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A 3D implicit structured multi-block grid finite volume method for computational structural dynamics

AEROSPACE SCIENCE AND TECHNOLOGY 2021年 117卷 106980-106980页

作者： Ma, Li Barakos, George N. Zhao, Qijun Nanjing Univ Aeronaut & Astronaut Natl Key Lab Rotorcraft Aeromech Nanjing 210016 Peoples R China Univ Glasgow Sch Engn CFD Lab Glasgow G12 8QQ Lanark Scotland

This work aims to develop a FVM-based structural solver that can seamlessly be integrated with computational Fluid dynamics (CFD) solvers for fluid-structure interaction (FSI) problems. For flexibility in gridding and efficient computation, hexahedral multi-block grids are adopted which are locally structured, but globally unstructured. Besides, ghost cells are introduced to solve the partial derivatives and displacements at the boundaries of the computational domain. Time-accurate solutions are obtained by employing a matrix-free, dual time stepping approach, and the implicit residual value smoothing method is used to increase the convergence rate. Stresses are evaluated using Green's theorem based on the gradients of the displacement of the cells. The proposed method is applied to static and dynamic response of 3D cantilevers. Results are found to agree well with analytical solutions, and the amplitude error of the dynamic response is less than 1.5%. Besides, resonance and beating phenomena were clearly observed and compared to Finite Element approaches in accuracy and efficiency. Finally, the dynamic response of a cantilever beam with NACA0012 airfoil is analyzed preliminarily. (C) 2021 The Authors. Published by Elsevier Masson SAS.

关键词： Finite volume method computational structural dynamics Multi-block grids Matrix-free dual time-stepping Dynamic response Airfoil

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Numerical investigation of flexible flapping wings using computational fluid dynamics/computational structural dynamics method

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PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING 2018年第1期232卷 85-95页

作者： Liu, Long Li, Hongda Ang, Haisong Xiao, Tianhang Nanjing Univ Aeronaut & Astronaut Coll Aerosp Engn Yudao St 29 Nanjing 210016 Jiangsu Peoples R China

A fluid-structure interaction numerical simulation was performed to investigate the flow field around a flexible flapping wing using an in-house developed computational fluid dynamics/computational structural dynamics solver. The three-dimensional (3D) fluid-structure interaction of the flapping locomotion was predicted by loosely coupling preconditioned Navier-Stokes solutions and non-linear co-rotational structural solutions. The computational structural dynamic solver was specifically developed for highly flexible flapping wings by considering large geometric non-linear characteristics. The high fidelity of the developed methodology was validated by benchmark tests. Then, an analysis of flexible flapping wings was carried out with a specific focus on the unsteady aerodynamic mechanisms and effects of flexion on flexible flapping wings. Results demonstrate that the flexion will introduce different flow fields, and thus vary thrust generation and pressure distribution significantly. In the meanwhile, relationship between flapping frequency and flexion plays an important role on efficiency. Therefore, appropriate combination of frequency and flexion of flexible flapping wings provides higher efficiency. This study may give instruction for further design of flexible flapping wings.

关键词： Flexible flapping wings computational fluid dynamics computational structural dynamics co-rotational flexion fluid-structure interaction

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Three-Dimensional Aeromechanical Analysis of Lift Offset Coaxial Rotors: A Helios Test Case

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JOURNAL OF AIRCRAFT 2024年第3期61卷 939-956页

作者： Patil, Mrinalgouda Datta, Anubhav Univ Maryland Aerosp Engn College Pk MD 20742 USA

Three-dimensional (3-D) solid finite element analysis (FEA) is used to model and study coaxial helicopter rotors. The 3-D FEA is coupled with a lifting line aerodynamic model with free wake to capture rotor-rotor interactions. Two open-access models are developed: one is the Metaltail (a hingeless coaxial rotorcraft), and the other is the coaxial rotor built from articulated UH-60A-like rotors. The former is the main focus of this work and is developed as an example case for the U.S. Army/DoD rotorcraft simulation software CREATETM-AV Helios, while the latter is merely for a regression test. The analysis is performed on a low-speed transition flight for which qualitative data are available for the Sikorsky S-97 Raider aircraft for comparison. Predictions of performance, airloads, vibratory loads, and 3-D stresses are discussed. In the absence of available geometry or property data of the S-97, this study is primarily meant to serve as a capability demonstration of 3-D rotor structural dynamic modeling for such rotors.

关键词： Articulated Rotor Finite Element Analysis Multibody dynamics Regression Testing Computer Aided Design Stress-Strain Analysis Rotorcraft computational structural dynamics Coaxial Rotors Lift Offset

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A meshless Runge-Kutta-based Physics-Informed Neural Network framework for structural vibration analysis

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ENGINEERING ANALYSIS WITH BOUNDARY ELEMENTS 2025年 170卷

作者： Xiao, Shusheng Bai, Jinshuai Jeong, Hyogu Alzubaidi, Laith Gu, Yuantong Queensland Univ Technol Sch Mech Med & Proc Engn Brisbane Qld 4000 Australia Queensland Univ Technol ARC Ind Transformat Training Ctr Joint Biomech Brisbane Qld 4000 Australia Tsinghua Univ Inst Biomech & Med Engn Dept Engn Mech AML Beijing 100084 Peoples R China

In recent years, Physics-Informed Neural Networks (PINN) have emerged as powerful meshless numerical methods for solving partial differential equations (PDEs) in engineering and science, including the field of structural vibration. However, PINN struggles due to the spectral bias when the target PDEs exhibit highfrequency features. In this work, a meshless Runge-Kutta-based PINN (R-KPINN) framework for structural vibration modelling is proposed for the first time. In the framework, the meshless features of traditional PINN are retained while applying Runge-Kutta (R-K) time integration to discretise the temporal domain, thereby reducing computational demands and enhancing temporal flexibility. Besides, the proposed R-KPINN allows for segmental training of PINN, reducing the dimensionality of the structural vibration problems and offering accurate solutions to relatively high-frequency functions. Through numerical examples including free, damped, and forced vibration of Euler-Bernoulli beams, the proposed framework provides effective and precise solutions for predicting the responses of structures. In summary, the proposed R-KPINN framework provides a flexible, efficient, and interpretable meshless method for solving structural vibration problems with state-of-the-art PINN techniques.

关键词： Physics-informed neural network computational structural dynamics Meshless method Runge-Kutta method

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An integrated three-dimensional aeromechanical analysis for the prediction of stresses on modern coaxial rotors

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INTERNATIONAL JOURNAL OF HIGH PERFORMANCE COMPUTING APPLICATIONS 2024年第4期38卷 356-376页

作者： Patil, Mrinalgouda Lumba, Ravi Jayaraman, Buvana Datta, Anubhav Univ Maryland Aerosp Engn College Pk MD USA US Army Combat Capabil Dev Command Aviat & Missile Ctr Moffett Field CA USA Univ Maryland Dept Aerosp Engn 3179 Glenn L Martin Hall Bldg 0884298 Campus Dr College Pk MD 20740 USA

This paper presents the first application of an Integrated Three-Dimensional aeromechanical analysis-defined as the coupled solution of three-dimensional finite element-based structural dynamics with a three-dimensional Reynolds-Averaged Navier-Stokes-based fluid dynamics-to predict the stresses on a modern coaxial rotor. The coupling was carried out with the University of Maryland's structural dynamic solver X3D and the U.S. Army's CREATETM-AV Helios suite of fluid dynamic solvers. A modern four-bladed hingeless coaxial rotor model-inspired by the gross dimensions of the Sikorsky S-97 Raider but generic and open source otherwise-is developed as a demonstration test case. The new structural solver is driven by parallel and scalable solvers and advanced high performance computing. It is enabled by high-order three-dimensional brick finite elements unified with multibody dynamics, integrated aerodynamics, and a special 3D-to-1D fluid-structure interfaces refines the power of delta-coupling procedure while retaining the advantages of existing CFD mesh motion schemes. The analysis predicts the three-dimensional stresses on the rotor blades and hub, together with the deformations, airloads, and wake, in an integrated manner. Two flight conditions are studied: a low-speed flight at 37 knots and a high-speed flight at 150 knots. Interesting three-dimensional unsteady stress patterns are revealed all across the blade but particularly inboard of 50% rotor radius-patterns that change from flight to flight and have remained invisible until now-since they could neither be predicted nor measured in flight. The maximum axial stresses exhibited 3/rev variation at low speed, and 2/rev variation at high speed flight. The lower rotor carried higher oscillatory stress burden at low speed, whereas both the rotors shared the same stress burden at high speed flight. The key conclusion is that such analysis is now indeed possible, and the stress patterns they reveal provide deeper insight

关键词： Coaxial rotors lift offset computational fluid dynamics computational structural dynamics 3-D finite element analysis 3-D RANS high performance computing X3D helios

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A POD-based input-output reduced-order modeling framework for acceleration of coupled-solver workflows

A POD-based input-output reduced-order modeling framework fo...

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AIAA SciTech Forum

作者： House, Alec M. Kaminsky, Andrew L. Wang, Yi Alam, Farid Pant, Kapil Tison, Nathan Korivi, Vamshi CFD Res Corp Aerosp & Def Solut Huntsville AL 35806 USA Univ South Carolina Dept Mech Engn Columbia SC 29208 USA CFD Res Corp Biol Energy & Mat Div Huntsville AL 35806 USA US Army DEVCOM Ground Vehicle Syst Ctr Flow Thermal & Survivabil Modeling & Simulat Bran Warren MI 48092 USA US Army DEVCOM Ground Vehicle Syst Ctr Analyt Div Warren MI 48092 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

Physics-based simulations of multiphysics interactions between multiple domains are present in nearly all engineering domains. Classically, these multiphysics simulations involve the coupling of two or more computational solvers, many of which may be computationally expensive, especially for resolving transient phenomena. In this work, a novel approach for the acceleration of coupled-solver workflows is introduced. The developed input/output reduced-order model (I/O ROM) combines model order reduction methods and data-driven surrogate modeling techniques to enable approximation of a single solver in a coupled-solver workflow. The novel component of this work stems from the framework's ability to both predict and ingest high-dimensional computational fields at the interfaces of the problem domains. The developed framework is demonstrated through the approximation of a computational fluid dynamics (CFD) solver in a conjugate heat transfer (CHT) workflow for prediction of the surface temperature of a simple vehicle geometry. The I/O ROM was shown to accelerate the CHT simulation by nearly two orders of magnitude to within 0.5% error on the surface of the ground vehicle.

关键词： Proper Orthogonal Decomposition Adaptive Mesh Refinement Convective Boundary Condition Cumulative Distribution Function Incompressible Flow Convection Fluid Structure Interaction Temperature Fields Conduction computational structural dynamics

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High-fidelity Aerostructural Optimization Benchmark for Aircraft Propellers in Hover

High-fidelity Aerostructural Optimization Benchmark for Airc...

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AIAA SciTech Forum

作者： Zoppelt, Seth A. Koyuncuoglu, Heyecan U. He, Ping Iowa State Univ Dept Aerosp Engn Ames IA 50011 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

This paper proposes an aerostructural optimization benchmark for aircraft propellers working in a hover condition. This benchmark uses an untwisted and untapered blade with a NACA0012 sectional profile as the baseline design. The objective function is the propeller shaft power coefficient. The design variables include the propeller twist, shape, chord, span, and rotation speed. The constraints include the propeller thrust coefficient, mass, von Mises stress, and geometry (e.g., thickness and curvature). We propose three different optimization configurations with various combinations of design variables. The proposed propeller aerostructural optimization benchmark can be solved using various optimization algorithms and modeling fidelities. This paper showcases a high-fidelity gradient-based optimization approach. To be more specific, we use the finite-volume computational fluid dynamics and finite-element structural dynamics solvers to simulate the fluid and solid domains, respectively. We then use the discrete adjoint approach to compute the derivatives for gradient-based optimization with a large number of design variables. To consider fluid-structure interaction and coupled derivative computation, we utilize OpenMDAO/MPhys, an open-source framework that facilitates high-fidelity multidisciplinary design optimization. We compare the objective, constraints, and distributions of spanwise shape, twist, and thrust between the baseline and optimized designs. This study has the potential to build a common benchmark and promote collaboration in the propeller multidisciplinary design optimization community.

关键词： Aerostructural Optimization Aircraft Propeller computational Fluid dynamics Propeller Performance OpenMDAO Multidisciplinary Design and Optimization Power Coefficient Fluid Structure Interaction Airfoil Profiles computational structural dynamics

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CFD-CSD Pre- test Hover Predictions Validation for the HVAB Rotor

CFD-CSD Pre- test Hover Predictions Validation for the HVAB ...

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AIAA SciTech Forum

作者： Jain, Rohit US Army Combat Capabil Dev Command Aviat & Missil Moffett Field CA 94035 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

Pre-test hover predictions obtained for the 11.08-foot-diameter, 4-blade, Mach-scaled Hover Validation and Acoustic Baseline (HVAB) rotor were compared with the recent hover test measurements obtained in the National Full-Scale Aerodynamics Complex (NFAC) 80- by 120-Foot Wind Tunnel at NASA Ames Research Center. The predictions were obtained using high-fidelity computational Fluid dynamics (CFD)-computational structural dynamics (CSD) coupled simulations in the CREATETM-AV Helios framework. Helios used NASA OVERFLOW and NASA FUN3D solvers for near-body CFD modeling and RCAS for CSD modeling. A comprehensive comparison was performed that included rotor performance, blade motions and deformations, laminar-turbulent transition location, airloads, surface pressure, and wake trajectory. Overall, the predictions agreed well with the test data.

关键词： computational Fluid dynamics computational structural dynamics Laminar Turbulent Transition National Full Scale Aerodynamics Complex FUN3D NASA NASA langley research center Wind Tunnel Walls Transition Modeling Vortex Structure

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Reduced order aerodynamic modeling augmented with neural network surrogate models coupled with rotorcraft comprehensive analysis

Reduced order aerodynamic modeling augmented with neural net...

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AIAA SciTech Forum

作者： Martinez-Gonzalez, Daniel Sitaraman, Jayanarayanan Jude, Dylan Roget, Beatrice Wissink, Andrew NASA Ames Res Ctr Sci & Technol Corp Moffett Field CA 94035 USA US Army Combat Capabil Dev Command Aviat & Missi Moffett Field CA USA Jude Aerodynam LLC Mountain View CA USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

Advancements in computational rotorcraft aeromechanics often necessitate the integration of multiple high-cost numerical solvers. The use of surrogate models has become an efficient and popular method to replace expensive components in simulation while retaining satisfactory accuracy. This paper details the latest advancements in a convolutional neural network-based surrogate model designed for helicopter rotor blades. Integrated within the CREATET-AV Helios Reduced Order Aerodynamic Model (ROAM), the surrogate is adept at predicting blade surface pressure fields on-par with high-fidelity simulations. The model accuracy and generalization capabilities are showcased in coupled computational Fluid dynamics/computational structural dynamics (CFD/CSD) rotor blade simulations. Moreover, the surrogate delivers results two orders of magnitude faster than high-fidelity methods. Validation cases reveal the model's proficiency in conducting effective trim calculations and providing improved predictions than existing lifting line aerodynamics that use airfoil tables.

关键词： computational Physics Rotorcrafts Convolutional Neural Network Aerodynamic Coefficients computational Fluid dynamics Rotor Blades computational structural dynamics Helicopter Rotor Airfoil American Institute of Aeronautics and Astronautics

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Numerical Investigation of Aeroelastic Characteristics of Grid Fin

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AIAA JOURNAL 2022年第5期60卷 3107-3121页

作者： Ye, Kun Zhang, Yifan Chen, Zeshuai Ye, Zhengyin Northwestern Polytech Univ Sch Aeronaut Xian 710072 Peoples R China

Grid fin is widely used in the field of aerospace because of its unique advantages in the aerodynamic and structural performance. Meanwhile, the aerodynamic and structural characteristics of the grid fin are quite different from those of the conventional rudder. Deep understanding of the aeroelastic characteristics and mechanism of the grid fin is of great reference value for the fine design of grid fin. In this paper, an efficient reduction-order-method-based aeroelastic analysis method is established, and the method is verified by the flutter case of AGARD 445.6 wing. Finally, based on this method, the flowfield characteristics and the variation of flutter characteristics with Mach number are studied in detail. The results show that in the subsonic region, the transonic flutter "dip " of the grid fin occurs earlier than that of the conventional wing due to the acceleration effect of the grid fin on the airflow. In the transonic region, when the flowfield is characterized by a bow shock wave, the critical flutter speed increases slightly with the increase of Mach number. However, in the supersonic region, when the flowfield is characterized by an oblique shock wave, the flutter critical velocity increases substantially with the increase of Mach number. It is found that the variation law of the flutter boundary with Mach number is very similar to that of the normal force and the pitching moment with Mach number, and there is a close relationship between them. The ratio of flutter speed of the grid fin to the freestream velocity will reach the minimum value near Ma=1.6. At the same time, it is discovered that the flutter instability of the grid fin is mainly caused by the coupling of the bending mode and torsional mode of the grid fin, and the instability mode is the torsional mode. Meanwhile, it should be noted that the flutter coupling characteristics of the grid fin differ greatly from those of the conventional rudder surface due to the great difference in structu

关键词： Grid Fin Aerodynamic Force Coefficients Aeroelastic Stability Shock Front Oblique Shock Direct Numerical Simulation Aerodynamic Performance computational structural dynamics Reynolds Averaged Navier Stokes Supersonic Flow

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