Relevant bibliographies by topics / Aeroelasticity

Academic literature on the topic 'Aeroelasticity'

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Published: 4 June 2021
Last updated: 14 September 2024

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Journal articles on the topic "Aeroelasticity"

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Dowell, Earl, John Edwards, and Thomas Strganac. "Nonlinear Aeroelasticity." Journal of Aircraft 40, no. 5 (September 2003): 857–74. http://dx.doi.org/10.2514/2.6876.

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Li, Rui, and Chang Hong Tang. "Analysis for Nonlinear Aeroelasticity on Structure and its Current Progress." Advanced Materials Research 1022 (August 2014): 118–21. http://dx.doi.org/10.4028/www.scientific.net/amr.1022.118.

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Firstly, the origin and mathematical mechanism of freeplay nonlinearity ,cubic nonlinearity, hysteresis nonlinearity was analyzed in this paper , and the importance of nonlinear aeroelasticity on structure was pointed out .On the current system of nonlinear aeroelasticity for the method of flutter analysis was summarized. Meanwhile on the mechanism of geometric nonlinearity and analytic methods have been studied, the future direction of the nonlinear aeroelasticity was concluded .
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S, Nithin, and Vijayalakshmi Bharathi K. "REVIEW ON AEROELASTICITY." International Journal of Engineering Applied Sciences and Technology 04, no. 08 (December 31, 2019): 271–74. http://dx.doi.org/10.33564/ijeast.2019.v04i08.047.

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TAMURA, Yukio, and Aakashi MOCHIDA. "INSTITUTE FOR AEROELASTICITY." Wind Engineers, JAWE 1987, no. 33 (1987): 113–16. http://dx.doi.org/10.5359/jawe.1987.33_113.

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Da Ronch. "Special Issue: Aeroelasticity." Aerospace 6, no. 9 (August 23, 2019): 92. http://dx.doi.org/10.3390/aerospace6090092.

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Bessert, N., and O. Frederich. "Nonlinear airship aeroelasticity." Journal of Fluids and Structures 21, no. 8 (December 2005): 731–42. http://dx.doi.org/10.1016/j.jfluidstructs.2005.09.005.

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Tian, Shuling, Rongjie Li, and Ke Xu. "Investigation of Aeroelasticity Effect on Missile Separation from the Internal Bay." International Journal of Aerospace Engineering 2023 (February 16, 2023): 1–16. http://dx.doi.org/10.1155/2023/9875622.

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There is a strong aerodynamic interference when launching the missile in the embedded mode. During the separation process, the carrier aircraft safety may be threatened due to large slenderness ratio, low structural stiffness, and aeroelasticity effects of the missile. The present study simulates missile separation in the presence of the aeroelasticity effects based on the computational fluid dynamics (CFD), rigid body dynamics (RBD), and computational structure dynamics (CSD) coupling method. A hybrid dynamic grid method consisting of the mixed overset unstructured grid and deformation grid is utilized. In order to verify the accuracy of the coupled numerical method, store separation from a wing and AGARD 445.6 wing flutter are first simulated as two standard test cases. The verification results imply that the present coupled numerical method is reliable and capable in simulation of the aeroelastic effect in missile separation. The influence of aeroelasticity on the separation trajectory of a missile from the internal bay is systematically studied at different states. Numerical results show that aeroelasticity substantially affects the missile angular displacement, while it has a slight impact on the linear displacement of the center of mass. Mach number and flight altitude are two important flight parameters that characterize the aeroelasticity effect on missile separation from the internal bay.
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Ye, Kun, Zhengyin Ye, Qing Zhang, and Zhan Qu. "Effects of aeroelasticity on the performance of hypersonic inlet." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 11 (June 1, 2017): 2108–21. http://dx.doi.org/10.1177/0954410017710275.

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Effects of the aeroelasticity on the performance of the hypersonic inlet have been investigated numerically in this study. The aeroelasticity has been simulated using the coupled computational fluid dynamics/computational structural dynamics method, which is solved by the in-house code. The unsteady Reynolds-averaged Navier–Stokes equations have been solved in the computational fluid dynamics simulation, and the modal method has been adopted in the computational structural dynamics simulation. Two cases have been utilized to validate the numerical method. Finally, the aeroelasticity has been simulated for inlet plate with different thicknesses. The effects of aeroelasticity on performance parameters and flow structure have been discussed in detail. The results show that the generalized displacements present the “beat” phenomenon in the time domain. The power spectral density of the generalized displacements implies that the aeroelastic instability is mainly caused by the coupling between the fourth- and fifth-order modes. The time-average flow rate coefficient and pressure rise ratio increase relative to the initial value, while the total pressure recovery coefficient decreases. The fluctuation amplitude of the flow rate coefficient is small, while that of the total pressure recovery coefficient and pressure rise ratio are relatively large. Besides, the phases of the three performance parameters are greatly different. Furthermore, the aeroelasticity has significant effect on the shock wave structure especially at the exit of the inlet.
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Li, Rui, and Chang Hong Tang. "Research and Application of Aeroelastic Analysis Based on Fluid-Structure Interaction." Advanced Materials Research 977 (June 2014): 418–22. http://dx.doi.org/10.4028/www.scientific.net/amr.977.418.

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the origins and characteristics of linear and nonlinear aeroelasticity are analyzed.And the deforming mesh , fluid-structure coupling schemes, the design method of aerodynamic module and structure module interface are also analyzed. their advantages and disadvantages are Pointed out. Finally, several recommendations are given for the development orientation of aeroelasticity in the future.
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Fedorenko, Myhailo, and Oleksander Bondarenko. "Possibilities of the finite element method for the analysis of the aeroelasticity of the wing of a light aircraft." MECHANICS OF GYROSCOPIC SYSTEMS, no. 47 (May 15, 2024): 110–22. http://dx.doi.org/10.20535/0203-3771472024307685.

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Modeling of the aeroelasticity of a straight wing for a light aircraft by the finite element method was carried out and the simulation results were verified by a binary model. The possibility of using the finite element method for modeling the aeroelasticity of a light-class aircraft is shown. A comparison of the aeroelasticity of a light aircraft wing with and without tapering was performed. The criterion for loss of wing stability during aeroelastic oscillations is the transition from a positive to a negative value of the damping coefficient in the wing-air system at a certain flight speed. Measures to strengthen the wing structure in order to ensure the necessary flight speed are indicated.
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Dissertations / Theses on the topic "Aeroelasticity"

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Swift, Adam. "Simulation of aircraft aeroelasticity." Thesis, University of Liverpool, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.569519.

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Aeroelastic phenomena such as flutter can have a detrimental effect on aircraft performance and can lead to severe damage or destruction. Buffet leads to a re- duced fatigue life and therefore higher operating costs and a limited performance envelope. As such the simulation of these aeroelastic phenomena is of utmost importance. Computational aeroelasticity couples computational fluid dynamics and computational structural dynamics solvers through the use of a transforma- tion method. There have been interesting developments over the years towards more efficient methods for predicting the flutter boundaries based upon the sta- bility of the system of equations. This thesis investigates the influence of transformation methods on the flutter boundary predition and considers the simulation of shock-induced buffet of a transport wing. This involves testing a number of transformation methods for their effect on flutter boundaries for two test cases and verifying the flow solver for shock-induced buffet over an aerofoil. This will be followed by static aeroelastic calculations of an aeroelastic wing. It is shown that the transformation methods have a significant effect on the predicted flutter boundary. Multiple transformation methods should be used to build confidence in the results obtained, and extrapolation should be avoided. CFD predictions are verified for buffet calculations and the mechanism behind shock-oscillation of the BGK No. 1 aerofoil is investigated. The use of steady calculations to assess if a case may be unsteady is considered. Finally the static aeroelastic response of the ARW-2 wing is calculated and compared against ex- perimental results.
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Souza, Carlos Eduardo de. "Nonlinear aeroelasticity of composite flat plates." Instituto Tecnológico de Aeronáutica, 2012. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2243.

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This work presents a study on aeroelastic analyses of composite laminated flat plates subject to large displacements through the coupling of a nonlinear corotational shell finite element (FE) with an unsteady vortex-lattice method (UVLM) formulation. A FE implemented for the analysis of flat plates has been extended to model laminated composites with different lamina orientations. An UVLM formulation that is capable of coupling with this large displacement structural model is implemented. An explicit partitioned method is evaluated for the coupling of both models, using spline functions to interpolate information from the structural operator to the aerodynamic one, inside a Generalized-? time-marching solution. The resulting aeroelastic formulation provides a framework able of performing time marching simulation of structures made of composite material allowing the characterization of their nonlinear behavior and of the limit-cycle oscillation response. Laminated flat plates designed for high flexibility and low flutter speed onset are used as investigation models. To support the numerical studies, test specimens made of carbon fiber were used in experimental modal analysis and wind tunnel aeroelastic tests. Effects of nonlinearities are easily observed in the numerical results, which are promising for expansion of the work and application to the analysis of more refined and complex composite flexible wings.
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Bueno, Douglas Domingues. "A contribution to aeroelasticity using lyapunov's theory." Instituto Tecnológico de Aeronáutica, 2014. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=3035.

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The main idea of this work is to apply the general theory of stability introduced by Lyapunov and to use linear matrix inequalities (LMIs) to study different issues in aeroservoelasticity. Many approaches have been developed on the control theory field involving LMIs, however, there is a limited number of works in the literature focused on aeroelasticity. That preliminary motivation allowed the development of different approaches on this topic. Three benchmark systems were used to evaluate and demonstrate these approaches. The first one is the three degree of freedom airfoil section and the second one is the AGARD 445.6 wing. The third benchmark system is the two degree of freedom pitch and plunge apparatus. The aerodynamic forces were computed using the Theodorsen';s theory and the Doublet Lattice method. Four different issues involving stability and control are discussed. The first one is the inclusion of structural uncertainties on the stability analysis. The second topic introduces the concept of continuous analysis and allows the study of stability of time-variant aeroelastic systems. The third issue comprises the design of controllers to suppress limit cycle oscillations in aeroelastic systems including discrete nonlinearities based on the Fuzzy Takagi-Sugeno modeling and, finally, the last topic proposes the use of Grammian matrices to determine the linear stability specially when a large number of cases of analysis are considered in the flight envelope. The introduced ideas are very promising for aeroservoelastic analysis using LMIs.
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Natarajan, Anand. "Aeroelasticity of Morphing Wings Using Neural Networks." Diss., Virginia Tech, 2002. http://hdl.handle.net/10919/28267.

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In this dissertation, neural networks are designed to effectively model static non-linear aeroelastic problems in adaptive structures and linear dynamic aeroelastic systems with time varying stiffness. The use of adaptive materials in aircraft wings allows for the change of the contour or the configuration of a wing (morphing) in flight. The use of smart materials, to accomplish these deformations, can imply that the stiffness of the wing with a morphing contour changes as the contour changes. For a rapidly oscillating body in a fluid field, continuously adapting structural parameters may render the wing to behave as a time variant system. Even the internal spars/ribs of the aircraft wing which define the wing stiffness can be made adaptive, that is, their stiffness can be made to vary with time. The immediate effect on the structural dynamics of the wing, is that, the wing motion is governed by a differential equation with time varying coefficients. The study of this concept of a time varying torsional stiffness, made possible by the use of active materials and adaptive spars, in the dynamic aeroelastic behavior of an adaptable airfoil is performed here. A time marching technique is developed for solving linear structural dynamic problems with time-varying parameters. This time-marching technique borrows from the concept of Time-Finite Elements in the sense that for each time interval considered in the time-marching, an analytical solution is obtained. The analytical solution for each time interval is in the form of a matrix exponential and hence this technique is termed as Matrix Exponential time marching. Using this time marching technique, Artificial Neural Networks can be trained to represent the dynamic behavior of any linearly time varying system. In order to extend this methodology to dynamic aeroelasticity, it is also necessary to model the unsteady aerodynamic loads over an airfoil. Accordingly, an unsteady aerodynamic panel method is developed using a distributed set of doublet panels over the surface of the airfoil and along its wake. When the aerodynamic loads predicted by this panel method are made available to the Matrix Exponential time marching scheme for every time interval, a dynamic aeroelastic solver for a time varying aeroelastic system is obtained. This solver is now used to train an array of neural networks to represent the response of this two dimensional aeroelastic system with a time varying torsional stiffness. These neural networks are developed into a control system for flutter suppression. Another type of aeroelastic problem of an adaptive structure that is investigated here is the shape control of an adaptive bump situated on the leading edge of an airfoil. Such a bump is useful in achieving flow separation control for lateral directional maneuverability of the aircraft. Since actuators are being used to create this bump on the wing surface, the energy required to do so needs to be minimized. The adverse pressure drag as a result of this bump needs to be controlled so that the loss in lift over the wing is made minimal. The design of such a "spoiler bump" on the surface of the airfoil is an optimization problem of maximizing pressure drag due to flow separation while minimizing the loss in lift and energy required to deform the bump. One neural network is trained using the CFD code FLUENT to represent the aerodynamic loading over the bump. A second neural network is trained for calculating the actuator loads, bump displacement and lift, drag forces over the airfoil using the finite element solver, ANSYS and the previously trained neural network. This non-linear aeroelastic model of the deforming bump on an airfoil surface using neural networks can serve as a fore-runner for other non-linear aeroelastic problems. This work enhances the traditional aeroelastic modeling by introducing time varying parameters in the differential equations of motion. It investigates the calculation of non-conservative aerodynamic loads on morphing contours and the resulting structural deformation for non-linear aeroelastic problems through the use of neural networks. Geometric modeling of morphing contours is also addressed.
Ph. D.
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Liu, Shaobin. "Continuum Sensitivity Method for Nonlinear Dynamic Aeroelasticity." Diss., Virginia Tech, 2013. http://hdl.handle.net/10919/23282.

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In this dissertation, a continuum sensitivity method is developed for efficient and accurate computation of design derivatives for nonlinear aeroelastic structures subject to transient
aerodynamic loads. The continuum sensitivity equations (CSE) are a set of linear partial
differential equations (PDEs) obtained by differentiating the original governing equations of
the physical system. The linear CSEs may be solved by using the same numerical method
used for the original analysis problem. The material (total) derivative, the local (partial)
derivative, and their relationship is introduced for shape sensitivity analysis. The CSEs are
often posed in terms of local derivatives (local form) for fluid applications and in terms of total
derivatives (total form) for structural applications. The local form CSE avoids computing
mesh sensitivity throughout the domain, as required by discrete analytic sensitivity methods.
The application of local form CSEs to built-up structures is investigated. The difficulty
of implementing local form CSEs for built-up structures due to the discontinuity of local
sensitivity variables is pointed out and a special treatment is introduced. The application
of the local form and the total form CSE methods to aeroelastic problems are compared.
Their advantages and disadvantages are discussed, based on their derivations, efficiency,
and accuracy. Under certain conditions, the total form continuum method is shown to be
equivalent to the analytic discrete method, after discretization, for systems governed by a
general second-order PDE. The advantage of the continuum sensitivity method is that less
information of the source code of the analysis solver is required. Verification examples are
solved for shape sensitivity of elastic, fluid and aeroelastic problems.
Ph. D.
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Kamakoti, Ramji. "Computational aeroelasticity using a pressure-based solver." [Gainesville, Fla.] : University of Florida, 2004. http://purl.fcla.edu/fcla/etd/UFE0005683.

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Seywald, Klaus. "Wingbox Mass Prediction considering Quasi-Static Nonlinear Aeroelasticity." Thesis, KTH, Flygdynamik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-59014.

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Nonplanar wing configurations promise a significant improvement of aerodynamic efficiency and are therefore currently investigated for future aircraft configurations. A reliable mass prediction for a new wing configuration is of great importance in preliminary aircraft design in order to enable a holistic assessment of potential benefits and drawbacks. In this thesis a generic numerical modeling approach for arbitrary unconventional wing configurations is developed and a simulation tool for their evaluation and mass prediction is implemented. The wingbox is modeled with a nonlinear finite element beam which is coupled to different low-fidelity aerodynamic methods obtaining a quasi-static aeroelastic model that considers the redistribution of aerodynamic forces due to deformation. For the preliminary design of the wingbox various critical loading conditions according to the Federal Aviation Regulations are taken into account. The simulation tool is validated for a range of existing aircraft types. Additionally, two unconventional configurations, the C-wing and the box-wing, are analyzed. The outlook provides suggestions for extensions and further development of the simulation tool as well as possible model refinements.
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Feng, Zhengkun. "A nonlinear computational aeroelasticity model for aircraft wings." Mémoire, Montréal : École de technologie supérieure, 2005. http://wwwlib.umi.com/cr/etsmtl/fullcit?pNR06026.

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Thèse (Ph.D.)-- École de technologie supérieure, Montréal, 2005.
"Thesis presented to École de technologie supérieure in fulfillment of the thesis requirement for the degree of doctor of philosophy". Bibliogr.: f. [160]-168. Également disponible en version électronique.
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Banerjee, J. R. "Advances in structural dynamics, aeroelasticity and material science." Thesis, City University London, 2015. http://openaccess.city.ac.uk/14901/.

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This submission for the degree of Doctor of Science includes all the publications by the author and a description of his research, covering the period 1969-2015. The main contributions to knowledge made by the author concern his new approaches to structural dynamics, aeroelasticity, material science and related problems. In particular, the major activities of his research relate to the (i) free vibration and buckling analysis of structures, (ii) dynamic stiffness formulation, (iii) response of metallic and composite structures to deterministic and random loads, (iv) aeroelasticity of metallic and composite aircraft, (v) a unified approach to flutter, dynamic stability and response of aircraft, (vi) aeroelastic optimisation and active control, (vii) application of symbolic computation in structural engineering research, (viii) development of software packages for computer aided structural analysis and design and (ix) thermal properties of polymer nanocomposites and hot ductility of steel. The free vibration analysis of structures is a research topic which has been an age old companion of the author ever since he was working for his Master’s degree in Mechanical Engineering in the early 1970s, when he chose a crankshaft vibration problem of the Indian Railways as the research topic for his Master’s thesis. With increasing maturity and experience, he provided solutions to vibration and buckling problems ranging from a simple single structural element to a high capacity transport airliner capable of carrying more than 500 passengers and a large space platform with a plan dimension of more than 30 metres. To provide these solutions, he resorted to an elegant, accurate, but efficient method, called the dynamic stiffness method, which uses the so-called dynamic stiffness matrix of a structural element as the basic building block in the analysis. The author has developed dynamic stiffness matrices of a large number of structural elements including beams, plates and shells with varying degrees of complexity, particularly including those made of composite materials. Recently he published the dynamic stiffness matrices of isotropic and anisotropic rectangular plates for the most general case when the plate boundaries are free at all edges. Computation of natural frequencies of isotropic and anisotropic plates and their assemblies for any boundary conditions in an exact sense has now become possible for the first time as a result of this development. This ground-breaking research has opened up the possibility of developing general purpose computer programs using the dynamic stiffness method for computer-aided structural analysis and design. Such computer programs will be vastly superior to existing computer programs based on the finite element method, both in terms to accuracy and computational efficiency. This is in line with the author’s earlier research on free vibration and buckling analysis of skeletal structures which led to the development of the computer program BUNVIS (Buckling or Natural Vibration of Space Frames) and BUNVIS-RG (Buckling or Natural Vibration of Space Frames with Repetitive Geometry) which received widespread attention. Numerous research papers emerged using BUNVIS and BUNVIS-RG as research tools. The author’s main contributions in the Aeronautical Engineering field are, however, related to the solutions of problems in aeroelasticity, initially for metallic aircraft and in later years for composite aircraft. He investigated the aeroelastic problems of tailless aircraft for the first time in his doctoral studies about 40 years ago. In this research, a unified method combining two major disciplines of aircraft design, namely that of stability and control, and that of flutter and response, was developed to study the interaction between the rigid body motions of an aircraft and its elastic modes of distortion. The computer program CALFUN (CALculation of Flutter speed Using Normal modes) was developed by the author for metallic aircraft and later extended to cover composite aircraft. The associated theories for composite aircraft were developed and the allied problems of dynamic response to both deterministic and random loads were solved. With the advent of advanced composite materials, the author’s research turned to aeroelasticity of composite aircraft and then to optimization studies. New, novel and accurate methods were developed and significant inroads were made. The author broke new ground by applying symbolic computation as an aid to the solution of his research problems. The computational efficiency of this new approach became evident as a by-product of his research. The development of software based on his theories has paved the way for industrial applications. His research works on dynamic stiffness modelling of composite structures using layer-wise and higher order shear deformation theory are significant developments in composites engineering. Such pioneering developments were necessitated by the fact that existing methodologies using classical lamination theory are not sufficiently accurate, particularly when the structural components made from composite materials are thick, e.g. the fuselage of a transport airliner. Given the close relationship between structural engineering and material science, the author’s research has broadened into polymers and nano-composites, functionally graded materials and hot ductility of steel. His research activities are continuing and expanding with further diversification of his interests.
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Eller, David. "On an Efficient Method fo Time-Domain Computational Aeroelasticity." Doctoral thesis, KTH, Farkost och flyg, 2005. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-584.

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The present thesis summarizes work on developing a method for unsteady aerodynamic analysis primarily for aeroelastic simulations. In contrast to widely used prediction tools based on frequency-domain representations, the current approach aims to provide a time-domain simulation capability which can be readily integrated with possibly nonlinear structural and control system models. Further, due to the potential flow model underlying the computational method, and the solution algorithm based on an efficient boundary element formulation, the computational effort for the solution is moderate, allowing time-dependent simulations of complex configurations. The computational method is applied to simulate a number of wind-tunnel experiments involving highly flexible models. Two of the experiments are utilized to verify the method and to ascertain the validity of the unsteady flow model. In the third study, simulations are used for the numerical optimization of a configuration with multiple control surfaces. Here, the flexibility of the model is exploited in order to achieve a reduction of induced drag. Comparison with experimental results shows that the numerical method attains adequate accuracy within the inherent limits of the potential flow model. Finally, rather extensive aeroelastic simulations are performed for the ASK 21 sailplane. Time-domain simulations of a pull-up maneuver and comparisons with flight test data demonstrate that, considering modeling and computational effort, excellent agreement is obtained. Furthermore, a flutter analysis is performed for the same aircraft using identified frequency-domain loads. Results are found to deviate only slightly from critical speed and frequency obtained using an industry-standard aeroelastic analysis code. Nevertheless, erratic results for control surface hinge moments indicate that the accuracy of the present method would benefit from improved control surface modeling and coupled boundary layer analysis.
QC 20100531
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Books on the topic "Aeroelasticity"

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Balakrishnan, AV. Aeroelasticity. New York, NY: Springer New York, 2012. http://dx.doi.org/10.1007/978-1-4614-3609-6.

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Holt, Ashley, and Halfman Robert L, eds. Aeroelasticity. New York: Dover Publications, 1996.

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Djojodihardjo, Harijono. Introduction to Aeroelasticity. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-16-8078-6.

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Gennaretti, Massimo. Fundamentals of Aeroelasticity. Cham: Springer Nature Switzerland, 2024. http://dx.doi.org/10.1007/978-3-031-53379-2.

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Dimitriadis, Grigorios. Introduction to Nonlinear Aeroelasticity. Chichester, UK: John Wiley & Sons, Ltd, 2017. http://dx.doi.org/10.1002/9781118756478.

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Dowell, Earl H., and Marat Ilgamov. Studies in Nonlinear Aeroelasticity. New York, NY: Springer New York, 1988. http://dx.doi.org/10.1007/978-1-4612-3908-6.

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service), SpringerLink (Online, ed. Aeroelasticity: The Continuum Theory. New York, NY: Springer New York, 2012.

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Johnson, Wayne. Airloads, wakes, and aeroelasticity. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1990.

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Dowell, Earl H. Studies in Nonlinear Aeroelasticity. New York, NY: Springer New York, 1988.

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A, Ilʹgamov M., ed. Studies in nonlinear aeroelasticity. New York: Springer-Verlag, 1988.

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Book chapters on the topic "Aeroelasticity"

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Chari, N., Prasad Mukkavilli, A. G. Sarwade, and Kamalakar Pallela. "Aeroelasticity." In Biophysics of Insect Flight, 121–31. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-5184-7_9.

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Balakrishnan, A. V. "Introduction." In Aeroelasticity, 1–8. New York, NY: Springer New York, 2012. http://dx.doi.org/10.1007/978-1-4614-3609-6_1.

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Balakrishnan, A. V. "Addendum: Axial Air flow Theory—Continuum Models." In Aeroelasticity, 367–86. New York, NY: Springer New York, 2012. http://dx.doi.org/10.1007/978-1-4614-3609-6_10.

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Balakrishnan, A. V. "Dynamics of Wing Structures." In Aeroelasticity, 9–46. New York, NY: Springer New York, 2012. http://dx.doi.org/10.1007/978-1-4614-3609-6_2.

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Balakrishnan, A. V. "The Air Flow Model/Boundary Fluid Structure Interaction/The Aeroelastic Problem." In Aeroelasticity, 47–63. New York, NY: Springer New York, 2012. http://dx.doi.org/10.1007/978-1-4614-3609-6_3.

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Balakrishnan, A. V. "The Steady-State (Static) Solution of the Aeroelastic Equation." In Aeroelasticity, 65–102. New York, NY: Springer New York, 2012. http://dx.doi.org/10.1007/978-1-4614-3609-6_4.

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Balakrishnan, A. V. "Linear Aeroelasticity Theory/ The Possio Integral Equation." In Aeroelasticity, 103–267. New York, NY: Springer New York, 2012. http://dx.doi.org/10.1007/978-1-4614-3609-6_5.

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Balakrishnan, A. V. "Nonlinear Aeroelasticity Theory in 2D Aerodynamics: Flutter Instability as an LCO." In Aeroelasticity, 269–326. New York, NY: Springer New York, 2012. http://dx.doi.org/10.1007/978-1-4614-3609-6_6.

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Balakrishnan, A. V. "Viscous Air flow Theory." In Aeroelasticity, 327–36. New York, NY: Springer New York, 2012. http://dx.doi.org/10.1007/978-1-4614-3609-6_7.

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Balakrishnan, A. V. "Optimal Control Theory: Flutter Suppression." In Aeroelasticity, 337–47. New York, NY: Springer New York, 2012. http://dx.doi.org/10.1007/978-1-4614-3609-6_8.

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Conference papers on the topic "Aeroelasticity"

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Dowell, Earl, John Edwards, and Thomas Strganac. "Nonlinear Aeroelasticity." In 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-1816.

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DOWELL, EARL. "Nonlinear aeroelasticity." In 31st Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1031.

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Scott, Davin R. "Aeroelasticity Past Present and Future." In International Pacific Air and Space Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1987. http://dx.doi.org/10.4271/872449.

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Bhatia, Kumar. "Airplane aeroelasticity - Practice and potential." In 39th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-430.

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Schuster, David, Danny Liu, and Lawrence Huttsell. "Computational Aeroelasticity: Success, Progress, Challenge." In 44th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-1725.

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Karpel, Moti, Daniella Raveh, and Yuval Levy. "Computational Aeroelasticity Research in Israel." In 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-2437.

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Huston, Dryver, Dylan Burns, Brent Boerger, and Robert Selzer. "Proximity lithography membrane mask aeroelasticity." In SPIE 31st International Symposium on Advanced Lithography, edited by Michael J. Lercel. SPIE, 2006. http://dx.doi.org/10.1117/12.660798.

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Dowell, E., and D. Tang. "Nonlinear aeroelasticity and unsteady aerodynamics." In 40th AIAA Aerospace Sciences Meeting & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-3.

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Akay, Hasan, Erdal Oktay, Zhenyin Li, and Xiaoyin He. "Parallel Computing for Aeroelasticity Problems." In 21st AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-3511.

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WEISSHAAR, TERRENCE. "Aeroelasticity - Advances and future directions." In 33rd Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-2446.

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Reports on the topic "Aeroelasticity"

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Beran, Philip S., Ned J. Lindsley, Jose Camberos, and Mohammad Kurdi. Stochastic Nonlinear Aeroelasticity. Fort Belvoir, VA: Defense Technical Information Center, January 2009. http://dx.doi.org/10.21236/ada494780.

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Beran, Philip S., and Richard D. Snyder. Computational Nonlinear Aeroelasticity. Fort Belvoir, VA: Defense Technical Information Center, January 2008. http://dx.doi.org/10.21236/ada475753.

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Dugundji, John, and Gun-Shing Chen. Dynamics and Aeroelasticity of Composite Structures. Fort Belvoir, VA: Defense Technical Information Center, March 1986. http://dx.doi.org/10.21236/ada172922.

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Wood, Robert. A Comprehensive Study of Aeroelasticity in Flapping-Wing MAVs. Fort Belvoir, VA: Defense Technical Information Center, August 2012. http://dx.doi.org/10.21236/ada581268.

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Squires, Kyle D. A High Resolution Aeroelasticity Method for Fighter Aircraft at Flight Reynolds Numbers. Fort Belvoir, VA: Defense Technical Information Center, September 2004. http://dx.doi.org/10.21236/ada427305.

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