检索结果-内蒙古大学图书馆

53rd aiaa/asme/asce/ahs/asc structures, structural dynamics and materials conference

ISBN: (纸本)9781600869372

The proceedings contain 647 papers. The topics discussed include: hybrid optimization for wind turbine thick airfoils;multidisciplinary design optimization for a reusable launch vehicle using multiple-phase pseudospectral optimization;a deterministic approach for reliability based topology optimization;multi-objective shape optimisation for horizontal-axis wind turbine blades;MPD augmentation of a thermal air rocket utilizing low energy nuclear reactions;exploring the best performing commercial wind turbines for different wind regimes in a target market;dynamic Bayes nets in SHM;comprehensive framework for integration of calibration, verification and validation;accounting for proof test data in a reliability based design optimization framework;damage characterization method for structural health management using reduced number of sensor inputs;and sensor configuration and optimization for detection of micro-anomalies in structural materials.

关键词：

来源：评论

学校读者我要写书评

暂无评论

53rd aiaa/asme/asce/ahs/asc structures, structural dynamics and materials conference

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics ...

引用

53rd aiaa/asme/asce/ahs/asc structures, structural dynamics and materials conference 2012

ISBN: (纸本)9781600869372

The proceedings contain 648 papers. The special focus in this conference is on structures, structural dynamics and materials. The topics include: MPD augmentation of a thermal air rocket utilizing low energy nuclear reactions;multi-objective shape optimisation for horizontal-axis wind turbine blades;hybrid optimization for wind turbine thick airfoils;a deterministic approach for reliability based topology optimization;parameterization of curvilinear spars and ribs (SpaRibs) for optimum wing structural design;a recursive approach for remaining fatigue life predictions of monitored structural systems;dynamic Bayes nets in SHM;interpretations, relationships, and application issues in model validation;comprehensive framework for integration of calibration, verification and validation;assessment of the accuracy of a model for use in prediction of component environments;efficient stiffened composite plate analysis;impact damage resistance and tolerance of polymer nanofiber interleaved composite laminates;methodology for predicting the threat of runway debris impact to large transport aircraft;developments in morphing composites;exploratory structural investigation of a Hawkmoth-inspired MAV's thorax;dynamic analysis of composite stiffened panels subjected to compressive load;random fatigue damage accumulation under variable amplitude loading;study of load sequence effects in combined cyclic fatigue using CDM approach;fatigue reliability analysis for high cycle fatigue regime;effects of surface renewal on fatigue crack initiation and growth of 7050 aluminum alloy;simulation of guided wave propagation in isotropic and composite structures using LISA;evaluation of strength of component-laminates in strip-based mechanisms;optimization of axially compressed laminated curved panels with cutouts;iterative time reversal in dispersive and non-dispersive media;temporal life prediction analysis of a turbine engine blade to disk attachment;comparison of wind turbine models subjected

关键词：

来源：评论

学校读者我要写书评

暂无评论

Physics-Based Multiscale Creep Strain and Creep Rupture Modeling for Composite materials

引用

aiaa JOURNAL 2016年第2期54卷 703-711页

作者： Jensen, Eric M. Fertig, Ray S. Univ Wyoming Dept Mech Engn Dept 3295 1000 East Univ Ave Laramie WY 82071 USA

In this study, a novel multiscale combined creep strain and creep rupture model is proposed. By comparing to experimental data, it was shown that the model provides accurate creep rupture predictions for unidirectional off-axis specimens. The creep strain model provides accurate predictions within the confines of the restrictions used in its development. This coupled model was incorporated into a progressive failure finite-element simulation so that the effects of load redistribution could be considered, which tended to increase the life of the part when strain gradients were present. The finite-element implementation also allowed for the consideration of realistic geometries resulting in complex stress states. By considering a perfectly flat specimen and one containing worst-case thickness variation, experimental open-hole creep rupture data was accurately bounded. This suggests that, by quantifying material defects, realistic lifetime predictions can be made, and an estimate of scatter can be acquired.

关键词： CREEP (materials) STRAINS & stresses (Mechanics) FRACTURE mechanics MATHEMATICAL models COMPOSITE materials FINITE element method

来源：评论

学校读者我要写书评

暂无评论

Modeling of Highly Flexible Multifunctional Wings for Energy Harvesting 56

Modeling of Highly Flexible Multifunctional Wings for Energy...

引用

56th aiaa/asme/asce/ahs/asc structures, structural dynamics, and materials conference / 33rd Wind Energy Symposium / 23rd aiaa/ahs Adaptive structures conference

作者： Tsushima, Natsuki Su, Weihua Univ Alabama Dept Aerosp Engn & Mech Tuscaloosa AL 35487 USA

ISBN: (数字)9781624103421

ISBN: (纸本)9781624103421

In this paper, modeling of energy harvesting from transient vibrations of slender wings using piezoelectric transduction is implemented in a strain-based geometrically nonlinear beam formulation. The resulting structural dynamic equations for multifunctional beams are then coupled with a finite-state unsteady aerodynamic formulation, allowing for both energy harvesting and piezoelectric actuation with the nonlinear aeroelastic system. With the development, it is possible to provide an accurate, integral aeroelastic and electromechanical solution of both energy harvesting from and active control for wing vibrations, considering the geometrical nonlinear effects of slender wings. The current paper focuses on modeling the energy harvesting subsystem and exploring its impact on the multifunctional system. Vibrations of a slender multifunctional wing excited by both aeroelastic instability and external wind gusts will be considered as the sources of energy harvesting. All simulations will be completed in the time domain to accurately capture the nonlinear behaviors of the slender multifunctional wing. Based on the time-domain analysis, results of this effort illustrate that the piezoelectric energy harvesting from transient vibrations may provide adequate energy to support onboard sensor operations. In addition, results indicate that a well-tuned piezoelectric energy harvesting system may control the wing vibration using the shunt damping effect.

关键词： Piezoelectric Energy Harvesting Nonlinear Aeroelasticity Slender Wing Sensor Technology Flutter Analysis Free Stream Velocity Stiffness Matrices Piezoelectric materials Vibration Suppression Unmanned Aerial Vehicle

来源：评论

学校读者我要写书评

暂无评论

Strain-Based Analysis for Geometrically Nonlinear Beams: A Modal Approach

引用

JOURNAL OF AIRCRAFT 2014年第3期51卷 890-903页

作者： Su, Weihua Cesnik, Carlos E. S. Univ Alabama Dept Aerosp Engn & Mech Tuscaloosa AL 35487 USA Univ Michigan Dept Aerosp Engn Ann Arbor MI 48109 USA

A strain-based geometrically nonlinear finite element beam formulation for structural dynamic and aeroelastic analysis of slender beams and wings has been successfully applied to study the coupled nonlinear aeroelasticity and flight dynamics of different, very flexible aircraft. To improve the ability to use such aeroelastic framework in control design, a modal-based approach is developed in this paper to solve the strain-based nonlinear beam equation's with a reduced number of degrees of freedom. The modal approach is applied to study geometrically nonlinear static and transient problems of constrained and free slender beams, subject to external structural or aerodynamic excitations. Accuracy and performance of the new formulation are compared with the direct nonlinear finite element procedure.

关键词： structural dynamics RESEARCH AEROELASTICITY AEROdynamics -- Research GIrdERS DEFORMATIONS (Mechanics) ELASTIC deformation COMPOSITE materials -- Research

来源：评论

学校读者我要写书评

暂无评论

Compression After Impact Analysis on Thin Face Sheet Honeycomb Core Sandwich Panels

引用

JOURNAL OF SPACECRAFT AND ROCKETS 2014年第1期51卷 200-212页

作者： McQuigg, Thomas D. Kapania, Rakesh K. Scotti, Stephen J. Walker, Sandra P. Virginia Polytech Inst & State Univ Blacksburg VA 24060 USA NASA Langley Res Ctr Hampton VA 23681 USA

A research study has been conducted on compression after impact of thin facesheet honeycomb core sandwich panels. This paper is focused on the modeling and analysis used to simulate the tests described in a companion paper. Of interest are composite sandwich panels with aerospace applications, which contain either a 3 or 6 lb/ft(3) honeycomb core. It was found that compression after impact testing of these coupons resulted in either an indentation propagation failure for the lower density core or a crack propagation failure mode for the higher density core. An analysis model is developed to account for both modes through the inclusion of progressive failure analysis of the facesheets and a homogenized, nonlinear material model for the honeycomb core. In addition, significant impact damage detail is included in the model based on experimental observation. Analysis results are compared with the experimental results for each of the 24 sandwich panel specimens tested. Good agreement of failure mode predictions with test results demonstrates the importance of considering both facesheet and core failure, as well as the initial damage severity. Finally, a parametric study highlights the strength benefits compared with mass penalty for various core densities.

关键词： IMPACT testing RESEARCH SANDWICH construction (materials) HONEYCOMB structures COMPRESSION loads SPACE vehicles -- materials

来源：评论

学校读者我要写书评

暂无评论

Compression After Impact Experiments on Thin Face Sheet Honeycomb Core Sandwich Panels

引用

JOURNAL OF SPACECRAFT AND ROCKETS 2014年第1期51卷 253-266页

作者： McQuigg, Thomas D. Kapania, Rakesh K. Scotti, Stephen J. Walker, Sandra P. Virginia Polytech Inst & State Univ Blacksburg VA 24060 USA NASA Langley Res Ctr Res Directorate Hampton VA 23681 USA NASA Langley Res Ctr Struct Mech & Concepts Branch Hampton VA 23681 USA

Experiments have been used to study the compression after impact of thin face-sheet composite honeycomb core sandwich panels. The sandwich panels consist of very thin, woven S2-fiberglass face sheets adhered to a Nomex honeycomb core. Two sets of coupons were tested;they were identical, except one set contained a 3 lb/ft(3) density core, and the other contained a heavier 6 lb/ft3 density core. Static indentation and low-velocity impact using a drop tower were used to study damage formation in these materials with energy levels up to 9 ft-lb (foot-pounds). A series of highly instrumented compression after impact tests was then completed. New techniques for studying the response and failure include high-speed video photography as well as digital image correlation for the full-field deformation measurement. Two failure modes were observed. It is concluded that the failure mode of these materials depends solely on the honeycomb core density of the coupon, with the lighter density core experiencing an indentation propagation failure, while the heavier specimens experienced a crack propagation failure mode.

关键词： COMPRESSION loads RESEARCH COMPOSITE materials -- Testing materials -- Compression testing HONEYCOMB structures SANDWICH construction (materials) CRACK propagation (Fracture mechanics)

来源：评论

学校读者我要写书评

暂无评论

Integrated computational materials design: From genome to flight

Integrated computational materials design: From genome to fl...

引用

54th aiaa/asme/asce/ahs/asc structures, structural dynamics and materials conference

作者： Olson, G.B. Materials Science and Engineering Northwestern University QuesTek Innovations LLC 2220 Campus drive Evanston IL 60208 United States

ISBN: (纸本)9781624102233

The depth of scientific knowledge in physical metallurgy has enabled the development of a successful computational materials design methodology grounded in a system of fundamental databases. Expansion of the approach to embrace acceleration of the full development and qualification cycle has demonstrated flight of the first fully computationally designed and qualified material, and further cycle acceleration is underway. © 2013 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Design

来源：评论

学校读者我要写书评

暂无评论

The effect of scale dependent discretization on the progressive failure of composite materials using multiscale analyses 54

The effect of scale dependent discretization on the progress...

引用

54th aiaa/asme/asce/ahs/asc structures, structural dynamics and materials conference

作者： Ricks, Trenton M. Lacy Jr., Thomas E. Pineda, Evan J. Bednarcyk, Brett A. Arnold, Steven M. Department of Aerospace Engineering Mississippi State University 316B Walker Eng. Bld. Mississippi State MS 39762 United States NASA Glenn Research Center Mechanics and Life Prediction Branch 21000 Brookpark Rd. Cleveland OH 44135 United States

ISBN: (数字)9781624102233

ISBN: (纸本)9781624102233

A multiscale modeling methodology, which incorporates a statistical distribution of fiber strengths into coupled micromechanics/ finite element analyses, is applied to unidirectional polymer matrix composites (PMCs) to analyze the effect of mesh discretization both at the micro- and macroscales on the predicted ultimate tensile (UTS) strength and failure behavior. The NASA code FEAMAC and the ABAQUS finite element solver were used to analyze the progressive failure of a PMC tensile specimen that initiates at the repeating unit cell (RUC) level. Three different finite element mesh densities were employed and each coupled with an appropriate RUC. Multiple simulations were performed in order to assess the effect of a statistical distribution of fiber strengths on the bulk composite failure and predicted strength. The coupled effects of both the micro- and macroscale discretizations were found to have a noticeable effect on the predicted UTS and computational efficiency of the simulations. © 2012 aiaa.

关键词： ABAQUS

来源：评论

学校读者我要写书评

暂无评论

Computational plasticity model for hydrostatic pressure dependent foam materials 54

Computational plasticity model for hydrostatic pressure depe...

引用

54th aiaa/asme/asce/ahs/asc structures, structural dynamics and materials conference

作者： Chen, Xiuhua Wang, Hai You, Zhong School of Aeronautics and Astronautics Shanghai Jiao Tong University No. 800 Dongchuan Rd. Shanghai 200240 China Department of Engineering Science University of Oxford Parks Road Oxford OX1 3PJ United Kingdom

ISBN: (数字)9781624102233

ISBN: (纸本)9781624102233

A computational plasticity model for hydrostatic pressure dependent foam materials is presented. A new semi-associated flow rule is proposed for a three-parameter generalized initial yield criterion which is based on the second invariant of deviatoric tensor and the first invariant of spherical tensor. The parameters to determine the flow vector and the initial yield failure criterion are based on the three uniaxial strengths, which are obtained by uniaxial tension, compression and pure shear test respectively. Different from other wellknown flow rules which depends on the plastic Poisson ratio, this flow rule uses the standard strength values for plasticity flow and is more convenient and robust to be used. An implicit integration method by return mapping algorithm is carried out and the consistent tangent Jacobian matrix is also presented for the implicit integration. The plasticity model is implemented into the commercial finite element software ABAQUS for implicit finite element analysis. Simple numerical results are validated by the test results of foam materials. © 2013 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Hydrostatic pressure

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：