激光陀螺抖动系统振动特性的有限元分析

建立了激光陀螺抖动系统的三维有限元模型,对其振动特性进行了模态分析,并对该系统进行了模态实验测量,最后将模态分析的结果和实验测量结果进行了对比。对比结果表明,所建立的有限元模型合理,分析结果可靠,对该系统的改进设计具有重要意义。     

磁悬浮飞轮转子组件温度场分析与研究

磁悬浮飞轮作为一种航天器的姿态控制执行机构当其工作在高真空环境下时，散热条件差，系统温度过高，导致转子组件热膨胀，产生热应力或改变磁轴承及电机的间隙，则会降低系统的可靠性。利用有限元软件ANSYS对一种磁悬浮飞轮系统的转子组件进行了温度场仿真，考虑了传导及辐射的传热方式，得到了飞轮转子组件的温度场分布，并且分析了组件材料属性对温度场分布的影响，最后对飞轮系统的强化传热进行了研究。分析所得温度值与实验测值相符，为磁悬浮飞轮系统的热设计及总体结构设计提供了重要依据。     

捷联惯导系统减振设计

机抖激光陀螺的捷联惯性导航系统结构设计的关键在于惯性测量单元（IMU）的减振设计。文章描述了一种IMU减振系统设计的方法,并在实际应用当中获得良好的效果。IMU减振系统的设计方法主要分为三大内容。首先是对减振系统中减振器的布局方案进行仿真分析,建立减振系统的六自由度振动响应模型,研究减振器布局方案的频谱特性,比较得到减振效果较优的减振器方案。然后针对获得的减振器布局方案,设计IMU结构框架和各向同性的减振器,并采用有限元的方法,对IMU的减振系统进行模态分析,获得IMU减振系统的前20阶模态频率和振型,用有限元仿真分析的方法来验证减振设计。目前这种IMU减振系统的设计方法已应用到某新型捷联惯导系统当中,减少了系统陀螺精度的降低。     

激光陀螺捷联惯导系统IMU结构模态分析

随着机抖激光陀螺捷联惯导系统以其诸多优点在军用与民用导航领域得到广泛的应用,对其体积和重量的要求变得越来越严格。机抖激光捷联惯导系统IMU小型化设计的关键在于减振系统的设计,而减振器仿真模型的建立是该减振系统模态仿真分析的难点。针对这一问题,提出一种通过ANSYS中的"Bushing连接"来模拟减振器的方法,并利用模态实验结果修正其参数,最终建立了一个准确的减振器模型,实现了对捷联惯导IMU振动模态的精确仿真与分析,为其IMU结构的进一步小型化设计奠定了基础。     

机抖激光陀螺动力学分析及优化设计

利用有限元分析软件ANSYS,建立了机抖激光陀螺有限元模型并进行了模态分析和随机振动分析,通过与试验结果对比,验证了模型的合理性和精确性,指出了现有结构的薄弱环节。利用灵敏度分析技术分析了安装盒底部、四壁和支柱等几何尺寸和约束位置对机抖激光陀螺固有频率的影响。计算表明:影响固有频率的主要因素是安装盒的支柱高度、底面厚度和约束位置,而安装盒四壁厚度对固有频率影响很小。最后对结构进行了优化设计,优化后结构一阶固有频率提高35.7%,二阶以上固有频率提高63%以上。     

安装蜂窝板动力学特性分析及主动控制试验研究

通过对蜂窝芯的等效化处理,建立了ANSYS的壳单元模型,并作有限元模态分析,然后与其试验模态分析结果比较,有限元分析结果和试验结果基本一致。通过ANSYS的PSD随机功率谱分析和模态分析所得振型确定了贴片位置,对蜂窝板进行了压电智能结构振动主动控制试验研究,得到了较好的振动抑制效果。分析结果为仪器安装蜂窝板的设计和实现智能结构控制提供了重要参考依据。     

MEMS陀螺仪结构模型及系统仿真

为了减小MEMS陀螺仪的正交误差,进一步提高陀螺精度,在Simulink环境中对陀螺结构和测控系统进行了建模和仿真。首先在理想状态的陀螺结构模型基础上建立了包含机械热噪声、模态间耦合等非理想因素的结构模型,并给出了陀螺结构的相关设计参数。其次在陀螺结构模型上以自激振荡和AGC控制技术为基础设计了驱动回路,该回路可在短时间内将驱动幅度稳定在10μm,且驱动频率为4048 Hz（驱动模态的谐振频率）。然后分析了模态间耦合信号的作用方式并建立了正交校正和检测闭环力反馈回路,仿真结果显示,在全闭环状态下检测模态所受耦合力的幅度比未校正状态下降了5个数量级,等效输入角速度也从205(°)/s下降到了6.58(°)/h。最后对陀螺模型进行了整体测试,得到其标度因数和阈值分别为21.76 mV/(°)/s和0.002(°)/s。     

静电陀螺仪实心球转子变形分析

介绍了静电陀螺仪实心球转子的两种典型结构，并利用有限元仿真工具根据工作环境对这两种结构分别进行了离心变形、温度变形、压力变形以及这三种载荷的耦合变形的仿真分析。得出了实心球转子的变形规律及变形量，为转子的设计和静电陀螺的建模提供了重要的参考依据。     

振动轮式微机械陀螺动力学方程、振动模态及其灵敏度分析

介绍了一种新的振动轮式微机机械陀螺仪的结构及工作原理,详细推导了该陀螺的动力学方程,分析了其运动规律,并建立了该陀螺的三维有限元模型,给出了前其四阶模态振型,对灵敏度进行了分析模拟。     

基于结构动力学的框架结构固有频率估算方法

对框架结构的一阶固有频率与单门框的一阶固有频率的关系进行了推导,找出一种通过部件模态参数估算整体系统的模态参数的方法．通过ANSYS有限元分析对该估算方法进行了验证,并在石油钻机井架底座的有限元模态分析中应用该方法对系统固有频率进行了估计,误差均不超过1％．结论表明,该方法对于框架串联结构的固有频率估算是方便且可行的．     

高速磁悬浮转子稳定性研究及其在控制力矩陀螺中应用

磁悬浮支承应用于控制力矩陀螺具有高精度，长寿命的优点。高速转子的陀螺效应导致的失稳制约了其在CMG中的应用，尤其是章动造成的磁悬浮转子高速失稳问题。该文分析了由于陀螺效应产生的章动造成系统失稳的根本原因，提出了控制系统的解决方案。研究结果表明，章动失稳的主要原因是系统的相位延迟造成的，尤其对数字控制系统，相位延迟更为严重，使用简单交叉解耦控制不能解决问题，需要对现有的控制器进行优化才能保证系统在高速下的稳定性。     

控制力矩陀螺用主动电磁轴承数字控制系统设计与实现

讨论了以TMS320VC33为核心的数字控制系统硬件结构。针对磁悬浮控制力矩陀螺转子的大惯量、小跨距、扁平转子和高速旋转时的陀螺效应，采用积分分离和不完全微分PID加交叉反馈控制策略。实验证明，该系统能够有效地抑制高速转子的陀螺效应，达到控制力矩陀螺电磁轴承高速稳定运行的要求。     

Dynamic analysis of a rigid-flexible inflatable space structure coupled with control moment gyroscopes

The vibration generated by the inflatable structure after deployment has a great impact on the performance of the payloads. In this paper, the influence of the control moment gyroscopes (CMGs) on the dynamic responses and characteristics of an inflatable space structure is studied, based on the flexible multibody dynamics in a combination of the absolute nodal coordinate formulation (ANCF) and the natural coordinate formulation (NCF). Firstly, the ANCF and NCF are used to accurately describe the large deformations and large overall motions of flexible inflatable tubes and rigid satellites, respectively. Then, instead of modeling gyroscopic flexible bodies, this paper pioneers a rigid body dynamic model of the CMG in detail by using the NCF modeling scheme, which can be attached to and coupled with any flexible bodies without any assumptions. Then, the orbital dynamic equations of the inflatable space structure coupled with distributed CMGs are obtained by considering the effects of Coriolis force, centrifugal force, and gravity gradient through coordinate transformation. The dynamic characteristics of the inflatable space structure are also analyzed by deriving the eigenvalue problem of a flexible multibody system. Finally, the accuracy of the CMG dynamic model is verified via a classic heavy top example. Several numerical examples are presented to study the influence of the magnitudes and directions of the rotor angular momentum of the CMGs on the dynamic responses and characteristics of the inflatable space structure.

     

A moderate deflection composite helicopter rotor blade model with an improved cross-sectional analysis

The compatibility between a composite beam cross-sectional analysis based on the variational asymptotic approach, and a helicopter rotor blade model which is part of a comprehensive rotorcraft analysis code is examined. It was found that the finite element cross-sectional analysis code VABS can be combined with a moderate deflection rotor blade model in spite of the differences between the formulations. The new YF/VABS rotor blade model accounts for arbitrary cross-sectional warping, in-plane stresses, and moderate deflections. The YF/VABS composite rotor blade model was validated against experimental data and various rotor blade analyses by examining displacements and stresses under static loads, as well as aeroelastic stability of a composite rotor blade in hover, and forward flight vibratory hubloads of a four bladed composite rotor.     

Dynamic stiffness characteristics of aero-engine elastic support structure and its effects on rotor systems: mechanism and numerical and experimental studies

The support structure of a rotor system is subject to vibration excitation,which results in the stiffness of the support structure varying with the excitation frequency(i.e., the dynamic stiffness). However, the dynamic stiffness and its effect mechanism have been rarely incorporated in open studies of the rotor system. Therefore, this study theoretically reveals the effect mechanism of dynamic stiffness on the rotor system. Then,the numerical study and experimental verification are conducted on...     

变转速共轴旋翼载荷建模及实验验证

对共轴双旋翼无人飞行器操纵结构的简化,会引起旋翼载荷变化更加复杂。共轴双旋翼转速控制方法有助于飞行控制系统的实现,但是在飞行控制律设计时,需要透彻了解变转速旋翼的气动载荷变化,建立精准的旋翼载荷模型。本文深入分析了旋翼变转速情况下单旋翼系统和共轴双旋翼系统的旋翼入流分布,建立了单旋翼变转速旋翼载荷计算方法,提出了共轴双旋翼变转速旋翼载荷计算方法。明确了低雷诺数对微型旋翼飞行器的旋翼载荷计算影响,引入雷诺数修正系数完成对旋翼翼型升阻系数气动参数的修正和验证,提高了变转速共轴双旋翼载荷模型的计算精度。设计了一套变转速单旋翼系统和共轴双旋翼系统的旋翼载荷测量实验装置,通过实验测试完成了对共轴双旋翼载荷计算方法的验证,表明了所提出的变转速共轴双旋翼载荷模型和实验测试装置是可信的。     

准三维旋转流体模型及其在部分充液转子稳定性分析中的应用

提了了一种简单的无粘旋转流体准三维模型,并给出了旋转流体对转子作用力的详细表达式,然后用该模型分析了部分充液刚性悬臂转子系统的稳定性,并与实验结果进行了比较,两者在定性上符合较好,准三维无粘流体模型与其它的无粘膜型一样也仅能用来分析无外阻尼或外阻尼较小的部分充液转子系统的稳定性问题。     

Subharmonic resonance of a symmetric ball bearing–rotor system

The performance of a ball bearing–rotor system is often limited by the occurrence of subharmonic resonance with considerable vibration and noise. In order to comprehend the inherent mechanism and the feature of the subharmonic resonance, a symmetrical rotor system supported by ball bearings is studied with numerical analysis and experiment in this paper. A 6DOF rotordynamic model which includes the non-linearity of ball bearings, Hertzian contact forces and bearing internal clearance, and the bending vibration of rotor is presented and an experimental rig is offered for the research of the subharmonic resonance of the ball bearing–rotor system. The dynamic response is investigated with the aid of orbit and amplitude spectrum, and the non-linear system stability is analyzed using the Floquet theory. All of the predicted results coincide well with the experimental data to validate the proposed model. Numerical and experimental results show that the resonance frequency is provoked when the speed is in the vicinity of twice synchroresonance frequency, while the rotor system loses stability through a period-doubling bifurcation and a period-2 motion i.e. subharmonic resonance occurs. It is found that the occurrence of subharmonic resonance is due to the together influence of the non-linear factors, Hertzian contact forces and internal clearance of ball bearings. The effect of unbalance load on subharmonic resonance of the rotor system is minor, which is different from that of the sliding bearing–rotor system. However, the moment of couple has an impact influence on the subharmonic resonances of the ball bearing–rotor system. The numerical and experimental results indicate that the subharmonic resonance caused by ball bearings is a noticeable issue in the optimum design and failure diagnosis of a high-speed rotary machinery.     

磁悬浮挠性转子系统模型复合辨识方法

针对磁悬浮挠性转子的纯有限元分析模型精度低的问题,提出一种磁悬浮挠性转子系统模型复合辨识方法。该方法首先采用有限元方法把磁悬浮挠性转子划分为多个Timoshenko梁单元,建立磁悬浮挠性转子系统模型,并对其挠性临界频率、阻尼、刚度和振型等关键参数进行分析,进而得到磁悬浮挠性转子的等效降阶数学模型;然后采用鲁棒自适应方法分析磁悬浮挠性转子系统的动态特性;最后,采用变LEVY方法从动态特性分析数据中对磁悬浮挠性转子进行系统辨识,校正有限元分析得到的降阶数学模型。实验结果表明,本方法可以得到磁悬浮挠性转子较为准确的系统模型。     

Nonlinear analysis of orbital motion of a rotor subject to leakage air flow through an interlocking seal

A nonlinear mathematical model for orbital motion of the rotor under the influence of leakage flow through a labyrinth seal was established in the present study. An interlocking seal was chosen for study. The rotor–seal system was modeled as a Jeffcot rotor subject to aerodynamic forcing induced by the leakage flow. Particular attention was placed on the serpentine flow path by spatially separating the aerodynamic force on the rotor surface into two parts, e.g., the seal clearance and the cavity volume. Spatio-temporal variation of the aerodynamic force on the rotor surface in the coverage of the seal clearance and the cavity volume was delineated by using the Muzynska model and perturbation analysis, respectively. The governing equation of rotor dynamics, which was incorporated with the aerodynamic force integrated over all seal clearances and cavity volumes, was solved by using the fourth-order Runge–Kutta method to obtain the orbit of the whirling rotor. Stability of the rotating rotor was inspected using the Liapunov first method. The results convincingly demonstrate that the destabilization speed of the rotor was reduced due to the aerodynamic force induced by the leakage flow through the interlocking seal. The nonlinear analysis method proposed in the present study is readily applied to dynamics of various rotor–seal systems with labyrinth seals.