Static and Dynamic Performance of a Morphing Trailing Edge Concept with High-Damping Elastomeric Skin

Arena, Maurizio; Nagel, Christoph; Pecora, Rosario; Schorsch, Oliver; Concilio, Antonio; Dimino, Ignazio

doi:10.3390/aerospace6020022

Cited by 12 publications

(5 citation statements)

References 36 publications

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“…In this work, the Nastran finite element solver was employed for all computational modal analyses, also known as normal modes analysis, which is a widely employed solver in the aerospace industry, such as in aircraft [51], rotorcraft [52], and spacecraft [33] analyses. The assembled models were meshed after defining the material properties of each constituent part.…”

Section: Computational Modal Analysis (Cma) Methodologymentioning

confidence: 99%

Modal Analysis of Conceptual Microsatellite Design Employing Perforated Structural Components for Mass Reduction

2022

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Mass reduction is a primary design goal pursued in satellite structural design, since the launch cost is proportional to their total mass. The most common mass reduction method currently employed is to introduce honeycomb structures, with space qualified composite materials as facing materials, into the structural design, especially for satellites with larger masses. However, efficient implementation of these materials requires significant expertise in their design, analysis, and fabrication processes; moreover, the material procurement costs are high, therefore increasing the overall program costs. Thus, the current work proposes a low-cost alternative approach through the design and implementation of geometrically-shaped, parametrically-defined metal perforation patterns, fabricated by standard processes. These patterns included four geometric shapes (diamonds, hexagons, squares, and triangles) implemented onto several components of a structural design for a conceptual satellite, with a parametric design space defined by two scale factors and also two aspect ratio variations. The change in the structure’s fundamental natural frequency, as a result of implementing each pattern shape and parameter variation, was the selection criterion, due to its importance during the launcher selection process. The best pattern from among the four alternatives was then selected, after having validated the computational methodology through implementing experimental modal analysis on a scaled down physical model of a primary load-bearing component of the structural design. From the findings, a significant mass reduction percentage of 23.15%, utilizing the proposed perforation concept, was achieved in the final parametric design iteration relative to the baseline unperforated case while maintaining the same fundamental frequency. Dynamic loading analysis was also conducted, utilizing both the baseline unperforated and the finalized perforated designs, to check its capability to withstand realistic launch loads through applying quasi-static loads. The findings show that the final perforated design outperformed the baseline unperforated design with respect to the maximum displacements, maximum Von Mises stresses, and also the computed margin of safety. With these encouraging outcomes, the perforated design concept proved that it could provide an opportunity to develop low-cost satellite structural designs with reduced mass.

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Section: Computational Modal Analysis (Cma) Methodologymentioning

confidence: 99%

Modal Analysis of Conceptual Microsatellite Design Employing Perforated Structural Components for Mass Reduction

2022

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“…Even when retracted, the trailing edge hinges still produce a turbulent boundary layer. Numerous researchers believe that the laminar flow technology has the maximum potential to reduce drag and to avoid flow separation [16,17]. For this goal, the wings require the design of thin airfoils, seamless high-quality surfaces and variable droop leading edges.…”

Section: Outline Of the Researchmentioning

confidence: 99%

Aerodynamic Design Optimization of a Morphing Leading Edge and Trailing Edge Airfoil–Application on the UAS-S45

et al. 2021

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This work presents an aerodynamic optimization method for a Droop Nose Leading Edge (DNLE) and Morphing Trailing Edge (MTE) of a UAS-S45 root airfoil by using Bezier-PARSEC parameterization. The method is performed using a hybrid optimization technique based on a Particle Swarm Optimization (PSO) algorithm combined with a Pattern Search algorithm. This is needed to provide an efficient exploitation of the potential configurations obtained by the PSO algorithm. The drag minimization and the endurance maximization were investigated for these configurations individually as two single-objective optimization functions. The aerodynamic calculations in the optimization framework were performed using the XFOIL solver with flow transition estimation criteria, and these results were next validated with a Computational Fluid Dynamics solver using the Transition Shear Stress Transport (SST) turbulence model. The optimization was conducted at different flight conditions. Both the DNLE and MTE optimized airfoils showed a significant improvement in the overall aerodynamic performance, and MTE airfoils increased the efficiency of CL3/2/CD by 10.25%, indicating better endurance performance. Therefore, both DNLE and MTE configurations show promising results in enhancing the aerodynamic efficiency of the UAS-S45 airfoil.

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“…Alsaidi et al [19,20] analyzed skins for multi-axial camber morphing wings made of lattice structures. Arena et al [21] developed a multi-segment adaptive trailing edge morphing wing with skin made of hard segments and elastomeric layers supported by foam pieces at the locations of the hinges of the trailing edge segments. They analyzed the design statically and dynamically, computationally and experimentally.…”

Section: Introductionmentioning

confidence: 99%

Parametric Study of a Composite Skin for a Twist-Morphing Wing

Bishay

Aguilar

2021

Aerospace

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Although the benefits of morphing wings have been proven in many studies in the last few decades, the wing skin design remains one of the challenges to advancing and implementing the morphing technology. This is due to the conflicting design requirements of high out-of-plane stiffness to withstand aerodynamic loads and low in-plane stiffness to allow morphing with the available actuation forces. Advancements in the design of hybrid and flexible composites might allow for design solutions that feature this balance in stiffness required for this application. These composites offer new design parameters, such as the number of plies, the fiber-orientation angle of each ply in the skin laminate, and the spatial distribution of the plies on the skin surface. This paper presents a parametric study of a composite skin for a twist-morphing wing. The skin is made of periodic laminated composite sections, called “Twistkins”, integrated in an elastomeric outer skin. The twisting deformation is localized in the elastomeric sections between the Twistkins. The design parameters considered are the number of plies in the composite Twistkins, the fiber-orientation angle of the plies, the torsional rigidity of the elastomer, the width ratio, and the number of elastomeric sections. The computational analysis results showed that the torsional compliance can be increased by increasing the width ratio, decreasing the number of elastomeric sections, number of composite plies and the elastomer’s torsional rigidity. However, this would also lead to a decrease in the out-of-plane stiffness. The nonlinearity and rates at which these parameters affect the skin’s behavior are highlighted, including the effect of the fiber-orientation angle of the laminate plies. Hence, the study guides the design process of this twist-morphing skin.

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Static and Dynamic Performance of a Morphing Trailing Edge Concept with High-Damping Elastomeric Skin

Cited by 12 publications

References 36 publications

Modal Analysis of Conceptual Microsatellite Design Employing Perforated Structural Components for Mass Reduction

Modal Analysis of Conceptual Microsatellite Design Employing Perforated Structural Components for Mass Reduction

Aerodynamic Design Optimization of a Morphing Leading Edge and Trailing Edge Airfoil–Application on the UAS-S45

Parametric Study of a Composite Skin for a Twist-Morphing Wing

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