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气动导数

气动导数的相关文献在1989年到2022年内共计114篇,主要集中在公路运输、航空、建筑科学 等领域,其中期刊论文77篇、会议论文29篇、专利文献60145篇;相关期刊42种,包括同济大学学报(自然科学版)、振动工程学报、航空计算技术等; 相关会议21种,包括第十七届全国结构风工程学术会议暨第三届全国风工程研究生论坛、第十四届全国空气弹性学术交流会、第十一届全国随机振动理论与应用学术会议等;气动导数的相关文献由220位作者贡献,包括顾明、陈政清、项海帆等。

气动导数—发文量

期刊论文>

论文:77 占比:0.13%

会议论文>

论文:29 占比:0.05%

专利文献>

论文:60145 占比:99.82%

总计:60251篇

气动导数—发文趋势图

气动导数

-研究学者

  • 顾明
  • 陈政清
  • 项海帆
  • 秦仙蓉
  • 王雄江
  • 周志勇
  • 朱乐东
  • 郭震山
  • 张若雪
  • 陈艾荣
  • 期刊论文
  • 会议论文
  • 专利文献

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    • 张建刚; 何康乐; 金鑫
    • 摘要: 提出了一种在方案阶段能快速准确预估飞机设计机动载荷的简捷计算方法.通过静气弹理论计算飞机的气动导数,以气动导数、操纵特性和质量特性为输入对飞机进行了机动模拟,得到各运动参数的时间历程,最后用涡格法计算出部件的分布载荷.将本文的计算结果与后续的传统方法计算结果进行比较,结果表明该方法是准确可靠的,能满足方案阶段飞机设计的载荷需求.该方法在方案阶段能有效克服传统方法需要大量的风洞试验得来的气动特性数据和压力分布数据的不足.本文的方法只需要较少的输入参数就可以进行,可在型号研制中节省时间,加快研制进度.
    • 张庆; 叶正寅
    • 摘要: 传统的一阶线性叠加的气动力模型不再适用于现代高机动性飞行器的非定常气动力建模,为了考察更高阶的气动力模型对非定常迟滞效应模拟的适用程度,本文采用自主发展的求解器,分别计算了NACA0012翼型在跨声速来流条件下做单自由度强迫沉浮、俯仰以及沉浮/俯仰两自由度耦合运动的非定常气动力的变化规律.然后在Etkin气动力模型的基础上,探讨了不同类型的高阶的气动导数在非定常气动力建模中的作用.研究结果表明:将Etkin气动力模型中升力和俯仰力矩对迎角的导数项由一阶拓展至二阶就可以较为精确地重构出翼型在强迫运动各阶段的非定常升力和俯仰力矩.
    • 刘令; 贾惠博; 宋韬; 吴立强; 石桦; 石蕾
    • 摘要: 导数作为高等数学中的核心概念之一具有广泛的应用性,在运用建筑学知识对建筑进行设计方面中,是决定建筑是否美观且实用的关键.本文通过浅析导数思想在建筑学方面的应用,阐明了导数思想在解决建筑学专业问题时的重要作用,建筑类院校也应加大对导数知识的教学力度,达到培养复合型高级建筑人才的目的.
    • 周奇; 朱乐东; 周成; 郭震山
    • 摘要: 自由振动试验法(FreeV法)用于平行分离双幅桥气动导数识别时,由于人工初始激励不同,节段模型产生的气动干扰不同,进而导致气动导数识别结果规律性差,识别数据离散性大.为此,提出了混合强迫振动试验法(MFV法),并对比分析了MFV法和FreeV法识别出的气动导数,以及基于MFV法和FreeV法的二维颤振分析结果与节段模型测试结果.研究结果表明:无论是上游桥还是下游桥,MFV法识别的气动导数均离散性较小,随折算风速的变化规律明确;而FreeV法识别的气动导数离散性较大,随折算风速的变化规律较差,尤其是受气动干扰效应影响较大的下游桥;基于MFV法预测的颤振临界风速与节段模型测试结果较为接近,而基于FreeV法预测的颤振临界风速与节段模型测试结果的偏差较大,尤其是下游桥,偏差更为显著;相比于FreeV法,MFV法能更为准确地模拟平行分离双幅桥的气动干扰效应,其颤振预测结果更准确.%When identifying the aerodynamic derivatives of parallel separated double-deck bridges using free-vibration testing method (FreeV method),the different initial manual excitations produce different aerodynamic interference between two sectional models,which cause the identification results are always significant discrete and irregular.Therefore,the mixed forced-vibration testing method (MFV method) is proposed in this article.The aerodynamic derivatives identified by FreeV method and MFV method are compared and analysed.The flutter analysis results based on the FreeV and MFV method are also in contrast with the test results.Research results show that,no matter the windward deck or the leeward deck,the aerodynamic derivatives identified by MFV method put up to small dispersions and good laws of variation with reduced wind speed.However,the aerodynamic derivatives obtained by FreeV method show larger dispersions and worse variation laws,especially those of the leeward deck which suffered from aerodynamic interference seriously.Furthermore,the flutter critical wind speeds calculated based on the MFV method are rather close to the test results,whereas those based on the FreeV method have a big discrepancies with the test results,especially those of leeward bridge.In contrast with the FreeV method,the MFV methodcould simulate the aerodynamic interference effect rationally and the flutter prediction results are more accurate.
    • 李寿英; 严杰韬; 肖春云; 陈政清
    • 摘要: 为了研究悬索桥吊索尾流索股的非定常气动力,制作表面光滑的吊索双索股刚性节段模型,采用HD-2风洞实验室自主研发的强迫振动装置重现双索股吊索尾流弛振现象,进行尾流索股2个自由度耦合振动状态下的横风向和顺风向测力试验,得到振动状态下尾流索股的气动升力和气动阻力时程.采用激光位移计同步测量2个方向的位移时程,识别尾流索股的8个相关气动导数,研究不同工况下气动导数随量纲一风速的变化规律,并验证采用气动导数拟合得到的非定常气动力的准确性.研究结果表明:尾流索股的气动刚度项系数H*4,H*6在高风速下会出现较大的正值,引起横风向运动气动负刚度,对尾流索股运动起放大作用;气动刚度项系数P*4,P*6仅在部分工况下引起气动负刚度;8个气动导数共同作用改变尾流索股的椭圆形运动轨迹;采用气动导数拟合得到的气动力与风洞试验测得的气动力大小吻合良好,可以利用气动导数对尾流索股的气动刚度力和气动阻尼力展开进一步研究.%Wake galloping is a kind of large amplitude vibration of the hangers always observed on large-span suspension bridges.In order to investigate the unsteady aerodynamic forces on the strand in the wake,two smooth ridge circular cylinder models were made and tested in the wind tunnel tests to measure the aerodynamic forces on the test model by a forced vibration system developed by HD-2 wind tunnel,on which the wake galloping reappeared.The lift and drag force histories,together with the displacement histories,were directly measured in the wind tunnel tests.Eight relative aerodynamic derivatives of the strand in the wake were simultaneously identified.The relationships between eight aerodynamic derivatives and reduced wind velocity in different cases are discussed,and the accuracy of unsteady aerodynamic forces integrated by aerodynamic derivatives is proved.The results show that the aerodynamic stiffness terms H*4 and H*6 have quite large positive values under high wind speed,and could cause negative aerodynamic stiffness in across-wind direction and enlarge the vibration amplitude of the strand.The aerodynamic stiffness terms P*4 and P*6 only have positive values in few cases.The wake-induced ellipse movement trajectories of the strand in the wake are determined by eight aerodynamic derivations.The unsteady aerodynamic forces obtained through aerodynamic derivatives agree well with that tested directly.The aerodynamic derivatives could be utilized to determine aerodynamic stiffness forces and aerodynamic damping forces for further investigation on wake galloping.
    • 战庆亮; 周志勇; 葛耀君
    • 摘要: 针对典型开口桥梁断面颤振抑振措施进行了风洞试验和数值模拟研究.风洞试验结果表明,原型断面在较低风速即发生了颤振失稳现象.通过数值模拟方法进行了颤振模拟,与风洞试验得到了一致的颤振临界风速,并研究了其颤振机理,即高折减风速下断面下表面产生的旋涡脱落及其漂移与断面扭转位移相匹配,产生了与断面运动方向相同的气动扭矩,导致了颤振发散.数值模拟显示,下稳定板可以有效阻碍断面下表面旋涡的脱落和运动,使得气动力在断面运动周期内做功为负,抑制颤振发散.节段模型风洞试验和全桥模型风洞试验结果显示,下稳定板是开口桥梁断面颤振的有效气动抑振措施.%Computational fluid dynamics and experimental methods are utilized to study the flutter characteristic and countermeasure mechanism of open-cross-section.The wind tunnel test results show that the prototype section of one suspension bridge tends to suffer flutter instability at relatively low wind speeds.The flutter critical wind speed is obtained by using the CFD approach,which conforms well with wind tunnel test results.Numerical simulations show that vortex shedding and drift from the lower surface of the section at high wind speeds match with the torsional displacement of the deck section.Vortex drifting produces the same direction aerodynamic torque as the section movement direction,leading to a flutter divergence.The same calculation is done with three sections added with different types of stabilization plates.The existence of stabilization plate prohibits the development and movement of main vortices,resulting in aerodynamic forces acting on the girder related less to displacement,thus suppress the flutter.Sectional and aerodynamics model wind tunnel tests are conducted to prove the effectiveness of stabilization plates.The results show that the lower stability plate is an effective vibration suppression measure for the flutter of the open-cross-section.
    • 李冬; 张辰; 王福新; 刘洪
    • 摘要: 利用计算流体动力学方法模拟了结冰后带舵面翼型的流场变化特征,分析了不同攻角条件下升力系数与舵面偏转角的量化关系,并对比了角冰和脊状冰条件下气动导数的差异.结果表明:与干净翼型相比,结冰后带舵面翼型的升力系数及升力系数关于舵面偏转角的变化率出现了较大降幅;舵面下偏导致的"上洗"效应将会加大冰型对流场的干扰,角冰引起的流动分离尺度受舵面偏转角的影响较大,且随着来流攻角增加而愈加明显;脊状冰可使翼型上表面产生大范围的流动分离,带舵面翼型的失速偏转角大幅提前,升力系数关于舵面偏转角的变化率大幅降低;在角冰条件下,带舵面翼型的相对气动导数呈现出3个不同的变化阶段,且随着来流攻角和舵面偏转角的增加而逐级下降,而在脊状冰条件下则呈现出2个不同的变化阶段,且其降幅更明显.
    • 蒋增辉; 宋威; 陈农
    • 摘要: 采用分段拟合技术对小迎角高超声速(马赫数Ma=6)非旋转钝锥双平面拍摄风洞自由飞试验结果进行了分析,获得了非旋转钝锥在小迎角高超声速下气动导数非线性的具体形式,分析了非旋转钝锥在小迎角下的非线性运动特点.研究发现在小迎角范围内钝锥的动导数系数均呈现明显的非线性,而静导数系数非线性较弱,可近似为线性.各组试验的静、动导数系数的非线性形式表明,除模型Ⅱ外的其余模型均为两方向振幅不同的极限圆锥运动,模型Ⅱ为极限平面运动.每组试验两个平面的静导数系数在小迎角范围内保持基本相等.而无论出现极限圆锥运动的四组试验还是出现极限平面运动的一组试验,模型在俯仰和偏航两个方向的动导数系数均存在较大差异.
    • 阮文斌; 刘洋; 熊磊
    • 摘要: 考虑飞行载荷计算中使用的气动导数存在不确定性,利用基于方差的全局灵敏度分析(GSA)方法,结合偏航机动的动力学模型,分析了侧向气动导数不确定性对侧向飞行载荷的影响.以某型飞机为例,运用该方法得到侧向气动导数的全局灵敏度排序.结果表明:侧滑角、阻尼贡献的垂尾侧向载荷及垂尾侧向总载荷受全机侧力系数对侧滑角导数的影响最大,受航向静稳定导数及方向舵操纵效能的影响次之;方向舵偏度贡献的垂尾侧向载荷只受全机侧力系数对方向舵偏度导数的影响;无尾飞机侧向载荷主要受航向静稳定导数、方向舵操纵效能及无尾飞机侧力系数对侧滑角导数的影响;偏航阻尼导数基本不影响各侧向飞行载荷.同时也验证了方法的有效性,对提高飞行载荷的计算精度有一定的指导意义.
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