Research on stability of laminated composite plate under nonlinear aerodynamic load

In this paper,we propose an finite element approach based on classical plate theory to investigate the dynamic stability of a layered composite plate subject to nonlinear aerodynamic load.This study considers the influence of temperature,nonlinear geometry,and nonlinear aerodynamic load on composite plate structures simultaneously.Specifically,the present work conduct comparison the results of the critical pressure value between the nonlinear aerodynamic load and the linear aerodynamic load,thereby pointing out some necessary cases which must consider the nonlinearity of aerodynamic load for calculating the aerospace structures.We determine the critical pressure value and vibrational amplitude response of the plate by means of calculation.The outcomes of our calculations can be useful in designing and repairing body shells and wings of aircraft equipment.

Influences of aerodynamic loads on hunting stability of high-speed railway vehicles and parameter studies

The influences of steady aerodynamic loads on hunting stability of high-speed railway vehicles were investigated in this study.A mechanism is suggested to explain the change of hunting behavior due to actions of aerodynamic loads：the aerodynamic loads can change the position of vehicle system（consequently the contact relations）,the wheel/rail normal contact forces,the gravitational restoring forces/moments and the creep forces/moments.A mathematical model for hunting stability incorporating such influences was developed.A computer program capable of incorporating the effects of aerodynamic loads based on the model was written,and the critical speeds were calculated using this program.The dependences of linear and nonlinear critical speeds on suspension parameters considering aerodynamic loads were analyzed by using the orthogonal test method,the results were also compared with the situations without aerodynamic loads.It is shown that the most dominant factors a ff ecting linear and nonlinear critical speeds are different whether the aerodynamic loads considered or not.The damping of yaw damper is the most dominant influencing factor for linear critical speeds,while the damping of lateral damper is most dominant for nonlinear ones.When the influences of aerodynamic loads are considered,the linear critical speeds decrease with the rise of cross wind velocity,whereas it is not the case for the nonlinear critical speeds.The variation trends of critical speeds with suspension parameters can be significantly changed by aerodynamic loads.Combined actions of aerodynamic loads and suspension parameters also a ff ect the critical speeds.The effects of such joint action are more obvious for nonlinear critical speeds.

Superposability of unsteady aerodynamic loads on bridge deck sections

The 2-dimensional unsteady aerodynamic forces,in the context of both a thin airfoil where theory of potential flow is always applicable and a bluff bridge-deck section where separated flow is typically induced,are investigated from a point of view of whether or not they conform to the principle of linear superposition in situations of various structural motions and wind gusts.It is shown that some basic preconditions that lead to the linear superposability of the unsteady aerodynamic forces in cases of thin airfoil sections are no longer valid for a bluff section.Theoretical models of bridge aerodynamics such as the one related to flutter-buffeting analysis and those concerning aerodynamic admittance(AA)functions,however,necessitate implicitly this superposability.The contradiction revealed in this work may throw light on the perplexing problem of AA functions pertaining to the description of buffeting loads of bridge decks.Some existing theoretical AA models derived from flutter derivatives according to interrelations valid only for thin airfoil theories,which have been employed rather extensively in bridge aerodynamics,are demonstrated to be illogical.Finally,with full understanding of the preconditions of the applicability of linear superposability of the unsteady aerodynamic forces,suggestions in regard to experiment-based AA functions are presented.

Characteristic Aerodynamic Loads and Load Effects on the Dynamics of a Floating Vertical Axis Wind Turbine

The development of offshore wind farms in deep water favors floating wind turbine designs, but floating horizontal axis wind turbines are facing the challenge of high cost of energy (CoE). The development of innovative designs to reduce the CoE is thus desirable, such as floating vertical axis wind turbines (VAWTs). This study demonstrates the characteristics of aerodynamic loads and load effects of a two-bladed floating VAWT supported by a semi-submersible platform. Fully coupled simulations are performed using the time-domain aero-hydro-servo-elastic code SIMO-RIFLEX-AC. It is found that thrust, lateral force, and aerodynamic torque vary considerably and periodically with the rotor azimuth angle. However, the variation in the generator torque can be alleviated to some extent by the control strategy applied. Moreover, the variations of platform motions and tensions in the mooring lines are strongly influenced by turbulent winds, whereas those of tower-base bending moments are not. The tower-base bending moments exhibit notable two-per-revolution (2P) response characteristics. © 2017 Tianjin University and Springer-Verlag GmbH Germany

A computational platform for considering the effects of aerodynamic and seismic load combination for utility scale horizontal axis wind turbines

The wide deployment of wind turbines in locations with high seismic hazard has led engineers to take into account a more comprehensive seismic design of such structures. Turbine specific guidelines usually use simplified methods and consider many assumptions to combine seismic demand with the other operational loads effecting the design of these structures. As the turbines increase in size and capacity, the interaction between seismic loads and aerodynamic loads becomes even more important. In response to the need for a computational tool that can perform coupled simulations of wind and seismic loads, a seismic module is developed for the FAST code and described in this research. This platform allows engineers working in this industry to directly consider interaction between seismic and other environmental loads for turbines. This paper details the practical application and theory of this platform and provides examples for the use of different capabilities. The platform is then used to show the suitable earthquake and operational load combination with the implicit consideration of aerodynamic damping by estimating appropriate load factors.

Modelling dynamic pantograph loads with combined numerical analysis

Appropriate interaction between pantograph and catenary is imperative for smooth operation of electric trains.Changing heights of overhead lines to accommodate level crossings,overbridges,and tunnels pose significant challenges in maintaining consistent current collection performance as the pantograph aerodynamic profile,and thus aerodynamic load changes significantly with operational height.This research aims to analyse the global flow characteristics and aerodynamic forces acting on individual components of an HSX pantograph operating in different configurations and orientations,such that the results can be combined with multibody simulations to obtain accurate dynamic insight into contact forces.Specifically,computational fluid dynamics simulations are used to investigate the pantograph component loads in a representative setting,such as that of the recessed cavity on a Class 800 train.From an aerodynamic perspective,this study indicates that the total drag force acting on non-fixed components of the pantograph is larger for the knuckle-leading orientation rather than the knuckle-trailing,although the difference between the two is found to reduce with increasing pantograph extension.Combining the aerodynamic loads acting on individual components with multibody tools allows for realistic dynamic insight into the pantograph behaviour.The results obtained show how considering aerodynamic forces enhance the realism of the models,leading to behaviour of the pantograph-catenary contact forces closely matching that seen in experimental tests.

UNSTEADY TRANSONIC AERODYNAMIC LOADINGS ON THE AIRFOIL CAUSED BY HEAVING, PITCHING OSCILLATIONS AND CONTROL SURFACE

An implicit upwind finite volume solver for the Euler equations using the improved flux - splitting method is established and used to calculate the transonic flow past the airfoils with heaving, pitching oscillations and the control surface. Results are given for the NACA64A - 10 airfoil which is in harmonic heaving and pitching oscillation and with the control surface in the transonic flow field. Some computational results are compared with the experiment data and the good agreements are shown in the paper.

APPLICATION OF NONLINEAR PID CONTROLLER IN AERODYNAMICS LOADING SYSTEM

The design idea of tracking-differentiator and the nonlinear PID controllerare introduced, the applicable algorithm and its real result for distributed aerodynamicsloading control system are discussed, and the construction of the test & contro1 system arealso presented. The application shows that the nonlinear PID algorithm has the advan-tages of high reliability, short run time and strong stability.

Nonlinear uncertainty impact of geometric variations on aerodynamic performance of low-pressure turbine blades with ultra-high loading under extreme operational conditions

Uncertainty impact of random geometric variations on the aerodynamic performance of low-pressure turbine blades is considerable,which is further amplified by the current ultra-high-lift design trend for weight reduction.Therefore,this uncertainty impact on ultra-highly loaded blades under extreme operational conditions near the margins with potential large-scale open separation is focused on in this study.It is demonstrated that this impact is significant,unfavourable,and nonlinear,which is clearly severer under extreme conditions.In addition to the overall attenuation and notable scattering of specific performance,the operational margins with open separation are also notably scattered with great risk of significant reduction.This scattering and nonlinearity are dominated by the variations in leading-edge thickness.The thinning of leading edge triggers local transition,enhancing downstream friction and reducing resistance to open separation,which is further exacerbated by operational deterioration.However,the opposite thickening yields less benefit,implying nonlinearity.This unfavourable impact highlights the need for robust aerodynamic design,where both a safer operational condition and a more robust blade are indispensable,i.e.,a compromise among performance,weight,and robustness.Besides the necessary limitation of loading levels,a mid-loaded design is recommended to reduce adverse pressure gradients in both the leading edge and rear region of the suction side,which helps to decrease the susceptibility of the transition and open separation to random perturbations.Similar improvements can also be achieved by appropriately thickening the leading edge.

Prediction of Aerodynamic Interactions of Helicopter Rotor on its Fuselage

An iterative and full-coupled rotor/fuselage aerodynamic interaction analytical method is developed based upon the rotor free-wake model and the 3-D fuselage panel model. A close vortex/ surface interaction model using the Analytical/Numerical Matching (ANM) was adopted in the method in order to simulate effectively the unsteady close interaction between the rotor tip-vortex and fuselage surface. By the analytical method, the unsteady and steady pressure distribution on the fuselage surface, and the unsteady lift and pitching moment of the fuselage in a rotor interaction environment were calculated for different advance ratios. It is shown that the unsteady aerodynamic loads of the fuselage due to the rotor interaction have the same periodic characteristics as the rotor. The comparisons between the present close vortex/surface interaction model and a previous model, which simply excludes vortex filaments inside the fuselage, were also made and the advantages of the former over the latter were demonstrated in improving unsteady close interaction calculations.

Experimental investigation on tip vortices and aerodynamics of a wing with ground effect

The tip vortices and aerodynamics of a NACA0012 wing in the vicinity of the ground were studied in a wind tunnel.The wing tip vortex structures and lift/drag forces were measured by a seven-hole probe and a force balance,respectively.The evolution of the flow structures and aerodynamics with a ground height were analyzed.The vorticity of tip vortices was found to reduce with the decreasing of the ground height,and the position of vortex-core moved gradually to the outboard of the wing tip.Therefore,the down-wash flow induced by the tip vortices was weakened. However,vortex breakdown occurred as the wing lowered to the ground.From the experimental results of aerodynamics,the maximum lift-to-drag ratio was observed when the angle of attack was 2.5°and the ground clearance was 0.2.

Lateral aerodynamic performance and speed limits of double-deck container vehicles with different structures

Based on 3D, steady N-S equations and k-e turbulence model, Fluent was employed to do numerical simulation for lateral aerodynamic performance of 6-axis X2K double-deck container trains with two different loading forms, and speed limits of the freight trains were studied. The result indicates that under wind environment： 1） As for vehicles without and with cross-loaded structure, aero-pressure on the former is bigger, but air velocity around the latter is larger; 2） When sideslip angle θ=0°, the airflow is symmetry about train vertical axis; when θ〉0°, the airflow is detached at the top of vehicles, and the air velocity increases above the separated line but decreases below it; 3） With θ increasing, the lateral force on the mid vehicle firstly increases but decreases as θ=75°; 4） When the 6-axis X2K fiat car loads empty boxes of a 40 ft and a 48 ft at 120 km/h, the overturning wind speed is 25.19 m/s, and the train should be stopped under the 12th grade wind speed.

EXPERIMENTAL INVESTIGATION OF AERODYNAMICINTERACTION EFFECT OF ROTOR WAKE ONFUSELAGE OF HELICOPTER

The interaction effect of rotor wake on fuselage of helicopter was investigated with experimental method. The results from experiment have proved that for the drag of fuselage the effect of rotor airflow is closely in connection with both the flight speed and the collective pitch of blades, while for the thrust and pitch moment of fuselage the collective pitch angle of blades plays more important role. A simple and effective computing method about aerodynamic interaction can be derived from the measured data. In order to implement the experiment, a fuselage model, a special sensor, the measurement and data acquisition and processing system were designed and manufactured according to the special requirements of this research project, thereby a good base was built up for carrying out experiments successfully with high quality.

Aerodynamic drag analysis of double-deck container vehicles with different structures

To study the aerodynamic performance of a new six-axis X2K double-deck container vehicle, numerical simulation was done based on three-dimensional, steady Navier-Stokes equations and k-e turbulence model. The results show that the pressure on the front surface of vehicle is positive, and others are negative. The maximum negative one appears as a ＂gate＂ shape on front surfaces. The pressure on vehicle increases with train speed, and pressure on vehicles with cross-loaded structure is smaller than that without it. The airflow around vehicles is symmetrical about train vertical axis, and the flow velocity decreases gradually along the axis to ground. Airflow around vehicles with cross-loaded structure is weaker than that without the structure. The aerodynamic drag increases linearly with the train speed, and it is minimum for the mid-vehicle. The linear coefficient for mid-vehicle without cross-loaded structure is 29.75, nearly one time larger than that with the structure valued as 15.425. So, from the view-point of aerodynamic drag, the cross-loaded structure is more reasonable for the six-axis X2K double-deck container vehicle.

浮式风力机若干特征动力学问题综述

总结浮式风力机类型及其对应的特征动力学问题,针对浮式风力机气动荷载、水动荷载的计算方法以及结构动力学、控制动力学典型问题进行论述。讨论了气动—水动—结构—伺服耦合分析的难点,重点分析了二阶波浪力、畸形波等非线性波浪荷载、流荷载及涡激运动对浮式风力机特征动力响应的影响。阐述了浮式风力机动力学研究的试验方法、数值仿真方法、样机测试方法,并对模型试验技术的相似理论、气动模型的实现和难点以及数值仿真的频域方法、时域方法和分析工具进行了归纳对比。研究表明:浮式风力机多场、多体耦合动力分析机理及相关技术仍不成熟,气动荷载、高阶非线性波浪荷载耦合模型的建立是动力学问题研究的重点,数值仿真及模型试验是浮式风力机动力响应研究的主要方法,样机测试技术的积累将促进设计标准的完善及浮式风电的产业化发展。

考虑风速纵、横分量的列车气动载荷变化特性

为探索侧向环境风作用下列车气动载荷变化特性,对任意风向角下随车移动点处的风速纵、横分量进行建模,研究考虑风速纵、横分量的列车气动载荷计算方法,并分析在列车速度200~400 km/h、平均风速10~35 m/s及风向角30°~150°时的列车气动载荷特性.研究发现:在不同风向角下,考虑风速横向分量后,高速列车气动载荷波动变大,作用于列车上的瞬时气动载荷极值增大;风速横向分量主要影响列车气动载荷的标准差,且影响程度与风向角有关;随着风向角接近临界风向角,风速横向分量对列车气动载荷标准差的影响逐渐变小,随着风向角远离临界风向角,风速横向分量对列车气动载荷标准差的影响逐渐变大;列车气动载荷的标准差/均值主要与侧偏角有关,且在风向角为30°及150°时较大,其次是风向角60°和120°,而在风向角90°时则较小.

高速列车突入复线隧道的横风效应分析

横风作用下运行环境不同导致高速列车气动特性发生突变,严重影响列车运行安全和乘客的舒适性。基于高速列车流场的可压缩、非定常特性,建立隧道-列车-横风三维数值模型,采用SST k-ω湍流模型进行求解,通过与动模型试验对比,验证了数值模拟的准确性,进一步分析横风对列车周围流场与表面压力分布的影响,得到了横风作用下列车气动荷载变化规律。研究结果表明:列车周围流场分布受横风影响显著,隧道外流场向列车背风侧偏移,并形成起始于隧道入口处的纵向涡旋,而隧道内列车背风侧涡旋消失,迎风侧形成延伸至入口处的垂向涡旋,并在列车驶入过程中隧道内涡旋结构逐渐消失。在列车驶入隧道前列车迎风面气动压力以正值为主,背风面气动压力以负值为主。当列车驶入隧道时列车表面压力发生剧烈变化,气动压力波动程度随列车驶入而明显减弱。气动荷载变化规律与风环境密切相关,无风时尾车横向力和升力变化幅值最大,而横风下头车横向力和升力变化幅值最大。此外,列车气动性能与编组位置密切相关,横风下头车横向力变化幅值分别是中车、尾车的4.8倍和15.4倍,头车升力变化幅值分别为中车、尾车的1.1倍和1.2倍,头车发生行车安全事故风险最高。研究成果可为类似情形下高速列车运行安全性评价和高铁隧道选线提供参考。

参数耦合下风力发电机叶片机械颤振检测研究

受气候、风速等因素影响,会使风力发电机叶片的运行条件发生较大变化,增加了颤振检测的难度。为此,该文提出参数耦合下风力发电机叶片机械颤振检测方法。建立风力发电机叶片结构模型,推导结构动力学方程,并利用优化后的参数耦合算法对其求解,获取非稳态气动载荷,通过动力学模型反馈得到叶片的结构响应和振动情况;构建非稳态气动降阶模型,采用能量法分析叶片的结构响应与气动载荷的时域或频域,计算能量交换角度,确定叶片的颤振程度,实现颤振检测。实验结果表明,该方法气动阻尼系数计算结果准确、检测正确率高、计算时间短。

风向角对高速列车驶出隧道过程中气动效应的影响

为研究风向角对驶出隧道过程中高速列车气动效应的影响,以某型高速动车组列车为研究对象,采用数值模拟方法对隧道内气动压力、列车风风速、流场分布及列车气动荷载进行分析。通过与动模型试验结果进出对比,验证数值模拟方法的准确性。研究结果表明:隧道壁面气动压力峰值及变化幅值最大值出现在隧道内部,且出现位置到隧道出口距离与风向角有关;背风侧气动压力受风向角影响更大,气动压力变化幅值随风向角增大呈现先减小后增大再减小的趋势;出口处列车风风速随风向角增大基本呈现先增大后减小的趋势,30°风向角时列车风风速最大,但迎、背风侧列车风风速峰值出现时刻不同;随着风向角增大,流场分布不对称性增强,列车绕流特性由流线型绕流逐渐过渡到钝体绕流,流动分离点到头车鼻尖的距离呈现先增大后减小最后再增大的变化规律,隧道内流动结构愈加复杂;气动横向力、升力变化幅值随风向角增加呈现先增后减趋势,头车横向力系数最大变化幅值分别是中车、尾车的2.4倍和2.6倍,升力系数最大变化幅值分别是中车、尾车的1.1倍和1.5倍,故保证头车安全是控制整车运行安全的关键;侧风下高速列车驶出隧道情形下的最不利风向角为30°,此时头车发生列车事故风险最高。

基于飞行实测载荷的副翼操纵导数识别

某型飞机横向操纵时副翼和扰流板会耦合偏转实现飞机的滚转运动,现有气动力参数辨识方法无法单独识别出副翼和扰流板的操纵导数。基于飞机控制律设计逻辑和滚转运动时结构的受载特点,提出一种基于飞行实测载荷的副翼操纵导数识别方法。通过实测机动飞行中机翼各测载剖面的结构载荷并结合剖面外结构质量与加速度分布,提出了机动飞行中机翼气动载荷的测量方法;结合飞机横向操纵瞬时滚转力矩平衡方程和操纵面偏转逻辑,推导了滚转改出时副翼操纵导数识别过程,提出了基于机翼实测载荷的副翼操纵导数识别方法;基于前述方法开展了副翼操纵导数识别,并分析了不同马赫数对副翼操纵导数的影响。研究表明,基于飞行实测载荷能够进行副翼操纵导数识别,而且同一马赫数下副翼操纵导数识别结果集中度较好,随着马赫数的增加,副翼操纵效能将会降低。飞行载荷实测结果可用于气动参数辨识工作中。