Flight-Dynamics and Flutter Analysis and Control of an MDAO-Designed Flying-Wing Research Drone

Schmidt, David K.; Danowsky, Brian P.; Kotikalpudi, Aditya; Seiler, Peter; Kapania, Rakesh K.

doi:10.2514/6.2019-1816

Cited by 14 publications

(9 citation statements)

References 14 publications

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“…The flutter suppression control law is designed based on an appropriate control oriented model, [2,4,6,7]. The linear parameter-varying (LPV) framework, [8,9] can serve as a good approach to model ASE systems for control design since it can capture the parameter varying dynamics of the aircraft.…”

Section: Fig 1 Flexop Demonstrator Aircraftmentioning

confidence: 99%

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Active Flutter Mitigation Testing on the FLEXOP Demonstrator Aircraft

Takarics

Patartics

Luspay

et al. 2020

AIAA Scitech 2020 Forum

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The paper details the research and corresponding implementation and testing steps of the FLEXOP demonstrator aircraft. Within the EU funded project an unmanned demonstrator aircraft is built to validate the mathematical modelling, flight control design and implementation side of active flutter mitigation. In order to validate the different methods and tools developed in this project, a flight test campaign is planned, in which the design and manufacturing of stiff wings (-0), are compared with very flexible wings (-1) with active flutter control, to see the overall benefit vs. risk of such technology. The mathematical models of the aircraft are first developed using FEM and CFD tools, what are later reduced by model order reduction techniques. The high-fidelity models are updated using Ground Vibration Test results. Manufacturing tolerances and variations in aircraft parameters are captured by systematic modelling of parametric and dynamic uncertainties. Both the simulation environment and the control design framework use different modelling fidelity, what are described within the paper. Reduced models are developed using two distinctive methods, respecting the control design needs: top-down balanced LPV reduction and bottom-up structure preserving methods. Based on the reduced order models various control design techniques have been elaborated by the consortium partners. In particular DLR developed and implemented a modal control method using H2 optimal blends for inputs and outputs. University of Bristol developed structured H-infinity optimal control methods, while SZTAKI proposed a worst-case gain optimal method structured controller synthesis method handling parametric and complex uncertainties. After the brief introduction of hardware-in-the-loop test setup and the description of mission scenarios the implementation issues of the baseline and flutter controllers are discussed. DLR and SZTAKI flutter controllers are evaluated in a hybrid software-/ hardware-in-the-loop test setup as at this stage of development the latter can not tolerate the estimated delay of the hardware system but their comparison is advantageous before future developments. Recommendations on active flutter mitigation methods are given based on the experience of synthesis and implementation of these controllers. Flight test results will follow these experiments, once the flight testing of the flutter wing commences.

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Section: Fig 1 Flexop Demonstrator Aircraftmentioning

confidence: 99%

“…The FLEXOP demonstrator UAV is shown in Figure 1. Another research project dealing with active flutter suppression is the PAAW project in the US, [2][3][4][5].…”

Section: Introductionmentioning

confidence: 99%

Active Flutter Mitigation Testing on the FLEXOP Demonstrator Aircraft

Takarics

Patartics

Luspay

et al. 2020

AIAA Scitech 2020 Forum

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“…The autopilot uses the midboard flaps ( 3 , 3 ) like a classical elevator for pitch attitude control and the inboard flaps ( 2 , 2 ) like classical ailerons for roll attitude control and is similar to the one described in [55]. Consequently, the flutter suppression controller is assigned full authority over the body flaps and outboard flaps, i. e. 1 , 1 , 4 , and 4…”

Section: Control Design and Evaluationmentioning

confidence: 99%

Robust Modal Damping Control for Active Flutter Suppression

Theis

Pfifer

Seiler

2020

Journal of Guidance, Control, and Dynamics

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“…As the cost and complexity of the UAV system increases with aircraft size, small systems are the preferred choice. The Huginn [12] or MUTT [13] UAV demonstrators are examples for low frequency body freedom flutter demonstration platforms. In comparison, the FLEXOP demonstrator follows the idea of investigating classical wing flutter.…”

Section: Aeroelastic Problem Descriptionmentioning

confidence: 99%

“…x ∈ χ (12) with the flutter speed U f lutter defined as the first unstable aeroelastic eigenmode and the corresponding flutter frequency f f lutter . To normalize the two objectives, the fictive point utopia [U re f , f re f ] = f is used.…”

Section: Aeroelastic Design Optimizationmentioning

confidence: 99%

Aeroelastic Wing Planform Design Optimization of a Flutter UAV Demonstrator

Hermanutz

Hornung

2020

Aerospace

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In this work, a study to design a highly flexible flutter demonstrator for the development and testing of active flutter suppression is presented. Based on the UAV mission, a bi-objective design optimization problem can be formulated. The aeroelastic UAV characteristic and imposed constraints, defined by operational aspects and the structural integrity are described by surrogate modeling. Within the framework of the multi-criteria optimization, an approach to construct the equally spaced Pareto frontier with a new approach for non-convex problems is presented. An efficient Pareto configuration to meet a natural low speed and low frequency is identified and its main influencing design features are analyzed.

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Flight-Dynamics and Flutter Analysis and Control of an MDAO-Designed Flying-Wing Research Drone

Cited by 14 publications

References 14 publications

Active Flutter Mitigation Testing on the FLEXOP Demonstrator Aircraft

Active Flutter Mitigation Testing on the FLEXOP Demonstrator Aircraft

Robust Modal Damping Control for Active Flutter Suppression

Aeroelastic Wing Planform Design Optimization of a Flutter UAV Demonstrator

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