曲线公路隧道交通风力非稳态模拟研究

为分析小半径曲线隧道对交通风力的影响,采用移动网格和滑移交界面技术对半径600 m的曲线隧道和直线隧道进行三维非稳态数值计算.结果表明,采用动网格技术进行直线隧道交通风力计算结果与实验吻合;曲线隧道中,隧道断面风速分布表现出极不对称性,外侧风速较大,内侧较小;曲线隧道交通风力较直线隧道明显增大,汽车内车道行驶交通风力大于外车道行驶;曲线隧道中,汽车头部侧面出现了负压峰值,与直线隧道相比,该值较低,车身侧面压力沿纵向逐渐增大,汽车尾部背风面存在较低的负压区.     

磁性隧道结自旋极化电子的隧穿特性

铁磁金属间通过中间层的自旋极化电子隧穿产生的磁性耦合,在自旋电子器件中有许多潜在的应用.考虑由一平面磁性势垒层隔开的两铁磁性金属电极构成的磁性隧道结,针对中间层形成的矩形势垒,在近自由电子模型的基础上,计算零偏压下的隧穿电导、自旋极化率和隧穿磁阻比率,分析势垒层特性、分子场强弱、分子场相对取向等对隧道结自旋极化电子隧穿特性的影响.计算结果对自旋电子器件的设计具有一定的指导意义.     

基于风洞的设备健康管理与数据有效性判定平台研究

低速增压风洞是满足我国航空工业科技发展而建设的一座气动力重大基础试验设施。为了保障该设施的高效率和可靠地运行,以各机电设备、电气测控设备、机械装置为对象,根据其故障模式和故障特点选取合适的监测点,获取实时工作状态数据,再以数据为基础,进行状态监测、故障诊断、故障预测,实现预先性决策和针对性快速维修。基于OSA-CBM 体系构建的风洞健康管理系统,根据设备的运行状态,实现对试验数据的有效性进行实时判定,并实现了风洞装备由事后维修向视情维修转变;实现了装备从使用、维护、管理模式由分散式管理向集约式管理的转变;实现了装备系统故障诊、预测及判读从人工智能向机器智能的转变。     

Additivity of tunnel number for small knots

We show that for small knots , and that for small knots . Received: March 10, 1997.     

Mathematical analogy of a beam on elastic supports as a beam on elastic foundation

This paper presents the mathematical hypothesis that a beam on equidistant elastic supports (BOES) can be considered as a beam on an elastic foundation (BOEF) in static and free vibration problems. This modeling of BOES as BOEF is presumed to be applicable to a limited range of support stiffness, spacing and flexural rigidity of the beam. The authors investigate the applicability of the modeling of BOEF from the property of characteristic solutions obtained from governing equations of both BOES and BOEF. In this study, the formulation of BOES leads to governing difference equations, and the motions of BOEF are expressed by differential equations. This is because exact solutions must be employed in order to verify their analogy accurately. The characteristic solutions obtained from these two governing equations are compared to each other in order to investigate the relationship between them.     

温度改变对钛氧化物忆阻器导电特性的影响

相同测试条件下,纳米钛氧化物忆阻器的导电过程存在不稳定性,制约了对器件瞬态阻抗的精确读取与控制,并影响了器件应用于电路设计的可靠性与稳定性.杂质漂移与隧道势垒的共存是导致上述不稳定性的可能因素,且杂质漂移特性与环境温度密切相关.然而,目前尚无通过控制温度提高忆阻器导电稳定性的具体研究.基于杂质漂移与隧道势垒共存,本文分析了温度与忆阻器导电特性的关联,研究了器件活跃区域厚度及初始掺杂层厚度的改变对临界温度的影响,利用SPICE软件进行了仿真验证并给出结果,得出提高忆阻器导电稳定性的方法有:增大活跃区域厚度、降低初始杂质浓度及保持环境温度稳定且低于临界温度,从而为制备性能稳定的忆阻器及推动器件在实际电路中的应用提供依据.     

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.     

近距侧爆情况下马蹄形隧道动态响应特点的研究

在数值模拟和动光弹试验研究的基础上 ,对马蹄形隧道在邻近爆破作用下的动态响应特点进行了分析 ,并在综合考虑入射应力波波长、隧道直径、爆源与隧道的相对距离的基础上 ,提出了隧道迎爆一侧的动应力集中因子的近似确定方法 ,为今后邻近隧道的爆破施工安全提供了有益的参考。     

FD-21风洞Ma=10高超声速推进试验技术探索

针对Mach数8以上（Ma>8）冲压发动机地面试验能力不足问题,基于FD-21高能脉冲风洞,开展了吸气式推进试验技术探索,提升了FD-21风洞的重活塞驱动能力,获得了总压18.66 MPa、总温3 950 K、Ma=9.62、静压436.6 Pa、速度3 km/s的高焓大动压模拟流场,同时发展了高时间分辨率吸收光谱测量技术和基于重模型自由飞原理的发动机推阻测量方法.在此基础上,设计了弯曲激波压缩二元发动机,构建了燃料在线供应与喷注控制、模型悬挂与瞬态释放及相关测量一体的试验系统,在所建立的Ma=9.62风洞模拟环境中进行了集成验证试验,定量测得了有/无氢气射流与空气/氮气超声速气流作用下二元发动机的壁面压力、吸收光谱峰值吸收率、轴向力等数据,并利用纹影观测到了进气道唇口与燃烧室部位的波系特征.多次试验所得的壁面压力、峰值吸收率、轴向力随时间变化曲线均存在2 ms以上的平台,表明二元发动机建立了准定常流动.冷热态及氮气对照组对应的壁面压力分布、峰值吸收率、轴向力等数据呈现出了明显不同,且二者规律近似一致,一方面说明所建立的模拟流场、燃烧诊断技术、发动机推阻测量技术是有效的,另一方面也表明二元发动机实现了点火燃烧、获得有效热功转换,为后续相关研究奠定了良好的基础.      

Limit Cycle Oscillations of a Wing Section with a Tip Mass

This paper presents an investigation into the limit cycleoscillation phenomenon for a nonlinear aeroelasticsystem under unsteady aerodynamics. The system consists of a sweptbackwing section carrying a tip mass with one degree of freedom. Thejunction stiffness considered between the wing and the tip mass istrilinear. The method of harmonic balance, which can be very practicalin the study of nonlinear flutter, is used for the theoretical analysisof limit cycle oscillations. Stable, unstable and semi-stable limitcycles are predicted in the system for both cases of hardening andsoftening springs. Results found by numerical simulation provide theamplitudes of limit cycles. The experimental results in wind tunneltests agree well with the predictions obtained both theoretically andnumerically.