Aerodynamics of indirect thrust measurement by the impulse method

The aerodynamic aspects of indirect thrust measurement by the impulse method have been studied both experimentally and numerically. The underlying basic aerodynamic principle is outlined, the phenomena in subsonic, supersonic and arc-heated jets are explored, and factors affecting the accuracy of the method are studied and discussed. Results show that the impulse method is reliable for indirect thrust measurement if certain basic requirements are met, and a simple guideline for its proper application is given.

Aerodynamic measurement of a large aircraft model in hypersonic flow

Accurate aerodynamic measurements in the hypersonic flow of large aircraft models in tunnels have practical significance, but pose a significant challenge. Novel aerodynamic force measurement methods have been proposed,but lack theoretical support. The forms of the force signals techniques for signal processing and calculation of aerodynamics are especially problematic. A theoretical study is conducted to investigate the dynamic properties based on models of the draw-rod system and slender rods. The results indicate that the inertia item can be neglected in the rod governing equation;further, the solutions show that the signals of each rod are a combination of aerodynamic signals（with a constant value） and sine signals, which can be verified by experimental shock tunnel results. Signal processing and aerodynamics calculation techniques are also found to be achievable via the flat part of the signals.

Experimental study on aerodynamic characteristics of a high-speed train on viaducts in turbulent crosswinds

In this study, experiments were carried out to investigate aerodynamic characteristics of a high-speed train on viaducts in turbulent crosswinds using a 1:25 scaled sectional model wind-tunnel testing. Pressure measurements of two typical sections, one train-head section and one train-body section, at the windward and leeward tracks were conducted under the smooth and turbulence flows with wind attack angles between-6° and 6°, and the corresponding aerodynamic force coefficients were also calculated using the integral method. The experimental results indicate that the track position affects the mean aerodynamic characteristics of the vehicle, especially for the train-body section. The fluctuating pressure coefficients at the leeward track are more significantly affected by the bridge interference compared to those at the windward track. The effect of turbulence on the train-head section is less than that on the train-body section. Additionally, the mean aerodynamic force coefficients are almost negatively correlated to wind attack angles, which is more prominent for vehicles at the leeward track. Moreover, the lateral force plays a critical role in determining the corresponding overturning moment, especially on the train-body section.

The Applications of Measurement System for Crankshaft

This paper will introduce two types of multi-parameter co-measuring system and their application in the produc- tion.The first is crankshaft bent deformation measuring machine system.The second is the crankshaft pneumatic-electric measur- ing system.They have been used in final inspection procedure of automation line for crankshaft of automobie engine with good re- sults,the structure principle and soft clash technological process of the measurement system are presented.

Aerodynamics and Flight Dynamics of Free-Falling Ash Seeds

Samaras or winged seeds spread themselves by wind. Ash seed, unlike other samaras, has a high aspect ratio wing which can generate enough lift force to slow down descent by rotating about the vertical axis and spinning around its wing span axis simultaneously. This unique kinematics and inherent fluid mechanism are definitely of great interest. Detailed kinematics of free falling ash seeds were measured using high-speed cameras, then corresponding aerodynamic forces and moments were calculated employing computational fluid dynamics. The results show that both rotating and spinning directions are in the same side and the spinning angular velocity is about 6 times of rotating speed. The terminal descending velocity and cone angles are similar to other samaras. Analysis of the forces and moments shows that the lift is enough to balance the weight and the vertical rotation results from a processional motion of total angular moment because the spin-cycle-averaged aer-odynamic moment is perpendicular to the total angular moment and can only change its direction but maintain its magnitude, which is very similar to a spinning top in processional motion except that the total angular moment of ash seed is not along the spin axis but almost normal to it. The flow structures show that both leading and trailing edge vortices contribute to lift generation and the spanwise spinning results in an augmentation of the lift, implying that ash seeds with high aspect ratio wing may evolve in a different way in utilizing fluid mechanisms to facilitate dispersal.

Automated Kinematics Measurement and Aerodynamics of a Bioinspired Flapping Rotary Wing

A physical model for a micro air vehicle with Flapping Rotary Wings （FRW） is investigated by measuring the wing kine- matics in trim conditions and computing the corresponding aerodynamic force using computational fluid dynamics. In order to capture the motion image and reconstruct the positions and orientations of the wing, the photogrammetric method is adopted and a method for automated recognition of the marked points is developed. The characteristics of the realistic wing kinematics are presented. The results show that the non-dimensional rotating speed is a linear function of non-dimensional flapping frequency regardless of the initial angles of attack. Moreover, the effects of wing kinematics on aerodynamic force production and the underlying mechanism are analyzed. The results show that the wing passive pitching caused by elastic deformation can sig- nificantly enhance lift production. The Strouhal number of the FRW is much higher than that of general flapping wings, indi- cating the stronger unsteadiness of flows in FRW.

Aerodynamic interference effects and mitigation measures on vortex-induced vibrations of two adjacent cable-stayed bridges

By examining the two neighboring Haihe Bridges with semi-and full-closed bridge decks,the aerodynamic interference between the two decks on the vortex-induced vibration(VIV)and the corresponding aerodynamic mitigation measures are investigated via a series of wind tunnel tests with a spring-suspended sectional model aided with computational fluid dynamics(CFD)method.The results show that the VIV responses of both bridges can be significantly affected by the aerodynamic interference and that the extent of the influence varies with the shapes of the windward and leeward decks.The VIV amplitudes of the windward bridge are often fairly close to those of the single bridge.However,those of the leeward bridge are magnified substantially by aerodynamic interference if the same structural and aerodynamic configurations are adopted for the two bridges.Otherwise,the VIV responses are not significantly increased and may even be reduced by the aerodynamic interference if different configurations are employed for the two bridges.Furthermore,an effective combined measure of adding wind barriers and sharpening the wind fairing noses of the two box decks is presented for mitigating both the vertical and torsional VIV responses of the windward and leeward bridges.

Uncertainty analysis of measured geometric variations in turbine blades and impact on aerodynamic performance

Inevitable geometric variations significantly affect the performance of turbines or even that of entire engines;thus,it is necessary to determine their actual characteristics and accurately estimate their impact on performance.In this study,based on 1781 measured profiles of a typical turbine blade,the statistical characteristics of the geometric variations and the uncertainty impact are analyzed,and some commonly used uncertainty modelling methods based on Principal-Component Analysis(PCA)are verified.The geometric variations are found to be evident,asymmetric,and non-uniform,and the non-normality of the random distributions is non-negligible.The performance is notably affected,which is manifested as an overall offset,a notable scattering,and significant deterioration in several extreme cases.Additionally,it is demonstrated that the PCA reconstruction model is effective in characterizing major uncertainty characteristics of the geometric variations and their impact on the performance with almost the first 10 PCA modes.Based on a reasonable profile error and mean geometric deviation,the Gaussian assumption and stochasticprocess-based model are also found to be effective in predicting the mean values and standard deviations of the performance variations.However,they fail to predict the probability of some extreme cases with high loss.Finally,a Chi-square-based correction model is proposed to compensate for this deficiency.The present work can provide a useful reference for uncertainty analysis of the impact of geometric variations,and the corresponding uncertainty design of turbine blades.

Aerodynamic force and moment measurement of 10°half-angle cone in JF12 shock tunnel

An aerodynamic force and moment measurement was conducted in JF12 long-testduration detonation-driven shock tunnel of Institute of Mechanics,Chinese Academy of Sciences.The test duration of JF12 is 100–130 ms.The nominal Mach number is 7.0 and the exit diameter of the contoured nozzle is 2.5 m.The total enthalpy is 2.5 MJ/kg which duplicates the hypersonic flight conditions of Mach number 7.0 at 35 km altitude.The test model is the standard aerodynamic force model of 10° half-angle sharp cone.The length of the test model is 1500 mm and the weight is 57 kg.The aerodynamic forces were measured with a six-component strain balance.The angles of attack were set to be à5°,0°,5°,10° and 14°,respectively.The experimental results show that in the 100–130 ms test duration,the signals of strain balance have 3–4 complete vibration cycles.So,the aerodynamic forces and moments can be obtained directly by averaging the signals of balance without acceleration compensation.The force measurement error of repeatability of JF12 is less than 2%.The aerodynamic force coefficients of JF12 are in good agreement with those of conventional hypersonic wind tunnels.For this test model at Mach number 7.0 and total enthalpy of 2.5 MJ/kg,the real-gas effects on aerodynamic force characteristics are not very evident.

Effects of Measuring Positions on the Measured Aerodynamic Performance of a Centrifugal Compressor

This paper performs a numerical simulation of three-dimensional flow field in a centrifugal compressor with long inlet and outlet pipes using CFX software.By arranging virtual probes at different positions in both inlet and outlet planes,the aerodynamic performance of the centrifugal compressor is measured and compared with each other.Then effects of measuring positions on measurement results are discussed.The results show that it will generate notable measuring errors of the pressure ratio and efficiency if the inlet total pressure is measured using a single-point probe.The inlet total pressure data can be accurate when they are measured using a 3-point rake.The outlet total pressure and total temperature data can not be accurate if they are respectively measured at one circumferential position even using a multi-point rake.Increasing tangential measuring positions at the outlet is effective to improve the test accuracy.When the outlet total pressure and total temperature are respectively measured at 3 tangential positions,the data can be almost accurate.

基于CFD与风洞试验的边主梁涡振气动措施

为能够快捷且经济地完成开口类钝体桥梁断面涡振制振气动措施的选型,以一座边主梁叠合梁斜拉桥为背景,采用“CFD(computation fluid dynamics)数值模拟选型+风洞试验验证”的思路对其涡振制振气动措施选型进行研究.该桥原设计主梁断面在常遇风速下存在显著涡激振动,为完成气动措施的初步选型,采用CFD数值计算对原设计断面的流场进行模拟,通过研究原设计断面的旋涡脱落状态确定主要旋涡抑制对象,进而有针对性地模拟了3种气动措施(下中央稳定板、导流板与风嘴)对主要脱落旋涡的抑制作用,通过将各断面旋涡脱落状态与三分力系数进行对比分析,得到各断面涡振性能的相对优劣关系,并最终选取风嘴与下中央稳定板结合而成的组合气动措施进行风洞验证试验.试验结果表明:该组合气动措施能够有效抑制梁体在各风攻角下的涡激振动,且在+5°风攻角下,通过风洞试验得到的导流板、下中央稳定板、风嘴组合气动3种措施对原设计断面涡振振幅的减小作用依此递增,分别为2.7%、27.7%与87.4%,制振能力高低关系与数值模拟结果相一致;本次数值模拟结果符合预期要求,未来可针对不同类型桥梁断面进一步扩展数值模拟与风洞试验结果对比的数据集,以期更为准确、快捷地完成气动措施的选型.

带挑臂PK箱梁涡振性能及优化措施机理研究

为研究带挑臂PK箱梁的涡振性能及气动优化措施,通过节段模型风洞试验研究了PK箱梁在0°、±3°风攻角下的涡振性能,并测试了人行道高度、封闭挑臂底部、栏杆透风率改变、不同倾角抑流板等气动措施对PK箱梁气动稳定性的影响,研究表明:主梁在0°、+3°风攻角下出现强烈的竖向涡激共振,并出现多个竖向涡振区间,同时在高风速下主梁出现了明显的扭转涡振;抬高人行道高度能降低各攻角下主梁的竖弯涡振响应,同时高风速下的扭转涡振得到极大程度的改善;通过封闭栏杆来改变栏杆透风率的研究发现,竖向间隔封闭人行道外侧护栏能破坏涡激气动力在展向的相关性,将主梁涡振峰值响应降低至规范限值的55.8%;0.25 m宽抑流板能有效改善主梁气动稳定性,抑流板倾角变化在20°~75°之间时,其均能完全抑制主梁涡振响应;气流在迎风侧人行道护栏处发生分离,在上表面卷起形成规律的大尺度旋涡,从而造成主梁剧烈的涡激振动,抑流板明显破坏了挑臂附近旋涡的形成,无法向下游发展形成规律的大尺度旋涡,从而能有效抑制主梁涡振。

路堤-桥梁过渡段车辆气动力风洞试验研究

为了探究路堤-桥梁过渡段处车辆的气动力,建立1:50的大比例尺路堤-桥梁过渡段和车辆试验模型,在桥梁和路堤段分别布置两种风屏障,并在车辆模型表面布置多个测压点,以研究不同防风措施下处于不同风向角的路桥过渡段车辆气动力。试验结果表明:与无防风措施相比,布置桥梁风屏障后最不利风向角会从-15°变为0°,此风向下过渡段处车辆的三分力最大;再进一步布置路堤风屏障后最不利风向角不变,但大幅度减小了0°风向角下车辆的侧力系数和力矩系数;布置路堤风屏障能有效减小车辆所受三分力;不同风向角下改变陆地风屏障参数产生的影响不同,针对路堤-桥梁过渡段布置防风措施时,应充分考虑其来流方向,以达到最优效果。

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。

大跨PK断面钢箱梁斜拉桥涡振性能及优化措施研究

红莲大桥主桥为主跨580 m的双塔斜拉桥,中跨主梁采用PK断面钢箱梁,该类主梁断面易发生涡振,需对其涡振性能及抑振措施进行研究。基于该桥有限元动力特性分析结果,制作PK断面钢箱梁1∶60缩尺比节段模型进行测振风洞试验,研究桥梁原始设计断面主梁的涡振性能,讨论增加结构阻尼比(增加至0.010和0.027)措施的涡振抑振效果,并对增设稳定板、水平导流板、部分封闭桥面栏杆等不同气动优化措施及组合对主梁涡振性能的影响进行分析。结果表明:原始设计PK断面钢箱梁的涡振振幅明显超过规范限值;增大结构阻尼比虽然可以有效抑制涡振响应,但阻尼比增加至0.027时竖弯涡振振幅仍然显著;在桥面检修栏杆上缘外挑1.6 m宽水平导流板可将涡振振幅降低到可忽略的水平;采用在检修栏杆上缘外挑1.1 m宽水平导流板、优化桥面燃气管道位置、调整防撞护栏下部封闭高度为0.42 m,或移除检修道栏杆底座、错列布置封闭检修道栏杆和防撞护栏等组合措施,虽不足以完全抑制涡振的发生,但可将涡振振幅控制至明显小于规范限值。

大跨度公铁两用双层钢桁桥涡激振动控制研究

桥梁的涡激振动主要受到主梁断面的气动外形、结构动力特性与来流特性的影响,而大跨桥梁是典型的风致敏感结构,所以在大跨度桥梁的设计中应当引起重视。以某大跨度公铁两用双层板桁组合桁架桥为背景,在XNJD-1回流串联风洞中进行了风洞试验,研究了该主梁的涡激振动现象。通过计算流体动力学(computational fluid dynamics, CFD)数值模拟分析了其主梁断面的涡激振动机理,并且将展向周期摄动法应用于钢桁梁的涡激振动控制,采取了一系列气动控制措施来抑制主梁的涡激振动,其中L型分流板与波浪形风嘴完全抑制了主梁的涡激振动。还通过风洞试验研究了波浪形风嘴的几何参数对抑振效果的影响,试验结果表明,波浪形风嘴的抑振效果对幅值变化比较敏感,增大幅值可以有效抑制主梁的涡激振动。

双幅钢箱梁竖弯涡振气动力演变特性

双幅钢箱梁桥是工程实践中一种常用的大跨度连续梁桥型式,但并列双箱复杂的旋涡脱落和交互作用可能引发显著的涡激振动现象,影响结构的疲劳性能和行车舒适性。本文以某六边形双幅钢箱连续梁桥为工程背景,对大比例节段模型开展了测振、测压风洞试验,对比了双幅钢箱梁在不同间距下竖弯涡振全过程(涡振前、上升区、振幅极值点、下降区及涡振结束)的分布气动力演变特点,提出了有效控制双幅钢箱梁桥涡振的气动措施。研究表明,双幅钢箱梁桥涡振锁定区间长、振幅大,+3°为最不利攻角,涡激力的倍频效应与间距和双幅箱梁涡振的振幅均有关。在小间距及低风速时,上、下游梁背风侧的分布气动力对涡激振动起到增强作用;在大间距或较小间距且高风速时,开槽附近上表面和下游梁斜腹板位置的分布气动力对涡激力起主要增强作用,也是双幅钢箱梁产生大幅涡激振动的诱因。提出了槽间裙板与两端风嘴组合的综合气动控制措施,通过切断槽间涡的传播途径从而降低桥面处分布气动力对涡激力的贡献,该措施可有效减弱双幅钢箱梁桥的竖弯涡振。

导流板倾斜角度对Π型叠合梁涡振性能的影响研究

型叠合梁被广泛应用于大跨度斜拉桥建设中,但该类断面较差的涡振性能严重影响了其应用前景。以某主跨为530 m的Π型叠合梁双塔斜拉桥为工程背景,通过风洞试验对Π型主梁的涡振性能及气动优化措施进行研究。试验结果表明,原设计Π型断面在各风攻角下均存在显著涡激振动,通过在断面工字梁下缘处设置导流板与下中央稳定板可降低梁体的涡振振幅,且导流板倾斜角度的改变对该组合气动措施的制振效果影响显著,其中30°倾角导流板组合气动措施的制振效果最优,可在规范要求阻尼比1.0%下显著抑制甚至消除梁体的涡激振动。通过CFD数值模拟对该组合气动措施的制振机理与导流板倾斜角度的变化对组合气动措施制振性能的影响机理进行了研究,计算结果表明,30°倾角导流板组合气动措施中的迎风侧导流板可显著改善上游断面的气体绕流状态,并配合下中央稳定板削弱Π型断面尾流的卡门涡脱,从而起到抑制主梁涡振的效果,改变导流板倾斜角度会在影响导流板自身附近旋涡生成的同时,影响下中央稳定板对断面下侧旋涡脱落状态的改善作用,从而对该组合气动措施的制振性能产生显著影响。

超音速气动喷雾技术噪声特性及致噪机理研究

超音速气动喷雾降尘是一种新型的微米级雾滴高效捕尘技术,在呼吸性粉尘治理方面效果良好,但造成的严重噪声污染不可忽视。为探究其噪声特性及致噪机理,研究采用试验的方法,利用YSD130噪声分析仪对超音速同轴雾化降尘装置噪声展开测定,通过对比不同工况下声源处气流噪声与喷雾噪声,分析其在不同压力、水流量下的频谱特性及变化规律。研究显示:超音速动力喷雾噪声以高频噪声为主,随着频率的增加,声压级增加,其噪声均值为110.1 dB,会造成人的听力系统受损。不完全的雾化会导致低频段(<500 Hz)的声压级增加,长期接触易引发神经衰弱、失眠、头疼等症状;更高效的雾化会导致中高频段(≥500 Hz)的声压级增加,长期暴露于该环境易引发声带疲劳、声带炎症等症状。在相同水流量下,随着压力的增大,超音速气动喷雾噪声的声压级呈先增大后减小的趋势。在相同压力下,随着水流量的增加,不同频段的声压级呈先增大后减小的趋势。气流能量降低和层间相对速度下降是噪声强度降低的主要原因。水流量为60 mL/min,气动压力为0.4 MPa时,噪声各项参数最大。研究结果丰富了气动喷雾噪声理论,可为超音速气动喷雾装置结构优化、噪声防治技术装备的研发提供理论支持。

风荷载下的树木动态行为参数测量方法综述

树木风害机理、风害损失及防治技术的研究是当前的研究热点,其共同基础是了解树木的空气动力学特性。对树木动态行为参数的测量是研究树木空气动力学的基础,对定量化研究树木风载及其安全性评估具有重要意义。在调研国内外相关文献的基础上对树木动态行为参数的测量方法进行了综述。首先,对树干、树枝和树叶的动态行为参数进行了总结;其次,从接触式和非接触式两方面对树木动态行为参数的测量方法进行归纳,对每种方法的适用范围及优缺点进行阐述分析;最后,讨论了目前测量方法的不足,对未来的测量方法进行展望。