The detection of structural deformation errors in attitude determination

In the determination of the attitude parameters from a multi-antenna GPS array, one of the major assumptions is that the body frame is rigid at all times. If this assumption is not true then the derived attitude parameters will be in error. It is well known that in airborne platforms the wings often experience some displacement during flight, especially during periods of initializing maneouvres, such as taking off, landing,and banking. Often it is at these points in time that it is most critical to have the most precise attitude parameters.There are a number of techniques available for the detection of modeling errors.The CUSUM algorithm has successfully been implemented in the past to detect small persistent changes. In this paper the authors investigate different methods of generating the residuals, to be tested by the CUSUM algorithm, in an effort to determine which technique is best suited for the detection of structural deformation of an airborne platform. The methods investigated include monitoring the mean of the residuals generated from the difference between the known body frame coordinates, and those calculated from the derived attitude parameters. The generated residuals are then passed to a CUSUM algorithm to detect any small persistent changes. An alternative method involves transforming the generated residuals into the frequency domain through the use of the Fast Fourier Transform. The CUSUM algorithm is then used to detect any frequency changes. The final technique investigated involves transforming the generated residuals using the Haar wavelet. The wavelet coefficients are then monitored by the CUSUM algorithm in order to detect any significant change to the rigidity of the body frame.Detecting structural deformation, and quantifying the degree of deformation, during flight will ensure that these effects can be removed from the system, thus ensuring the most precise and reliable attitude parameter solutions. This paper, through a series ofsimulations, will assess the effectiveness of the above mentioned techniques for detecting structural deformation effects on a GPS multi-antenna array. These principles are then tested with experimental data.     

昆虫翅膀的运动参数测量研究

研究可用于精确测量昆虫运动参数的条纹投影法.应用具有高衍射效率的声光调制器(AOD)生成投影条纹,通过调整各衍射光束的角度获得不同角间距的条纹,可用来测量反射比较低的昆虫翅膀.结合AOD和光栅,从两个相互垂直的方向投射条纹,可以在>90°的测量范围内测量蜜蜂的拍打翅膀.结果表明,在蜜蜂的一个拍打周期内,用该方法可以有效地测量其拍打角、滞后角,扭转角和扭转变形,相对测量误差<2%.     

多级提水高扬程泵站高压变频节能的计算与分析

针时平定县供水管理局娘子关各站机电水泵在直接启动时站与站之间存在流量不匹配问题而造成扬程损失,提出了改进措施,重点对多级提水高扬程泵站的高压变频节能进行了计算与分析.     

昆翅在飞行中的动态形变

通过理论模化途径研究昆翅在飞行中的动态形变机制.设计翅气动力试验平台,验证翅准静态形变影响气动力的"柔性楔形效应"理论解释.探讨昆翅的变刚度特性表明,弦向刚度分布规律符合二项式函数时具有优越性和现实性,进而指出昆姻结构的变刚度特性是产生高升力的基本条件.建立了柔性翅的简化力学模型,通过坐标变换法求解在气动力和惯性力共同...     

拖网网袖力学的初步研究

本文侧重对拖网网袖的力学性能进行理论分析和实验研究，揭示出网袖网衣对整顶拖网力学性能的影响，以供拖网设计者作理论参考。作者认为，增大网袖网目、减少网袖网衣用量或采用无袖结构，均能明显地降低整顶拖网的水阻力。适当缩短网袖长度可有效地提高网口垂直扩张高度。在外海及远洋作业中，若按实验结果改进网袖设计，以推进网具大型化实现轻网快拖捕捞中上层快速游泳鱼类。     

高扬程多级泵站系统老化多指标综合评价

20世纪 70～ 80年代在西北地区为了农业生产修建了许多大中型高扬程泵站 ,各泵站或多或少都存在着年久老化问题 .而多级泵站又是一个包括各级泵站在内的复杂系统 ,系统内一个单元性能改变都会对系统产生影响 .采用单元化方法将多级泵站系统单元化 ,按每一级划分成子单元 ,引入各级泵站老化多指标综合评价的方法 ,建立了多级泵站系统中各泵站老化矩阵分析模型 ,并对甘肃景泰川高扬程提水灌区多级泵站系统进行模拟 ,分析计算出高扬程多级泵站系统内各级泵站综合老化隶属度的评价指标 .模拟计算结果基本与实际相吻合     

The effect of scale changes on repetitive patterns: Influence of 6-aminonicotinamide on feather germ number

There are many examples of patterned developing systems which are size invariant: if the total size of the system is reduced, then the pattern responds by changing its scale in such a way that the number of pattern elements remains constant. This phenomenon is one of the bases which underaly the formulation of the concept of positional information, one of the great unifying ideas in developmental biology. However, there are less common examples of patterns which are size dependent. In these, alterations of overall size lead to a reduction in pattern elements. Such size-dependent patterns are therefore of theoretical interest. Here we describe how the number of feather germs along the wing bud of the developing chick embryo responds to shortening of the limb, and consider the implications of these observations.     

扑翼微型飞行器自适应鲁棒姿态控制

给出了扑翼微型飞行器姿态控制系统的数学模型,并提出了一种自适应鲁棒控制的新方法。飞行过程的复杂性使得姿态控制器的设计极具挑战性,主要困难是系统表现为非线性、不确定性、多变量参数耦合以及各种干扰。由于自适应鲁棒控制不依赖系统的精确数学模型,所以将系统分为名义模型、结构不确定性和非结构不确定性,对其分别设计直接反馈控制器、自适应控制器和鲁棒控制器,并用李亚普诺夫定理分析了系统的稳定性。仿真结果证实了所提方法的有效性。     

等离子体激励改善高升力机翼气动特性的仿真

为探索大迎角下介质阻挡放电(DBD)对高升力机翼的作用机理,采用体积力模型和Eddy Viscosity Transport Equation全湍流模型耦合进行DBD激励改善其气动特性的模拟仿真研究。在来流速度45 m/s条件下,对比实验数据与仿真模型,验证了仿真模型的正确性;并采用该模型分析了机翼弦向、展向的2组截面流线图。结果表明:DBD激励位于机翼前缘能很好地提高高升力机翼大迎角气动特性,显著改善上翼面涡结构,促进分离流附体;可将机翼最大升力系数提高11.1%,失速迎角推迟2°,且随迎角增大,流动控制效果逐渐减弱直到消失。     

垂尾跨声速弹性载荷研究

研究了战斗机垂尾在跨声速范围的非线性气动弹性行为和弹性载荷特性。针对飞机垂尾,计算了飞机垂尾的颤振边界,通过CFD／CSD耦合时域内推进结构运动方程,得到弹性结构的响应历程,并记录每一时刻的气动载荷和结构惯性载荷,将气动载荷信息转换到CSD的结点上,加载到结构模型上进行瞬态响应分析,得到结构的动应力响应,计算给出了0°侧滑角时不同马赫数下的颤振边界和Ma=0.9、侧滑角2°和10°时的非定常气动载荷与非定常惯性载荷和弹性载荷的时域响应,分析了惯性载荷、气动载荷和弹性载荷对颤振的影响以及方向舵对垂尾颤振的影响。