Generation of Non-Gaussian Random Vibration Excitation Signal for Reliability Enhancement Test

During environment testing, the time histories of some dynamic environments follow non-Gaussian distribution. It is always assumed that the random vibration simulated follows Gaussian distribution, because the traditional digital random vibration control system can only supply the random vibration excitation signal of Gaussian. Yo simulate the real environment of product, a method is developed in this paper that can generate non-Gaussian random signal with specified power spectrum density （PSD）, skewness and kurtosis by shot noise. In this way, non-Gaussian random vibration can be produced on traditional electrodynamic shaker. It solves the problems of spectral valley and energy shortage in low frequency on omni-axis shaker. At last, the wavelet is used to analyze the non-Gaussian signal     

低频电动振动台的关键技术

简要介绍了低频电动振动台校准系统的结构和工作原理，分析了其存在非线性的原因。针对这些因素提出了在整个系统特别是对其核心——低频电动振动台的研制设计过程中应采取的措施、改进的方法和关键技术。     

Experiences with dynamic load simulation by means of modal forces in the presence of structural non-linearities

The dynamic qualification of space structures today is performed by means of driven base tests in order to simulate the dynamic environment during launch. This method is limited to structures that fit onto the shaker facility. For large and unwieldy structures an alternative approach can be utilised which applies modal forces for the qualification. Modal forces are patterns of single forces that are able to excite single resonances. These force patterns can be applied by movable electrodynamic shakers. This article reviews the background of the method. A test strategy is proposed which is based on narrow-banded swept sine excitation and considers structural non-linearities observed frequently. The qualification method was utilised during the qualification of the European Robotic Arm (ERA). The experiences gained during the test campaign are compiled in the paper. The advantages and disadvantages of dynamic qualification by means of modal forces are discussed.     

一种磁性并联低刚度隔振器

为了能够抑制低频微幅振动,提出了一种磁性并联低刚度隔振器,其由固支的承载梁和磁性弹簧并联构成.其中,磁性弹簧由4个永磁体对组成,每个永磁体对中的两块永磁体相吸配置,并在梁上对称均布;利用等效电流法对永磁体进行建模,根据安培定律给出了永磁体之间磁力的计算表达式,最后通过曲线拟合得到了其近似表达式;分析讨论了梁的等效刚度计算方法,进而得到了所提出的隔振系统的等效刚度计算方法;在不考虑系统非线性影响时,对该隔振系统进行了隔振特性分析及数值仿真.结果表明:与传统的线性隔振器相比,该隔振器能够有效地隔离低频振动,降低隔振系统的固有频率,从而拓宽了隔振器的隔振频带,并改善了系统的阻尼特性,有效地降低了共振区域的共振峰值.      

旋转叶片频率转向与振型转换特性

通过对典型旋转叶片的有限元分析, 讨论了旋转叶片动频特性的“频率转向”和“振型转换”问题, 尤其是关于多模态耦合的复杂“频率转向”和“振型转换”的现象和特点.首先讨论了旋转叶片动频特性中的两阶模态间“频率转向”和“振型转换”问题, 说明了这种耦合振动问题的机理, 然后研究了多阶模态相互耦合所导致的复杂“频率转向”和“振型转换”现象, 对其基本特点进行了详细的分析和说明.      

旋转Timoshenko梁的动力学分析

针对旋转Timoshenko梁结构,在梁的纵向、横向变形中均考虑横向弯曲以及轴向伸缩的耦合作用,同时在横向弯曲中考虑剪切变形的影响,在柔性梁的2个变形方向上均考虑了变形的二次耦合项,并充分考虑轴向离心力、横向惯性力的作用,利用有限元方法进行离散并利用Hamilton原理建立非线性变形模式下的一种新的Timoshenko梁动力学方程。对一平面旋转梁进行仿真计算,通过分析不同情况下的频率与端点变形位移,说明耦合作用的"软化"效果,以及轴向离心力、横向惯性力对模型的影响。     

基于压电纤维复合材料的离心叶轮叶片高阶模态测量

为准确获取离心叶轮叶片的高阶振动特性及其模态,利用压电纤维复合材料(Marco fiber composite,MFC)对离心叶轮叶片进行模态测试。设计了MFC激励系统,提出了MFC选型、激励和测点位置的确定方法,研究了不同信号的高阶模态激励效果,并分析了MFC附加质量和刚度对叶片固有频率和模态的影响;结合有限元仿真结果,对比分析了前20阶振动模态的异同。试验结果表明:MFC具有操作简单、重复性好、信噪比高、能够稳定激励出高阶模态等优势,计算模态与测量模态吻合较好,在第6～8阶与第12～15阶之间存在模态密集区域;MFC附加质量和刚度对实验固有频率的影响低于4%。提出的MFC激励方法可用于具有较高固有频率的航空发动机部件的模态测量。     

Structurally coupled characteristics of rotor blade using new rigid-flexible dynamic model based on geometrically exact formulation

In rotor dynamics, blades are normally modelled as a slender beam, in which elastic deformations are coupled with each other. To identify these coupling effects, new rigid-flexible structural model for helicopter rotor system is proposed in this paper. Finite rotations of the whole blade(on flapwise, lagwise, and torsional) are described as three global rigid degrees of freedom.The nonlinear deformation geometrics of the beam is built on geometrically exact beam theory.New expressions for blade ...     

Vibration suppression of thin-walled workpiece machining considering external damping properties based on magnetorheological fluids flexible fixture

Milling of the thin-walled workpiece in the aerospace industry is a critical process due to the high flexibility of the workpiece. In this paper, a flexible fixture based on the magnetorheological(MR) fluids is designed to investigate the regenerative chatter suppression during the machining.Based on the analysis of typical structural components in the aerospace industry, a general complex thin-walled workpiece with fixture and damping constraint can be equivalent as a rectangular cantilever beam. On the basis of the equivalent models, natural frequency and mode shape function of the thin-walled workpiece is obtained according to the Euler–Bernoulli beam assumptions. Then,the displacement response function of the bending vibration of the beam is represented by the product of all the mode shape function and the generalized coordinate. Furthermore, a dynamic equation of the workpiece-fixture system considering the external damping factor is proposed using the Lagrangian method in terms of all the mode shape function and the generalized coordinate, and the response of system under the dynamic cutting force is calculated to evaluate the stability of the milling process under damping control. Finally, the feasibility and effectiveness of the proposed approach are validated by the impact hammer experiments and several machining tests.     

带中介轴承的双转子系统振动耦合作用评估

为了评估中介轴承对双转子系统的振动耦合作用,从临界转速位置振型变化、临界转速变化、模态振型与稳态不平衡响应的应变能分布变化、中介轴承受力变化等多角度,阐释双转子耦合振动的表现形式和关联关系,提出了相应的评价指标或评估方法,并以典型燃气涡轮发动机双转子系统为对象,进行了分析评估。结果表明,单转子的模态振型可能在双转子模态振型中表现为3种形式,一一对应出现、重复出现或耦合出现,对应的临界转速及应变能分布也会随之产生相应的变化;中介轴承受力在临界转速位置出现峰值,而应变能分布变化最大的转速位置与系统临界转速位置不一致,同时还受不平衡激励位置影响;各单元应变能占比变化量随转速变化曲线可详细分析特定不平衡激励下系统应变能分布变化情况。所提方法可为双转子-中介轴承系统的设计、故障诊断提供参考。     

A dynamic modeling approach for nonlinear vibration analysis of the L-type pipeline system with clamps

There exists a lot of research on the nonlinear vibration of the pipeline system with different boundary conditions. To the best of our knowledge, little research on the actual constraint of the clamp has been performed. In this paper, according to hysteresis loops of the clamp obtained from experimental test, the simplified bilinear stiffness and damping model is proposed. Then the Finite Element (FE) model of L-type pipeline system with clamps is established using Timoshenko beam theory in combination with aforementioned stiffness-damping model. Both hammering and shaker tests verify the FE model via the comparisons of natural frequencies and vibration responses. The results show that the maximum errors of natural frequencies and vibration responses are about 8.31% and 17.6%, respectively. The proposed model can simulate the dynamic characteristics of the L-type pipeline system with clamps well, which is helpful to provide some guidance for the early design stage of pipeline in aero-engine.     

空间电动力绳系电流峰值点变化规律研究

为研究电流峰值点在几种影响因素下的变化规律,建立一种能够捕捉绳系电子发射与收集自洽平衡过程的新算法——电路空间耦合算法。为验证该方法的计算精度,以1.35kW霍尔推力器为等离子体源,在真空舱内开展绳系的电荷收集试验,在电路参数方面,计算精度约为12.8%,在场参数方面,计算精度约为3.6%。在此基础上,针对不同偏置电压、绳系长度以及绳系直径,对绳系的绳上电流分布、电势分布以及空间电势分布等参数进行数值计算。结果显示:电动力绳系的电流峰值点会随着偏置电压升高、绳系长度增加及绳系直径增大而发生比例上的向阳极端漂移,揭示了电子轨道运动限制的机制在各类壁面电荷输运机制中占优,导致电流峰值点漂移的产生。     

Aeroelastic analysis of a shipboard helicopter rotor with ship motions during engagement and disengagement operations

An aeroelastic simulation of a shipboard helicopter rotor with ship motions during engagement and disengagement operations is investigated to explore the coupled dynamic behavior between the rotor and the ship. A finite element analysis based on a moderate deflection beam model is employed to capture the flap, lag and torsion deflections of the rotor blade. The ship is treated as a six-degree-of-freedom rigid body. By using the Hamilton?s principle, system equations of motion are derived based on the generalized force formulation. The responses agree well with the test data of the rotor blade droop stop impact and the transient aeroelastic response of the shipboard teetering model rotor. Parametric investigations illustrate that the ship pitch motion has significant influence on the maximum negative displacement of the blade tip. Additional over 25% increase of the tip deflection can be introduced by the ship pitch motion. The aerodynamic and inertial couplings between the ship motion and the rotor have significantly nonlinear influence on the transient aeroelastic response. Both terms should be taken into account in the coupled helicopter–ship dynamics model.     

自由阻尼梁高频能量流响应的解析模型

针对自由阻尼梁的高频振动问题,基于波动理论提出了大阻尼复合结构的能量流解析模型。利用等效复刚度方法确定了完全自由阻尼梁结构的等效弯曲刚度和损耗因子,基于能量流分析方法构建了结构的能量密度控制方程,求解了结构的高频能量流响应。分析了弯曲波在阻尼结构耦合处的能量传递特性,构建了局部自由阻尼梁的高频能量流解析模型,预测了大阻尼耦合结构的高频振动特性。数值结果表明,提出的能量流解析解与经典的时空平均波动解一致逼近,因而能够精确地预测自由阻尼梁等大阻尼复合结构的高频能量流响应。     

利用互相关函数进行环境激励下的模态分析

对互相关函数理论的进一步发展作了详细推导 ,探索出一条将互相关函数理论同多种经典模态分析方法相结合进行环境激励下模态分析的方法。以一悬臂梁为试验模型 ,在白噪声激励下将互相关函数代替脉冲响应函数用于多参考点复指数法和特征实现算法进行模态识别 ,并同功率谱峰值法结果进行了对比。研究表明 ,利用互相关函数理论同某些经典模态识别方法相结合能够有效地识别出环境激励下的系统模态参数     

有效载荷基频降低对火箭动特性的影响

为了分析有效载荷基频降低对火箭动特性的影响规律,采用纵横扭一体化梁模型与耦合质量方法模拟箭体承力结构与液体推进剂,使用NASTRAN中的RBE2单元模拟芯级与助推器连接接头.通过修改有效载荷有限元模型以得到不同的有效载荷基频,选取飞行过程中的四个典型秒状态,计算三种不同有效载荷基频下全箭的前九阶固有振动频率.结果表明：纵横扭一体化梁模型在进行全箭动特性分析时模型简单,结果满足要求,可用于设计初期的模态分析;同时,分析得到基频降低对全箭动特性的影响规律,给卫星设计人员提供了相关依据.     

Dynamic Analysis of Contact Bounce of Aerospace Relay Based on Finite Difference Method

Contact bounce of relay, which is the main cause of electric abrasion and material erosion, is inevitable. By using the mode expansion form, the dynamic behavior of two different reed systems for aerospace relays is analyzed. The dynamic model uses Euler-Bernoulli beam theory for cantilever beam, in which the driving force (or driving moment) of the electromagnetic system is taken into account, and the contact force between moving contact and stationary contact is simulated by the Kelvin-Voigt viscoelastic contact model. Analytical results have been complemented by the finite difference calculation of the nonlinear partial differential equations of reed system. The calculation results indicate that with the driving force (or driving moment) being increased, the closing time of contact is decreased, but the maximum bouncing displacement and bouncing time tend to be decreased first and then increased, which means that there are minimum values of maximum bouncing displacement and bouncing time. The closing time of contact, the maximum bouncing displacement, and bouncing time all tend to be decreasing with the pushrod being approaching the contact. The model can be used as design tool to improve relay performance and reduce contact bounce.     

全模颤振双索悬挂系统刚体模态频率研究

研究绳系结构和绳索预紧力对全模颤振双索悬挂系统刚体模态频率的影响。首先，基于绳索并联机构理论，对双索悬挂系统进行静力学建模，引入加权矩阵，推导了双索悬挂系统静刚度模型；其次，建立双索悬挂系统无阻尼振荡方程，分析双索悬挂系统刚体模态频率变化规律；进而，搭建了双索悬挂系统地面样机，开展系统模态频率测试试验，研究系统刚体模态频率的影响因素及其变化规律；最后，参考试验结果修正所建数学模型。结果表明，随着绳索预紧力的增加，系统刚体模态频率呈上升趋势，但各阶刚体模态的固有频率上升速率不同，平动模态的固有频率受绳索预紧力影响比转动模态小得多；在转动模态方面，滚转模态的固有频率最大且上升快；在平动模态方面，升沉模态的固有频率大于横侧滑模态的固有频率；双索经过的机身前后滑轮与飞机模型质心之间的相对位置变化会不同程度地影响支撑系统俯仰模态、偏航模态的固有频率，但几乎不影响其滚转模态的固有频率。研究发现，通过控制悬挂绳索预紧力的大小，合理设计机身上的滑轮安装位置，能够有效降低双索悬挂系统刚体模态频率。研究结果对于优化设计全模颤振双索悬挂系统具有指导意义。     

机身刚度对双体飞机颤振的影响规律分析

针对某双体飞机颤振特性复杂的问题,本文采用片条理论修正后的偶极子网格方法,建立了双体飞机非定常气动力模型,同时基于地面振动试验建立了不同机身刚度双体飞机等效梁模型。通过有限元方法,分析了机身刚度对双体飞机结构动力学的影响,同时通过求解耦合得到的频域方程,探究了机身刚度对双体飞机颤振的影响规律。研究结果表明,机身截面垂向刚度对机身一阶垂直对称弯曲模态、机身一阶垂直反对称弯曲模态与平尾滚转模态频率影响较大。机身截面垂向刚度降低到原设计刚度67%时,机身反对称弯曲模态对平尾扭转效应增强,机身一阶垂直反对称弯曲模态、平尾滚转模态与平尾一阶垂直反对称弯曲模态耦合,双体飞机在269.34 m/s时发生颤振,颤振频率为37.2 Hz。     

MIMO随机振动试验控制的逆多步预测模型法

多输入多输出（MIMO）随机振动试验在产品可靠性验证中扮演重要角色。逆系统方法作为一种时域方法，直接由参考信号（即期望得到的响应信号）生成驱动信号，但容易产生不稳定的结果。本文以系统的有限差分模型为基础，推导了逆多步预测模型，并建立了该逆模型与矩阵幂次算法结合的MIMO随机振动试验方法。通过悬臂梁模型进行双输入双输出仿真试验，验证了逆多步预测模型进行MIMO随机振动试验驱动生成的可行性。在三轴振动台上进一步验证该方法进行MIMO随机振动试验控制的能力。