Effect of drag reducing riblet surface on coherent structure in turbulent boundary layer

The characteristics of turbulent boundary layer over streamwise aligned drag reducing riblet surface under zero-pressure gradient are investigated using particle image velocimetry. The formation and distribution of large-scale coherent structures and their effect on momentum partition are analyzed using two-point correlation and probability density function. Compared with smooth surface, the streamwise riblets reduce the friction velocity and Reynolds stress in the turbulent boundary layer, indicating the drag reduction effect. Strong correlation has been found between the occurrence of hairpin vortices and the momentum distribution. The number and streamwise length scale of hairpin vortices decrease over streamwise riblet surface. The correlation between number of uniform momentum zones and Reynolds number remains the same as smooth surface.     

基于线性频散信号构建的复杂航空结构Lamb波高分辨率损伤成像

在对复杂航空结构的Lamb波损伤成像中,Lamb波频散容易使信号波包发生扩展和变形,从而降低信号的分辨率,并最终影响损伤监测结果,因此Lamb波频散补偿已成为急需解决的一个重要问题。目前常用的频散补偿方法需要理论计算Lamb波频散曲线,难以适用于复杂航空结构。本文利用现场直接测得的相对波数曲线进行线性频散信号构建(Linearly-dispersive signal construction,LDSC)的频散补偿处理,解决了航空复杂结构中Lamb波频散难以补偿的问题。然后,将LDSC用于延迟叠加损伤成像中,以实现高分辨率损伤成像。为了降低多反射的复杂航空结构形式对成像结果的影响,引入了1.5波峰正弦调制的准宽带Lamb波激励波形。最后通过在真实复杂的某型飞机大梁结构上的实验证明了所提方法的有效性。     

Residual stress determination in friction stir butt welded joints using a digital image correlation-aided slitting technique

This paper presents an incremental cutting method for evaluating the longitudinal residual stresses in a butt welded thin plate via combining the traditional residual stress measurement methods and the advanced optical technique.The proposed approach,which can be called digital image correlation (DIC)-aided slitting technique,introduces a successive extension slot to a speci men and employs the DIC technique to measure the released displacement profiles of the cutting sections after each cutting increment.Then the displacement profiles are used to directly calculate the residual stress distributions up to the slot tip and hence,a stress distribution can be obtained after a cutting increment.Finally,all of the stress distributions are averaged to ultimately determine the original residual stress field.This method does not include any complex experimental operations or tedious derivation,and the resolution of stress variation is greatly improved by the continuous measurement of the released displacements.The presented method has been preliminarily verified by a specimen with residual stress introduced by a four-point bending test.The results show that residual stresses determined by the DIC-aided slitting technique agree well with those from finite element (FE) prediction.The residual stress in a friction stir welded aluminum specimen obtained by the presented technique is also consistent with the evaluations given by X-ray diffraction.Fur thermore,the residual stresses obtained by the DIC-aided slitting technique demonstrate higher accuracy and stability than the evaluations derived by the DIC-aided contour method.     

基于Lorentz信息度量的分窗二值方法

光照不均是对数字图象进行二值化处理时需要解决的一个问题。在利用 Otsu自动阈值选择法进行分窗二值化的同时 ,给出一种基于 Lorentz信息度量的金字塔数据结构判别过程 ,有效地解决了分窗二值化方法 ,克服光照不均时 ,由于分窗大小而使得窗口内仅含背景 (或对象物 )以致影响二值化正确性这一问题。     

飞机结构部件飞行载荷估算方法研究

介绍一种考虑飞机各部件间相互影响（干扰）的气动载荷估算方法。把该方法用于估算全动平尾的飞行载荷,并用它估算了Ｆ－７全动平尾在对称机动情况下的飞行载荷,且与飞行实侧载荷作了比较。结果表明,估算和实测载荷相差１０％左右。这种估算方法,在飞机设计阶段,可用于估算飞机其它部件（机翼、垂尾等）飞行载荷。     

复合材料夹层结构的弯扭稳定性

对复合材料层合板做面板,蜂窝做夹芯的夹层结构在受到弯、扭载荷作用下的稳定性进行了研究。面板采用对称铺层、等高度蜂窝夹芯,利用能量法对临界载荷进行了计算并给出了一些计算曲线。     

应用信标模式测速的实现方法及论证

根据未来固体火箭型号试验越来越多,首区无线电设备受火箭尾焰干扰的情况以及测控体制的发展要求,探讨了利用信标模式[1]进行高精度测量时所面临的工程问题,包括信标模式下测量值的误差项分析,减小测量误差的方法等内容。     

智能结构的梁有限元模型

本文详细阐述了含压电传感器和执行器的智能结构梁单元模型的建立过程，并以双压电晶片悬臂梁为例，检验了所提模型的精度。     

空间结构展开与刚化

空间展开结构具有能构建大型结构、轻质而且成本低廉的特点。在航天器中呈折叠状的空间结构在空间充气展开后，要呈刚化，使其不因温度变化而引起变形并且不会因空间碎片或流星体的碰撞而被损坏。文中提出了展开前的折叠方法和包装效率评估方法。提出了两种刚化薄膜，在储存状态下易于折叠并能保持其所有的性能。一种采用单层薄膜浸渍长储存寿命树脂基的三轴编织纤维，另一种采用宽广温度范围长储存寿命的交互编织纤维刚性薄膜。     

翼面结构结点载荷转换分配方法的比较分析

在对飞机的翼面结构进行有限元分析时,如何将气动载荷有效地加载到有限元模型上至关重要。研究翼面结构中气动结点载荷向有限元结点载荷转换的三种分配方法:三点排、四点排、多点排,并使用这三种方法对翼面结构有限元模型进行分析计算。结果表明:三种方法均能满足总载荷相同、总压心相同,且满足载荷分配要求;多点排方法不仅能适用于极端条件下的载荷分配且算法实现简单、计算效率高、理论依据强,还能实现载荷加载点位置的自由选取,四点排、三点排依次次之。所得结论可为结构有限元计算的载荷前处理和拓扑优化中的载荷分配提供一定参考和借鉴。