刚结式消力池侧墙、翼墙受力与配筋计算分析

对消力池侧墙、翼墙断裂倾斜破坏进行了综合性力学分析，提出了合理的配筋计算，为今后水工设计提供科学理论依据。     

多层墙梁试验研究

墙梁结构用于多层房屋中,托梁需承托若干层楼层传来的荷载,一般荷载较大,而托梁上的墙体一般都与纵横墙体连结,是一空间受力体系;承受较大荷载的墙梁,将通过与它联结的墙体把部分荷载传递开去,因此计算墙梁时,需考虑与墙梁连结的部分墙体(称翼墙)的作用,为了解翼墙的作用,它对墙梁抗弯、抗剪、局压的影响,我们对带翼墙的多层墙梁进行了有限元分析计算,对影响诸因素作了分析,并进行了两个带翼墙的两层墙梁试验,对多层墙梁的受力与破坏特征有了进一步的了解,为考虑翼墙影响提供了依据。     

后置混凝土翼墙加固框架角柱抗震性能试验

为考察后置混凝土翼墙加固框架角柱的抗震性能,设计制作了6个在相邻两侧面后置混凝土翼墙的试件.这6个在役框架角柱加固前试验轴压比分为0.31、0.36、0.40三档,纵筋采用HRB400钢筋,纵筋配筋率分为1.23%、1.05%、0.82%三档;箍筋采用HPB300钢筋,箍筋配箍率为0.6%.对这6个试件进行低周反复荷载试验,发现加固后的试件平行于受力方向翼墙在远离角柱一侧损伤严重,而角柱和垂直于受力方向翼墙损伤较轻,达到了加固后原柱同时承受竖向荷载和水平地震作用,翼墙以抵御水平地震作用为主并作为耗能元件有效耗能的目的.     

燕山水库溢洪道闸上游翼墙体型优化试验研究

燕山水库溢洪道工程为对称布置.针对原布置溢洪道闸上游左岸翼墙附近存在的旋滚水流等不良流态,采用按重力相似准则设计的水工正态物理模型进行试验研究,通过对5种不同体型翼墙的流态、流速、流量等水力参数的综合比较,进行体型优化,消除了圆弧段与直墙段连接部位附近的不良流态,达到了闸上游水面平稳、流速分布均匀、翼墙附近水体平顺的目的.同时优选出墙后回填土的适宜范围.     

钢筋混凝土扭曲面翼墙在黄河下游引黄闸改建工程中的应用

为了将钢筋混凝土扭曲面翼墙引入黄河下游引黄闸改建工程中,以山东黄河打渔张引黄闸工程为例,探讨了钢筋混凝土扭曲面的设计、施工工艺流程和关键施工技术。     

600MW机组配风改造降低锅炉NO_x生成及结焦的原因分析

针对某电厂2×600 MW机组锅炉存在的SCR进口NOx浓度高、翼墙结焦严重的问题,提出配风改造方案,在翼墙增加配风口,改造后的SCR进口NOx浓度下降明显,翼墙结焦得到缓解。     

高强混凝土剪力墙屈服位移计算方法

考虑高强混凝土受压强度高等特点,在高强混凝土剪力墙截面刚达到屈服状态时,假定截面受压区混凝土压应力为线性分布,基于平截面假定,用弯矩曲率分析法得到了剪力墙截面屈服曲率公式。采用屈服曲率公式,对影响高强混凝土剪力墙屈服曲率的参数进行了分析。结果表明,除轴压比外,纵向受力钢筋屈服应变对屈服曲率影响最大;在轴压比较大时,剪力墙截面两端翼墙的影响也较大。通过对计算结果的回归分析,提出了考虑轴压比、纵向受力钢筋屈服应变和剪力墙截面两端翼墙面积影响的屈服曲率计算公式。提出了高强混凝土剪力墙顶点屈服位移的计算公式,公式的计算值与12个高强混凝土高悬臂墙顶点屈服位移的试验值比较吻合。简化公式也适用于普通混凝土剪力墙的屈服位移计算。     

短肢剪力墙低周反复试验研究

通过低周反复荷载试验揭示了短肢墙从弹性应力状态到砼开裂、钢筋屈服、直至结构破坏的全过程.试体分为两组,无翼墙与有翼墙各一组,结果表明:当无翼墙试体墙肢较短时,墙肢底部纵筋首先屈服;墙肢较长时,连梁箍筋首先屈服.有翼墙试体无论肢厚比大小,均在墙肢和翼墙底部纵筋处首先屈服.从强度和耗能能力来看,肢厚比在6.5左右时,结构的综合性能较好.     

最小二乘法在水力计算数表中的应用

运用曲线拟合的最小二乘法，构造直角式翼墙进口无坎宽顶堰流量系数经验公式。经误差分析表明此方法可靠，高效。     

关于实用钢卷剪切装置的设计

介绍设计了一套实用钢卷剪切装置的各主要机构及其有关参数，该装置剪切钢卷最大宽度B=600mm，厚度为0．5～2mm，剪切速度≤0．5m／s．设计主要依据诺沙利计算法，计算了剪切力，圆盘刀剪所需扭矩及功率，同时计算了各传动系统的传动比。     

Shock control bump optimization for a low sweep supercritical wing

Shock control bumps are a promising technique in reducing wave drag of civil transport aircraft flying at transonic speeds.This paper investigates the optimization of 3D shock control bumps on a supercritical wing with a sweep angle of 16°at the1/4 chord.A similar supercritical wing with a higher sweep angle of 24.5°at the 1/4 chord has been adopted as a baseline for the study.Numerical results show that the drag coefficient of the low sweep wing with the optimized 3D shock control bumps is reduced below that for the high sweep wing,indicating shock control bumps can be used as an effective means to reduce the wave drag caused by reducing the wing sweep angle.From the point of view of the wing structure design,lower sweep angle will also bring the benefits of weight reduction,resulting in further fuel reduction.     

蜻蜓翅膀微观结构及其润湿性

利用视频光学接触角测量仪对6种蜻蜓翅膀表面的接触角进行了测量,发现蜻蜓翅膀具有疏水性能,接触角在135.14°~149.85°之间,其值与测量部位无关,与蜻蜓种类有关。用扫描电子显微镜对蜻蜓翅膀表面微观结构进行观测,发现蜻蜓翅膀上布满柱状纳米级结构形态,柱直径分布范围为66.90~200.73 nm,柱间距为20.00~650.00 nm,翅膜厚度为1.58~4.08μm。分析了蜻蜓翅膀表面疏水机理,研究表明:蜻蜓翅膀的疏水机理满足Cassie模型,其疏水性能主要由体表纳米级别的柱状结构与体表成分共同作用的结果。蜻蜓翅膀润湿性能的研究为微型飞行器及自清洁材料的制备提供了理论依据。     

Comparison of two design methods of aerodynamic biobjectives for airfoil and wing shapes

It is well known that a modern fighter should have high aerodynamic performance, i.e. high CL/CD at subsonic speed and low drag at supersonic speed at the meantime. To realize low cruise drag at supersonic flight the wing plane should not be cambered, while to get high aerodynamic efficiency at subsonic/transonic flight, it should be cambered. A naturally way to solve this conflict is to make the fighter have an 揳daptive wing? i.e. to change the wing shape automatically to satisfy the requir…     

Experimental Study of Effects of Tail Wings on Submunition Aerodynamic Characteristics

Aimed at the needs of deceleration of submunitions dispensed from the ballistic missile, wind tunnel tests were performed on the submunitions with different tail wing sizes at the Mach number range from 0.7 to 3.0 and the angle of attack range from 0° to 14°. Experimental data about the variance of aerodynamic coefficients with the Mach number and angle of attack were obtained systemically. The effects of the tail wing sizes on the drag coefficients and the center of pressure coefficients were discussed. Analyzed results show the arc tail wings designed are beneficial to both the deceleration effect and static stability. These results are significant to the tail wing design and its applications to the submunitions deceleration..     

隐身反设计下飞翼布局气动与隐身综合设计

为同时获得良好的气动和隐身性能,基于双发动机布局下飞翼无人机大鼓包式机身,采用隐身反设计思路,开展了飞翼布局气动与隐身综合设计与分析研究,提出了一种减小翼型前缘半径的机身前缘类"鹰嘴"形飞翼布局优化构型.分别采用CFD(计算流体力学)方法对M6机翼进行气动数值模拟方法验证,以及基于FEKO软件中MLFMM(多层快速多极子方法)和PO(物理光学法)对圆柱体和某飞翼布局缩比模型进行隐身数值计算方法验证,并利用该方法获得了飞翼布局无人机气动与隐身综合特性.结果表明:建立的气动与隐身数值模拟方法计算结果与实验吻合较好,数值计算方法是可靠的;基于隐身反设计思路构建的机身前缘类"鹰嘴"形飞翼布局设计不仅纵向气动特性略微提升,且前向(-25°~25°)隐身性能明显提高,充分表明了隐身反设计思路的有效性;前缘类"鹰嘴"形设计主要影响机身表面压力分布,并有助于提升升阻特性;前缘类"鹰嘴"形设计比传统钝形前缘设计在不同频率和不同滚转角下隐身特性均有所提高.     

飞机总体设计阶段机翼结构质量分配方法研究

提出了一种机翼结构质量分配方法,能根据飞机总体设计参数,把机翼结构质量分配到承弯结构、承剪结构、分布气动载荷所需结构、起落架安装影响结构等12个功能结构部分。建立了飞机总体设计阶段机翼结构质量分配的分析模型,然后根据现有飞机机翼的质量和飞机总体几何参数,用参数优化方法确定了该分析模型中的结构修正系数,从而得到一个机翼结构质量分配模型,用8架飞机的机民办所完成的算例证明了该方法的有效性和合理性。     

Wing load investigation of the plunge-diving locomotion of a gannet Morus inspired submersible aircraft

In this paper,we studied the wing root pivot joint’s radial load of a submersible airplane which imitates the locomotion of gannet’s Morus plunge-diving,by implementing a test device name Mimic-Gannet.The housing of the device was designed by mimicking the morphology of a living gannet,and the folding wings were realized by the mechanism of variable swept back wing.Then,the radial loads of the wing root were obtained under the conditions of different dropping heights,different sweptback angles and different water-entry inclination angles(i.e.,the angle between the longitudinal body axis and the water surface),and the relationships between the peak radial load and the above three parameters were analyzed and discussed respectively.In the studied areas,the minimum peak radial load of the pivot joint is 50.93 N,while the maximum reaches up to1135.00 N.The largest peak load would be generated for the situation of vertical water entry and zero wing sweptback angle.And it is of great significance to choose the three parameters properly to reduce the pivot joint’s radial load,i.e.,larger wing sweptback angle,smaller dropping height and water-entry inclination angle.It is also concluded that the peak radial load on the wing root is closely linear with the water-entry dropping height and the wing sweptback angle with a significant correlation.Eventually,the relationship between the wing load and the dropping height,water-entry inclination angle or wing sweptback angle,could be used to calculate the wing load about plunge-diving of a submersible aircraft,and the conclusions reveal the wing load characteristic of the gannet’s plunge process for the biologists.     

阻力方向舵在飞翼式高空长航时无人机中的应用

根据飞翼式高空长航时无人机的风洞实验结果,分析了全机尤其是阻力方向舵的气动和操稳特性,据此采用经典方法设计了阻力方向舵的控制律,提出用阻力方向舵进行航向控制和速度控制的方案,并指出由于存在操纵耦合,有必要进行阻力方向舵和升降舵交联控制。非线性飞行仿真结果表明,阻力方向舵具有满意的航向和速度操纵能力,采用交联控制后速度响应更平稳,并可减小33的高度偏差和56的俯仰角偏差。