Relevant bibliographies by topics / Wings - Load Alleviation

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  1. Journal articles
  2. Dissertations / Theses
  3. Book chapters
  4. Conference papers

Academic literature on the topic 'Wings - Load Alleviation'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 September 2023

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Journal articles on the topic "Wings - Load Alleviation"

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Krüger, Wolf R., Yasser M. Meddaikar, Johannes K. S. Dillinger, Jurij Sodja, and Roeland De Breuker. "Application of Aeroelastic Tailoring for Load Alleviation on a Flying Demonstrator Wing." Aerospace 9, no. 10 (September 21, 2022): 535. http://dx.doi.org/10.3390/aerospace9100535.

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This article presents the application of aeroelastic tailoring in the design of wings for a flying demonstrator, as well as the validation of the design methodology with flight test results. The investigations were performed in the FLEXOP project (Flutter Free Flight Envelope Expansion for Economical Performance Improvement), funded under the Horizon 2020 framework. This project aimed at the validation of methods and tools for active flutter control, as well as at the demonstration of the potential of passive load alleviation through composite tailoring. The technologies were to be demonstrated by the design, manufacturing and flight testing of an unmanned aerial vehicle of approximately 7 m wingspan. This article addresses the work towards the load alleviation goals. The design of the primary load-carrying wing-box in this task is performed using a joint DLR–TU Delft optimization strategy. Two sets of wings are designed in order to demonstrate the potential benefits of aeroelastic tailoring—first, a reference wing in which the laminates of the wing-box members are restricted to balanced and symmetric laminates; second, a tailored wing in which the laminates are allowed to be unbalanced, hence allowing for the shear–extension and bending–torsion couplings essential for aeroelastic tailoring. Both designs are numerically optimized, then manufactured and extensively tested to validate and improve the simulation models corresponding to the wing designs. Flight tests are performed, the results of which form the basis for the validation of the applied aeroelastic tailoring approach presented in the article.
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Castrichini, A., V. Hodigere Siddaramaiah, D. E. Calderon, J. E. Cooper, T. Wilson, and Y. Lemmens. "Preliminary investigation of use of flexible folding wing tips for static and dynamic load alleviation." Aeronautical Journal 121, no. 1235 (November 21, 2016): 73–94. http://dx.doi.org/10.1017/aer.2016.108.

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ABSTRACTA recent consideration in aircraft design is the use of folding wing-tips with the aim of enabling higher aspect ratio aircraft with less induced drag while also meeting airport gate limitations. This study investigates the effect of exploiting folding wing-tips in flight as a device to reduce both static and dynamic loads. A representative civil jet aircraft aeroelastic model was used to explore the effect of introducing a wing-tip device, connected to the wings with an elastic hinge, on the load behaviour. For the dynamic cases, vertical discrete gusts and continuous turbulence were considered. The effects of hinge orientation, stiffness, damping and wing-tip weight on the static and dynamic response were investigated. It was found that significant reductions in both the static and dynamic loads were possible. For the case considered, a 25% increase in span using folding wing-tips resulted in almost no increase in loads.
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Liu, Haojie, and Xiao Wang. "Aeroservoelastic design of piezo-composite wings for gust load alleviation." Journal of Fluids and Structures 88 (July 2019): 83–99. http://dx.doi.org/10.1016/j.jfluidstructs.2019.04.010.

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Krishnamurthy, Vikram, and Vega Handojo. "Structural design process and subsequent flight mechanical evaluation in preliminary aircraft design: demonstrated on passenger ride comfort assessment." CEAS Aeronautical Journal 12, no. 2 (April 2021): 457–69. http://dx.doi.org/10.1007/s13272-021-00505-x.

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AbstractNew fuel-efficient aircraft designs have high aspect ratio wings. Consequently, those aircraft are more flexible. Additionally, load alleviation functions are implemented to reduce the structural loads, which results in further reductions of the structural stiffness. At the same time, the structural design impacts other disciplines in preliminary aircraft design, especially flight mechanics. For example, it is important to know how at that design stage such flexible aircraft with load alleviation affect passenger ride comfort in turbulent flight. For an efficient design process, it is essential to answer such questions with accurate multi-disciplinary tools and methods as early as possible to minimize development risk and avoid costly and time-consuming redesign loops. Current available tools and methods are not accurate enough for this task. To address this issue, the DLR MONA based design and the TUB flight mechanical assessment tool MITRA are linked to investigate the impact of the structural design on specific flight mechanical assessments such as passenger ride comfort. This is particularly interesting since the implemented load alleviation functions are designed to reduce loads, and not explicitly to improve passenger ride comfort. By conducting this assessment for a particular aircraft configuration, more insight into passenger ride comfort and the key contributors can be gained during preliminary design. This paper describes the combined toolchain and its application on a generic long-range reference aircraft to investigate the effects of load alleviation functions on passenger ride comfort and discusses the results.
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Ajaj, Rafic M., Erick I. Saavedra Flores, Mohammadreza Amoozgar, and Jonathan E. Cooper. "A Parametric Study on the Aeroelasticity of Flared Hinge Folding Wingtips." Aerospace 8, no. 8 (August 10, 2021): 221. http://dx.doi.org/10.3390/aerospace8080221.

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This paper presents a parametric study on the aeroelasticity of cantilever wings equipped with Flared Hinge Folding Wingtips (FHFWTs). The finite element method is utilized to develop a computational, low-fidelity aeroelastic model. The wing structure is modelled using Euler–Bernoulli beam elements, and unsteady Theodorsen’s aerodynamic strip Theory is used for aerodynamic load predictions. The PK method is used to estimate the aeroelastic boundaries. The model is validated using three rectangular, cantilever wings whose properties are available in literature. Then, a rectangular, cantilever wing is used to study the effect of folding wingtips on the aeroelastic response and stability boundaries. Two scenarios are considered for the aeroelastic analysis. In the first scenario, the baseline, rectangular wing is split into inboard and outboard segments connected by a flared hinge that allows the outboard segment to fold. In the second scenario, a folding wingtip is added to the baseline wing. For both scenarios, the influence of fold angle, hinge-line angle (flare angle), hinge stiffness, tip mass and geometry are assessed. In addition, the load alleviation capability of FHFWT is evaluated when the wing encounters discrete (1-cosine) gusts. Finally, the hinge is assumed to exhibit cubic nonlinear behavior in torsion, and the effect of nonlinearity on the aeroelastic response is assessed and analyzed for three different cases.
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An, Chao, Chao Yang, Changchuan Xie, and Yang Meng. "Gust Load Alleviation including Geometric Nonlinearities Based on Dynamic Linearization of Structural ROM." International Journal of Aerospace Engineering 2019 (May 12, 2019): 1–20. http://dx.doi.org/10.1155/2019/3207912.

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This paper describes a framework for an active control technique applied to gust load alleviation (GLA) of a flexible wing, including geometric nonlinearities. Nonlinear structure reduced order model (ROM) and nonplanar double-lattice method (DLM) are used for structural and aerodynamic modeling. The structural modeling method presented herein describes stiffness nonlinearities in polynomial formulation. Nonlinear stiffness can be derived by stepwise regression. Inertia terms are constant with linear approximation. Boundary conditions and kernel functions in the nonplanar DLM are determined by structural deformation to reflect a nonlinear effect. However, the governing equation is still linear. A state-space equation is established in a dynamic linearized system around the prescribed static equilibrium state after nonlinear static aeroelastic analysis. Gust response analysis can be conducted subsequently. For GLA analysis, a classic proportional-integral-derivative (PID) controller treats a servo as an actuator and acceleration as the feedback signal. Moreover, a wind tunnel test has been completed and the effectiveness of the control technology is validated. A remote-controlled (RC) model servo is chosen in the wind tunnel test. Numerical simulation results of gust response analysis reach agreement with test results. Furthermore, the control system gives GLA efficacy of vertical acceleration and root bending moment with the reduction rate being over 20%. The method described in this paper is suitable for gust response analysis and control strategy design for large flexible wings.
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Kilimtzidis, Spyridon, and Vassilis Kostopoulos. "Static Aeroelastic Optimization of High-Aspect-Ratio Composite Aircraft Wings via Surrogate Modeling." Aerospace 10, no. 3 (March 6, 2023): 251. http://dx.doi.org/10.3390/aerospace10030251.

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The race towards cleaner and more efficient commercial aviation demands novel designs featuring improved aerodynamic and structural characteristics, the main pillars that drive aircraft efficiency. Among the many proposed and introduced, the increase in the aspect ratio of the wings enables greater fuel efficiency by reducing induced drag. Nevertheless, such structures are characterised by elevated flexibility, aggravating static and dynamic aeroelastic phenomena. Consequently, the preliminary and conceptual design and optimization stages using high-fidelity numerical tools is rendered extremely intricate and prohibitive in terms of computational cost. Low-fidelity tools, contrastingly, enable computational-burden alleviation. In our approach, a computational framework for the low-fidelity steady-state static aeroelastic optimization of a composite high-aspect-ratio commercial aircraft wing via surrogate modelling is proposed. The methodology starts with the development of the 3D panel method as well of the elements of the surrogate model. The design variables, objective function and constraints which formulate the optimization problem are then provided. Moreover, comparison against rigid aerodynamics indicate the significant load-alleviation capabilities of the present case study. The effect of structural nonlinearities is also explored. The optimization framework is executed and optimal laminates for the structural members are obtained. The optimal structure was deemed critical in panel buckling.
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Breitenstein, C., and R. Radespiel. "Flow simulation of the flight manoeuvres of a large transport aircraft with load alleviation." Aeronautical Journal 126, no. 1298 (October 28, 2021): 681–709. http://dx.doi.org/10.1017/aer.2021.93.

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AbstractA new method for predicting manoeuvre loads on a large transport aircraft with a swept-back wing and a load alleviation system based on control surface deflections is developed. For this purpose, three-dimensional Reynolds-averaged Navier–Stokes (RANS) simulations of the rigid wing–fuselage configuration are performed while the aerodynamics of the tailplane are estimated by means of handbook methods. For a closer analysis, different quasi-steady pitching manoeuvres are chosen based on the CS-25 regulations. One of these manoeuvres is also simulated with active load alleviation, leading to a reduction in the wing-root bending moment by more than 40%. Besides demonstrating the potential of the considered load alleviation system, it is shown which manoeuvres are especially critical in this context and which secondary effects come along with load alleviation.
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Ye, Bo, Youxu Yang, and Zhiyong Cheng. "Flare folding wing tips for static and gust loads alleviation." Journal of Physics: Conference Series 2459, no. 1 (March 1, 2023): 012071. http://dx.doi.org/10.1088/1742-6596/2459/1/012071.

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Abstract The Passive gust load alleviation device can effectively simplify the control system by relying on the adaptive deformation of the structure. This research examines the influence of using folding wingtips during flight as a means of reducing static loads and gusty loads. Effects of hinge direction, wing-tip weight, stiffness and wing-tip centre of gravity on static and gust alleviation performance has been examined. The results show that the flare folding wing-tip can significantly reduce the static load and gust load of the aircraft. In a static aeroelastic trim analysis, a folding wingtip can increase span by 25% without increasing the wing root bending moment and decrease the trim angle of attack by 0.14°. In the gust response analysis, the maximum bending moment of wing root can be decrease by nearly 50% compared with the fixed wing-tip, only 17% higher than the baseline model without a wing-tip.
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Gatto, A., P. Bourdin, and M. I. Friswell. "Experimental Investigation into the Control and Load Alleviation Capabilities of Articulated Winglets." International Journal of Aerospace Engineering 2012 (2012): 1–15. http://dx.doi.org/10.1155/2012/789501.

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An experimental investigation into the real-time flow and control characteristics of a flying wing with articulated winglets is described in this paper. The philosophy of the concept centres around the use of active, in-flight adjustment of each wing's winglet dihedral angle, both as a primary means of aircraft roll control (single winglet actuation) and though smaller equal and simultaneous winglet deflections, tailor and alleviate main wing load. Results presented in this paper do provide good evidence of the concept's ability to adequately perform both tasks, although for the current chosen wing/winglet configuration, roll control authority was unable to achieve, per unit of control surface deflection, the same level of performance set by modern aileron-based roll control methodologies.
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Dissertations / Theses on the topic "Wings - Load Alleviation"

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Gauthier, Perron Sébastien. "Passive gust load alleviation through bend-twist coupling of composite beams on typical commercial airplane wings." Thesis, Massachusetts Institute of Technology, 2012. http://hdl.handle.net/1721.1/77111.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2012.
Cataloged from department-submitted PDF version of thesis. This electronic version was submitted and approved by the author's academic department as part of an electronic thesis pilot project. The certified thesis is available in the Institute Archives and Special Collections.
Includes bibliographical references (p. 89-91).
The effects of bend-twist coupling on typical commercial airplane wings are evaluated. An analytical formulation of the orthotropic box beam bending stiffness matrix is derived by combining Euler-Bernoulli beam theory and classical laminated plate theory. The out-of-plane displacement due to the twist of the cross section is modeled by a bilinear warping function. The analytical model is evaluated and validated against finite element analysis and experimental results. The model can accurately predict the twist and deformation of orthotropic box beams within 15% of the benchmarking data and provides best results for beams of higher aspect ratios and with layup angles below 30 degrees. Airplane level aero-structural simulations are performed in ASWING using models of Boeing's 737 and 777. The composite wings are sized for a static load increase and a set of gusts as prescribed by the FAA. Using unbalanced laminates to generate the structural coupling leads to significant strength penalties if the loading is not parallel to the laminate's fiber directions. The optimal laminate angle for which the weight saving benefits of bend-twist coupling are maximized corresponds to the wing's principal stress direction. Beyond that angle, the wings will exhibit more coupling but the laminate strength penalties are too large to be overcomed by the benefits of bend-twist coupling. The addition of coupling to the wings leads to reductions in peak spanwise bending moments in the order of 20% to 45%. It is demonstrated that the mechanism behind this reduction involves increased wing tip twist which alleviates part of the outboard wing load. This ultimately results in weight savings in the order of 2% to 4%. The findings suggest that the benefits of bend-twist coupling are more important on heavier airplanes such as the 777 due to the effects of the cube-square law.
by Sébastien Gauthier Perron.
S.M.
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Abudaram, Yaakov Jack. "Wind tunnel testing of load-alleviating membrane wings." [Gainesville, Fla.] : University of Florida, 2009. http://purl.fcla.edu/fcla/etd/UFE0041340.

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Skinner, Shaun N. "Study of a C-wing configuration for passive drag and load alleviation." Thesis, University of Glasgow, 2018. http://theses.gla.ac.uk/30778/.

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Non-planar wing configurations are often hypothesised as a means for improving the aerodynamic efficiency of large transport aircraft; C-wings may have the ability to exploit and unify drag reduction, aeroelasticity, and dynamics and control but their capacity to do so is ambiguous. The aim of this work is to provide an experimental demonstration with the aim of verifying the C-wing configuration’s potential application for drag and load alleviation. The successful application of a C-wing system for improving the aerodynamic efficiency depends upon the ability to construct the wing system such that a sufficiently low root bending moment and parasitic drag is maintained, relative to an equivalent planar wing system. This was facilitated by the development of a structured genetic algorithm (sGA) optimisation architecture capable of utilising fundamental aerodynamic theory, design specifications, and experimental facility constraints to provide non-arbitrary wing topology designs. The optimisation procedure aided in the design of a planar wing analogous of a typical mid-sized transport commercial aircraft wing topology, representing a 10% scale model. From this baseline design the sGA reconfigured the outboard 26% of the wing to independently form a C-wing topology, increasing the planforms aerodynamic efficiency by 74.5%. A modular wingtip semi-span model was designed to house the sGA planar and Cwing designs inside the University of Glasgow’s de Havilland wind tunnel for tests at Re = 1.5x10^6. A number of experimental techniques adopted, such as force/moment measurements, laser-Doppler vibrometry, PCB piezoelectric accelerometry, direct image correlation (DIC), surface flow visualizations, and stereoscopic particle image velocimetry (SPIV), provide insight into the semi-span model and wingtip arrangement structural dynamics and flow field physics. Aerodynamic performance metrics show that despite the C-wing operating with a 19.1% higher wing wetted area, a peak total drag reduction of 9.5% at a = 6^o is achieved in addition to a 1.1% reduction in the wing root bending moment for equivalent lift. Study of the near field wake indicated that this was achieved by the C-wing establishing a low vorticity spiral core vortex with accelerated vortex decay properties. The C-wing has also been found capable of passively attenuating buffet induced vibrations of the main-wing by up to 68.6%.
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Miller, Simon James. "Adaptive wing structures for aeroelastic drag reduction and loads alleviation." Thesis, University of Manchester, 2011. https://www.research.manchester.ac.uk/portal/en/theses/adaptive-wing-structures-for-aeroelastic-drag-reduction-and-loadsalleviation(562181ed-7153-44cb-b0c7-9bfe1f79ae0f).html.

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An investigation into two distinct novel adaptive structures concepts is performed with a view to improving the aerodynamic efficiency of aircraft wings.The main focus of the work is on the development of a rotating spars concept that enables the adaptive aeroelastic shape control of aircraft wings in order to reduce drag. By altering the orientation of the internal wing structure, it becomes possible to control the flexural and torsional stiffnesses of the wing, as well as the position of the elastic axis. It follows then that control of the aeroelastic deformation is also possible. Consequently, the aerodynamic performance can be tailored, and more specifically the lift-to-drag ratio can be maximised through continuous adjustment of the structure.To gain a thorough understanding of the effect of the concept on a wing, an assumed modes static aeroelastic model is developed, and studies are performed using this. These studies establish guidelines with regards to the effective design of a wing incorporating the rotating spars concept. The findings of these studies are then used to establish a baseline design for a wind tunnel model. A finite element model of this is constructed and aeroelastic analyses are used to improve the model and arrive at the final experimental wing design. The wind tunnel tests confirm analytical trends and the robustness of an approach to automaticallyadapt the structure to maintain an aerodynamic performance objective.The remainder of the work investigates the application of an all-moving wing tip device with an adaptive torsional stiffness attachment as a passive loads alleviation system. Through consideration of the attachment stiffness and position, it is possible to tune the device throughout flight in order to minimise the loads that are introduced into the aircraft structure in response to a gust or manoeuvre. A dynamic aeroelastic wing model incorporating the device is developed and used to perform parameter studies; this gives an insight into the sizing and placement of the device. Next, a finite element representation of a conceptual High Altitude Long Endurance (HALE) aircraft is used as a baseline platform for the device. Aeroelastic analyses are performed for the baseline and modified models to investigate the effect of the attachment stiffness and position on the gust response and aeroelastic stability of the system. The reduced loading within thestructure of the modified aircraft then enables the model to be optimised in order to reduce the mass of the aircraft.
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Castrichini, Andrea. "Parametric assessment of a folding wing-tip device for aircraft loads alleviation." Thesis, University of Bristol, 2017. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.720822.

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Agarwal, R. K. "Study Of Aerodynamic Effectiveness Of Wing Tip Sails For Gust Load Alleviation." Thesis, 2004. http://hdl.handle.net/2005/1139.

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Book chapters on the topic "Wings - Load Alleviation"

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Fujimori, A., H. Ohta, and P. N. Nikiforuk. "CONTROLLER DESIGNS OF A GUST LOAD ALLEVIATION SYSTEM FOR AN ELASTIC RECTANGULAR WING." In Automatic Control in Aerospace 1989, 153–58. Elsevier, 1990. http://dx.doi.org/10.1016/b978-0-08-037027-9.50024-0.

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Conference papers on the topic "Wings - Load Alleviation"

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Gauthier Perron, Sebastien, and Mark Drela. "Passive Gust Load Alleviation Through Bend-Twist Coupling of Composite Beams on Typical Commercial Airplane Wings." In 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-1490.

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Yin, HuiWei, Zhigang Wu, and Chao Yang. "Design and Analysis of a Wind Tunnel Test Model System for Rolling Maneuver Load Alleviation of Flying Wings." In 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1860.

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Roessler, Christian, Philipp Stahl, Franz Sendner, Andreas Hermanutz, Sebastian Koeberle, Julius Bartasevicius, Vladyslav Rozov, et al. "Aircraft Design and Testing of FLEXOP Unmanned Flying Demonstrator to Test Load Alleviation and Flutter Suppression of High Aspect Ratio Flexible Wings." In AIAA Scitech 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-1813.

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Zarepoor, Masoud, and Onur Bilgen. "Cross-Well Actuation of Bistable Structures Subjected to Noise Disturbance." In ASME 2017 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/smasis2017-3751.

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Large loads due to fluid-structure interaction can lead to high bending stresses and fatigue failure in wings and wind turbine blades. A solution for the mentioned problem is using a bistable composite laminate for load alleviation. A bistable composite laminate is capable of attaining two statically stable shapes, and it can be designed to alleviate a critical load, such as wind gust, by snapping from one stable position to the other. Piezocomposite actuators can be used to reverse the snap-through and bring back the structure to its original optimal aerodynamic shape, after the gust load is alleviated. However, there will always be a limit on the size of the piezocomposite actuator used; hence, severe force and energy constraints exist to achieve the snap-through. In this context, this paper focuses on the minimum required actuation energy for performing snap-through of a bistable structure. The paper shows how the required energy for cross-well transfer varies as a function of damping ratio and frequency ratio at specific harmonic force amplitude when the system is externally disturbed with a band-limited noise signal. A band-limited noise signal is chosen to model external/ambient disturbances. This paper uses the Duffing-Holmes equation as a one-degree-of-freedom representative model of a bistable structure. This equation is numerically solved to calculate the required energy for cross-well oscillation under different system and forcing conditions. Various non-dimensional parameters are used to highlight interesting phenomena. It is found that the domain of low energy regions decreases by increasing the level of noise.
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Scaramal, Mariano, Umberto Saetti, and Joseph Horn. "Load Alleviation Control using Dynamic Inversion with Direct Load Feedback." In Vertical Flight Society 77th Annual Forum & Technology Display. The Vertical Flight Society, 2021. http://dx.doi.org/10.4050/f-0077-2021-16792.

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This paper addresses the use of dynamic inversion with direct load feedback to provide combined load alleviation and flight control of rotorocraft. The method is applied to a compound utility rotorcraft with similar airframe properties as a UH-60A along with a lifting wing. The controller makes use of flaperons and horizontal stabilizer in addition to the conventional main rotor / tail rotor blade pitch controls to track pilot commands while also minimizing pitch link loads. The nonlinear simulation is developed in FLIGHTLAB® with structural models of the rotor blades and control system. This model must be linearized to a linear time-invariant (LTI) system to support linear Dynamic Inversion control design. The vehicle dynamics and critical fatigue load are modeled with a linear time-periodic (LTP) model which is converted via harmonic decomposition into a high-order LTI model. This model is then reduced to design controllers across a range of airspeeds. The controllers are tested both in linear model simulations and using the full nonlinear FLIGHTLAB® model. The results show that the load alleviating controller achieves significant reduction in the pitch link peak-to-peak loads with minimal change in response characteristics, indicating that load alleviation can be achieved with no degradation in handling qualities.
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Khalil, Khalid, Salvatore Asaro, and Andre Bauknecht. "Active Flow Control Devices for Wing Load Alleviation." In AIAA AVIATION 2020 FORUM. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-2940.

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Silvestre, Flávio, Antônio Bernardo Guimarães Neto, Domingos Rade, ROBERTO GIL ANNES DA SILVA, Rafael Bertolin, Gefferson Silva, Pedro Gonzalez, and Thiago Versiani. "Gust Load Alleviation in a Smart Idealized Wing." In 24th ABCM International Congress of Mechanical Engineering. ABCM, 2017. http://dx.doi.org/10.26678/abcm.cobem2017.cob17-2047.

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Castrichini, Andrea, Vijaya Hodigere Siddaramaiah, Dario Calderon, Jonathan E. Cooper, Thomas Wilson, and Yves Lemmens. "Nonlinear Folding Wing-Tips for Gust Loads Alleviation." In 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1846.

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Hashemi, Kelley E., Nhan T. Nguyen, Michael C. Drew, Daniel Chaparro, and Eric Ting. "Performance Optimizing Gust Load Alleviation Control of Flexible Wing Aircraft." In 2018 AIAA Guidance, Navigation, and Control Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-0623.

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Ferrier, Yvonne, Nhan T. Nguyen, Eric Ting, Daniel Chaparro, Xuerui Wang, Coen C. de Visser, and Q. Ping Chu. "Active Gust Load Alleviation of High-Aspect Ratio Flexible Wing Aircraft." In 2018 AIAA Guidance, Navigation, and Control Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-0620.

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