IMPROVED QUANTITATIVE FEEDBACK THEORY TECHNIQUE AND APPLICATION TO THREE-AXIS HYDRAULIC SIMULATOR

In order to meet tracking performance index of three-axis hydraulic simulator, based on classical quantitative feedback theory （QFT）, an improved QFT technique is used to synthesize controller of low gain and bandwidth. By choosing a special nominal plant, the improved method assigns relative magnitude and phase tracking error between system uncertainty and nominal control plant. Relative tracking error induced by system uncertainty is transformed into sensitivity problem and relative tracking error induced by nominal plant forms into a region on Nichols chart. The two constraints further form into a combined bound which is fit for magnitude and phase loop shaping. Because of leaving out pre-filter of classical QFT controller structure, tracking performance is enhanced greatly. Furthermore, a cascaded two-loop control strategy is proposed to heighten control effect. The improved technique＇s efficacy is validated by simulation and experiment results.

Numerical simulation of subsonic and transonic flow flieds and aerodynamic characteristics of anti-tank intelligent mine

Anti-tank intelligent mine is a kind of new intelligent anti-tank bomb relying on high precision detector.It can effectively capture and damage targets with wind resistance coefficient and other factors affecting its flight characteristics under consideration.This article is based on the three-dimensional model of intelligent mine.To analyze its subsonic and transonic flow fields and the change law of aerodynamic force factor with the growth of the angle of attack,computational fluid dynamics software is used for intelligent mine flow field numerical calculation and the change law of pressure center.The results show that the large drag coefficient is conducive to the stability of scanning.Drastic changes of the flow field near the intelligent mine will disable its scanning movement.The simulation results can provide a reference for scanning stability analysis,overall performance optimization and appearance improvement.

Torque Control Algorithm and Its Simulation of Capturing a Moving Target for Free Flying Space Robots

Torque control algorithm and its simulation of capturing a moving target for Free Flying Space Robots(FFSR) are discussed in this paper. The efficient recursive algorithm of joint driven torque for FFSR is developed. The torque control algorithm combined with Resolved Motion Rate Contro(RMRC) based on Generalized Jacobian Matrix(GJM) for capturing a moving target is proposed. The computer simulation verifies the effectiveness of the proposed algorithm.

Co-Simulation模式软硬件协同仿真体系结构及实现

介绍和对比了HDL Co-Simulation、Vector、Transaction三种主要的软硬件协同仿真模式的执行流程及性能,并对其中的Co-Simulation模式软硬件协同仿真方法进行了体系结构的设计和功能部件的划分,描述了各部分组件的主要功能,并通过软、硬件试验平台对其进行了建模和编程实现,测试了其仿真性能。通过实验表明,该体系结构能够适用于任何Co-Simulation以及Vector模式的软硬件协同仿真实验,并可在保留基奉框架的情况下,通过部分功能的扩充,满足Transaction模式软硬件协同仿真的需求。

Study on relative orbital configuration in satellite formation flying

In this paper, the relative orbital configurations of satellites in formation flying with non-perturbation and J2 perturbation are studied, and an orbital elements method is proposed to obtain the relative orbital configurations of satellites in formation. Firstly, under the condition of non-perturbation, we obtain many shapes of relative orbital configurations when the semi-major axes of satellites are equal. These shapes can be lines, ellipses or distorted closed curves. Secondly, on the basis of the analysis of J2 effect on relative orbital configurations, we find out that J2 effect can induce two kinds of changes of relative orbital configurations. They are distortion and drifting, respectively. In addition, when J2 perturbation is concerned, we also find that the semi-major axes of the leading and following satellites should not be the same exactly in order to decrease the J2 effect. The relationship of relative orbital elements and J2 effect is obtained through simulations. Finally, the minimum relation perturbation conditions are established in order to reduce the influence of the J2 effect. The results show that the minimum relation perturbation conditions can reduce the J2 effect significantly when the orbital element differences are small enough, and they can become rules for the design of satellite formation flying.

Novel approach for determining the optimal axial preload of a simulating rotary table spindle system

This paper presents a new theoretical model to determine the optimal axial preload of a spindle system, for challenging the traditional method which relies heavily on experience of engineers. The axial preloading stiffness was treated as the sum of the spindle modal stiffness and the framework elastic stiffness, based on a novel concept that magnitude of preloads can be controlled by measuring the resonant frequency of a spindle system. By employing an example of a certain type of aircraft simulating rotary table, the modal stiffness was measured on the Agilent 35670A Dynamic Signal Analyzer by experimental modal analysis. The equivalent elastic stiffness was simulated by both finite element analysis in ANSYS? and a curve fitting in MATLAB?. Results showed that the static preloading stiffness of the spindle was 7.2125×107 N/m, and that the optimal preloading force was 120.0848 N. Practical application proved the feasibility of our method.

Three-axis coupled flight control law design forflying wing aircraft using eigenstructure assignment method

Due to elimination of horizontal and vertical tails,flying wing aircraft has poor longitudinal and directional dynamic characteristics.In addition,flying wing aircraft uses drag rudders for yaw control,which tends to generate strong three-axis control coupling.To overcome these problems,a flight control law design method that couples the longitudinal axis with the lateraldirectional axes is proposed.First,the three-axis coupled control augmentation structure is specified.In the structure,a‘‘soft/hard"cross-connection method is developed for three-axis dynamic decoupling and longitudinal control response decoupling from the drag rudders;maneuvering turn angular rate estimation and subtraction are used in the yaw axis to improve the directional damping.Besides,feedforward control is adopted to improve the maneuverability and control decoupling performance.Then,detailed design methods for feedback and feedforward control parameters are established using eigenstructure assignment and model following technique.Finally,the proposed design method is evaluated and compared with conventional method by numeric simulations.The influences of control derivatives variation of drag rudders on the method are also analyzed.It is demonstrated that the method can effectively improve the dynamic characteristics of flying wing aircraft,especially the directional damping characteristics,and decouple the longitudinal responses from the drag rudders.

A study of PID and L1 adaptive control for automatic balancing of a spacecraft three-axis simulator

Purpose–The three-axis simulator relies on the air film between the air bearing and the bearing seat to achieve weightlessness and the frictionless motion condition,which is essential for simulating the micro-disturbance torque of a satellite in outer space.However,at the beginning of the experiment,the disturbance torque caused by the misalignment between the center of gravity of the simulator and the center of rotation of the bearing is the most important factor restricting the use of the space three-axis simulator.In order to solve this problem,it is necessary to set the balance adjustment system on the simulator to compensate the disturbance torque caused by the eccentricity.The paper aims to discuss these issues.Design/methodology/approach–In this paper,a study of L1 adaptive automatic balancing control method for micro satellite with motor without other actuators is proposed.L1 adaptive control algorithm adds the low-pass filter to the control law,which in a certain sense to reduce the high-frequency signal and speed up the response time of the controlled system.At the same time,by estimating the adaptive parameter uncertainty in object,the output error of the state predictor and the controlled object can be stabilized under Lyapunov condition,and the robustness of the system is also improved.The automatic balancing method of PID is also studied in this paper.Findings–Through this automatic balancing mechanism,the gravity disturbance torque can be effectively reduced down to 10−6 Nm,and the automatic balancing time can be controlled within 7 s.Originality/value–This paper introduces an automatic balancing mechanism.The experimental results show that the mechanism can greatly improve the convergence speed while guaranteeing the control accuracy,and ensuring the feasibility of the large angle maneuver of spacecraft three-axis simulator.

Three Dimensional Microstructure and Image-Based Simulation of a Fly Ash/Al Syntactic Foam Using X-ray Micro-Computed Tomography

An aluminum matrix syntactic foam, incorporated with hollow-structured fly ash particles, was fabricated by pressure infiltration technique. X-ray micro-computed tomography was used to characterize its heterogeneous microstructure three dimensionally （3D）. The quantification of some microstructure features, such as content and size distribution of hollow fly ash particles, was acquired in 3D. The tomographic data were exploited as a rapid method to generate a microstructurally accurate and robust 3D meshed model. The thermal transport behavior has been modeled using a commercial finite-element code to conduct steady state analyses. Simulation of the thermal conductivity showed good correlation with experimental result.

Experiment and Numerical Simulation on Axial Compressive Performance of Autoclaved Fly Ash Solid Brick Masonry Columns

To study the influence of slenderness on the axial compressive performance of autoclaved fly ash solid brick masonry columns, compression experiments were conducted on 12 samples of autoclaved fly ash solid brick masonry column and 4 samples of fired clay brick masonry column. The damage patterns and compressive performance were compared and analyzed. The experimental results indicate that the compressive bearing capacity decreases as slenderness increases from 3 to 18, and the compressive bearing capacity of the autoclaved fly ash solid brick masonry columns is lower than that of the fired clay brick masonry columns. The formulae for the axial compressive bearing capacity of autoclaved fly ash solid brick masonry columns were derived based on the experiments. The nonlinear FEA program ANSYS was adopted to simulate the behaviors of masonry columns. By comparing the simulation results and experimental results, it is shown that the simulation results agree well with the experimental ones. The rationality and applicability of the simulation results were verified.

Dynamic Optimization Algorithm for Flying Trajectory of a Free flying Space Robot

A new method of dynamic optimization for the flying trajectory of a free flying space robot based on its flying motion characteristics is presented. The continuous flying trajectory is broken into a number of segment and the control efforts and the duration of the segment are chosen as the optimization parameters. The objective function is made by using the weighted sum of the fuel used and the time spent, and the constraint equations are selected. Finally, the internal point punishment function method is adopted in the optimization program, and the results of computer simulation are given.

Simulation of Ash Deposition Behavior in an Entrained Flow Coal Gasifier

Fly ash deposition is an important phenomenon associated with ash/slag handling and discharge in the entrained-flow coal gasification process. Fouling and slagging inside the gasifier may cause reliability and safety problems because they can impose strong negative effects on the gasifier wall in the way of heat transfer and chemical corrosion. For these reasons, this study focuses on investigating the ash deposition distribution inside of a two-stage entrained-flow gasifier. The computational model is developed in order to simulate the gasification process with a focus on modeling ash formation, fly ash, and ash deposition. The Eulerian-Lagrangian approach is applied to solve the reactive thermal-flow field and particle trajectories with heterogeneous reactions. The governing equations include the Navier-Stokes equations, twelve species transport equations, and ten global chemical reactions consisting of three heterogeneous reactions and seven homogeneous reactions. The coal/ash particles are tracked with the Lagrangian method. The effects of different coal/ash injection schemes and different coal types on ash deposition have been investigated. The results show that the two-stage fuel feeding scheme could distribute the ash throughout a larger gasifier’s volume and, hence, could reduce the peak ash deposition rate and make the ash distribution more uniform inside the gasifier. Gasification of a high-ash coal results in a high ash deposition rate, low syngas higher heating value (HHV), and low carbon conversion rate. The result of ash deposition rate in this study can be used as a boundary condition to provide ash particle influx distribution for use in slagging models.

板坯连铸结晶器内凝固坯壳的三维数值模拟

基于流场和温度场的计算，对断面为1780 mm×225 mm 的板坯结晶器进行数值模拟，考虑3种不同水口条件下，钢液流动对凝固壳的冲刷，计算出凝固壳厚度的三维分布特征，并与二维切片法的计算结果进行了对比。结果表明：有水口时结晶器角部位置凝固壳最大值为约45 mm，宽面和窄面中心凝固厚度壳最大值为24 mm，分别比无水口条件下凝固壳薄1～2 mm；钢液的扩散会使凝固壳在距离结晶器角部300 mm和顶部400 mm的位置形成约深度2．5 mm的凹陷；同时钢液会冲刷整个结晶器窄面的凝固壳，在窄面中心最严重；对比不同的水口，凸底水口冲刷最大，凹底最小。

回采工作面瓦斯涌出量耦合预测模型研究

为准确、快速地预测回采工作面瓦斯涌出量,提出一种基于主成分分析法(PCA)和改进的果蝇算法(MFOA)优化支持向量机(SVM)的回采工作面绝对瓦斯涌出量预测模型。模型首先运用PCA方法对原始数据进行降维处理,消除数据冗余,而后采用改进的果蝇算法对SVM参数进行全局寻优,避免SVM参数的选取对模型预测结果的不利影响,最终建立基于PCA-MFOA-SVM的耦合预测模型,并以实际监测数据为例进行仿真预测。结果表明:该模型预测的平均绝对误差为0.077 5 m3/t,平均相对误差为1.323 7%,与其他模型相比,预测精度高,综合性能好,能够实现回采工作面瓦斯涌出量的动态预测。

调压阀流体空化特性仿真及影响因素分析

针对船用二级调压阀空化问题,建立流域瞬态仿真模型,结合Singhal空化模型和标准k-ε湍流模型对调压阀流体空化现象进行数值模拟,通过流场气体体积分数分析,得出了流体空化强度及分布形态的演变规律,通过流体速度场和压力场分析,阐明了空化演变过程调压阀流场特性,进而研究了开度、流量和背压对调压阀流体空化现象的影响规律。结果表明:在空化初生阶段,节流口处压力梯度大且流速高达69.89 m/s,形成冲击射流,在节流口和阀芯壁面处产生固定型空化;在空化发展阶段,壁面处空化强度增强,范围变大,局部气体体积分数可达80%以上;在空化溃灭阶段,固定型空化尾部受到湍流影响逐渐脱落,并向下游移动随后溃灭,局部气体体积分数逐渐降至0;调压阀开度或背压增大使得流体空化强度减弱且范围减小,流量增大致使流场空化强度增强且范围增大。

基于ANSYS的调节阀温度场分析与数值模拟

基于ANSYS有限元分析软件,采用热流耦合与单独温度场两种分析方法,对调节阀的温度场进行分析。结果表明,采用热流耦合方法,可以提高温度分析精度,但计算过程复杂。通过对调节阀温度场的数值模拟,提出了降低执行机构温度的有效途径。

基于CFD的发动机舱流场及温度场数值仿真

以内埋式通风口为研究对象,应用混合化网格,建立发动机短舱模型。采用SIMPLE算法,求解了流动和换热控制方程。对舱内流动和换热问题进行研究,得到了地面开车、地面滑行,以及不同高度、不同马赫数条件下动力装置舱内流场和温度场,解决了内埋式通风口进口流量无法测量的难题,为新型动力装置冷却通风系统的研究具有指导意义。

LF钢包流场数值模拟及应用

应用Fluent软件对某钢厂80 t精炼钢包流场进行数值模拟,分析了不同透气砖布置和不同氩气流量对钢包流场及钢液混匀效果的影响。结果表明,底吹氩钢包透气砖采用0.5R-0.67R-60°的布置方式可以减少卷渣,减少混匀时间。应用表明,改造后的钢包缩短钢液混匀时间10 s,软吹10 min后夹杂物总量减少1 800个(50个视场),明显提高了精炼效果。

面向SPARC V8的SOC软硬件协同仿真环境的设计与实现

SOC芯片的规模、复杂度和集成度日益增加,对其进行验证的复杂度和难度也在不断提高,使用软硬件协同仿真技术进行早期验证与开发,已成为SOC设计的一项重要的支撑技术.针对SPARC V8嵌入式处理器SOC设计的验证需求,利用ModelSim FLI接口及Windows虚拟设备驱动程序构建了一个仿真背板,设计实现了一个基于LEON2内核RTL级源代码和SPE-C集成调试环境的软硬件协同仿真环境,并通过LEON2处理器不同配置下的多种测试程序对该软硬件协同仿真环境的功能与性能进行了验证.

电磁阀内部流场数值模拟

在液体火箭发动机系统仿真过程中,对于控制发动机脉冲工作的电磁阀,其数学模型建立的准确性将对仿真结果产生很大的影响。本文采用商用CFD软件F luent,对某电磁阀分别进行了稳态流场和非稳态流场的数值计算。通过稳态流动模拟,得到了电磁阀出口的质量流量和阀门前后压降的关系式。通过非稳态流场的计算,得到了电磁阀出口的质量流量以及阀门前后压降随阀门关闭过程的变化情况,并对流量和压降的这种变化进行了分析。结果表明:使用F luent软件对阀门内部流场进行数值模拟,较好地反映了其工作状态,是建立电磁阀数学模型的基础。