格林函数法研究机弹干扰对航弹初始弹道的影响

应用格林函数法对机翼下气流对航弹初始弹道的影响进行了研究。揭示了机弹干扰的机理，影响的主要原因是干扰气流改变了航弹初始运动阶段的压力分布，从而引起气动系数的变化，形成其特有的弹道特性。     

A wrinkle in flight: the role of elastin fibres in the mechanical behaviour of bat wing membranes

Bats fly using a thin wing membrane composed of compliant, anisotropic skin. Wing membrane skin deforms dramatically as bats fly, and its three-dimensional configurations depend, in large part, on the mechanical behaviour of the tissue. Large, macroscopic elastin fibres are an unusual mechanical element found in the skin of bat wings. We characterize the fibre orientation and demonstrate that elastin fibres are responsible for the distinctive wrinkles in the surrounding membrane matrix. Uniaxial mechanical testing of the wing membrane, both parallel and perpendicular to elastin fibres, is used to distinguish the contribution of elastin and the surrounding matrix to the overall membrane mechanical behaviour. We find that the matrix is isotropic within the plane of the membrane and responsible for bearing load at high stress; elastin fibres are responsible for membrane anisotropy and only contribute substantially to load bearing at very low stress. The architecture of elastin fibres provides the extreme extensibility and self-folding/self-packing of the wing membrane skin. We relate these findings to flight with membrane wings and discuss the aeromechanical significance of elastin fibre pre-stress, membrane excess length, and how these parameters may aid bats in resisting gusts and preventing membrane flutter.     

Tensile Deformation Properties of Corrugated Style Fiber Reinforced Composite Skin for a Morphing Wing

A type of skin structure which is made by a Circular Arc Corrugated Style Fiber Reinforced Composite(CACSFRC)is proposed to meet the requirements of the large and continuous deformation and high load capacity of a morphing wing skin.A mechanical model is developed to predict the tensile deformation properties and equivalent elastic modulus of the composite skin.Corrugated and plane skin samples are manufactured and tested.The theoretical analysis and tension tests show that CCSFRC skin has markedly much mor...     

A Study of the Vortical Flow over a Delta Wing with a Leading Edge Extension

The present paper describes computational and experimental work on the vortex flow characteristics of a sharp-edged delta wing with a leading edge extension (LEX). Experiment was carried out using a low-speed wind tunnel that has a test section of 3.5 m(W)×2.45 m(H)×8.7 m(L). The angle of attack of the delta wing ranges from 10° to 30°. The free stream velocity is fixed at 20 m/s, which corresponds to Reynolds number of 0.88×106. Computations using the mass-averaged implicit 3D Navier-Stokes equations were applied to predict the complicated vortical flow over the delta wing. The governing equations were discretized in space using a fully implicit finite volume differencing formation. The standard k-e turbulent model was employed to close the governing equations. The present computations predicted the experimented flow field with a good accuracy.     

压缩载荷下闭合斜裂纹的分支裂纹渐近扩展分析

采用滑动裂纹模型并结合现有张开斜裂纹的I 型分支裂纹扩展特性的研究成果,研究了闭合斜裂纹的I型分支裂纹的渐近扩展特点,结果表明：1) 闭合斜裂纹的I 型分支裂纹路径的渐近线为平行于最大主应力的一条直线,并得出了渐近线方程;和张开斜裂纹的翼型裂纹不同,闭合斜裂纹的翼型裂纹路径的渐近线不一定过初始裂纹中心点,该渐近线位置与初始裂纹面的摩擦系数、初始裂纹长度及初始裂纹角有关;2) 闭合斜裂纹的I 型分支裂纹的扩展路径可以近似采用双曲线描述,并得出了描述I 型分支裂纹扩展路径的方程.采用ABAQUS 二次开发对闭合斜裂纹的分支裂纹的扩展过程进行了数值模拟,并采用数值模拟和现有试验相结合的方法验证了以上结论的正确性.     

一种基于采样点的大规模群体实时三维可视化方法

大规模群体的三维可视化是虚拟现实领域的研究热点之一.目前,由于驱动方法与渲染效率的问题,在虚拟空间中创建的大规模虚拟群体很难同时满足驱动与渲染过程的逼真与实时.该问题对于群体规模庞大,个体外形、动作具有一定程度个性化,需要进行独立运动控制的场景尤为明显.针对这一问题,提出了一个高效的大规模虚拟群体三维可视化方法：首先,通过使用模板派生技术从少量模板模型派生出大量外观各异的个体模型;其次,使用运动数据个性化变形技术实现了运动数据的重用;最后,使用基于采样点的渲染技术实现了大规模数据的实时显示.在上述工作基础上,研究并开发了一套大规模虚拟群体的三维可视化系统,能够方便的在普通PC机上实时、逼真的展示大规模的运动虚拟群体,并实现了60000群众紧急疏散过程的实时三维可视化.     

新型网状加劲薄壁屋盖结构体系仿生研究

首先,对实验中获取的高清晰度蜻蜓翅膀数码图片进行细致地分析,找出了翅膀网状翅脉结构中翅脉的分布规律与尺寸变化、网格形状的差异等结构特征;然后,建立了蜻蜓翅膀平面结构模型和起拱起皱的三维空间结构模型,并利用ANSYS对其进行分析,采用三节点等参数梁元Beam189模拟翅脉和八节点等参数曲壳单元Shell 93模拟翅膜,以考虑翅脉和翅膜间的变形协调性。研究表明：三维空间结构模型中的起拱、起皱能显著提高翅膀结构的刚度和改善翅膀结构中内力的分布;如果将四、六边形的网格单元进行合理搭配,还可以使结构刚度和材料利用率得到优化。最后,基于以上研究成果,提出了三个具有不同网格分布的新型薄壁屋盖结构体系仿生模型,并对它们进行了几何非线性分析。     

排式双翼布局低雷诺数气动特性计算研究

作为一种新型的气动布局形式,排式布局对低雷诺数流动具有较高的气动效率,适用于柔性可充气飞行器,比如充气式飞机或是高空飞艇。但是,由于前、后翼之间强烈的气动干扰现象,目前对此类布局的气动特性认识还十分有限。为了充分理解这种布局的气动特点,在前期风洞试验的基础上,开展了数值模拟工作,详细地研究了低雷诺数情况下翼型厚度、表面波纹状外形及后翼偏转角度等几何因素对此类飞行器气动特性的影响规律。计算结果表明,在计算的迎角范围内,排式布局能通过前后翼之间的气动干扰延缓或抑制机翼后缘处的流动分离,从而提高整体气动效率,因此排式布局在未来很适合应用于小型无人机或是飞艇等可充气式飞行器构型上。     

基于AI技术的固定翼无人机集群分布式规避控制系统研究与设计

固定翼无人机集群是由多个固定翼无人机组成的群体,在飞行任务中协同工作。相比于单个无人机,固定翼无人机集群具有更高的综合性能和更广阔的应用前景。但由于固定翼无人机在恶劣环境作业过程中存在着很多风险,例如障碍物撞击、相邻无人机碰撞等,威胁无人机的安全性。故设计了基于AI技术的固定翼无人机集群分布式规避控制系统。系统硬件单元主要包括AI视觉传感器设计单元、激光雷达传感器设计单元、控制器设计单元与无线通信网络设计单元,通过上述硬件设备提供实时的环境信息,控制无人机飞行姿态,实现信息共享。软件模块基于AI技术解算无人机位置和姿态,计算障碍物位置实现形状感知,完成无人机集群分布式规避控制。通过硬件与软件的协同作业,实现了固定翼无人机集群的分布式规避控制。实验结果显示:应用设计系统获得的无人机位置感知结果、障碍物位置感知结果与实际位置相同,路径总偏离量数值为4m,充分证实了设计系统控制性能较佳。     

内置涡核破碎翼参数对旋风分离器性能影响的仿真研究

内置涡核破碎翼旋风分离器具有保持较高效率同时降低压降的特点。研究涡核破碎翼参数对分离器性能的影响有重要的意义。本文利用计算流体动力学方法(CFD),采用雷诺应力模型(RSM)和离散化模型(DPM),模拟涡核破碎翼参数对分离器性能的影响。结果发现:随着相邻涡核破碎翼间距增大,分离器收集效率及压降均呈现缓慢增长趋势,而随着每组涡核破碎翼个数增加,分离器收集效率及压降均呈缓慢下降趋势。