Aeroelastic Analysis and Optimization of High-aspect-ratio Composite Forward-swept Wings

In order to analyze the effects of forward-swept angle and skin ply-orientation on the static and dynamic aeroelastic characteristics, the aeroelastic modeling and calculation for high-aspect-ratio composite wings with different forward-swept angles and skin ply-orientation are performed. This paper presents the results of a design study aiming to optimize wings with typical forward-swept angles and skin ply-orientation in an aeroelastic way by using the genetic/sensitivity-based hybrid algorithm. Under the conditions of satiated multiple constraints including strength, displacements, divergence speeds and flutter speeds, the studies are carried out in a bid to minimize the structural weight of a wing with the lay-up thicknesses of wing components as design variabies. In addition, the effects of the power of spanwise variation function of lay-up thicknesses of skins and iugs on the optimized weights are also analyzed.

Structural Modeling and Aeroelastic Analysis of High-Aspect-Ratio Composite Wings

A unified structural model for high-aspect-ratio composite wing with arbitrary cross-section is developed. Two types of lay-ups of the composite wing, namely, circumferentially uniform stiffness （CUS） configuration and circumferentially asymmetric stiffness （CAS） configuration, are investigated. The present structural modeling method is validated through ANSYS FEM software for the case of a composite box beam. Then, the case of a single-cell composite wing with NACA0012 airfoil shape is considered. To investigate the aeroelastic problem of high-aspect-ratio composite wings, the linear ONERA aerodynamic model is used to model the unsteady aerodynamic loads under the case of small angle of attack. Finally, flutter speeds of the high-aspect-ratio wing with various composite ply angles are determined by using U-g method.

Stall Flutter Analysis of High-Aspect-Ratio Composite Wing

The stall flutter characters of high-aspect-ratio composite wing are investigated, and the effects of structure geometric nonlinearity and stiffness couple created by composite anisotropy on them also are discussed. Firstly, the high-aspect-ratio wing is modeled as a composite thin-walled closed section Euler beam whose displacement and rotation both could be of finite value, and the nonlinear dynamic equations is build up on it with all the effects of geometric nonlinearity, aerodynamic nonlinearity and anisotropy of material being considered. Then vibration equations are deduced through perturbing the dynamic equations at wing＇s equilibrium position, and coupled with unsteady stall aerodynamic model and ONERA model, to obtain the nonlinear stall flutter analysis equations of wing. Finally, the flutter stabilities with various wind speeds are determined by the harmonic balance method. With several exampies, the validity of the stall flutter model is proved, and the significant effects of geometric nonlinearity on the stall flutter various characters as wall as the effects of ply angle on the stall flutter speed and frequency also are discussed.

Stiffness Distribution and Aeroelastic Performance Optimization of High-Aspect-Ratio Wings

The relationship between stiffness distribution and aeroelastic performance for a beam-frame model and a3-D model is investigated based on aeroelastic optimization of global stiffness design for high-aspect-ratio wings.The sensitivity information of wing spanwise stiffness distribution with respect to the twist angle at wing tip,the vertical displacement at wing tip,and the flutter speed are obtained using a sensitivity method for both models.Then the relationship between stiffness distribution and aeroelastic performance is summarized to guide the design procedure.By using the genetic/sensitivity-based hybrid algorithm,an optimal solution satisfying the strength,aeroelastic and manufacturing constraints is obtained.It is found that the summarized guidance is well consistent with the optimal solution,thus providing a valuable design advice with efficiency.The study also shows that the aeroelastic-optimization-based global stiffness design procedure can obtain the optimal solution under multiple constraints with high efficiency and precision,thereby having a strong application value in engineering.

一种高硬度复杂薄壁翼片的机械加工工艺设计

一种高硬度复杂薄壁翼片目前没有高速铣削的加工手段可利用,需要普通铣削结合真空炉处理的方式来满足产品技术要求,加工难度大,生产进度紧。通过工艺攻关、工艺优化形成了翼片的机械加工工艺方案,采用普通铣削后进行真空炉淬火的方式保证翼片角度、厚度、孔径和力学性能要求,最后用电火花切割的方式将工件与工艺台分离保证翼轴孔距和外形尺寸。结合真空炉处理和电火花切割的特点,及时处理了加工过程中出现的热处理变形、切割外形导致孔距超差等技术问题,最终保证首批次合格产品按进度交付。所涉及到的翼片工艺方案、工艺台、定位基准选择、控制热处理变形的工装、电火花切割工装等内容属于西安现代控制技术研究所首次应用,具有创新性,对于弹体结构件中技术要求较高的翼片及同类结构的零件有一定的参考价值。

HyperFLOW 软件数值模拟TrapWing 高升力外形

采用High-Lift研讨会提供的梯形翼外形(TrapWing),利用自主研发的基于结构、非结构网格的通用CFD软件HyperFLOW进行了数值计算,以评估其对复杂外形低速流的模拟能力。分别采用了三套不同拓扑结构的计算网格,包括两套非结构/混合网格和一套多块结构网格,每套网格又分为粗、中、细三种密度不同的网格数量以考察其网格收敛性。利用Richardson插值法,对计算结果开展了可信度分析。结果表明,不管是结构网格还是非结构网格,HyperFLOW均建立了可接受的可信度;对于高升力外形数值模拟,SA湍流模型要比SST湍流模型模拟的更准确;在失速迎角附近,现有的二阶精度解算器仍需持续改进。

输电线路单导线覆冰形状对直流大电流融冰时间的影响

直流大电流融冰是输电线路冰灾防御的有效手段。根据实际运行条件下输电线路单导线覆冰形状在导线各处不一的情况,计算分析单导线圆形覆冰和翼形覆冰的直流大电流融冰时间。计算结果表明,翼形冰融冰时间仅为圆形冰融冰时间的10%左右。在重庆大学雪峰山能源装备安全国家野外观测研究站对LGJ—300/50和LGJ—400/35两种型号单导线进行直流大电流融冰实验。实验结果表明:LGJ—300/50导线翼形冰融冰时间为圆形冰融冰时间的10.6%,LGJ—400/35导线翼形冰融冰时间为圆形冰融冰时间的8.3%。基于此,该文提出抑制导线形成圆形冰促使其生长为翼形冰可降低直流大电流融冰时间,减少融冰能量消耗。

升力翼高速列车前后翼干扰特性研究

在高速列车车顶安装升力翼旨在通过提高列车气动升力减小轮轨作用力,是一种新型等效减重的手段。升力翼安装到高速列车顶部后,其工作环境与航空相比有很大不同,升力翼与升力翼之间存在相互干扰。以三车编组1꞉10缩比某型CRH高速列车模型为研究对象,采用改进型延迟分离涡模拟(IDDES)方法,分别针对不同高度和不同间距布局的两翼高速列车进行数值模拟分析,探讨前后升力翼布局对升翼力列车气动力和周围流场结构的影响规律及其作用机理。研究结果表明:对于不同间距布局,当后翼距离前翼过近时,前翼翼尖涡流的干扰导致流速加大,压差变小,最终使气动升力有所降低;而当前后翼间距过大时,即后翼远离前翼尾流干扰范围,后翼由于无法受到前翼下洗气流的正向作用,使得升力减小。对于不同高度布局,错落式布局下前翼的尾流涡旋由于高度差的原因远离后翼,相较于等高式布局,错落式布局中前翼尾流对后翼造成的干扰程度较小。错落式布局的列车整体升力性能优于等高式布局的列车整体升力性能,且前低后高式布局下,列车的增升效果最好。综合不同间距和不同高度布局的结果可知,对于两翼高速列车,翼间距为0.90H时前低后高式布局的整车气动性能最优,尤其是列车升力可以得到显著提升。

大展弦比飞行器变形辅助高度控制策略

针对变形飞行器结构/飞行耦合动力学的飞行控制问题,以大展弦比飞行器为研究对象开展了变形辅助高度控制策略研究。采用单元翼多体假设,构建了大展弦比飞行器二面角变形结构,建立了结构/飞行纵向耦合动力学模型,基于线性二次型(LQR)控制器设计方法设计了主动变形(AM)和被动变形(PM) 2种控制策略。其中,被动变形控制策略仅采用升降舵作为控制输入,结构二面角动态行为由耦合动力学驱动;主动变形控制策略以二面角铰链处的扭矩作为额外输入对高度跟踪进行协调控制。仿真分析了2种控制策略下的高度跟踪效果及状态变化,研究结果表明:采用主动变形控制策略可有效改善高度跟踪暂态过程的性能,降低姿态回路的阻尼特性,为未来先进变形飞行器的结构/飞行一体化控制提供研究基础。

升力翼对高速列车通过隧道时气动效应的影响

在高速列车上安装升力翼可以为高速列车提供升力,降低列车对轨道的压力,从而有效减少轮轨磨损,但安装升力翼对列车在隧道内行驶时的气动性能产生较大影响,为此,基于三维非定常可压缩RNG k−ε两方程湍流模型,对升力翼列车通过隧道时的气动效应进行数值模拟研究。研究结果表明:在列车进入隧道过程中,升力翼尾流结构增大,对列车表面压力产生一定的影响;升力翼尾流使列车表面压力下降,同时升力翼增加车隧阻塞比,使列车表面的压力上升,两者共同影响列车表面压力,导致列车表面压力分布复杂;安装升力翼使列车表面与隧道壁面的压力幅值均增加,列车表面压力幅值最大增加5.4%,隧道壁面压力幅值最大增加14.1%;同时,对隧道出口的微气压波产生不利影响,在距离隧道出口20 m处的微气压波幅值上升4.1%。研究结果可为升力翼的参数优化设计提供指导。

升力翼对列车气动特性及运行安全性的影响研究

为探究升力翼高速列车的可行性,结合列车空气动力学和车辆多体系统动力学理论,建立了有/无升力翼高速列车空气动力学模型和车辆系统动力学模型,对有/无升力翼高速列车在明线无风及横风运行环境下的气动特性及运行安全性进行了仿真研究。研究结果表明:安装升力翼可提升高速列车的气动升力及升阻比,但气动阻力也大幅度增大;有/无翼高速列车周围流场特性差异较大,安装升力翼后列车表面压力分布及流线流向改变,列车滑流速度峰值增大,两侧及尾流区域速度分布改变。横风下列车表面压力分布及背风测涡脱结构改变,头车受到的气动阻力、升力、侧力及点头力矩相比于无翼时有明显的增大,升力与侧滚力矩差异明显,侧滚力矩方向改变且数值增大,摇头力矩变化很小。明线无风下,安装升力翼能够减小6%~13%的轮轨垂向力,其中尾车由于气动升力最大,轮轨垂向力减幅最显著;运行速度在450 km/h及以下时升力翼高速列车能够安全平稳运行,运行速度在500 km/h时升力翼高速列车轮轨垂向力和轮重减载率超限;影响安全性的主要原因是升力翼扩大了各节车之间气动载荷的差异,升力翼的气动布局有待进一步改善,建议减小头车和尾车的升力;横风环境下,升力翼高速列车头车受到升力、侧力及侧滚力矩数值明显增大,运行安全性恶化,横风安全域缩小。

升力翼高速列车曲线通过时的轮轨黏着性能研究

建立考虑轮轨关系、升力翼及流场耦合特性等因素的车辆系统动力学模型,分析升力翼高速列车曲线通过时的运动姿态和轮轨接触特性响应,研究列车在曲线轨道运行的轮轨黏着性能,探讨轨道不平顺、曲线半径、运行速度及轮轨接触条件对轮轨黏着性能的影响。研究结果表明:气动升力通过改变列车运行动态响应和轮轨接触特性导致内、外侧轮轨垂向力和纵向蠕滑力重新分配,促使内侧轮更易失去黏着;气动升力和运行速度的增大均会劣化轮轨黏着性能,但曲线半径的增大将显著提升轮轨黏着水平;轨道不平顺削弱了轮轨黏着性能,干态、湿态、油态条件下的轮轨黏着性能依次恶化。列车牵引运行时,干态、湿态、油态条件下的轮轨均能满足牵引力安全限值要求,但制动运行时,湿态和油态条件下的轮轨均不能满足制动力安全限值要求。研究结果可为超高速列车的安全运行与节能设计提供技术支持。

酱卤鸭脖和鸭翅贮藏过程中细菌多样性及关键腐败菌分离研究

为探究不同区域酱卤鸭脖和鸭翅在贮藏过程中的细菌群落变化规律和可能的关键腐败菌,该研究以散装市售酱卤鸭脖和鸭翅为研究对象,采集南昌市4个不同区域样品,在室温下(20℃)贮藏2~6 d。利用Illumina MiSeq测序技术,对24个样品中的细菌16S rDNA进行测序,共产生989839条有效序列,这些序列聚类成458个操作性分类单元。生物信息学分析表明:1)所有样品总体上按地理位置聚集,但不同种类酱卤鸭肉制品和不同贮藏时间的样品相对分散,说明地理位置是影响酱卤鸭肉制品微生物多样性的主要因素,种类和贮藏时间是另外2个影响因素;2)酱卤鸭脖和鸭翅中绿色魏斯氏菌(Weissella viridescens)、小牛葡萄球菌(Staphylococcus vitulinus)和热杀索丝菌(Brochothrix thermosphacta)丰度最高,且是所有样品中的共有微生物,说明它们可能是酱卤鸭脖和鸭翅贮藏过程中的主要腐败微生物。通过纯培养和分子生物学手段从样品中分离并鉴定到一株绿色魏斯氏菌6-M,推测其可能是关键致腐微生物。该研究为了解酱卤鸭脖和鸭翅的微生物腐败机制以及制定有效的防腐策略提供了理论依据和菌种资源。

升力翼列车通过隧道的气动效应研究

升力翼列车是一种通过增加升力翼来提升气动升力的新概念列车,可等效降低自身重力,有效减少轮轨磨损。本研究基于RNG k−ε湍流模型,采用滑移网格模拟方法,研究了不同攻角升力翼列车通过隧道的气动效应,并通过动模型实验数据对数值计算方法的精度进行验证。研究结果表明:升力翼列车进入隧道后列车升力增大,相较于明线,隧道内平均升力增加了33.3%;在进入隧道时攻角由12.5°减小为7.5°,可以较好地减小进入隧道时的升力波动,同时也可减小列车和隧道表面的压力峰值,有利于列车平稳通过隧道。通过对比有、无升力翼的列车可发现,车体前端主要受到升力翼增加车隧阻塞比的影响,而压力上升;车体后端主要受到升力翼尾流的影响,压力降低。本研究结果可为升力翼列车平稳通过隧道提供技术支持。

大展弦比机翼随动加载方法与装置研究

大展弦比机翼载荷标定实验中,随着载荷的增加,机翼会发生弯曲变形,导致加载点的法向载荷方向发生变化,对载荷标定实验的准确性产生影响。为解决此问题,设计了一套大展弦比随动加载装置,该装置通过电缸控制加载点竖直方向的位移,通过位移台控制电缸水平方向的位移,利用联动控制系统使载荷标定实验中施加在机翼翼面的作用力与翼面始终保持垂直,保证机翼所受载荷始终沿法向。开展随动加载与砝码垂向加载对比实验,结果表明:随动加载获得的数据相关系数达到0.999,相较砝码垂向加载获得的数据相关系数0.976更优,验证了随动加载装置的有效性。该装置不仅具有体积较小、操作简便的优点,还为推动大展弦比机翼性能研究提供了有力支撑。

无人机倾斜摄影测量技术在高海拔铁路中的应用

为了解决传统测绘技术手段在高海拔地区铁路建设中工作效率低、测量精度差、安全隐患高等问题。采用垂起固定翼无人机飞行平台搭载倾斜摄影相机,针对高海拔地区地貌特征和勘测要求,建立完整的航飞技术工作流程,利用无人机倾斜摄影测量技术完成铁路现场勘测工作,可有效减少高海拔地区铁路勘测的外业工作量,由检查点数据对比分析结果可以看出,检查点平面中误差为0.06 m,高程中误差为0.12 m,满足地形图和实景三维模型的精度要求。研究结果表明,无人机倾斜摄影测量技术可为生产项目提供靠高清影像、地形图数据和三维模型,无人机具有机动性、灵活性、不受地形和地物的限制等优势,可以提高生产效率,降低作业成本,大幅降低高海拔地区测量作业的安全隐患。

鹤大高速公路护栏改造工程新材料及新工艺应用研究

G11鹤大高速公路运行近20年,现状护栏腐蚀严重。为保证高速公路运营管理的顺畅及用路人的安全,文章着眼该高速公路波形梁钢护栏改造升级,采用更加环保的高性能熔融结合环氧粉末进行防腐涂装。该防腐涂装是一种绿色、成熟、低能耗的新型环保涂装技术,涂装后的钢构件耐腐蚀性能优异,更具有超长耐久性、高性价比和轻维护等特性。

LARGE AERODYNAMIC FORCES ON A SWEEPING WING AT LOW REYNOLDS NUMBER

The aerodynamic forces and flow structure of a model insect wing is studied by solving the Navier-Stokes equations numerically.After an initial start from rest,the wing is made to execute an azimuthal rotation(sweeping)at a large angle of attack and constant angular velocity.The Reynolds number(Re)considered in the present note is 480(Re is based on the mean chord length of the wing and the speed at 60% wing length from the wing root).During the constant-speed sweeping motion,the stall is absent and large and approximately constant lift and drag coefficients can be maintained.The mechanism for the absence of the stall or the maintenance of large aerodynamic force coefficients is as follows.Soon after the initial start,a vortex ring,which consists of the leading-edge vortex(LEV),the starting vortex,and the two wing-tip vortices,is formed in the wake of the wing.During the subsequent motion of the wing,a base-to-tip spanwise flow converts the vorticity in the LEV to the wing tip and the LEV keeps an approximately constant strength.This prevents the LEV from shedding.As a result, the size of the vortex ring increases approximately linearly with time,resulting in an approximately constant time rate of the first moment of vorticity,or approximately constant lift and drag coefficients. The variation of the relative velocity along the wing span causes a pressure gradient along the wing- span.The base-to-tip spanwise flow is mainly maintained by the pressure-gradient force.

Effects of tip perturbation and wing locations on rolling oscillation induced by forebody vortices

The wing rock motion is frequently suffered by a wing-body configuration with low swept wing at high angle of attack. It is found from our experimental study that the tip perturbation and wing longitudinal locations affect significantly the wing rock motion of a wing-body. The natural tip perturbation would make the wing rock motion of a nondeterministic nature and an artificial mini-tip perturbation would make the wing rock motion deterministic. The artificial tip perturbation would, as its circumferential location is varied, generate three different types of motion patterns： （1） limit cycle oscillation, （2） irregular oscillation, （3） equilibrium state with tiny oscillation. The amplitude of rolling oscillation corresponding to the limit cycle oscillatory motion pattern is decreased with the wing location shifting downstream along the body axis.

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