陶瓷材料动态压缩损伤本构模型

运用细观损伤力学理论,从动态压缩载荷下陶瓷材料内翼型裂纹的产生和扩展的损伤机理出发,建立了陶瓷材料的弹脆性动态损伤本构模型,给出相应的损伤演化方程.假设裂纹成核满足Weibull分布,讨论了成核分布参数、原始缺陷尺寸对材料动态断裂应力、断裂应变的影响,并用动态损伤演化模型计算了冲击载荷下AD90陶瓷的动态应力应变曲线,计算结果和实验结果符合很好.     

Optical properties of Ag@cicada wing substrate deposited by Ag nanoparticles

In this paper, Ag nanoparticles were deposited on Ag@cicada wing array by using the cicada wings as templates to study its optical properties, including surface enhanced Raman scattering (SERS), polarization and surface enhanced fluorescence (SEF). The nanogaps between adjacent conical protrusion can be well dominated by adjusting the sputtering time and the optimal substrate AgNPs@Ag@cicada wing arrays have a noteworthy enhancement of SERS signal. Characterization of the prepared optimal substrate certified that it possesses the excellent SERS performances. Basically consistent SERS signal strength at the different polarization angles of the optimal substrate indicates that its polarization-independence. The SEF spectra shows that the optimal substrate has a slightly lower and unstable enhancement at this initial stage of repeated examination due to the weak adhesion between the Ag@cicada wing arrays and Ag nanoparticles. The outstanding optical properties indicate that it has enormous potential in the label-free detection and biological analytes determination.     

The effects of vortex breakdown on the static rolling aerodynamics of finned slender body

The static rolling aerodynamics of a finned slender body is numerically studied in this paper.Simulation results show a nonlinear uprising of the rolling moment when the angle of attack is greater than 20°in subsonic flows.Asymmetric vortex break down phenomenon on the"horizontal"rudders is found to be responsible for this phenomenon.By introducing the geometric-equivalent angle of attack and geometric-equivalent sweep angle,the cause of the nonlinear rolling moment characteristics can be explained by the delta wing vortex breakdown analysis.     

Vortex control by the spanwise suction flow on the upper surface of delta wing

The numerical investigation has been performed to explore the feasibility of vortex control by leading edge sucking excitation on a delta wing. The results reveal that the flow on the upper surface of the delta wing changes significantly in a wide range of the angle of attack. For the vortical flow at moderate angle of attack, the secondary and tertiary vortices are weakened or suppressed, and the total lift is almost unchanged. For the stalled flow at high angle of attack, the leading edge concentrated vortex is recovered, and the lift is enhanced with increasing suction rate. For the bluff-body flow at even high angles of attack, the lift can still be improved. The concentrated vortex disappears on the upper surface, and the load increment is nearly unchanged along the chordwise direction. The project supported by the National Natural Science Foundation of China (19802018).     

Effects of unsteady deformation of flapping wing on its aerodynamic forces

Effects of unsteady deformation of a flapping model insect wing on its aerodynamic force production are studied by solving the Navier-Stokes equations on a dynamically deforming grid.Aerodynamic forces on the flapping wing are not much affected by considerable twist,but affected by camber deformation.The effect of combined camber and twist deformation is similar to that of camber deformation.With a deformation of 6% camber and 20°twist(typical values observed for wings of many insects),lift is increased bv 10%～20%and lift-to-drag ratio by around 10%compared with the case of a rigid flat-plate wing.As a result.the deformation can increase the maximum lift coefficient of an insect.and reduce its power requirement for flight.For example,for a hovering bumblebee with dynamically deforming wings(6?mber and 20°twist),aerodynamic power required is reduced by about 16%compared with the case of rigid wings.     

基于三路舵机驱动的扑翼飞行模型气动特性研究

扑动而形成非定常气动现象是扑翼飞行过程中产生高升力的主要原因。本文以Ellington实验的鹰蛾翅膀为原形,设计扑翼实验及数值计算模型。通过压差传感器对翅膀模型上翼面固定位置进行测压,分析前缘涡的产生及脱落情况(考虑动压效应)。测量上下翼面固定位置处的压差,揭示扑翼飞行中产生高升力的主要原因。利用烟风洞观察扑翼模型周围流场结构及特殊涡产生变化情况。另外,根据Ellington提供的升力关系式估算了扑翼模型在一个周期内的平均升力。最后,基于三维欧拉方程对扑翼飞行气动特性进行数值模拟,计算结果与实验吻合良好。     

扑翼柔性及其对气动特性的影响

以往对扑翼气动特性的研究基本上都是基于简单的匀速刚性模型,但是通过大量观察不同飞鸟的扑翼动作发现,该模型与鸟翼的实际扑动还有很大差别。鸟翼不但上扑段和下扑段所需时间不同,而且在扑动过程中,鸟翼的形状无论沿弦向或展向都存在着相当大的柔性变形。本文在原有匀速刚性模型的基础上,加入了扑动速率变化和形状变化的影响,得出新的变速柔性扑翼分析模型,使之更接近鸟翼柔性扑动的真实情况。通过对比计算发现,柔性变形对扑翼的升力与推力都有着显著影响,如果控制得当,柔性变形能大大改善扑翼的气动性能。     

A theoretical investigation of the development of stationary crossflow vortices in the boundary layer on a swept wing

Crossflow instability plays very important role in the transition of the boundary layer on a swept wing, typical in the engineering applications. Experiments revealed that the linear stability theory well predicted the form of the crossflow vortices, but usually much overpredicted their growth rate. Using nonlinear theory of hydrodynamic stability, combined with some other considerations, we were able to obtain the growth rate in good agreement with experimental observations. The project supported by the National Natural Science Foundation of China, Grant No. 19572048     

翼面气动外形对栅格翼减阻的影响

从节约空间的角度考虑,带一定弧度的翼面有利于栅格翼在弹体上的安装.通过风洞实验研究了两种不同安装方式的弧形翼面栅格翼的气动特性,并和翼面无弧度的栅格翼进行比较.结果显示,弧形翼面的栅格翼阻力系数均小于翼面无弧度的栅格翼,升阻比除跨音速阶段外比后者表现更好,同时对一种前缘后掠的栅格翼模型进行了数值计算,比较研究结果显示,对栅格翼的迎风面栅格进行一定角度的后掠能有效减小超音速阶段的波阻,是一种栅格翼减阻设计的新思路.