可接入射频半实物的试验数据转换系统设计与实现

试验环节是产品研制生命周期中的重要环节,但是一直以来都缺乏有效的管理手段,在整个测试阶段都存在大量的人为的、重复性的工作,导致试验效率低下,为改善这一现状,提高试验效率,提出了一种基于PXIe数据采集系统,借助LabVIEW和DIAdem软件的测试系统解决方案：以LabVIEW控制数据高速同步采集,DIAdem调用LabVIEW模块执行算法分析,通过软件集成,实现对测试系统的全面管理,包括数据采集、数据检索、数据分析、报表生成及整个流程的自动化控制。本文以C919飞机电源测试系统为介绍对象,对该套测试系统解决方案进行阐述,实际测试情况表明,在数据吞吐率大于200M/S的情况下,相对传统测试方法,该测试方案在保证测试精度的基础上,极大的提高了试验效率,极大的提高了系统的可扩展性和可维护性。     

无模型自适应控制在飞机防滑刹车中的应用

针对飞机防滑刹车系统的复杂性和非线性,在分析滑移率控制式飞机防滑刹车系统的工作原理基础上,提出了一种基于无模型自适应控制的飞机防滑刹车控制算法;该算法无需精确的动力学模型,直接利用输入输出信息实现飞机防滑刹车的最佳滑移率控制;仿真结果表明:采用无模自适应防滑刹车控制算法,在5s之内就能获得稳定的滑移率,为提高飞机刹车的效率提供了一条新的思路。     

Feedback methods for inverse simulation of dynamic models for engineering systems applications

Inverse simulation is a form of inverse modelling in which computer simulation methods are used to find the time histories of input variables that, for a given model, match a set of required output responses. Conventional inverse simulation methods for dynamic models are computationally intensive and can present difficulties for high-speed applications. This article includes a review of established methods of inverse simulation, giving some emphasis on iterative techniques that were first developed for aeronautical applications. It goes on to discuss the application of a different approach that is based on feedback principles. This feedback method is suitable for a wide range of linear and non-linear dynamic models and involves two distinct stages. The first stage involves design of a feedback loop around the given simulation model, and in the second stage, that closed-loop system is used for inversion of the model. Issues of robustness within closed-loop systems used in inverse simulation are not significant as there are no plant uncertainties or external disturbances. Thus, the process is simpler than that required for the development of a control system of equivalent complexity. Engineering applications of this feedback approach to inverse simulation are described through case studies that put particular emphasis on non-linear and multi-input multi-output models.     

飞行器气动参数辨识进展

飞行器气动参数辨识研究的主题,是应用系统辨识技术从飞行试验数据求取气动力,从而建立飞行器动力学系统的数学模型.它研究的对象是飞行器;解决的是空气动力学问题;采用的基本方程是飞行动力学的运动方程组;应用的研究手段是现代控制论的滤波、预测和估计理论.它是处于空气动力学、飞行力学、弹性力学和现代控制论之间的应用性研究课题. 本文综述了国内外公开发表的飞行器参数辨识研究的理论结果和实践经验,分八个专题——模型辨识,参数估计,数据预处理和相容性检验,试验设计与最佳输入,弹性与非定常效应,频域辨识,闭环辨识,辨识准度与系统验证——评述其研究进展和现状.      

高超声速飞行器两类典型防热材料的性能表征与评价

针对高超声速飞行器翼前缘用超高温陶瓷材料及机身大面积金属热防护结构材料在高温环境下的力学响应分析与评价方法进行了全面的回顾和总结.综述了大面积金属热防护系统在传热、静力学、热力耦合性能、疲劳性能及抗冲击性能等方面国内外的研究进展;以及超高温陶瓷材料在热冲击、增韧机制、抗氧化性能等方面评价与表征技术,并结合国内研究状况展望了今后的发展方向.      

航空飞机计算机通信中滤波器的优化设计

航空飞机计算机通信系统进行通信的过程中,由于航空飞机上的电子设备相互之间的电磁干扰严重,导致信道中存在大量的干扰信号。提出基于小波变换算法的抗干扰滤波器设计方法。根据小波变换算法相关原理,综合航空飞机通信中特有的软阀值特点,利用自适应调整参数的方法得到高空通信中的最优小波系数阀值,使得高空噪声过滤阀值函数具有更强的适应性。利用新的阀值函数设计了新的滤波器,对行滤波模块和列滤波模块的设计进行了详细阐述。实验结果表明。利用设计的滤波器能够对航空飞机计算机通信过程中的干扰信号进行有效滤波,缩短了滤波时间,提高了高空通信系统的抗干扰能力。     

民用飞机关联性诊断技术研究

关联性诊断作为一种重要的故障诊断方法,对于缩短民机等复杂系统故障判定时间、减少故障损失、提高检修准确性、节约维修费用等,有着重大的理论意义和应用价值。本文介绍了民用飞机故障诊断技术的研究现状,在此基础上,提出并深入阐述了一种关联性诊断方法的原理与功能设计,并以风挡防冰系统为例进行验证。结果表明,根据原理分析所建立的系统模型,能够正确识别风挡防冰子系统故障,证明了该方法的有效性。     

基于像清晰化函数最优化的高速机载相机动态像质补偿技术

为满足高速飞行器对目标快速识别和打击的需求,针对大观测场高速机载光电探测系统像质退化严重、像质补偿元件机构复杂、像差校正实时性较差的问题,提出采用可变形反射镜作为动态像质补偿器对传统高速动态成像光学系统像质进行补偿和改进.利用基于像清晰化函数最优化的自适应光学动态像质补偿技术的优化算法对系统动态像差进行闭环实时校正,通过仿真对所提出的方法进行可行性分析和验证.仿真结果表明:与校正前相比,该校正方法使光学系统在60°大角度观测场内泽尼克动态像差变化量的峰谷值最大下降17.5%,点列图弥散斑均方根半径降低至10.61%,校正后的系统残余像差小,在整个观测场内,像质均接近光学衍射极限.     

Investigation of Different Condensation Regimes in Isobaric Turbulent Air-Steam Jets

Condensation in axisymmetric turbulent air-steam jets is studied theoretically and experimentally under bench experiment conditions in which a hot mist jet is injected from a nozzle into air. On the basis of the physico-mathematical model developed, four problems are considered: homogeneous condensation in the jet at a fairly low ambient air temperature, heterogeneous condensation on particles introduced into the jet at the nozzle outlet, heterogeneous condensation on particles ejected into the jet from the surrounding space, and condensation on ions entering the jet from a corona point on the flow axis. The local characteristics of the dispersed phase (mean particle size, standard deviation of the particle size, particle number and volume concentrations) and its integral characteristics (coefficient of vapor conversion into condensed phase and the optical thickness of the jet in different sections) are determined. The calculation results are compared with experimental data. As an application of the model developed, the characteristics of heterogeneous condensation in the jets of certain modern aircraft engines (IL-96-300, Tu-204, MiG-29, Boeing-707) are found on the assumption that the condensation occurs on particles entering the jet at the nozzle outlet and the particle growth rate in all stages (including the initial stage of particle irrigation) coincides with the growth rate of liquid drops.     

全机跨音速大迎角绕流的数值分析

应用有限体积法求解Ｅｕｌｅｒ方程计算了真实飞机外形的跨音速大迎角绕流流场及空气动力特性。本方法能自动捕获大后掠机翼前缘脱体涡，侧缘涡，机身体涡以及它们间的相互干扰。计算的机翼压力分布及全机气动力系数与实验值符合良好。表明了本文所采用的计算网格生成技术及流场计算方法是有效、可行的。