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Advances in Aerospace Materials and Structures最新文献

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Determination of the Permeability Tensor of Fibrous Reinforcements for VARTM VARTM纤维增强材料渗透张量的测定
Advances in Aerospace Materials and Structures Pub Date : 1999-11-14 DOI: 10.1115/imece1999-0136
Pavel B. Nedanov, S. Advani, Shawn W. Walsh, William O. Ballata
{"title":"Determination of the Permeability Tensor of Fibrous Reinforcements for VARTM","authors":"Pavel B. Nedanov, S. Advani, Shawn W. Walsh, William O. Ballata","doi":"10.1115/imece1999-0136","DOIUrl":"https://doi.org/10.1115/imece1999-0136","url":null,"abstract":"\u0000 VARTM and SCRIMP composite manufacturing processes use a highly permeable media to distribute the resin through the thickness of the composite. Hence, manufacturing simulations of resin flow in such processes requires reliable data for in-plane as well as transverse permeability. The goal of this study is to propose a method for simultaneous determination of the principal values of 3D-permeability tensor of fibrous reinforcements. The permeability components are calculated from experimental data, consisting of flow front position with time during resin impregnation in three dimensions from a radial source under constant pressure using the SMARTweave [Walsh (1993), Fink et al.(1995)] sensor system. Experimental results are compared with numerical simulation.","PeriodicalId":240121,"journal":{"name":"Advances in Aerospace Materials and Structures","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116259336","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: 3
Buckling of Debonded (Delaminated) Sandwich Panels With Transversely Flexible Core 具有横向柔性芯的脱粘(分层)夹层板的屈曲
Advances in Aerospace Materials and Structures Pub Date : 1999-11-14 DOI: 10.1115/imece1999-0132
Y. Frostig, V. Sokolinsky
{"title":"Buckling of Debonded (Delaminated) Sandwich Panels With Transversely Flexible Core","authors":"Y. Frostig, V. Sokolinsky","doi":"10.1115/imece1999-0132","DOIUrl":"https://doi.org/10.1115/imece1999-0132","url":null,"abstract":"\u0000 Buckling behavior of sandwich panels with a compressible core which are debonded at one of their face sheet-core interfaces is presented. The buckling analysis is based on the principles of the High-Order Sandwich Panel Theory (HSAPT). The effect of the delamination length and location on the critical loads and the buckling modes is studied numerically. Edge delamination as well as inner delamination results are presented. The effect of contact on the critical loads and the buckling modes is presented. A comparison with experimental buckling modes is discussed and conclusions are drawn.","PeriodicalId":240121,"journal":{"name":"Advances in Aerospace Materials and Structures","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121509913","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: 6
A Numerical Approach to Predict the Mechanical Behaviour of Woven Fabric Composites 机织复合材料力学性能的数值预测方法
Advances in Aerospace Materials and Structures Pub Date : 1999-11-14 DOI: 10.1115/imece1999-0140
E. Riva
{"title":"A Numerical Approach to Predict the Mechanical Behaviour of Woven Fabric Composites","authors":"E. Riva","doi":"10.1115/imece1999-0140","DOIUrl":"https://doi.org/10.1115/imece1999-0140","url":null,"abstract":"\u0000 This paper presents a numerical tool for the design of the composites structures that allows to predict the mechanical behaviour of woven fabric composites, both in terms of global stiffness and damage process, and therefore to optimise the components dimensions and weight. Starting from an accurate study of the mesostructure of the material, finite element models are developed. To reduce the computational effort, a submodeling technique was used by employing two separate meshes: global and local meshes. Two idealised configurations are examined: they have a circular warp and fill yarn path and a lenticular cross-section. The mechanical response is estimated in terms of global stiffness and stress-strain curves of plain weave composites by simulating the damage process. The agreement between the FE global stiffness and experimental and analytical data is good. The FE results are very sensitive to the curvature of the yarns. Similar results were obtained for the FE stress-strain curves.","PeriodicalId":240121,"journal":{"name":"Advances in Aerospace Materials and Structures","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121696618","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
New Formulation for Composite Sandwich Shell Finite Element 复合材料夹层壳有限元新公式
Advances in Aerospace Materials and Structures Pub Date : 1999-11-14 DOI: 10.1115/imece1999-0139
A. Tabiei, R. Tanov
{"title":"New Formulation for Composite Sandwich Shell Finite Element","authors":"A. Tabiei, R. Tanov","doi":"10.1115/imece1999-0139","DOIUrl":"https://doi.org/10.1115/imece1999-0139","url":null,"abstract":"\u0000 Sandwich shell finite element formulation is developed and presented. The sandwich shell element formulation allows for orthotropic faces and core material. The sandwich shell element is based on first shell order shear deformable theory utilized by most shell finite elements for isotropic materials. Consequently, the presented procedure can be adopted for any shell element available in commercial finite element packages. The formulation is based on the equalities of stress and moment resultants between a sandwich shell element and a typical homogenous shell element. The developed element is implemented in the nonlinear finite element code DYNA3D to validate and check its accuracy, efficiency and overall performance. The predicted results show good agreement with results obtained from far more complicated and computationally intensive 3-D analyses.","PeriodicalId":240121,"journal":{"name":"Advances in Aerospace Materials and Structures","volume":"66 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122602741","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
Buckling and Postbuckling of Sandwich Beams With Delaminated Faces Based on Higher Order Core Theory 基于高阶核理论的分层夹层梁屈曲和后屈曲
Advances in Aerospace Materials and Structures Pub Date : 1999-11-14 DOI: 10.1115/imece1999-0129
R. Li, Y. Frostig, G. Kardomateas
{"title":"Buckling and Postbuckling of Sandwich Beams With Delaminated Faces Based on Higher Order Core Theory","authors":"R. Li, Y. Frostig, G. Kardomateas","doi":"10.1115/imece1999-0129","DOIUrl":"https://doi.org/10.1115/imece1999-0129","url":null,"abstract":"\u0000 Delaminations within the face sheets are often observed when a sandwich structure is exposed to impact loads. The buckling and postbuckling behavior of sandwich beams with delaminated faces is investigated in this work. The governing nonlinear equations, boundary conditions, and continuity conditions are formulated through variational principles. The beam construction consists of upper and lower, metallic or composite laminated symmetric skins, and a soft core of a foam or low strength honeycomb type. A high order theory is used for the core that accounts for the nonlinear distortion of the plane of section of the core and the compressibility in the vertical direction. The delamination considered is an interface crack, in which the substrate includes the transversely flexible core. The case of a debond at one of the skin-core interfaces is also included. The effects of the delamination length and location on the overall and local behavior are examined with an arbitrary initial imperfection.","PeriodicalId":240121,"journal":{"name":"Advances in Aerospace Materials and Structures","volume":"53 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122428335","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
Composite Materials in Defense: Overview and Outlook 国防用复合材料:综述与展望
Advances in Aerospace Materials and Structures Pub Date : 1999-11-14 DOI: 10.1115/imece1999-0145
L. Sloter
{"title":"Composite Materials in Defense: Overview and Outlook","authors":"L. Sloter","doi":"10.1115/imece1999-0145","DOIUrl":"https://doi.org/10.1115/imece1999-0145","url":null,"abstract":"\u0000 The Department of Defense maintains an annual investment of $7.4 billion in basic and applied research and advanced technology development. This investment is the foundation of future systems and operational capability and supports an annual $70 billion investment in the engineering development, testing, and acquisition of new systems. The Materials Science and Technology Program at $330 million per year forms a significant part of this investment. Currently, approximately $90 million within the Materials Program is invested in composite materials of all types. These investments are described in context of the overall Defense Science and Technology Program and with respect to the future Defense capabilities and materiel opportunities that are enabled by composite materials. Emphasis is placed on the changing nature of the Defense missions, the platforms required to meet those missions, and the role of composite materials in Defense platforms. Significant challenges posed by expected operations and acquisition needs are related to composite materials. The need for improved affordability in composite systems is discussed in terms of current projects and future challenges and outlook.","PeriodicalId":240121,"journal":{"name":"Advances in Aerospace Materials and Structures","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122616328","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
Delamination Suppression in Sandwich Beams Using Translaminar Reinforcements 跨层增强材料抑制夹层梁的分层
Advances in Aerospace Materials and Structures Pub Date : 1999-11-14 DOI: 10.1115/imece1999-0130
B. Wallace, B. Sankar, P. Ifju
{"title":"Delamination Suppression in Sandwich Beams Using Translaminar Reinforcements","authors":"B. Wallace, B. Sankar, P. Ifju","doi":"10.1115/imece1999-0130","DOIUrl":"https://doi.org/10.1115/imece1999-0130","url":null,"abstract":"\u0000 The present study is concerned with translaminar reinforcement in a sandwich beam for preventing buckling of a delaminated face-sheet under axial compression. Graphite/epoxy pins are used as reinforcement in the thickness direction of sandwich beams consisting of graphite/epoxy face-sheets and a Aramid honeycomb core. Compression tests are performed to understand the effects of the diameter of the reinforcing pins and reinforcement spacing on the ultimate compressive strength of the delaminated beams. A finite element analysis is performed to understand the effects of translaminar reinforcement on the critical buckling loads and post-buckling behavior of the sandwich beam under axial compression.","PeriodicalId":240121,"journal":{"name":"Advances in Aerospace Materials and Structures","volume":"54 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121565493","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
Optimal Design of Composite Plates Under Thermal Loads 热载荷作用下复合材料板的优化设计
Advances in Aerospace Materials and Structures Pub Date : 1999-11-14 DOI: 10.1115/imece1999-0143
S. Abrate
{"title":"Optimal Design of Composite Plates Under Thermal Loads","authors":"S. Abrate","doi":"10.1115/imece1999-0143","DOIUrl":"https://doi.org/10.1115/imece1999-0143","url":null,"abstract":"\u0000 In this article, the effect of thermal expansion on laminated composite plates are examined and the influence of the layup is studied using non-dimensional lamination parameters. A maximum of 12 parameters are needed to describe all possible laminates regardless of the number of plies. In some applications, the layup is selected to minimum thermal expansion in a certain direction. We show that thermal expansion cannot be prevented in all directions. Thermal deflections of symmetrically laminated plates that are continuous over many line supports are determined using the Rayleigh-Ritz method. The constitutive equations and the thermal loads are expressed in terms of four non-dimensional lamination parameters. Layups that minimize thermal deflections are determined for several types of composite plates subjected to temperature increases that vary linearly through the thickness.","PeriodicalId":240121,"journal":{"name":"Advances in Aerospace Materials and Structures","volume":"194 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116221698","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
Non-Circular Cylindrical Shells of Mid-Plane Asymmetric Construction Subjected to an Internal Pressure 受内压作用的中平面非对称结构的非圆圆柱壳
Advances in Aerospace Materials and Structures Pub Date : 1999-11-14 DOI: 10.1115/imece1999-0150
Zhaohui Chen, J. Vinson
{"title":"Non-Circular Cylindrical Shells of Mid-Plane Asymmetric Construction Subjected to an Internal Pressure","authors":"Zhaohui Chen, J. Vinson","doi":"10.1115/imece1999-0150","DOIUrl":"https://doi.org/10.1115/imece1999-0150","url":null,"abstract":"\u0000 In future large cargo transport aircraft, such as the Global Range Transport proposed in the New World Vistas program of the United States Air Force, it is likely that the fuselage cross-section will be non-circular. For efficient cargo space, the fuselage cross-section being investigated is that of a rectangle with rounded corners. In order to minimize the resulting bending stresses, sandwich construction is being investigated, and in particular a mid-plane asymmetric construction is being studied to utilize bending-stretching coupling to minimize these bending stresses still further in the sandwich construction. The bending-stretching coupling can be introduced by using sandwich faces of different thickness and/or different materials and/or different fiber orientation of the composite material.\u0000 The Theorem of Minimum Potential Energy is employed to investigate the subject problem. In this study, the lateral deflection that is assumed, a separable solution, employs the results of previous investigations: for the axial function, the lateral deflection of the analytical solution for a circular cylindrical shell with various boundary conditions subjected to an internal pressure is used; for the circumferential component of the lateral displacement, the series solution used previously by the authors for a ring solution of the same circumferential shape and loading is used.\u0000 The magnitude and location of the maximum stresses in each face for each material system is then determined, and the maximum deflection is also found. Thus, the mechanics of the elastic behavior of this elastic thin walled shell subjected to this loading is adequately described. Some example problems are discussed, and various material systems and geometries are compared.","PeriodicalId":240121,"journal":{"name":"Advances in Aerospace Materials and Structures","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127818536","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
Particulate Enhanced Damping in Sandwich Structures 夹层结构中的颗粒增强阻尼
Advances in Aerospace Materials and Structures Pub Date : 1999-11-14 DOI: 10.1115/imece1999-0134
S. Maley
{"title":"Particulate Enhanced Damping in Sandwich Structures","authors":"S. Maley","doi":"10.1115/imece1999-0134","DOIUrl":"https://doi.org/10.1115/imece1999-0134","url":null,"abstract":"\u0000 This paper investigates the damping effect of loose particulate within the core of sandwich structures. Beam specimens fabricated from aluminum honeycomb core and IM7 carbon fiber face sheets with various amounts of loose particulate are experimentally examined. Both free vibration and forced vibration tests are performed. It is shown that a moderate amount of particulate can cause a large increase in damping. The effect of varying amounts of particulate is also investigated. Plate equations of motion with damping and inertia terms are derived to model the beam and compare with experimental results. Effective mass and effective viscous damping are generated by matching the theoretical model to the experimental data.","PeriodicalId":240121,"journal":{"name":"Advances in Aerospace Materials and Structures","volume":"4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1999-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126919809","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
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