昆虫飞行的空气动力学

昆虫是最早出现、数量最多和体积最小的飞行者. 它们能悬停、跃升、急停、快速加速和转弯, 飞行技巧十分高超. 由于尺寸小, 因而翅膀的相对速度很小, 从而进行上述飞行所需的升力系数很大. 但昆虫翅膀的雷诺数又很低. 它们是如何在低雷诺数下产生高升力的, 是流体力学和生物学工作者都十分关心的问题. 近年来这一领域有了许多研究进展. 该文对这些进展进行综述, 并对今后工作提一些建议. 因2005 年前的工作已在几篇综述文章有了详细介绍, 该文主要介绍2005 年以来的工作. 首先简述昆虫翅的拍动运动及昆虫绕流的基本方程和相似参数; 然后对2005 年之前的工作做一简要回顾. 之后介绍2005 年后的进展, 依次为: 运动学观测; 前缘涡; 翅膀柔性变形及皱褶的影响; 拍动翅的尾涡结构; 翼/身、左右翅气动干扰及地面效应; 微小昆虫; 蝴蝶与蜻蜓; 机动飞行. 最后为对今后工作的建议.     

卫星编队飞行动力学与控制研究

简要介绍了卫星编队飞行的动力学与控制研究的最新进展,对今后研究工作的重点提出了建议．     

地球轨道航天器编队飞行动力学与控制研究综述

航天器编队飞行被定义为跟踪或维持航天器之间的期望相对间隔、期望指向和相对位置。本文概括介绍了近年来地球轨道飞行编队的动力学和控制方面研究的发展状况,包括传统推进系统和新型无推进剂编队系统的动力学建模方法和控制器设计技术等。在传统推进编队系统中,航天器由使用化学燃料或等离子体的推进器提供推力,可以实现高精度地相对姿态/位置保持或重构,控制简单,灵活性高,但是需要消耗较多的能源。相比之下,在新型无推进剂编队系统中,航天器通过新的推力方式,如大气阻力作用,非接触内力,地磁洛伦兹力,动量交换等,将大大延长编队任务的寿命,并有效地避免羽流污染,但会带来新的控制问题。本文总结了这些领域中动力学与控制方面的研究方法及取得的成果,并提出了相关领域值得深入研究的问题和后续发展的方向。     

平流层飞艇动力学与控制研究进展

本文简要介绍了飞艇的发展沿革和研究现状. 通过同传统的航空器、航天器、潜艇和低空飞艇进行比较, 阐述了平流层飞艇的飞行原理. 从基本运动模型和复杂受力情况的角度, 系统地讨论了飞艇动力学研究进展, 包括空气动力学研究、静力分析、热力学分析、柔性体动力学及流固耦合研究. 然后综述了飞艇控制方法研究进展, 包括小扰动线性化控制、输入输出反馈线性化控制、基于Lyapunov 非线性稳定性的控制及其他控制方法. 最后展望了在平流层飞艇动力学与控制领域需要从6 个方面加强研究.      

地球轨道航天器编队飞行动力学与控制研究综述1)

航天器编队飞行被定义为跟踪或维持航天器之间的期望相对间隔、期望指向和相对位置。本文概括介绍了近年来地球轨道飞行编队的动力学和控制方面研究的发展状况,包括传统推进系统和新型无推进剂编队系统的动力学建模方法和控制器设计技术等。在传统推进编队系统中,航天器由使用化学燃料或等离子体的推进器提供推力,可以实现高精度地相对姿态/位置保持或重构,控制简单,灵活性高,但是需要消耗较多的能源。相比之下,在新型无推进剂编队系统中,航天器通过新的推力方式,如大气阻力作用,非接触内力,地磁洛伦兹力,动量交换等,将大大延长编队任务的寿命,并有效地避免羽流污染,但会带来新的控制问题。本文总结了这些领域中动力学与控制方面的研究方法及取得的成果,并提出了相关领域值得深入研究的问题和后续发展的方向。     

空气动力学研讨课建设的探索与实践

为了丰富基础课堂教学资源、满足本科生通识教育的需求,北京航空航天大学近期推出建设名师研讨课、新生研讨课、专业研讨课等,毫无疑问这些对学校本科教学的深化改革具有重要的促进作用.针对我校国家级精品课程空气动力学教学改革的实践,总结了在建设空气动力学名师研讨课过程中的构思和经验,以供参考.空气动力学是一门理论与实际紧密结合的基础课程,在研讨课建设中,提出以空气动力学典型问题为引导,通过启发、实验、讨论、分析等多种形式,引导学生积极主动思考,从鸟的飞行原理、实验现象和结果中获取灵感、凝练科学问题,对激发学习兴趣、提高创新实践能力等具有明显效果.     

大型漂浮式风电装备耦合动力学研究: 历史、进展与挑战

风电是可再生能源的主力军, 在优化能源结构、缓解气候变化方面发挥着重要作用. 经过数十年的发展, 风电装备逐渐向大型化和离岸化方向发展, 并由此形成“由陆向海, 由浅入深, 由固定式向漂浮式”的演变之路. 在水深大于50米的深远海域, 采用漂浮式支撑基础搭载大型或超大型风电机组是兼顾技术可行度和成本优势的理想选择. 如今, 大型漂浮式风机已成为下一代深远海风能大规模开发的主力装备, 是深化海洋风能开发的先导战略性高端装备, 是风电领域的研究热点和技术高地. 本文围绕大型漂浮式风电装备耦合动力学问题, 综述了国内外浮式风电技术的发展历程和研究现状, 结合作者团队多年的研究与实践经验, 介绍了浮式风机耦合动力学及其优化控制中的基础问题与研究现状, 总结了现阶段浮式风机耦合动力学研究中的困难与挑战, 为浮式风电研究人员提供参考.     

编队飞行星座相对运动的运动学描述与编队构型设计

分别以纬度幅角和平近点角、平纬度幅角及偏近点角为变量,推导了几种简单的编队飞行星座相对运动的运动学模型,这些模型和动力学模型(Hill方程)相一致,但更便于应用。并在此基础上,给出了当编队构型为空间圆形和星下点圆形时进行编队构型设计的一种运动学方法,该方法直接给出了星座中各星的轨道根数的计算方法,实例证明该方法简单实用。     

飞行和游动的生物力学与仿生技术--香山科学会议第214次学术讨论会介绍

在隆重纪念香山科学会议举办十周年之际,香山科学会议第214次学术讨论会于2003年10月21日-23日在北京香山饭店举行.本次讨论会的主题是“飞行和游动的生物力学与仿生技术”.出席讨论会的代表42人,包括来自高等院校和中国科学院、航天科技集团等有关研究所的专家、学者,以及有关部门的科技管理专家.讨论会的执行主席为童秉纲院士和崔尔杰院士. 20世纪末,各种先进微型制造技术、微机电系统、微电子和一体化技术有了迅速发展.在此基础上,人们提出了微     

仿生扑翼飞行机器人翅型的研制与实验研究

模仿昆虫和小鸟飞行的扑翼飞行机器人将举升、悬停和推进功能集于一个扑翼系统,与固定翼和旋翼完全不同,因此研究只能从生物仿生开始。生物飞行的极端复杂性使得进行完整和精确的扑翼飞行分析非常复杂,因此本文在仿生学进展基础上,通过一些合适的假设和简化,建立了仿生翅运动学和空气动力学模型,并以此为基础研制了多种翅型。研制了气动力测量实验平台,对各种翅型进行了实验研究。实验结果表明,研制的翅型都能产生一定的升力,其中柔性翅具有较好的运动性能和气动性能,并且拍动频率和拍动幅度对升力有较大影响。     

Enclosure enhancement of flight performance

We use a potential flow solver to investigate the aerodynamic aspects of flapping flights in enclosed spaces. The enclosure effects are simulated by the method of images. Our study complements previous aerodynamic analyses which considered only the near-ground flight. The present results show that flying in the proximity of an enclosure affects the aerodynamic performance of flapping wings in terms of lift and thrust generation and power consumption. It leads to higher flight efficiency and more than 5% increase of the generation of lift and thrust.     

The effects of corrugation and wing planform on the aerodynamic force production of sweeping model insect wings

The effects of corrugation and wing planform (shape and aspect ratio) on the aerodynamic force production of model insect wings in sweeping (rotating after an initial start) motion at Reynolds number 200 and 3500 at angle of attack 40° are investigated, using the method of computational fluid dynamics. A representative wing corrugation is considered. Wing-shape and aspect ratio (AR) of ten representative insect wings are considered; they are the wings of fruit fly, cranefly, dronefly, hoverfly, ladybird, bumblebee, honeybee, lacewing (forewing), hawkmoth and dragonfly (forewing), respectively (AR of these wings varies greatly, from 2.84 to 5.45). The following facts are shown. (1) The corrugated and flat-plate wings produce approximately the same aerodynamic forces. This is because for a sweeping wing at large angle of attack, the length scale of the corrugation is much smaller than the size of the separated flow region or the size of the leading edge vortex (LEV). (2) The variation in wing shape can have considerable effects on the aerodynamic force; but it has only minor effects on the force coefficients when the velocity at r ₂ (the radius of the second moment of wing area) is used as the reference velocity; i.e. the force coefficients are almost unaffected by the variation in wing shape. (3) The effects of AR are remarkably small: when AR increases from 2.8 to 5.5, the force coefficients vary only slightly; flowfield results show that when AR is relatively large, the part of the LEV on the outer part of the wings sheds during the sweeping motion. As AR is increased, on one hand, the force coefficients will be increased due to the reduction of 3-dimensional flow effects; on the other hand, they will be decreased due to the shedding of part of the LEV; these two effects approximately cancel each other, resulting in only minor change of the force coefficients. The project supported by the National Natural Science Foundation of China (10232010 and 10472008) and Ph. D. Student Foundation of Chinese Ministry of Education (20030006022) The English text was polished by Keren Wang.     

Unsteady aerodynamic forces and power requirements of a bumblebee in forward flight

Aerodynamic forces and power requirements in forward flight in a bumblebee (Bombus terrestris) were studied using the method of computational fluid dynamics. Actual wing kinematic data of free flight were used in the study (the speed ranges from 0 m/s to 4.5 m/s; advance ratio ranges from 0–0.66). The bumblebee employs the delayed stall mechanism and the fast pitching-up rotation mechanism to produce vertical force and thrust. The leading-edge vortex does not shed in the translatory phase of the half-strokes and is much more concentrated than that of the fruit fly in a previous study. At hovering and low-speed flight, the vertical force is produced by both the half-strokes and is contributed by wing lift; at medium and high speeds, the vertical force is mainly produced during the downstroke and is contributed by both wing lift and wing drag. At all speeds the thrust is mainly produced in the upstroke and is contributed by wing drag. The power requirement at low to medium speeds is not very different from that of hovering and is relatively large at the highest speed (advance ratio 0.66), i.e. the power curve is J-shaped. Except at the highest flight speed, storing energy elastically can save power up to 20%–30%. At the highest speed, because of the large increase of aerodynamic torque and the slight decrease of inertial torque (due to the smaller stroke amplitude and stroke frequency used), the power requirement is dominated by aerodynamic power and the effect of elastic storage of energy on power requirement is limited.The project supported by the National Natural Science Foundation of China (10232010) and the National Aeronautic Science fund of China (03A51049)The English text was polished by Xing Zhang.     

可变形儒可夫斯基翼型亚音速非定常气动力的研究

对于翼面变形速度远小于来流速度情况下的儒可夫斯翼型亚音速绕流问题,通过仿射变换将可压缩流动转换成不可压缩流动,将解析解和离散涡方法相结合计算变形机翼的不可压缩流动速度场,再利用逆变换得到变形机翼的亚音速流动速度场,进而分析非定常气动力特性,建立变形机翼的准定常升力系数和非定常附加升力系数在可压缩和不可压缩两种状态下的简单近似对应关系。计算结果显示变形机翼的非定常气动升力近似等于准定常计算结果叠加上虚拟质量力导致的非定常附加升力,该非定常附加升力随翼型变形速率呈线性关系,由机翼当前时刻飞行姿态、翼型及其变形速率确定,与具体变形历史过程无关。低来流马赫数时虚拟质量力导致的非定常效应显著,高亚音速流动时准定常升力起主导作用。同时还分析了不同马赫数下机翼往复变形过程中升力的变化特性,指出尽管高亚音速变形机翼的气动升力近似等于准定常气动升力,但不能忽视非定常附加升力的影响,非定常附加升力将导致完成往复变形需要外界输入正比于Ma∞/[(1-Ma2∞)]的功。     

Analysis of the aerodynamic interaction between two plunging plates in tandem at low Reynolds number for maximum propulsive efficiency

The thrust generated by two heaving plates in tandem is analyzed computationally by solving the Navier–Stokes equations for an incompressible and two-dimensional flow at low Reynolds numbers. We consider with detail two particular sets of configurations of interest in forward flight in a wide range of heaving amplitudes and frequencies: a plunging leading plate with the trailing plate at rest, and the two plates heaving with the same frequency and amplitude, but varying the phase difference. In almost all cases the thrust efficiency of the leading plate is augmented in relation to a single plate heaving with the same frequency and amplitude. In the first configuration with a trailing plate at rest, we characterize the range of nondimensional heaving frequencies and amplitudes of the leading plate for which the stationary trailing plate contributes positively to the global thrust. The maximum global thrust efficiency of this configuration, reached for an advance ratio slightly less than unity and a reduced frequency close to 5, is about the same as the maximum efficiency for an isolated plate, reached for slightly smaller frequencies. But for low frequencies the tandem configuration with the trailing plate at rest is more thrust efficient than the isolated plate. We also characterize the nondimensional frequency and amplitude regions for which the flow becomes chaotic. In the second configuration, the maximum of the total thrust efficiency is reached for a phase lag of 180° (counterstroking), particularly for an advance ratio unity and a reduced frequency 4.4. It is almost the same as the maximum thrust efficiency in the other configuration with the trailing plate at rest and that of a single plate. We discuss the flow structures and the aerodynamic interaction between plates responsible for the optimal thrust configuration in both cases.     

可变形儒可夫斯基翼型非定常气动力的研究

对于翼面变形法向运动速度远小于来流速度的儒可夫斯基机翼,将解析解和离散涡方法相结合计算变形机翼的流场及非定常气动力,较详细地分析了变形机翼升力系数的准定常计算方法的误差来源,并给出修正方法.计算结果显示脱落涡尾迹对升力系数和机翼绕流环量的影响很小,变形机翼升力系数准定常计算方法的误差丰要来源于流体非定常运动引起的虚拟质量力,该非定常附加升力仅与当前时刻飞行姿态及翼犁形状和变形速率有关,与具体的变形历史过程无关,变形机翼的升力近似等于准定常计算结果叠加上相应的虚拟质量力.