Design of Shape-Adaptive Deployable Slat-Cove Filler for Airframe Noise Reduction

Arena, Gaetano; Groh, Rainer; Pirrera, Alberto; Turner, Travis L.; Scholten, William; Hartl, Darren J.

doi:10.2514/1.c036070

Cited by 4 publications

(3 citation statements)

References 47 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…However, this narrative has been challenged more recently, and instabilities have been exploited for novel functionalities. This has led to the creation of well-behaved nonlinear structures [5] such as shape-adaptive structures [6][7][8][9], deployable structures [10][11][12], zero or negative stiffness structures [13,14], energy harvesters [15], as well as non-destructive testing techniques [16][17][18][19][20].…”

Section: Introductionmentioning

confidence: 99%

Structural function from sequential, interacting elastic instabilities

et al. 2023

View full text Add to dashboard Cite

Elastic instabilities have traditionally been considered a failure mechanism; however, recent years have seen numerous studies exploiting instabilities as a means to achieve structural functionality. By contrast, interacting instabilities and compound buckling are still largely viewed as a failure mechanism. In this paper, we show that interacting instabilities can also be exploited to achieve bespoke functionality. We focus on ‘sequential instabilities’, whose associated critical points cannot both lie on a fundamental equilibrium path. We obtain sequential instabilities by combining canonical bifurcations, (e.g. limit point, pitchfork) as building-blocks. Initially, this concept is explored through simple bar-and-spring models that are found to have several properties not exhibited by the building blocks from which they are constructed. Further, the utility of the building block approach, and that of sequential, interacting instabilities, is demonstrated through the development of a morphing structure which must rapidly deploy after a critical input displacement is attained, and meet specific post-deployment stiffness requirements. Two design concepts are proposed, each comprising building blocks to mirror the fundamental working principles identified through the bar-and-spring models. Finite-element models of the design solutions are presented, demonstrating how the designs positively use sequential, interacting instabilities in order to meet the challenging requirements of the application. This work extends the contextual framework of instabilities that can be used to create structures with novel functionality.

show abstract

Section: Introductionmentioning

confidence: 99%

Structural function from sequential, interacting elastic instabilities

et al. 2023

View full text Add to dashboard Cite

show abstract

“…Many authors investigate ways to suppress these negative effects, in order to achieve good flight characteristics with a lighter structure [4][5][6][7][8][9]. Some authors focus on developing structural optimization methods, modifying the aircraft structure to have an acceptable aeroelastic response, while retaining a low weight [4,9]. Another proposed passive method of improving the aeroelastic response of the aircraft is to use optimized tuned mass dampers [5].…”

Section: Introductionmentioning

confidence: 99%

“…These structural and control law optimizations are highly iterative processes, requiring either a lot of computing power or low-order computationally inexpensive aeroelasticity models. Some authors use aeroelasticity models based on computational fluid dynamics (CFD) [4,7]. Because of its accuracy and versatility, CFD is a commonly used tool in both aerospace and other disciplines [10][11][12][13][14].…”

Section: Introductionmentioning

confidence: 99%

Aeroelasticity Model for Highly Flexible Aircraft Based on the Vortex Lattice Method

Dagilis,

Kilikevičius

2023

Aerospace

View full text Add to dashboard Cite

With the increasing use of composite materials in aviation, structural aircraft design often becomes limited by stiffness, rather than strength. As a consequence, aeroelastic analysis becomes more important to optimize both aircraft structures and control algorithms. A low computational cost aeroelasticity model based on VLM and rigid-body dynamics is proposed in this work. UAV flight testing is performed to evaluate the accuracy of the proposed model. Two flight sections are chosen to be modeled based on recorded aerodynamic surface control data. The calculated accelerations are compared with recorded flight data. It is found that the proposed model adequately captures the general flight profile, with acceleration peak errors between −6.2% and +8.4%. The average relative error during the entire flight section is 39% to 44%, mainly caused by rebounds during the beginning and end of pull-up maneuvers. The model could provide useful results for the initial phases of aircraft control law design when comparing different control algorithms.

show abstract

Functionalising buckling for structural morphing in kinetic façades: Concepts, strategies and applications

Khezri¹,

Rasmussen²

2022

Thin-Walled Structures

View full text Add to dashboard Cite

Design of Shape-Adaptive Deployable Slat-Cove Filler for Airframe Noise Reduction

Abstract: to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp. *EPSRC Doctoral Prize Fellow, Bristol Composites Institute (ACCIS); currently Materials Applications Engineer, Rolls-Royce; gaetano.arena@ rolls-royce.com.

Cited by 4 publications

References 47 publications

Structural function from sequential, interacting elastic instabilities

Structural function from sequential, interacting elastic instabilities

Aeroelasticity Model for Highly Flexible Aircraft Based on the Vortex Lattice Method

Functionalising buckling for structural morphing in kinetic façades: Concepts, strategies and applications

Contact Info

Product

Resources

About