Analysis and Design Issues for Modern Aerospace Vehicles最新文献

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Free Vibration Analysis of Composite Plates With Tailored Thermal Residual-Stresses 热残余应力定制复合材料板的自由振动分析
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0721
S. F. M. de Almeida, J. Hansen
{"title":"Free Vibration Analysis of Composite Plates With Tailored Thermal Residual-Stresses","authors":"S. F. M. de Almeida, J. Hansen","doi":"10.1115/imece1997-0721","DOIUrl":"https://doi.org/10.1115/imece1997-0721","url":null,"abstract":"\u0000 Thermal residual-stresses introduced during manufacture and their effect on the free vibration of stringer stiffened composite plates is investigated. The principal idea in the work is to include stiffeners on the perimeter of a composite plate in which the laminate for the stiffeners and the plate are different. Such an arrangement yields manufacturing induced thermal residual-stresses which result from the difference in manufacturing and operating temperatures as well as the difference in thermal expansion coefficients and elastic properties of the plate and the stiffeners. The analysis is based on an enhanced Reissner-Mindlin plate theory and involves two separate calculations. In the first, the thermal residual-stress state is determined for an unconstrained plate. In the second, the free vibration problem is solved; thermal effects from the first calculation are included by way of nonlinear membrane-bending coupling which in turn defines the free vibration reference state. The problem is solved using a finite element formulation to determine the natural frequencies and vibration modes of the plates. Two different plate-stiffener geometries are used to illustrate the effects of stringer size, stringer placement and temperature difference. Two principal results are obtained: first, it is shown that thermal residual-stresses can have a significant effect on the natural frequencies; secondly, thermal residual-stresses can be tailored to increase natural frequencies.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"79 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128144788","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
Micromechanics Study of Plastic Zone at Crack Tip in Steel Under Cyclic Load 循环荷载作用下钢裂纹尖端塑性区的细观力学研究
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0746
Qing Wang, Mingyuan Du, F. Chiang
{"title":"Micromechanics Study of Plastic Zone at Crack Tip in Steel Under Cyclic Load","authors":"Qing Wang, Mingyuan Du, F. Chiang","doi":"10.1115/imece1997-0746","DOIUrl":"https://doi.org/10.1115/imece1997-0746","url":null,"abstract":"A novel experimental micromechanics technique SIEM (Speckle Interferometry with Electron Microscopy) is employed to examine the plastic deformation field at crack tip during fatigue process. A fatigue cracked specimen made of AISI-SAE 1035 carbon steel was tested under a three-point bend load. Both displacement and strain fields were mapped over an area of 50μm by 40μm at the crack tip. Accumulation of the local damage due to fatigue was revealed by showing the evolution of the plastic zone at the crack tip. Crack growth was found in mixed mode at small scale. The variation of plastic crack opening displacement with the number of fatigue cycles in both mode I and mode II were determined. Two mechanism of crack propagation, crack branching and crack-wake ligament bridging, were observed and clearly demonstrated on the deformation map.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125749514","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
Micromechanics of High Cycle Fatigue in Single and Polycrystals 单晶和多晶高周疲劳细观力学
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0748
T. Lin, K. Wong, N. Teng
{"title":"Micromechanics of High Cycle Fatigue in Single and Polycrystals","authors":"T. Lin, K. Wong, N. Teng","doi":"10.1115/imece1997-0748","DOIUrl":"https://doi.org/10.1115/imece1997-0748","url":null,"abstract":"\u0000 The micromechanic analysis of a fatigue band in the most favorably oriented crystal at the free surface of a polycrystal is reviewed. The localization of plastic strain in thin slip bands under monotonic loadings and the ratchet mechanism of fatigue bands provided by the stress fields of two closely located parallel thin slices sliding in opposite directions are shown. Each of these two thin slices slides monotonically. The alternate sliding of the two thin slices results in the macroscopic forward and backward plastic strain in cyclic loading.\u0000 Single crystals are used in turbine engine parts. The fatigue band analysis of polycrystals is extended to analyze the fatigue band in single crystals. Hysteresis loops of a single crystal under constant stress amplitudes and under constant plastic strain amplitudes are shown. Two sets of these hysteresis loops, one with small initial stress and one with large initial stress, are presented. These calculated hysteresis loops explains the two diagonal sharp corners in each loop to be due to reversals of loadings.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"25 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115073340","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
On the Response of a Sandwich Panel With a Bilinear Core 双线性堆芯夹层板的响应研究
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1080/107594199305656
L. Mercado
{"title":"On the Response of a Sandwich Panel With a Bilinear Core","authors":"L. Mercado","doi":"10.1080/107594199305656","DOIUrl":"https://doi.org/10.1080/107594199305656","url":null,"abstract":"\u0000 Sandwich panels can fail in a variety of ways. In the present paper one type of failure is investigated and modeled which has a number of important applications, e.g., marine hulls. Here core yielding is assumed to initiate and grow in the sandwich panel while the face sheets remain bonded, unbuckled and in the elastic range. For elastic face sheets, the core shear stresses can be determined from equilibrium of the face sheets independent of core yield. Core shear strains can then be found from the stress-strain curve and an algorithm is constructed for determining shear deflection. Bending deflection is found from the elastic solution. This approach works well except when the bilinear stress strain behavior approaches the perfectly plastic core. With the aid of a detailed finite element solution it is shown that the classical sandwich theory assumptions begin to break down and that the face sheets now carry an appreciable part of the shear load. This effect is shown in detail for four point beam bending where the classical sandwich solution is 20∼30% below the ABAQUS results and the experimental data. For the bilinear case, not close to perfectly plastic, however, the extension of the classical theory to the core yielding problem provides excellent results.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129921451","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: 19
Mechanisms for Size Effects in Bending of Fiber Composites 纤维复合材料弯曲尺寸效应机理研究
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0708
S. Swanson
{"title":"Mechanisms for Size Effects in Bending of Fiber Composites","authors":"S. Swanson","doi":"10.1115/imece1997-0708","DOIUrl":"https://doi.org/10.1115/imece1997-0708","url":null,"abstract":"\u0000 The size of the specimen or structure has often been cited as having an effect on the apparent strength of fiber composites. Bend tests are often used to infer size effects, as the stressed volume is typically smaller than in uniform tension or compression test specimens. However bend tests also have a stress gradient through the thickness. In the present work a model is developed for compression failure of fiber composites that includes through-the-thickness effects. A primary feature of the model is that through-the-thickness shear stresses are predicted to occur because of the varying bending displacement of the wavy fibers. These shear stresses have a stabilizing effect on the fibers, and thus raise the apparent compressive strength. When applied to bend tests, the model predicts that the apparent compressive strength of fiber composites will depend on the specimen thickness, in accord with experimental evidence in the literature. The result is that through-the-thickness effects are predicted to affect the compressive strength of fiber composites, and this effect is distinct from a true size effect.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"60 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122889150","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
Computation of the Maximum Amplitude of a Mistuned Bladed Disk Assembly via Infinity Norm 用无穷范数计算失谐叶盘总成的最大振幅
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0742
A. Sinha
{"title":"Computation of the Maximum Amplitude of a Mistuned Bladed Disk Assembly via Infinity Norm","authors":"A. Sinha","doi":"10.1115/imece1997-0742","DOIUrl":"https://doi.org/10.1115/imece1997-0742","url":null,"abstract":"\u0000 The maximum amplitude of a mistuned bladed disk assembly has been computed on the basis of the infinity norm of a complex matrix relating amplitudes and phases of blades’ vibration and sinusoidal forcing functions. Numerical results are presented for a model containing a single degree of freedom per blade. In addition, minimum values of the maximum amplitude have also been computed along with their sensitivities to small changes in mistuning parameters.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"44 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123344732","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: 19
A Finite Element Modal-Coordinate Formulation for Thermal Postbuckling of Composite Plates 复合材料板热后屈曲的有限元模态坐标公式
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0724
Yucheng Shi, Raymond Y. Y. Lee, C. Mei
{"title":"A Finite Element Modal-Coordinate Formulation for Thermal Postbuckling of Composite Plates","authors":"Yucheng Shi, Raymond Y. Y. Lee, C. Mei","doi":"10.1115/imece1997-0724","DOIUrl":"https://doi.org/10.1115/imece1997-0724","url":null,"abstract":"\u0000 A finite element formulation in modal coordinates is developed for nonlinear thermal postbuckling of thin composite plates. The linear buckling mode shapes used to model the postbuckling deflection are investigated. The participation from each mode to the postbuckling deflection is presented quantitatively. The minimum number of modes for convergent solution can be assured. Postbuckling of symmetrically laminated, antisymmetric angle-ply, and unsymmetrically laminated composite plates under mechanical and thermal loads are studied. Deflection shape changes are observed in long rectangular plate. Multiple postbuckling solutions or branches are obtained for plate under combined mechanical and thermal loadings.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"24 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123176672","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
Stress Dependency of the Thermoelastic and Piezoelectric Coefficients 热弹性系数和压电系数的应力依赖性
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.2514/2.680
C. Bert, V. Birman
{"title":"Stress Dependency of the Thermoelastic and Piezoelectric Coefficients","authors":"C. Bert, V. Birman","doi":"10.2514/2.680","DOIUrl":"https://doi.org/10.2514/2.680","url":null,"abstract":"\u0000 An analysis based on fundamental mechanics and thermodynamics is presented for a solid in which the elastic and piezoelectric coefficients are temperature dependent. It is proven that as a consequence of the temperature dependency, the thermal expansion and piezoelectric coefficients must be stress dependent.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124655979","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: 12
Stacking Sequence Effects on the Process-Induced Free-Edge Stresses in Thermoplastic Composite Laminates 叠层顺序对热塑性复合材料层合板工艺诱导自由边应力的影响
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0712
M. Domb, J. Hansen
{"title":"Stacking Sequence Effects on the Process-Induced Free-Edge Stresses in Thermoplastic Composite Laminates","authors":"M. Domb, J. Hansen","doi":"10.1115/imece1997-0712","DOIUrl":"https://doi.org/10.1115/imece1997-0712","url":null,"abstract":"\u0000 A numerical model is developed for prediction of the process-induced thermal residual stresses in thermoplastic composite laminates. The model addresses the development of the residual stress state in fracture-critical free-edge regions as well as through-thickness stress variations. The current approach provides a unique capability for the investigation of the influence of thermal processing and structural parameters on the resulting buildup of residual stresses during manufacturing. Therefore, it can assist in the design and analysis of thermoplastic composites to tailor mechanical and strength characteristics. Thermal processing considered here includes solidification from the molten state at a specific surface cooling rate, and application of a posterior annealing cycle. A significant reduction in the free-edge stresses is obtained via a quench/anneal cycle in comparison to the recommended nominal cooling from the melt. Alteration of the stacking sequence of the plies in the laminate can further reduce the magnitude of the interlaminar stresses. Results are shown for the case of a quasi-isotropic APC-2 (graphite/PEEK) laminate configuration.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127613798","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
Similitude of Failure and Size Effect in Fiber Composites 纤维复合材料的破坏相似性及尺寸效应
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0704
Z. Bažant
{"title":"Similitude of Failure and Size Effect in Fiber Composites","authors":"Z. Bažant","doi":"10.1115/imece1997-0704","DOIUrl":"https://doi.org/10.1115/imece1997-0704","url":null,"abstract":"\u0000 The present brief paper reviews recent test resuts at Northwestern University and to briefly outlines some new theoretical, experimentally yet unconfirmed, deductions for the law governing the size effect in failures with an asymptotic residual stress in the crack, which may be either tensile, due to unbroken crack-bridging fibers, or compressive, due to buckling of fibers in a kink band treated apporoximately as a compression crack. This law is of approximate nature and ensues as a simple asymptotic matching of the size effects for small and large structural sizes.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"24 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1997-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122967575","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
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