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Comparative Study of Beam and Plate Theories for Moderate Aspect Ratio Wings

AIAA JOURNAL 2023年第2期61卷 859-874页

作者： Hossein Modaress-Aval, Amir Bakhtiari-Nejad, Firooz Dowell, Earl H. Shahverdi, Hossein Peters, David Amirkabir Univ Technol Tehran *** Iran Duke Univ Durham NC 27708 USA Washington Univ St Louis MO 63130 USA

The main objective of the present study is to identify the best structural model for both aeroelastic and structural analysis of unswept rectangular wings with aspect ratios between 2 to 5. The paper presents a detailed study of the similarities and differences between the classical beam and plate theories, which provides new insight into this classical problem. To perform the aeroelastic analysis, the three-dimensional Peters aerodynamic model is coupled with classical plate theory. This combination leads to a new simpler three-dimensional aeroelastic model that can reduce the computational time. The results have been evaluated using both the unpublished and highly cited experimental data. Interestingly, by performing both structural and aeroelastic analyses, a comment can be stated that, even for relatively low aspect ratios (4 < AR < 5) of thin rectangular cantilever plates, the model based on the beam theory is closer to the experimental model compared to the plate theory. This finding may be unexpected by many researchers. Also, using a novel approach, it has been shown that the most significant difference between the beam and plate theories results arises from a subtle difference in the displacement field, which has not been given attention so far.

关键词： High Aspect Ratio Continuum Mechanics Beam (Structures) State Space Aeroelastic Models Euler Bernoulli Beam Theory structural modeling and simulation Aircraft Wing Design Rayleigh Ritz Method Finite Element Method Finite Element Software

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Boom-Membrane Space Structure's Incomplete Deployment After Storage in OrigamiSat-1 Ground Demonstrator

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AIAA JOURNAL 2024年第7期62卷 2401-2413页

作者： Chubachi, Takaomi Furuya, Hiroshi Sakamoto, Hiraku Tokyo Inst Technol Dept Mech Engn Sch Engn Tokyo 1528550 Japan

This study investigates the deployment reliability of multifunctional membrane deployable space structures that can be compactly stored and deployed in a two-dimensional direction using carbon composite booms to realize the construction of thin-film solar arrays and membrane antennas. Herein, two aspects are experimentally clarified using the structural models of a nano-satellite OrigamiSat-1, which is a 1 m-by-1 m square multifunctional deployable membrane structure demonstrator. First, a measurement system is developed to quasi-statically quantify the deployment torque of the structural models that failed to complete deployment after long-term storage and fell into an undesirable equilibrium shape. The measurement results confirm that the deployment torque decreases with long-term storage of the structure, and the torque in the deployment direction becomes negative at the deployment angle of the undesirable equilibrium shape. Therefore, as the second contribution, design modifications are made to the boom and membrane, and quasi-static and dynamic deployment tests are employed to evaluate their effects. The deployment reliability evaluation method and two design updates proposed herein will contribute to future space demonstrations and the utilization of lightweight membrane deployment structures with high packaging efficiency.

关键词： Space Structures Membrane Structures Satellites structural modeling and simulation Thin Films Aperture Antennas Smart Structures and Materials Micro Gravity Environment Solar Cells (Photovoltaic Cells) Polymer Matrix Composites

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Nonlinear Reduced Order modeling of Heated Structures with Temperature-Dependent Properties

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AIAA JOURNAL 2024年第1期63卷 244-259页

作者： Matney, Andrew Murthy, Raghavendra Song, Pengchao Wang, X. Q. Mignolet, Marc P. Northrop Grumman Corp Launch & Missile Def Syst Chandler AZ 85286 USA Arizona State Univ Fac Mech & Aerosp Engn SEMTE Tempe AZ 85287 USA

This paper focuses on extending coupled structural-thermal reduced order modeling approaches for the prediction of the nonlinear geometric response of heated structures to efficiently account for temperature-dependent structural and thermal properties. structurally, a linear dependence of the elasticity tensor and thermal expansion coefficient is assumed consistently with typical material behavior. The resulting structural reduced order model (ROM) equations exhibit polynomials of the temperature generalized coordinates, the coefficients of which are readily identified. A different strategy is proposed for conductance and capacitance properties which typically depend nonlinearly on temperature. It relies on splitting the temperature generalized coordinates into a small set of dominant ones having a nonlinear effect on the ROM conductances and capacitances and a much larger set affecting them linearly. The inclusion of uncertainty in the structural ROM is also addressed extending earlier work limited to temperature independent properties. These strategies are exemplified on a representative hypersonic vehicle panel undergoing a full mission profile and with aero-thermal-structural coupling. The ROM predictions are observed to be very close to the full finite element ones for the mean model. Moreover, an uncertainty analysis demonstrates the strong sensitivity of the response to the structural model in the strongly nonlinear regions of the trajectory.

关键词： structural modeling and simulation structural Displacement Reduced Order Model Nonlinear Geometric Heated Structure Coupled aero-thermo-structural analysis Uncertainty modeling

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Force/Moment-Conserving Pressure Mapping Scheme for Fluid/Structure Interaction Analysis

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AIAA JOURNAL 2023年第4期61卷 1462-1474页

作者： Lee, Kyu Beom Cho, Jin Yeon Kim, Jeongo Ho Inha Univ 36 Gaetbeol Ro Incheon 21999 South Korea

With the developments in computer-aided engineering, more complex and difficult simulations have become possible, and the demand for fluid/structure interaction (FSI) analysis has been increasing. Various approximation methods have been developed for pressure/load data mapping for FSI analysis. However, for most existing mapping algorithms, the sum of force/moment, which is one of the most important physical properties to be conserved, is not generally conserved. In this paper, we propose a new pressure mapping technique that is intuitive and easy to implement while algorithmically preserving force/moment for interfaces with complex and simple shapes. This technique distributes the pressure of the computational fluid dynamics (CFD) boundary mesh as concentrated loads to the nodes of the nearest structural element. The load distribution from each CFD cell is assumed to satisfy a plane equation, and the mapping loads are obtained by solving the equations to determine the coefficients of the plane equation. Furthermore, an algorithm to search for neighboring structural nodes for load mapping has been developed for various situations. To verify the proposed method, a simple plate model, pipe model with internal flow, and full-scale aircraft model were used. The results of the validation examples showed reliable load distributions and structural deformations with force/moment conservation.

关键词： Fluid Structure Interaction Smoothed Particle Hydrodynamics structural Analysis Finite Element modeling structural modeling and simulation Computer Aided Engineering Multidisciplinary Aircraft Design

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Investigation of Surrogate modeling Options with High-Dimensional Input and Output

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AIAA JOURNAL 2023年第3期61卷 1334-1348页

作者： Guo, Yulin Mahadevan, Sankaran Matsumoto, Shunsaku Taba, Shunsuke Watanabe, Daigo Vanderbilt Univ Dept Civil & Environm Engn Nashville TN 37235 USA Mitsubishi Heavy Ind Co Ltd Res & Innovat Ctr Strength Res Dept Nagasaki 8510392 Japan

Surrogate models are employed in engineering analysis to replace detailed physics-based models to achieve computational efficiency in problems that require multiple evaluations of the model. The accuracy of the surrogate model depends on the quality and quantity of data collected from the expensive model. This paper investigates surrogate modeling options for problems with high-dimensionality in both the input and output spaces. Several methods for reducing the output dimension are investigated, namely, singular value decomposition (SVD), random projection, randomized SVD, and diffusion map;similarly, several methods for input dimension reduction are investigated, namely, variance-based sensitivity analysis and active subspace discovery. The most effective combination of options for input and output dimension reduction is identified in a systematic way, followed by the construction of Gaussian process surrogate models in the low-dimensional space. The prediction error in the original space includes both the reconstruction error and surrogate error;a systematic approach is developed to quantify and compare the relative contributions of the two types of errors. The proposed general, systematic approach of exploring available options is applied to an aircraft fuselage panel. The effectiveness of various dimension reduction techniques with surrogate model construction are investigated in terms of accuracy and computational effort.

关键词： Numerical Analysis Singular Value Decomposition Probability Density Functions Mathematical Analysis Aircraft Components and Structure Finite Element Analysis Support Vector Machine Karhunen Loeve Expansion Monte Carlo simulation structural modeling and simulation

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Impact of Airframe-Propulsion System modeling Strategies on Key structural Performance Metrics

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JOURNAL OF AIRCRAFT 2023年第2期60卷 281-292页

作者： Colbert, Stephen Quinn, Damian Nolan, Declan C. Fox, Rob Gaskell, Jill Queens Univ Belfast Sch Mech & Aerosp Engn Belfast BT9 5AG North Ireland Rolls Royce plc Whole Engine Modeling Derby DE24 8BJ England

Whole-aircraft coupled aerodynamics, flight dynamics, and structural dynamics models are commonly employed during the aircraft design process, generally increasing in fidelity, and associatively accuracy, as the design matures. While literature acknowledges the impact of explicitly representing the propulsion system in such models, it does not address the impact of structural idealizations on key metrics that inform early conceptual design. This paper investigates the impact of a range of propulsion system structural modeling strategies and their attendant idealizations on the accuracy with which key structural performance metrics may be acquired. A conventional tube-and-wing airframe with under-wing-mounted, high-bypass-ratio, turbofan propulsion systems is employed as a verification case. The lowest-fidelity modeling strategies defined herein are capable of acquiring airframe loads and vertical power plant center-of-mass inertial loads within +/- 2%. Higher-fidelity, predominantly 2D strategies are necessary for acquisition of propulsion system displacements, deformations, and power plant swing frequency within +/- 10% of a global finite element model. However, sufficient data must be available to allow the construction of higher-fidelity strategies during early design stages.

关键词： Propulsion and Power Aircraft Components and Structure Power Station structural Finite Elements structural modeling and simulation Aircraft Engines Airbreathing Jet Engine structural Dynamics and Characterization Aircraft Design Process Aeroelastic Analysis

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Multiscale Model for Hydrogen Chloride Uptake on Aluminum for Spacecraft Fire Safety

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JOURNAL OF SPACECRAFT AND ROCKETS 2024年第3期61卷 839-846页

作者： Niehaus, Justin E. Mazumder, Sandip NASA Glenn Res Ctr Cleveland OH 44135 USA Ohio State Univ 201 West 19th Ave Columbus OH 43210 USA 21000 Brookpk Rd Cleveland OH 44135 USA

An electrical fire within spacecraft environments often produces poisonous gases, such as hydrogen chloride (HCl). These gases adsorb on the interior materials of the spacecraft, primarily treated aluminum surfaces. A safe design of the spacecraft can be facilitated by modeling the spacecraft compartment. In this study, a multiscale model is developed to predict HCl uptake by anodized aluminum, which has a thick oxide layer covering its surface compared to other treatments. X-ray photoelectron spectroscopy revealed that aluminum chloride is found deep in the oxide layer of anodized aluminum, implying that the pore-scale transport and reaction of HCl within the oxide layer covering the aluminum surface must be considered. Hence, a multiscale approach is warranted. A pore-scale model is first developed, wherein the HCl reacts with the aluminum oxide pore walls to create an aluminum chloride layer. The HCl then diffuses through that layer for further reaction, until the layer (diffusion resistance) grows too large and the uptake of HCl stops. This pore-scale model is coupled with a reactor-scale model to predict overall HCl uptake. Results show that this new multiscale approach predicts the uptake of HCl far more accurately when compared to experimental data than previously used single (reactor)-scale models.

关键词： structural modeling and simulation Spacecrafts Chromate Conversion Coating X Ray Photoelectron Spectroscopy Effective Diffusion Coefficient Reaction Rate Constant Backward Euler Method Aerospace Sciences Polyvinyl Chloride Aircraft Components and Structure

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Methodology for Numerically Stabilizing a Harmonic-Balance-Based Forced Response Aeroelastic Solution Approach

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AIAA JOURNAL 2023年第2期61卷 965-972页

作者： Thomas, Jeffrey P. Dowell, Earl H. Duke Univ Dept Mech Engn & Mat Sci Durham NC 27708 USA

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Thermal Structures for Aerospace Applications

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丛书名： AIAA Education Series

1996年

作者： Earl A. Thornton

ISBN: (数字)9781600862540

ISBN: (纸本)9781563471902

As aircraft flight speeds have increased and orbital missions have mandated complex space structures, the need for a deeper understanding of aerospace thermal structural behavior has grown. The purpose of this book is to study the basic problems of complex computer analyses as they relate to this behavior. With in-depth presentations, this book sets out to allow readers to develop an understanding of the basic physical behavior of thermal structures, gain an appreciation for the role of classical engineering thermal and stress analyses, and apply computational methods to provide insight into realistic behavior.

关键词： Aerodynamics Aeroelasticity Aeronautical Engineering Aeronautics Aerothermodynamics Airspeed Beam (Structures) Boundary Layers Buckling Analysis Composite Materials Computational Fluid Dynamics Conservation of Momentum Equations Continuum Mechanics Convection Coolant Cooling Technology Cylindrical Shell Structures Deformation Deformation Mechanisms Equations of Fluid Dynamics FEM Elements Finite Element Method Flexible and Active Structures Flow Regimes Fluid Dynamics Fluid Flow Properties Heat Conduction Heat Exchangers Heat Transfer Heating System Heating, Ventilating, and Air Conditioning Material Properties Materials Materials and structural Mechanics Mechanical Properties Mechanical and structural Vibrations Numerical Heat Transfer Plastic Deformation Plasticity Radiative Heat Transfer Shell Structures Skin Friction Solar Heating Solid Mechanics Stress-Strain Analysis structural Analysis structural Design and Development structural Dynamics and Characterization structural Engineering structural Mechanics structural modeling and simulation Structures, Design and Test Thermal Control and Protection Thermal Effects Thermal Measurement Thermal modeling and Analysis Thermodynamic Properties Thermodynamics Thermophysical Properties Thermophysics and Heat Transfer Torsional Vibration Trusses Vortex Dynamics

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Highly Flexible Structures: modeling, Computation, and Experimentation

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丛书名： AIAA Education Series

2007年

作者： P.Frank Pai

ISBN: (数字)9781600861925

ISBN: (纸本)9781563479175

This book provides new methods and advanced experimental techniques for the design, analysis, and testing of highly flexible deployable/inflatable structures (HFSs), including systematic nonlinear modeling approaches, newly developed geometrically exact structural theories, numerically exact solution methods, fully nonlinear finite element techniques, and non-contact techniques for static and dynamic testing. Chapter 1 summarizes characteristics of HFSs, points out challenging modeling and analysis issues, and presents state-of-the-art measurement systems for testing HFSs. Chapter 2 presents the fundamentals of structural mechanics to prepare the reader for geometrically exact modeling of HFSs. Chapter 3 presents the fundamentals of nonlinear finite element analysis and the multiple shooting method of solving nonlinear ordinary differential equations for numerically exact solutions. The book then proceeds in treating different structural systems from simple 1D systems (trusses and cables in chapter 4, and beams in chapter 5), to 2D systems (plats and shells in chapter 6, and membranes in chapter 7), and to complex systems (smart structures in chapter 8). The author uses the lowest possible level of mathematical complexity as possible to convey concepts. In addition to more than 350 descriptive illustrations, the accompanying DVD contains computer programs and videos of experiments. These programs and visual tools aid the reader in quickly developing a basic understanding. The text, chapter questions, solutions manual, and accompanying CD will support a one-semester graduate-level course.

关键词： Beam (Structures) Buckling Analysis Classical Mechanics Computational Fluid Dynamics Computer Programming and Language Computer-Aided Manufacturing Computing and Informatics Computing, Information, and Communication Continuum Mechanics Cylindrical Shell Structures Deformation Dynamic Analysis FEM Elements Failure Analysis Fatigue Analysis Finite Element Method Finite Element Software Flexible and Active Structures Fluid Dynamics General Physics Hilbert-Huang Transform Material Properties Materials Materials and structural Mechanics Mechanical Properties Mechanical and structural Vibrations Membrane Structures Newton's Laws of Motion Numerical Analysis Plastic Deformation Runge-Kutta Methods Shell Structures Signal Processing Smart Structures and Materials Solid Mechanics Stress-Strain Analysis structural Analysis structural Design and Development structural Dynamics and Characterization structural Engineering structural Kinematics and Dynamics structural Mechanics structural modeling and simulation structural System Structures, Design and Test Trusses Vibration Measuring Instruments

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