Analysis and Design Issues for Modern Aerospace Vehicles最新文献

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

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

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

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

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

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

引用次数: 0

Forced Response Prediction of Gas Turbine Rotor Blades 燃气轮机转子叶片强迫响应预测

Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0750

Gary Hilbert, R. Ni, Ronald K. Takahashi

{"title":"Forced Response Prediction of Gas Turbine Rotor Blades","authors":"Gary Hilbert, R. Ni, Ronald K. Takahashi","doi":"10.1115/imece1997-0750","DOIUrl":"https://doi.org/10.1115/imece1997-0750","url":null,"abstract":"\u0000 An analytical forced response prediction system is used to predict turbomachinery airfoil vibratory stress amplitudes. The forced airfoil vibration can be caused by time dependent (unsteady) aerodynamic loads due to interaction with the flow field from neighboring airfoils rows, such as shocks, wakes, or pressure waves, or due to self induced unsteady aerodynamics such as vortex shedding and unsteady tip vortices. The amplitude of the forced response is of particular interest when the frequency of the time dependent unsteadiness is close to the natural frequency of the forced airfoil. At this condition, the airfoil is at or near resonance and vibratory stress can exceed the material capability causing high cycle fatigue (HCF) failures.\u0000 The airfoil forced response prediction system presented here combines structural static and dynamic analysis with steady and unsteady computational fluid dynamic analysis in an iterative coupled solution to the aeroelastic problem. The system includes three dimensional viscous multistage steady and unsteady computational fluid dynamics and three dimensional geometric nonlinear structural static, linear free vibration and modal forced response analysis to predict the airfoil amplitude in the resonance modes during engine operation.\u0000 This analysis system is being used to help identify the cause of HCF failure and determine corrective action. The analysis system is demonstrated using a compressor rotor excited by upstream and downstream vanes. Results are then compared with engine test data.","PeriodicalId":403237,"journal":{"name":"Analysis and Design Issues for Modern Aerospace Vehicles","volume":"8 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":"116767576","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: 7

Strain Rate Compression Performance for a Linear Core Sandwich Beam, I 线性芯芯夹层梁的应变率压缩性能[j]

Analysis and Design Issues for Modern Aerospace Vehicles Pub Date : 1997-11-16 DOI: 10.1115/imece1997-0735

D. Weissman-Berman

引用次数: 0