Active Flutter Suppression Techniques in Aircraft Wings

Ghiringhelli, G.L.; Lanz, M.; Mantegazza, Paolo; Ricci, Sergio

doi:10.1016/b978-0-12-012752-8.50007-6

Cited by 9 publications

(5 citation statements)

References 66 publications

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“…From a general dynamic point of view such a recovery makes available a dynamically residualized model [9] that adequately recovers both the poles and the zeros of interest [10]. A precise static recovery affords a better evaluation of the actuator forces, so allowing to better check their design limitations and saturations.…”

Section: Structural Modelmentioning

confidence: 99%

Modeling and control of massively actuated, magnetically levitated, adaptive mirrors

Manetti

Morandini

Mantegazza

et al. 2010

2010 IEEE International Conference on Control Applications

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The successful design of non contact, magnetically levitated, massively actuated deformable mirrors and their control system requires the use of medium to high fidelity hybrid multidisciplinary simulation models, encompassing: deformable structures, fluid dynamics of the air film interposed between the mirror and its reference backplane, sensor and actuator dynamics, the control system. Such models must serve the diverse needs for the analysis, design and verification of a fully decentralized control solution and to simulate all of on the field operational phases including initial feedback design, the identification of the static feed-forward matrix and control self tuning. The paper presents the related modeling techniques along with a few results and experimental correlations validating various aspects of the presented capabilities.

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Section: Structural Modelmentioning

confidence: 99%

Modeling and control of massively actuated, magnetically levitated, adaptive mirrors

Manetti

Morandini

Mantegazza

et al. 2010

2010 IEEE International Conference on Control Applications

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“…Static Output Control (SOF) [41] is a simple and effective approach to aeroservoelastic control law synthesis that has been already studied and proven successful for active flutter suppression (AFS) and gust load alleviation (GLA) [42], [43], [44]. In the implementation of Static Output Feedback (SOF), the control input, 𝑼(𝑠), is obtained from measured responses, 𝒀(𝑠), by means of a constant gain matrix, 𝑮(𝑠), as 𝑼(𝑠) = 𝑮(𝑠) 𝒀(𝑠).…”

Section: A Static Output Feedback (Sof)mentioning

confidence: 99%

Wind Tunnel System for Active Flutter Suppression Research: Overview and Insights

Ricci¹,

Toffol²,

Gaspari³

et al. 2022

AIAA Journal

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The paper describes the development of a new state of the art large wind tunnel model for active flutter suppression studies as well as the supporting techniques used in tests focused on the effects of uncertainty. Design guidelines and the resulting aeroelastic characteristics of the model are covered together with representative test results. Those would allow other researchers working in this area to develop control laws for the new model and evaluate them. A number of important lessons and insight are reported regarding the design of the model, the level of success of commonly used mathematical modelling techniques to capture its behaviour, sources of analysis / test correlation discrepancies, multi-function utilization of control surfaces for both system identification and flutter suppression, active flutter suppression testing safety, and techniques for estimating by tests of the robustness of closed-loop active aeroservoelastic systems. The new system has made it possible to repeatedly "push" the actively controlled model, using various flutter suppression control laws, safely, to the actual flutter limit in tests numerous times. This capability

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“…The chosen approach leads to a description of the control systems, in the frequency domain, as equivalent mass, damping, and stiffness matrices, thus avoiding a state-space representation of the unsteady aerodynamic forces. 12 In fact, some control algorithms, such as linear quadratic Gaussian control, have not been considered because they require a representation of the unsteady aerodynamic forces in the time domain that is not yet implemented in AIDIA aeroservoelastic modules. The linearized open-loop aeroelastic response equations, in the Laplace transform domain s, are …”

Section: Active Control Systemsmentioning

confidence: 99%

“…Because of the s-k (usually known as p-k) approximation implied in Eq. (12), the solution of the flutter problem is formulated as a nonstandard eigenproblem that is solved by a continuation method unifying analysis and sensitivity calculations in a very effective way. 13 …”

Section: Flutter Analysismentioning

confidence: 99%

Integrated Servostructural Optimization in the Design of Aerospace Systems

Bindolino

Ricci

Mantegazza

1999

Journal of Aircraft

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Multidisciplinary optimization is playing a fundamental role in the design of aerospace vehicles because of the need to simultaneously take into account the strong interactions among different disciplines to ensure an efficient design. This paper presents a multimodel, multiobjective formulation of the servostructural optimization problem specifically tailored toward airplane preliminary design. Structural and control design variables are simultaneously treated along with constraints and objective functions related to different aeroservoelastic and structural performances. Reduced-order models, based on finite element method/ boundary element method, are adopted to reduce the computational burden of the optimization process.

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Active Flutter Suppression Techniques in Aircraft Wings

Cited by 9 publications

References 66 publications

Modeling and control of massively actuated, magnetically levitated, adaptive mirrors

Modeling and control of massively actuated, magnetically levitated, adaptive mirrors

Wind Tunnel System for Active Flutter Suppression Research: Overview and Insights

Integrated Servostructural Optimization in the Design of Aerospace Systems

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