陀螺仪进动与章动运动分析

为了分析阻尼条件下陀螺仪章动与进动关系,从陀螺仪动力学模型出发,利用动静法建立运动方程,推导出理想条件下和阻尼条件下的进动与章动模型,指出章动方向上角度的变化中包含重力矩引起的章动和铅垂轴方向阻尼力矩引起的转子轴进动2个方面的影响,并通过实验得到进动和章动摆动曲线,同时证明阻尼能有效消除章动,为以后研究陀螺仪章动提供理论依据。     

弹支-刚性转子系统过共振瞬态响应特性研究

针对结合弹支-刚性转子系统的动力学特点,利用Lagrange能量法建立了考虑变速特性的转子系统瞬态响应动力学方程,模型中区别考虑了非旋转阻尼和旋转阻尼的影响.采用精细积分算法计算获得过临界区的转子瞬态响应特性,进一步对比分析了角加速度和阻尼特性对转子系统瞬态振动响应幅频特性和相频特性的影响规律.研究结果表明：变转速引起系统的刚度矩阵变化并产生附件的激励力;瞬态过共振响应幅值明显小于稳态响应幅值,且过共振越快速、阻尼越大时系统瞬态振动响应幅值越小.针对过瞬态相频特性,在临界转速附近出现一个新的相位角(加速过共振小于90°),此相位不受角加速度值和旋转阻尼比的影响,但随着非旋转阻尼比的增大呈增大趋势.     

基于非线性自回归时序模型的振动系统辨识

针对线性和弱非线性振动系统进行了研究,提出采用非线性自回归时序(GNAR)模型进行系统频率辨识和判断系统性或非线性基本特征的方法。首先根据摄动法求解非线性微分方程的理论,论证GNAR模型与线性和弱非线性系统之间的本质联系,推导出GNAR模型系数与线性和非线性系统频率之间的解析关系,然后给出由GNAR模型系数和结构判断系统是否存在非线性,及辨识系统频率和非线性项基本特征的方法。最后,以单自由度线性振动系统和无阻尼Duffing振动系统为算例验证该辨识方法的有效性和准确性。实验结果表明,基于GNAR模型的振动系统基本特征辨识方法具有较好的识别精度,能用于估计系统的动力学特性。     

一种重力敏感器阻尼系数测试方法

当重力敏感器内部充满阻尼液时,其表体内弹性系统的阻尼系数由阻尼液粘度和敏感器内部结构共同决定.提出了一种实际测量重力敏感器阻尼系数的测试方法.分析了重力敏感器的阻尼系数和内部结构的关系,给出了敏感器工作原理模型,推导出敏感质量振幅的函数关系式.通过在力矩线圈上施加不同频率、不同幅值的激励源信号并测试敏感质量振幅的方式,绘制出不同阻尼系数下敏感质量的振幅-频率关系曲线,将之与理论函数曲线对照来确定相应的阻尼系数值.试验结果表明:该阻尼系数测试方法能够有效地测试出充满不同粘度阻尼液的重量敏感器的阻尼系数,为阻尼液粘度的选取和控制回路的设计提供参考.     

具有谐波减速器的柔性关节参数辨识

为了辨识具有谐波减速器的柔性关节模型的关键参数,设计了一套基于多传感器融合的离线辨识方法,根据电机的位置传感器、电流传感器和关节力矩传感器的实验数据完成柔性关节模型关键参数的辨识.首先,建立采用谐波减速器柔轮输出的柔性关节模型;然后,使用正反转加载力矩的方法辨识出电机的力矩系数;并在空载的情况下,由关节力矩和电机输出力矩分别辨识出关节端和电机端的摩擦力;最后,采用敲击法初步辨识出关节的刚度和阻尼后,在关节位置受限条件下,逐渐增加电机输出力矩,得到柔性关节刚度和关节力矩的非线性关系.多次实验的结果显示,辨识出的参数具有较高的重复性,验证了该方法的有效性.     

小型无人直升机横纵向模型参数辨识方法

针对小型无人直升机具有多变量、非线性和强耦合的特点,提出一种基于参数辨识的横纵向通道动力学建模方法.该方法根据直升机小扰动运动学方程和小型无人直升机空气动力学特点,推导了小型无人直升机横纵向通道动力学模型.在悬停条件下通过对模型进行简化,得到小型无人直升机横纵向通道待辨识线性耦合模型.根据飞行实验数据,通过采用多变量最小二乘方法估计出该耦合模型的未知参数.模型预测数据和实际飞行数据的比较结果表明,所建模型能充分反映该小型无人直升机在悬停状态下的横纵向通道动力学特性,具有较高精度且结构相对简单,可作为自主飞行控制器设计的参考模型.     

不确定性转子系统的随机有限元建模及响应分析

随机特性和随机载荷会引起转子系统动力响应的不确定性,是转子动力学分析中的重要影响因素.本文基于Timosheke梁理论,把转轴的材料和几何随机特性表示为一维随机场函数,推导出随机转轴有限元列式,建立转子系统随机动力学模型,并给出随机载荷作用下随机转子系统动力响应统计量的分析方法.分别对线性和非线性涡轮泵转子系统进行了随机动力响应分析,并同Monte Carlo仿真结果进行对比,结果表明所建立的随机有限元动力学模型和给出的随机响应分析方法是合理可行的,可以有效应用于实际转子系统随机动力学分析和设计中.     

深空探测柔性太阳帆航天器动力学建模与姿态控制

太阳帆利用太阳辐射压力提供太空航行的必要动力,由于具有理论上的无限速度和无需消耗任何燃料等优势,被认为是完成未来深空探测任务的有效技术途径之一.柔性太阳帆航天器的动力学模型包括多体动力学、刚柔耦合动力学和太阳辐射光压模型,复杂的动力学特性导致其姿态控制设计具有很强的挑战性.针对带有控制杆的柔性太阳帆航天器,本文采用拉格朗日方程和有限元法,给出了面向控制的解析式动力学模型.所推导的刚柔耦合动力学模型,刻画了太阳帆航天器的本质动力学特性,即双框架控制杆的短周期运动,姿态与柔性太阳帆的耦合效应,以及在太阳光压恢复力矩下的姿态静稳定性和长周期运动.基于带控制杆的太阳帆航天器的双时间尺度特性,提出了双回路控制结构,用于实现航天器俯仰轴和偏航轴的姿态控制.将内回路设计为PD控制器,用于实现质心位置的调整.将外回路设计为PID控制器,用于阻尼姿态运动,并实现在平衡太阳光压力矩下的姿态保持.从而将柔性太阳帆航天器的复杂姿态控制问题转化为两个低阶子问题,实现了在不同频带上的控制设计.仿真结果验证了动力学建模和姿态控制设计方法的有效性.     

一类微小型碟式飞行器低速气动特性的数值分析

微小型飞行器是一种新型航空器,围绕与微小型飞行器相关的低雷诺数空气动力学问题是目前的研究热点。该文以一类微小型碟式飞行器为研究对象,对碟式飞行器在低速情况下,一定飞行攻角范围内的低雷诺数气动力特性进行了数值模拟,湍流模型为低雷诺数k-ε双层模型,计算出来的升力系数、阻力系数和力矩系数,与风洞吹风实验数据比较,误差在10%~15%之间,表明该文的数值方法是成功的。通过数值分析,得到碟式飞行器在低雷诺数下的一些基本气动性能,对研制微小型飞行器有一定的借鉴作用。     

分布式拉杆转子扭转振动系统动力学特性分析

为了更好的提高能源利用率,以新兴、高效的分布式拉杆转子系统为代表的燃气轮机与蒸汽轮机联合发电技术在电力部门得到快速发展.本文主要研究了分布式拉杆转子系统扭转振动的非线性动力学特性,通过等效简化等方法建立了分布式拉杆转子系统扭转振动方程.利用平均法获得动力学方程解析解和系统扭转振动幅频曲线,进一步研究了其周期解的稳定特性,并发现系统阻尼,立方刚度和外激频率等参数对其影响规律.本文的分析结果对燃气轮机转子系统动力学设计具有一定的指导意义.     

镀铜转子在力矩器中的应用

陀螺仪力矩器转子采用环形结构,定子与转子之间无磁阻转矩产生,也无齿槽粘合现象,运行平稳,噪音小,加工容易,相比鼠笼结构有独特的优势。从原理、设计方法、制造工艺方面研究了环形转子在力矩器中的作用和不同镀铜层厚度对输出力矩的影响。     

TORQUE AND FLUX TRACKING OF INDUCTION MOTORS

The problem of torque tracking and rotor flux norm regulation of induction motors perturbed by an unknown constant load torque was recently solved with an observer-based controller in Reference 5. In this paper we extend this result to treat the practically important case when the rotor flux norm is required to follow a time-varying reference. The controller design follows the passivity-based approach and proceeds in two steps: first, we define a target closed-loop dynamics compatible with the physical model of the motor that delivers the desired rotor flux and torque. Second, we propose a nonlinear dynamic output feedback controller that ensures this behaviour is asymptotically achieved. A proof of global tracking is given under the assumption of known motor parameters. Some key features of our physically based design are that the control law does not require measurement of rotor variables, is always well defined and does not rely on (intrinsically nonrobust) nonlinear dynamics cancellation. A corollary of our main result is the proof that a slight modification of the classical indirect field-oriented controller ensures global tracking for current-fed machines. © 1997 by John Wiley & Sons, Ltd.     

弹性箔片轴承-盘式永磁电机转子系统轴向冲击响应

轴向磁通永磁(Axial Flux Permanent Magnet,AFPM)电机在给转子输出周向电磁转矩的同时,还作为一种“磁轴承”,与弹性箔片轴承(Gas Foil Bearings,GFBs)并联工作.当GFBs支承的单定子单转子AFPM电机转速发生突变时(如加、减速),叶轮或者透平会产生一个瞬时轴向力.为揭示此轴向冲击对转子系统振动的影响机理,针对采用2个径向GFBs和1个轴向GFB支承的单定子单转子AFPM电机,建立了系统的刚性转子动力学方程,计入了永磁体的轴向吸力、径向回复力以及轴向GFB的推力对转子振动的影响.计算显示：轴向冲击对横向振动的影响非常小,箔片结构刚度的非线性效应会对转子振荡幅值和时间均产生影响,永磁体的负刚度绝对值越大,轴向振幅越大.在设计时,要注意永磁轴承刚度、箔片结构刚度和结构阻尼的合理匹配,以保证转子在轴向冲击下的轴向振荡时间和振幅均不超过允许值.     

利用交叉耦合效应抑制转子系统碰摩的控制方法

为了揭示交叉耦合效应对转子/定子碰摩响应的影响,解析推导了考虑定子质量、碰摩面刚度及交叉耦合阻尼和刚度项的转子/定子模型的同频全周碰摩解,并分析了该解的稳定性.结果表明:碰摩时转子的交叉耦合刚度和定子的交叉耦合阻尼可以减少摩擦力向转子横向振动的能量输入,从而减小碰摩力和转子碰摩响应的幅值.依据此特性,本文提出了通过产生交叉耦合效应来主动抑制转子碰摩破坏的控制思想,并通过仿真计算说明了相应控制方法的有效性.     

Control system design and input shape for orientation of spherical wheel motor

This paper presents control system design of a multi degrees-of-freedom (DOF) spherical wheel motor (SWM) in a class of ball-joint-like direct drive actuators to control orientation of the shaft. Three controllers (model based open-loop (OL), two closed-loop (CL) controllers) based on a push-pull torque model have been developed from rotor dynamics and magnetic field model referred to here as Distributed Multipole (DMP) model which provides accurate torque computation. The model based OL controller along with three control input shapes has been examined for the inclination control. Their results offer physical intuition, practical effectiveness, and also demonstrate the accuracy of magnetic field and torque computation. Then, two feedback controllers, a PD controller with and without the observer, have been developed for regulating its rotor inclination and experimentally evaluated against the OL controller. Finally, the performance on each controller has been compared to show the effect of the controllers on transient response. The experimental results verify control system design and demonstrate the motion capability of the SWM. While the experimental results illustrate the ability to control, they also reveal constraints and limitations of the controllers and provide insights for future design of control systems for the SWM.     

A speed-sensorless indirect field-oriented control for induction motors based on high gain speed estimation

The authors design a new speed sensorless output feedback control for the full-order model of induction motors with unknown constant load torque, which guarantees local asymptotic tracking of smooth speed and rotor flux modulus reference signals and local asymptotic field orientation, on the basis of stator current measurements only. The proposed nonlinear controller exploits the concept of indirect field orientation (no flux estimation is required) in combination with a new high-gain speed estimator based on the torque current tracking error. The estimates of unknown load torque and time-varying rotor speed converge to the corresponding true values under a persistency of excitation condition with a physically meaningful interpretation, basically equivalent to non-null synchronous frequency. Stability analysis of the overall dynamics has been performed exploiting the singular perturbation method. The proposed control algorithm is a “true” industrial sensorless solution since no simplifying assumptions (flux and load torque measurements) are required. Simulation and experimental tests show that the proposed controller is suitable for medium and high performance applications.     

Modeling and simulation of levitation control for a micromachined electrostatically suspended gyroscope

This paper presents a novel micromachined electrostatically suspended gyroscope (MESG) based on non-silicon micro electro mechanical systems technology, which can measure dual-axis angular velocity and tri-axis linear acceleration. The position of the rotor is detected capacitively and controlled electrostatically. In order to levitate the rotor along the Z axis, a levitation control model based on integrated control strategy for the MESG is presented. The damping coefficient is calculated by finite element analysis and deduced by analytical solution. According to the analysis of the levitation control force of the rotor, a three-degree-of-freedom close-loop control model is constructed. The theoretical relationship between the proportional integral derivative control parameters and stiffness properties is deduced. Initial levitation simulation result shows that the control principle is reasonable, which shows quick-response performance and global stability. Furthermore, digitally controlled levitation circuits have been designed.     

From the Test Benches to the First Prototype of the muFly Micro Helicopter

The goal of the European project muFly is to build a fully autonomous micro helicopter, which is comparable to a small bird in size and mass. The rigorous size and mass constraints infer various problems related to energy efficiency, flight stability and overall system design. In this research, aerodynamics and flight dynamics are investigated experimentally to gather information for the design of the helicopter’s propulsion group and steering system. Several test benches are designed and built for these investigations. A coaxial rotor test bench is used to measure the thrust and drag torque of different rotor blade designs. The effects of cyclic pitching of the swash plate and the passive stabilizer bar are studied on a test bench measuring rotor forces and moments with a 6–axis force sensor. The gathered knowledge is used to design a first prototype of the muFly helicopter. The prototype is described in terms of rotor configuration, structure, actuator and sensor selection according to the project demands, and a first version of the helicopter is shown. As a safety measure for the flight tests and to analyze the helicopter dynamics, a 6DoF vehicle test bench for tethered helicopter flight is used.     

Vibration-based automatic power-generation system

Two types of electric power generator systems that automatically extract power from oscillating motion of a human body or vibration of machines and structures are proposed and studied. The first system utilizes self-excited rotation of an eccentric rotor that rotates in one direction in synchronization with the applied oscillating motion. Connecting an electrical load to the generator increases the damping about the rotor axis, and numerical analysis shows that there exists an upper limit to this damping to maintain the self-excited rotation mode. Excessive damping reduces the rotor to a swinging motion, resulting in decreased power output. The second type utilizes resonant vibration of a permanent magnet unit suspended by a set of springs. In order to maximize the output power, a micro controller changes the connection of the generator coils, which in effect changes the electro-mechanical damping, to keep the vibration amplitude within the allowable stroke. Theoretical analysis and experimental results are presented for both systems.     

Advanced LIGA technology for the integration of anelectrostatically controlled bearing in a wobble micromotor

This work concerns the alleviation of friction in a novel design of multistator electrostatic wobble motor. The output torque and the kinematic accuracy of this device are limited by the sliding friction between the rotor and the top surface of the bearing. A solution for an axial bearing has been developed using an advanced LIGA technique to integrate polymethylmethacrylate (PMMA) cylinders into nickel micro structures. A new version of the micromotor has been fabricated, utilizing an axial electrostatic field to hold the rotor against an engineered sliding surface. The integrated bearing stabilizes the rotor and potentially permits operation in liquid environments by sealing the stator electrodes