检索结果-内蒙古大学图书馆

AIAA Aviation Forum

作者： Ilie, Marcel Havenar, John Georgia Southern Univ Dept Mech Engn Statesboro GA 30458 USA

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

The aeroelastic phenomena of a modified ONERA M6 wing equipped with wingtip devices in transonic flight regimes is computationally studied using a fully-coupled aeroelastic approach. The present research concerns the development of a computationally efficient and accurate method for the aeroelastic studies of fixed wing in transonic and supersonic flows. Therefore, we propose a fully-coupled, time- marching aeroelastic approach utilizing an URANS model. The computational studies are carried out to assess the effect of the freestream Mach number and angle of attack on the structural dynamics and stresses developed in the ONERA M6 winglet wing. The studies are carried out for a range of Mach numbers, M-infinity = 0.8 - 1.4 and angles of attack, alpha = {2 degrees, 4 degrees, 6 degrees}. The analysis reveals that the aeroelastic deformation of the wing and induced stress in the wing structure increase with the freestream Mach number.

关键词： computational aeroelasticity Freestream Mach Number Angle of Attack Fluid Continuum Unsteady Reynolds Averaged Navier Stokes Winglets Structural Dynamics Wingtip Device Supersonic Flight Turbulent Boundary Layer

来源：评论

学校读者我要写书评

暂无评论

A DG-VLM framework for computational static aeroelastic analysis of composite wings

引用

COMPOSITE STRUCTURES 2025年 353卷

作者： Campagna, Dario Gulizzi, Vincenzo Benedetti, Ivano Univ Palermo Dept Engn Palermo Italy Nazl Alta Matemat Grp Nazl Fis Matemat Rome Italy

A computational framework for static aeroelastic analysis of composite laminated plates is proposed, whose novelty is the conjoined use of a structural discontinuous Galerkin (DG) formulation and an aerodynamic vortex lattice method (VLM), suitably coupled for the monolithic solution of the aeroelastic problem. The structural method is built on variable-order generalized kinematics, which allows the seamless adoption of either beam or plate modeling strategies, with on-demand order of polynomial approximation over the transverse and in-plane dimensions of the structural elements. The underlying DG formulation also simplifies the coupling between the structural and aerodynamic grids, thus providing a versatile tool for the aeroelastic analysis of either low or high aspect-ratio composite wings. Several numerical tests have been performed to assess the convergence features of the proposed framework as well as its accuracy with respect to available computational and experimental benchmark data. The obtained results confirm its robustness and highlight its potential for aeroelastic assessments in early aircraft conceptual design.

关键词： computational aeroelasticity Aeroelastic divergence Multi-layered composite plates Discontinuous Galerkin method Vortex lattice method

来源：评论

学校读者我要写书评

暂无评论

Roll Maneuverability of Transonic High-Aspect-Ratio-Wing Aircraft with Flared Folding Wingtips

引用

JOURNAL OF AIRCRAFT 2024年第3期61卷 915-938页

作者： Sanghi, Divya Cesnik, Carlos E. S. Riso, Cristina Univ Michigan Dept Aerosp Engn 1320 Beal Ave Ann Arbor MI 48109 USA Georgia Inst Technol Daniel Guggenheim Sch Aerosp Engn 275 Ferst Dr Northwest Atlanta GA 30332 USA

This paper investigates the roll maneuvers of a very flexible, transonic high-aspect-ratio-wing aircraft with flared folding wingtips, representing a potential future commercial transport configuration. The computational study leverages a fully coupled nonlinear aeroelastic-flight dynamics framework for simulating roll maneuvers commanded by deflecting control surfaces inboard or outboard of the flared folding wingtip hinge. Releasing the flared folding wingtips during flight makes the aircraft roll faster only when deflecting outboard-of-hinge leading-edge control surfaces. However, the achieved roll angles and rates are much lower than the ones obtained by deflecting inboard-of-hinge trailing-edge control surfaces, whose roll control effectiveness is not impacted or even degrades when releasing the flared folding wingtips. These trends are explained by analyzing the role of sweep-induced washout effects in the very flexible, transonic high-aspect-ratio wing, revealing physical mechanisms not identified in previous studies on straight or swept wings with moderate flexibility. Higher wing out-of-plane bending stiffness increases the effectiveness of flared folding wingtips in enhancing roll maneuvers at low dynamic pressure but plays a slight role at high dynamic pressure. This study highlights the need to consider the impact of washout effects for different flight conditions and levels of wing flexibility when assessing the ability of flared folding wingtips to enhance the roll maneuverability of transonic high-aspect-ratio-wing aircraft.

关键词： Flight Control Surfaces Aircraft Control Flight Dynamics Flexible Wings Transonic aeroelasticity Nonlinear aeroelasticity Wingtip Device computational aeroelasticity Roll Control Load Alleviation Control

来源：评论

学校读者我要写书评

暂无评论

computational aeroelastic analysis of wings based on the structural discontinuous Galerkin and aerodynamic vortex lattice methods

引用

AEROSPACE SCIENCE AND TECHNOLOGY 2024年 144卷

作者： Gulizzi, Vincenzo Benedetti, Ivano Univ Palermo Dept Engn Viale Sci Edificio 8 I-90128 Palermo Italy

An original computational framework for the aeroelastic analysis of wings featuring general transverse section is developed. The framework is based on the coupling between a novel discontinuous Galerkin structural model and an aerodynamic vortex lattice method, which is implemented in both the planar and non-planar version. The structural model, which constitutes the novelty of the present work, allows generalized kinematics and is thus able to capture higher-order structural deformation modes. With respect to other more used structural representations, the discontinuous Galerkin approach is based on the use of discontinuous basis functions and suitably-defined boundary terms to enforce the inter-element continuity and boundary conditions. Such features naturally enable high-order accuracy, ease of parallelization and, specifically for this work, straightforward coupling with the vortex lattice method. The framework is validated through benchmark tests, providing favourable matching with reference literature data.

关键词： computational aeroelasticity Discontinuous Galerkin method Higher-order structural modelling Vortex lattice method

来源：评论

学校读者我要写书评

暂无评论

Fluid-Structure Coupled Analysis of Maneuver Load Alleviation on a Large Transport Aircraft

引用

JOURNAL OF AIRCRAFT 2024年第4期61卷 1247-1261页

作者： Breitenstein, Christian Muller, Jens Hillebrand, Marco Woidt, Malte Haupt, Matthias Radespiel, Rolf Tech Univ Carolo Wilhelmina Braunschweig Inst Stromungsmech Aircraft Aerodynam Grp Hermann Blenk Str 37 D-38108 Braunschweig Germany Univ Stuttgart Inst Aerodynam & Gasdynam Aircraft Aerodynam Grp Pfaffenwaldring 21 D-70569 Stuttgart Germany Tech Univ Carolo Wilhelmina Braunschweig Inst Flugzeugbau & Leichtbau Multiphys Grp Hermann Blenk Str 35 D-38108 Braunschweig Germany Tech Univ Carolo Wilhelmina Braunschweig Inst Stromungsmech Hermann Blenk-Str 37 D-38108 Braunschweig Germany

Fluid-structure coupled simulations are performed for quasi-steady pitching maneuvers of a large transport aircraft with a load alleviation system consisting of trailing edge flaps and droop noses at the leading edge. For the fluid part of the simulation, a RANS approach is used, whereas the structural simulation is based on a linear modal model. The selected maneuvers are located on the lift boundary of the maneuver envelope at maximum load factor, as not only are the structural loads high here, but also redistributing lift for load alleviation is especially challenging as the wing is close to stall. For a target value of 33% reduction in wing bending loads, which is derived from the CS-25, the effects of applying load alleviation on wing loads, deformations, and aircraft maneuverability are investigated. It is found that the desired reduction of wing bending loads can be achieved for all maneuvers considered, while controlling the torsional moment turns out to be more difficult. A loss of maneuverability due to load alleviation is observed for only one of the maneuvers, while for the other maneuvers, maneuverability could even be increased. To assess the influence of the elasticity of the wing, additional simulations of the rigid wing are carried out and compared with the elastic results. Finally, other potential applications of the considered flap system are also explored. Here, for example, a cruise drag reduction of up to 1.8% is possible by adjusting the spanwise lift distribution.

关键词： Maneuver Loads Load Alleviation Load Control Flow Control computational aeroelasticity Transport Aircraft

来源：评论

学校读者我要写书评

暂无评论

Comparison of aerodynamic models for horizontal axis wind turbine blades accounting for curved tip shapes

引用

WIND ENERGY 2023年第1期26卷 5-22页

作者： Horcas, Sergio Gonzalez Ramos-Garcia, Nestor Li, Ang Pirrung, Georg Barlas, Thanasis Tech Univ Denmark DTU Dept Wind Energy Roskilde Denmark

Curved tip extensions are among the rotor innovation concepts that can contribute to the higher performance and lower cost of horizontal axis wind turbines. One of the key drivers to exploit their advantages is the use of accurate and efficient computational aerodynamic models during the design stage. The present work gives an overview of the performance of different state-of-the-art models. The following tools were employed, in descending order of complexity: (i) a blade-resolved Navier Stokes solver, (ii) a lifting line model, (iii) a vortex-based method coupling a near-wake model with a far-wake model, and (iv) two implementations of the widely used blade element momentum method (BEM), with and without radial induction. The predictions of the codes were compared when simulating the baseline geometry of a reference wind turbine and different tip extension designs with relatively large sweep angle and/or dihedral angle. Four load cases were selected for this comparison, to cover several aspects of the aerodynamic modeling: steady power curve, pitch step, extreme operating gust impact, and standstill in deep stall. The present study highlighted the limitations of the BEM-based formulations to capture the trends attributed to the introduction of curvature at the tip. This was true even when using the radial induction submodel. The rest of the computational methods showed relatively good agreement in most of the studied load cases. An exception to this was the standstill configuration, as the blade-resolved Navier-Stokes solver was the only code able to capture the highly unsteady effects of deep stall.

关键词： IEA 10 MW RWT computational aerodynamics computational aeroelasticity computational Fluid Dynamics Blade Element Momentum Lifting Line Near wake

来源：评论

学校读者我要写书评

暂无评论

Parametric AeroServoElastic-Gust Reduced-Order Models with State Consistence Enforcement

Parametric AeroServoElastic-Gust Reduced-Order Models with S...

引用

AIAA SciTech Forum

作者： Kim, Jinhyuk Shu, Jung, I Wang, Yi Simac, Josh Kaminsky, Andrew Univ South Carolina Dept Mech Engn Columbia SC 29208 USA CFD Res Corp Huntsville AL 35806 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

This paper presents a novel data-driven, parametric AeroServoElastic-Gust reduced-order models (ASEG-ROMs) in the state-space form to capture complex dynamic interactions between aerodynamics, control surfaces, structure, and gust load within a unified framework. To address the challenges associated with state inconsistence and rapid model coefficient variation across varying flight conditions, state-consistence enforced Autoregressive model with exogenous inputs (SCE-ARX) methods are employed, yielding salient state consistence, smooth model parameter variation, and excellent ROM interpolatibility. The optimal ROM configuration parameters are obtained under the guidance of the genetic algorithm (GA), enabling a fully automated ROM development process, and minimizing the experience and trial-and-error process of users. The effectiveness of ASEG-ROMs generated by SCE-ARX is compared with native ARX models and demonstrates consistent pole migration and dynamic transition of the interpolated ROMs, which, however, is absent in those generated by native ARX. The ASEG-ROMs can be easily reconfigured into other practically relevant ROMs, such as AE-, ASE-, and AEG-ROMs by removing specific physics components. The reconfigured ROMs also exhibit excellent performance when combined with GA-guided SCE-ARX. Overall, the proposed ASEG-ROMs offer accurate and reliable analysis capabilities for a broad range of flight conditions.

关键词： Reduced Order Modelling Aerodynamic Force Genetic Algorithm Control Surfaces Autoregressive Model Proper Orthogonal Decomposition computational aeroelasticity Aerodynamic Performance Stiffness Matrices Neural Networks

来源：评论

学校读者我要写书评

暂无评论

Flutter Prediction Report in Support of the High-Angle Working Group at the Third Aeroelastic Prediction Workshop

Flutter Prediction Report in Support of the High-Angle Worki...

引用

AIAA SciTech Forum

作者： Chwalowski, Pawel Stanford, Bret K. Jacobson, Kevin E. Poplingher, Lior Raveh, Daniella E. Jirasek, Adam Seidel, Jurgen Pagliuca, Giampaolo Berberoff-Naval, Jose N. Forster, Matt Righi, Marcello Immordino, Gabriele Da Ronch, Andrea Lamberson, Steven E. Prosser, Daniel Fadiga, Ettore Oliani, Stefano Rondina, Francesco Capone, Luigi NASA Langley Res Ctr Hampton VA 23681 USA Technion Israel Inst Technol Fac Aerosp Engn IL-3200003 Haifa Israel USAF Acad High Performance Comp Res Ctr Dept Aeronaut Colorado Springs CO 80840 USA BAE Syst Air Computat Engn Bristol BS34 7QW Avon England Zurich Univ Appl Sci Fed Inst Technol Zurich ETHZ1 Zurich Switzerland Zurich Univ Appl Sci Zurich Switzerland Univ Southampton Southampton Hants England Bowhead Total Enterprise Solut LLC Springfield VA 22150 USA NAWCAD Patuxent River Patuxent River MD 20670 USA NAWCAD Patuxent River Appl Aerodynam Branch Patuxent River MD 20670 USA Leonardo SpA Leonardo Labs Via Pieragostini 80 Genoa Italy Leonardo SpA Leonardo Labs Digital Twin & Adv Simulat Lab Via Pieragostini 80 Genoa Italy

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

This paper presents a summary of the computational flutter results associated with the AIAA third Aeroelastic Prediction Workshop (AePW-3) High-Angle Working Group (HAWG). The computational results are compared against the experimental data collected during the Pitch and Plunge Apparatus (PAPA) Benchmark Supercritical Wing (BSCW) test campaign conducted in the Transonic Dynamics Tunnel (TDT) at NASA Langley Research Center thirty years ago. During that test several flutter points were identified at transonic conditions. One of these points, specifically near Mach 0.8 and 5 degrees angle of attack, became a focal point of the computational challenge within HAWG. Various fidelity time-domain, Reduced Order Model (ROM) and Linearized Frequency Domain (LFD) methods were used by seven participating teams. While there are encouraging trends in the computational results, the range of the predicted flutter dynamic pressure is still quite large due to the stall flutter mechanism. A description of each participating team's software and methods is included.

关键词： Unsteady Reynolds Averaged Navier Stokes Reduced Order Modelling Angle of Attack computational aeroelasticity Signal Processing NASA langley research center Freestream Conditions Flow Conditions Doublet Lattice Method CFL3D

来源：评论

学校读者我要写书评

暂无评论

Evaluation of Generalised Forces Using CFD-Based Methods for Efficient Linear/Nonlinear Simulations

Evaluation of Generalised Forces Using CFD-Based Methods for...

引用

AIAA SciTech Forum

作者： Hale, Errol Candont, Michael Muscarello, Vincenzo Marzocca, Pier RMIT Univ Sir Lawrence Wackett Def & Aerosp Ctr Aerosp Engn & Aviat Melbourne Vic 3082 Australia RMIT Univ Sir Lawrence Wackett Def & Aerosp Ctr Melbourne Vic 3082 Australia

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

The development of efficient and accurate Reduced-Order Models (ROMs) for transonic aeroelastic systems with freeplay poses a significant challenge for aeroelasticians, requiring linearization of both nonlinear structural and aerodynamic systems. In this paper, well established aerodynamic and structural model order reduction methods are rigorously assessed for their usability, efficiency and accuracy when applied an all-movable tail model with freeplay in the transonic flow regime. Two methods for augmenting the structural modal basis are considered, namely fictitious masses (FM) and residual vectors (RV), while the transonic aerodynamic forces are modeled using CFD-based aerodynamic impulse response functions. The results demonstrate that under full nonlinear fluid loading conditions both the FM and RV approaches perform excellently (against the benchmark full CFD-CSD solution). When considering linearized aerodynamic loading, the FM model outperforms RV. The limitations of the linearized aerodynamic ROM are also assessed, demonstrating a significant reduction in accuracy for freeplay values greater than 0.1

关键词： computational Fluid Dynamics Reduced Order Modelling Unsteady Aerodynamic Modeling computational aeroelasticity Unsteady Transonic Flow Finite Element Modeling ANSYS Frequency Response Functions Dynamic Modelling Flight Envelope

来源：评论

学校读者我要写书评

暂无评论

Load and Displacement Transfer through Quaternion-Based Formulation of the Absolute Orientation Problem

Load and Displacement Transfer through Quaternion-Based Form...

引用

AIAA SciTech Forum

作者： Kiviaho, Jan F. Collins, Eric Univ Dayton Res Inst Dayton OH 45469 USA Mississippi State Univ Ctr Adv Vehicular Syst CAVS Starkville MS 39762 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

Load and displacement transfer schemes facilitate the partitioned analysis of fluid-structure interactions (FSI). The Matching-based Extrapolation of Loads and Displacements (MELD) transfer scheme was developed to enable the analysis and design optimization studies of a particular aeroelastic model, and it has since been employed in several studies of similar configurations. MELD relies on the solution of the absolute orientation problem, in which an optimal rigid motion is sought to fit the displacement described by two sets of positional measurements. MELD's original implementation of the solution is based on the singular value decomposition (SVD). In this implementation, the SVD must be differentiated, which entails certain mathematical intricacies and programming complexities. This current work explores a quaternion-based formulation of the absolute orientation problem with a solution that avoids the SVD. Eliminating the complications of the SVD leads to simpler and more robust load and displacement transfer algorithms, which are presented. The work also explores a reinterpretation of MELD in terms of continuum mechanics and statistical analysis. This added perspective on the methodology makes it easier to compare to alternatives.

关键词： Fluid Structure Interaction Continuous Probability Distributions computational aeroelasticity Continuum Mechanics Design Optimization Structural Simulation Structural Finite Elements Black Box American Institute of Aeronautics and Astronautics Point Set Registration

来源：评论

学校读者我要写书评

暂无评论

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案：

请选择收藏分类：

通借通还

建议与咨询 留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案： 新增检索档案 确定 取消

请选择收藏分类： 新增自定义分类 确定 取消

通借通还

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

请选择保存的检索档案：

请选择收藏分类：