Sliding Mode Controller Design for Position and Speed Control of Flight Simulator Servo System with Large Friction

Flight simulator is an important device and a typical high-performance position and speed servo system used in the hardware-in-the-loop simulation of flight control system. Friction is the main nonlinear resistance in the flight simulator servo system, especially in a low-speed state. Based on the description of dynamic and static models of a nonlinear Stribeck friction model, this paper puts forward sliding mode controller to overcome the friction, whose stability is

THE EIGENVALUE SENSITIVITY ANALYSIS AND DESIGN FOR INTEGRATED FLIGHT/PROPULSION CONTROL SYSTEM

In this paper, sensitivity approaches are taken to analyze and design an integrated flight propulsion control system where the interaction between subsystems direitly affects the stability property and handling performances of the aircraft. The eigenvalue sen sitivity approach is employed to study the effect of coupling parameters on system stability and gain sensitivity approach is used to direct the reduced states feedback suboptimal control system design. Simulation results show that the integrated flight propulsion control system designed by sensitivity approaches is of good performance.

System Simulation Science and Simulation System Technology

This paper mainly discusses the following problems: the important meaning and special function of simulation system; the definition, contents and relationship of system and system simulation science; the definition and technology of simulation system and its equipments; and systematic description and exploration in relation to the developing trend of system simulation science and simulation system technology.

星载高精度偏振扫描仪热控设计与验证

偏振扫描仪安装于卫星对地板,周围有其他载荷的遮挡,热环境复杂,是卫星热控设计的难点。文章根据扫描仪不同部组件的控温要求设计热控方案,包括:主光学组件与框架隔热并包覆多层隔热组件;红外探测器热沉、头部电路盒分别设计独立的散热路径,通过外贴热管连接辅助散热板散热;结合电加热主动控温;在主要部位安装隔热垫。该热控方案已通过热平衡试验在地面的考核验证,在轨遥测数据显示:主光学组件温度控制在(16±1)℃,头部电路盒温度控制在6~8℃,红外探测器热沉温度控制在(-22±1)℃,满足扫描仪各项温度指标要求。以上表明该热控方案合理有效,对同类型光学载荷的热控设计及优化具有借鉴意义。

水下控制模块安装工具结构设计与对接精度分析

水下控制模块是水下生产系统的关键部件,针对水下控制模块在水下如何精准、高效、安全地实现回收和再安装工作的问题,本文设计了一种水下控制模块安装工具。对此安装工具进行了机械结构的设计,将安装工具各部分结构在工作过程中的作用进行了介绍。针对安装工具能够顺利完成水下控制模块的安装,基于安装工具各部分结构对接精度关系分析,通过数学建模与仿真分析,得到影响水下控制模块安装精度的原因,设计合理的安装精度参数。将仿真分析得到的数据与设计参数相比较,可证明水下控制模块的结构设计能满足水下控制模块的对接定位精度要求。结果表明:各精度参数满足水下控制模块安装工具设计要求,在此设计参数下安装工具能够完成水下控制模块的精确安装。

Modified robust optimal adaptive control for flight environment simulation system with heat transfer uncertainty

To solve the rapid transient control problem of Flight Environment Simulation System(FESS) of Altitude Ground Test Facilities(AGTF) with large heat transfer uncertainty and disturbance, a new adaptive control structure of modified robust optimal adaptive control is presented.The mathematic modeling of FESS is given and the influence of heat transfer is analyzed through energy view. To consider the influence of heat transfer in controller design, we introduce a matched uncertainty that represents heat transfer influence in the linearized system of FESS. Based on this linear system, we deduce the design of modified robust optimal adaptive control law in a general way. Meanwhile, the robust stability of the modified robust optimal adaptive control law is proved through using Lyapunov stability theory. Then, a typical aero-engine test condition with Mach Dash and Zoom-Climb is used to verify the effectiveness of the devised adaptive controller. The simulation results show that the designed controller has servo tracking and disturbance rejection performance under heat transfer uncertainty and disturbance;the relative steady-state and dynamic errors of pressure and temperature are both smaller than 1% and 0.2% respectively. Furthermore,the influence of the modification parameter c is analyzed through simulation. Finally, comparing with the standard ideal model reference adaptive controller, the modified robust optimal adaptive controller obviously provides better control performance than the ideal model reference adaptive controller does.

基于MBSE的民机飞行控制系统架构设计

基于模型的系统工程(model-based systems engineering,MBSE)已被广泛应用于复杂系统设计之中。通过构建功能、行为和结构之间的关系,提出一种基于MBSE的多层级递进式架构设计流程。随后,以高度控制需求为导向,对民机飞行控制系统进行了示例化建模。结果表明,基于MBSE的民机飞行控制系统多层级递进式架构设计能够充分发挥数字模型可重用的优势,保证需求与功能、逻辑和物理架构的紧密结合,提高系统设计的可追溯性,可为后续领域层阶段模型设计提架构参考。

基于AADL2SPN的飞行控制系统可靠性分析

飞行控制系统是典型的安全关键系统,其可靠性对保证飞机安全运行具有重要作用。传统的可靠性分析方法过于依赖分析人员的经验,主观性强,极易导致可靠性模型与设计模型之间存在不一致性。综合利用架构分析设计语言(AADL)和随机Petri网(SPN)描述系统的故障传播行为,提出一种基于模型的可靠性分析方法;利用AADL构建某横侧向电传飞控系统的名义模型和错误模型,提出AADL模型中错误传播相关信息的提取方法,利用所提取信息自动生成描述系统故障传播行为的SPN模型;在此基础上,通过蒙特卡洛仿真完成该横侧向电传飞控系统的可靠性评估。经与故障树分析方法对比,结果表明:最大相对误差小于0.018%,满足工程需要;所构建的可靠性模型由AADL模型自动生成,能够确保可靠性模型与设计模型的一致性,避免了对设计人员经验的依赖。

基于SIMULNK的单轴重型燃气轮机建模与仿真研究

通过面向对象的模块化建模方法,在MATLAB/SIMULINK软件中建立了燃气轮机部件模块库,并进行了燃气轮机系统变工况仿真研究。为了提高仿真精度,本文采用变比热容的计算方法,并考虑气体组分的变化对整个系统模型的影响,建立了一种考虑容积惯性和转动惯性的、非线性的单轴重型燃气轮机实时动态仿真模型。仿真结果表明,该模型设计合理、结构清晰,可应用于重型燃气轮机控制系统的研制和测试,并具有很好的通用性和扩展性。

飞控系统多元数据融合虚拟试验仿真模型验证

为提高飞控系统虚拟试验仿真模型的有效性与可信性,解决虚拟试验中多元冗余与强耦合数据的问题,提出了一种基于多元数据融合的仿真模型验证方法。首先,通过多元仿真数据融合,减少噪声和误差;其次,运用皮尔逊相关系数分析多元输出数据的相关性,并结合时域卷积神经网络-长短期记忆(TCN-LSTM)方法融合数据特征,深入挖掘数据的时空关联性;最后,通过概率分布分析评估仿真数据与参考数据的差异,转化为可信度等级,实现仿真模型的有效验证。实验结果表明,80%的输出数据达到仿真模型可信标准,其中有50%的输出数据达到完全可信标准,该方法显著提升了仿真模型的验证精度与可靠性。

基于FBS的汽车起重机远程操控系统人机交互设计研究

目的通过人机交互分析与FBS设计模型得出远程操控过程中的用户交互范式与原型设计,构建出远程操控系统的人机交互过程,形成起重机远程操控系统设计方案。方法首先,根据用户调研与实验对现有起重机操控系统中的人机交互特征进行分析和研究,构建起重机远程操控系统的人机交互模型;其次,结合功能需求与用户行为特征,结合FBS(功能-行为-结构)的设计分析方法得出起重机远程交互系统的结构组成,根据人机交互相关研究设计出具体的解决方案;最后,运用CreoManikin进行人机工程仿真分析验证。结论通过人机交互分析和FBS设计模型确定设计因素并进行方案设计,形成起重机远程操控系统设计方案,对工程机械远程操作系统产品的设计研发具有一定的理论研究意义与应用价值。

大型矿用电铲永磁外转子提升系统动力学特性研究

针对传统电铲提升系统存在传动效率低、能量损耗高、维护工作量大等问题,基于永磁外转子滚筒直接驱动提升装置,提出了一种电铲提升设计方案,并对永磁外转子提升系统的动力学特性进行了研究。首先,分析了电铲挖掘轨迹,建立了以时间为历程的挖掘轨迹函数表达式,确定了齿尖载荷、挖掘体积的计算方法,从而对挖掘过程中铲斗的受力进行了分析;然后,利用SolidWorks建立了电铲三维模型,将其导入SimulationX的CAD模块,建立了电铲多体动力学模型,并加载了外部载荷曲线以模拟铲斗挖掘过程中的受力情况;之后,将电铲多体动力学模型封装成MATLAB子系统,连接到Simulink的永磁外转子滚筒控制模块,采用了比例积分(PI)调节器和永磁同步电机(PMSM)矢量控制方法提高了滚筒的动态性能和抗扰动能力;最后,利用Simulink中的联合仿真模型对电铲挖掘过程进行了仿真分析,得到了提升力、推压力和电机功率等变化曲线。研究结果表明:与传统提升系统相比,永磁外转子滚筒提升系统节能降耗约27%,而电铲挖掘过程整体节能约18%,并在1∶30模拟样机试验台对提升推压力进行了对比验证。永磁外转子滚筒提升方案大大降低了挖掘能耗,为电铲绿色装备转型提供了参考。

基于MIKE模型的南沙区内涝模拟研究

基于广州市南沙区2022年的Landsat 8遥感影像数据,通过ENVI 5.3中监督分类方法,解译得到南沙区土地利用数据,通过构建二维地表淹没模型,模拟4种重现期(2年、10年、50年、100年一遇)暴雨条件下,研究区的洪涝淹没与易涝点分布情况。结果表明,该区域土地利用类型以透水区(养殖坑塘、水体、林地与耕地)为主,占研究区总面积的75.41%;当遭遇100年一遇暴雨影响时,会产生4个较为严重的积水区域,最大淹没水深超过1.6 m,易涝区域集中于长距离跨海大桥与沿海人工围垦区域。研究成果可为制定南沙区城市防洪策略提供参考。

Design,modeling,and control of morphing aircraft:A review

A morphing aircraft can adapt its configuration to suit different types of tasks,which is also an important requirement of Unmanned Aerial Vehicles(UAV).The successful development of an unmanned morphing aircraft involves three steps that determine its ability and intelligent:configuration design,dynamic modeling and flight control.This study conducts a comprehensive survey of morphing aircraft.First,the methods to design the configuration of a morphing aircraft are presented and analyzed.Then,the nonlinear dynamic characteristics and aerodynamic interference caused by a morphing wing are described.Subsequently,the dynamic modeling and flight control methods for solving the flight control problems are summarized with respect to these features.Finally,the general as well as special challenges ahead of the development of intelligent morphing aircraft are discussed.The findings can provide a theoretical and technical reference for designing future morphing aircraft or morphing-wing UAVs.

Control performance simulation and tests for Microgravity Active vibration Isolation System onboard the Tianzhou-1 cargo spacecraft

The Microgravity Active vibration Isolation System(MAIS),which was onboard China’s first cargo-spacecraft Tianzhou-1 launched on April 20,2017,aims to provide high-level microgravity at an order of 10^(-5)–10^(-6)g for specific scientific experiments.MAIS is mainly composed of a stator and a floater,and payloads are mounted on the floater.Sensing relative motion with respect to the stator fixed on the spacecraft,the floater is isolated from vibration on the stator via control forces and torques generated by electromagnetic actuators.This isolation results in a high-level microgravity environment.Before MAIS was launched into space,its control performance had been simulated on computers and tested by air-bearing platform levitation and aircraft parabolic flight.This article first presents an overview of the MAIS’s hardware system,particularly system structure,measurement sensors,and control actuators.Its system dynamics,state estimation,and control laws are then discussed,followed by the results of computer simulation and engineering tests,including the test of the six-degree-of-freedom motion by aircraft parabolic flight.Simulation and test results verify the accuracy of the control strategy design,effectiveness of the control algorithms,and performance of the entire control system,paving the way for operation of MAIS in space.This article also presents the steps recommended for the control performance simulation and tests of MAIS-like devices.These devices are expected to be used on China’s Space Station for various scientific experiments that require a high-level microgravity environment.

基于Simulink的风机主控测试系统

介绍了基于Matlab/Simulink环境下的风力发电机组主控系统硬件在环仿真测试系统设计及开发流程、风机结构动力学及空气动力模型的搭建方法以及测试系统软件的开发设置,并对整个测试系统的仿真测试精度进行比对验证。

Design and Application of Discrete Sliding Mode Control with RBF Network-based Switching Law

This article proposes a novel approach combining exponential-reaching-law-based equivalent control law with radial basis function (RBF) network-based switching law to strengthen the sliding mode control (SMC) tracking capacity for systems with uncertainties and disturbances. First, SMC discrete equivalent control law is designed on the basis of the nominal model of the system and the adaptive exponential reaching law, and subsequently, stability of the algorithm is analyzed. Second, RBF network is used to f...

面向正向开发的民用飞机飞控系统功能设计方法

功能设计是复杂系统设计开发中极其重要的任务,需要依靠正向开发方法来保障功能设计的正确性和完整性.为此,以民用飞机的飞行控制系统(飞控系统)为例,提出面向正向开发的功能设计方法.首先,借助系统建模语言建立飞机级到系统级再到部件级的功能需求关系模型;然后,按照SAE ARP4754A民用飞机系统开发指南中的安全性评估方法分析安全性需求,并结合功能需求构建飞控系统的功能知识集;最后,采用功能单元方块图和功能集成方块图对飞控系统进行功能建模.该方法对复杂系统的功能设计具有借鉴意义.

飞控液压系统故障诊断方法研究

飞控液压系统作为飞机控制系统的关键装备,一旦其发生故障将对飞机的运行安全造成严重影响。以飞控液压系统——飞机舱门液压驱动系统为研究对象,基于其系统结构和基本原理使用AMESim平台进行仿真建模,并通过故障仿真模拟开展故障诊断研究工作,提出了一种基于多级注意力机制的自编码器-多层感知机故障诊断方法,可以有效指导装备的维护维修工作并提高装备的运行安全性。首先,通过自编码器进行特征提取;然后,基于多级注意力机制进一步挖掘关键特征信息;最后,利用多层感知机作为分类器开展故障诊断工作。实验结果表明,与其他传统的机器学习和深度学习模型相比,所提方法的故障诊断准确率达到了97.5%且假正类率仅为1.1%,充分证明了所提方法的有效性。

考虑安全性的BWB民机飞行控制系统设计

翼身融合(BWB)飞行器满足未来民用航空经济、绿色、低碳的运行需求,是重要的发展方向。针对BWB飞行器的飞行控制系统,对其安全性与系统设计进行了研究。给出基于系统理论的事故模型及过程,与相应的安全性分析,重点对BWB飞行器飞行控制系统内的复杂逻辑关系、不安全控制动作、危害致因进行分析;进行切换系统设计,给出低可靠先进系统和高可靠备用系统的设计过程,并分析切换逻辑;基于设计进行仿真验证。研究结果表明:系统理论过程分析方法能够支持BWB飞行器飞行控制系统复杂逻辑关系的安全隐患分析,同时所设计的飞行控制系统具有一定的安全性与实用性。