Aerospace and Materials最新文献

A Systematic Shear-Lag Approach for Analyzing the Failure Mechanisms in Ceramic Matrix Composites 陶瓷基复合材料破坏机制的系统剪切滞后分析方法

Aerospace and Materials Pub Date : 1996-11-17 DOI: 10.1115/imece1996-0484

D. D. Robertson, J. Solti, S. Mall

引用次数: 1

Failure Development in Particulate Composites 颗粒复合材料的失效发展

Aerospace and Materials Pub Date : 1996-11-17 DOI: 10.1115/imece1996-0494

A. Rubinstein, Peng Wang

引用次数: 0

Bridging Fiber Stress in Metal Matrix Composites: An Analytical Model 金属基复合材料中的桥接纤维应力:一个解析模型

Aerospace and Materials Pub Date : 1996-11-17 DOI: 10.1115/imece1996-0499

H. Ghonem

引用次数: 0

Fatigue Damage in Metal Matrix Composites 金属基复合材料的疲劳损伤

Aerospace and Materials Pub Date : 1996-11-17 DOI: 10.1115/imece1996-0488

G. Voyiadjis, R. Echle

{"title":"Fatigue Damage in Metal Matrix Composites","authors":"G. Voyiadjis, R. Echle","doi":"10.1115/imece1996-0488","DOIUrl":"https://doi.org/10.1115/imece1996-0488","url":null,"abstract":"\u0000 In recent years the design and performance of aerospace vehicles changed due to enhancement and improvement in the design and the materials employed. Special consideration has to be given to the performance of the materials chosen for such vehicles. Titanium matrix composites (TMC) have been identified among the metal matrix composites as candidate materials capable of sustaining the arising loads while maintaining their structural integrity. Material behavior during fatigue loading has to be given special consideration since this loading condition is dominant during the flight regime. Material degradation due to fatigue loading is modeled using a micro-mechanical fatigue damage model for uni-directional metal matrix composites. The evolution of damage is considered at the constituent level by employing a damage criteria for each individual constituent. The overall material damage is obtained by using the Mori-Tanaka averaging scheme. A numerical implementation of the model is used to demonstrate its capabilities by presenting the analytical results for damage evolution in the fibers as well as in the matrix material for isothermal high cycle fatigue loading. Results for varying material and model parameters are also presented.","PeriodicalId":326220,"journal":{"name":"Aerospace and Materials","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1996-11-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130617192","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Micromechanical Edge Effects in Glass Matrix Composites 玻璃基复合材料的微机械边缘效应

Aerospace and Materials Pub Date : 1996-11-17 DOI: 10.1115/imece1996-0469

G. Tandon, R. Kim, R. Dutton

引用次数: 0

A Finite Element Method for Separable HRR Solutions in Bi-Material Systems 双材料系统中可分离HRR解的有限元法

Aerospace and Materials Pub Date : 1996-11-17 DOI: 10.1115/imece1996-0464

Ningsheng Zhang, P. Joseph, A. Kaya

引用次数: 0

Characterization of Inelastic Deformation During the Transverse Loading of Weakly-Bonded Unidirectional Metal Matrix Composites 弱键单向金属基复合材料横向加载时的非弹性变形表征

Aerospace and Materials Pub Date : 1996-11-17 DOI: 10.1115/imece1996-0474

R. Neu, J. Kroupa

{"title":"Characterization of Inelastic Deformation During the Transverse Loading of Weakly-Bonded Unidirectional Metal Matrix Composites","authors":"R. Neu, J. Kroupa","doi":"10.1115/imece1996-0474","DOIUrl":"https://doi.org/10.1115/imece1996-0474","url":null,"abstract":"\u0000 A combined numerical and experimental analysis of a unidirectional titanium matrix composite (SCS-6/Timetal 21S) under a series of transverse loadings and unloadings is capable of separating the interfacial fiber-matrix bond strength into two distinct components: one associated with chemical bonding and the other with mechanical bonding. The influence of the mechanical bonding, which is the clamping due to the thermal residual stress state, is determined by finite element analysis with an imperfectly-bonded interface. The chemical bond strength is deduced by subtracting the mechanical bond strength component from the experimental response. Combined numerical and experimental analyses were conducted at two temperatures. At 25°C, the initial inelastic deformation from fiber-matrix separation is controlled by the mechanical component of the bond which is much larger than the chemical component; however, at 650°C, it is controlled by the chemical component. The mechanical bond strength is very dependent on temperature, whereas the chemical bond strength is only weakly dependent on temperature. In addition, the transverse response of unidirectional SCS-6/Timetal 21S was numerically determined for a wide range of temperatures (25°C to 815°C) and strain rates (8.33 × 10−4 1/s to 8.33 × 10−6 1/s) for both perfectly- and imperfectly-bonded cases.","PeriodicalId":326220,"journal":{"name":"Aerospace and Materials","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1996-11-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129526905","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

Fatigue of Ceramic Matrix Composites: Damage Mechanisms and Fatigue Life Diagrams 陶瓷基复合材料的疲劳:损伤机制和疲劳寿命图

Aerospace and Materials Pub Date : 1996-11-17 DOI: 10.1115/imece1996-0481

R. Talreja

引用次数: 4

A Micromechanical Model for Layered Porous Materials 层状多孔材料的微观力学模型

Aerospace and Materials Pub Date : 1996-11-17 DOI: 10.1115/imece1996-0468

Yinan Wu, N. Katsube

引用次数: 0

Modeling Delamination Growth in Composites 复合材料分层生长建模

Aerospace and Materials Pub Date : 1996-11-17 DOI: 10.1115/imece1996-0492

E. D. Reedy, F. Mello

{"title":"Modeling Delamination Growth in Composites","authors":"E. D. Reedy, F. Mello","doi":"10.1115/imece1996-0492","DOIUrl":"https://doi.org/10.1115/imece1996-0492","url":null,"abstract":"\u0000 A method for modeling the initiation and growth of discrete delaminations in shell-like composite structures is presented. The laminate is divided into two or more sublaminates, with each sublaminate modeled with four-noded quadrilateral shell elements. A special, eight-noded hex constraint element connects opposing sublaminate shell elements. It supplies the nodal forces and moments needed to make the two opposing shell elements act as a single shell element until a prescribed failure criterion is satisfied. Once the failure criterion is attained, the connection is broken, creating or growing a discrete delamination. This approach has been implemented in a three-dimensional finite element code. This code uses explicit time integration, and can analyze shell-like structures subjected to large deformations and complex contact conditions. The shell elements can use existing composite material models that include in-plane laminate failure modes. This analysis capability was developed to perform crashworthiness studies of composite structures, and is useful whenever there is a need to estimate peak loads, energy absorption, or the final shape of a highly deformed composite structure.\u0000 This paper describes the eight-noded hex constraint element used to model the initiation and growth of a delamination, and discusses associated implementation issues. Particular attention is focused on the delamination growth criterion, and it is verified that calculated results do not depend on element size. In addition, results for double cantilever beam and end notched flexure specimens are presented and compared to measured data to assess the ability of the present approach to model a growing delamination.","PeriodicalId":326220,"journal":{"name":"Aerospace and Materials","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1996-11-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127723193","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 2