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检索条件"任意字段=54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference"

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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...

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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

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Deployable membrane structures with rolled-up booms and their deployment characteristics 54

Deployable membrane structures with rolled-up booms and thei...

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

作者： Natori, M.C. Katsumata, Nobuhisa Okuizumi, Nobukatsu Watanabe, Akihito Yamakawa, Hiroshi Waseda University Advanced Research Institute for Science and Engineering 3-4-1 Okubo / 55S-608 Shinjyuku Tokyo 165-8555 Japan Waseda University Department of Modern Mechanical Engineering 3-4-1 Okubo / 59-314 Shinjyuku Tokyo 165-8555 Japan Department of Mechanical Aerospace and Materials Engineering Muroran Institute of Technology 27-1 Mizumoto Muroran Hokkaido 050-8585 Japan Department of Space Flight Systems 3-1-1 Chuoh-ku Yoshinodai Sagamihara Kanagawa 252-5210 Japan Sakase Adtech Co. Ltd 14-10 Shimoyasuta Maruoka-cho Sakai City Fukui 910-0363 Japan Waseda University Shinjyuku 3-4-1 Okubo Tokyo 165-8555 Japan

ISBN: (数字)9781624102233

ISBN: (纸本)9781624102233

Based on geometrical considerations on folding patterns of disk-like flat surfaces, deployable membrane structures with rolled-up booms and deployment behaviors of those conceptual models are presented. Newly developed bi-convex tape booms covered by braid, which deploy from rolled-up configuration by their own stowed elastic energy without any actuators, are applied for two types of deployable membrane space structures;one is with hoop booms (hoop design) and the other is with rib booms (rib design). Hoop design structures are introduced using small conceptual models, and their deployment is demonstrated. As rib design structures, conceptual models suitable for stepwise deployment procedure are developed, and their various deployment aspets are shown in detail. © 2013 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Membrane structures

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X-FEM Co-simulation of delamination and matrix cracking in fiber metal laminated structures under fatigue loading 54

X-FEM Co-simulation of delamination and matrix cracking in f...

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

作者： Fang, Eugene Stuebner, Michael Lua, Jim GEM-NJ Office Global Engineering and Materials Inc. Princeton NJ 08540 United States

ISBN: (数字)9781624102233

ISBN: (纸本)9781624102233

A mesh independent discrete multi-mode damage insertion, propagation, and interaction solution module has been developed and implemented within Abaqus via its user-defined subroutines. the resulting toolkit can perform the co-simulation of metal ply cracking and its associated delamination evolution at the composite and metal ply interface under constant amplitude fatigue loading. It can characterize multiple initial delaminations and ply cracks that are independent of an existing finite element mesh and track their moving fronts without remeshing. A solid shell based on an assumed-strain approach is implemented to capture 3D stress distribution in thin plies. the phantom pair element approach and the VCCT are applied to extract the stress intensity factor at crack tips. A virtual extension technique is used to improve the SIF prediction. A user-defined element for a discrete spring has been developed and coupled with a virtual crack closure technique (VCCT). A two-way fatigue damage control module has been developed based on the criticality of the fracture parameters at either the delamination or the metal crack front. Robustness and feasibility of the developed toolkit for Abaqus has been demonstrated through its application to both a conventional and non-conventional FML system with single and multiple initial cracks. © 2012 aiaa.

关键词： Metals

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A systematic approach to materials information management for aerospace design

A systematic approach to materials information management fo...

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44th aiaa/asme/asce/ahs/asc structures, structural dynamics, and materials conference

作者： Marsden, Will M. Cebon, David Granta Design Cambridge United Kingdom

ISBN: (纸本)9781624101007

the materials information requirements of the aerospace sector are considered, specifically 'consolidation' (management of raw test data), 'analysis' (investigation of material trade-offs) and 'dissemination (secure distribution of data throughout an organization). An information architecture that satisfies the complex requirements of the aerospace materials industry is discussed and a case-study is presented.

关键词： Aerospace engineering

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Topology optimization of thermal structures with stress constraints 54

Topology optimization of thermal structures with stress cons...

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

作者： Deaton, Joshua D. Grandhi, Ramana V. Wright State University Department of Mechanical and Materials Engineering Dayton OH 45435 United States

ISBN: (数字)9781624102233

ISBN: (纸本)9781624102233

It is known in topology optimization, that in the presence of thermal loading, the conventional maximum stiffness design objectives generally do not lead to maximum strength structures due to the design dependency of thermoelastic loads. In this paper we present the application of stress constraints to structural topology optimization problems with thermal loading in an effort to develop a new technique for the design of hot structures where thermal stresses are of primary concern. A modern stress-relaxation technique is employed to circumvent the singularity phenomena in the stress constraints. In addition, we utilize stress aggregation functions to reduce the number of constraints in the optimization problem. We note that pre-existing formulations for thermoelastic topology optimization and stress-constraint handling are employed, but for the first time they are combined to consider thermal stresses. Preliminary numerical results indicate that the stress-constrained problem leads to different designs with superior thermoelastic performance when compared to the minimum compliance problems. In today's aerospace industry, a number of practical examples are evident where the capability developed in this work is desirable. these include the design of engine exhaust-washed structures (EEWS) on embedded engine aircraft and integrated thermal protection systems (TPS) on hypersonic vehicles. In both cases, structural components are subjected to an extreme combined loading environment that is characterized by elevated temperatures and design against thermal stresses is of paramount concern. © 2013 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： thermal stress

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On a probabilistic strain-based fatigue life estimation

On a probabilistic strain-based fatigue life estimation

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44th aiaa/asme/asce/ahs/asc structures, structural dynamics, and materials conference

作者： Heffern, thomas Kolar, Ramesh Dept. of Aero. and Astronautics Naval Postgraduate School Monterey CA 93943 United States

ISBN: (纸本)9781624101007

Probabilistic approaches in the design and analysis of aerospace vehicle have attracted attention in recent times. In particular, the fatigue life prediction and risk assessment of structural components is of importance in the aging aircraft. this paper discusses the application of Monte Carlo simulation technique for determination of fatigue material constants to be used in the strain-based approach to fatigue.

关键词： Fatigue of materials

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A domain evolution model for the ferroelectric hysteresis of piezoceramic materials

A domain evolution model for the ferroelectric hysteresis of...

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44th aiaa/asme/asce/ahs/asc structures, structural dynamics, and materials conference

作者： Narayanan, V. Lu, X. Hanagud, S. School of Aerospace Engineering Georgia Institute of Technology Atlanta GA 30332-0150 United States

An applicable and physically based model that bridges micro- and macroscopic concepts was developed to describe the nonlinear material and thermodynamic behaviors of piezoelectric ceramics. the Von Mises circular dist... 详细信息

ISBN: (纸本)9781624101007

关键词： Piezoelectric materials

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Improving spectral signatures for fatigue crack identification

Improving spectral signatures for fatigue crack identificati...

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

作者： Cooley, Phillip E. Slater, Joseph C. Shiryayev, Oleg V. Wright State University Department of Mechanical and Materials Engineering Dayton OH 45435 United States Petroleum Institute Abu Dhabi United Arab Emirates

ISBN: (纸本)9781624102233

Fatigue cracks pose significant risk to turbomachinery blisks, and current inspection methods are slow, costly and imperfect. Developing an automated structural health monitoring (SHM) system can help to reduce costs and improve detection probability, but a fast method for producing the necessary data libraries is prerequisite. In an effort to develop such a method for simulating nonlinear structural response, fatigue cracks in beams have been modeled as inputs to the system to produce an approximate closed-form solution for the total response. Although the time savings are considerable, and the method has proven capable of correctly identifying fatigue cracks over an effective region in data generated by a more traditional dual-model approach, additional renement is needed. the self-excitation terms are no longer assumed, but are now derived by considering damage as a perturbation of the area moment of inertia. Alternative definitions for the spectral signature are considered, and a new type of profile is developed to permit validation against experimental data from a single damaged beam. Some experimental data is obtained, though the input has spectral distortion. Although the simulation and experimental results are similar, there are still discrepancies that remain and will need to be investigated. Overall, more experimental results are needed to validate and improve the investigated method before it can be applied to more complicated structures such as bladed disks. © 2013 by Phillip E. Cooley, Oleg V. Shiryayav, and Joseph C. Slater.

关键词： Fatigue crack propagation

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Smart armors made from shape memory materials

Smart armors made from shape memory materials

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44th aiaa/asme/asce/ahs/asc structures, structural dynamics, and materials conference

作者： Kamel, G.M.A. Egyptian Army Military technical research center Egyptian National Authority for Standardization Egypt

ISBN: (纸本)9781624101007

Modeling and mathematical calculation showed that a 0.01 of armor thickness will reduce the speed from 1400 M/S to 1300 M/S due to shape memory effect. Experimental firing test on polyamide material revealed that the shape memory effect has a great effect to stop the bullet after a short distance compared to the material not equipped with this shape memory property.

关键词： Armor

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Component mode reduced order models for geometric mistuning of integrally bladed rotors 54

Component mode reduced order models for geometric mistuning ...

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

作者： Beck, Joseph A. Brown, Jeffrey M. Cross, Charles J. Slater, Joseph C. Air Force Research Laboratory Aerospace Systems 1950 5th Street Wright-Patterson AFB OH 45433 United States Department of Mechanical and Materials Engineering Wright State University 3640 Colonel Glenn Hwy Dayton OH 45435 United States

ISBN: (数字)9781624102233

ISBN: (纸本)9781624102233

Two methods that explicitly model airfoil geometry surface deviations for mistuning prediction in integrally bladed rotors (IBRs) are developed by performing a modal analysis on different degrees of freedom (DOFs) of a parent reduced order model (ROM). the parent ROM is formulated with Craig-Bampton component mode synthesis in cyclic symmetry coordinates for an IBR with a tuned disk and airfoil geometric deviations. the first method performs an eigen-analysis on the constraint-mode DOFs that provides a truncated set of interface modes while the second method includes the disk fixed interface normal mode in the eigen-analysis to yield a truncated set of ancillary modes. Both methods can utilize tuned or mistuned modes, where the tuned modes have the computational benefit of being computed in cyclic symmetry coordinates. Furthermore, the tuned modes only need to be calculated once which offers significant computational savings for subsequent mistuning studies. Each geometric mistuning method relies upon the use of geometrically mistuned airfoil modes in the component mode framework to provide a very accurate ROM. Free and forced response results are compared to both the full finite element model (FEM) solutions and a traditional frequency-based approach used widely in academia and the gas turbine industry. It is shown that the developed methods provide highly accurate results with a significant reduction in solution time compared to the full FEM and parent ROM. © 2012 aiaa.

关键词： Airfoils

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