缩比模型轮胎转速对整车风阻影响分析

在缩比模型风洞试验中,若车轮转速设置与气体来流相同,会使轮胎旋转角速度倍增,导致缩比模型设计难度增大,同时试验中的不稳定因素也会增加,因此需要对缩比模型风洞试验中轮胎转速对风阻的影响进行分析,以探究轮胎降转速试验的可行性。本文基于某MPV车型,通过风洞试验及计算流体动力学（CFD）仿真方法对轮胎转速对整车风阻的影响进行分析,结果表明：轮胎转速对风阻测试结果有影响;缩比模型车轮速度设定与来流相同时,缩比模型与全尺寸风阻结果更一致。     

下击暴流作用下的开洞超高层建筑风致内压及净压

通过自制发生装置在大气边界层风洞中模拟下击暴流风场,对典型开洞高层建筑进行内外压风洞试验,研究下击暴流和B类风场作用下开洞高层建筑的内压、净压特性和内压增益函数,进一步识别孔口特征参数,并将内压极值的理论计算结果与试验结果进行对比分析。结果表明,随风向角的增大,内压系数平均值和极值均先减小后增大。两侧面的净压极值最大,易发生风致破坏。开洞面由于内外压相关系数为正值,内外压作用相互抵消,其净压最小。在50°斜风向的来流作用下,内压增益幅值远大于其他风向角下的结果,且在Helmholtz共振频率处的内压能量显著增大。除70°～100°风向角外,其他风向角下内压系数极值的理论值与试验值吻合良好。     

Hydrogenated silicene based magnetic junction with improved tunneling magnetoresistance and spin-filtering efficiency

In this paper, hydrogenation is used for the generation of band gap in silicene and the hydrogenated silicene is then studied for its spintronic application. Upon hydrogenation, silicene transforms into a wide band gap material with a band gap of 3.32 eV. Parameters like magneto-resistance and spin-filtering efficiency of magnetic tunnel junction (MTJ) with CrO₂ as semi-metallic electrodes and hydrogenated silicene as scattering region are found to increase compared to pristine silicene as scattering region. The simulation results show that the magneto-resistance of hydrogenated silicene remains above 85% (higher than the pristine counterpart) for the entire bias range. In addition, the spin-filtering efficiency in hydrogenated silicene reaches a value as high as 96% whereas in case of pristine silicene it remains below 90% for the entire bias range.     

Solid state reactions of nitrogenous heterocyclic compounds (II)

Solid state Michael addition reaction of indole with α, β-unsaturated carbonyl compounds was carried out, by which a series of compounds containing three different heterocyclic groups binding to one carbon atom were ob-tained. In the presence of Lewis acid, indole could undergo the solid state condensation reaction with aromatic ketones and aldehydes or quinones. The solid state reaction showed higher selectivity and yield than solution reaction. The structures of products were identified by IR,¹H NMR, MS. elemental analysis and X-ray crystal analysis. The reac-tion mechanism was also proposed. Project supported by the National Natural Science Foundation of China     

高超声速飞行器气动热关联换算方法研究

气动热风洞实验是地面研究和预测飞行器气动热环境的重要手段之一, 但由于风洞实验模拟能力的限制, 风洞实验的流场参数和模型的几何尺度都会与实际飞行情况存在一定的差别, 导致地面风洞实验中得到的模型表面气动加热率数据无法直接用于飞行条件下的热环境预测和热防护设计. 以往通过针对具体飞行器的试验结果进行数据拟合后外插的气动热关联换算方法指向性较强, 没有考虑到气动热的具体影响参数, 存在一定局限性, 难以外推应用于其他外形的飞行器. 为解决通过气动热风洞实验数据外推预测飞行条件下气动热的技术难题, 基于无量纲NS方程和边界层理论分析研究了影响气动热的主要参数, 并通过推导化简边界层近似解热流公式, 针对层流流态建立了气动热关联换算方法, 可以考虑当地边界层外缘参数的影响, 具有一定通用性. 在此基础上, 利用建立的方法将Reentry-F飞行器缩比模型的风洞实验数据换算到该飞行器飞行条件下的典型工况, 并与飞行测量结果进行了比较, 外推预测结果与飞行测量结果符合较好, 表明建立的关联方法可以用于气动热风洞实验数据的外推换算.      

流变岩体中让压支护作用下隧道力学行为研究

高地应力深埋软岩隧道大变形问题已成为隧道工程建设领域的突出难题. 根据高地应力深埋软岩隧道的变形特征, 基于"围岩能量吸收、变形释放"的让压支护是解决软岩隧道大变形问题的有效方法. 针对流变岩体中深埋圆形隧道在让压支护作用下的力学响应问题, 通过引入分数阶微积分理论, 采用Abel黏壶元件建立了改进的分数阶Burgers蠕变模型来表征围岩的时效变形. 此外, 通过在让压支护不同变形阶段引入刚度修正系数, 克服了传统支护未能考虑围岩变形释放的问题. 据此, 本文推导了在考虑支护延迟安装影响下, 不同变形阶段围岩与让压支护相互作用的解析解. 为了验证理论研究的正确性, 对一算例进行了不同解答及工程结果的比对, 吻合较好. 最后, 参数研究结果表明: 围岩与让压支护间的相互作用受蠕变本构模型分数阶阶数影响较大. 隧道的位移或支护压力与让压位移、支护刚度修正系数间存在线性比例关系, 但由于刚度修正系数仅保持在较小的变化范围内, 隧道的位移或支护压力变化并不显著.      

杭州大剧院风压分布的风洞试验研究

杭州大剧院外观造型新颖独特，由一个近似为椭球的双曲面屋盖和一个倒置的圆锥面玻璃幕墙相交形成大剧院的主体建筑的外轮廓．本文结合该主体结构的抗风设计要求，制作了1：200刚性模型进行结构表面脉动风压平均风压分布的风洞试验研究，详细介绍了风洞试验及数据处理方法，讨论了在不同风向角下椭球面屋盖和圆锥面玻璃幕墙的风压分布．为了便于整体结构设计，本文根据结构的实际情况对椭球面和圆锥面进行分块并给出相应的分块风压数据，最后根据各风向角下的风压分布特征给出了整体结构抗风设计的最不利风向角．     

用反向渐进结构优化方法研究洞室支护优化

洞室开挖支护的优化是在铁路隧道、矿山开挖、水电站建设中经常面对的课题,特别是研究洞室开挖支护拓扑优化有着重要的意义。本文利用近年来发展的渐进优化方法(ESO)的概念,提出了反向ESO方法的迭代格式,建立了洞室开挖支护优化的准则及其敏感度,研究了均匀地基不同地应力条件使得开挖卸荷产生的总应变能最小的最优支护拓扑。结果证明了反向ESO方法的适用性,最优支护拓扑大致成椭圆或者圆形,其主轴方向与最大主应力主轴方向相同。     

恒流应力下E2PROM隧道氧化层的退化特性研究

在电容测量的基础上研究了薄隧道氧化层在恒定Fowler-Nordheim(F-N)隧穿电流下的退化情况. 这种退化是恒流应力和时间的函数，对恒流应力大小的依赖性更加强烈，隧道氧化层在F-N电流下的退化是注入电荷密度(Q_inj)的函数. 在较低Q_inj下氧化层中发生正电荷俘获，在较高Q_inj下发生负电荷俘获，导致栅压变化的反复. 关键词： 2PROM')" href="#">E²PROM 隧道氧化层 退化 恒流应力     

The stability analysis of rolling motion of hypersonic vehicles and its validations

The stability of the rolling motion of near space hypersonic vehicles with rudder control is studied using method of qualitative analysis of nonlinear differential equations, and the stability criteria of the deflected rolling motions are improved. The outcomes can serve as the basis for further study regarding the influence of pitching and lateral motion on the stability of rolling motion. To validate the theoretical results, numerical simulations were done for the rolling motion of two hypersonic vehicles with typical configurations. Also, wind tunnel experiments for four aircraft models with typical configurations have been done. The results show that: 1) there exist two dynamic patterns of the rolling motion under statically stable condition. The first one is point attractor, for which the motion of aircraft returns to the original state. The second is periodic attractor, for which the aircraft rolls periodically. 2) Under statically unstable condition, there exist three dynamic patterns of rolling motion, namely, the point attractor, periodic attractor around deflected state of rolling motion, and double periodic attractors or chaotic attractors.