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Buckling and Fundamental Frequency Optimization of Tow-Steered Composites Using Layerwise structural Models

AIAA JOURNAL 2023年第9期61卷 4149-4163页

作者： Sanchez-Majano, Alberto Racionero Pagani, Alfonso Polytech Univ Turin Dept Mech & Aerosp Engn I-10129 Turin Italy

Variable-angle-tow (VAT) composite laminates can eventually improve the mechanical performance of lightweight structures by taking advantage of a larger design space compared to straight-fiber counterparts. Here, we provide a scalable low- to high-fidelity methodology to retrieve the tow angles that maximize the buckling load and the fundamental frequency of VAT plates. A genetic algorithm is used to solve the optimization problem in which the objective function is mimicked using a surrogate model. Both unconstrained and manufactured-constrained problems are solved. The surrogates are built with outcomes from numerical models generated by means of the Carrera unified formulation, which enables to obtain straightforwardly different degrees of accuracy by selecting the order of the structural theory employed. The results show both the validity and flexibility of the proposed design approach. It is shown that, although the optimal design fiber angle orientations are consistently similar, discrepancies in the prediction of the buckling load or fundamental frequency can be found between high-fidelity layerwise and low-to-refined equivalent-single-layer models, of which classical laminated plate or first-shear deformation theories are degenerate examples.

关键词： Buckling Analysis structural modeling and simulation Fiber Volume Fraction Genetic Algorithm Finite Element Method Optimization Algorithm Mechanical and structural Vibrations Composite Structures Variable Stiffness Composites Variable-angle Tow

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Uncertainty Quantification of the ONERA 7A Rotor Performance and Loads Using Comprehensive Analysis

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JOURNAL OF AIRCRAFT 2023年第4期60卷 1141-1159页

作者： Khurana, Manas El Din, Itham Salah Yeo, Hyeonsoo Sci & Technol Corp Ames Res Ctr Moffett Field CA 94035 USA ONERA French Aerosp Lab Dept Aerodynam Aeroelast & Acoust F-92190 Meudon France US Army Combat Capabil Dev Command Aviat & Missile Ctr Ames Res Ctr Moffett Field CA 94035 USA

Quantification of blade stiffness uncertainties and sensitivities on rotor power and structural loads for the ONERA 7A rotor is established using the U.S. Army and ONERA rotorcraft comprehensive analysis tools. A stochastic-based approach is implemented to generate probabilistic bounds of the response outputs, including rotor performance and loads due to uncertainties in blade stiffness using 1) a Monte Carlo approach coupled directly with U.S. Army's rotorcraft comprehensive toolset, and 2) a surrogate of ONERA's rotorcraft comprehensive analysis solver using polynomial chaos expansions to efficiently predict the response outputs. The analysis showed that uncertainties in blade torsion, flap, and lag stiffnesses impact the predicted rotor power by a quantifiable amount. Significant uncertainties in peak torsion, flap, and chord bending moments are also confirmed. The sensitivities of the stiffness properties on response outputs using Sobol indices are also studied. The results show that total required power is exclusively sensitive to variability in torsion stiffness with no interaction effects with flap and lag stiffnesses. Sensitivities due to independent parameter effects and by combining with other parameters on peak structural loads are also examined. The analysis demonstrates the merits of integrating a stochastic, data-driven approach for uncertainty and sensitivity analyses in rotorcraft aeromechanics predictions.

关键词： structural Analysis Rotorcrafts structural modeling and simulation Continuous Probability Distributions Mathematical Analysis Polynomial Chaos Expansion Uncertainty Quantification Sensitivity Analysis Comprehensive Analysis Monte Carlo simulations

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Aeroelastic Analysis Using Deforming Cartesian Grids

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AIAA JOURNAL 2023年第3期61卷 1095-1108页

作者： Boschitsch, Alexander H. Whitehouse, Glen R. Continuum Dynam Inc Ewing NJ 08558 USA

Ongoing work in air-vehicle design illustrates the potential of advanced concepts to provide significant improvements in efficiency;but with their incorporation of lightweight flexible structures, such configurations may require active control systems to ensure reliability and safety. However, many contemporary analysis methods are inefficient for aeroelastic analysis and design of such configurations. This paper describes the development of a new approach that automates the geometry setup, mesh generation, and assembly of fluid-structural coupling interfaces to enable efficient aeroelastic and aeroservoelastic analysis of advanced concepts. The core elements for this approach are a cut-cell Cartesian grid-based computational fluid dynamics solver, a nonlinear beam element structural model, a conservative fluid-structural interface treatment, and the formulation and implementation of a new deforming grid capability within the cut-cell Cartesian grid solver. Herein, emphasis is on this latter component with detailed description given of the mesh motion strategy, evaluation of fluxes and structural loads at the surface, and computation of geometrical properties such as cell volume, directed face areas, centroids, and motion-induced fluxes for deforming Cartesian grids required to advance the flow states. Aeroelastic simulations exercising the capability show favorable agreement with data and predictions in the literature for subsonic and supersonic applications.

关键词： Aeroelastic Analysis structural modeling and simulation Computational Fluid Dynamics Unstructured Grid structural Displacement Supersonic Aircraft Flexible and Active Structures Aerodynamic Damping Cartesian Grids Deforming Grids

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

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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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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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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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Determinants of Pilots' Performance: Investigating Technology Trust and Situation Awareness

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JOURNAL OF AEROSPACE INFORMATION SYSTEMS 2024年第8期21卷 651-660页

作者： Lopes, Nuno Moura Aparicio, Manuela Neves, Fatima Trindade Univ Nova Lisboa NOVA Informat Management Sch NOVA IMS P-1070312 Lisbon Portugal Univ NOVA Lisboa NOVA IMS Campus Campolide Lisbon Portugal

simulation devices have been used in aviation training for decades, probably more than in other industries. Embarking on this study, we aim to understand the relationship between the information quality provided by the information system (simulator) to pilots with the effect on situation awareness and trust in technology. Also, we aim to understand how experienced pilots with total flight and simulator hours affect their situation awareness. Furthermore, the study introduces a novel theoretical model to explore how situation awareness and trust in technology jointly impact individual pilot performance. We used structured equation modeling within the data retrieved from a survey of 233 pilots. Our results show a large effect on individual pilot performance in a simulator between situation awareness and information quality. Also, the impact on trust in technology is supported with a large effect by information quality. There is a medium effect between information quality and situation awareness, with the experience shown by pilots having a small effect on situation awareness.

关键词： Operational Flight Trainer Information System Aviation Airline Operations Human Machine Interaction structural modeling and simulation Aviation Safety International Air Transport Association Crew Resource Management

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Framework of Physically Consistent Homogenization and Multiscale modeling of Beam Structures

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AIAA JOURNAL 2024年第12期62卷 4855-4869页

作者： Lu, Zhiyuan Zhang, Zewei Yang, Yu Dong, Leiting Atluri, Satya N. Beihang Univ Sch Aeronaut Sci & Engn Natl Key Lab Strength & Struct Integr Beijing 100191 Peoples R China Tianmushan Lab Hangzhou 310023 Peoples R China Aircraft Strength Res Inst China Natl Key Lab Strength & Struct Integr Xian 710065 Peoples R China Texas Tech Univ Dept Mech Engn Lubbock TX 79409 USA

In this work, a framework of physically consistent homogenization and multiscale modeling (PCHMM) is developed to analyze complex slender structures with homogenized one-dimensional beam models. Firstly, it is highlighted that periodic boundary conditions are not valid for the representative volume element (RVE)-based homogenizations if a shear-deformable beam model is to be obtained. Addressing this issue, physically consistent boundary conditions (PCBCs) are discussed in detail, which accounts for the influence of shear forces on the behavior of the slender structure and the corresponding RVE. A procedure of enforcing such boundary conditions is also given, applying sectional stresses to the RVE with fictitious DoFs. Additionally, we introduce a newly developed correct formula to calculate effective sectional properties which guarantee the cross-scale energy conservation though a modified Hill's condition. The PCHMM framework, with homogenization/dehomogenization procedures using PCBC and the modified Hill's condition, is also conveniently integrated into a commercial finite element software. The correctness and effectiveness of the developed framework of homogenization and multiscale analysis are demonstrated through several numerical examples, including lattice beams, twist-morphing metamaterial spars, and a realistic wing. The extension of this theory to plate/shell structures will be presented in our future work.

关键词： structural modeling and simulation Beam (Structures) Multiscale modeling Homogenization Boundary Condition

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