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Analysis and Design Issues for Modern Aerospace Vehicles最新文献

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Singular Solutions of Multi-Material Wedges Under Thermomechanical Loading 热机械载荷下多材料楔的奇异解
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0718
W. Yin, K. Jane, Chien-chang Lin
{"title":"Singular Solutions of Multi-Material Wedges Under Thermomechanical Loading","authors":"W. Yin, K. Jane, Chien-chang Lin","doi":"10.1115/imece1997-0718","DOIUrl":"https://doi.org/10.1115/imece1997-0718","url":null,"abstract":"\u0000 Multi-material wedges associated with free edges, matrix and interface cracks, adhesive joints, skin-stiffener attachments and other types of discontinuities in composite structures generally incur singular stress fields at the vertex of the wedge. Accurate elasticity solutions of the wedge under thermo-mechanical loads may be obtained by combining eigensolutions with appropriate coefficients and a particular solution associate with the loading. When the wedge is under a temperature load, or when the two exterior edges of the wedge are subjected to non-vanishing traction loads, the elasticity solution may differ significantly from the asymptotic solution as given by the dominant singular term. In such cases, a failure criterion in terms of the asymptotic solution or the stress intensity factors may not be appropriate.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"27 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":"126745877","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
Vibration of a Flexible Solar Array Caused by the Change of Thermal Input in Orbit 轨道热输入变化引起的柔性太阳帆板振动
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0720
L. Tabacchi, M. Natori, Hiroshi Hirikado
{"title":"Vibration of a Flexible Solar Array Caused by the Change of Thermal Input in Orbit","authors":"L. Tabacchi, M. Natori, Hiroshi Hirikado","doi":"10.1115/imece1997-0720","DOIUrl":"https://doi.org/10.1115/imece1997-0720","url":null,"abstract":"\u0000 Behaviour of large flexible space structures (antennas, solar arrays, frames of space stations, etc.) is strongly influenced by thermal loads in orbit. Thermally induced forces can affect flexible space structures in several ways: thermal buckling and thermally induced vibrations due to relatively rapid heating are two typical phenomena. In orbit attitude disturbances of an actual spacecraft are presented as a remarkable example of such phenomena. Analytical models are developed and numerical simulations performed in order to demonstrate that the vibration of the spacecraft flexible solar arrays is the most likely disturbance source. The results are shown to be in agreement with flight data and laboratory tests.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"39 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":"126919212","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
Thermal Stresses in a Layer due to a Train of Laser Pulses 由激光脉冲序列引起的层内热应力
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0713
R. Hetnarski, L. Hector, Woo-Seung Kim
{"title":"Thermal Stresses in a Layer due to a Train of Laser Pulses","authors":"R. Hetnarski, L. Hector, Woo-Seung Kim","doi":"10.1115/imece1997-0713","DOIUrl":"https://doi.org/10.1115/imece1997-0713","url":null,"abstract":"\u0000 A solution of a thermoelastic problem dealing with the effects of the radiation generated by a repetitively pulsing laser directed toward a thin thermoelastic layer bonded to an inert semi-space is presented. Both the thermoelastic potential method and the Love stress function are employed. The temporal variation of each pulse is modeled mathematically as a function with three constants, while the radial intensity distribution of each pulse is taken as a Gaussian distribution. Results are presented in the form of graphs.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"30 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":"128371482","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
Statical and Vibrational Behavior of Orthogonally Reinforced Flat Panels Exposed to Thermomechanical Loading 热机械载荷下正交加固平板的静态和振动特性
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0714
M. Souza, L. Librescu
{"title":"Statical and Vibrational Behavior of Orthogonally Reinforced Flat Panels Exposed to Thermomechanical Loading","authors":"M. Souza, L. Librescu","doi":"10.1115/imece1997-0714","DOIUrl":"https://doi.org/10.1115/imece1997-0714","url":null,"abstract":"\u0000 A number of results related with the non-linear response of orthogonally stiffened flat panels exposed to thermomechanical loading are presented. The results concern both the statical and vibrational responses.\u0000 The effects played in this context by the various reinforcement schemes and the initial geometric imperfection are considered and pertinent conclusions are highlighted. The paper constitutes a completion of a number of results previously reported by the authors of this paper (see Librescu and Souza (1992, 1997) and Souza and Librescu (1995).","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"18 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":"115721591","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
Variability of Rotor Wake Interactions and Airfoil Unsteady Aerodynamics 旋翼尾流相互作用的变异性与翼型非定常空气动力学
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0740
A. J. Sanders, S. Fleeter,
{"title":"Variability of Rotor Wake Interactions and Airfoil Unsteady Aerodynamics","authors":"A. J. Sanders, S. Fleeter,","doi":"10.1115/imece1997-0740","DOIUrl":"https://doi.org/10.1115/imece1997-0740","url":null,"abstract":"\u0000 Multistage interaction effects on rotor blade-to-blade wake variability and the resulting downstream vane row unsteady aerodynamic response are experimentally investigated in a high speed fan stage. Multistaging effects on the rotor wake are quantified by acquiring data over two complete rotor revolutions at each of several IGV clocking positions relative to downstream stationary probes. The resulting downstream vane response data are acquired over a range of steady loading conditions, with both design and off-design operation of the rotor considered. Multistage interactions are shown to significantly affect the rotor wake characteristics and lead to the generation of rogue wakes. The fundamental periodicity of these interactions is one complete rotor revolution due to the unequal number of blades and vanes in the machine. The rotor wake and resultant vane row unsteady aerodynamic response variability are also quantified. Off-design rotor operation results in wakes with the largest variability, on the order of the average velocity deficit. The vane response variability is even more pronounced, being as large as 160% of the maximum average unsteady lift over one blade pass period.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"76 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":"127284887","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
Orthotropic Column Buckling: The Euler and Engesser/Haringx/Timoshenko Formulas Versus an Elasticity Solution 正交各向异性柱屈曲:欧拉和Engesser/Haringx/Timoshenko公式与弹性解
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0707
G. Kardomateas
{"title":"Orthotropic Column Buckling: The Euler and Engesser/Haringx/Timoshenko Formulas Versus an Elasticity Solution","authors":"G. Kardomateas","doi":"10.1115/imece1997-0707","DOIUrl":"https://doi.org/10.1115/imece1997-0707","url":null,"abstract":"\u0000 The well known column buckling formulas of Euler and these of Engesser / Haringx / Timoshenko (which correct for transverse shear) were derived for isotropic materials, and are routinely used in composite structural applications. The accuracy of these formulas, when orthotropic composite material and moderate thickness are involved, is investigated in the present study by comparing the critical loads from these formulas with the predictions of a three-dimensional orthotropic elasticity solution. The column is assumed to be in the form of a hollow circular cylinder and the Euler or Timoshenko loads are based on the axial modulus. As an example, the cases of an orthotropic material with stiffness constants typical of glass/epoxy or graphite/epoxy and the reinforcing direction along the periphery or along the cylinder axis are considered. First, it is found that the elasticity approach predicts in all cases a lower than the Euler value critical load. Moreover, the degree of non-conservatism of the Euler formula is strongly dependent on the reinforcing direction; the axially reinforced columns show the highest deviation from the elasticity value. Second, the Engesser or first Timoshenko shear correction formula is conservative in all cases examined, i.e. it predicts a lower critical load than the elasticity solution. The Haringx or second Timoshenko shear correction formula is in most cases (but not always) conservative. However, in all cases considered, the second estimate is always closer to the elasticity solution than the first one. For the isotropic case both Timoshenko formulas are conservative estimates.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"36 12 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":"130795604","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-Uniqueness of Two Inverse Problems of Thermally and Force-Loaded Smart Structures: Sensor Shaping and Actuator Shaping Problem 热载荷和力载荷智能结构反问题的非唯一性:传感器整形和执行器整形问题
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0715
H. Irschik, A. Belyaev, M. Krommer, K. Schlacher
{"title":"Non-Uniqueness of Two Inverse Problems of Thermally and Force-Loaded Smart Structures: Sensor Shaping and Actuator Shaping Problem","authors":"H. Irschik, A. Belyaev, M. Krommer, K. Schlacher","doi":"10.1115/imece1997-0715","DOIUrl":"https://doi.org/10.1115/imece1997-0715","url":null,"abstract":"\u0000 Flexural vibrations of smart beams with integrated piezoelectric actuators and sensors are considered. For the case of a spatial variation of the sensor/actuator activity, actuator and sensor equations are derived taking into account the interaction of mechanical, electrical and thermal fields. Self-sensing actuators are included. With respect to the non-uniform spatial distribution of the sensors/actuators, shaping problems are formulated. Possible non-uniqueness of these inverse problems is pointed out. Shape functions responsible for non-uniqueness of the shaping problems are termed nilpotent solutions. Within the context of simplified sensor/actuator equations widely used in the literature, a class of nilpotent shape functions is derived for redundant beams by analogy to an auxiliary quasi-static problem of thermally induced flexure. Nilpotent shape functions of the sensor/actuator shaping problem thus turn out to correspond to bending moments in the auxiliary thermoelastic problem.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"693 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":"122978162","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: 4
Dynamics for Large Deflections of a Sandwich Plate With Thin Piezoelectric Face Layers 薄压电夹层板大挠度的动力学研究
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0730
Y. Y. Yu
{"title":"Dynamics for Large Deflections of a Sandwich Plate With Thin Piezoelectric Face Layers","authors":"Y. Y. Yu","doi":"10.1115/imece1997-0730","DOIUrl":"https://doi.org/10.1115/imece1997-0730","url":null,"abstract":"\u0000 The frequency range for structural dynamics and vibration is first discussed. Nonlinear dynamics for large deflections of a sandwich plate is then reviewed. Finally, large deflections of a sandwich plate with two thin piezoelectric PVDF face layers are treated, and governing equations of motion are derived.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"32 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":"116585613","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
Design Criteria for Sandwich Panels for Building Construction 建筑夹层板设计标准
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0729
J. M. Davies
{"title":"Design Criteria for Sandwich Panels for Building Construction","authors":"J. M. Davies","doi":"10.1115/imece1997-0729","DOIUrl":"https://doi.org/10.1115/imece1997-0729","url":null,"abstract":"\u0000 Sandwich cladding panels comprising two metal skins and a lightweight insulating core are finding ever-increasing use as the wall and roof cladding for a wide range of building types. Their main attraction is their outstanding thermal performance but the designers and specifiers of such panels, and competing cladding systems, have to consider a wide range of other parameters in order to arrive at the best solution for their design requirements. This paper gives an overview the current scene, with particular reference to Europe, and makes specific comments on some of the current issues. Naturally, the structural design is discussed but particular attention is also paid to some of the other issues such as fire performance and durability which are less well documented.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"43 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":"132267326","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
On the Optimization of Composite Cylindrical Sandwich Shells Subjected to Beam Type Bending 梁式弯曲复合材料圆柱夹层壳的优化研究
Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0738
J. Vinson
{"title":"On the Optimization of Composite Cylindrical Sandwich Shells Subjected to Beam Type Bending","authors":"J. Vinson","doi":"10.1115/imece1997-0738","DOIUrl":"https://doi.org/10.1115/imece1997-0738","url":null,"abstract":"\u0000 Sandwich construction offers several advantages over monocoque and various discretely stiffened structures. These include greater load carrying ability, reduced weight, higher buckling loads and higher fundamental natural frequencies. The equations for the analysis and design of sandwich cylindrical shells subjected to beam type bending are presented herein. These equations are then manipulated to provide the face thickness, core depth, and core shear modulus to produce a minimum weight structure for a given load index and face material system. A factor of merit to select the best face material is also presented. As examples, Carbon/epoxy and E-glass/epoxy cross-ply composite faced sandwich shells are compared, as well as comparison with a monocoque cross-ply laminated shell.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"18 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":"132683276","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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