扑动轨迹对扑翼气动特性影响的数值研究

国内外对扑翼飞行的气动性能进行了大量研究,这些研究大多针对特定运动轨迹下的扑翼,然而大量观察发现,昆虫在飞行时其翅膀会出现各种不同的运动形式,这些不同的翅膀运动方式必定对其气动性能产生重要影响。该文基于对昆虫的实验和数值模拟中常用的几种扑动轨迹模型分析,建立了三种具有相同准稳态气动力的扑翼扑动轨迹,并采用数值求解N-S 方程的方法,研究了前飞状态下不同扑动轨迹对扑翼气动特性产生的影响。结果显示扑动和转动均为简谐函数轨迹形式的扑翼具有较高的升举效率和推进效率。进一步通过对不同扑动轨迹扑翼流场分析得出,扑动轨迹不能改变扑翼产生的尾流性质,但可以影响涡的强度,从而使扑翼产生不同的气动性能。     

柔性扑翼气动性能的数值研究

国内外对扑翼飞行的气动特性进行了大量研究,这些研究大多基于简谐扑动的刚性翼,然而大量观察发现鸟或昆虫飞行时,翅膀存在明显的柔性变形,这种变形对其气动性能具有显著的影响。该文针对一简化的二维柔性扑翼模型,采用数值求解N-S方程并耦合扑翼柔性变形方程的计算方法,研究了扑翼柔性变形对其气动性能的影响。结果显示扑翼的柔性变形改变了扑翼周围的涡结构,从而影响扑翼的气动性能;适当的柔性变形能延迟前缘涡的脱落,从而有效地改善扑翼的推进效率,但同时减弱了扑翼在低雷诺数环境中产生高升力的尾迹捕捉机制。     

仿生翼型对半主动扑翼捕能性能的影响

为了分析仿生翼型对半主动扑翼捕能性能的影响,该文在Fluent流体求解器的基础上,通过二次开发,编制了一套可有效求解流体流动、扑翼主动转动和被动往复扑动的计算程序。在此基础上,研究仿蜻蜓翼型、仿海鸥翼型、NACA0012和NACA0015四种翼型的捕能性能,结果表明采用仿生翼型的扑翼具有更好的捕能性能。进一步通过对不同外形扑翼的流场分析发现,采用仿生翼型可使扑翼在被动往复扑动过程中产生更强的涡流,并且在俯仰运动过程中可延缓涡流从扑翼表面脱落,从而使扑翼具有较好的捕能性能。     

仿生扑翼飞行器的气动效率研究

该文主要采用BLU-SGS混合动态网格隐式算法进行时间推进,空间离散采用二阶迎风格式的有限体积法。求解非定常Navier-Stokes方程,完成了二维不可压缩流场的数值模拟。在该基础上,通过积分计算的形式得到整个机翼平面的气动力,研究揭示了不同扑动频率、风速参数、减缩频率、雷诺数与飞行气动效率的关系,表明参数的合理调试对仿生扑翼飞行器的有效飞行起到重要影响。针对不同参数条件,研究分析了气动力以及气动效率结果,为后续气动特性问题的研究提供参考。     

扑翼飞行器气动力测量技术研究进展与展望

扑翼飞行器是一种仿照鸟类飞行的新概念小型无人飞行器,区别于传统固定翼和旋翼飞行器,它主要通过机翼扑动与空气相互作用来提供飞行动力,从而实现飞行器的姿态变动。扑翼飞行器气动特性测试的实质是揭示在非定常流场环境下,扑翼飞行器气动力的产生机制,以及相关扑翼飞行器设计参数对气动特性的影响。通过气动试验方法为扑翼飞行器飞行控制和结构优化等研制工作提供数据支持,将对新型扑翼飞行器理论研究以及飞控品质的提升起到巨大的推动作用。     

扑翼飞行器测力平台设计与振动特性仿真分析

扑翼飞行器是基于鸟类仿生学理论衍生出的新型无人飞行器,主要通过机翼周期性上下扑动来提供飞行器所需的升力和推力,在军用和民用飞行器领域均有广阔的应用前景。扑翼飞行器气动力测量作为样机气动性测试的重要手段,多维气动力的准确测量可为新型扑翼飞行器设计优化和飞控品质的提高提供试验数据支持。本文介绍了一种新型组合式多维小量程测力平台,可实现扑翼飞行器六维气动力和气动力矩的测量。考虑到扑翼飞行器机翼上下扑动过程动态测力需求,应用Ansys Workbench有限元分析软件对测力平台进行了模态分析和频响分析,获得在工作频率下的频率响应,仿真结果表明测力平台的振动特性满足设计要求。     

展向柔性对扑翼推力影响原因的数值分析

为研究展向柔性对扑翼推力的影响及产生影响的原因,该文使用一种折叠翼模型作为研究对象,改变展向折叠的弹性系数,联立求解N-S方程和刚体运动方程,并进行了展向柔性对推力影响原因的分析。结果表明:适当的展向柔性可以减小阻力系数,但过大的展向柔性却会增加阻力系数;展向柔性之所以能够改变阻力系数,是因为展向柔性的引入改变了有效攻角沿展向的分布。若展向柔性的引入能够增加有效攻角绝对值沿展向的分布,那么就可以减小瞬时阻力系数。     

一种超低空飞行的仿生扑翼飞行器的设计及分析

为研制既具备一定的负载能力,又具有高隐蔽性的飞行器,依据鸟类的飞行方式,设计了一种可以超低空飞行的仿生扑翼飞行器.首先,计算了扑翼飞行器传动机构的自由度,从原理上确定了设计方案的可行性,并确定了飞行器各个构件的尺寸;其次,利用设计软件Creo绘制飞行器三维模型,通过运动仿真得出飞行器的扑动符合设计要求;然后,利用ADA...     

一种考虑攻角影响的超音速翼面颤振分析方法

采用活塞理论计算非定常气动力，用新的方法考虑了攻角的影响，和颤振运动方程耦合求解三维翼面的颤振临界条件。分别计算了四种翼型(平板翼，圆弧翼，六边形翼和四边形翼)的颤振临界速度，计算结果和风洞试验数据比较，二者相当一致。     

基于动态近似边界条件的气动弹性数值模拟

发展了一种利用欧拉方程计算非定常气动力的数值方法,通过在固定物面边界上满足动态近似边界条件计算出非定常气动力,避免了在每个时间步重新生成网格或需用动网格技术进行网格变形处理过程,提高了计算效率。运用这种方法计算了一系列非定常气动力算例,并与非结构动网格准确边界条件下的欧拉方程解和实验数据进行了比较,进一步分析了翼型俯仰角和马赫数对非定常气动力相对误差的影响。将气动力解算器与结构方程耦合进行气动弹性数值模拟,计算了跨音速具有S型颤振边界的二元气动弹性标准算例-Isogaiwing。算例结果表明,利用动态近似边界条件的欧拉方程具有简便、高效的特点,并能在小振幅情况下得到与精确边界条件精度相当的非定常流场解,还可以用于气动弹性分析。     

Added mass effect on flapping foil

Unsteady effects caused by accelerating bodies in water play a very important role in biological propulsion. However, such propulsion mechanisms are challenging for simulation as both body geometry and locomotion patterns are quite complex and a natural first step is to model the motion of a standard man-made airfoil. The work presents simulations of harmonic oscillations of a NACA 0012 foil in water and the hydrodynamic forces generated were obtained by a Boundary Element Method (panel method) code. The focus is placed on one of the most important unsteady effects, the added mass effect, which has not been sufficiently addressed in the literature. The corresponding unsteady forces were obtained through appropriately devised two-dimensional added mass tensor. The computational results were compared to existing analytical ones and a maximum error of 10⁻⁶ was obtained for the added mass coefficients of the circle of unit diameter. The development of a dedicated numerical approach for the calculation of the added mass tensor is necessitated by the lack of analytical solution for a variety of wing shapes such as NACA foils. The simulations showed that for the range of investigated parameters the inertia thrust and lift generated by the flapping foil increase sharply when the added mass contribution is considered. For example, if the Strouhal number is set to 0.3 and the ratio between the wing and fluid densities to 0.3, the time average of the inertia thrust increases by 23 times and the maximum of the inertia lift is ca. 37 times larger when the added mass effect is considered. Generally, a densities' ratio of order 1 results in an increase of the time-average inertia thrust of order 10. It was confirmed that, as the densities' ratio becomes larger, the contribution of the added mass to the generated inertia forces decreased. As the Strouhal number increases, the added mass effect was found to be more dominant due to the imposed motion kinematics, i.e. the pitch amplitude. The obtained results show clearly that for the specific case of flapping flight in dense fluids the unsteady effects caused by the object acceleration are of prime importance for two reasons: (i) accurate estimate of the generated thrust and (ii) realistic assessment of the resulting structural loads.     

Effect of wavelength of fish-like undulation of a hydrofoil in a free-stream flow

Fish-like undulating body was proposed as an efficient propulsion system, and various mechanisms of thrust generation in this type of propulsion are found in the literature—separately for undulating and pitching fishes/foil. The present work proposes a unified study for undulating and pitching foil, by varying wavelength \(\lambda \) (from 0.8 to 8.0) of a wave travelling backwards over the NACA0012 hydrofoil in a free-stream flow; the larger wavelength is shown to lead to the transition from the undulating motion to pitching motion. The effect of wavelength of undulation is studied numerically at a Reynolds number \(Re=4000\), maximum amplitude of undulation \(A_{max}=0.1\) and non-dimensional frequency of undulation \(St=0.4\), using level-set immersed-boundary-method based in-house 2D code. The Navier–Stokes equation governing the fluid flow is solved using a fully implicit finite-volume method, while level-set equation governing the movement of the hydrofoil is solved using an explicit finite-difference method. It is presented here that the thrust generation mechanism for the low wavelength case undulating \((\lambda =0.8)\) foil is different from the mechanism for the high wavelength pitching foil. With increasing wavelength, mean thrust coefficient of the undulating foil increases and asymptotes to value for the pure pitching foil. Furthermore, the ratio of maximum thrust coefficient to maximum lateral force coefficient is found to be larger for the smaller wavelength undulating foil as compared with the larger wavelength pitching foil.     

尺度效应对水下合成射流推力特性影响研究

该文通过数值方法研究了尺度效应对水环境下合成射流推力及推进效率的影响,不同尺度下激励器的网格采用等比例缩放的方式得到,数值计算在fluent进行,且数值计算方法通过实验数据进行了验证。数值计算结果发现,当激励器尺度为0.1 mm时,推力曲线与速度曲线非常接近,此时平均推力及推进效率均较小。随着尺度增加,当激励器尺度大于1 mm时,推力曲线不对称度增加,且推力曲线的上升区间所占周期增加而下降区间所占周期减小,此时平均推力及推进效率都有明显提高。建立了合成射流的推力模型,该模型将合成射流推力分解为三部分:质量效应、加速效应及外部流场的压强效应。给出了不同尺度下的涡量图、速度分布图,通过对其分析可知,尺度较小时粘性作用较强,此时,内部流体的加速效应及外流场压强效应均很小,导致推进效率较低。随着尺度增加,粘性作用减弱,推进效率开始增加,当尺度增加到粘性可以忽略时,推进效率不再随尺度增加。     

推进轴系纵向振动引起的艇体声振特性分析

螺旋桨在艇体艉部不均匀伴流场中旋转产生的脉动推力激励起推进轴系纵向振动,振动经推力轴承基座传递至艇体,引起艇体水下低频辐射噪声。通过建立推进轴系、推力轴承基座和艇体耦合结构模型,分析推进轴系─艇体的耦合振动模态,结果显示,艇体弹性支撑边界条件对推进轴系的纵向振动特性有一定影响。采用基于模态叠加法的有限元结合边界元方法分析推进轴系纵向振动激励下的艇体水下辐射声场,分析表明,艇体第1阶纵向振动模态是参与艇体水下声辐射的主模态。进一步在推力轴承及其基座间安装动力吸振器以减小推进轴系纵向振动向艇体的传递,使艇体水下辐射噪声得到一定程度上的控制。     

Boundary element simulation of inviscid flow around an oscillatory foil with vortex sheet

The dynamic performance of a rigid foil with harmonic vertical and rotational motions in fluid flow has been studied through velocity potential theory. A boundary element based time stepping scheme is introduced to simulate the flow around the foil and the vortex wake. The body surface condition is satisfied on the exact foil surface and the motion and deformation of the wake sheet shed at the trailing edge is tracked. Kelvin condition is satisfied and a Kutta condition for the unsteady motion is proposed to circumvent the singularity at the trailing edge. Point vortex, which is reduced from wake vortex dipole, is introduced to approximate the vorticity. The performance of foil NACA0012 with harmonic vertical and rotational motions are studied extensively; the propulsion/swimming mode, energy harvesting mode and the flying mode are analysed in detail.     

扑翼空气动力学研究进展与应用

昆虫、鸟类与蝙蝠等生物具有高超的飞行能力,是扑翼飞行器的主要模仿对象。近年来,扑翼空气动力学领域的研究取得了很大进展,该文主要对其主要研究成果进行综述,重点介绍扑翼空气动力学各研究方向的最新进展,包括昆虫、鸟类与蝙蝠扑翼的主要升力机制,翅膀形态学参数与微观结构、翅膀柔性与动态变形、翼-翼干扰、翼-身干扰、个体间干扰及地面效应等对扑翼气动特性的影响。同时还对仿生扑翼飞行器气动研究的新进展进行了介绍,并提出了扑翼空气动力学所面临的主要问题和挑战。