley
Keyword(s):  
Morphing Wing ◽  
Wing Structures

Topology Synthesis of Distributed Actuation Systems for Morphing Wing Structures

2007 ◽  
Vol 44 (4) ◽  
pp. 1205-1213 ◽  
Author(s):  
Daisaku Inoyama ◽  
Brian P. Sanders ◽  
James J. Joo
Keyword(s):  
Morphing Wing ◽  
Wing Structures ◽  
Actuation Systems

scholarly journals Ground Structures-Based Topology Optimization of a Morphing Wing Using a Metaheuristic Algorithm

Metals ◽  
2021 ◽  
Vol 11 (8) ◽  
pp. 1311
Author(s):  
Seksan Winyangkul ◽  
Kittinan Wansaseub ◽  
Suwin Sleesongsom ◽  
Natee Panagant ◽  
Sumit Kumar ◽  
...  
Keyword(s):  
Topology Optimization ◽  
Optimization Problems ◽  
Future Research ◽  
Structural Constraints ◽  
Metaheuristic Algorithm ◽  
Morphing Wing ◽  
Aircraft Wing ◽  
Multi Objective ◽  
Wing Structures ◽  
Wing Structure

This paper presents multi-objective topology and sizing optimization of a morphing wing structure. The purpose of this paper is to design a new aircraft wing structure with a tapered shape for ribs, spars, and skins including a torsion beam for external actuating torques, which is anticipated to modify the aeroelastic characteristic of the aircraft wing using multi-objective optimization. Two multi-objective topology optimization problems are proposed employing ground element structures with high- and low-grid resolutions. The design problem is to minimize mass, maximize difference of lift effectiveness, and maximize the buckling factor of an aircraft wing subject to aeroelastic and structural constraints including lift effectiveness, critical speed, and buckling factors. The design variables include aircraft wing structure dimensions and thickness distribution. The proposed optimization problems are solved by an efficient multi-objective metaheuristic algorithm while the results are compared and discussed. The Pareto optimal fronts obtained for all tests were compared based on a hypervolume metric. The objective function values for Case I and Case II at 10 selected optimal solutions exhibit a range of structural mass as 115.3216–411.6250 kg, 125.0137–440.5869 kg, lift effectiveness as 1.0514–1.1451, 1.0834–1.1639 and bucking factor as 38.895–1133.1864 Hz, 158.1264–1844.4355 Hz, respectively. The best results reveal unconventional aircraft wing structures that can be manufactured using additive manufacturing. This research is expected to serve as a foundation for future research into multi-objective topology optimization of morphing wing structures based on the ground element framework.

scholarly journals Elastic composite skin for a pure shear morphing wing structures

2014 ◽  
Vol 26 (3) ◽  
pp. 352-363 ◽  
Author(s):  
Rui Wu ◽  
Jian Sun ◽  
Zhizhong Chang ◽  
Rui Bai ◽  
Jinsong Leng
Keyword(s):  
Pure Shear ◽  
Morphing Wing ◽  
Elastic Composite ◽  
Wing Structures

A Novel Basic Conceptual Design and Analysis of a Morphing Wing Using Re-Entrant Hexagonal Cellular Structure

2011 ◽  
Vol 308-310 ◽  
pp. 548-552
Author(s):  
Wen Jun Dong ◽  
Qin Sun
Keyword(s):  
Cellular Structure ◽  
Lift Coefficient ◽  
Spanwise Direction ◽  
Morphing Wing ◽  
Relative Thickness ◽  
Coefficient Increase ◽  
Wing Structures ◽  
Wing Structure ◽  
Wing Morphing ◽  
Multiple Missions

A novel morphing wing structure is designed based on the concept of re–entrant hexagonal cellular structure. The re–entrant hexagonal cellular structure is adopted because of its ability to undergo large overall displacements with limited deformation in spanwise direction. The presented unconventional cellular based morphing wing structure can satisfy the requirements of configuration changing while wing morphing, which can makes the aircraft remain at the most effective state and perform multiple missions effectively and efficiently. Numerical analyses were performed to exploit the presented wing structures using commercial finite element method. It was shown that the morphing wing structure examined here had can change its relative thickness as much as 5%, which can make lift coefficient increase significantly. Therefore, the presented structure can be served as a smart variable wing structure and has much effective and efficient aerodynamic performance.

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