Experiment about Drag Reduction of Bionic Non-smooth Surface in Low Speed Wind Tunnel

The body surface of some organisms has non-smooth structure, which is related to drag reduction in moving fluid. To imitate these structures, models with a non-smooth surface were made. In order to find a relationship between drag reduction and the non-smooth surface, an orthogonal design test was employed in a low speed wind tunnel. Six factors likely to influence drag reduction were considered, and each factor tested at three levels. The six factors were the configuration, diameter/bottom width, height/depth, distribution, the arrangement of the rough structures on the experimental model and the wind speed. It was shown that the non-smooth surface causes drag reduction and the distribution of non-smooth structures on the model, and wind speed, are the predominant factors affecting drag reduction. Using analysis of variance, the optimal combination and levels were obtained, which were a wind speed of 44 m/s, distribution of the non-smooth structure on the tail of the experimental model, the configuration of riblets, diameter/bottom width of i mm, height/depth of 0.5 mm, arranged in a rhombic formation. At the optimal combination mentioned above, the 99% confidence interval for drag reduction was 11.13% to 22.30%.

Performance analysis of 20 Pole 1.5 KW Three Phase Permanent Magnet Synchronous Generator for low Speed Vertical Axis Wind Turbine

This paper gives performance analysis of a three phase Permanent Magnet Synchronous Generator (PMSG) connected to a Vertical Axis Wind Turbine (VAWT). Low speed wind condition (less than 5 m/s) is taken in consideration and the entire simulation is carried in Matlab/Simulink environment. The rated power for the generator is fixed at 1.5 KW and number of pole at 20. It is observed under low wind speed of6 m/s, a turbine having approximately1 mof radius and2.6 mof height develops 150 Nm mechanical torque that can generate power up to 1.5 KW. The generator is designed using modeling tool and is fabricated. The fabricated generator is tested in the laboratory with the simulation result for the error analysis. The range of error is about 5%-27% for the same output power value. The limitations and possible causes for error are presented and discussed.

Piezoelectric Power Harvesting via Acoustic-Pressure Driven by Low-Speed Wind-Force with Resonating-Tube and Wind-Collector

Wind-driven power harvestings attract attentions since their target wind speeds are quite low less than the so-called cut-in wind speed, which is generally recognized as around 3 m/s. The extant power harvestings driven by wind-induced-air-column-resonations (i.e. acoustic-pressures) are still lacking simplicity, scale flexibility and solid strategies for practical applications. Therefore, the piezoelectric power harvesters via acoustic-pressures driven by low-speedwind-forces with resonating-tubes and wind-collectors were invented so as to complement all the lacks. The wind-collector as well as the resonating-tube contributed to upraise the power harvesting density. The champion power harvesting density of 19.5 nW/dm2 could be procured at 2.3 m/s of an artificial wind and the optimal resonating-tube and wind-collector. Power harvesting proofs from the natural wind with low mean speeds down to about 0.6 m/s were successfully obtained. The cut-in wind speed of the prototype piezoelectric power harvester was found to be quite low as about 0.4 m/s, signifying its ubiquity. Finally, a multi-bundle pendant-type piezoelectric power harvester was specifically presented together with professing the solid and multiple strategies for practical applications.

Performance Assessment of Darrieus Turbine with Modified Trailing Edge Airfoil for Low Wind Speeds

Darrieus wind turbines are simple lift based machines with exceptionally high efficiencies in terms of power coefficient compared to similar drag based vertical axis turbines. However, in low Reynolds numbers, a notable performance loss was reported. As a potential solution, truncated NACA 0018 airfoil (NACA 0018TC-39) has been introduced with baseline cavity modification to achieve better start-up characteristics and to enhance the low wind speed performance. The baseline cavity will provide an additional benefit of reverse drag at low TSR which is obligatory for low wind speed start-up. Numerical optimization has been carried out on the conceived airfoil NACA 0018TC-39 to find out the effective truncation percentage in terms of the chord. The numerical study has been extended to compare NACA 0018 and NACA 0018TC-39 airfoil for their aerodynamic performances in terms of lift, drag coefficients and separation characteristics. The NACA 0018TC-39 airfoil was incorporated within a non-swept straight bladed Darrieus turbine miniature to experimentally evaluate the performance in terms of dynamic power coefficient, dynamic torque coefficient and static torque coefficient and compared with conventional NACA 0018 airfoil at six different Reynolds numbers 178917, 193827, 208737, 223646, 238556 and 268376. The experimental contrast implied that NACA 0018TC-39 airfoil turbine yielded almost double power coefficients at low Reynolds number compared to conventional NACA 0018 airfoil without hampering its performance at higher Reynolds number.

CFD-Based Performance Analysis and Experimental Investigation of Design Factors of Vertical Axis Wind Turbines under Low Wind Speed Conditions in Thailand

This paper presents effects of design factors on mechanical performance of Vertical Axis Wind Turbines (VAWTs), and an experimental investigation of optimal VAWT performance under low wind speed conditions in Thailand. Design factors include types of wind turbines, number of blades, types of materials, height-to-radius ratios, and design modifications. Potential VAWT models with different design factors are numerically analyzed within a virtual wind tunnel at various wind speeds by utilizing XflowTM?Computational Fluid Dynamics (CFD) software. The performance curves of each VAWT are obtained as plots of power coefficients against tip speed ratios. It is found that the type of wind turbine, number of blades, and height-to-radius ratio have significant effects on mechanical performance whereas types of materials result in shifts of operating speeds of VAWTs. Accordingly, an optimal VAWT prototype is developed to operate under actual low speed wind conditions. The performance curve from experimental results agrees with the CFD results. The proposed methodology can be used in the computer design of VAWTs to improve mechanical performance before physical fabrication.

Study on Hydraulic Transmission of Offshore Low-speed Wind Energy Generator

For offshore hydraulic drive wind turbines,the problems of unsatisfactory speed control and low efficiency at low wind speeds are targeted.A low-speed high-torque radial piston pump is designed to replace the traditional fixed pump with a particular focus on its low-speed performance.The pump is characterized by small internal leakage at low wind speeds and high volumetric efficiency,which is beneficial to improve the power generation efficiency of the system.A new linear control method based on the PID algorithm and feedforward compensation was proposed to obtain the constant speed output control of variable motor at low wind speed.With the model for wind turbine and fixed pump-variable motor main drive system,the system was simulated and experimentally proved to verify the feasibility and anti-interference performance of the system control method at low wind speeds.A promising outcome was obtained on the response characteristics of system power and efficiency at low wind speeds.This can be a powerful technical support for the normal ustility of hydraulic drive wind turbines.

多频率组合波形阵风场模拟与测量研究

基于数值模拟方法选取设定FL-51风洞阵风发生器的装置参数,如发生器叶片的数量、展长、弦长及间距等。发生器采用液压摆动缸独立驱动形式,可模拟正弦波、三角波及随机波等多种波形的多频率组合运动,同时能够减少安装传动件,并提升发生器性能。通过阵风场校测结果表明:叶片能够实现摆动频率为0 Hz~15 Hz,在校测范围内发生器产生的正弦流场较均匀;在来流风速40 m/s、叶片摆动频率为10 Hz、摆角为15°时,最大阵风幅值为8.5 m/s。地面测试与流场校测结果表明:该文所提出的阵风场模拟技术可以实现低速风洞多频率多波形组合运动,为风洞试验提供复杂的阵风流场。

大型低速风洞全模阵风试验支撑装置研制与验证

为适应日益增多的低速风洞全模阵风试验的需要,发展阵风试验技术,在航空工业气动院FL-10风洞研制了一套双自由度支撑装置,该装置放开了模型升沉和俯仰方向的较大运动自由度,实现了飞机刚体运动模态的模拟。装置主要结构为“钢梁+小滑车”,小滑车可在钢梁上自由滑动,避免了采用滑轨形式导致模型运动过程中出现卡滞现象;采用整流翼型与风洞上下壁板连接,减小了对风洞的破坏,降低了对风洞流场的影响;装置升沉运动高度为3 m,俯仰角范围可达±34°;升沉摩擦因数小,机构变形量小,具备模型防护功能。应用该装置成功开展了民机阵风载荷减缓试验,证明了装置设计合理,可以应用于低速全模阵风试验。

计及高风速和低风速影响的海上风电机组两阶段滚动优化维护策略

针对复杂天气变化影响下海上风电机组维护决策问题,提出了考虑高风速与低风速影响的海上风电机组两阶段滚动优化机会维护策略。首先,提出考虑高风速冲击影响的维护役龄回退模型,量化实际部件退化与及维护成本关系。其次,建立了考虑低风速停机事件维护机会影响的海上风电机组长短期两阶段预防性机会维护模型,滚动更新长期预防性机会维护阈值。最后仿真结果表明,本文所提模型能够有效降低海上风电机组停机成本以及故障损失,提高机组寿命周期内的维护效益。

高速列车弓网受流系统放电实验平台设计

为掌握外环境下高速列车的运行特点,开展弓网电弧变化特性研究,该文设计并研制了高速列车弓网受流系统放电实验平台,其风洞系统由风洞结构、风扇转子系统、风洞控制系统、弓网电弧发生系统、观测系统组成。测试结果表明:低速直流风洞风速可达50 m/s,湍流度低于1%,速度不均匀性小于1%,流场稳定性不超过1%,气流偏角不超过0.5°,满足《低速风洞和高速风洞流场品质要求》(GJB 1179A—2012)中所规定的参数指标。该系统为探究强气流场环境下弓网电弧物理特性的变化规律提供了良好的实验环境,可为高速运行环境下列车弓网电弧研究提供参考数据。

螺旋桨驱动用低速大扭矩电机扁线绕组应用探索

针对低空航空器螺旋桨用低速大扭矩推进电机的使用需求,从绕组形式选取方面着手开展圆线方案与扁线方案综合对比分析。结果显示,扁线方案的散热性能更佳,但在设计加工、电磁性能、整机质量和效率方面不及圆线方案。分析结果可为低速大扭矩电机设计者在绕组选型、极槽组合等方面的选取提供参考。

卷积神经网络STAP低空风切变风速估计

由于机载气象雷达前视阵下存在非均匀性地杂波,导致难以获得足够的独立同分布样本,影响杂波协方差矩阵准确估计,进而影响风速估计。对此,该文提出一种基于卷积神经网络STAP的低空风切变风速估计方法,通过少量样本就能够实现高分辨杂波空时谱估计。首先,基于卷积神经网络模型训练好高分辨杂波空时谱卷积神经网络,接着计算杂波协方差矩阵,进而计算卷积神经网络STAP最优权矢量进行杂波抑制,达到对低空风切变风速精确估计。该文在小样本情况下,将稀疏恢复问题通过卷积神经网络实现,完成对高分辨杂波空时谱有效估计,仿真实验结果表明该方法可以有效估计空时谱,并完成风速估计。

基于D3AR的半球共形阵低空风切变风速估计方法

针对半球共形阵体制下进行低空风切变检测时会受到强地杂波信号的干扰,导致风切变信号难以检测的问题,提出了一种基于空时自回归的直接数据域算法(Space-Time Autoregressive Direct Data Domain,D3AR)的低空风切变风速估计方法。该方法首先将待检测距离单元的数据从空域、时域以及空时域进行信号对消处理;然后将处理后的数据矩阵描述为空时自回归(Autoregression,AR)模型并估计模型参数;再通过构造与杂波子空间正交的空间来实现对杂波的抑制,最后通过提取待检测单元的最大多普勒频率来估计风场速度。根据仿真结果显示,该方法有效地实现了地杂波抑制,并且能够精确估计风速。

基于矩阵信息几何样本筛选下局域联合处理的低空风切变风速估计方法

针对非均匀杂波环境下,机载气象雷达低空风切变风速估计不准确的问题,本文提出了一种基于矩阵信息几何样本筛选下局域联合处理(Joint Domain Localized,JDL)的低空风切变风速估计方法。该方法首先提取雷达回波信号的特征信息建模为矩阵流形,然后通过选取几何度量方式估计几何均值矩阵,利用广义内积法(Generalized Inner Product,GIP)计算几何均值矩阵与各样本间相似度,并从训练样本中筛选样本相似度较高的训练样本估计待检测单元的杂波协方差矩阵,最后利用JDL方法构造降维变换矩阵,对杂波协方差矩阵进行降维处理,并构造降维处理器对非均匀杂波进行抑制,从而实现低空风切变风速估计。

大型低速风洞尾撑机构研制

尾撑机构是为大型低速风洞研制配套的多用途支撑设备,其主要用途包括:支撑战斗机模型完成大迎角状态测力、测压试验任务,迎角连续变化范围-15°~90°,侧滑角连续变化范围±35°;支撑大尺度模型(最大翼展达6 m)完成常规测力、测压、地效试验等任务,满足迎角连续变化范围-10°~75°;支撑特殊模型进行特种试验,包括细长体模型、螺旋桨模型、动力模拟试验模型等。标模试验验证结果表明:该机构刚性强,模型支撑牢固,运行灵活,模型姿态变化定位精确,可满足常规和大量特种模型支撑和姿态变化需要。

4.5 m×3.5 m低速风洞动导数试验技术研究

动导数是飞行器操稳特性分析、控制律设计过程中的关键参数。为满足大型飞行器研制对高精度动导数数据的获取需求,中国航空工业空气动力研究院基于4.5 m×3.5 m低速风洞开发了具备5种振荡试验能力的低速动导数试验系统。该试验系统利用伺服液压摆动马达和伺服液压缸作为运动的驱动元件,经过伺服阀的控制直接产生任意波形的强迫运动,具有运动传递间隙小、运动控制精度高、系统自动化程度高等特点。可实现2.5 m量级模型的动导数试验,风速范围30~60 m/s,迎角范围-36°~36°,侧滑角范围-40°~40°。利用动态标模及某翼身融合布局模型进行了动导数验证试验,结果表明该系统获得的动导数数据规律合理,数据精度在3%以内,可为大型飞行器研制提供高质量的动导数试验数据。

基于高斯混合模型聚类的双馈风电场动态等值建模方法

针对风电场动态运行条件下等值建模精度偏低、聚类依据不足的难题,提出一种基于高斯混合模型聚类思想的风电场等值建模方法。首先,分析单台双馈感应式风力发电机在低电压穿越期间的动态响应特性,根据响应特性的集群特征构建聚类指标。然后,提出基于高斯混合模型动态初步聚类、优化聚类数目的两阶段等值建模方法,推导出赤池信息和贝叶斯信息准则下聚类数目的寻优算法。以典型中等规模风电场为例,在Matlab/Simulink平台进行不同故障穿越条件的仿真测试,结果表明所提风电场等值建模方法聚类有效、精度高。

4 m×3 m风洞大迎角机构上位机软件

针对大迎角机构机械装置、控制硬件的改造升级,基于Labview框架平台设计编写上位机控制软件。优化更新基于TCP/IP协议的Socket通信,增设虚拟支杆设定、模型防碰撞识别等功能。编制的控制软件已成功应用于气动中心4 m×3 m低速风洞大迎角试验。结果表明,该软件有效提升了试验质量效率和设备运行安全。

集中绕组模块组合式定子结构对低速大功率永磁电机性能影响

针对集中绕组模块组合式定子结构对低速大功率直驱永磁同步电机性能的影响进行研究。首先介绍了模块化定子的分块规则和分块数。基于绕组函数法推导了单个定子单元模块在不同拆分方式下的绕组函数和电感表达式。基于有限元仿真先分析了仅绕组分块对电机性能影响;然后分析了冲片和绕组都分块对电机性能影响。通过对比空载和负载性能,总结出各种定子模块化拆分方案的优缺点,为大功率低速直驱永磁同步电机的模块化设计与制造建立了基础。

利用双通道激光雷达验证低信噪比反演算法

针对相干测风激光雷达(LiDAR)在低信噪比(SNR)下反演算法的可靠性和精度难以验证的问题,搭建了一种双通道的脉冲相干测风LiDAR系统,可以同时获取高、低SNR的2组数据,并使用高SNR通道的结果作为真值,比较利用不同的算法在低SNR通道进行矢量风速估计的结果。该系统避免了使用其他观测设备作为真值时难以配准或观测目标不统一的问题。本文研究利用雷达获取的观测结果验证了各个算法的有效性,并在各个算法间进行了横向对比。最终,依据各个算法的性能表现和计算复杂度,指明了各个算法具有优势的使用场景。该结果对于充分利用现有系统、使用新算法提高低SNR下的数据获取效率,或在指定探测指标的前提下降低激光能量等硬件要求、实现系统小型化有一定意义。