飞行器非线性气动弹性和颤振主动控制研究进展

首先，针对发展性能先进的新一代飞行器所涉及到的非线性气动弹性理论与分析技术，结合国内外研究进展情况，着重从建模技术、求解方法、非线性气弹特性分析几个方面进行概括总结。其次，对在飞行器设计中一直颇受关注的、智能材料在飞行器结构颤振及振动主动控制中应用研究现状也给予简要的介绍。最后指出一些尚待进一步研究的问题。     

Wing wettability of Odonata species as a function of quantity of epicuticular waxes

Dragonflies have gained much attention due to their sophisticated wing surface structure, and their associated superhydrophobic, self-cleaning and bactericidal properties. In this work, we compared and contrasted the chemical composition and surface morphology of the wing membranes of four species of dragonfly and damselfly from the Odonata family collected in 1970s (Diplacodes melanopsis and Xanthagrion erythroneurum) and 2011 (Diplacodes bipunctata, and Ischnura heterosticta). Diplacodes species are dragonflies, whilst Xanthagrion and Ischnura are damselflies. Fourier-transform infrared spectroscopy data obtained from the Australian Synchrotron were used to classify the fundamental components of all four of the insect species’ wings. The spectra of all species were dominated by CH stretching, amide I and amide II and OH stretch absorbance indicating the presence of a similar membrane composition of chitin, protein and wax in all four species. Although the samples were collected 40 years apart, there was no evidence of degradation having taken place during this time. Despite the overall similarities in spectral profile, species-specific differences were observed, most notably in the intensity of the νCH₂ peaks, which in part reflected the amount of waxes present on the wings, which appeared to be different between individual species. The surface topography also contained minor differences in the diameter and the spacial distribution of its nanopillars. It is postulated that the differences in surface wettability of the wings could be attributed to these minor differences in surface chemistry and surface topography. For example, X. erythroneurum presented the highest water contact angle (WCA) of 160° whilst the D. melanopsis wings exhibited the lowest WCA (138°), and the wettability of their wings was found to directly correlate with the intensity of hydrocarbon peaks found in their respective IR specta.     

Aeroelastic study of flexible flapping wings by a coupled lattice Boltzmann-finite element approach with immersed boundary method

In this paper, the behavior of two-dimensional symmetric flapping wings moving in a viscous fluid is investigated. Harmonic motion is applied to idealize flying organisms with flexible wings and extensive testing is carried out to investigate the resultant flight behavior related to the ability to take-off or accelerate the flapping wing system away from a starting location. Special attention is paid to analyze the effect of the main mechanical parameters, as well as the effect of lateral wind on flight performances. Moreover, aiming to investigate the possible benefits of flying in flocks, a couple of synchronously flapping wings is considered in addition to the single arrangement. The numerical simulations are performed by solving the fluid–structure interaction problem through a strongly coupled partitioned approach. Fluid dynamics are modeled at the mesoscopic scale by the lattice Boltzmann method. The resulting macroscopic quantities are derived, as usual, based on the statistical molecular-level interpretation.Wings are modeled by geometrically nonlinear, elastic beam finite elements and structure dynamics is solved by the time discontinuous Galerkin method. Fluid–structure interface conditions are handled using the immersed boundary method. The resultant numerical approach combines simplicity and high computational efficiency. A Monte Carlo simulation strategy is employed to characterize the flight behavior subjected to lateral wind. Various scenarios are discussed.     

Effects of mass and chordwise flexibility on 2D self-propelled flapping wings

A self-propelled flexible flapping wing 2D numerical model undergoing a combined pitching and heaving motion is presented. Since such freely moving foil experiences zero net thrust, a definition of efficiency for this kind of problem is proposed and discussed against other formulations found in the literature. It is also shown that the deviation motion of wings such as that found in natural flyers is likely a consequence of the fluid–structure dynamics of the wings. The passive deviation motion observed in numerical simulations is either a consequence of a feathering mechanism referred to as rigid feathering or of the inertial displacement caused by the wing deformation. The effects of flexibility on the performance of the wing are also presented. It is found that flexibility may significantly enhance the efficiency in pressure-driven deformation cases. The rigid feathering mechanism is found to have an effect similar to that of the feathering caused by wing flexibility on the performances of pressure-driven deformation cases.     

Cr4Mo4V轴承钢滚动接触疲劳和磨损性能研究

通过球棒滚动接触疲劳(RCF)试验机,研究了Cr4Mo4V轴承钢在4050润滑油润滑和0.18滑滚比条件下的滚动接触疲劳和磨损性能.结果表明:Cr4Mo4V钢的应力-寿命(S-N)曲线数据分散性较大,疲劳寿命随着应力增加呈下降趋势.Cr4Mo4V钢滚动接触磨损主要为磨料磨损,黏着磨损和疲劳磨损,随着应力和时间增加磨损体积增加,滚道凹槽深度达到17μm.通过光学显微镜(OM)和扫描电子显微镜(SEM)观察试样棒剖面与滚道交界处疲劳裂纹,发现疲劳破坏类型主要有两种:起源于表面的剥落(SOF)和起源于白蚀区的剥落(WSF).通过滚道径向切割抛光酸蚀显示Cr4Mo4V钢滚动接触疲劳影响区,随着应力和循环接触次数的增加,在次表层依次发现黑蚀区(DER)、白蚀区(WEA)和蝴蝶组织(BW).表面碳化物的剥落坑,黏着磨损和疲劳磨损的凹坑导致了表面起裂、白蚀区和蝴蝶组织中的碳化物和夹杂导致微裂纹的产生,链状碳化物使裂纹往深处扩展.     

ARNOLD CIRCULATION AND MULTI-OPTIMAL DYNAMIC CONTROLLING MECHANISMS IN DRAGONFLY WINGS

This paper aims to reveal the multi-optimal mechanisms for dynamic control in dragonfly wings. By combining the Arnold circulation with such micro/nano structures as the hollow inside constructions of the pterostigma, veins and spikes, dragonfly wings can create variable mass, variable rotating inertia and variable natural frequency. This marvelous ability enables dragonflies to overcome the contradictory requirements of both light-weight-wing and heavy-weight-wing, and displays the multi-optimal mechanisms for the excellent flying ability and dynamic control capacity of dragonflies. These results provide new perspectives for understanding the wings' functions and new inspirations for bionic manufactures.     

A parametric investigation of the propulsion of 2D chordwise-flexible flapping wings at low Reynolds number using numerical simulations

This paper presents a numerical investigation of the effects of chordwise flexibility on flapping wings at low Reynolds number. The numerical simulations are performed with a partitioned fluid–structure interaction algorithm using artificial compressibility stabilization. The choice of the structural dimensionless parameters is based on scaling arguments and is compared against parameters used by other authors. The different regimes, namely inertia-driven and pressure-driven wing deformations, are presented along with their effects on the topology of the flow and on the performance of a heaving and pitching flapping wing in propulsion regime. It is found that pressure-driven deformations can significantly increase the thrust efficiency if a suitable amount of flexibility is used. Significant thrust increases are also observed in zero pitching amplitude cases. The effects of the second and third deformation modes on the performances of pressure-driven deformation cases are discussed. On the other hand, inertia-driven deformations generally deteriorate aerodynamic performances of flapping wings unless the behavior of the wing deformation is modified by the presence of sustainable superharmonics in a way that produces slight improvements. It is also shown that wing flexibility can act as an efficient passive pitching mechanism that allows fair thrust and better efficiency to be achieved when compared to a rigid pitching–heaving wing.     

两串列扑翼的相位差对平均推力影响机理的实验研究

在一个低雷诺数的循环水洞中,实验研究了前后翅翼之间的相位差对两串列扑翼平均推力的影响.利用一个三分量的Kistler 压力传感器来测量扑翼的瞬时力;利用一个数字粒子测速仪系统(TSI DPIV) 来测量扑翼的前缘涡以及其周围的流场. 当相位差从0° 增加到360°,前翅的平均推力随着相位差正弦变化;前翅平均推力的增加是由于后翅的前缘涡和滞止区域增加了前翅的有效攻角. 后翅平均推力曲线有一个明显的V 字形低谷.低谷处较小的平均推力是由于前翅的脱落涡抑制了后翅前缘涡的形成并且减小了其有效攻角.当间距为0.5倍弦长相位差约为290°时,前后翅翼平均推力系数的合值能达到最大值0.667,明显大于两倍的单翼平均推力系数(2×0.255).      

Voigt线型两翼拟合非均匀流场吸光度的方法研究

在吸收光谱领域特别是可调谐半导体激光直接吸收光谱(dTDLAS)技术中, 需要精确测量吸收光谱的积分吸光度值以精确反演出流场温度、组分浓度等参数。对于非均匀流场,单光路吸收光谱测量时,由于沿测量路径的谱线展宽随流场状态的变化而变化,见诸文献的研究主要采用Voigt或Lorentz线型对吸光度曲线拟合处理或直接对吸光度曲线数值积分获取积分吸光度值,针对方法可能引入的误差进行了模拟分析,并提出Voigt线型两翼拟合吸光度的方法来获取吸收光谱的积分吸光度值,以减小拟合误差。采用流场测量中常用的H₂O作为目标气体,选取了8条具有不同低态能级的吸收线,以实验室平焰炉为原型建立两种非均匀流场模型,并通过分段法对流场非均匀性进行等效处理。分别采用Voigt线型拟合法、数值积分法和Voigt线型两翼拟合法模拟计算两模型的积分吸光度值,通过与理论积分吸光度值对比得出各方法的误差大小,从而确定出在不同的非均匀流场情况下相适应的积分吸光度值获取方法。