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Relevant bibliographies by topics / Aero-Thermo-Elastic

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Journal articles
Dissertations / Theses
Book chapters
Conference papers

Academic literature on the topic 'Aero-Thermo-Elastic'

Author: Grafiati

Published: 4 June 2021

Last updated: 11 February 2022

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Journal articles on the topic "Aero-Thermo-Elastic"

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Fazilati, Jamshid, Vahid Khalafi, and Hossein Shahverdi. "Three-dimensional aero-thermo-elasticity analysis of functionally graded cylindrical shell panels." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 5 (2018): 1715–27. http://dx.doi.org/10.1177/0954410018763861.

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In the present paper, the aero-thermo-elastic behavior of a finite (three-dimensional) cylindrical curved panel geometry made from functionally graded material under high supersonic airflow is investigated. A generalized differential quadrature formulation is adopted while a steady-state through-the-thickness thermal field is also assumed. The geometry curvature and structural nonlinearity effects are included based on von Karman–Donnell strain–displacement relations. The nonlinear piston theory of third order is utilized in order to predict the unsteady aerodynamics loads induced from surrounding supersonic air stream. The functionally graded material is considered with temperature-dependent properties distributed in the thickness according to a power law function. Derived from the equilibrium equations, the aero-thermo-elastic governing equations are reduced to number of ordinary differential equations through using of the generalized differential quadrature method where the structure response is derived using fourth-order Runge–Kutta technique. The contribution of some parameters including flow Mach number, flow dynamic pressure, thickness temperature gradient, and functionally graded material volume fraction index on the flutter response as well as route-to-chaos behavior are reviewed. The calculated results are compared with those available in the literature wherever available and the accuracy and quality of the adopted generalized differential quadrature formulation in analyzing the aero-thermo-elastic behavior of three-dimensional functionally graded curved panels is shown. It reveals that using a three-dimensional approach, if any of Mach number and panel’s upper surface temperature is increased, the route-to-chaos behavior is reached through quasi-periodic motions.

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Kang, Wei, Yang Tang, Min Xu, and Jia-Zhong Zhang. "Stability and Bifurcation of a Nonlinear Aero-thermo-elastic Panel in Supersonic Flow." Journal of Applied Nonlinear Dynamics 4, no. 3 (2015): 251–57. http://dx.doi.org/10.5890/jand.2015.09.005.

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3

Mahmoudkhani, S., M. Sadeghmanesh, and H. Haddadpour. "Aero-thermo-elastic stability analysis of sandwich viscoelastic cylindrical shells in supersonic airflow." Composite Structures 147 (July 2016): 185–96. http://dx.doi.org/10.1016/j.compstruct.2016.03.020.

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Tang, Hong, Guo Guang Chen, and Hui Zhu He. "An Aero-Thermo-Elasticity Method Applied on the Supersonic Aircraft Model." Applied Mechanics and Materials 215-216 (November 2012): 438–42. http://dx.doi.org/10.4028/www.scientific.net/amm.215-216.438.

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Coupling between the vibration frequencies and the unsteady aerodynamic will reduce the flutter speed and ride quality through the aerodynamic heat transfer. As the flight speed improved, the aeroelastic analysis has become an essential means of aircraft design. The method of aero-thermo-elastic (ATE) analysis is coupled with aircraft aeroelastic analysis and thermal deformation, and is more realistic reflection of the actual flight of the aircraft. In this paper, an ATE analysis of aircraft adopted by computational fluid dynamics/computational structural dynamics (CFD/CSD) methods, and compared with the traditional analysis, to provide analytical tools for the supersonic aircraft design.

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Baghdasaryan, G. Y., M. A. Mikilyan, I. A. Vardanyan, E. H. Danoyan, and K. Melikyan. "Influence of boundary conditions on the aero-thermo-elastic stability of a closed cylindrical shell." Journal of Physics: Conference Series 1474 (February 2020): 012008. http://dx.doi.org/10.1088/1742-6596/1474/1/012008.

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Zhou, Kai, Jinpeng Su, and Hongxing Hua. "Aero-thermo-elastic flutter analysis of supersonic moderately thick orthotropic plates with general boundary conditions." International Journal of Mechanical Sciences 141 (June 2018): 46–57. http://dx.doi.org/10.1016/j.ijmecsci.2018.03.026.

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Zhou, Kai, Xiuchang Huang, Zhenguo Zhang, and Hongxing Hua. "Aero-thermo-elastic flutter analysis of coupled plate structures in supersonic flow with general boundary conditions." Journal of Sound and Vibration 430 (September 2018): 36–58. http://dx.doi.org/10.1016/j.jsv.2018.05.035.

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Zhou, Kai, Zhengmin Hu, and Hongxing Hua. "Investigations on the aero-thermo-elastic characteristics of arbitrary polygon built-up structures in supersonic airflow." International Journal of Mechanical Sciences 196 (April 2021): 106300. http://dx.doi.org/10.1016/j.ijmecsci.2021.106300.

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Abbas, Laith K., Xiaoting Rui, P. Marzocca, M. Abdalla, and R. De Breuker. "A parametric study on supersonic/hypersonic flutter behavior of aero-thermo-elastic geometrically imperfect curved skin panel." Acta Mechanica 222, no. 1-2 (2011): 41–57. http://dx.doi.org/10.1007/s00707-011-0525-8.

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Rafiee, Mohammad, Mohsen Mohammadi, B. Sobhani Aragh, and Hessameddin Yaghoobi. "Nonlinear free and forced thermo-electro-aero-elastic vibration and dynamic response of piezoelectric functionally graded laminated composite shells." Composite Structures 103 (September 2013): 188–96. http://dx.doi.org/10.1016/j.compstruct.2012.12.050.

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Dissertations / Theses on the topic "Aero-Thermo-Elastic"

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"Modeling, Analysis, and Control of a Hypersonic Vehicle with Significant Aero-Thermo-Elastic-Propulsion Interactions: Elastic, Thermal and Mass Uncertainty." Master's thesis, 2011. http://hdl.handle.net/2286/R.I.8873.

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abstract: This thesis examines themodeling, analysis, and control system design issues for scramjet powered hypersonic vehicles. A nonlinear three degrees of freedom longitudinal model which includes aero-propulsion-elasticity effects was used for all analyses. This model is based upon classical compressible flow and Euler-Bernouli structural concepts. Higher fidelity computational fluid dynamics and finite element methods are needed for more precise intermediate and final evaluations. The methods presented within this thesis were shown to be useful for guiding initial control relevant design. The model was used to examine the vehicle's static and dynamic characteristics over the vehicle's trimmable region. The vehicle has significant longitudinal coupling between the fuel equivalency ratio (FER) and the flight path angle (FPA). For control system design, a two-input two-output plant (FER - elevator to speed-FPA) with 11 states (including 3 flexible modes) was used. Velocity, FPA, and pitch were assumed to be available for feedback. Aerodynamic heat modeling and design for the assumed TPS was incorporated to original Bolender's model to study the change in static and dynamic properties. De-centralized control stability, feasibility and limitations issues were dealt with the change in TPS elasticity, mass and physical dimension. The impact of elasticity due to TPS mass, TPS physical dimension as well as prolonged heating was also analyzed to understand performance limitations of de-centralized control designed for nominal model.
Dissertation/Thesis
M.S. Electrical Engineering 2011

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"Modeling, Analysis, and Control of a Hypersonic Vehicle With Significant Aero-Thermo-Elastic-Propulsion Interactions, and Propulsive Uncertainty." Master's thesis, 2010. http://hdl.handle.net/2286/R.I.8592.

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abstract: This thesis examines the modeling, analysis, and control system design issues for scramjet powered hypersonic vehicles. A nonlinear three degrees of freedom longitudinal model which includes aero-propulsion-elasticity effects was used for all analysis. This model is based upon classical compressible flow and Euler-Bernouli structural concepts. Higher fidelity computational fluid dynamics and finite elementmethods are needed formore precise intermediate and final evaluations. The methods presented within this thesis were shown to be useful for guiding initial control relevant design. The model was used to examine the vehicles static and dynamic characteristics over the vehicles trimmable region. The vehicle has significant longitudinal coupling between the fuel equivalency ratio (FER) and the flight path angle (FPA). For control system design, a two-input two-output plant (FER - elevator to speed-FPA) with 11 states (including 3 flexible modes) was used. Velocity, FPA, and pitch were assumed to be available for feedback. Propulsion system design issues were given special consideration. The impact of engine characteristics (design) and plume model on control system design were addressed.Various engine designs were considered for comparison purpose. With accurate plume modeling, effective coupling from the FER to the FPA was increased, which made the peak frequency-dependent (singular value) conditioning of the two-input two-output plant (FER-elevator to speed-FPA) worse. This forced the control designer to trade off desirable (performance/robustness) properties between the plant input and output. For the vehicle under consideration (with a very aggressive engine and significant coupling), it has been observed that a large FPA settling time is needed in order to obtain reasonable (performance/ robustness) properties at the plant input. Ideas for alleviating this fundamental tradeoff were presented. Plume modeling was also found to be particularly significant. Controllers based on plants with insufficient plume fidelity did not work well with the higher fidelity plants. Given the above, the thesismakes significant contributions to control relevant hypersonic vehicle modeling, analysis, and design.
Dissertation/Thesis
M.S. Electrical Engineering 2010

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Book chapters on the topic "Aero-Thermo-Elastic"

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Fazelzadeh, Seyyed Ahmad, Piergiovanni Marzocca, and Mohammad Hosseini. "Fluid-Thermo-Elastic and Aero-Thermo-Elastic Governing Equations for FGM Structures." In Encyclopedia of Thermal Stresses. Springer Netherlands, 2014. http://dx.doi.org/10.1007/978-94-007-2739-7_871.

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Conference papers on the topic "Aero-Thermo-Elastic"

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Abbas, Laith, Xiaoting Rui, Pier Marzocca, Mostafa Abdalla, and Roeland De Breuker. "Nonlinear Aero-Thermo-Visco-Elastic Behavior of Geometrically Imperfect Curved Skin Panel." In 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-2596.

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Kamali, Soudeh, Dimitri J. Mavriplis, and Evan M. Anderson. "Development and Validation of a High-Fidelity Aero-Thermo-Elastic Analysis Capability." In AIAA Scitech 2020 Forum. American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-1449.

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Kamali, Soudeh, Dimitri J. Mavriplis, and Evan M. Anderson. "Sensitivity Analysis for Aero-Thermo-Elastic Problems Using the Discrete Adjoint Approach." In AIAA AVIATION 2020 FORUM. American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-3138.

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4

Udrescu, Radu. "Combined forced-self-excited oscillations of panels under aero-thermo-elastic conditions." In 8th Symposium on Multidisciplinary Analysis and Optimization. American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-4790.

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5

Shahriar, Al, Kourosh Shoele, and Rajan Kumar. "Aero-thermo-elastic Simulation of Shock-Boundary Layer Interaction over a Compliant Surface." In 2018 Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-3398.

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Grasselt, David, Klaus Höschler, and Chetan Kumar Sain. "Fluid-Structure Interaction With a Fully Integrated Multiphysics Environment." In ASME 2017 Fluids Engineering Division Summer Meeting. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/fedsm2017-69078.

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The paper is focusing on Fluid-Structure Interaction (FSI) process modelling to look for the aero-elastic equilibrium with commercial software packages. The center of intention is to prove whether Ansys Workbench is capable to handle industrial size FSI applications on the one side and to identify possible excitation regions in the example case on the other. The three steps taken to come to a thermal-enhanced bidirectional fluid-structure approach within a fully integrated (monolithic) multiphysics environment are explained: aerodynamic assessment, thermo-structure mechanical setup and unidirectional coupling, as well as bidirectional coupling. Each subchapter describes the specific challenges, how they are solved and which results can be obtained or expected. The paper is focusing on the setup of a bidirectional process chain and does not set the thematic priority on detailed modelling and its results.

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