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aeroelastic modeling to investigate the wind-induced response of a multi-span transmission lines system

WIND AND STRUCTURES 2022年第2期34卷 231-257页

作者： Azzi, Ziad Elawady, Amal Irwin, Peter Chowdhury, Arindam Gan Shdid, Caesar Abi DDA Claims Management Miami FL 33178 USA Florida Int Univ Dept Civil & Environm Engn Miami FL 33199 USA Florida Int Univ Int Hurricane Res Ctr Extreme Events Inst Miami FL 33199 USA Lebanese Amer Univ Dept Civil Engn Beirut Lebanon

Transmission lines systems are important components of the electrical power infrastructure. However, these systems are vulnerable to damage from high wind events such as hurricanes. This study presents the results from a 1:50 scale aeroelastic model of a multi-span transmission lines system subjected to simulated hurricane winds. The transmission lines system considered in this study consists of three lattice towers, four spans of conductors and two end-frames. The aeroelastic tests were conducted at the NSF NHERI Wall of Wind Experimental Facility (WOW EF) at the Florida International University (FIU). A horizontal distortion scaling technique was used in order to fit the entire model on the WOW turntable. The system was tested at various wind speeds ranging from 35 m/s to 78 m/s (equivalent full-scale speeds) for varying wind directions. A system identification (SID) technique was used to evaluate experimental-based along-wind aerodynamic damping coefficients and compare with their theoretical counterparts. Comparisons were done for two aeroelastic models: (i) a self-supported lattice tower, and (ii) a multi-span transmission lines system. A buffeting analysis was conducted to estimate the response of the conductors and compare it to measured experimental values. The responses of the single lattice tower and the multi-span transmission lines system were compared. The coupling effects seem to drastically change the aerodynamic damping of the system, compared to the single lattice tower case. The estimation of the drag forces on the conductors are in good agreement with their experimental counterparts. The incorporation of the change in turbulence intensity along the height of the towers appears to better estimate the response of the transmission tower, in comparison with previous methods which assumed constant turbulence intensity. Dynamic amplification factors and gust effect factors were computed, and comparisons were made with code specific values. The resonance

关键词： aerodynamic damping aeroelastic modeling buffeting response dynamic amplification factors gust effect factors system identification transmission lines wall of wind

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Unsteady Lifting-Line Theory for Camber Morphing Wings State-Space aeroelastic modeling

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AIAA JOURNAL 2024年第12期62卷 4654-4664页

作者： Giansante, Riccardo Bernardini, Giovanni Gennaretti, Massimo Roma Tre Univ Dept Civil Comp Sci & Aeronaut Technol Engn Via Vasca Navale 79 I-00146 Rome Italy

A novel frequency-domain analytical-numerical model for the aerodynamic solution of camber morphing wings is developed. The model combines an unsteady lifting-line formulation with K & uuml;ssner-Schwarz aerodynamic theory to provide the pressure distribution and thus the transcendental aerodynamic matrix that relates the generalized aerodynamic forces to the Lagrangian coordinates of a given wing structural dynamics model. The state-space form of the aerodynamic loads is obtained from the rational matrix approximation of the aerodynamic matrix. This, combined with the wing structural dynamics operator, can readily provide the state-space form of the aeroelastic problem. To assess the accuracy of the proposed aerodynamic solution method, numerical investigations are performed. These consist of its application to several conventional wing configurations and wings with camber morphing, followed by the comparisons of the corresponding solutions with the predictions given by a well-validated panel-method solver for potential flows. These results are shown to be in very good agreement, thus demonstrating that the proposed approach can capture the effects due to wing tapering, sweep angle, and camber morphing, while requiring a remarkably lower computational effort. The excellent accuracy of a few-pole finite-state approximation of the aerodynamic matrix is finally proven for a swept wing with camber morphing.

关键词： Morphing Wing Unsteady Aerodynamic modeling aeroelastic modeling Reduced Order Model

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aeroelastic modeling to study the wind-induced response of a self-supported lattice tower

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ENGINEERING STRUCTURES 2021年 245卷 112885-112885页

作者： Azzi, Ziad Elawady, Amal Irwin, Peter Chowdhury, Arindam Gan Shdid, Caesar Abi Florida Int Univ Dept Civil & Environm Engn Miami FL 33174 USA Florida Int Univ Extreme Events Inst Int Hurricane Res Ctr Miami FL 33174 USA Lebanese Amer Univ Dept Civil Engn Beirut Lebanon

The results from a 1:50 scale aeroelastic model of a self-supported steel lattice tower subjected to simulated hurricane winds are presented. The lattice tower considered is a typical structure that is used as part of a tower insulator-conductor system for electrical transmission infrastructure. The aeroelastic tests were conducted at the NSF Wall of Wind Experimental Facility (WOW EF) at the Florida International University (FIU). The tower was tested at various wind speeds ranging from 50 m/s to 92 m/s (equivalent full-scale speeds) for varying wind directions. Two system identification (SID) techniques were utilized to evaluate along-wind aerodynamic damping and compare with theoretical estimates. The SID techniques were also utilized to evaluate crosswind aerodynamic damping. A buffeting analysis was conducted to estimate the response of the tower and compare it to measured values at the WOW. Drag and moment coefficients were calculated from the measured responses, and the dynamic amplification factors (DAF) as well as gust effect factors were computed. The analysis required consideration of the variation of the turbulence intensity along the height of the tower in the buffeting analytical equations. The drag coefficients are shown to agree with values proposed in the current standards. However, there might be a need to introduce base moment coefficients in lattice tower design. The resonance contribution is shown to reach a maximum of 18% of the peak response of the tower.

关键词： aeroelastic modeling Transmission tower Wall of wind System identification Aerodynamic damping Buffeting response Drag coefficient Moment coefficient Dynamic amplification factors

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aeroelastic modeling and CFD Simulation of Wind-Tunnel Scale Aspect Ratio 13.5 Common Research Model

Aeroelastic Modeling and CFD Simulation of Wind-Tunnel Scale...

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作者： Xiong, J Nguyen, N Stanford, B. K Bartels, R. E National Aeronautics and Space Administration Washington DC. American Institute of Aeronautics and Astronautics Reston Virginia United States Wyle (United States) El Segundo California United States Ames Research Center Mountain View California United States Langley Research Center Hampton Virginia United States

This paper presents an aeroelastic modeling and simulation study of an aspect ratio 13.5 wind-tunnel scale Common Research Model (CRM) with distributed flaps. A vortex-lattice VSPAERO model of the CRM model is developed. A transonic small disturbance/integral boundary layer correction method is implemented in the VSPAERO model to account for the transonic and viscous flow effects. The structural deformation of the CRM model is calculated using a NASTRAN equivalent beam model. The VSPAERO model is coupled to the NASTRAN equivalent beam model to provide a rapid aero-structural analysis. A validation of the VSPAERO aeroelastic model is conducted by comparing the results to FUN3D CFD aeroelastic simulation results. An aerodynamic database is generated using the developed VSPAERO aeroelastic model for the real-time drag optimization and maneuver load alleviation study of the wind-tunnel scale CRM model.

关键词： Cfd aeroelastic modeling Crm

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Comparison of aeroelastic modeling and Robust Flutter Analysis of a Typical Section

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IFAC-PapersOnLine 2016年第17期49卷 409-414页

作者： Iannelli, A. Marcos, A. Lowenberg, M. University of Bristol BS8 1TR United Kingdom

A comparison of robust flutter analyses within the µ framework is presented. The chosen test bed is the typical section with unsteady aerodynamic loads, which enables basic modeling features to be captured and so extend the gained knowledge to practical problems treated with modern techniques. The two main approaches to pose the LFT problem are investigated and features such as numerical accuracy and physical uncertainty description are assessed. A criterion is proposed to correlate the families of plants originated by the uncertainty description of the aerodynamic operator when different approximation algorithms are employed. © 2016

关键词： Uncertainty analysis Approximation algorithms Flexible structures Flutter (aerodynamics) aeroelastic modeling Flutter analysis Numerical accuracy Practical problems Robust flutter analysis Robust stability Structured singular values Unsteady aerodynamic load

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Data-Driven Approach to the Development of an aeroelastic Flutter Precursor

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AIAA JOURNAL 2025年第1期63卷 174-183页

作者： Meivar, Boaz Karpel, Moti Technion Israel Inst Technol IL-32000 H_efa Israel

This paper presents a novel algorithm for aeroelastic flutter early detection. Two new features for flutter onset detection are presented. Flutter early warning is accomplished using only measured signals, with essentially no prior knowledge needed about the aircraft or the flutter mechanism involved. The algorithm consists of three stages: 1) extraction of regularity features, 2) calibration by addition of white noise to nominal measurements, and 3) thresholding. Four types of datasets were used: a) synthetic data, b) simulated data generated using aeroelastic response simulations to stochastic gusts, c) measured data from a wind tunnel experiment, and d) flight test data including actual flutter onsets. The algorithm was shown to be able to flag an impending flutter event before critical onset occurs. (The Python code for paper is available at https://***/bmeivar/flutter.)

关键词： Flight Testing Wind Tunnels aeroelastic modeling Probability Density Functions Power Spectral Density Gaussian Mixture Models Flutter Analysis Aircraft Flutter Data Science

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Guaranteed Cost Gain-Scheduled Control of Typical aeroelastic Section Model

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2025年第3期48卷 714-722页

作者： Pereira, Renan L. Gonzalez, Pedro J. Silvestre, Flavio J. Aeronaut Inst Technol Elect Engn Div BR-12228900 Sao Jose Dos Campos Brazil Tech Univ Berlin Flight Control & Aeroelast FMRA D-10587 Berlin Germany Tech Univ Berlin Flight Control & Aeroelast FMRA Marchstr 12 D-10587 Berlin Germany

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On the Dynamic Behavior of Wings Incorporating Floating Wingtip Fuel Tanks

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JOURNAL OF AIRCRAFT 2024年第3期61卷 785-800页

作者： Healy, Fintan Courcy, Joe De Gu, Huaiyuan Rezgui, Djamel Cooper, Jonathan Wilson, Thomas Castrichini, Andrea Univ Bristol Dept Aerosp Engn Bristol BS8 1TR England Univ Bristol Dept Aerosp Engn Aerosp Engn Bristol BS8 1TR England Airbus Operat Ltd Bristol BS34 7QQ England Airbus Operat Ltd Flight Phys Bristol BS34 7QQ England

Recent studies have shown that semi-aeroelastic hinge devices can enable larger aircraft wingspans. Such a device would be folded on the ground to meet airport width restrictions, locked during cruise for optimal aerodynamic performance, and released during maneuvers to alleviate flight loads. In contrast, this paper uses a wind tunnel experiment to study the aeroelastic behavior of floating wingtip fuel tanks. This device consists of a freely floating wingtip with an additional mass attached in the form of a liquid-filled fuel tank. The static aeroelastic results show that altering the fuel tank's filling level and position allows the wingtip to float at an optimal angle for aerodynamic efficiency across various angles of attack and fuel masses. Additionally, this paper shows that, with careful selection of the mass distribution of the wingtip, dynamic load alleviation comparable to the semi-aeroelastic hinge concept can be achieved during turbulence and one-minus-cosine encounters. Furthermore, the effect of fluid motion is shown to reduce incremental loads during random turbulence encounters by up to 10%;however, it has a negligible impact on the response to one-minus-cosine encounters. Such results are also confirmed by a numerical model incorporating a simple reduced-order fluid sloshing model.

关键词： Reduced Order Modelling Aerodynamic Force Aerodynamic Performance Wind Tunnel Models Aircraft Wing Design Fuel Sloshing Effects Body Reference Frame Euler Bernoulli Beam Theory Aircraft Wing Components aeroelastic modeling

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Wind Tunnel Testing of Tethered Inflatable Wings

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JOURNAL OF AIRCRAFT 2024年第6期61卷 1717-1734页

作者： Desai, Siddhant Schetz, Joseph A. Kapania, Rakesh K. Gupta, Rikin Virginia Tech Kevin T Crofton Dept Aerosp & OceanEngineering Blacksburg VA 24060 USA Toyota Res Inst North Amer Future Mobil Res Dept Ann Arbor MI 48105 USA Ansys Inc Canonsburg PA 15317 USA Supernal Washington DC USA

A wind tunnel testing approach for tethered inflatable wings is presented. Use cases for such wings range from airborne wind energy systems to high-altitude communication platforms. The tests were conducted for two tethered inflatable wings, one made out of nylon fabric and the other an ultra-high-molecular-weight polyethylene fabric. They were tested within a speed range of 15-32.5 m/s for three tether attachment configurations. Stereo photogrammetry data, force and moment measurements, and wake pressure measurements were recorded for each speed and test configuration. These measurements provide an experimental database for aeroelastic model validation and comparison with high-fidelity computational fluid dynamics studies. The effects of wing fabric material and tether attachment configurations on aerodynamic performance were explored and found to have a profound impact. These tests also highlight the possibility of passive aeroelastic tailoring of the wing configuration to achieve desired aerodynamic performance in the form of high lift and load alleviation. Some testing challenges and possible sources of measurement uncertainty are also discussed.

关键词： Wind Tunnel Models Aerodynamic Performance Aerodynamic Testing aeroelastic modeling Pressure Coefficient Inflatable Aircraft Flexible Wings Airborne Wind Energy Crosswind Kite Power Kite Tether

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Model Reference Control for Reducing Pilot-Induced Oscillation Tendencies

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2025年第2期48卷 226-239页

作者： Newton, Loren J. Kroo, Ilan M. Stanford Univ Dept Aeronaut & Astronaut Stanford CA 94305 USA

Lags between pilot inputs and aircraft responses may lead to a pilot-vehicle system entering into a pilot-induced oscillation. A model reference control element can compensate for these lags, avoiding pilot-induced oscillations and improving tracking performance. Neural network compensation drives the combined controller-plant system to exhibit a closed-loop response similar to that of an idealized system, immune to the factors that trigger pilot-induced oscillations. Actuator rate limiting has been a historically ubiquitous cause of pilot-induced oscillations;meanwhile, aeroelastic effects pose a threat to future lightweight, flexible aircraft designs. Model reference control can reduce pilot-induced oscillation tendencies caused by either of these factors. This paper presents the methods used to train the model reference controller, including conditions for system stability under model reference control. It then showcases results from a pair of simulation experiments applying the control design to compensate for rate limiting and aeroelasticity, respectively. Results demonstrate that the model reference control scheme reduces pilot-induced oscillation tendencies and improves closed-loop tracking performance.

关键词： Artificial Neural Network Lyapunov Equation aeroelastic modeling Aerospace Engineering Aircraft Dynamic Modes Flight Control Pilot Induced Oscillation Model Reference Control

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