Static aeroelastic analysis of very flexible wings based on non-planar vortex lattice method

A rapid and efficient method for static aeroelastic analysis of a flexible slender wing when considering the structural geometric nonlinearity has been developed in this paper. A non-planar vortex lattice method herein is used to compute the non-planar aerodynamics of flexible wings with large deformation. The finite element method is introduced for structural nonlinear statics analysis. The surface spline method is used for structure/aerodynamics coupling. The static aeroelastic characteristics of the wind tunnel model of a flexible wing are studied by the nonlinear method presented, and the nonlinear method is also evaluated by comparing the results with those obtained from two other methods and the wind tunnel test. The results indicate that the traditional linear method of static aeroelastic analysis is not applicable for cases with large deformation because it produces results that are not realistic. However, the nonlinear methodology, which involves combining the structure finite element method with the non-planar vortex lattice method, could be used to solve the aeroelastic deformation with considerable accuracy, which is in fair agreement with the test results. Moreover, the nonlinear finite element method could consider complex structures. The non-planar vortex lattice method has advantages in both the computational accuracy and efficiency. Consequently, the nonlinear method presented is suitable for the rapid and efficient analysis requirements of engineering practice. It could be used in the preliminary stage and also in the detailed stage of aircraft design.

Vortex solitons in the semi-infinite gap of optically induced periodic lattices

Vortex solitons with a ring vortex core residing in a single lattice site in the semi-infinite gap of square optical lattices are reported. These solitons are no longer bound states of the Bloch-wave unit （Bloch-wave distribution in one lattice site） at the band edge of the periodic lattice, and consequently they do not bifurcate from the corresponding band edge. For saturable nonlinearity, one family of such solitons is found, and its existing curve forms a closed loop, which is very surprising. For Kerr nonlinearity, two families of such vortex solitons are found.

Spontaneous Formation of Anti-ferromagnetic Vortex Lattice in a Fast Rotating BEC with Dipole Interactions

When a Bose-Einstein condensate is set to rotate, superfluid vortices will be formed, which finally condense into a vortex lattice as the rotation frequency further increases. We show that the dipole-dipole interactions renormalize the short-range interaction strength and result in a distinction between interactions of parallel-polarized atoms and interactions of antiparallel-polarized atoms. This effect may lead to a spontaneous breakdown of the rapidly rotating Bose condensate into a novel anti-ferromagnetic-like vortex lattice. The upward-polarized Bose condensate forms a vortex lattice, which is staggered against a downward-polarized vortex lattice. A phase diagram related to the coupling strength is obtained.

Alternating Current Response of Two—Dimensional Vortex Lattice with Random Pinning

Using a model of long-range interactions between vortices, we investigate numerically the alternating current (ac) response of two-dimensional vortex lattice with randomly distributed point-like pinning centers. Mode-locking steps are observed in the simulated current-voltages characteristics, and the number of steps increases with the superimposed ac amplitude and frequency. Our results are in good agreement with recent experiments.

A δ-function-like peak in the specific heat of two-dimensional vortex lattice： Monte carlo study

A repulsive vortex\|vortex interaction model was used to numerically study the melting transition of the two\|dimensional vortex system with Monte Carlo method. Then a δ\|function\|like peak in the specific heat was observed and the internal energy showed a sharp drop at the melting temperature, which indicated that there exists a first\|order melting transition at finite temperatures. The Lindemann criterion was also investigated and valid, but different from previous simulation results.

二维涡旋的Lattice Boltzmann方法模拟

介绍一个流体问题的LatticeBoltzmann并行模拟模型,该模型也是一种细胞自动机模型。用该模型模拟了二维的涡旋现象。利用计算机可视技术,可动态显示流体流动的演化过程,可用于分析、仿真流体流动现象,也可用于设计、优化一些物体与流体接触的边界。

Lattice Boltzmann simulation of flows in bifurcate channel at rotating inflow boundary conditions and resulted different outflow fluxes

The Lattice Boltzmann method （LBM） is used to simulate the flow field in a bifurcate channel which is a simplified model of the draft tube of hydraulic turbine machine. According to the simulation results, some qualitative conclusions can be deduced. The reason of uneven flux in different branches of draft tube is given. Not only the vortex rope itself, but also the attenuation of the rotation strength is important in bringing on the uneven flux. The later leads to adverse pressure gradient, and changes the velocity profile. If the outlet contains more than one exit, the one that contains the vortex rope will lose flux because of this adverse pressure gradient. Several possible methods can be used to minimize the adverse pressure gradient domain in order to improve the efficiency of turbine machine.

Equilibrium Energy and Entropy of Vortex Filaments in the Context of Tornadogenesis and Tornadic Flows

In this work, we study approximations of supercritical or suction vortices in tornadic flows and their contribution to tornadogenesis and tornado maintenance using self-avoiding walks on a cubic lattice. We extend the previous work on turbulence by A. Chorin and collaborators to approximate the statistical equilibrium quantities of vortex filaments on a cubic lattice when both an energy and a statistical temperature are involved. Our results confirm that supercritical (smooth, “straight”) vortices have the highest average energy and correspond to negative temperatures in this model. The lowest-energy configurations are folded up and “balled up” to a great extent. The results support A. Chorin’s findings that, in the context of supercritical vortices in a tornadic flow, when such high-energy vortices stretch, they need to fold and transfer energy to the surrounding flow, contributing to tornado maintenance or leading to its genesis. The computations are performed using a Markov Chain Monte Carlo approach with a simple sampling algorithm using local transformations that allow the results to be reliable over a wide range of statistical temperatures, unlike the originally used pivot algorithm that only performs well near infinite temperatures. Efficient ways to compute entropy are discussed and show that a system with supercritical vortices will increase entropy by having these vortices fold and transfer their energy to the surrounding flow.

分数阶衍射蜂窝晶格中带隙涡旋孤子的传输与控制

基于分数阶非线性薛定谔方程,研究分数阶衍射效应下蜂窝晶格中带隙涡旋光孤子的存在性与传输特性.首先采用平面波展开法得到蜂窝晶格能带结构,其次在带隙结构中分别采用改进的平方算子迭代法、分步傅里叶法和傅里叶配置法研究含有蜂窝晶格势的分数阶非线性薛定谔方程中带隙涡旋孤子的模式及其传输特性.研究结果发现带隙涡旋孤子的传输特性受Lévy指数和传播常数的影响.在稳定区间,带隙涡旋孤子可以稳定传输,而在非稳定区间,带隙涡旋孤子会随着传输距离的增加而逐渐汇聚,失去环状结构演变为基孤子.且Lévy指数越大,带隙涡旋孤子能够稳定传输的距离越长,功率越低.此外,相邻晶格同相位两个带隙涡旋孤子与旁瓣能量相叠加,反相位两带隙涡旋孤子与旁瓣能量相抵消,传输过程中逐渐失去环状结构,演化为类偶极子模式,且受方位角调制影响而周期性旋转.在非相邻晶格处两带隙涡旋孤子,由于旁瓣影响较小,带隙涡旋孤子在传输过程中能较好地保持环状结构.

舰载直升机主动甲板着舰气动载荷特性

被动与主动流动控制可减小舰艇艉流强度,但直升机着舰甲板处仍存在明显回流现象,由此导致直升机气动载荷变化显著。提出了自动升降的舰艇主动甲板,建立基于格子玻尔兹曼方法 (LBM)的舰艇主动甲板流场分析方法,并结合单向耦合模型,嵌入旋翼黏性涡粒子法,研究直升机主动甲板着舰气动载荷特性。通过与SFS2舰艇流场试验、分离涡模拟(DES)方法、大涡模拟(LES)方法比较,验证了所建方法的准确性。随后研究主动甲板对舰艇流场和直升机着舰气动载荷的影响特性。结果表明:相比于标准SFS2舰艇,主动甲板有效抑制了直升机着舰甲板处回流,以及直升机旋翼拉力损失、滚转和俯仰力矩,最大降幅分别为21.6%、55.1%、74.6%。

PT对称光晶格势中的涡旋光孤子传输特性的研究

本研究提出了一种实现具有宇称时间(PT)对称性的光学贝塞尔势的方案。通过从冷原子气体中光的衍射、非局域非线性和PT对称势约束之间的相互作用入手,研究了如何存在、传播和操纵二维涡旋光孤子。结果显示,该系统支持稳定的二维涡旋光孤子,其拓扑电荷最大值为|m|=6。此外,可通过控制PT对称晶格势的虚部来保证这种孤子的稳定性。由于里德堡-电磁感应透明(Rydberg-EIT)效应增强了局域和非局域非线性,因此这些二维涡旋光孤子只需要很低的功率就可以激发出来。研究结果不仅对PT对称势以及操纵二维涡旋光孤子有重要意义,还在光信息处理和传输方面具有很好的应用前景。

一种分布式电推进飞机的多学科参数快速估计方法

由于分布式电推进飞机综合性能显著,各个学科的交叉性强,是未来航空领域飞行器发展的趋势,因此建立一种适用于总体设计阶段的多学科参数评估方法对分布式电推进飞机的设计有着重大的意义。为了提高电动飞机在初始设计阶段的效率,本文提出了一种分布式电推进飞机的多学科参数快速估计方法。该方法对分布式电推进飞机进行总体建模并搭建能源系统框架,使用基于势流理论的简化气动分析方法对螺旋桨与机翼的气动—推进耦合特性进行分析。经仿真验证,该简化气动模型可以较好地模拟螺旋桨与机翼的气动—推进耦合特性。利用该方法在设定的飞行剖面下对某分布式电推进飞机进行多学科参数快速估计,得到了整个飞行剖面下的飞机气动性能变化及电推进系统的性能变化,为分布式电推进飞机的总体设计提供了支撑。

电动飞机分布式螺旋桨—机翼设计分析方法研究

为逐步实现航空器从传统能源到清洁能源的转换,将传统涡桨飞机改型成分布式电推进螺旋桨飞机是目前重要的研究方向。本文以运12F飞机巡航性能为约束,根据动量理论对其改型为分布式螺旋桨飞机后的机翼参数进行修正;从螺旋桨桨盘面积、螺旋桨与电动机匹配关系、螺旋桨质量三个方面综合评估确定分布式电推进螺旋桨个数;根据巡航及爬升任务剖面的拉力需求进行螺旋桨设计;将最终确定的分布式螺旋桨—机翼模型与原型机模型在OpenVSP中进行升阻力对比分析。结果表明,分布式螺旋桨的滑流效应在小速度、大迎角下增升作用更明显,可用于提升飞机起飞及爬升阶段性能指标。在巡航及爬升状态下,分布式螺旋桨上置比下置升力特性更好,升力系数可提高约5%,但在小速度时,升力系数提升的代价是阻力系数增加。本文研究为传统涡桨飞机改型为分布式螺旋桨飞机总体设计提供了参考。

二维光晶格中旋转玻色-爱因斯坦凝聚基态中的涡旋分布

利用多重网格预条件共轭梯度法,研究了囚禁在二维光晶格与谐振势组成的复合势阱中的旋转玻色-爱因斯坦凝聚体中的涡旋分布,探讨了光晶格深度、晶格常数和凝聚体旋转频率对旋转凝聚体中涡旋分布的影响.结果表明,由于光晶格势阱的引入,凝聚体中产生涡旋,且涡旋位于外部势阱极小值处.随着光晶格势阱深度的增加,凝聚体集聚在光晶格势阱的底部,形成格点状分布,其中的涡旋形成涡旋对,并融合形成更大的涡旋.在晶格常数较小时,凝聚体中涡旋分布形成类似Abrikosov涡旋晶格,随着晶格常数的增加,凝聚体中涡旋的分布形式出现多样化,出现了内中外三层结构.随着旋转频率的增加,凝聚体中涡旋数目也随之增加,涡旋分布也更加复杂和富于变化,凝聚体密度分布范围也随着旋转频率的增加而扩展.当凝聚体旋转频率接近外部谐振势阱的谐振频率,即凝聚体处于最低朗道能级近似时,其中的涡旋数量大幅度增加,且出现涡旋成对组合与融合现象,并形成了涡旋斑图花纹.

Simultaneous creation of multiple vortex-antivortex pairs in momentum space in photonic lattices

Engineering of the orbital angular momentum(OAM)of light due to interaction with photonic lattices reveals rich physics and motivates potential applications.We report the experimental creation of regularly distributed quantized vortex arrays in momentum space by probing the honeycomb and hexagonal photonic lattices with a single focused Gaussian beam.For the honeycomb lattice,the vortices are associated with Dirac points.However,we show that the resulting spatial patterns of vortices are strongly defined by the symmetry of the wave packet evolving in the photonic lattices and not by their topological properties.Our findings reveal the underlying physics by connecting the symmetry and OAM conversion and provide a simple and efficient method to create regularly distributed multiple vortices from unstructured light.

粒子与集体行为

布洛赫电子的运动受到贝里曲率的影响,已是人们熟知的量子几何效应。凝聚态系统中的各种集体行为,以及它们与电子系统的耦合,为量子几何现象的探索提供了更加广阔的舞台。针对几种典型的对称破缺状态,文章就下列方向中的有关研究和应用作出简略回顾和展望,包括晶格振动与声子、磁化动力学与自旋波、玻色凝聚体与量子涡旋、超导序参量与准粒子以及晶格形变与人工引力。

The Full Multi-wake Vortex Lattice Method:a detached flow model based on Potential Flow Theory

One of the main issues concerning the standard Vortex Lattice Method is its application to partially or fully detached flow conditions,where non-linear aerodynamic characteristics appear as the angle of attack increases and/or the aspect ratio decreases.In order to solve such limitations,a pure numerical approach based entirely on the Vortex Lattice Method concepts has been developed.The so-called steady“Full Multi-wake Vortex Lattice Method”comes from the main hypothesis that each discretized element on the body’s surface detaches their own wakes downstream.The obtained results match for lift,drag and moment coefficients for the entire aspect ratio range configurations(under straight wakes and inviscid assumptions).Future unsteady versions of such a multi-wake approach could improve the current results obtained through Vortex Element Methods(as vortons or isolated vortex filaments).

Multidimensional multiplexing holography based on optical orbital angular momentum lattice multiplexing

The use of orbital angular momentum(OAM)as an independent dimension for information encryption has garnered considerable attention.However,the multiplexing capacity of OAM is limited,and there is a need for additional dimensions to enhance storage capabilities.We propose and implement orbital angular momentum lattice(OAML)multiplexed holography.The vortex lattice(VL)beam comprises three adjustable parameters:the rotation angle of the VL,the angle between the wave normal and the z axis,which determines the VL’s dimensions,and the topological charge.Both the rotation angle and the VL’s dimensions serve as supplementary encrypted dimensions,contributing azimuthally and radially,respectively.We investigate the mode selectivity of OAML and focus on the aforementioned parameters.Through experimental validation,we demonstrate the practical feasibility of OAML multiplexed holography across multiple dimensions.This groundbreaking development reveals new possibilities for the advancement of practical information encryption systems.

面向柔性扑翼翼面形状和运动参数的优化设计

扑翼机具备仿鸟类的外形,能够隐蔽执行侦查监视任务,合理设计翼面形状和运动过程能够提升扑翼飞行气动效应。当前针对扑翼翼面设计问题,缺乏考虑流固耦合效应的优化设计研究,还未在设计阶段考虑改变柔性翼面形状对扑翼气动特性的影响,且现有研究只涉及对翼面形状或扑翼运动的单因素分析讨论,缺乏综合2种设计因素的优化设计。针对定速前飞的柔性扑翼翼面进行气动特性优化设计,采用Newmark-β方法求解结构响应,并与现成软件求解器的计算结果进行对比,验证结构动力学计算方法的准确性,用非定常涡格法(UVLM)计算扑翼气动力,搭建了高效的流固耦合计算框架。由于扑翼复杂设计空间具有多个局部最优点,采用与并行计算结合的细分矩形(DIRECT)全局优化算法,提高计算效率,对柔性扑翼翼面的形状和运动参数进行迭代优化,确定最大化推进效率的设计参数,并与刚性模型优化结果进行对比。结果表明:柔性扑翼翼面形状和运动优化设计能够获得更高的推进效率,与只采用形状优化相比最优推进效率提高了5.6%,比刚性模型优化结果提高了27.0%。

分布式电推进飞机概念方案气动特性快速评估方法

分布式电推进(DEP)飞机充分利用气动/推进耦合效应提高飞机的气动效率,但动力数量增加导致螺旋桨滑流与翼面流场干扰强烈,气动分析和设计的复杂度及计算成本上升。为提高DEP飞机早期设计阶段气动设计效率,降低研制成本,采用线性无黏的涡格法-激励盘理论(VLM-ADT)、涡格法-非定常涡格法(VLM-UVLM)及加入黏性修正的VLM(Modified-VLM)提出气动特性快速评估方法。对单机翼、单螺旋桨/机翼耦合、X-57机翼(巡航、高升力状态)及分布式螺旋桨/机翼耦合构型的气动特性进行快速评估。与基于雷诺平均Navier-Stokes(RANS)方程求解器的结果对比,单机翼和单螺旋桨/机翼升力系数和阻力系数一致性良好,误差最大不超过8.2%;俯仰力矩系数在同一数量级。X-57机翼和分布式螺旋桨/机翼的升力系数与RANS方程结果吻合度较高,误差最大不超过10%。考虑黏性修正的VLM所计算的X-57机翼和分布式螺旋桨/机翼的总阻力系数与RANS方程结果趋势一致。分布式螺旋桨滑流增加机翼的动压,使机翼局部有效迎角发生改变,改变了机翼当地升阻特性。所提方法为分布式螺旋桨飞机在早期设计阶段气动特性快速评估和气动布局方案快速选型提供了一种兼顾计算精度和效率的有效方法。