DSP+FPGA结构的嵌入式图形处理设计

机载座舱显示系统已成为飞机综合化航电系统的一个重要组成部分,图形显示处理模块更是显示系统不可或缺的关键单元。分析了目前图形处理模块的设计方式,提出了一种基于DSP+FPGA结构的图形处理方法。并设计出了一款能够实现OpenGL函数接口标准的图形处理模块。模块具有算法处理效能高、可编程、应用可裁剪的特点。     

DIMA系统软件集成技术研究

本文针对分布式综合模块化系统中核心计算平台模块设计通用化、安装可替换以及功能可重构等要 求,研究系统软件集成技术和方法,提出了DIMA 系统中通用处理模块可互换性及功能可重构的解决方案,解 决了系统中通用处理模块资源有效利用和管理简易化的问题。     

基于TMS320DM642的视频处理模块的硬件设计

介绍了一种基于多媒体处理芯片TMS320DM642的视频处理模块的硬件设计方案,阐述了该模块的功能要求及硬件实现方法.模块的设计以TMS320DM642为核心处理器,充分利用了TMS320DM642的片上外设资源,综合构成了一套能够对一路网络视频进行解码,还能够同时对两路复合视频(PAL/NTFS/SECAM)进行编码的系统.模块支持业界流行的MPEG-4和H.264视频编解码标准.该设计方案为软件设计人员以及多种实际应用场合提供了一个通用的平台.     

基于PC/104总线和ADS7805的多路小信号实时监测系统

开发了基于PC/104总线和ADS7805的实时监测系统。该系统主要由信号转换模块、A/D转换模块、CPLD逻辑控制模块EPM7128和PC/104总线组成。它能够在板卡上实现信号的采集监测,并能通过PC/104总线与上位机通信,实现数据的存储、后端处理及显示。参考了实时数据采集处理系统的设计思想,重点阐述了系统原理及硬件、软件的设计。     

基于ADuC845的高温测温仪表研制

介绍了基于ADuC845的高温测温仪表的硬件组成和软件设计.本系统包括信号采集、信号处理、显示与键盘等组成模块,采用分段线性插值算法对高温曲线进行拟合.经过现场实验测试,该系统能够用于高温测试,工作状态稳定.     

搭建CAM系统与数控机床之间的桥梁

数控机床的复杂性与CAM系统的多样性和复杂性决定了后置处理在数控加工中的重要性.与众不同的后置处理技术和数控加工工艺的优化模块成就了ICAM技术公司在数控加工后置处理行业的领先地位.尤其在高端数控加工行业,更是举足轻重.     

基于.NET和XML的动态通用查询模块的设计与实现

传统查询模块由于代码固定,不能根据用户需求自由组合查询条件,缺乏健壮性等缺点,已经不能满足信息系统对查询项目不确定性的要求.在研究各类信息系统查询特点的基础上,提出一种新的动态通用查询模块应该具备的功能,查询关键字动态的由数据库确定,查询条件由用户自由组合,采用ASP.NET和C#作为主要开发工具,利用XML文件跨平台交换的特点进行查询参数传递,实现了该模块.最后对系统的异常处理进行了阐述.     

一种新型的分布式数据采集器(二)

4 系统结构和工作原理 900系列分布式数据采集系统由900系列数据采集模块、电源、通讯电缆、主机构成.可以在1.2 km的范围内,根据现场使用需要随意组成最少1个模块、20个测量点;最多不超过99个模块、1980个测量点(取决于模块)的测量系统.前端传感器输入信号可以是模拟信号(如温度、压力、电压、电流、应变等);也可以是数字信号(如开关状态监测、事件捕获、测频计数等).测量结果经模块内部A/D转换后,用RS485通讯方式,经屏蔽双绞线送至主计算机进行采集,并以固定的数据格式输出,用户可根据需要,采用相应的软件对采集到的信号进行处理.典型测量系统组成如图1所示.     

火星探测光学自主导航半物理仿真系统设计

针对火星探测中的捕获段和环火段,探讨火星探测光学自主导航半物理仿真系统的设计方案.研究了轨道动力学模型和光学相机导航系统图像处理方法,建立了自主导航算法模块的观测模型和输出显示模块的模型,利用Unscented卡尔曼滤波算法对探测器的位置和速度滤波.仿真结果表明,自主导航精度较高.     

基于VI的动态数据采集系统设计

在对某产品的测试过程中,首先要对多路信号进行测试并实施采集.因此,设计以动态数据采集模块PXI-3369及前端调理适配设备SH-1212为硬件平台,以虚拟仪器软件Lab VIEW为运行平台,开发了拥有参数配置模块、状态检测模块、标定系统模块、数据采集与信号输出模块、校准系统模块、数据处理模块的系统软件.通过应用,证明了该系统具有实用性、先进性、经济性和可靠性的特点.     

基于飞机油箱模型形状特征油量测量切片步长选择方法研究

 在分析飞机数字式油量测量过程中目前广泛使用的切片法油量测量原理的基础上,针对现有的定步长切片法无法得到准确、可靠的燃油质量特性数据库的缺陷,结合对飞机油箱模型形状特征的分析,提出了基于飞机油箱模型形状特征的油量测量切片步长选择方法。此方法包括切片步长整体和局部选择两个过程,整体选择以实现相邻两切片平面所夹油箱模型体积近似相等为目的来确定切片步长,以体现油箱模型截面整体变化规律;局部选择以设计切片平面与截面突变平面重合或尽可能接近的方式,突出油箱截面的局部变化特征。实验结果表明：该切片步长选择方法较定步长方法能够建立更为合理、可靠的燃油质量特性数据库,从而提高了油量测量精度。     

The effect of inlet conditions on the flow and heat transfer in multiple rotating cavity with axial throughflow

This paper discusses experimental results from two different build configurations of a heated multiple rotating cavity test rig.Measurements of heat transfer from the discs and tangential velocities are presented.The test rig is a 70% full scale version of a high pressure compressor stack of an axial gas turbine engine.Of particular interest are the internal cylindrical cavities formed by adjacent discs and the interaction of these with a central axial throughflow of cooling air.Tests were carried out for a range of non-dimensional parameters representative of high pressure compressor internal air system flows(Re up to 5×106 and Rez up to 2×105).Two different builds have been tested.The most significant difference between these two build configurations is the size of the annular gap between the(non-rotating) drive shaft and the bores of the discs.The heat transfer data were obtained from thermocouple measurements of surface temperature and a conduction solution method.The velocity measurements were made using a two component,LDA system.The heat transfer results from the discs show differences between the two builds.This is attributed to the wider annular gap allowing more of the throughflow to penetrate into the cavity.There are also significant differences between the radial distributions of tangential velocity in the two builds of the test rig.For the narrow annular gap,there is an increase of non-dimensional tangential velocity V/Ωr with radial location to solid body rotation V/Ωr=1.For the wider annular gap,the non-dimensional velocities show a decrease with radial location to solid body rotation.      

二维翼段颤振的μ控制

 采用超声电机作为作动器来实现含控制面的翼段颤振鲁棒抑制。针对作者设计的二维翼段颤振主动抑制系统，通过理论与实验相结合的方法，建立了考虑沉浮方向阻尼和作动器模型参数不确定性的控制系统模型，设计了μ控制器，并对控制器做了降阶处理。数值仿真和风洞试验表明，μ控制器可有效地抑制颤振的发生，将颤振临界速度提高23.4%。相对于H_∞控制器，μ控制器的控制效果和鲁棒性更好。     

Abnormal Shape Mould Winding

为解决网格化芯模的缠绕问题,本文提出了复合材料面片缠绕机理;接着详细分析了面片缠绕过程中的芯模凹曲面上纤维滑线和架空现象,应用微分几何曲面理论和空间几何理论,提出判据及其解决方案;最后,针对飞机发动机进气道的缠绕成型,编制缠绕控制程序并进行相应的实验,验证了面片缠绕方法的可行性。     

基于H∞性能指标的质量矩拦截弹鲁棒控制

 以所建立的质量矩拦截弹数学模型为基础，利用微分几何的反馈线性化理论，得到一个解耦线性系统，考虑到拦截弹的鲁棒性要求和3个滑块的协调控制问题，提出采用双回路的设计方法，内回路采用线性二次调节器（LQR），外回路采用考虑混合灵敏度问题的H_∞控制设计。仿真结果证明了该方法动态性能满足设计要求，同时对系统参数的不确定性具有较强的鲁棒性。     

航天器返回地球的气动特性综述

航天器返回地球的飞行过程中,气动特性是实现将宇宙飞行速度减到落地前速度、保证再入飞行得到有效控制以及再入防热安全可靠的关键因素。针对简单旋成体气动外形、半弹道式再入控制、烧蚀防热类返回航天器,综述了返回地球过程中变化的空气流域特性、航天器周围的气体绕流环境、空气与航天器作用产生的动力学与热效应等。系统地给出了该类航天器的再入气动特性参数与飞行性能的共性规律,包括:气动阻力与再入减速、气动升力与再入轨迹控制、配平攻角与飞行稳定性、气动加热与防热,以及再入过程中不同气动特性航天器、气象条件变化等对再入飞行性能的影响规律。为航天器开展返回飞行过程的跨流域气动性能工程研制提供设计参考。     

Research on Auto-detection for Remainder Particles of Aerospace Relay Based on Wavelet Analysis

Aerospace relay is one kind of electronic components which is used widely in national defense system and aerospace system. The existence of remainder particles induces the reliability declining, which has become a severe problem in the development of aerospace relay. Traditional particle impact noise detection (PIND) method for remainder detection is ineffective for small particles, due to its low precision and involvement of subjective factors. An auto-detection method for PIND output signals is proposed in this paper, which is based on direct wavelet de-noising (DWD), cross-correlation analysis (CCA) and homo-filtering (HF), the method enhances the affectiv-ity of PIND test about the small particles. In the end, some practical PIND output signals are analysed, and the validity of this new method is proved.     

Effects of Mo on the Microstructure and Hydrogen Sorption Properties of Ti-Mo Getters

The effects of Mo on the microstructure evolution, porosity and hydrogen sorption properties of Ti-Mo getters are investigated in this work. The results show that the addition of Mo prolongs the densification process of Ti-Mo getters and results in a significant amount of sintered pores. With the Mo content increasing, the porosity of getters firstly increases reaching the maximum value as it at- tains about 7.5wt.%, and then drops. At the room temperature, the hydrogen sorption property of getters increases progressively with the Mo content increasing, but the tendency is not very clear before its content lies below 2.5wt.%. When the Mo content achieves about 7.5wt.%, the hydrogen sorption property proves to be the best. The discussion is made about the above mentioned phenomena inclusive of hydrogen sorption properties of getters under different activation conditions (from 500-750 ℃).     

Preparation of Highly Dispersed Antimony-doped Tin Oxide Nano-powder via Ion-exchange Hydrolysis of SnCl4 and SbCl3 and Azeotropic Drying

Antimony-doped tin hydroxide colloid precipitates have been synthesized by hydrolysis of SnCl4 and SbCl3 using: (1) an ion-exchange hydrolysis to remove chlorine ions, and (2) isoamyl acetate as an azeotropic solvent to obviate water. The obtained dried powder is of high dispersivity without any need for further grinding. The size and dispersivity of the final particles are investigated with the aid of TG-DTA, BET, XRD and TEM. After having calcined, the antimony-doped tin oxide nanopowder possesses a tetragonal rutile structure with high dispersivity, uniform particles and low hard agglomeration.