Passive Gust Loads Alleviation in a Truss-Braced Wing Using an Inerter-Based Device

Szczyglowski, Christopher Patrick; Neild, Simon A; Titurus, Branislav; Jiang, Jason Zheng; Coetzee, Etienne

doi:10.2514/1.c035452

Cited by 12 publications

(4 citation statements)

References 33 publications

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“…The University of Bristol Ultra-Green (BUG) cantilevered wing design was inspired by the strut-supported highaspect-ratio wing of the NASA SUGAR Volt aircraft configuration [30], with the main aim of studying the nonlinear aeroelastic effects associated with large wing deflections [9,31,32]. The BUG half-wing FEM model (48564 degrees of freedom) has a span of 25.89m and is shown in Fig.…”

Section: B Representative Gfem Of a High-aspect-ratio Wingmentioning

confidence: 99%

Slender-Wing Beam Reduction Method for Gradient-Based Aeroelastic Design Optimization

Stodieck¹,

Cooper²,

Neild³

et al. 2018

AIAA Journal

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The efficiency and scope of aeroelastic wing optimization strategies can be increased using analysis-specific structural idealizations, such as high-fidelity models for detailed stress analyses and low-fidelity models for aeroelastic analyses. In this work, a numerical method is presented that enables efficient and accurate reduction of a high-fidelity finite element model to a Timoshenko beam-based model with lumped masses. The result is a representation based on 13 independent physical beam stiffness parameters per element. The method also yields analytical beam sensitivities with respect to changes in the high-fidelity model. Using these, an approach is suggested for integrating the beam reduction method into a gradient-based multidisciplinary design optimization architecture. The reduction technique is demonstrated on a simplified wing-box and on the University of Bristol Ultra-Green aircraft configuration wing. The effects of unbalanced skin composite laminates, rotated internal ribs, varying wing taper and sweep, and wing boundary constraints on the wing stiffness are shown to be captured with sufficient accuracy for static and dynamic aeroelastic analysis purposes. The accuracy

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Section: B Representative Gfem Of a High-aspect-ratio Wingmentioning

confidence: 99%

Slender-Wing Beam Reduction Method for Gradient-Based Aeroelastic Design Optimization

Stodieck¹,

Cooper²,

Neild³

et al. 2018

AIAA Journal

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“…Here, it is shown that the maximum relative velocity is achieved during the 9m gust. This is because the short gusts have the largest bandwidth [38], meaning that they excite the higher frequency modes of the structure which, generally speaking, are truss-dominated modes. Furthermore, due to the higher bandwidth of the short gusts the excitation frequency is much larger which gives a higher velocity and acceleration for a given displacement.…”

Section: Gust Response Of the Baseline Aeroelastic Modelmentioning

confidence: 99%

“…For the model considered in this study, it appears that the jury-strut is an inappropriate location for a device that influences the behaviour of the outboard bending mode. It is possible that a rotational device co-located at the strut-wing joint, as in [38], would provide better performance in terms of alleviating the outboard bending.…”

Section: B Tuned-inerter-dampermentioning

confidence: 99%

Passive Gust Load Alleviation In a Truss-Braced Wing Using an Inerter-Based Device

Szczyglowski¹,

Neild²,

Titurus³

et al. 2018

2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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This paper presents a novel method for gust loads alleviation in a truss-braced wing in which an inerter-based device located in the truss structure is used to reduce peak-loads during a discrete "1-cosine" gust. Recent studies have shown that gust loads and flutter are critical to the wing sizing and the overall performance of the truss-braced wing concept and it is understood that without additional efforts to mitigate against these effects the benefits of the truss-braced wing concept may be significantly reduced. It is demonstrated that the use of a tunable device known as a tuned inerter damper allows specific vibration modes to be targeted during the gust response, resulting in a reduction of 25% in root bending moment and 5% in root torque when tuned to the second global wing bending mode. Furthermore, it is noted that the force coefficients of the tuned inerter damper are small in comparison with the pure damper device and could be feasible within the scope of an aerospace application.

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“…Recently, it has been proposed that the truss could serve not simply as static support, but also to reduce dynamic gust loads by inserting a vibration absorber into one of the struts, either as a traditional suspension system [5], or as an inerter-based device [6]. The geometric nonlinearities stemming from the greater flexibility associated with HAR wings, however, mean that the traditional modelling methods, based on linear elastic and aerodynamic theory, are not necessarily adequate, and can lead to conservative structural designs [7], and to inaccurate estimations of the flutter speeds [3,8].…”

Section: Introductionmentioning

confidence: 99%

Real-Time Hybrid Testing of Strut-Braced Wing Under Aerodynamic Loading Using an Electrodynamic Actuator

et al. 2020

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Real-Time Hybrid Simulation (RTHS) is an experimental framework that allows the testing of components or substructures under realistic, dynamic boundary conditions, by imposing the reactions calculated from a model of the rest of the assembly through one or more actuators. In the context of rapid prototyping of mechanical components, RTHS could be used to explore the design space of a device while at the same time physically validating its interaction with other components of the final assembly from the early stages of the design-to-production cycle.In this work, RTHS was applied for the first time to the investigation of aerodynamic gust loading alleviation devices in a highly flexible strut-braced wing. The model wing was taken as the physical substructure and tested in a low-speed wind tunnel equipped with gust generators. The load alleviation device was simulated through a real-time feedforward-feedback controller, and its response imposed via an electro-mechanical

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Passive Gust Loads Alleviation in a Truss-Braced Wing Using an Inerter-Based Device

Cited by 12 publications

References 33 publications

Slender-Wing Beam Reduction Method for Gradient-Based Aeroelastic Design Optimization

Slender-Wing Beam Reduction Method for Gradient-Based Aeroelastic Design Optimization

Passive Gust Load Alleviation In a Truss-Braced Wing Using an Inerter-Based Device

Real-Time Hybrid Testing of Strut-Braced Wing Under Aerodynamic Loading Using an Electrodynamic Actuator

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