惯性平台并联缓冲器复位精度的分析与综合

以一种用于惯性平台的并联缓冲器为研究对象，分析了其动平台位姿误差与各结构参数误差间的关系。首先，利用全微分理论建立了并联缓冲器的精度模型；然后，结合实际制造精度给定各结构参数误差的值，利用此模型估算出了缓冲器动平台的输出误差；最后，以尽量缩小各结构参数误差值的差异为附加约束条件，建立了精度综合的最优化模型，并根据惯性平台对精度的实际要求进行计算，结果表明：将动平台的复位精度控制在15?以内时，相应的结构参数制造公差应小于0.0134 mm。     

一种SINS/GNSS级联闭环反馈式组合导航系统的设计与研究

对于目前的级联式SINS／GNSS组合导航系统来说，其卡尔曼滤波器的输出校正方式不能深入到捷联解算内部，无法抑制平台姿态误差的发散，也无法校正惯性器件误差，因而在该方式长时间运行不能控制滤波发散，导舷精度随时间下降。为此设计了一种SINS／GNSS级联闭环反馈式组合导航系统，该系统能对SINS的位置、速度误差、平台误差及惯性器件误差作出最优估计并实施反馈。通过仿真证明：该系统不仅能提高导航解的精度，还在校准的同时具有动机座对准能力，满足了长时间导航定位的稳定性。     

火箭橇试验分离制导工具误差的有效性分析

火箭橇试验能在地面提供逼真的飞行环境,是制导系统可靠性检验与精度鉴定的有效手段,代表了未来制导系统测试的一个发展方向。利用火箭橇试验分离制导工具误差是制导系统精度鉴定的核心内容,对此进行了研究:给出了解析式平台制导系统的火箭橇试验方法;推导了制导工具误差系数分离模型;重点对火箭橇试验分离制导工具误差的有效性与精度进行了分析。结果表明,常规解析平台跟踪发射惯性坐标系的情况下,仅能有效辨识少数工具误差系数,系数辨识的精度很大程度上受制于外测精度;进一步分析表明其成因皆由火箭橇试验特性所致。最后给出了三种改善工具误差分离精度的途径。     

小型静电陀螺仪电极面积及电极装配误差研究

介绍了小型静电陀螺仪的电极支承结构和电极面积误差引起的干扰力矩的计算公式,并根据影响电极面积的各种因素推导出了电极面积的误差范围。根据装配误差产生干扰力矩的情况确定了最终的装配精度,为电极的设计提供了重要的参考依据。     

INS/CNS/GPS组合导航系统仿真研究

研究了INS／CNS／GPS组合导航系统的原理和特点，对组合导航系统进行了计算机仿真，提出了采用平台失准角、INS与GPS的位置之差和速度之差作为观测量的方法。采用卡尔曼滤波技术，可以估计出平台的失准角、惯性器件误差及导航参数误差。仿真结果表明：通过校正惯导平台、消除导航参数误差，可以大大提高了系统的导航精度。     

基于Simulink的高精度重力仪稳定平台水平误差仿真

给出陀螺稳定平台水平误差的数学模型，然后介绍了Simulink的稳定平台水平误差建模方法，并建立了系统的Simulink仿真图形模型，对稳定平台水平误差及其；引起的重力仪测量误差进行了仿真，并对仿真结果进行了分析。该仿真方法避免了求拉氏变换和拉氏反变换所带来的大量运算，不仅能保证误差分析的精度，而且使系统的误差分析过程变得容易、直观、迅捷。Simulink仿真表明，稳定平台不水平引起的重力仪测量误差为2．12mGal，远大于重力仪的设计误差0．5mGal。因此，必须补偿水平加速度引起的重力仪测量误差。     

SiC/Al技术延长惯性平台标定周期的理论研究

平台漂移误差测试和标定是保证惯性系统精度最基本的措施之一，应用于武器载体特别是战术弹时，要求尽量延长标定周期。在长期存储过程中，陀螺、加速度计等惯性元件测量轴的安装精度会因安装应力和自重应力作用而有损失，使平台漂移模型失真。理论分析表明，复合材料技术可大大减小此类误差，从而可通过长期保持惯导系统机械零位精度来延长平台标定周期。     

基于可观测性分析的方位旋转式惯导初始对准仿真研究

方位旋转式平台惯导系统(ARGINS)可以通过平台绕方位轴旋转抑制陀螺漂移和加速度计零偏,提高系统精度.平台旋转同样会影响系统静基座初始对准的精度.文中给出了ARGINS系统初始对准的误差方程和速度观测方程,应用分段定常系统可观测性分析理论和奇异值可观测度分析方法,定量地给出了ARGlNS系统状态的可观测度,并进行了ARGINS静基座初始对准过程的数字仿真和结果分析.结果表明:与固定指北式惯导系统相比,ARGIYS系统通过平台旋转提高了加速度计零偏和水平陀螺漂移的可观测度,可以应用卡尔曼滤波对系统的平台失准角和惯性元件误差进行估计并提高对准精度.     

离心机上辨识陀螺加速度计二次项系数的优化试验设计

提出了一种在带有反转平台的精密离心机上标定陀螺加速度计误差模型二次项系数K 2的D-最优试验方案。应用该D-最优试验方案,通过重复试验,能够在测试点最少的情况下获得高测试精度,实现陀螺加速度计误差模型系数的最优(D-最优的)辨识。推导了测量随机误差、试验方案的测试点、测试点的重复测试次数以及误差模型系数方差之间的关系式。精度分析的结果表明,应用D-最优试验方案,采取重复试验的方法,能够有效地减小二次项系数K的估计量的方差,从而提高K的辨识精度。     

半球谐振子装配倾角误差对频率裂解的影响分析

精密的装配工艺是保证半球谐振陀螺仪高精度性能的关键技术,研究装配误差对陀螺性能的影响可以为完善和优化工艺参数提供理论指导和依据。围绕装配过程中产生的偏心、倾斜误差对谐振子频率裂解的影响开展研究,建立了倾斜装配误差对谐振子频率裂解的影响数学模型。首先将谐振子唇沿与极板作为等效电容,建立装配倾角误差与等效电容之间的关系模型;然后基于等效电容两端电压与半球谐振子的静电力之间的数学模型,分析静电力不均匀对谐振子刚度的影响;最后建立数学模型分析了刚度扰动对频率裂解的影响。研究结果表明,对于直径30 mm的熔融石英半球谐振子,与基座的装配倾角误差为1角分时,由倾角误差引入的频率裂解为10-4 Hz量级。关于倾角误差对谐振子频率裂解的影响分析,为高精度半球谐振陀螺的精密装配工艺以及工艺参数配置奠定理论分析基础。     

基于动态神经元网络的激光陀螺输出误差模型

惯性敏感器误差补偿技术对提高武器装备的性能具有重要的意义,而误差补偿的关键在于误差模型的辨识。由于动态神经元网络是在前馈网络的节点引入前馈和反馈环节,理论上已证明其具有很强的动态逼近能力,可用来描述任意的非线性动态系统。根据惯性敏感器误差的动态特性,本探讨将动态神经元网络引入到激光陀螺误差建模中去,详细介绍了网络结构和对应的动态梯度算法。通过仿真算例说明,动态神经元网络在激光陀螺输出误差建模时具有一定的优点：网络收敛速度快、较好的跟踪性能、稳定性好。     

Stochastic Vibration Model of Gear Transmission Systems Considering Speed-Dependent Random Errors

A dynamic and stochastic simulation model is developed for analyzing the vibration of gear transmission systems with consideration of the influence of the time-variant stiffness, loads, and gear transmission errors. The gear transmission system is viewed as a non-linear, time-correlated and stationary stochastic system. The transmission errors of gears are decomposed into harmonic and random components based on the spectral analysis. To simulate the random component, a second order Markov process with time-variant parameters considering influence of rotational speed is proposed and the method to determine the model parameters based on the random error of measured gear transmission error is developed. A simulation system is developed. The input to the simulation system is a white Gaussian noise process and harmonic errors, and the output is the rotational vibration acceleration of gears. Experiments are carried out to verify the proposed model. The influences of the random error on vibration acceleration are examined using the developed simulation system.     

大型客机后缘襟翼操纵与非对称控制

针对大型客机后缘襟翼操纵与非对称控制的复杂结构及运动机构动力学仿真问题,通过零部件模态综合法建立刚柔混合多体动力学模型,替代传统的有限元法,综合考虑结构柔性、关节轴承摩擦、滑轮架摩擦、机翼盒段变形协调支持边界影响,实现了大型客机后缘襟翼在空中多状态/多工况载荷综合作用下的仿真分析．总体上看,仿真计算的各作动器驱动载荷变化规律与试飞结果一致,驱动载荷最大值误差小于10 %．受内襟翼靠近机身部分的翼面风洞测压数据及机身变形支持边界等不确定因素影响,初始启动和襟翼小偏度时各作动器操纵载荷仿真结果与试飞结果相对误差偏大．通过数值仿真,进行后缘襟翼单作动器脱开故障的非对称控制需求及其交联装置动态冲击过程分析,仿真结果表明内外襟翼交联装置可以有效减小后缘襟翼单作动器脱开故障非对称变形影响．     

Design of fractional robust adaptive intelligent controller for uncertain fractional-order chaotic systems based on active control technique

In this paper, a robust fractional-order adaptive intelligent controller is proposed for stabilization of uncertain fractional-order chaotic systems. The intelligent neuro-fuzzy network is used to estimate unknown dynamics of system, while the neuro-fuzzy network parameters as well as the upper bounds of the model uncertainties, disturbances and approximation errors are adaptively estimated via separate adaptive rules. An SMC scheme, with a fractional-order sliding surface, is employed, as the controller to improve the velocity and performance of the proposed control system and to eliminate the unknown but bounded uncertainties, external disturbances and approximation errors. The Lyapunov stability theorem has been also employed to show the stability of the closed-loop system, robustness against uncertainties, external disturbances and approximation errors, while the control signal remains bounded. Explanatory examples and simulation results are given to confirm the effectiveness of the proposed procedure, which consent well with the analytical results.     

Stabilized finite element formulation for incompressible flow on distorted meshes

Flow computations frequently require unfavourably meshes, as for example highly stretched elements in regions of boundary layers or distorted elements in deforming arbitrary Lagrangian Eulerian meshes. Thus, the performance of a flow solver on such meshes is of great interest. The behaviour of finite elements with residual‐based stabilization for incompressible Newtonian flow on distorted meshes is considered here. We investigate the influence of the stabilization terms on the results obtained on distorted meshes by a number of numerical studies. The effect of different element length definitions within the elemental stabilization parameter is considered. Further, different variants of residual‐based stabilization are compared indicating that dropping the second derivatives from the stabilization operator, i.e. using a streamline upwind Petrov–Galerkin type of formulation yields better results in a variety of cases. A comparison of the performance of linear and quadratic elements reveals further that the inconsistency of linear elements equipped with residual‐based stabilization introduces significant errors on distorted meshes, while quadratic elements are almost unaffected by moderate mesh distortion. Copyright © 2008 John Wiley & Sons, Ltd.     

On the accuracy of high-order discretizations for underresolved turbulence simulations

In this paper, we investigate the accuracy of a high-order discontinuous Galerkin discretization for the coarse resolution simulation of turbulent flow. We show that a low-order approximation exhibits unacceptable numerical discretization errors, whereas a naive application of high-order discretizations in those situations is often unstable due to aliasing. Thus, for high-order simulations of underresolved turbulence, proper stabilization is necessary for a successful computation. Two different mechanisms are chosen, and their impact on the accuracy of underresolved high-order computations of turbulent flows is investigated. Results of these approximations for the Taylor–Green Vortex problem are compared to direct numerical simulation results from literature. Our findings show that the superior discretization properties of high-order approximations are retained even for these coarsely resolved computations.     

小姿态导航平台射前快速自标定

为了实现某型导弹小姿态惯性导航平台射前自标定,分析并建立了精确实用的小姿态导航平台静态误差模型,设计了转动控制与测漂电路,充分利用射向条件和平台稳定性,实现导航平台在全装弹状态下自动转动、锁定和测漂,并以加速度计和陀螺输出作为开环观测量,结合误差模型分离出各误差系数。通过对各种误差进行综合仿真分析,得到标定系数的相对误差不超过4,其标定时间缩短为借助转台标定所需时间的40,满足了射前标定的精确性和快速性要求。方案在不改变现有装备的情况下,控制平台按照预设轨迹小角度旋转两次,仅分别在三个预设位置同时对三个陀螺进行测漂标定,适合实际导弹发射。     

Dynamic response analysis of an overhung rotor with interval uncertainties

Nonlinear Dynamics - Rotor system is an important part in rotating machineries. As a matter of fact, rotors are subject to uncertainties inevitably due to occasions such as assembling errors,...     

多体系统动力学方程违约修正的数值计算方法

多体系统动力学方程为微分代数方程,一般将其转化成常微分方程组进行数值计算,在数值积分的过程中约束方程的违约会逐渐增大.本文对具有完整、定常约束的多体系统,在修改的带乘子Lagrange正则形式的方程的基础上,根据Baumgarte提出的违约修正的方法,给出了一种多体系统微分代数方程违约修正法和系统的动力学方程的矩阵表达式.通过对曲柄-滑块机构的数值仿真,计算结果表明本文给出的方法在计算精度和计算效率上好于Baumgarte提出的两种违约修正的方法.     

The influence of errors in an interferogram analysis

In determining the influence of random errors in experimental measurement and data reduction, calculus may be applied to some problems where compounded error effects are encountered. However, for some processes it may be more convenient to apply a method of analysis described here which is based on computer simulation of errors, a variation of the so-called Monte Carlo technique. Interferometric moiré fringe patterns corresponding to in-plane displacement fields at 0, 45 and 90 deg, to the plane of the crack, taken from compact tension specimens, were analyzed to evaluate theJ-integral fracture parameter. Since theJ value for each load point was derived from over 100 separate measurements of fringe spacings, each with a significant probability of error, and it was desired to establish the magnitude of these errors on the final outcome, a Monte Carlo simulation of the analysis errors was performed. As a result of the simulation exercise, it could be concluded that the level of errors generated in the fringe-analysis procedure did not significantly affect the value ofJ obtained.