Flight control design for a highly flexible flutter demonstrator

Luspay, Tamás; Ossmann, Daniel; Wuestenhagen, Matthias; Teubl, Daniel; Baár, Tamás; Pusch, Manuel; Kier, Thiemo; Waitman, Sérgio; Ianelli, Andrea; Marcos, Andrés; Vanek, Bálint; Lowenberg, Mark H

doi:10.2514/6.2019-1817

Cited by 22 publications

(24 citation statements)

References 17 publications

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“…Thereby, the numerical values of the model as well as the resulting controller can be provided herein. For realistic physical applications, the reader is referred to [19], [20] and [21], where the proposed blending approach is successfully applied to different aeroelastic systems.…”

Section: Numerical Examplementioning

confidence: 99%

$\mathcal{H}_{2}$ -Optimal Blending of Inputs and Outputs for Modal Control

Pusch

Ossmann

2020

IEEE Trans. Contr. Syst. Technol.

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For many dynamical systems it is required to actively control individual modes, especially when these are lightly damped or even unstable. In order to achieve a maximum control performance, these systems are often augmented with a large number of control inputs and measurement outputs. To overcome the challenge of choosing an adequate combination of input and output signals for modal control, an H2-optimal isolation of modes via blending of inputs and outputs is proposed in this article. Enforcing an explicit mode decoupling, the approach enables controlling individual modes with simple single-input single-output controllers. A numerically efficient algorithm is derived for the joint computation of the interdependent input and output blending vectors. The effectiveness of the proposed approach is demonstrated by increasing the modal damping of an aeroelastic system.Index Terms-mode decoupling, modal control, over-actuated and over-sensed systems

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Section: Numerical Examplementioning

confidence: 99%

$\mathcal{H}_{2}$ -Optimal Blending of Inputs and Outputs for Modal Control

Pusch

Ossmann

2020

IEEE Trans. Contr. Syst. Technol.

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“…This allows a fast and precise actuation by the flutter controller while limiting the effect of mechanical freeplay and hysteresis associated with reduction mechanisms. A fourth-order model for this actuator was identified in [18], and is given by…”

Section: Actuators and Sensors Modelsmentioning

confidence: 99%

“…Its aim is to develop multidisciplinary aircraft design capabilities by achieving a closer coupling of wing aeroelasticity and flight control systems in the design process. A flexible-wing remotely piloted demonstrator is designed in the framework of this project [15,16] and will be used to achieve flight-test validation of aeroelastically tailored design [17] and AFS [18,19]. A concept drawing of the demonstrator is presented in Fig.…”

Section: Introductionmentioning

confidence: 99%

H∞ Control Design for Active Flutter Suppression of Flexible-Wing Unmanned Aerial Vehicle Demonstrator

Waitman

Marcos

2020

Journal of Guidance, Control, and Dynamics

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“…Such high order LPV model is unsuitable for control synthesis. Either LPV model order reduction techniques [26][27][28][29][30][31], or a bottom-up modeling approach can be applied as presented in Reference [32] to obtain a control oriented, reduced-order model. The present paper focuses on the latter.…”

Section: Bottom-up Modeling Of the Mini Mutt Aircraftmentioning

confidence: 99%

“…ASE models, however, are usually of very high order for control design. Model order reduction of LPV systems is still not a straightforward task [26][27][28][29][30][31]. In order to overcome these challenges, the ASE models are built using the "bottom-up" modeling approach [32].…”

Section: Introductionmentioning

confidence: 99%

Grid-Based and Polytopic Linear Parameter-Varying Modeling of Aeroelastic Aircraft with Parametric Control Surface Design

Mocsányi

Takarics

Kotikalpudi

et al. 2020

Fluids

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The main direction of aircraft design today and in the future is to achieve more lightweight and higher aspect ratio airframes with the aim to improve performance and to reduce operating costs and harmful emissions. This promotes the development of flexible aircraft structures with enhanced aeroelastic behaviour. Increased aeroservoelastic (ASE) effects such as flutter can be addressed by active control technologies. Control design for flutter suppression heavily depends on the control surface sizing. Control surface sizing is traditionally done in an iterative process, in which the sizing is determined considering solely engineering rules and the control laws are designed afterwards. However, in the case of flexible vehicles, flexible dynamics and rigid body control surface sizing may become coupled. This coupling can make the iterative process lengthy and challenging. As a solution, a parametric control surface design approach can be applied, which includes limitations of control laws in the design process. For this a set of parametric models is derived in the early stage of the aircraft design. Therefore, the control surfaces can be optimized in a single step with the control design. The purpose of this paper is to describe as well as assess the developed control surface parameterized ASE models of the mini Multi Utility Technology Testbed (MUTT) flexible aircraft, designed at the University of Minnesota. The ASE model is constructed by integrating aerodynamics, structural dynamics and rigid body dynamics. In order to be utilized for control design, control oriented, low order linear parameter-varying (LPV) models are developed using the bottom-up modeling approach. Both grid- and polytopic parametric LPV models are obtained and assessed.

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Flight control design for a highly flexible flutter demonstrator

Cited by 22 publications

References 17 publications

$\mathcal{H}_{2}$ -Optimal Blending of Inputs and Outputs for Modal Control

$\mathcal{H}_{2}$ -Optimal Blending of Inputs and Outputs for Modal Control

H∞ Control Design for Active Flutter Suppression of Flexible-Wing Unmanned Aerial Vehicle Demonstrator

Grid-Based and Polytopic Linear Parameter-Varying Modeling of Aeroelastic Aircraft with Parametric Control Surface Design

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