数据采集系统动态准确度的一种评价方法

介绍了一种用于评价数据采集系统动态准确度的定义及测试方法，同时评价了其动态条件下的偏置误差、增益误差及模数转换有效位数，最终给出了一种数据采集系统的实际测试评价结果。     

HB 6448<飞机供电系统性能参数的数字式测试>的应用

结合对HB6448《飞机供电系统性能参数的数字式测试》贯彻中所出现的问题，阐述了该标准编制时曾研究和考虑过标准贯彻中应注意的几个问题以及一些数字式测试的概念和经验问题，诸如电气参数的采集方式、采样速率和采集点数，以及对这些采集数据的处理方法。了解和掌握上述问题，有助于保证测试结果的可信度和准确度。     

低通滤波器在数据采集系统中的应用

针对飞行训练模拟器数据采集系统中的噪声干扰问题,将低通滤波器应用于飞行训练模拟器的数据采集系统中,并详细介绍了该数据采集系统的工作过程。测试结果表明,低通滤波器的应用,可提高数据采集系统的采集精度和稳定性,增强系统的抗干扰能力。     

基于AD7714的激光对中仪的设计与实现

为了提高机械轴对中的效率和准确度,研制了基于AD7714的激光对中仪系统,该系统通过一定的测量手段对设备的定轴和动轴的相对位置进行检测和调整,以保证其位于同一条直线上。系统通过自行研制的硬件对任意角度的激光点的位置信息进行测量,并通过LabVIEW的图形化界面和编程环境对数据进行采集和处理,最后给出垂直偏差和水平偏差。     

军用飞机DSI数据采集系统的设计

由于军用飞机航空电子动态仿真与综合(DSI)系统所使用的固定采集周期的数据采集方法限定了采集速度,同时还影响到数据实时采集性能,针对该问题本文提出军用飞机DSI数据采集系统的设计方案.该方案的硬件结构基于MAX1308型AD转换器、DIO-144型采集卡,并设计了接口关系.系统的软件采用事件确认收发应答机制,并能确保在...     

基于PCI-6232和LabVIEW的发动机防喘振性能试验数据采集系统设计

介绍了一种基于图形化虚拟仪器编程软件LabVIEW 的防喘性能试验数据采集系统设计方案,并且详细论述了性能测试的实现方法。本系统以美国NI公司的数据采集卡PCI-6232为硬件平台,采用连续采集方式进行数据采集,并将数据存储到文本文件中。试验结果表明,该系统能够有效地完成对信号数据的采集和及时图形显示,并能够准确的产生脉冲输出信号。     

大数据分析方法在风洞试验中的应用

针对风洞常规试验采用阶梯抽样采集的方法,得到的试验数据和信息较少,导致试验数据分析和试验故障分析困难的问题,尝试在风洞常规试验中构建起风洞试验大数据的采集、收集和分析处理平台,并利用大数据较强的洞察能力,助力风洞试验中的疑难问题的分析。主要通过将风洞采集方法改为连续采集试验全程数据,开发杂混数据的通用风洞试验数据处理程序,开发海量试验数据分析显示软件等步骤,搭建起风洞试验大数据综合处理系统。并通过此平台对风洞试验大数据进行挖掘计算,使隐含的有用信息显现出来,为试验数据和试验故障深入分析指明方向。该平台在2m量级的高速风洞试验中的应用表明,此系统实现了风洞试验全程全部试验数据信息的采集,实现了风洞试验大数据的处理分析和结果展示。通过大数据分析有助于快速理清常规试验中的疑难问题。通过对风洞传统采集、处理方法的改进,实现了风洞试验从传统的阶梯抽样采集的小数据时代到采集全部试验数据信息的大数据时代的转变。从风洞试验大数据中获取的频率、概率、相关关系等数据可以为故障的定位分析、事件因果关系的分析等提供有力的数据支持。     

基于DSP的无线图像传输系统

介绍一种基于DSP的嵌入式无线图像压缩及无线传输系统的设计与实现方法.系统采用JPEG国际标准.下位机实现图像采集、压缩以及图像数据无线传输;上位机接收图像数据并完成与PC机的通信.通过DMA在图像采集、压缩及数据传输中的应用,提高了系统的运行效率.     

基于VXI总线的数据高速采集与记录的实现

介绍了使用E1432A数字化仪模块和N2216A磁盘存储模块组成的VXI总线测试系统实现数据高速采集与记录的途径，说明了使用E1432A实现数据高速采集和使用N2216A实现数据高速存储与记录的方法，给出了E1432A和N2216A编程的方法。     

基于智能传感器的浮空器数据采集系统研究及应用

实验浮空器囊体内部超热情况,研制了一套基于智能传感器的数据采集系统,介绍了系统组成和温度、压力传感器等硬件,详细描述了系统软件设计情况。相比于传统人工观察记录的方法,该数据采集系统可实现无人值守传感器数据采集与记录,大大提高了实验自动化水平,降低了实验人员劳动强度。     

STADAR: Servo Tester with Automatic Data Acquisition and Reduction

STADAR is a Servo Tester with Automatic Data Acquisition and Reduction developed for the Apollo program. This paper describes the operational capability of STADAR and discusses certain aspects of the design. STADAR evaluates system performance by supplying an input stimuli and two data acquisition and analysis channels. Stimuli (0.02-30 c/s 0-10 V peak) are automatically programmed to a frequency accuracy of ±0.01 percent and an amplitude accuracy of ± 0.1 percent. Data acquisition accuracy is 0.1 percent or 50 microvolts. System design utilizes programmable data filters to improve system S/N ratio. Active filter mechanization methods and results are presented as well as techniques for instantaneous precise generation of stimuli which are automatically programmed.     

发动机安装损失试验精确测温方法研究

直升机发动机装机后,一般都需进行安装损失的飞行试验,通过发动机进气温升与进气压损等数据的测量,利用发动机性能计算软件,分析装机状态下的发动机性能变化。UMA2000数据采集系统预设的蕈程相对于发动机温升的变化范围过宽,往往导致较大的测量误差,直接影响发动机安装损失的分析结论。通过在UMA2000数据采集系统引入偏置电压的方法,实现了发动机进气温升测量精度的大幅提高。     

无陀螺捷联惯导系统捷联方案研究

提出了无陀螺捷联惯导系统的惯性测量单元沿单轴相对载体旋转的捷联方案,对该方案进行了理论分析和数值仿真。结果表明,合理安装９ 个加速度计并适当选取捷联矩阵,则捷联方案无需高精度测量惯性测量单元相对载体旋转角速度也能大大提高载体角速度的精度。为满足相同的导航精度要求,本方案可降低对加速度计精度的要求约１０００ 倍。     

Microsatellite Laser Altimeter

A feasibility study is presented of a laser altimeter conceived as an auxiliary device of an imaging camera to perform stereo pairs correction by high accuracy range measurements. System configuration is compliant to microsatellite constraints and is integrated to a high-resolution imaging sensor. System performance analysis is carried out by means of analytical models and computer codes and plots are presented to select key parameters allowing definition of a preliminary laser altimeter configuration     

Next generation test support systems for the aircraft life cycle

The objective of this paper is to present the experience of EADS in using a common test support system for integration and qualification testing, aircraft ground equipment (AGE), in-service software maintenance facilities (ISMF) and ground crew training. EADS uses its test support system AIDASS (Advanced Integrated Data Acquisition and Stimulation System) in different phases of the aircraft life cycle. AIDASS is comprised of a real-time front-end system and a standard PC for the user interface. The EADS test support system is used in almost all phases of the aircraft life cycle, for instance, for integration and verification testing, as aircraft ground equipment, for in-service software maintenance and training of ground crews. This test support system is used for the software maintenance in the TORNADO program at different airforces in Europe. The airforces also share test setups with industry     

偏最小二乘回归在军用飞机价格预测中的应用

由于军用飞机性能要求的不断提高,影响飞机采购价格的费用驱动因子繁多,使得原有的价格预测模型已经不适用于现代军用飞机。分析了军用飞机采购价格样本数据少、费用驱动因子多的特点,考虑到偏最小二乘回归(PLSR)方法在处理小样本多元数据方面的优势,应用PLSR对军用飞机采购价格进行预测。PLSR首先提取第1、第2主成分对采购价格样本的特异点进行剔除;然后进行变量投影重要度分析以筛选费用驱动因子;最后,PLSR对费用驱动因子进行回归建立军用飞机价格预测模型。实例表明,在军用飞机价格预测方面,与原有的预测模型和逐步多元回归模型相比,应用PLSR预测的精度更高,更能体现采购价格与飞机性能参数之间的关系。     

多级轴流压气机不同工况下失速／喘振试验研究

通过试验的形式，开展了多级轴流压气机在静叶优化角度及中间级引气情况下的失速／喘振试验研究。采用高精度、高频响的动态压力传感器，高速同步采集板、快速A／D采集板和高速处理机相结合，借助于频谱分析的方法来找出失速／喘振频率，并且找出对应该频率的各通道之间的相位差，分析出失速／喘振首发级。利用DASP6．61数据大容量自动采集与信号处理系统对喘振信号进行数学处理。试验结果表明：测量手段及数学处理模型是可行的。在压气机静叶优化条件下，不同的引气量对失速／喘振有影响。     

Continuing challenges in lithium battery development

In these days of emphasizing standardization, Acquisition Reform, Non-Developed Items (NDI) and Commercial-Off-The-Shelf (COTS) technologies, we are facing new challenges associated with these trends. Program managers are pressured to use a standard or COTS battery, while simultaneously, the new systems being developed have increasingly complex and demanding power requirements. Hardware must be developed with shorter schedules, and policies of Acquisition Reform limit the amount of control the government has over the development of a given item. In this paper, we review battery development efforts that have resulted in unexpected problems. Relevant data from both current and past test programs are presented. Recommendations are provided concerning how to best avoid duplication of effort, while ensuring that the final product will have the best chances of succeeding     

THE CLUSTER DATA PROCESSING SYSTEM: A DISTRIBUTED SYSTEM IN SUPPORT OF A CHALLENGING SCIENTIFIC MISSION

The Cluster mission is aimed at the study of small-scale structures that are believed to be fundamental in determining the behaviour of key interactive processes of cosmic plasma. The mission will be controlled from the European Space Operations Centre (ESOC). ESOC is also in charge of the commanding of the scientific payloads on-board the four Cluster spacecraft after negotiation with the Cluster Principal Investigators (PIs) and of collecting and distributing the mission's scientific results to the Cluster community. This paper describes the process of translating the scientific requirements of the Cluster mission into a data-processing system supporting the mission via the definition of an appropriate operational scenario. In particular, the process of negotiation between the PIs and ESOC to command the spacecraft is mediated by the Joint Science Operations Centre (JSOC) and finalised by the Cluster Mission Planning System (CMPS) while the return of the data to the Cluster community is actuated by the Cluster Data Disposition System (CDDS). The Cluster Mission Control System (CMCS) provides the interface between these two systems and the spacecraft. These elements constitute the Cluster Data-Processing System (CDPS).